Adina Command Referece Manual

UTOMATIC

YNAMIC

NCREMENTAL

ONLINEAR

NALYSIS

ADINA User InterfaceCommand Reference Manual

Volume I:ADINA Solids & Structures Model Definition

Report ARD 09-2 May 2009

ADINA R&D, Inc.

ADINA User InterfaceCommand Reference Manual

Volume I:

ADINA Solids & Structures Model Definition

Report ARD 09-2

May 2009

for the ADINA System version 8.6

ADINA R & D, Inc.71 Elton Avenue

Watertown, MA 02472 USA

tel. (617) 926-5199telefax (617) 926-0238

www.adina.com

Notices

ADINA R & D, Inc. owns both this software program system and its documentation. Boththe program system and the documentation are copyrighted with all rights reserved by ADINAR & D, Inc.

The information contained in this document is subject to change without notice.

ADINA R & D, Inc. makes no warranty whatsoever, expressed or implied that the Programand its documentation including any modifications and updates are free from errors anddefects. In no event shall ADINA R & D, Inc. become liable to the User or any party for anyloss, including but not limited to, loss of time, money or goodwill, which may arise from theuse of the Program and its documentation including any modifications and updates.

Trademarks

ADINA is a registered trademark of K. J. Bathe / ADINA R & D, Inc.

All other product names are trademarks or registered trademarks of their respective owners.

Copyright Notice

© ADINA R & D, Inc. 1994 - 2009May 2009 PrintingPrinted in the USA

ADINA R & D, Inc. v

Table of contents

Table of contents

Chapter 1 Introduction .......................................................................................................... 1-11.1 Program execution ................................................................................................ 1-31.2 Command syntax ................................................................................................... 1-31.3 Input details .......................................................................................................... 1-61.4 Messages ............................................................................................................ 1-101.5 File input/output .................................................................................................. 1-111.6 The AUI database ................................................................................................ 1-111.7 Listings ................................................................................................................ 1-121.8 Units .................................................................................................................... 1-131.9 Tips for writing batch files ................................................................................... 1-131.10 Related documentation ........................................................................................ 1-13

Chapter 2 Quick index .......................................................................................................... 2-12.1 New commands, parameters and options ............................................................. 2-32.2 Quick overview of commands ............................................................................. 2-10

Chapter 3 Input/output .......................................................................................................... 3-13.1 Database operations ............................................................................................. 3-33.2 Analysis data files ................................................................................................ 3-93.3 External data ........................................................................................................ 3-123.4 Auxiliary files ....................................................................................................... 3-283.5 Program termination ............................................................................................. 3-363.6 Auxiliary commands ............................................................................................ 3-38

Chapter 4 Interface control and editing ............................................................................... 4-14.1 Settings ................................................................................................................. 4-34.2 Editing ................................................................................................................... 4-9

Chapter 5 Control data .......................................................................................................... 5-15.1 General .................................................................................................................. 5-35.2 Analysis details ................................................................................................... 5-225.3 Options ................................................................................................................ 5-355.4 Solver details ....................................................................................................... 5-535.5 Automatic control ................................................................................................ 5-575.6 Time-dependence ................................................................................................ 5-635.7 Iteration ............................................................................................................... 5-665.8 Tolerances ........................................................................................................... 5-745.9 Analysis output ................................................................................................... 5-785.10 Solution monitoring ........................................................................................... 5-100

v i AUI Command Reference Manual: Vol. I � ADINA Structures Model Definition

Table of contents

Chapter 6 Geometry definition ............................................................................................. 6-16.1 Coordinate systems .............................................................................................. 6-36.2 Points .................................................................................................................... 6-66.3 Lines ..................................................................................................................... 6-86.4 Surfaces ............................................................................................................... 6-356.5 Volumes ................................................................................................................ 6-506.6 Solid models ........................................................................................................ 6-636.7 Spatial functions .................................................................................................. 6-786.8 Transformations ................................................................................................... 6-856.9 Miscellaneous ..................................................................................................... 6-956.10 ADINA - M........................................................................................................ 6-102

Chapter 7 Model definition ................................................................................................... 7-17.1 Material models .................................................................................................... 7-37.2 Cross-Sections/Layers ...................................................................................... 7-1687.3 Element properties ............................................................................................. 7-1887.4 Substructures and cyclic symmetry .................................................................. 7-2257.5 Contact conditions ............................................................................................ 7-2387.6 Fracture mechanics ............................................................................................ 7-3107.7 Boundary conditions ......................................................................................... 7-3347.8 Loading .............................................................................................................. 7-3687.9 Initial conditions ................................................................................................ 7-4027.10 Systems ............................................................................................................. 7-414

Chapter 8 Finite element representation ............................................................................. 8-18.1 Element groups ..................................................................................................... 8-38.2 Mesh generation.................................................................................................. 8-588.3 Elements ............................................................................................................. 8-154

Chapter 9 Direct finite element data input ........................................................................... 9-19.1 Nodal data ............................................................................................................. 9-39.2 Element data ........................................................................................................ 9-149.3 Boundary conditions ........................................................................................... 9-549.4 Loads ................................................................................................................... 9-629.5 Initial conditions .................................................................................................. 9-759.6 Contact ................................................................................................................ 9-879.7 Fracture ................................................................................................................ 9-919.8 Substructures and cyclic symmetry .................................................................... 9-97

Command index ............................................................................................................... Index-1

Appendix 1 - Error messages ................................................................................................ A-1

Chapter 1

Introduction

ADINA R & D, Inc. 1-3

1. Introduction

This reference manual provides concise descriptions of the command input requirements forthe ADINA User Interface (AUI). This introduction serves to give some background informa-tion and indicate the general command syntax including descriptions of the conventionsused.

1.1 Program execution

Commands can be entered in the following modes:

Interactive

(a) AUI is running with the user interface displayed � you can enter commands into the userinterface command window.

(b) AUI is running in command mode (using the "-cmd" option) � you can enter commandsfrom standard input.

Batch

(a) AUI is running with the user interface displayed � you can read commands from a file bychoosing File→Open.

(b) Commands can be read from a given file using the aui startup options -s (UNIX versions)or -b (Windows version).

You can also read commands from a file using the READ command (see Section 3).

1.2 Command syntax

Here is the layout of a typical command reference page:

COMMAND[1] PARAM1 PARAM2[2]...

data1i data2i[3]...

General description of command function.[4]

Sec. 1.1 Program execution

1-4 AUI Command Reference Manual: Vol. I � ADINA Structures Model Definition

Chap. 1 Introduction

PARAM1 [<default>][6]

Description of parameter PARAM1[5]. {<input choices>}[7]

PARAM2 [<default>]Description of parameter PARAM2. {<input choices>}

...

data1i [<default>][6]

Description of data line entry data1i[5] (ith row, column 1). {<input choices>}[7]

data2i [<default>]Description of data line entry data2i (ith row, column 2). {<input choices>}

...

Auxiliary commands[8]

LIST COMMANDBrief description of this command.

DELETE COMMANDBrief description of this command.

Issuing a command allows you to alter the data associated with the command. This datacomprises the values associated with the command parameters and possibly a table, input via"data lines", associated with the command.

In the above, the command name "COMMAND"[1], given at the top of the reference page,has the first few characters emphasized to show the minimum number of characters requiredto be input to uniquely identify the command. A list of parameters[2] and data lines[3] for thecommand then follows. In this list the first few characters in the parameter and data linenames are emphasized to show the minimum number of characters required to uniquelyidentify the parameter and data line names.

Following a general outline of the command function[4], a description of the commandparameters and data line entries is given below the relevant keynames[5].

The parameters usually have default values[6] which are assumed if the parameter is notexplicitly specified. The default values are indicated in brackets [ ] � a bold value indicates adefault value (number or string) and an italicized string indicates the source of the defaultvalue, which is either (a) a text description of the default, (b) a parameter name from the same


command, or (c) a combination of command + parameter names, indicating that the default istaken from the setting of another (different) command parameter.

A parameter for which no default is provided means that there is no default � i.e., some choicemust be entered for that parameter.

One important parameter type is that of an entity identifier � for which the parameter keyname"NAME" is normally reserved. If the object identified by NAME has already been defined,then the other parameter defaults are set to the previous settings for that object. If a newNAME is given then the defaults, as indicated by the command reference pages herein, aretaken. In the former case, execution of the command redefines the named object.

The choice of parameter values is often discussed within the parameter description, but,where appropriate, a simple list of choices follows the parameter description[7]. For example,parameters with simple logical choices will have the list "{YES/NO}" appended to thedescription.

When a table is associated with the command, the command includes data input lines. Forsome commands, the table is initially empty, but for other commands the table alreadyincludes data lines.

The columns of a data line can be divided into two types: key columns and data columns.When a data line has key columns, the key value columns always precede the data valuecolumns. In this case the values of the key columns uniquely identify the data line, and,therefore, two data lines cannot have the same key column values � for such input, thesecond input data line overwrites the data associated with the key column values.

You can delete a data line by preceding the key column values with the DELETE prefix. Whena data line does not have key columns, two or more data lines can have the same values � butyou cannot use the DELETE prefix to delete data lines without key columns. However, youcan always delete all of the data lines of a table using the @CLEAR or CLEAR keywords.This is of course especially useful for those tables in which there are no key columns.

For data line input, not all the columns need be specified; the ENTRIES keyword, which canbe input as the first data line following the command line, can be used to select a subset ofthe data column entries (see below). Then the values you enter in the subsequent data linesare associated with the columns indicated by the ENTRIES parameters, the other datacolumns taking default values whenever possible. Note, however, that key columns arerequired input, and should thus be included in the ENTRIES column list.

Many commands have "auxiliary" commands[8] which are entered with one of the followingprefixes:

Sec. 1.2 Command syntax



LIST List object definitions.DELETE Delete objects from the database.UPDATE Update command defaults.RESET Reset command defaults.COPY Copy objects.SET Set "currently active" objects.SHOW Show "currently active" objects.

A LIST prefixed command has several forms:

LIST COMMAND List all object identifiers (names).

LIST COMMAND NAME List definition of object with identifier NAME.

LIST COMMAND FIRST LAST List definitions of a range of objects with integerlabel numbers. Parameters FIRST, LAST mayalso take the string values �FIRST�, �LAST�,�ALL�.

A DELETE prefixed command has the following forms:

DELETE COMMAND NAME Delete the object with identifier NAME.

DELETE COMMAND FIRST LAST Delete a set of objects with integer labelnumbers in the specified range.

Note that an object may not be deleted if another model entity depends on its existence aspart of its own definition. For example, a geometry line cannot be deleted if it forms a bound-ing edge of some geometry surface.

1.3 Input details

Command inputPlease refer to command AUTOMATIC LOAD-DISPLACEMENT in the following discussion(Section 5.5):

AUTOMATIC LOAD-DISPLACEMENT POINT DOF DISPLACEMENTALPHA DISPMAX CONTINUERPRINT TYPE NODE

When entering commands, only as many characters as necessary to uniquely specify thecommand name need be entered. The same rule applies to the parameters and data line entry


key names within a command. The minimum number of characters necessary are indicated inbold.

Note that command / parameter is case insensitive. All commands, parameters, values arestored in upper case, except for string variables (headings, graph legends, etc.).

Parameter values may be input in any order if the keynames are used, e.g.,

AUTOMATIC LOAD-DISPLACEMENT DOF=3 RPRINT=YES DISPMAX=5.0DISPLACEMENT=4.0 POINT=17

Some or all of the parameters can be excluded if the positional order of the parameters isobserved, e.g.,

AUTOMATIC LOAD-DISPLACEMENT 17 3 4.0, ,5.0, ,YES

(the parameters ALPHA and CONTINUE have been omitted by the use of the commas).

A mix of keyname parameters and positional input is allowed, e.g.,

AUTOMATIC LOAD-DISPLACEMENT 17 DISPLACEMENT=4.0 DOF=3,,5.0,,YES

The above uses of the AUTOMATIC LOAD-DISPLACEMENT command are all equivalent.The omitted parameters in each case take the default values.

Data linesMany commands require data line (tabular) input, e.g., MODAL-DAMPING (see Section 5.3):

MODAL-DAMPINGmodei factori

Use the ENTRIES keyword to select only the data columns that you want to enter (the otherdata columns will be given default values):

MODAL-DAMPINGENTRIES MODE FACTOR1 1.02 0.53 2.54 1.5DATAEND

Most commands which take this form of input also allow for incremental row generation via the"STEP inc TO" option where "inc" represents an increment in the generation, i.e., in the above

Sec. 1.3 Input details



example modei+k, modei+2k, ..., modej-k, are all generated, with the corresponding values for "factor"linearly interpolated between factori and factorj. When generating integer values, the differencebetween the first and last values must be an integer multiple of the STEP increment (i.e.,modulo((modej-modei),k) = 0). There is a default step increment, which for integer values isnormally 1; in this case "STEP 1 TO" may be input simply as "TO". Here are some examples:

MODAL-DAMPING1 5.5TO3 7.5@

or

MODAL-DAMPING1 5.5STEP 1 TO 3 7.5DATAEND

Both of these are equivalent to

MODAL-DAMPING1 5.52 6.53 7.5@

Note that data line input may be terminated either by entering the symbol "@" or the string"DATAEND" � data line input will be terminated automatically by input of the next command.

Data line rows can be deleted by preceding the key value by the prefix DELETE. This methodof deletion also supports row "generation" � i.e., "DELETE i STEP k TO j" may be used todelete a range of values.

All the data lines associated with a command may be deleted simultaneously using theCLEAR or @CLEAR keywords. This is useful when you want to define a table if you do notknow if the table is already defined or not:

TIMEFUNCTION 1CLEAR

which removes all the currently defined data lines of timefunction 1.

The columns for data line input can be selected by use of the keyword ENTRIES in the firstinput data line following the command line, e.g.,


COORDINATES POINTENTRIES NAME Y Z

which indicates that only global Y and Z coordinates are to be input for geometry points inthe subsequent data lines. The X coordinate assumes the default value 0.0, and thussubsequent data lines entered describe points in the global Y-Z plane.

NamesAUI names are usually of two types � alphanumeric strings of up to 30 characters or integerlabel numbers. Integer label numbers are normally greater than or equal to 1.

Integer valuesIntegers can be input with a maximum of 9 significant digits. For positive values, a preceding+ sign may, if desired, be input.

Real valuesSpecification of real values can include a decimal point and/or an exponent. The exponentmust be preceded by the letters E, e, D, or d, e.g.,

2E52.0d+05200000.

all refer to the same real number.

Alphanumeric valuesAlphanumeric values must start with a letter (A-Z, a-z) or number (0-9). The only permissiblecharacters allowed are the letters A-Z, a-z, the digits 0 to 9, the hyphen (-), and the underscore (_).Lower-case characters in an alphanumeric value are always converted to upper-case by the AUI.

String valuesA string should be enclosed by apostrophes ('). Any apostrophe within the string must beentered twice. Any character can be included in a string. Lower-case characters in a stringvalue are not converted to upper-case.

FilenamesA filename should be enclosed by apostrophes ('). Filenames can be up to 256 characterslong.

Length of input linesInput lines to the AUI can each contain up to 256 characters.

Line continuation, line separator, blanks, and commasIf the last non-blank character of a command or data line is a comma (,), then the command or

Sec. 1.3 Input details



data is continued on the next input line. The total length of an input line and all of itscontinuations can be up to 2000 characters.

A slash (/) in an input line can be used to end a command or data input line; more commandsor data can then be entered on the same input line.

A blank, several blanks, <Tab> characters, a comma, or a comma surrounded by blanks act asdelimiters. Commands, parameter keynames and values must be separated by delimiters.

CommentsComment lines can appear anywhere in the input and are identified by an asterisk (*) incolumn 1, e.g.,

* This is a comment line

Parameter substitutionYou can define parameters as numeric expressions, and use the parameter values in latercommands. This feature is useful when creating batch files used in structural optimization.For example:

PARAMETER A `5 + 7`PARAMETER B `2*$A`PARAMETER C `3 + $A + 4*$B`BODY BLOCK DX1=$A DX2=$B DX3=$C

1.4 Messages

Commands will often echo messages confirming their successful completion, or provide otherinformation. Otherwise you may get error/warning messages with varying levels of severity:

*** INPUT ERRORYou have entered an unacceptable parameter value or data. The command will notexecute with invalid input.

*** WARNINGThe command has completed, but has detected a possible inconsistency which may haveto be resolved.

*** ALERTThe command has completed, but has detected a definite modeling inconsistency whichhas to be resolved in order to create a valid model.

*** ERRORThe command has not completed.


*** INTERNAL ERRORThe program has determined some conflict in the database, normally indicating asoftware bug. You should contact ADINA R & D Inc. if you encounter such a message.In order to track down the source of the problem it would be most useful if the inputresponsible for this condition is made available to the support engineers.

*** MEMORY OVERFLOWThe command has not completed, due to the program running out of memory. Increse thememory allocation to the program

1.5 File input/output

The AUI uses several files for handling I/O. Here is a brief description of some of them,together with a suggested filename extension convention:

<file>.in ADINA-IN batch command input.<file>.idb ADINA-IN permanent database.<file>.plo ADINA-PLOT batch command input.<file>.pdb ADINA-PLOT permanent database.<file>.ses AUI session file (echo of command input).<file>.ps PostScript snapshot.<file>.dat Analysis data.<file>.por Analysis porthole.<file>.out Analysis printout.

1.6 The AUI database

The AUI uses an internal database to store and retrieve data used during program execution.The internal database is stored in main memory and, if main memory is not sufficient, a tempo-rary database file is created to hold the excess data. The internal database can be saved in adisk file, called a permanent database file, so that it can be retrieved in a future run.

Five commands are used to create, open and save databases. DATABASE NEW creates anew empty internal database. DATABASE OPEN initializes the internal database using aspecified permanent database file. DATABASE SAVE saves the internal database to disk,allowing you to specify the name of the database file. DATABASE ATTACH causes the AUIto use the specified permanent database file as the internal database. DATABASE DETACHrenames the internal database file as a permanent database file. All of these commands aredescribed in Section 3.1.

The permanent database file is similar to a text file used in a word processing program. Likethe text file, the permanent database file resides on disk and can be retrieved by the program

Sec. 1.5 File input/output



in a future run. The permanent database file can be saved on disk periodically duringprogram execution to protect against loss of data due to computer failure. During each saveoperation, a different permanent database file can be selected so that several versions of thedatabase are available for retrieval. (This is similar to saving several versions of a text file ondisk when working with a word processing program.) For the differences between DATABASEOPEN and DATABASE ATTACH, see the command description for DATABASE ATTACH. Forthe differences between DATABASE SAVE and DATABASE DETACH, see the commanddescription for DATABASE DETACH.

1.7 Listings

Many AUI commands generate lists. For example, the ZONELIST command (see The AUICommand Reference Manual, Volume IV) lists the values of variables. You can also specifywhether listings are to be sent to your terminal or to a disk file (see the FILELIST command).

When the listings are sent to your terminal, you are prompted by

--More--( %)

after each screen of the listing. The number printed before the percent sign represents thepercentage of the file that has been displayed so far. Responses to this prompt are asfollows:

<return> Display another line of the listing.<space bar> Display another screenful of the listing.<i><space bar> Display i more lines.D or d Display the next half-screen (a scroll) of the listing.<i>D or <i>d Set the number of lines in the scroll to i and display the next scroll.<i>Z or <i>z Set the number of lines in each screen to i and display the next screen.<i>S or <i>s Skip i lines and print a screenful of lines.<i>F or <i>f Skip i screenfuls and print a screenful of lines.<i>B or <i>b Skip back i screenfuls and print a screenful of lines.Q or q Stop the listing.= Print the current line number in the listing.. Repeat the last prompt response.

In these responses, <i> represents an optional integer argument, defaulting to 1. If you arefamiliar with the UNIX operating system, you will recognize that the above options corre-spond closely to the options of the 'more' command.


1.8 Units

In model definition no particular unit system is assumed. Any consistent unit system may beadopted. Certain thermodynamic constants do, however, have a choice of temperature unitsystem (Celsius/Centigrade/Kelvin, Fahrenheit/Rankine).

1.9 Tips for writing batch files

Increasing execution speed: The AUI contains features that are useful when you entercommands using the dialog boxes, but are not useful when you read commands from a batchfile. These features are activated by default. You can deactivate the features to increase thespeed at which batch files are processed, and to reduce the memory requirements of the AUI.The features are

Undo/redo storage:Command CONTROL UNDO=-1 turns off storage for undo/redo information.

Automatic model rebuilding:Command CONTROL AUTOMREBUILD=NO turns off automatic model rebuilding.

Session file creation:Command FILESESSION NO turns off creation of the session file.

Storage of session file information in the database:To turn off this feature, use the command CONTROL SESSIONSTORAGE=NO.

Stopping after an error or memory overflow is detected:Command CONTROL ERRORACTION=SKIP activate a feature that AUI skips theremaining commands in a batch file after an error or memory overflow is detected.

Summary:Use the following commands to perform all of the above actions:

FILESESSION NOCONTROL UNDO=-1 AUTOMREBUILD=NO SESSIONSTORAGE=NO,

ERRORACTION=SKIP

1.10 Related documentation

At the time of printing of this manual, the following documents are available with the ADINASystem:

Sec. 1.8 Units



Installation NotesDescribes the installation of the ADINA System on your computer.

ADINA User Interface Command Reference ManualVolume I: ADINA Solids & Structures Model Definition, Report ARD 09-2, April 2009Volume II: ADINA Heat Transfer Model Definition, Report ARD 09-3, April 2009Volume III: ADINA CFD Model Definition, Report ARD 09-4, April 2009Volume IV: Display Processing, Report ARD 09-5, April 2009These documents describe the AUI command language. You use the AUI commandlanguage to write batch files for the AUI.

ADINA User Interface Primer, Report ARD 09-6, April 2009Tutorial for the ADINA User Interface, presenting a sequence of worked examples whichprogressively instruct you how to effectively use the AUI.

Theory and Modeling GuideVolume I: ADINA Solids & Structures, Report ARD 09-7, April 2009Volume II: ADINA Heat Transfer, Report ARD 09-8, April 2009Volume III: ADINA CFD & FSI, Report ARD 09-9, April 2009Provides a concise summary and guide for the theoretical basis of the analysis programsADINA, ADINA-T, ADINA-F, ADINA-FSI and ADINA-TMC. The manuals also providereferences to other publications which contain further information, but the detail con-tained in the manuals is usually sufficient for effective understanding and use of theprograms.

ADINA Verification Manual, Report ARD 09-10, April 2009Presents solutions to problems which verify and demonstrate the usage of the ADINASystem. Input files for these problems are distributed along with the ADINA Systemprograms.

TRANSOR for I-DEAS Users Guide, Report ARD 09-15, April 2009Describes the interface between the ADINA System and I-deas®.

ADINA System 8.6 Release Notes, April 2009Provides a description of the new and modified features of the ADINA System 8.5.

You will also find the following book useful:

K. J. Bathe, Finite Element Procedures, Prentice Hall, Englewood Cliffs, NJ, 1996.Provides theoretical background to many of the solution techniques used in the ADINASystem.

This page is intentionally left blank

Chapter 2

Quick index

Quick index Chap. 2 Quick index


2.1 New commands, parameters and options

In version 8.6, the following new commands, parameters and options were added to Volume I of the AUI Command Reference Manual. The commands are listed in page number order.

Command Parameter Option/[Default] Page

LOAD-CLOUD 3-19

LOAD-STL 3-20

NASTRAN-ADINA DEFAULT Description change 3-23

MASTER TMC-MODEL HEAT 5-6

TMC-CONTROL

GAMMA, TEMP-CUTOFF, CUTOFF, TEMP-RELAX, HEAT-RELAX 5-18

TMC-CONTROL METHOD COMPOSITE 5-18

TMC-ITERATION TMCTOL, LINE-SEARCH 5-73

TOLERANCES ITERATION 5-76

PRINTNODES NODESETS 5-90

CONTACT-OUTPUT-NODES 5-92

SAVENODES NODESETS 5-95

MONITOR 5-100

MONITOR-CONTROL 5-102

LINE SECTION P1, P2 6-23

BODY-DSCADAP 6-76

BODY MID-SURFACE 6-119

MATERIAL MOHR-COULOMB

TEMPEFFECTS, ECC, ALPHA 7-38

MATERIAL NONLINEAR-ELASTIC NU, MATRIX 7-50

MATERIAL PLASTIC-CYCLIC 7-65

MATERIAL SMA TOLIL New default 7-75

MATERIAL USER-SUPPLIED NSUBD Description change 7-86

Chap. 2 Quick index Quick index

2-4 AUI Command Reference Manual: Vol. I − ADINA Structures Model Definition


MATERIAL USER-SUPPLIED

LENGTH3, LENGTH4, AUTOLEN, NONSYM, DENSITY 7-86

TMC-MATERIAL ISOTROPIC DENSITY 7-92

TMC-MATERIAL ORTHOTROPIC DENSITY 7-93

TMC-MATERIAL TEMPDEP-K DENSITY 7-94

TMC-MATERIAL TEMPDEP-C-ISOTROPIC DENSITY 7-95

TMC-MATERIAL TEMPDEP-C-ORTHOTROPIC DENSITY 7-96

TMC-MATERIAL TEMPDEP-C-K DENSITY 7-98

TMC-MATERIAL TIMEDEP-K DENSITY 7-99

PLCYCL-ISOTROPIC BILINEAR 7-107

PLCYCL-ISOTROPIC MULTILINEAR 7-108

PLCYCL-ISOTROPIC EXPONENTIAL 7-109

PLCYCL-ISOTROPIC MEMORY-EXPONENTIAL 7-110

PLCYCL-KINEMATIC ARMSTRONG-FREDRICK 7-111

PLCYCL-RUPTURE AEPS 7-112




CROSS-SECTION PROPERTIES

CTOFFSET, CSOFFSET, STINERTIA, SRINERTIA, TRINERTIA, WINERTIA, WRINERTIA, DRINERTIA 7-180

LINE-ELEMDATA TRUSS print(i), save(i) 7-188

CONTACT-3-SEARCH 7-307

FRACTURE

PRESSURE, TEMPERATURE, DYNAMIC 7-310

FRACTURE LVUS3, TECHNIQUE Description change 7-310

CRACK-PROPAGATION Description change 7-314

J-VIRTUAL-SHIFT POINT Description change 7-320

J-VIRTUAL-SHIFT LINE Description change 7-322

J-VIRTUAL-SHIFT SURFACE Description change 7-324

J-VIRTUAL-SHIFT RING Description change 7-325

J-VIRTUAL-SHIFT RING RING-TYPE

NODE, AUTOMATIC 7-325

R-CURVE Description change 7-329

USER-RUPURE 7-333

RIGIDLINK DOFSI 7-334

CONSTRAINT TRANSFORMATION 7-338

FIXITY dof(i) BEAM-WARP 7-347

C-PROP TBIRTH, TDEATH 7-391

R-PROP TBIRTH, TDEATH, SHAPE 7-392

APPLY-LOAD SHELLNODE 7-395




INITIAL-MAPPING ORDER 7-410

EGROUP TRUSS GAPWIDTH 8-3

EGROUP TWODSOLID RUPTURE-LABEL 8-6

EGROUP TWODSOLID FRACTURE, LVUS1, LVUS2 Description change 8-6

EGROUP THREEDSOLID RUPTURE-LABEL 8-12

EGROUP THREEDSOLID FRACTURE, LVUS1, LVUS2 Description change 8-12

EGROUP BEAM

TMC-MATERIAL, BOLT-NUMBER, BOLT-LOAD, WARP 8-19

EGROUP BEAM BOLTFORCE, BOLTNCUR Description change 8-19

EGROUP ISOBEAM TMC-MATERIAL 8-24

EGROUP SHELL TMC-MATERIAL, WTMC, RUPTURE-LABEL 8-33

EGROUP PIPE TMC-MATERIAL 8-40

EGROUP PIPE OVALIZATION, OPTION, BOLT-TOL Description change 8-40

EGROUP SPRING NONLINEAR MNO-G 8-45

BOLT-OPTIONS 8-56

BOLT-TABLE 8-57

GFACE NCOINCIDE SELECTED 8-122

GBODY NCOINCIDE SELECTED 8-128

GHEXA MINSIZE Description change 8-136

GHEXA SHIFTX, SHIFTY, SHIFTZ, MAX-REF 8-136

TRUSS-LINE Correction 8-160

NODESET OPTION

LINE-EDGE, SURFACE-FACE, CHAIN 9-10




NODESET ANGLE 9-10

BOUNDARIES pore(i), temperature(i), beam-warp(i) 9-54

RIGIDLINK-NODE 9-59

CRACK-PROPAGATION NODES Description change 9-91

J-VIRTUAL-SHIFT NODE Description change 9-92

J-VIRTUAL-SHIFT ELEMENT Description change 9-93

Updates from 8.6.1


REBAR-LINE NCOINCIDE 8-159

Updates from 8.6.2


MASTER MODEX RESULTS 5-6

CYCLIC-CONTROL BOUND-ELEMENT 7-228

CONTACT-CONTROL Description change 7-239

CGROUP CONTACT2 Description change 7-243

CGROUP CONTACT3 Description change 7-264

EGROUP TRUSS PRINT, SAVE, TBIRTH,TDEATH Omission inserted 8-3

EGROUP TWODSOLID

PRINT, SAVE, TBIRTH,TDEATH Omission inserted 8-6

EGROUP THREEDSOLID

PRINT, SAVE, TBIRTH,TDEATH Omission inserted 8-12




EGROUP BEAM PRINT, SAVE, TBIRTH,TDEATH Omission inserted 8-19

EGROUP ISOBEAM PRINT, SAVE, TBIRTH,TDEATH Omission inserted 8-24

EGROUP PLATE PRINT, SAVE, TBIRTH,TDEATH Omission inserted 8-29

EGROUP SHELL PRINT, SAVE, TBIRTH,TDEATH Omission inserted 8-33

EGROUP PIPE PRINT, SAVE, TBIRTH,TDEATH Omission inserted 8-40

EGROUP SPRING PRINT, SAVE, TBIRTH,TDEATH Omission inserted 8-45

EGROUP GENERAL PRINT, SAVE, Omission inserted 8-47

REBAR-LINE NCOINCIDE 8-159



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Chap. 2 Quick index

2.2 Quick overview of commands

The following is a quick overview of all AUI commands in Volume I of the AUI ReferenceManual and their functions. The commands are presented in the order in which they appear.

Chapter 3: Input/output

Section 3.1: Database operations

DATABASE NEW, creates a new database.DATABASE OPEN, creates a new database

using the specified permanent data-base file.

DATABASE WRITE, saves the currentinternal database as a permanentdatabase file.

DATABASE SAVE, saves the currentinternal database as a permanentdatabase file.

DATABASE ATTACH, allows access to thespecified file as an AUI database file.

DATABASE DETACH, creates a permanentdatabase file by detaching a workingcopy of the database file.

Section 3.2: Analysis data files

ADINA, initiates model validation and/orcreates an ADINA data file.

REBUILD-MODEL, forces the AUI torebuild the model.

Section 3.3: External data

LOADDXF, loads an AutoCAD® DXF fileinto the database.

LOADIGES, loads an IGES file into thedatabase.

LOADSOLID, loads Parasolid® part into thedatabase.

LOAD-CLOUD, reads in a point cloud file(depicting the boundary of an object)and writes out an STL file.

LOAD-STL, Loads an STL format file into the

AUI by creating a STL body.NASTRAN-ADINA, maps a NASTRAN®

data file into the database.EXPORT NASTRAN, exports an ADINA

model to a NASTRAN file.EXPORT UNIVERSAL, exports the mesh in

ADINA-AUI to an I-DEAS® universalfile format.

Section 3.4: Auxiliary files

READ, reads AUI input commands from thespecified file.

FILEREAD, controls the source of inputcommands to the AUI.

FILESESSION, controls the generation andoutput of a session file.

FILELIST, controls the format and output oflistings.

FILEECHO, controls the echoing of inputcommands.

FILELOG, controls the output of logmessages.

COMMANDFILE , creates a file of commandsto recreate the current model.

RTOFILE, defines the contents of a run-time-option file.

Section 3.5: Program termination

PAUSE, stops processing commands until akey is hit.

END, terminates the program.

Section 3.6: Auxiliary commands

PARAMETER, defines a parameter that canbe substituted in a later command.


Chap. 2 Quick index

Chapter 4: Interface control and editing

Section 4.1: Settings

CONTROL, defines certain parameters thatcontrol program behavior.

Section 4.2: Editing

UNDO, cancels the effects of previous com-mands.

REDO, cancels the effects of previousUNDO commands.

Chapter 5: Control data

Section 5.1: General

FEPROGRAM, specifies the finite elementanalysis program to be used to solvethe problem.

HEADING, specifies a title for the problemdescribed by the model database.

MASTER, defines the data controlling theexecution of the analysis programADINA.

DOF-ACTIVE, used to identify the activedegree of freedom (DOF) of reducedmodel.

TMC-CONTROL, controls the performanceof heat transfer analysis with ADINA.

Section 5.2: Analysis details

ANALYSIS DYNAMIC-DIRECT-INTEGRATION, specifies time integration

parameters for dynamic analysis.FREQUENCIES, specifies control data for a

frequency solution.BUCKLING-LOADS, specifies control data

for evaluating static buckling loads andcorresponding mode shapes.

ANALYSIS MODAL-TRANSIENT, pro-vides control data for a mode superposi -

tion analysis.ANALYSIS MODAL-PARTICIPATION-FACTORS, provides control data for a modal

participation factor analysis.ANALYSIS MODAL-STRESSES,

provides control data for modal stresscalculations.

Section 5.3: Options

KINEMATICS, defines the kinematicformulation.

MASS-MATRIX, selects the type of massmatrix to be used in dynamic analysis.

RAYLEIGH-DAMPING, specifies RayleighDamping coefficients.

MODAL-DAMPING, defines modal dampingfactors to be used in mode superposi-tion analysis.

FAILURE MAXSTRESS, defines a failurecriterion of type MAXSTRESS.

FAILURE MAXSTRAIN, defines a failurecriterion of type MAXSTRAIN.

FAILURE TSAI-HILL, defines a failurecriterion of type TSAI-HILL.

FAILURE TSAI-WU, defines a failurecriterion of type TSAI-WU.

FAILURE HASHIN, defines a failurecriterion of type HASHIN.

FAILURE USERSUPPLIED, defines a failurecriterion of type USERSUPPLIED.

TEMPERATURE-REFERENCE, definesreference temperatures and temperaturegradients for both initial conditions andthermal loads.

Section 5.4: Solver details

SOLVER ITERATIVE, defines control datafor the iterative solution of the matrixsystem of equilibrium equations.

PPROCESS, specifies the number of theprocessors used to split element groupsinto sub-groups.


Chap. 2 Quick index

TMC-SOLVER ITERATIVE, defines controldata for the iterative solution of thematrix system of equilibrium equationsfor heat transfer analysis.

Section 5.5: Automatic control

AUTOMATIC LOAD-DISPLACEMENT,defines parameters for an automaticload-displacement control (LDC)procedure.

AUTOMATIC TIME-STEPPING, definesparameters controlling the automatictime-stepping procedure.

AUTOMATIC TOTAL-LOAD-APPLICA-TION, controls the total-load-application

(TLA) procedure.

Section 5.6: Time dependence

TIMESTEP, defines a timestep sequencewhich controls the time/loadstepincrementation during analysis.

TIMEFUNCTION, defines a timefunction,which may be referenced, e.g., by anapplied load.

Section 5.7: Iteration

ITERATION, selects the equilibrium iterationscheme to be employed for a nonlinearanalysis.

STIFFNESS-STEPS, controls the outputtimesteps at which the effective stiffnessmatrix is reformed by the analysisprogram.

EQUILIBRIUM-STEPS, controls the outputtimesteps at which equilibrium iterationsare performed.

TMC-ITERATION, selects the equilibriumiteration scheme to be employed for aheat transfer analysis.

Section 5.8: Tolerances

TOLERANCES GEOMETRIC, specifiescertain geometric tolerances.

TOLERANCES ITERATION, specifies theconvergence criteria and correspondingtolerances controlling the equilibriumiteration scheme.

Section 5.9: Analysis output

PRINTOUT, controls the amount of outputprinted.

PRINT-STEPS, controls the outputtimesteps at which results are printed.

PORTHOLE, controls the saving of inputdata and solution results on the port-hole file.

NODESAVE-STEPS, controls the outputtimesteps at which nodal results aresaved in the porthole file.

ELEMSAVE-STEPS, controls the outputtimesteps at which element results aresaved on the porthole file.

PRINTNODES, selects nodes (defined by�blocks� or geometry entities) for whichsolution results shall be printed.

CONTACT-OUTPUT-NODES, select nodesfor output of contact results.

REACTION-NODES, selects nodes forprinting reaction forces.

SAVENODES, selects nodes (defined by�blocks� or geometry entities) for whichthe solution results shall be saved inthe porthole file.

DISK-STORAGE, indicates file storage andinput/output control.

Section 5.10: Solution monitoring

MONITOR, defines solution monitors totrack the change of variables duringsimulation.


Chap. 2 Quick index

MONITOR-CONTROL, control settings forthe solution monitoring feature.

Chapter 6: Geometry definition

Section 6.1: Coordinate systems

SYSTEM, defines a local coordinate system.

Section 6.2: Points

COORDINATES POINT, defines geometrypoint coordinates.

Section 6.3: Lines

LINE STRAIGHT, defines a straightgeometry line between two geometrypoints.

LINE ARC, defines a geometry line as acircular arc, or as an arc with varyingradius.

LINE CIRCLE, defines a circle geometryline.

LINE CURVILINEAR, defines a geometryline as a linearly interpolated curve in agiven local coordinate system.

KNOTS, defines a vector of �knot� valuesfor NURBS definition.

LINE POLYLINE, defines a geometry line asa polyline, i.e., a curve controlled by aseries of geometry points.

LINE SECTION, defines a geometry line tobe part of another geometry line.

LINE COMBINED, defines a geometry lineas a combination of other geometrylines.

LINE REVOLVED, defines a geometry line(a circular arc) by rotating a geometrypoint about an axis.

LINE EXTRUDED, defines a geometry lineby displacing a geometry point in agiven direction.

LINE TRANSFORMED, defines a geometryline to be a geometrical transformation

of another geometry line.SPLIT-LINE, creates two geometry lines of

type SECTION by �splitting� a givenline into two parts connected at somepoint on the given line.

LNTHICKNESS, defines line thicknesses(e.g., for defining axisymmetric shellthicknesses).

Section 6.4: Surfaces

SURFACE PATCH, defines a geometrysurface to be bounded by edges whichare specified geometry lines.

SURFACE VERTEX, defines a geometrysurface to be bounded by edges whichare specified by their end geometrypoints - the vertices of the surface.

SURFACE GRID, defines a geometrysurface as a grid (array) of geometrypoints, which control the shape of thesurface.

SURFACE EXTRUDED, defines a geometrysurface by displacing a geometry line ina given direction.

SURFACE REVOLVED, defines a geometrysurface by rotating a geometry lineabout some axis.

SURFACE TRANSFORMED, defines ageometry surface via a transformation ofanother surface.

SFTHICKNESS, defines surface thick-nesses.

CHECK-SURFACES, checks geometrysurface connections looking for twoadjoining surfaces which are oppositelyoriented, i.e., with opposite surfacenormals.

Section 6.5: Volumes

VOLUME PATCH, defines a geometryvolume to bebounded by faces whichare specified geometry surfaces.


Chap. 2 Quick index

VOLUME VERTEX, defines a geometryvolume in terms of the vertices.

VOLUME REVOLVED, defines a geometryvolume by rotating a geometry surfaceabout some axis.

VOLUME EXTRUDED, defines a geometryvolume by displacing a geometrysurface in a given direction.

VOLUME SWEEP, defines one or moregeometry volumes by sweeping one ormore geometry surfaces along a line.

VOLUME TRANSFORMED, defines ageometry volume to be a geometricaltransformation of another volume.

Section 6.6: Solid models

BODY SURFACES, defines a solid body viaa collection of oriented surfaces.

BODY VOLUMES, defines a solid body viaa collection of volumes.

FACE-THICKNESS, defines solid geometryface thicknesses.

FACELINK, establishes a link, for meshingpurpose, between two faces of distinctsolid models, or between a face of asolid model and a surface.

SPLIT-EDGE, splits an edge of a body intotwo edges by giving a parameter alongthe edge.

SPLIT-FACE, splits a face of a body into twofaces by giving two points on the face.

BODY-DISCREP, creates a �discreteboundary represenation� for a givenbody.

BODY-DEFEATURE, removes �small�features from the �discrete boundaryrepresenation� of a given body.

BODY-CLEANUP, removes �short�bodyedges and/or �thin� body faces from theAUI represenation� of a given body.

BODY-RESTORE, restores the AUI topo-logical representation of the body

corresponding to its state beforecommands such as BODY-CLEANUP,REM-EDGE or REM-FACE are executed.

BODY-DSCADAP, adapts (according to themesh densities set prior) the surfacetriangles that make up the geometry ofan STL body.

Section 6.7: Spatial functions

LINE-FUNCTION, describes the variation ofa quantity along a line.

SURFACE-FUNCTION, describes thevariation of a quantity over a surface.

VOLUME-FUNCTION, describes thevariation of a quantity within a volume.

Section 6.8: Transformations

TRANSFORMATION COMBINED,defines a general transformation as anordered sequence of existing transformations.

TRANSFORMATION DIRECT, defines ageneral 3-D transformation bydirectly specifying the transformationmatrix.

TRANSFORMATION POINTS, defines arigid-body 3-D transformation by thespecification of 6 geometry points, 3�initial� points and 3 �target�points.

TRANSFORMATION REFLECTION,defines a 3-D reflection (mirror) transformation.

TRANSFORMATION ROTATION, definesa 3-D rotation transformation.

TRANSFORMATION SCALE, defines a 3-D scaling transformation.

TRANSFORMATION TRANSLATION,defines a 3-D translation transformation.

TRANSFORMATION INVERSE, defines a3-D geometry transformation as theinverse of another transformation.


Chap. 2 Quick index

Section 6.9: Miscellaneous

DOMAIN, defines a geometry �domain�,which is a collection of geometryentities.

MEASURE, determines the distance betweentwo points or the length of an edge or aline.

GET-EDGE-FACES, lists the body facesconnected to a body edge.

GET-EDGE-POINTS, lists the AUI pointsbounding a body edge.

GET-FACE-EDGES, lists the body edgesbounding a body face.

REM-EDGE, removes a body edge bycollapsing one end point onto the other.

REM-FACE, removes a body face bycollapsing one bounding edge onto theother.

Section 6.10: ADINA - M

BODY BLEND, modifies specified edges ofa body to have �a radius� blend.

BODY BLOCK, defines a solid geometry or�brick�shape.

BODY CHAMFER, applies chamfers toedges of a solid body.

BODY CONE, defines a cone shape solidgeometry.

BODY CYLINDER, defines a cylinder shapesolid geometry.

BODY HOLLOW, hollows a solid geometrywith thickness THICKNESS.

BODY INTERSECT, modifies an existingsolid body by taking the intersection ofit with other, overlapping body.

BODY LOFTED, creates a sheet body bylofting through a set of lines or edgesand creates a solid body by loftingthrough a set of surfaces, faces, andsheet bodies.

BODY MERGE, modifies an existing solidbody by joining it with a set of othersolid bodies.

BODY MID-SURFACE, creates sheetbodies from a thin-walled solid body.

BODY OPTION, provides the options forADINA-M bodies.

BODY PARTITION, partition body with aset of faces of the body.

BODY PIPE, defines a pipe shape solidgeometry.

BODY PRISM, defines a prismatic shapesolid geometry.

BODY PROJECT, projects lines into a faceof the body.

BODY REVOLVED, creates a body byrevolving face of existing body aroundan axis.

BODY SECTION, partition solid bodyusing sheets.

BODY SEW, sews a set of sheet bodies intosewn bodies.

BODY SHEET, defines a sheet body by aset of geometry lines.

BODY SPHERE, defines a sphere shapesolid body.

BODY SUBTRACT, modifies an existingsolid body by removing from it a set ofother solid, overlapping bodies.

BODY SWEEP, creates a body by sweepingexisting face of a body in a givendirection or along a line.

BODY TORUS, defines a torus shape solidgeometry.

BODY TRANSFORMED, defines a solidgeometry by copying or moving anexisting ParasolidÒ body.

SHEET PLANE, defines a planar sheet usedfor partition of bodies.

VOLUME BODY, converts a body into ageometrical volume.

SURFACE FACE, converts a face of a bodyinto a geometric surface.


Chap. 2 Quick index

Chapter 7: Model definition

Section 7.1: Material models

MATERIAL ANAND, defines an Anandmaterial.

MATERIAL ARRUDA-BOYCE, defines anArruda-Boyce material model.

MATERIAL CAM-CLAY, defines a nonlin-ear Cam-Clay material model.

MATERIAL CONCRETE, defines a nonlin-ear concrete material model.

MATERIAL CREEP, defines a nonlinearcreep material.

MATERIAL CREEP-IRRADIATION,defines an irradiation creep material.

MATERIAL CREEP-VARIABLE, defines anonlinear creep material with variablecreep coefficients.

MATERIAL CURVE-DESCRIPTION,defines a nonlinear geological material,with the option of tension cut-off orcracking.

MATERIAL DRUCKER-PRAGER, defines anonlinear Drucker-Prager material modelwith a hardening cap and tensioncut-off.

MATERIAL ELASTIC, defines an isotropiclinear elastic material.

MATERIAL FLUID, defines a linear fluidmaterial.

MATERIAL GASKET, defines a gasketmaterial model.

MATERIAL GURSON-PLASTIC, defines anonlinear Gurson plastic material.

MATERIAL HYPERELASTIC, defines ahyperelastic material, which is incom-pressible nonlinear elastic, for rubber-like materials.

MATERIAL HYPER-FOAM, defines ahyper-foam material model.

MATERIAL ILYUSHIN, defines a nonlinearelastic-plastic material with the Ilyushinyield condition and isotropic hardening.

MATERIAL MOHR-COULOMB, defines anonlinear Mohr-Coulomb material.

MATERIAL MOONEY-RIVLIN, defines aMooney-Rivlin material, which isincompressible nonlinear elastic, forrubber materials.

MATERIAL MROZ-BILINEAR, defines anelastic-plastic material with Mroz yieldcriteria and bilinear hardening.

MATERIAL MULTILINEAR-PLASTIC-CREEP, defines a nonlinear thermo-elastic-

plastic-multilinear and creep material,with von Mises yield condition andisotropic, kinematic or mixed strainhardening.

MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE, defines a nonlinear

thermo-elastic-plastic-multilinear creepmaterial model with variable creepcoefficients.

MATERIAL NONLINEAR-ELASTIC,defines a nonlinear elastic material.

MATERIAL OGDEN, defines an Ogdenmaterial, which is incompressiblenonlinear elastic, for rubber materials.

MATERIAL ORTHOTROPIC, defines anorthotropic linear elastic material.

MATERIAL PLASTIC-BILINEAR,defines a bilinear elastic-plastic materialmodel with von Mises yield condition.

MATERIAL PLASTIC-CREEP, defines anonlinear thermo-elastic-plastic andcreep material, with von Mises yieldcondition and isotropic or kinematicstrain hardening.

MATERIAL PLASTIC-CREEP-VARIABLE,defines a nonlinear thermo-elastic-plastic creep material model withvariable creep coefficients.


Chap. 2 Quick index

MATERIAL PLASTIC-CYCLIC, defines aplastic-cyclic material.

MATERIAL PLASTIC-MULTILINEAR,defines a multilinear elastic-plasticmaterial model with von Mises yieldcondition.

MATERIAL PLASTIC-ORTHOTROPIC,defines a nonlinear orthotropic plasticmaterial.

MATERIAL SMA, defines a shape-memoryalloy material.

MATERIAL SUSSMAN-BATHE,defines a Sussman-Bathe materialmodel.

MATERIAL THERMO-ISOTROPIC,defines a nonlinear isotropicthermo-elastic material.

MATERIAL THERMO-ORTHOTROPIC,defines a nonlinear orthotropicthermo-elastic material.

MATERIAL THERMO-PLASTIC, defines anonlinear thermo-plastic material.

MATERIAL USER-SUPPLIED, defines auser-supplied material for use withADINA, with options for piezoelec-tric or consolidation analyses.

MATERIAL VISCOELASTIC, defines atime and teperature dependent vis-coelastic material model.

TMC-MATERIAL ISOTROPIC, defines aconstant isotropic conductivity and aconstant specific heat material for TMCanalysis.

TMC-MATERIAL ORTHOTROPIC, definesan orthotropic conductivity and constantspecific heat material for TMC analysis.

TMC-MATERIAL TEMPDEP-K, defines amaterial with temperature dependentconductivity and constant specific heatfor TMC analysis.

TMC-MATERIAL TEMPDEP-C-ISOTRO-PIC, defines a material with temperaturedependent specific heat and constant

isotropic conductivity for TMC analysis.TMC-MATERIAL TEMPDEP-C-ORTHOTROPIC, defines a material with

constant, orthotropic, conductivity andtemperature dependent specific heat forTMC analysis.

TMC-MATERIAL TEMPDEP-C-K, defines amaterial with temperature dependentspecific heat and conductivity for TMCanalysis.

TMC-MATERIAL TIMEDEP-K, defines amaterial with time dependent conductivityand constant specific heat for TMCanalysis.

CURVE-FITTING, defines a fitting curve forhyperelastic material models.

VISCOELASTIC CONSTANTS, definesviscoelastic contants for a viscoelasticmaterial model.

PHI-MODEL-COMPLETION, contrrolsparameters for phi model completionphase of potential-based fluid elements.

PLCYCL-ISOTROPIC BILINEAR, sets up aPLCYCL-ISOTROPIC definition of typebilinear.

PLCYCL-ISOTROPIC MULTILINEAR, setsup a PLCYCL-ISOTROPIC definition oftype multilinear.

PLCYCL-ISOTROPIC EXPONENTIAL,sets up a PLCYCL-ISOTROPIC definition of type exponential.

PLCYCL-ISOTROPIC MEMORY-EXPO-NENTIAL, sets up a PLCYCL-ISOTROPIC

definition of type memory-exponential.PLCYCL-KINEMATIC ARMSTRONG-FREDRICK, sets up a PLCYCL-KINEMATIC

definition of type Armstrong-Fredrick.PLCYCL-RUPTURE AEPS, sets up a

PLCYCL-RUPTURE definition of typeAEPS (accumulated effective plasticstrain).

RUBBER-TABLE MOONEY-RIVLIN,defines a rubber-table data set of typeMooney-Rivlin.


Chap. 2 Quick index

RUBBER-TABLE OGDEN, defines arubber-table data set of type Ogden.

RUBBER-TABLE ARRUDA-BOYCE,defines a rubber-table data set of typeArruda-Boyce.

RUBBER-TABLE HYPER-FOAM, defines arubber-table data set of type hyper-foam.

RUBBER-TABLE SUSSMAN-BATHE defines a rubber-table data set of typeSussman-Bathe.

RUBBER-TABLE TRS, defines arubber-table data set of type TRS(thermorheologically simple).

RUBBER-MULLINS OGDEN-ROXBURGH,defines a data set of type rubber-Mullins, subtype Ogden-Roxburgh.

RUBBER-VISCOELASTIC HOLZAPFEL,defines a data set of type rubber-viscoelastic, subtype Holzapfel.

RUBBER-ORTHOTROPIC HOLZAPFEL,defines a data set of type rubber-orthotropic, subtype Holzapfel.

COEFFICIENTS-TABLE, defines aneffective stress vs. creep coeffientstable.

CREEP-COEFFICIENTS LUBBY2, definesthe dependency of creep law coeffi-cients on temperature.

CREEP-COEFFICIENTS MULTILINEAR,defines the temperature and depen-dence of stress creep coefficients.

CREEP-COEFFICIENTS TEMPERATURE-ONLY, defines the dependency of creep law

coefficients on temperature.CREEP-COEFFICIENTS USER-SUPPLIED,

Defines a user supplied creep coefficientdependence function.

CURVATURE-MOMENT, defines a curvaturevs. moment curve.

FTABLE, defines a modulus vs. decaycoefficient table for MATERIALVISCOELASTIC.

FORCE-STRAIN, defines a force vs. straincurve.

IRRADIATION-CREEP-TABLE, defines anirradiation creep table.

MOMENT-CURVATURE-FORCE, defines amoment-curvature-force property forBEAM elements.

MOMENT-TWIST-FORCE, defines amoment-twist-force property for BEAMelements.

NEUTRON-DOSE, defines a neutronfluence.

NEUTRON-TABLE, defines a neutronfluence table.

PORE-FLUID-PROPERTY, defines proper-ties of a pore fluid.

PROPERTY NONLINEAR-C, defines anonlinear relationship between dampingand velocity.

PROPERTY NONLINEAR-K, defines anonlinear relationship between forceand relative displacement.

PROPERTY NONLINEAR-M, defines atime-dependent mass property.

PROPERTYSET, defines stiffness, mass,damping, and stress transformationproperties for SPRING elements.

RIGIDITY-MOMENT-CURVATURENONLINEAR-ELASTIC, defines a nonlin-

ear-elastic rigidity property.RIGIDITY-MOMENT-CURVATUREPLASTIC-MULTILINEAR, defines a plastic-

multilinear rigidity property.RUPTURE MULTILINEAR, defines a

rupture criterion in terms of multilineartemperature-dependent curves.

RUPTURE THREE-PARAMETER, defines athree-parameter law rupture criterion.

RUPTURE-CURVE, defines a rupture-strainvs. stress curve.

SCURVE, defines a stress-strain curve whichcan be referenced by a material model.


Chap. 2 Quick index

SSCURVE, defines a stress-strain1-2 curvewhich can be referenced by a materialmodel.

LCURVE, defines a loading-unloading curvewhich can be referenced by the gasketmaterial model.

STRAINRATE-FIT, defines a strainrate-fitfor the curve fitting of strainratematerial parameters.

TWIST-MOMENT, defines a twist vs.moment curve.

Section 7.2: Cross-sections/layers

CROSS-SECTION BOX, defines a boxcross-section.

CROSS-SECTION I, defines an I-beamcross-section.

CROSS-SECTION L, defines an L-beamcross-section.

CROSS-SECTION PIPE, defines a pipecross-section.

CROSS-SECTION RECTANGULAR,defines a rectangular cross-section.

CROSS-SECTION U, defines a U-beamcross-section.

CROSS-SECTION PROPERTIES, defines ageneral cross-section in terms ofprincipal moments of inertia and areas.

LAYER, defines the control parameters ofeach surface layer (for multi-layer shellelements).

PLY-DATA, defines the layer thickness for afiber-matrix composite.

Section 7.3: Element properties

LINE-ELEMDATA TRUSS, assigns data forTRUSS elements to geometry lines.

EDGE-ELEMDATA TRUSS, assigns data forTRUSS elements on edges.

SURF-ELEMDATA TWODSOLID, assignsdata for TWODSOLID elements togeometry surfaces.

FACE-ELEMDATA TWODSOLID, assignsdata for TWODSOLID elements onfaces.

VOL-ELEMDATA THREEDSOLID, assignsdata for THREEDSOLIDelements ingeometry volumes.

BODY-ELEMDATA THREEDSOLID,assigns data for THREEDSOLIDelements in bodies.

LINE-ELEMDATA BEAM , assigns data forBEAM elements to geometry lines.

EDGE-ELEMDATA BEAM, assigns data forBEAM elements on edges.

LINE-ELEMDATA ISOBEAM, assigns datafor ISOBEAM elements to geometrylines.

EDGE-ELEMDATA ISOBEAM, assigns datafor ISOBEAM elements on edges.

SURF-ELEMDATA PLATE, assigns data forPLATE elements to geometry surfaces.

FACE-ELEMDATA PLATE, assigns data forPLATE elements on faces.

SURF-ELEMDATA SHELL, assigns data forSHELL elements to geometry surfaces.

FACE-ELEMDATA SHELL, assigns data forSHELL elements on faces.

ELAYER, assigns material to individualelement on diffferent layers for shellelement.

LINE-ELEMDATA PIPE, assigns data forPIPE elements to geometry lines.

EDGE-ELEMDATA PIPE, assigns data forPIPE elements on edges.

LINE-ELEMDATA GENERAL, assigns datafor GENERAL elements on lines.

EDGE-ELEMDATA GENERAL, assigns datafor GENERAL elements on edges.

SURF-ELEMDATA GENERAL, assigns datafor GENERAL elements on surfaces.

FACE-ELEMDATA GENERAL, assigns datafor GENERAL elements on faces.

VOL-ELEMDATA GENERAL, assigns datafor GENERAL elements in volumes.


Chap. 2 Quick index

BODY-ELEMDATA GENERAL, assignsdata for GENERAL elements in bodies.

SURF-ELEMDATA FLUID2, assigns datafor FLUID2 elements on surfaces.

FACE-ELEMDATA FLUID2, assigns datafor FLUID2 elements on faces.

VOL-ELEMDATA FLUID3, assigns data forFLUID3 elements in volumes.

BODY-ELEMDATA FLUID3, assigns datafor FLUID3 elements in bodies.

MATRIX STIFFNESS, defines a stiffnessmatrix for general elements.

MATRIX MASS, defines a mass matrix forgeneral elements.

MATRIX DAMPING, defines a dampingmatrix for general elements.

MATRIX STRESS, defines a stress matrixfor general elements.

MATRIXSET, defines the matrixset for thecurrent GENERAL element group.

MATRIX USER-SUPPLIED, defines theelement stiffness matrix in a generalelement group to be provided bysubroutine CUSERG.

MASSES, assigns concentrated masses tothe nodes on a set of geometry entities.

DAMPERS, assigns concentrated dampersto the nodes on a set of geometryentities.

Section 7.4: Substructure and cyclicsymmetry

SUBSTRUCTURE, defines substructures.REUSE, connects a substructure to the main

structure.CYCLIC-CONTROL, specifies parameters

that control cyclic symmetry analysis.CYCLICLOADS, cyclic symmetric part of

loading.CYCLICBOUNDARY, defines cyclic

symmetric boundarie based on points,lines, surfaces or nodes.

CYCLICBOUNDARY TWO-D, definescyclic symmetric boundaries based onlines or edges.

CYCLICBOUNDARY THREE-D, definescyclic symmetric boundaries based onsurfaces or faces.

AXIS-ROTATION, defines a rotational axiswhich can be referenced other com-mands.

EG-SUBSTRUCTURE, creates substructuresin terms of existing element groups.

Section 7.5: Contact conditions

ANALYTICAL-RIGID-TARGET, definesparameters for analytical rigid targetanalysis.

CONTACT-CONTROL, specifies parameterscontrolling the behavior of the algo-rithms used in modeling contact.

CGROUP CONTACT2, defines a contactgroup consisting of 2-D or axisymmetriccontact surfaces.

CGROUP CONTACT3, defines a contactgroup consisting of 3-D contactsurfaces.

CONTACTBODY, defines a contact body i.e.a geometry surface in 2D or a geometryvolume in 3D.

CONTACTSURFACE, defines a contactsurface, i.e., a set of geometry bound-aries which are expected to be in contacteither initially or during analysis withanother similarly defined contactsurface.

CONTACTPOINT, defines a contact point,i.e., a set of geometry points (in 2-D or 3-D analysis) which are expected to be incontact.

DRAWBEAD, defines a drawbead for metalforming analysis.

COULOMB-FRICTION, specifies variableCoulomb friction coefficient.


Chap. 2 Quick index

USER-FRICTION, specifies the parametersused in the calculation of user-suppliedfriction for the current contact group.

CS-OFFSET, specifies offset distances forindividual contact-surfaces.

CONTACTPAIR, defines a contact pair, i.e.,two contact surfaces which are eitherinitially in contact or are anticipated tocome into contact during analysis.

CONTACT-3-SEARCH, creates 3D contactsurfaces and contact pairs between twobodies within the given distance range.

Section 7.6: Fracture mechanics

FRACTURE, defines controlling data foranalysis of fracture mechanics problems.

CRACK-GROWTH, specifies the parametersthat govern control of the growth of apropagating crack.

CRACK-PROPAGATION, defines the initialcrack front position or the virtual/actualcrack propagation path.

J-LINE POINT, defines a line contour via acircle centered at a point.

J-LINE RING, defines a line contour via aring of elements.

J-VIRTUAL-SHIFT POINT, defines a virtualmaterial shift via a circle centered at apoint.

J-VIRTUAL-SHIFT LINE, defines a virtualmaterial shift via the nodes lying on anyof a given set of lines.

J-VIRTUAL-SHIFT SURFACE, defines avirtual material shift via the nodes lyingon any of a given set of surfaces.

J-VIRTUAL-SHIFT RING, defines a virtualmaterial shift via a number of rings ofelements about the crack front.

R-CURVE, defines a resistance curve setwhich can be used in a crack growthanalysis.

SINGULAR, defines a set of �singular�nodes-vertex nodes whose adjacentnon-vertex nodes are moved to the �1/4point�, giving a singularity at therequired nodes.

USER-RUPTURE, specifies user-definedrupture data.

Section 7.7: Boundary conditions

RIGIDLINK, specifies rigid links betweengeometry entities.

CONSTRAINT, specifies a constraintequation which expresses a slave(dependent) degree of freedom as alinear combination of a set of master(independent) degrees of freedom.

CONSTRAINT-MS, similar to theCONSTRAINT command, but alsoallows the specification of multiple slaveentities for a single master entity.

CONSTRAINT-G, defines generalizedconstraint equations for ADINA.

FIXITY, defines a fixity boundary condition.FIXBOUNDARY, assigns fixity conditions to

a set of geometry entities.ZOOM-BOUNDARY, specifies the boundary

of a zoom model that is inside (internalto) the coarse model.

ENDRELEASE, defines an �endrelease�condition for elements of type BEAM.

FSBOUNDARY, defines a fluid-structure-interaction boundary.

FSBOUNDARY TWO-D, defines a fluid-structure-interaction boundary for 2Danalysis.

FSBOUNDARY THREE-D, defines a fluid-structure-interaction boundary for 3Danalysis.


Chap. 2 Quick index

POTENTIAL-INTERFACE, defines a free-surface potential-interface for ADINA.

POTENTIAL-INTERFACE INFINITE,defines an infinite potential-interface forADINA.

BOUNDARY-SURFACE SURFACE-TENSION, defines a surface tension

boundary for ADINA.OVALIZATION-CONSTRAINT POINT,

enforces the zero-slope-of-skin in thelongitudinal direction for pipe elementnodes.

FREESURFACE, defines a free surface onthe boundary lines (2-D) or surface(3-D)for potential-based problems.

BCELL, defines a boundary cell using a 4-node or 3-node cell.

Section 7.8: Loading

LOAD CENTRIFUGAL, defines a centrifu-gal load.

LOAD CONTACT-SLIP, defines a contact-slip load.

LOAD CONVECTION, defines a convection load.

LOAD DISPLACEMENT, defines adisplacement load.

LOAD ELECTROMAGNETIC, defines anelectromagnetic load.

LOAD FORCE, defines a force load.LOAD LINE, defines a line load, i.e., a

distributed load in terms of force/unitlength.

LOAD MASS-PROPORTIONAL, defines amass proportional load.

LOAD MOMENT, defines a moment load.LOAD NODAL-PHIFLUX, defines a nodal-

phiflux load.LOAD PHIFLUX, defines a phiflux load.LOAD PIPE-INTERNAL-PRESSURE,

defines a pipe-internal-pressure load.LOAD POREFLOW, defines a poreflow

load.

LOAD PORE-PRESSURE, defines a pore-pressure load.

LOAD PRESSURE, defines a pressure load.LOAD RADIATION, defines a radiation

load.LOAD TEMPERATURE, defines a tempera-

ture load.LOAD TGRADIENT, defines a temperature

gradient load to specify the temperaturegradient in the thickness direction of asurface (when applied to shell elements).

CPROP, defines conveciton properties forconvection loading.

RPROP, defines radiaiton properties forradiation loading.

LOAD-CASE, used in a linear static analysisto identify the current load case.

LCOMBINATION, defines a new load caseas a linear combination of previouslydefined load cases.

APPLY-LOAD, specifies loads applied tomodel geometry.

LOAD-PENETRATION, controls transfer ofapplied pressure loads to neighboringelements when an element �dies�.

Section 7.9: Initial conditions

INITIAL-CONDITION, defines an initialcondition.

SET-INITCONDITION, assigns initialconditions to a set of geometry entities.

STRAIN-FIELD, defines an initial strain field.IMPERFECTION POINTS, specifies

imperfections at points based onbuckling mode shapes which havebeen previously calculated.

IMPERFECTION SHAPE, used for initialshape calculations based on previouslycalculated nodal displacements.

INITIAL-MAPPING, loads an initial condi-tion mapping file and interpolatesvariable values at nodes.


Chap. 2 Quick index

THERMAL-MAPPING, interpolates nodaltemperatures and gradients from a giventemperature field contained in a mappingfile.

Section 7.10: Systems

SKEWSYSTEMS CYLINDRICAL, defines a�skew� Cartesian coordinate system interms of a cylinder origin and axisdirection.

SKEWSYSTEMS EULERANGLES, definesa �skew� Cartesian coordinate system interms of Euler angles.

SKEWSYSTEMS NORMAL, defines a�skew� Cartesian coordinate system tobe such that one of its directions isnormal to a given line or surface.

SKEWSYSTEMS POINTS, defines a�skew� Cartesian coordinat system interms of geometry points.

SKEWSYSTEMS SPHERICAL, defines a�skew� Cartesian coordinate system interms of a sphere origin.

SKEWSYSTEMS VECTORS, defines a�skew� Cartesian coordinate system interms of direction vectors.

DOF-SYSTEMS POINTS, assigns skewcoordinate systems to geometry points.

DOF-SYSTEMS LINES, assigns skewcoordinate systems to geometry lines.

DOF-SYSTEMS EDGES, assigns skewcoordinate systems to solid geometryedges.

DOF-SYSTEMS SURFACES, assigns skewcoordinate systems to geometrysurfaces.

DOF-SYSTEMS FACES, assigns skewcoordinate systems to solid geometryfaces.

DOF-SYSTEMS VOLUMES, assigns skewcoordinate systems to geometryvolumes.

DOF-SYSTEMS BODIES, assigns skewcoordinate systems to solid geometrybodies.

DOF-SYSTEMS NODESETS, assigns skewcoordinate systems to node sets.

SHELLNODESDOF, specifies the number ofdegrees of freedom for shell midsurfacenodes associated with a set of geometryentities.

AXES CONSTANT, defines an �axes-system� in terms of constant directionvectors.

AXES LINE1, defines an �axes-system� viaa geometry line.

AXES LINE2, defines an �axes-system� viatwo geometry lines.

AXES NODES, defines an �axes-system� viathree nodes.

AXES POINT2, defines an �axes-system�via two geometry points.

AXES POINT3, defines an �axes-system�via three geometry points.

AXES POINT-LINE, defines an �axes-system� via a geometry line and ageometry point.

AXES SURFACE, defines an �axes-system�via a geometry surface.

AXES EDGE, defines an �axes-system� via ageometry edge.

AXES FACE, defines an �axes-system� via ageometry face.

AXES CYLINDRICAL, defines a cylindri-cal axes system in terms of an origin andan axis direction.

AXES SPHERICAL, defines a sphericalaxes system in terms of an origin.

SET-AXES-MATERIAL, assigns materialaxes-system, defined by commandAXES, to a set of geometry entities.

SET-AXES-STRAIN, assigns initial-strainaxes-systems, defined by the commandAXES, to a set of geometry entities.


Chap. 2 Quick index

Chapter 8: Finite element representation

Section 8.1: Element groups

EGROUP TRUSS, defines an element groupconsisting of truss elements.

EGROUP TWODSOLID, defines an elementgroup consisting of planar oraxisymmetric elements.

EGROUP THREEDSOLID, defines anelement group consisting ofthree-dimensional solid elements.

EGROUP BEAM, defines an element groupconsisting of Hermitian beam elements.

EGROUP ISOBEAM, defines an elementgroup consisting of isoparametric beamelements.

EGROUP PLATE, defines an element groupconsisting of plate elements.

EGROUP SHELL, defines an element groupconsisting of shell elements.

EGROUP PIPE, defines an element groupconsisting of pipe elements.

EGROUP SPRING, defines an elementgroup consisting of spring elements.

EGROUP GENERAL, defines an elementgroup consisting of linear generalelements.

EGROUP FLUID2, defines an element groupconsisting of planar or axisymmetricfluid elements.

EGROUP FLUID3, defines an element groupconsisting of 3-D fluid elements.

EGCONTROL, specifies general control datafor an element group.

BOLT-OPTIONS, defines bolt options foruse with the EGROUP BEAM command.

BOLT-TABLE, specifies the bolt loadingsequence.

Section 8.2: Mesh generation

TRANSITION-ELEMENT, converts a set ofshell elements along an edge of a face/surface into shell transition elements.

BLAYER, generates boundary layers onspecified body faces.

COPY-TRIANGULATION, copies facetriangulation for later use by meshingcommands like GFACE or GBODY.

DELETE-TRIANGULATION, deletes facetriangulations created by the COPY-TRIANGULATION command.

LIST-TRIANGULATION, lists all faces(body and face labels) which havetriangulation created by the COPY-TRIANGULATION command.

SUBDIVIDE DEFAULT, defines defaultmesh subdivision data.

SUBDIVIDE MODEL, assigns meshsubdivision data to the entire currentmodel geometry.

SUBDIVIDE POINT, assigns mesh subdivi-sion data to geometry points.

SUBDIVIDE LINE, assigns mesh subdivi-sion data to geometry lines.

SUBDIVIDE SURFACE, assigns meshsubdivision data to geometry surfaces.

SUBDIVIDE VOLUME, assigns meshsubdivision data to geometry volumes.

SUBDIVIDE EDGE, assigns mesh subdivi-sion data to edges of a solid geometrybody.

SUBDIVIDE FACE, assigns mesh subdivi-sion data to faces of a solid geometrybody.

SUBDIVIDE BODY, assigns mesh subdivi-sion data to solid geometry bodies.

POINT-SIZE, specifies the element size atgeometr points.

SIZE-FUNCTION BOUNDS, defines amesh size function using the vertices ofthe model bounding box.


Chap. 2 Quick index

SIZE-FUNCTION HEX, defines a mesh sizefunction using the vertices of an inputbox.

SIZE-FUNCTION POINT, defines a meshsize function via a point source.

SIZE-FUNCTION AXIS, defines a mesh sizefunction via a line source.

SIZE-FUNCTION PLANE, defines a meshsize function via a planar source.

SIZE-FUNCTION COMBINED, defines amesh size function as a combination ofothers.

SIZE-LOCATIONS, specifies mesh size atcertain locations (other than geometrypoints).

NLTABLE, creates a table with specificationof number of layers across thin sections.

GPOINT, creates a node at a point with thesame coordinates.

GLINE, creates elements along a set ofgeometry lines.

GSURFACE, creates elements on a set ofgeometry surfaces.

GVOLUME, creates elements on a set ofgeometry volumes.

GEDGE, creates elements on a set of solidgeometry edges.

GFACE, creates elements on a set of solidgeometry faces.

GBODY, creates elements for a solid geom-etry body.

GBCELL, creates 3D elements from bound-ary cells.

GHEXA, generates brick element dominantfree-form meshes for a given body.

GADAPT, deletes and remeshes a finiteelement mesh.

ELDELETE, deletes elements generated onspecific geometry for a given elementgroup.

COPY-MESH-BODY, copies a mesh fromone body to another body via affinetransformation.

CSURFACE, creates a set of contactelements on a contact surface.

CSDELETE, deletes contact elementsgenerated on specific geometry for agiven contact group.

GLUEMESH, glues two dissimilar meshestogether.

Section 8.3: Elements

TRUSS-POINTS, defines axisymmetric trusselements at geometry points.

SPRING POINTS, defines spring elementsat points.

SPRING LINES, defines spring elementsbetween geometry lines.

REBAR- LINE, defines a rebar using lines.The rebar defined is then referenced inthe EGROUP TRUSS command to modelrebar elements.

TRUSS-LINE, defines TRUSS elementsbetween lines.

ELTHICKNESS, defines shell elementthickness.

Chapter 9: Direte finite element data input

Section 9.1: Nodal data

COORDINATES NODE, defines coordi-nates for (current substructure) nodes.

SKEWSYSTEMS NODES, defines a �skew�Cartesian coordinate system in terms ofnodes.

DOF-SYSTEM NODES, assigns skewcoordinate systems to nodes in thecurrent substructure.

MASSES NODES, assigns concentratedmasses to nodes.

DAMPERS NODES, assigns concentrateddampers to nodes.

SHELLNODESDOF NODES, specifies thenumber of degrees of freedom for shellmidsurface nodes.


Chap. 2 Quick index

SHELLDIRECTORVECTOR, definesdirector vectors that can be applied viacommand SHELLNODESDOF.

NODESET, defines a collection of nodes.RIGIDNODES SHELL, specifies special

constraints for shell midsurface nodes.

Section 9.2: Element data

AXES-NODES, defines an �axes-system� viathree model nodes.

AXES-INITIALSTRAIN, defines a set ofaxes to be used with the definition ofinitial strains in element.

AXES-ORTHOTROPIC, defines set ofprincipal material axes to be used withorthotropic material model.

ELEDGESET, defines an element edge setcontaining edges of 2-D elements.

ELEMENTSET, defines an element setcontaining elements.

ELFACESET, defines an element face setcontaining faces of 3-D and shellelements.

ENODES, defines element nodal connectiv-ity.

MESH-CONVERT, changes number ofnodes per element.

ENODES-INTERFACE, defines fluid-structure interface elements.

EDATA, specifies property data associatedwith individual elements in a group.

COPY-ELEMENT-NODES, copies allelements and nodes (in groups) betweendatabase models for two analysisprograms.

DELETE-FE-MODEL, deletes all finite-element data from the database.

REVOLVE, creates 3D elements by revolving2D elements about an axis.

SWEEP, creates 3D elements by extruding2D elements along a vector.

Section 9.3: Boundary conditions

BOUNDARIES, assigns boundary condi-tions to nodes.

CONSTRAINT-NODE, specifies a constraintequation between nodal degrees offreedom.

RIGIDLINK-NODE, specifies a rigid linkbetween two nodes.

OVALIZATION-CONSTRAINT NODE,used to enforce the zero-slope-of-pipe-skin condition in the longitudinaldirection at pipe-element nodes.

FSI-FACE, defines FSI boundary usingelement face nodes.

Section 9.4: Loads

APPLY CONCENTRATED-LOADS,Defines concentrated loads applied tonodes.

APPLY DISPLACEMENTS, definesprescribed displacements applied tonodes.

APPLY ELECTROMAGNETIC-LOADS,defines electromagnetic loads applied tonodes.

APPLY PIPE-INTERNAL-PRESSURES,defines internal pressures applied topipe element nodes.

APPLY TEMPERATURES, defines tempera-tures applied to nodes.

APPLY TGRADIENTS, defines temperaturegradients applied to shell elementsurface nodes.

APPLY USER-SUPPLIED-LOADS, signalsthe presence of user-supplied loads.

LOADS-ELEMENT, used to apply loadsonto element edges or faces.


Chap. 2 Quick index

Section 9.5: Initial conditions

INITIAL ACCELERATIONS, assigns initialaccelerations to nodes.

INITIAL DISPLACEMENTS, assigns initialdisplacements to nodes.

INITIAL FLEXURALSTRAINS, assignsinitial flexural strains to plate elementnodes.

INITIAL OVALIZATIONS, assigns initialovalizations to pipe element nodes.

INITIAL PINTERNALPRESSURES,assigns initial pipe internal pressures topipe element nodes.

INITIAL STRAINS, assigns initial strains tonodes.

INITIAL SGRADIENTS, assigns initialstrain gradients to shell elementmidsurface nodes.

INITIAL TEMPERATURES, assigns initialtemperatures to nodes.

INITIAL TGRADIENTS, assigns initialtemperature gradients to shell elementnodes.

INITIAL VELOCITIES, assigns initialvelocities to nodes.

INITIAL WARPINGS, assigns initialwarpings to pipe element nodes.

IMPERFECTION NODES, specifiesimperfections at nodes based on thebuckling mode shapes, which have beenpreviously calculated.

Section 9.6: Contact

CONTACT-ELEMSET, defines a contactsurface using element edge or face set.

CONTACT-FACENODES, defines a contactsurface within the current group usingface nodenumbers.

CONTACT-NODES, defines a contact-surface in terms of nodes, within thecurrent contact group.

Section 9.7: Fracture

CRACK-PROPAGATION NODES, used todefine the initial crack front position andthe virtual/actual crack propagation pathin terms of nodes.

J-VIRTUAL-SHIFT NODE, defines a fixedvirtual-crack-extension material shift viaa set of nodes.

J-VIRTUAL-SHIFT ELEMENT, defines afixed virtual-crack-extension materialshift via a set of elements.

J-LINE ELEMENT, defines a line contourconnected by a series of element faces.

SINGULAR NODES, defines a set of vertexnodes whose adjacent non-vertex nodesare to be moved.

Section 9.8: Substructures and cyclicsymmetry

REUSE-NODES, defines the nodal connectivity between the substructure and themain structure.

CYCLICBOUNDARIES NODES,associates cyclicboundaries in termsof nodes.


Chapter 3

Input/Output


Sec. 3.1 Database operations

DATABASE NEW SAVE PERMFILE PROMPT

DATABASE NEW creates a new database. The new database is initially empty. Beforecreating the new database, you have the option of saving any current internal database todisk. This option is controlled by parameters SAVE and PERMFILE.

SAVE [UNKNOWN]Used only when a database has been modified.

YES The program saves the current internal database to disk using thefilename specified by parameter PERMFILE. Then the programcreates a new internal database.

NO The program does not save the current internal database beforecreating a new internal database.

UNKNOWN The program asks you if you want to save the database.

PERMFILE [the last permanent database namepreviously specified]

Used only when the database has been modified. PERMFILE is the filename of the permanentdatabase file when saving the current database file to disk. You will be prompted for thisname if you do not enter a value for this parameter and no permanent database name waspreviously specified.

PROMPT [UNKNOWN]Used when saving a permanent database file.

YES You will be prompted �Ready to save permanent database file?�.

UNKNOWN You will be prompted �Permanent database file already exists� ifthe database file already exists.

NO You will not receive a prompt.

Auxiliary commands

DATABASE CREATE SAVE PERMFILEDATABASE CREATE has the same effect as DATABASE NEW.

DATABASE NEW


Chap. 3 Input/Output

DATABASE OPEN FILE SAVE PERMFILE PROMPT

DATABASE OPEN creates a new database using the permanent database file specified in thiscommand. Before creating the new database, the current internal database is optionallysaved to disk.

FILE [the last previously specified permanent database filename]

The filename of the permanent database file to be opened. If you do not enter a filename andthere is no default value, the program will prompt you for the filename.


YES The current internal database is saved to disk using the filenamespecified by parameter PERMFILE.

NO The current internal database is not saved before clearing thecurrent database and opening the specified database.

UNKNOWN The program will ask you if you want to save the database.

PERMFILE [the last previously specified permanent database filename]

Used only if the database has been modified. PERMFILE is the filename of the permanentdatabase file when saving the current database file to disk. The program will prompt you ifyou do not enter a value for PERMFILE and if no permanent database filename has previ-ously been specified.



UNKNOWN You will be prompted �Permanent database file already exists,� ifthe database file already exists.

NO You will not receive a promp

Note: It is allowed to open a database created by AUI 7.0, AUI 7.1 or AUI 7.2. However, allgraphics and model display definitions are deleted and reinitialized in the AUI workingcopy of the opened database.

DATABASE OPEN



DATABASE WRITE PERMFILE PROMPT

DATABASE WRITE saves the current internal database as a permanent database file. It isthe same as the DATABASE SAVE command except that DATABASE WRITE is availableonly when the database has been modified.

PERMFILE [the last previously entered permanent database filename specified]

Specifies the filename of the permanent database file. The program will prompt you if you donot enter a value for PERMFILE and if no permanent database filename has previously beenspecified.





DATABASE WRITE



DATABASE SAVE PERMFILE PROMPT

DATABASE SAVE saves the current internal database as a permanent database file.

PERMFILE [the last previously entered permanentdatabase filename specified]

Specifies the filename of the permanent database file. The program will prompt you if you donot enter a value for PERMFILE and if no permanent database filename has previously beenspecified.





DATABASE SAVE



DATABASE ATTACH FILE

DATABASE ATTACH allows access to the specified file as an AUI database file. UnlikeDATABASE OPEN (described in this section), DATABASE ATTACH does not make aworking copy of the database file prior to opening it. Instead you work directly with thespecified file as you use the AUI, possibly modifying the file�s contents.

The advantages of DATABASE ATTACH as compared to DATABASE OPEN are: diskrequirements are reduced because the AUI does not create a copy of the database file, andthe CPU time to attach a database is much less than the CPU time required to open it.

The disadvantages of DATABASE ATTACH are: (1) important information can be inadvert-ently modified or deleted from an attached database file, (2) the attached database cannotshrink, but can only grow as the AUI is used and (3) an attached database file cannot besaved, but can only be detached using DATABASE DETACH (described in this section).

Before you can use DATABASE ATTACH, you must first save any current database, andthen use DATABASE NEW (described in this section) to create a new database. You can useDATABASE ATTACH only if the current database is new and unmodified.

DATABASE ATTACH clears the permanent database filename.

You can attach a database that was created by earlier versions of the AUI. In this case,however, the AUI deletes and reinitializes all graphics and model display definitions in theattached database.

Exiting the AUI when a database is attached automatically detaches the database.

FILEThe filename of the permanent database file to be attached. If no filename is entered, the AUIwill prompt you for the filename.

Note: It is allowed to open a database created by AUI 7.0, AUI 7.1 or AUI 7.2. However, allgraphics and model display definitions are deleted and reinitialized in the AUIworking copy of the opened database.

DATABASE ATTACH



DATABASE DETACH PERMFILE PROMPT

DATABASE DETACH creates a permanent database file by detaching the working copy ofthe database file. Unlike DATABASE SAVE, DATABASE DETACH does not create a newpermanent database file.

The advantages of DATABASE DETACH as compared to DATABASE SAVE are: diskrequirements are reduced because the AUI does not create a copy of the database file, andthe CPU time to detach a database is much less than the CPU time required to save it.

The disadvantage of DATABASE DETACH is: the AUI does not compress the database fileby removing unused records.

After the database is detached, the AUI creates a new empty internal database.

A database can be detached at any time whether or not it was attached using DATABASEATTACH.

PERMFILEThe working copy of the database file is renamed to PERMFILE.





DATABASE DETACH


Sec. 3.2 Analysis data files

ADINA OPTIMIZE STARTNODE FILE FIXBOUNDARYMIDNODE OVERWRITE DUPLICATE

ADINA initiates model validation and, if the model is valid, creates an ADINA input data file,if requested.

OPTIMIZE [SOLVER]Equation numbering may be optimized so as to minimize the profile and bandwidth of theADINA solution matrices. The node label numbers are not affected by the equation number-ing. {SOLVER/YES/NO}

SOLVER If the sparse solver is used (see parameter SOLVER in command MASTER),then equation numbering is not optimized. Otherwise, equation numberingis optimized.

YES Equation numbering is optimized.

NO Equation numbering is not optimized.

STARTNODE [automatically selected]Label number of a main structure node, used to initiate the optimized equation numberingalgorithm. If such a node is not given, one will be automatically selected. The starting nodeshould be a peripheral node on the boundary of the main structure.

FILEThe filename of the ADINA input file to be generated. If no file name is given then onlymodel validation is performed.

FIXBOUNDARY [YES]Inactive degrees of freedom, i.e., those which are not connected to any elements and are notused in constraint equations, may be automatically deleted. {YES/NO}

MIDNODE [NO]Midside nodes on element edges may be moved to the straight line connecting the relevantvertex nodes. {YES/NO}

OVERWRITE [CONTROL PROMPT]Determines, if the filename given by FILE already exists, whether the command will overwrite itscontents with the currently generated input data. If set to UNKNOWN, a prompt will be givenrequesting confirmation for overwriting an existing file. {YES/NO/UNKNOWN}

ADINA


Chap. 3 Input/Output REBUILD-MODEL

REBUILD-MODELForces the AUI to rebuild the whole model.


Sec. 3.2 Analysis data files

This page intentionally left blank.

REBUILD-MODEL



LOADDXF FILE GCOINCIDE GCTOLERANCE

LOADDXF loads an AutoCAD® DXF file into the database. The points and lines are con-verted into AUI geometry entities.

This command supports only up to AutoCAD Release 12 DXF files.

FILEThe DXF file to be loaded in this command. Only a formatted file is accepted.

GCOINCIDE [YES]Point coincidence checking. If GCOINCIDE is set to YES then point coordinates are checked,and if within

GCTOLERANCE × (max. difference in global coordinates between all previous points)

then no new point number is created at that location, i.e., the previous point label number isassumed. {YES/NO}

GCTOLERANCE [1.0E-5]Tolerance used to determine point coincidence.

LOADDXF


Sec. 3.3 External data




LOADIGES FILE GCOINCIDE GCTOLERANCE TWOD-XY ADINA-MLABEL SEWING SEWGAP TOLER1 TOLER2 OPTION1REVERSE OPTION3 OPTION4 SCALEFACTOR PRECSPLABEL LLABEL XZERO X-SHIFT Y-SHIFT Z-SHIFT

Loads an IGES file into the database.

FILEThe IGES file to be loaded in this command. Only a formatted and uncompressed file isaccepted.

GCOINCIDE [YES]Point coincidence checking option. If set to YES, then point coordinates are checked, and ifwithin

GCTOLERANCE × (max. difference in global coordinates between all previous points)

then no new point is created at that location, i.e. the previous point label number is assumed.Only valid when ADINA-M = NO.{YES/NO}

GCTOLERANCE [1.0E-5]Tolerance used to determine point coincidence. Only valid when ADINA-M = NO.

TWOD-XY [NO]Indicates whether or not to rotate the IGES geometry model so that the XY plane is trans-formed into the YZ plane (as used in two-dimensional ADINA, ADINA-T, and ADINA-Fmodels). {YES/NO}

ADINA-M [NO]Indicates whether IGES data is to be loaded into ADINA-M. {YES/NO}Parameters GCOINCIDE, GCTOLERANCE and TWOD-XY are ignored by ADINA-M.

LABEL [(highest current sheet body or solid body labelnumber) + 1]

Sheet body or solid body label number.

SEWING [NO]Indicates wether ADINA-M sheet bodies are to be sewn together. {YES/NO}

SEWGAP [0.01]ADINA-M sewing body gap ratio. The gap value used to sew the body is SEWGAP * (max.difference in global coordinate between the maximum and minimum of the IGES body).

LOADIGES



TOLER1This parameter is obsolete.

TOLER2This parameter is obsolete.

OPTION1This parameter is obsolete.

REVERSEThis parameter is obsolete.



SCALEFACTOR [1.0]ADINA-M scale factor - input IGES coordinate values are to be divided by, i.e. (x-coordinate,y-coordinate, z-coordinate)/scalefactor.

PRECSThis parameter is obsolete.

PLABEL [(current highest point label number) + 1]Starting point label.

LLABEL [(current highest line label number) + 1]Starting line label.

XZERO [NO]The flag to set the x coordinate to 0. {NO/YES}

X-SHIFT [0.0]Y-SHIFT [0.0]Z-SHIFT [0.0]Shift the IGES geometry by X-SHIFT, Y-SHIFT, and Z-SHIFT in the x, y, and z direction,respectively. Note that if XZERO=YES, X-SHIFT is ignored. These three parameters areused only when ADINA-M=NO.

LOADIGES






LOADSOLID PARTFILE BODYNAME XORIGIN YORIGIN ZORIGINAX AY AZ BX BY BZ PCOINCIDE PCTOLERANCEMANIFOLD FORMAT OLD-UNIT NEW-UNIT SYSTEMREPAIR

The LOADSOLID command loads a Parasolid® part (or "transmit") file into the database. Themodel may be displayed, meshed, and loads, boundary conditions may be assigned to its faces,edges, and vertices. For each body within the Parasolid® file a solid geometry BODY is createdwhich is used to reference that body.

This command is only active when ADINA-M has been licensed.

PARTFILEThe name of a Parasolid® part file (i.e. for part file name "abcdef.x_t" you inputPARTFILE=abcdef.

BODYNAME [(current highest body label number)+1]This is the label number to be assigned to the first BODY to be created which is used to referto the first body in the part file -- other bodies in the part file will automatically be assignedBODY label numbers incremented from this parameter (i.e. (BODYNAME+1),(BODYNAME+2), ..., etc.)

XORIGIN [0.0]YORIGIN [0.0]ZORIGIN [0.0]The global coordinates of the origin of the model.

AX [1.0]AY [0.0]AZ [0.0]A vector (in global coordinates) giving the direction of the X-axis of the model.

BX [0.0]BY [1.0]BZ [0.0]A vector (in global coordinates) which together with vector (AX, AY, AZ) gives the X-Yplane of the model.

PCOINCIDE [NO]Indicates whether or not the vertices of the part are to be checked for coincidence withexisting geometry point coordinates. {NO/YES}

LOADSOLID



PCTOLERANCE [1.0E-5]Tolerance used to determine whether two points are coincident.

MANIFOLD [NO]Indicates whether non-manifold bodies are converted into manifold bodies. {NO/YES}

FORMAT [TEXT]Parasolid part file format.

TEXT text format.

BINARY binary format.

OLD-UNIT [METER]The unit of the part in the Parasolid file to be imported.{METER/CMETER/MMETER/INCH/FOOT}

NEW-UNIT [METER]The unit of the part after it is imported into ADINA-M.{METER/CMETER/MMETER/INCH/FOOT}

LOADSOLID

SYSTEM [0]If system label is greater than 0 and it is Cartesian coordinate system, replace XORIGIN,YORIGIN, ZORIGIN, AX, AY, AZ, BX, BY, BZ with the values from the given system.

REPAIR [NO]Repair the bodies if errors are detected. {NO/YES}



LOAD-CLOUD FILE STL-FILE BINARY BYTESWAP OUTLENGTH

elementi

Reads in a point cloud file (depicting the boundary of an object) and writes out an STL filewhich can then be loaded into the AUI with the LOAD-STL command. A tetrahedral mesh of thepoint cloud is initially built and elements are automatically "sculpted" away from the boundarygoing in. This command is used repeatedly until the point cloud mesh corresponds to theobject.

FILEName of the point cloud file. Each line of the file contains a point defined by three coordinates(x, y and z). The point cloud file is assumed to be noise-free and represent accurately (must befine enough) the geometry of the object's boundary. The object the point cloud is representingis assumed to be a single body (not an assembly of bodies).

STL-FILEIf none given, the command will not generate the STL file. It will however save the point cloudmesh into the AUI (which can then be reloaded if the command is called again). If a STL filename is given, the command will create the STL file and delete the current point cloud meshthat's residing in memory.

BINARY [NO]If set to NO, the output STL file format is supposed to be ASCII.If set to YES, the output STL file format is supposed to be binary. The byte ordering issupposed to be "little endian" (the norm for STL binary files). {NO/YES}

BYTESWAP [NO]If the byte ordering (see BINARY parameter) is "big endian", BYTESWAP should be set toYES. Because STL files are supposed to be written as "little endian", turning on BYTESWAPshould not be needed in general {NO/YES}

OUTLENGTH [0.0]Elements of the current point cloud mesh with at least one boundary face bigger (longest side)than OUTLENGTH are assumed to be outside and are thus removed from the mesh. Becausethis process changes the current boundary, a "sculpting" phase follows which automaticallyremoves elements which are believed to be outside. If set to 0.0 (default), it is not used.

elementiElements given are removed from the current point cloud mesh. Because this process changesthe current boundary, a "sculpting" phase follows which automatically removes elements whichare believed to be outside.

LOAD-CLOUD



LOAD-STL FILE BODY RIDGEANG NCTOLERANCE RIDGETOLMAXNVARS COTOLERANCE MAXNVARC NMTOLERANCERIDGEAN2 BYTESWAP

Loads an STL format file into the AUI by creating a STL body. Once loaded, mesh densities(MODE = LENGTH) can be applied to the created STL body, its faces and edges (just like for anADINA-M body). The command BODY-DSCADAP applies the mesh densities and generates adiscrete representation of the STL body which can then be meshed with the GBODY command.

It is assumed the model contained in the STL file is single-bodied and solid (defines a three-dimensional volume). If the model is made up of several bodies, the command still loads theSTL file as a single body made up of disconnected parts. To create multiple bodies, the modelshould be saved as multiple STL files, one for each body to be created.

Upon completion, if the STL file cannot be loaded, problems are either coming from thetolerance choice or the STL model itself.

If the number of under connected edges (connected to a single triangle) is greater than 0, thetolerance (NCTOLERA) may be set too low or the model is not watertight.

If the number of over connected edges (connected to more than two triangles) is greater than0, the tolerance (NCTOLERA) may be set too high or the model has non-manifold features(see NMTOLERA parameter).

If the number of non-manifold vertices is greater than 0, make sure the tolerance used foreliminating non-manifold features (NMTOLERA) is greater than 0 (but always significantlylower than NCTOLERA). Eliminating non-manifold features is attempted only when thenumber of under connected edges is 0.

If NCTOLERA is changed, NMTOLERA must be changed accordingly as it should always belarger than NCTOLERA.

If changing the tolerance (NCTOLERA) does not resolve all problems, it is likely the STL fileis not valid in representing a conforming triangular mesh.

If the STL file loads properly, it is assumed that the geometry it represents is not self-intersecting.

FILEName of file containing the STL data.

BODY [(highest body label number) + 1]Label of STL body to be created.

LOAD-STL



RIDGEANG [60 (degrees)]Controls ridge detection and therefore the creation of body edges. If two adjacent triangles inthe STL file have an angle greater than RIDGEANG, the common edge is assumed to be on aridge and will be part of a body edge, potentially separating two body faces.

By setting the RIDGEANG to 180, the created body will have no edges and no vertices (points).

NCTOLERANCE [1.0e-5]Tolerance used for checking coincidence of facet nodes (vertices of triangle facets).

RIDGETOL [0.0]Tolerance used to decide whether to discard potential edges on body edges. Given an edge andits two adjacent triangles in the STL file, if the distance from a vertex to the opposite edge issmaller than RIDGETOL (relative to its length) for each triangle, then the edge cannot beconsidered a ridge. By default, RIDGETOL is set to 0.0, meaning it is disabled. In most cases,enabling RIDGETOL is not necessary.

MAXNVARS [0.0]Maximum normal variation used in edge swapping (to improve quality of STL surface mesh priorto ridge detection). This threshold should remain small enough to maintain the shape of theoriginal model. By default, MAXNVARS is set to 0.0, meaning it is only enabled on planes.

COTOLERANCE [1.0e-4]Edges that are smaller than COTOLERANCE (relative to model size) are collapsed.Faces with large angle such that distance from vertex at large angle to opposite side is smallerthan COTOLERANCE are swapped. This is done to remove small features from the STL surfacemesh prior to ridge detection.Note: COTOLERANCE should be larger than NCTOLERANCE.

MAXNVARC [90.0]Maximum normal variation used in edge collapsing (to improve quality of STL surface meshprior to ridge detection). If COTOLERANCE is small then MAXNVARC may be large. IfCOTOLERANCE is large then MAXNVARC should be small.

NMTOLERANCE [1.0e-3]If the surface triangles in the STL file represent a non-manifold body (for example, the surfacemesh contacts itself at vertices or edges), it is possible to "break" the surface mesh by duplicat-ing vertices where the surface mesh contacts itself and pulling them away from each other.NMTOLERANCE represents how far duplicate vertices should be pulled apart from each other,relative to the dimensions of the model.

If set to 0.0, it is turned off.

LOAD-STL


Chap. 3 Input/Output LOAD-STL

NMTOLERANCE should always be greater than NCTOLERANCE.

RIDGEAN2 [180 (degrees)]Before the creation of body edges, if a ridge edge (see RIDGEANG description) is notconnected (at either end), it can be extended so as to make sure any edge connects (at eitherend) to one or more other ridge edges. New ridge edges will be created only if the adjacenttriangles have an angle greater than RIDGEAN2.By default, RIDGEAN2 is set to 180, which signifies this extension feature is not activated. Ifactivated (RIDGEAN2 is not equal to 180), RIDGEAN2 should be smaller than RIDGEANG.

BYTESWAP [NO]If the STL file is binary and the byte ordering is "big endian" (as opposed to "little endian"which is the norm for STL binary files), BYTESWAP should be set to YES. {NO/YES}


Sec. 3.3 External dataNASTRAN-ADINA

NASTRAN-ADINA FILE XY-YZ BEAM SUBCASE BCELLCONVERT-ELEMENT-TYPE DEFAULT DUPLICATESPLIT ELFACESET NODESET

NASTRAN-ADINA maps a NASTRAN® data file into the ADINA-IN database.

FILEThe NASTRAN® data filename.

XY-YZThis parameter is now obsolete. The program will automatically rotate 2D models in the XYplane to the YZ plane.

BEAM [THREE]Indicates whether hermitian beam elements are to be considered as having two-dimensionalor three-dimensional action. {TWO/THREE}

SUBCASE [0]The label number of a subcase defined in the NASTRAN® data file. If SUBCASE=0, the firstsubcase is used. {≥0}

BCELL [NO]Indicates whether boundary cells (see command BCELL) are created from shell elementsaccording to the property identification number (PID). All elements with the same PID are putinto the same BCELL. {NO/YES/REPLACE}

NO Do not create boundary cells.

YES Create boundary cells. In addition, if the shell elements are attached to 3-Delements, the program will also create element-face sets (see ELFACESETcommand) and node sets (see NODESET command). All shell elements usedfor creating these ELFACESETs and NODESETs are not deleted.

REPLACE Create boundary cells. In addition, if the shell elements are attached to 3-Delements, the program will also create element-face sets (see ELFACESETcommand) and node sets (see NODESET command). All shell elements usedfor creating these ELFACESETs and NODESETs will be deleted.

CONVERT-ELEMENT-TYPE [NONE]Specifies whether or not to convert 4-node shell elements to 8-node. {NONE/SHELL}

The parameters RBAR, RBE2, NCTOLERANCE, RBAR-MATERIAL, RBAR-AREA, RBAR-


Chap. 3 Input/Output NASTRAN-ADINA

DIAMETER, RBAR-THICKNESS, RBE2-MATERIAL, RBE2-AREA, RBE2-DIAMETER, andRBE2-THICKNESS are now obsolete. The conversion of RBAR and RBE2 elements is nowspecified in the NX Nastran bulk data entry NXSTRAT (see parameters EQRBAR andEQRBE2).

DEFAULT [AUI]Specifies which default values and convention should be used when a parameter is notspecified. {AUI/NXN}

AUI Use AUI default values and convention.

NXN Use NX Nastran advanced nonlinear analysis (SOL 601/701) default values andconvention. Nodal temperature and displacement loads with different time functionsare added instead of averaged if DEFAULT=NXN.

Note:The following default values are different between AUI and SOL 601/701 in NX Nastran.

Command Parameter AUI NXN

CGROUP EPST 0.0 1.0E-3

CGROUP CONSISTENT-STIFFNESS DEFAULT OFF

CONTACT-CONTROL POST-IMPACT YES NO

DUPLICATE [YES]This flag indicates whether or not to issue an error message when the Nastran file has aduplicate node or element. {NO/YES}

NO No error message issued. Later entries will override the earlier entries.

YES Error message issued.

SPLIT [PROGRAM]Indicates whether elements from different bulk entry (e.g., CHEXA, CPENTA, CTETRA) buthaving the same PID are split into different element groups. By default (i.e., PROGRAM),splitting is done for ADINA and ADINA-T models but not for ADINA-F models.{PROGRAM/YES/NO}

ELFACESET [BCELL]Flag to create elfaceset from attached SHELL element. {BCELL/NO/YES/REPLACE}

BCELL Take the default flag from BCELL parameter


Sec. 3.3 External dataNASTRAN-ADINA

NO No elfaceset will bce created

YES Create elfaceset and keep the attached SHELL element group

REPLACE Create elfaceset then delete the attached SHELL element group

Note that as long as one of BCELL, ELFACESET or NODESET = REPLACEthe attached SHELL element will be deleted.

NODESET [BCELL]Flag to create nodeset from attached SHELL element. {BCELL/NO/YES/REPLACE}

BCELL Take the default flag from BCELL parameter

NO No nodeset will bce created

YES Create nodeset and keep the attached SHELL element group

REPLACE Create nodeset then delete the attached SHELL element group

Note that as long as one of BCELL, ELFACESET or NODESET = REPLACEthe attached SHELL element will be deleted.



EXPORT NASTRAN FILE OVERWRITE FORMAT

Exports an ADINA model to a NASTRAN file. By default, the small field format is used.

FILESpecifies the NASTRAN file name.

OVERWRITE [CONTROL PROMPT]Determines, if the file name given by FILE already exists, whether the command will overwriteits contents with the currently generated input data. If set to UNKNOWN, a prompt will begiven requesting comfirmation for overwriting an existing file. {YES/NO/UNKNOWN}

FORMAT [SMALL]Indicates the format to export the NASTRAN file. {SMALL/LARGE}

EXPORT NASTRAN


Sec. 3.3 External dataEXPORT UNIVERSAL

EXPORT UNIVERSAL FILE

Exports the mesh in ADINA-AUI to an I-DEAS® universal file format.

FILESpecifies the name of the universal file to be created.


Chap. 3 Input/Output READ

READ FILE REWIND SCANDATA

READ reads AUI input commands from the file specified by parameter FILE until the end ofthe file is reached or the READ END command is encountered in the file. After the READcommand is executed, subsequent input is read from the previous command input source(that is, the input source from which the READ command was entered).

READ commands can be nested (that is, a file processed by the READ command can itselfinclude a READ command).

FILEThe name of the file from which AUI commands are read (up to 80 characters long). Note thatthe name END is not allowed.

REWIND [NO]If the file pointer is at end-of-file or if the file is not currently open, the read file is rewoundbefore beginning to read commands regardless of the value of this parameter. {YES/NO}

SCANDATA [� �]If SCANDATA is specified, the file is scanned until the SCANDATA string (1 - 80 characters)is found anywhere within an input record. Reading of input data from the file starts at thebeginning of the record that contains the string.

Auxiliary commands

READ ENDTerminates reading from file.


Sec. 3.4 Auxiliary files

FILEREAD OPTION FILE

FILEREAD controls the source of input commands to the AUI.

OPTION [INTERFACE]

INTERFACE Commands are read from the terminal or window from whichyou invoked the AUI.

FILE Commands are read from the file specified by the FILE parameter.

FILEThe filename of the file from which commands are read. Used only if OPTION = FILE.

Auxiliary commands

LIST FILEREAD

FILEREAD



FILESESSION OPTION FILE

FILESESSION controls the generation and output of a session file. The session file containsthe commands needed to repeat an AUI session.

A session file differs from an echo file in that:

1) You can generate a session file from a user-interface AUI session (this is the primaryuse of the session file).2) A session file contains all command parameters, regardless of whether you entered

them or whether they were default parameters.3) Changes to data input lines are handled in a different manner.

OPTION [NO]

NO No session file is created.

OVERWRITE A session file is generated and overwrites any existing contentsof the specified file.

APPEND A session file is generated and is appended to any existingcontents of the specified file.

FILEThe filename of the session file.

Auxiliary commands

LIST FILESESSION

FILESESSION



FILELIST OPTION FILE LINPAG EJECT

FILELIST controls the format and output of listings.

OPTION [INTERFACE]

INTERFACE Listings are output at the terminal or window from which youinvoked the AUI. Listings are buffered using an interface similarto UNIX �more� that allows you to scroll through listings.

FILE Listings are output to the file specified by the FILE parameter.

FILEThe filename of the file to which listings are written. Used only if OPTION = FILE.This can be the same file used for command echoing or logging.

LINPAG [0]The maximum number of lines output between list headings. You can suppress list headings(except for the first list heading) by specifying LINPAG = 0.

EJECT [NO]Specifies whether page ejects are placed before headings. {YES/NO}

Auxiliary commands

LIST FILELIST

FILELIST



FILEECHO OPTION FILE

FILEECHO controls the echoing of your input commands.

OPTION [INTERFACE]

NO No echoing of input commands.

INTERFACE Input commands are echoed back to the terminal or window fromwhich you invoked the AUI.

FILE Input commands are echoed back to the file specified by the FILEparameter.

FILEThe filename of the file to which input commands are echoed back. Used only if OPTION =FILE. This can be the same file for logs or listings.

Auxiliary commands

LIST FILEECHO

FILEECHO



FILELOG OPTION FILE

FILELOG controls the output of log messages.

OPTION [INTERFACE]

INTERFACE Log messages are written to the terminal or window from whichyou invoked the AUI.

FILE Log messages are written to the file specified by the FILEparameter.

FILEThe filename of the file to which log messages are written. Used only if OPTION = FILE.This can be the same file used for echoed commands or listings.

Auxiliary commands

LIST FILELOG

FILELOG



COMMANDFILE FILENAME PROMPT OPTION GRAPHICS

Creates a file containing the commands needed to recreate the model stored in the currentdatabase.

FILENAMEThe name of the file to be created. This parameter must be entered.

PROMPT [CONTROL PROMPT]You will be prompted �Ready to write command file?� if PROMPT = YES. You will beprompted �The command file already exists� if the specified file already exists and PROMPT =UNKNOWN. You will not be prompted if PROMPT = NO. Note that the default is taken from theparameter with the same name of the CONTROL command.

OPTION [SESSION]If OPTION = SESSION, the command file produced is a record of all commands issued whenthis database file is in use. The command file contains model modifications and deletions aswell as model additions. Commands in the command file may contain references to other files,for example, when a porthole file is loaded, the command file contains a LOADPORTHOLEcommand.

Currently OPTION must be set to SESSION. This parameter is provided for future develop-ments of the AUI.

GRAPHICS [NO]This parameter is used when OPTION = SESSION to control whether graphics commandssuch as FRAME, MESHPLOT, VIEW, etc. are written to the command file. If GRAPHICS =YES, graphics commands are written to the command file, otherwise they are not written.

COMMANDFILE



RTOFILE PROGRAM

texti

This command defines the contents of a run-time-option (.rto) file. When an ADINA, ADINA-T or ADINA-F data file (.dat file) is created, a corresponding run-time-option file (.rto file) isalso created.

If the RTOFILE command is not run, or if there are no lines of text in the RTOFILE command,then no .rto file is created.

PROGRAM [Current FE program]The finite element program for which the .rto file will be created. {ADINA/ADINA-T/ADINA-F}

textiA line of text in the .rto file. This text must be enclosed by single quotes. There can be anarbitrary number of lines of text in the .rto file.

Allowable input in the .rto file depends on the finite element program.

Auxiliary commands

LIST RTOFILEDELETE RTOFILE

RTOFILE



PAUSE

When the AUI reads the PAUSE command, it stops processing commands until you hit a key.

PAUSE


Sec. 3.5 Program termination

END SAVE PERMFILE PROMPT IMMEDIATE

END terminates the program. EXIT, QUIT and STOP are equivalent to END.

If the program is reading data from a file specified by the FILEREAD command and the end ofthe file is reached, the END command is executed automatically.


YES The program saves the current internal database to disk using the filenamespecified by parameter PERMFILE. Then the program creates a newinternal database.

NO The program does not save the current internal database before creating anew internal database.

UNKNOWN The program asks you if you want to save the database.

PERMFILE [the last previously specified permanentdatabase filename]

PERMFILE is the filename of the permanent database file when saving the current databasefile to disk; used only if the database has been modified. The program will prompt you if youdo not enter a value for PERMFILE and if no permanent database filename has previouslybeen specified.



UNKNOWN You will be prompted �Permanent database file already exists� if thedatabase file already exists.


IMMEDIATE [NO]If IMMEDIATE=YES, the program immediately stops execution without saving the databaseor prompting you. This option is most useful when writing batch scripts to force the programto terminate. {YES / NO}

Auxiliary commandsEXIT SAVE PERMFILE PROMPTQUIT SAVE PERMFILE PROMPTSTOP SAVE PERMFILE PROMPTEXIT, QUIT and STOP are equivalent to END.

END



PARAMETER NAME EXPRESSION

Defines a parameter that can be substituted in a later command. The AUI evaluates the givenexpression and stores the resulting number as the value of the parameter.

Note: Parameter definitions and values are not stored in the database.

NAMEThe name of the parameter (1 to 30 alphanumeric characters). The name is not case sensitive.If the parameter is not already defined, a new parameter is created, otherwise the existingparameter is modified.

EXPRESSIONA string (up to 256 characters long) that contains a numeric expression. The expressionstring can contain the following items:

The arithmetic operators +, -, *, /, ** (exponentiation)

Numbers (either real numbers or integers)

The following functions:

ABS(x) absolute valueAINT(x) truncationANINT(x) nearest whole numberACOS(x) arccosineASIN(x) arcsineATAN(x) arctangentATAN2(x,y) arctangent(x/y)COS(x) cosineCOSH(x) hyperbolic cosineDIM(x,y) positive differenceEXP(x) exponentialLOG(x) natural logarithmLOG10(x) common logarithmMAX(x,y,...) largest valueMIN(x,y,...) smallest valueMOD(x,y) remainderingSIGN(x,y) transfer of signSIN(x) sineSINH(x) hyperbolic sineSQRT(x) square root

PARAMETER


Sec. 3.6 Auxiliary commands

STEP(x) the unit step function:0.0 if x ≤ 0.01.0 if x < 0.0

TAN(x) tangentTANH(x) hyperbolic tangent

All trigonometric functions operate on or return angles in radians.

Examples

PARAMETER A '3.0' // A = 3PARAMETER B '5 + 7' // B = 12PARAMETER C '6 * \ // The string can be entered on several

5 ' // command lines as in this example; C = 30

Parameter substitution

When the command-line parser finds a token value that starts with a $, the parser finds theparameter name with that token value and substitutes the parameter value. For example, inthe commands

PARAMETER X1 '2.0/3.0'PARAMETER X2 'SQRT(5.0)'PARAMETER X3 'SIN(2.0)'BODY BLOCK DX1=$X1 DX2=$X2 DX3=$X3

the parser looks for the values of X1, X2 and X3 and substitutes the values (e.g. the charac-ters '0.666666666666667') for the names (e.g. the characters 'X1'). Hence the abovecommands are exactly equivalent to the command

BODY BLOCK DX1=0.666666666666667 DX2=2.23606797749979, DX3=0.909297426825682

The token values need not be in upper-case:

BODY BLOCK DX1=$x1 DX2=$x2 DX3=$x3

Parameter substitution occurs before command execution, so the following is allowed:

PARAMETER A '2.0'PARAMETER A '$A + 1' // A = 3

PARAMETER



Now you may want to put the symbol $ into a string without parameter substitution occuring.The rule is: if the next character after the $ is a letter [a-z], the command-line parser attemptsparameter substitution. So

PARAMETER A '3.0'USERTEXT ABC'The cost is $2000.00''The size is $A'DATAEND

is equivalent to

USERTEXT ABC'The cost is $2000.00''The size is 3'DATAEND

A convenient way to output the value of a single parameter is with the ECHO command:

PARAMETER X1 '2.0/3.0'ECHO $X1ECHO 'The value of X1 is $X1'

Auxiliary commands

LIST PARAMETERLists the values of all parameters.

ECHO STRINGOutputs the given string. This command can be used to output the value of a parameter,see the examples given in the PARAMETER command description. STRING is a string(up to 256 characters long).

PARAMETER

Chapter 4

Interface control and editing


Sec. 4.1 Settings

CONTROL PLOTUNIT VERBOSE ERRORLIMIT LOGLIMIT UNDOPROMPT AUTOREPAINT DRAWMATTACH DRAWTEXTDRAWLINES DRAWFILLS AUTOMREBUILD ZONECOPYSWEEPCOINCIDE SESSIONSTORAGE DYNAMICTRANSFORMUPDATETHICKNESS AUTOREGENERATE ERRORACTIONFILEVERSION INITFCHECK SIGDIGIT AUTOZONE PSFILEVERSION

CONTROL defines certain parameters that control program behavior. The parameters definedby the CONTROL command are stored in the database.

PLOTUNIT <not currently active> [PERCENT]

VERBOSE <not currently active> [YES]

ERRORLIMIT <not currently active> [0]

LOGLIMIT <not currently active> [0]

UNDO [5]The UNDO parameter controls the number of commands that can be undone using the UNDOcommand. If UNDO = 0, the UNDO command cannot be used, if UNDO = 1, UNDO can beused to undo the effects of the previous command, if UNDO = 2, UNDO can be used toundo the effects of the previous two commands, etc. Setting UNDO = 0 can significantlyspeed up the processing of batch files.

PROMPT [UNKNOWN]Controls the default behavior for prompts which may arise from various commands.

NO No command prompts will be issued - this is useful in batchmode - eliminating any interaction.

YES Command prompts are always issued.

UNKNOWN Command prompts are issued only when necessary.

AUTOREPAINT [YES]When AUTOREPAINT = YES, the AUI automatically repaints that area of the graphicswindow that is exposed to the removal or motion of overlapping windows or dialogs. Youmay want to set AUTOREPAINT to NO to suppress the repainting; in that case, you can usethe REFRESH command whenever you want to repaint the graphics window.

DRAWMATTACH [YES]When DRAWMATTACH = YES, mesh plot attachments (band plots, load plots, elementvector plots, reaction plots, line contour plots) are drawn. Otherwise, they are not drawn.

CONTROL


Chap. 4 Interface control and editing

One use of this option would be to turn off drawing of mesh plot attachments before movingthe mesh plots with the mouse.

DRAWTEXT [EXACT]DRAWLINES [EXACT]DRAWFILLS [EXACT]These options control the drawing of text, lines and fills:

EXACT Use the requested colors while drawing.

SATURATED Convert all colors to saturated colors before drawing.

GRAY Convert all colors to gray scales before drawing.

INVERSE Convert all colors to the INVERSE color before drawing (theINVERSE color is the opposite of the background color).

NO Do not draw.

AUTOMREBUILD [YES]When you enter a command that alters the geometry or finite element model, the AUI rebuildsall corresponding data structures so that the model can be re-plotted. This feature can bedeactivated by setting AUTOMREBUILD = NO (in this case, if you want to plot the model,you must use the ADINA, ADINA-T or ADINA-F commands to rebuild the model before-hand).

Setting AUTOMREBUILD = NO can significantly speed up the processing of batch files.

Notes : 1) One important use of parameters DRAWTEXT, DRAWLINES, DRAWFILLSis when making plots in black and white for reports. In this case you mightuse DRAWTEXT = INVERSE, DRAWLINES = INVERSE, DRAWFILLS =GRAY.

2) The drawing parameters apply both to graphics as displayed on the screenand to graphics as produced using SNAPSHOT or MOVIESAVE.

3) One use of DRAWFILLS = SATURATED is to speed up shaded color imagedrawing, especially using X Window graphics; all shades of each color areconverted to the same color, resulting in significantly fewer color changes.

ZONECOPY [NO]Controls whether the commands BANDPLOT, MESHPLOT, ELINEPLOT, EVECTORPLOT,LCPLOT, REACTIONPLOT, BANDSTYLE, MESHSTYLE, ELINESTYLE, EVECTORSTYLE,LCSTYLE, REACTIONSTYLE create copies of the input zones. Zone copies are alwayscreated by these commands in AUI 7.0 but not in later versions of the AUI. The preferred

CONTROL


Sec. 4.1 SettingsCONTROL

setting of ZONECOPY is NO, but YES may be necessary to read input/session files producedfor/by AUI 7.0. {YES/NO}

SWEEPCOINCIDE [YES]Controls whether the SURFACE/VOLUME REVOLVED/EXTRUDED geometry definitioncommands check for coincident lines and surfaces, as well as for coincident vertices (points).AUI 7.0 did not attempt to connect adjacent surfaces/volumes, resulting in duplicate linesand surfaces fro such �sweep� geometry definition. The default in AUI 7.1 and higher is toconnect adjacent surfaces/volumes whenever possible. However, AUI 7.0 input/session fileswhich contain such �sweep� geometry will likely fail, so it may well be necessary to setSWEEPCOINCIDE=NO to correctly process older input files. {YES/NO}

SESSIONSTORAGE [YES]If SESSIONSTORAGE = YES, the subsequent commands are stored in the AUI database. Youcan output these commands using the command COMMANDFILE. In the event of a systemcrash, you can retrieve these commands by opening the AUI temporary database, andsubsequently issuing the COMMANDFILE command.

If SESSIONSTORAGE = NO, subsequent commands are not stored in the AUI database andtherefore cannot be retrieved. You may wish to set SESSIONSTORAGE = NO before readingcommands from a batch file to eliminate the overhead of storing those commands within theAUI database.

Note that the storage of commands in the AUI database is independent of the writing ofcommands to the session file determined by command FILESESSION.

DYNAMICTRANSFORM [YES]Controls how the program indicates the transformation when you move, resize or rotategraphics using the mouse. If DYNAMICTRANSFORM=YES, the program redraws all pickedgraphics completely and redraws all other graphics that overlap the picked graphics. IfDYNAMICTRANSFORM=PARTIAL, the program partially redraws all picked graphics anddoes not redraw overlapping graphics. If DYNAMICTRANSFORM=NO, the programindicates the transformation using a bounding box.

UPDATETHICKNESS [YES]When you change the thickness of geometry surfaces or faces, all elements generated ontothe surfaces or faces are automatically updated with the updated thickness. {YES/NO}

In AUI 7.2 and lower, elements are not automatically updated. Therefore you may need to setUPDATETHICKNESS=NO so that input files constructed for use with AUI 7.2 and lower workcorrectly.



AUTOREGENERATE [NO]If AUTOREGENERATE=YES, the program regenerates the graphics after you run a commandthat changes the model definition. This parameter only applies to commands that are runfrom the command-line (or read from a file); it does not apply to dialog box input from the userinterface. Note that the user interface always regenerates the graphics after you use a dialogbox that changes the model definition. {YES/NO}

ERRORACTION [CONTINUE]Defines AUI action when error is detected. Parameter affects only commands read from abatch file.

CONTINUE AUI continues to process commands.

SKIP AUI skips the remaining commands up to the next READ ENDcommand, if any.

Note: For more details see AUI Command Reference Manual: Vol. IV - Display processing.

FILEVERSION [V85]This parameter tells the AUI which algorithms to use during subsequent commands. Use thisflag to request algorithms from previous versions of the AUI. For example, if you constructeda batch file in AUI 8.3, set FILEVERSION=V83 to specify that the AUI 8.2 algorithms shouldbe used in processing the file. {V73 / V74 / V75 / V80 / V81 / V82 / V83 /V84 / V85}.

INITFCHECK [NO]This parameter tells the AUI whether or not to consider subsequent commands as part of aninitialization file. If INITFCHECK=NO, subsequent commands are not considered part of aninitialization file, if INITFCHECK=YES, subsequent commands are considered part of aninitialization file.

When INITFCHECK=YES, the AUI does not check resultants and aliases for errors. There-fore resultants and aliases can be included in initialization files when INITFCHECK=YES.Also the AUI always allows the use of the FEPROGRAM command whenINITFCHECK=YES.

SIGDIGITS [6]This parameter controls the number of significant digits used in listings. Between 1 and 16significant digits can be requested.

AUTOZONE [YES]When AUTOZONE=YES, the AUI automatically creates zones for many common parts of themodel, such as element groups, contact surfaces and geometry bodies. See the description in

CONTROL


Sec. 4.1 SettingsCONTROL

the Zones - Introduction section of this manual (Section 6.2.) { YES / NO }

For models with many element groups or geometry bodies, you may want to turn off theAUTOZONE feature to save storage and CPU time.

PSFILEVERSION [V0]This parameter gives the Parasolid version number used for saving Parasolid files. Forexample, V150 means to save in Parasolid version 15.0 format. V0 means the Parasolidversion used to compile the AUI. { V0 / V80 / V90 / V91 / V100 / V110 /V111 / V120 / V121 / V130 / V140 / V150 / V160}

Notes1) One important use of parameters DRAWTEXT, DRAWLINES, DRAWFILLS is when

making plots in black and white for reports. In this case you might use DRAWTEXT= INVERSE, DRAWLINES = INVERSE, DRAWFILLS = GRAY.

2) The drawing parameters apply both to graphics as displayed on the screen and tographics as produced using SNAPSHOT or MOVIESAVE (see Section 3.3).

3) One use of DRAWFILLS = SATURATED is to speed up shaded color image drawing,especially using X Window System graphics; all shades of each color are convertedto the same color, resulting in significantly fewer color changes.

4) Example of a session file that will not work unless ZONECOPY = YES:

*LOADPORTHOLE OPERATIO=CREATE FILE=...*MESHPLOT MESHSTYL=DEFAULT ZONENAME=WHOLE_MODEL RESPONSE=DEFAULT,

MODELDEP=DEFAULT VIEW=DEFAULT MESHWIND=DEFAULT PLOTAREA=DEFAULT,SUBFRAME=DEFAULT ELDEPICT=DEFAULT NODEDEPI=DEFAULT,BOUNDEPI=DEFAULT GPDEPICT=DEFAULT GLDEPICT=DEFAULT,GSDEPICT=DEFAULT GVDEPICT=DEFAULT MESHREND=DEFAULT,MESHANNO=DEFAULT FRONDEPI=DEFAULT CONDEPIC=DEFAULT,VSDEPICI=DEFAULT CRACKDEP=DEFAULT RESULTCO=DEFAULT

*NODEDEPICTIO NAME=MESHPLOT00001 SYMBOLPL=YES SYMBOL=�@C[1,5]�, SYMBOLCO=GREEN SYMBOLSI=0.150000005960000 UNITSYMB=CM NUMBER=NO, NUMBERCO=GREEN NUMBERSI=0.250000000000000 UNITNUMB=CM@STARTMODIFY@ENDMODIFY*MESHPLOT NAME=MESHPLOT00001 MESHSTYL=DEFAULT ZONENAME=MESHPLOT00001, RESPONSE=MESHPLOT00001 MODELDEP=MESHPLOT00001 VIEW=MESHPLOT00001, MESHWIND=MESHPLOT00001 PLOTAREA=MESHPLOT00001,


Chap. 4 Interface control and editing CONTROL

SUBFRAME=MESHPLOT00001 ELDEPICT=MESHPLOT00001, NODEDEPI=MESHPLOT00001 BOUNDEPI=MESHPLOT00001, GPDEPICT=MESHPLOT00001 GLDEPICT=MESHPLOT00001, GSDEPICT=MESHPLOT00001 GVDEPICT=MESHPLOT00001, MESHREND=MESHPLOT00001 MESHANNO=MESHPLOT00001, FRONDEPI=MESHPLOT00001 CONDEPIC=MESHPLOT00001, VSDEPICI=MESHPLOT00001 CRACKDEP=MESHPLOT00001, RESULTCO=MESHPLOT00001

The second mesh plot requires a zone name MESHPLOT00001; this zonename is produced by the first MESHPLOT command by a copy. Noticethat the initial mesh plot works regardless of the value of CONTROL ZONECOPY.

5) Example of commands that work unexpectedly unless ZONECOPY = NO:

MESHPLOT ZONE=PART1ACTIVEZONECLEAR�PART1�DATAENDLINE STRAIGHT 1 1 2REGENERATE

We expect that the REGENERATE command will draw line 1, as line 1 has been added toactive zone PART1 and the mesh plot contains zone PART1. However the REGENERATEcommand will only draw line 1 if CONTROL ZONECOPY = NO.

Auxiliary commands

LIST CONTROLLists the values of the parameters set by the CONTROL command.


Sec. 4.2 Editing

UNDO NUMBER

UNDO cancels the effects of previous commands.

UNDO is possible only if CONTROL UNDO is greater than zero. See Section 4.1 for adescription of the CONTROL command.

The UNDO command can itself be undone by REDO (described in this section).

NUMBER [1]The number of previous commands to be undone. The maximum possible number of previouscommands that can be undone is set by CONTROL UNDO. However, the actual number ofprevious commands that can be undone may be less than this.

UNDO



REDO NUMBER

REDO cancels the effects of previous UNDO commands (described in this section). It can beused only if the previous command was either UNDO or REDO.

The REDO command can be followed by the UNDO command to cancel the REDO.

NUMBER [1]The number of previous UNDO commands to be undone.

REDO

Chapter 5

Control data


Sec. 5.1 General

FEPROGRAM PROGRAM

FEPROGRAM specifies the finite element analysis program to be used to solve the problemdescribed by the model database.

PROGRAM [ADINA]The finite element analysis program name. The following choices are available:

ADINA For displacement and stress analysis.

ADINA-T For heat transfer analysis.

ADINA-F For fluid flow and heat transfer analysis.

Auxiliary commands

LIST FEPROGRAMLists the currently selected finite element analysis program.

FEPROGRAM


Chap. 5 Control data

HEADING STRING

HEADING specifies a title for the problem described by the model database.

STRING [�*** NO HEADING DEFINED ***�]The problem heading, input as a string of up to 80 characters (including blank spaces)enclosed within apostrophes (�).

Auxiliary commands

LIST HEADINGLists the current problem heading.

HEADING


Sec. 5.1 General


5-6 AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition


MASTER ANALYSIS MODEX TSTART IDOF OVALIZATIONFLUIDPOTENTIAL CYCLICPARTS IPOSIT REACTIONSINITIALSTRESS FSINTERACTION IRINT CMASS SHELLNDOFAUTOMATIC SOLVER CONTACT-ALGORITHM TRELEASERESTART-LDC FRACTURE LOAD-CASE LOAD-PENETRATIONMAXSOLMEM MTOTM RECL SINGULARITY-STIFFNESSSTIFFNESS-FACTOR MAP-OUTPUT MAP-FORMAT NODAL-DEFORMATION-FILE POROUS-COUPLING ZOOM-LABELAXIS-CYCLIC PERIODIC VECTOR-SHELL EPSI-FIRST STABILIZESTABFACTOR RESULTS FEFCORR BOLTSTEP EXTEND-SSCURVECONVERT-SSVAL DEGEN TMC-MODEL ENSIGHT-OUTPUT

MASTER defines the data controlling the execution of the analysis program ADINA.

ANALYSIS [STATIC]Selects the category of analysis to be performed.

STATIC Static analysis.

DYNAMIC-DIRECT-INTEGRATION Dynamic analysis.

FREQUENCIES Frequency / mode-shape calculation.

BUCKLING-LOADS Linearized buckling load calculation.

MODAL-TRANSIENT Mode superposition for time integration ofmodal response.

MODAL-PARTICIPATION-FACTORS Calculation of modal participation factors forsubsequent response spectrum, harmonic, orrandom analyses.

MODAL-STRESSES Calculation of modal stresses.

MODEX [EXECUTE]Selects the execution mode of the analysis. {CHECK/EXECUTE/RESTART/RESULTS}

CHECK ADINA checks the data without executing.

EXECUTE ADINA checks the data and executes.

RESTART ADINA performs a restart, reading data from a previous run, checks thedata and executes.

MASTER


Sec. 5.1 General

RESULTS ADINA performs result-recovery.

TSTART [0.0]Solution start time. For a restart run (MODEX = RESTART) TSTART must equal a solutiontime at which data was saved from a previous run.

IDOF [000000]Master degree of freedom code. A six digit integer, where each digit indicates either anallowed (0) or a deleted (1) degree of freedom. A degree of freedom deleted by this parameteris deleted from the entire model. The digits correspond to the following degrees of freedom:

Digit 1: X-translation (a-translation for a skew system).Digit 2: Y-translation (b-translation for a skew system).Digit 3: Z-translation (c-translation for a skew system).Digit 4: X-rotation (a-rotation for a skew system).Digit 5: Y-rotation (b-rotation for a skew system).Digit 6: Z-rotation (c-rotation for a skew system).

The default is for all degrees of freedom to be active.

Note: The directions of rotational degrees of freedom at a shell element mid-surface nodewith a local reference system depend on the orientation of the director vector orelement normal vector, as applicable.

Note: Preceding zeroes may be omitted, i.e., IDOF = 111 is equivalent to IDOF = 000111.

OVALIZATION [NONE]Pipe element nodes can have additional ovalization and warping degrees of freedom, asselected by the following options:

NONE All ovalization and warping degrees of freedom are deleted.

IN-PLANE Only the 3 ovalization and 3 warping degrees of freedom corre-sponding to in-plane loading are admissible.

OUT-OF-PLANE Only the 3 ovalization and 3 warping degrees of freedom corre-sponding to out-of-plane loading are admissible.

ALL All 6 ovalization and 6 warping degrees of freedom are admissible.

FLUIDPOTENTIAL [AUTOMATIC]Selects the fluid potential degree of freedom. If there are elements in groups of type FLUID2or FLUID3 with a potential-based formulation, this degree of freedom is automaticallyselected. {AUTOMATIC/YES/NO}

MASTER



CYCLICPARTS [1]The number of cyclic symmetric parts of the main structure. If the value is greater than orequal to 2 then a cyclic symmetric analysis is performed. The maximum number of cyclicsymmetric parts allowed is 999. CYCLICPARTS = 1 indicates no cyclic symmetry.

IPOSIT [STOP]Specifies the preferred behavior of ADINA when a zero or negative diagonal element isencountered, i.e. when the system matrix is not positive definite.

STOP ADINA may terminate, see note below.

CONTINUE ADINA continues execution.

Note: The selection IPOSIT = STOP may be overridden by ADINA, as follows:

IPOSIT = STOP

Linear analysis:ADINA stops if the stiffness matrix is not positive definite, except whenpotential-based fluid elements are in use.

Non-linear analysis:ADINA stops if the stiffness matrix is not positive definite, unless:

- the automatic load-displacement (LDC) option is being used, or- the automatic time-stepping (ATS) option is being used, or- the element birth/death option is used, or- potential-based fluid elements are being used, or- a contact analysis is being performed.

IPOSIT = CONTINUE

ADINA will always continue execution. If an exact zero pivot is encountered,ADINA assigns a very large number to the diagonal term, effectively attaching avery stiff spring to the degree of freedom. If the stiffness matrix is not positivedefinite in linear analysis, this usually means that the problem is not well defined(e.g. insufficient restraint). Use of IPOSIT = CONTINUE in such cases can givemisleading results.

REACTIONS [YES]Indicates whether reaction forces and moments corresponding to fixed or prescribed degreesof freedom are evaluated and printed. {NO/YES/SELECTED/SUM-SELECTED}

NO No reaction forces and moments corresponding to fixed or pre-scribed degrees of freedom are evaluated and printed.

MASTER


Sec. 5.1 General

YES All reaction forces and moments corresponding to fixed or pre-scribed degrees of freedom are evaluated and printed.

SELECTED Reaction forces are printed for nodes selected by command REAC-TION-NODES.

SUM-SELECTED The sum of reaction forces for nodes selected by command REAC-TION-NODES are printed.

INITIALSTRESS [NO]Indicates whether the initial strains input at nodes are to be interpreted by ADINA as thecorresponding initial stresses. {NO/YES/DEFORMATION}

NO Initial strains at nodes are not interpreted as initial stresses.

YES Initial strains at nodes are interpreted as initial stresses, butstresses do not result in deformation.

DEFORMATION Nodal initial strains are to be interpreted as initial stress which resultin deformation.

FSINTERACTION [NO]Determines whether the analysis involves fluid-structure interaction. {YES/NO}

Note: FSINTERACTION = YES is automatically set if FSBOUNDARY is used.

IRINT [DEFAULT]Frequency of saving ADINA results to restart file.

> 0 Restart file overwritten every IRINT timesteps.

< 0 Restart file appended every IRINT timesteps.

DEFAULT Number of steps in first time step block (see TIMESTEP ) for explicittimestepping (see ANALYSIS DYNAMIC-DIRECT-INTEGRATION ).1 otherwise.

CMASS [NO]Controls whether the total mass, total volume, moments and products of inertia, centroid, andcenter of mass are calculated by ADINA for each element group. {YES/NO}

SHELLNDOF [AUTOMATIC]Specifies the default number of degrees of freedom to be associated with shell midsurfacenodes. This default may be overridden by SHELLNODESDOF, which specifies the number of

MASTER



degrees of freedom for shell midsurface nodes.

5 or FIVE Shell midsurface nodes will have 3 translation degrees of freedom(global or skew) together with two rotation degrees of freedomcorresponding to a local midsurface coordinate system � seeSHELLNODESDOF.

6 or SIX Shell midsurface nodes will have 3 translation and 3 rotation degreesof freedom corresponding to the global or assigned skewsystem.

0 or AUTOMATIC Shell midsurface nodes will have five degrees of freedom, unlessmodeling considerations, determined automatically, such as branchshell structures or direct specification of rotation degrees of freedom(see SHELLNODESDOF ), require that six degrees of freedom beemployed.

AUTOMATIC [OFF, (FSINTERACTION=NO)][ATS, (FSINTERACTION=YES)]

Selects a method of automatic incrementation control during analysis. {OFF/ATS/LDC/TLA/TLA-S}

OFF No automatic incrementation; user-defined time step sequence is followed.

ATS Automatic time step control is enabled � see commandAUTOMATIC TIME-STEPPING.

LDC Automatic load-displacement control is enabled � see commandAUTOMATIC LOAD-DISPLACEMENT.

TLA The program ignores any time step and time function specified. Instead, 50 timesteps of size 0.2 are used with a linear ramp time function (100% load at time of10.0), and following settings are used.- ATS with an acceleration scheme is used- maximum number of equilibrium iterations = 30- line search is used- limits maximum incremental displacement in each iteration to 5% of largest

model length

TLA-S Total load application with stabilization. In addition to TLA settings, thefollowing stabilization settings are used.- stiffness matrix stabilization factor of 1.0e-10 is used- low-speed dynamics option is used- contact damping is used

MASTER


Sec. 5.2 Analysis details

See command AUTOMATIC TOTAL-LOAD-APPLICATION for changing thesettings used in the TLA or TLA-S scheme.

SOLVER [SPARSE]Selects the type of solution algorithm used to solve the equilibrium equation system.{SKYLINE/ITERATIVE/SPARSE/MULTIGRID/3D-ITERATIVE/NONSYM-SP}

SKYLINE A skyline direct solution algorithm (active column Gauss elimina-tion) is used.

ITERATIVE An iterative solution (incomplete Cholesky preconditionedconjugate gradient method) is used.

SPARSE A sparse-matrix solver is used.

MULTIGRID A multigrid solver is used.

3D-ITERATIVE An iterative solver is used for models with relatively large numberof 3-D higher order elements.

NONSYM-SP A nonsymmetric sparse solver is used.

Note: See SOLVER ITERATIVE for input of parameters controlling the operation of theiterative solver.

CONTACT-ALGORITHM [CONSTRAINT-FUNCTION]Selects the default algorithm used for contact groups. See the Theory and Modeling Guidefor further details. {CONSTRAINT-FUNCTION/SEGMENT-METHOD/RIGID-TARGET}

It is recommended to use the CONTACT-CONTROL command�s CONTACT-ALGORITHMparameter instead for this purpose as this parameter may be obsolete in future releases.

TRELEASE [0.0]When the element death option is utilized, an element will �die� (i.e., have zero stiffnesscontribution) at a given time TDEATH associated with the element. By default (TRELEASE =0.0) an element �dies� immediately when the solution time reaches TDEATH. However,when TRELEASE > 0.0, an element will �die� over the solution time interval from TDEATHto (TDEATH + TRELEASE). {≥ 0.0}

RESTART-LDC [NO]Determines whether or not the load vector is transferred to a restart run.

NO The load vector is not written at the end of an analysis, nor is it read as anexternal load vector in a restart analysis.

MASTER



YES The load vector is written at the end of an analysis, and it is read as anexternal load vector in a restart analysis.

FRACTURE [NO]Controls whether or not the analysis involves fracture mechanics. {YES/NO}

LOAD-CASE [NO]Controls whether or not multiple load cases are used in a linear analysis. If LOAD-CASE =SIMPACK, the SIMPACK interface will be used. {YES/NO/SIMPACK}

LOAD-PENETRATION [NO]Controls whether or not load penetration is employed in the analysis, whereby distributed(pressure) load is transferred upon element death. {YES/NO}

MAXSOLMEMThis parameter is obsolete.

MTOTMThis parameter is obsolete.

RECLThis parameter is obsolete.

SINGULARITY-STIFFNESS [YES]Assign �drilling� stiffness to rotational degrees of freedom with zero stiffness associatedwith shell nodes connected to rigid links, beams, or pipes. {NO/YES}

STIFFNESS-FACTOR [1E-4]Stiffness factor value used when SINGULARITY-STIFFNESS = YES. The actual stiffnessused is obtained by multiplying this factor by the rotational stiffness at the shell nodes.

MAP-OUTPUT [NO]Indicates whether the mapping file is written. If the file is written, the frequency follows thefrequency of the porthole file. {NO/YES/REMESH/NODAL/ZOOM-INITIAL/ZOOM-ANALYSIS/FSB}

NO No mapping file output.

YES ADINA will output mapping file.

REMESH AUI read nodal deformation file to recreate geometry for remeshing.

NODAL ADINA will output mapping file only for nodal results. This type of

MASTER



mapping file can be used as initial conditions for a subsequent analysisusing a different mesh.

ZOOM-INITIALADINA will output mapping file for use by a zoom model.

ZOOM-ANALYSISADINA will perform analysis for a zoom model. A mapping file created in aprevious analysis (with MAP-OUTPUT = ZOOM-INITIAL) is required.If the boundary of the zoom model coincides with the boundary of theoriginal model, the ZOOM-BOUNDARY command must also be specified(see figure at ZOOM-BOUNDARY command).

FSB MASTER command will read previous mapping file and updateFSI-BOUNDARY with deformed coordinate. Note that this option is onlyused with FSINTERACTION = YES and the adaptive-mesh option is usedin the ADINA-F model.

MAP-FORMATIndicates whether the mapping file is written in text or binary format. {YES/NO}

NO binary file.

YES text file.

NODAL-DEFORMATION-FILESpecifies the name of the nodal deformation file. If MAP-OUTPUT=REMESH AUI will readthis file. When the program reads the nodal deformation file to recreate geometry forremeshing, the following actions are taken:

- all elements and their nodes are deleted.- all volumes and surfaces are deleted.- all lines which contain nodes are modified such that the line now passes through the new nodal positions.

Note: MAP-OUTPUT=REMESH is currently restricted only for 2-D problem where themodel uses only AUI native geometry (i.e. lines and surfaces).

POROUS-COUPLING [NO]Porous-coupling. {NO/YES}

ZOOM-LABEL [1]Current zoom model label number .

MASTER


Chap. 5 Control data MASTER

AXIS-CYCLIC [0]Label number of cyclic symmetry axis defined by axis-rotation command. Default AXIS-CYCLIC = 0 means use global X axis.

PERIODIC [NO]Specifies whether periodic loads are to be applied to cyclic parts. {NO/YES}

NO different loads are used for different cyclic parts.

YES the load applied on the first cyclic part is rotated about the cyclic axis and applied tothe other cyclic parts. Unlike basic cyclic symmetry analysis, a periodic symmetryanalysis can be nonlinear. It can also be used with explicit dynamic time integration.

VECTOR-SHELL [GEOMETRY]Flag for calculation of shell-vector direction

GEOMETRY shell-vector direction from surface/face normal direction

ELEMENT shell-vector direction from element

EPSI-FIRST [NO]Indicates whether the analysis is first solved with the applied initial strain before loads areapplied. If EPSI-FIRST=YES, then the automatic time stepping (ATS) method can also be usedto scale the initial strains in case the solution fails to converge when the full initial strains areapplied in one step.{NO/YES}

STABILIZE [AUTOMATIC]The flag to set the option to stabilize the stiffness matrix. {AUTOMATIC/NO/YES}

AUTOMATIC Automatically use stabilization if the ratio of the maximum to minimumdiagonals of the factorized stiffness matrix is greater than 1.0E11.

NO Do not use stabilization.

YES Use stabilization.

STABFACTOR [1.0E-10]The stabilization factor used if STABILIZE when is set to YES or AUTOMATIC.

RESULTS [PORTHOLE]Specifies the output option for the results. {PORTHOLE/OP2/OP2+PORT/UNV/UNV+PORT}



PORTHOLE ADINA porthole file format

OP2 Nastran .OP2 file format

OP2+PORT Nastran OP2 file and ADINA porthole file formats

UNV I-deas universal file format

UNV+PORT I-deas universal file and ADINA porthole file formats

FEFCORR [NO]Perform fixed-end-force correction for beams. {YES/NO}

BOLTSTEP [1]The number of steps to iterate for calculation of bolt force.

EXTEND-SSCURVE [YES]Automatically extend the stress-strain curve to strain value of 100.0 by default. {NO/YES}

CONVERT-SSVAL [NO]Option to convert stress-strain curve input from engineering stress/strain to true stress/strain. {NO/YES}

The plastic-multilinear, multilinear-plastic-creep and the multilinear-plastic-creep materialmodels are affected by the setting of this parameter as follows:

When CONVERT-SSVAL=NO, stressi and straini are interpreted as true stresses and strains.Stresses and strains entered in the SCURVE command are also intrepreted as true stressesand strains.

When CONVERT-SSVAL=YES, stressi and straini are interpreted as engineering stresses andstrains. Stresses and strains entered in the SCURVE command are also intrepreted as engi-neering stresses and strains.

DEGEN [YES]Indicator for spatial isotropy correction of degenerate 8-node 2D elements or 20-node 3Delements. {YES/NO/UNUSED}

TMC-MODEL [NO]Specifies whether the model contains thermal properties and the type of thermal-mechanicalcoupling analysis. {NO/ONEWAY/ITERATIVE/HEAT}

MASTER



NO No heat transfer analysis is performed by the program.

ONEWAY The program performs first a heat transfer step to calculate temperatures,then a stress/displacement (mechanical) step. Note that the heat transferstep size can be different than the mechanical step size. Also, heat transfercan be a transient analysis and mechanical analysis can be a static analysis(or any combination thereof).

ITERATIVE An iterative thermo-mechanical coupling is used. The program iteratesbetween heat transfer and mechanical solutions. The same step size is usedin both cases. A solution is obtained if both temperature and displace-ment results converge. Note that the option is available for contact withfriction, or thermo-plastic and rubber materials only.

HEAT The program ignores any structural loads and boundary conditions andperforms a pure heat transter analysis.

ENSIGHT-OUTPUT [NO]Indicates whether an EnSight output file is written and which format is used. If the file iswritten, it will be written at end of each time step when the porthole file is written.{NO/UNFORMATTED/FORMATTED}

NO No EnSight output file is written

UNFORMATTED An unformatted EnSight output file is written

FORMATTED A formatted EnSight output file is written

Auxiliary commands

LIST MASTER

MASTER



DOF-ACTIVE

nodei dofi

The command is used to identify the active degree of freedom (DOF) of reduced model. It isonly used when LOAD-CASE = SIMPACK in the MASTER command.

nodeiNode label number.

dofiType of DOF.{X-TRANSLATION/Y-TRANSLATION/Z-TRANSLATION/R-ROTATION/Y-ROTA-TION/Z-ROTATION}

DOF-ACTIVE



TMC-CONTROL ANALYSIS TIMESTEP TSTEP-NAME AUTOMATICSOLVER HEAT-MATRIX METHOD MAXSUBD ALPHATSTART GAMMA TEMP-CUTOFF CUTOFF TEMP-RELAXHEAT-RELAX

TMC-CONTROL defines parameters that control TMC analysis.

ANALYSIS [STEADY-STATE]Selects the type of heat transfer analysis to be performed.{STEADY-STATE/TRANSIENT}

STEADY-STATE Steady-state analysis.

TRANSIENT Time dependent analysis.

TIMESTEP [CURRENT]Flag to specify the time step for heat transfer analysis. {CURRENT/SPECIFIED}

CURRENT Use the same time step as ADINA.

SPECIFIED Specify the time step using the TSTEP-NAME parameter.

TSTEP-NAMESpecifies the time step for heat transfer analysis. It is used only when TIMESTEP = SPECI-FIED.

AUTOMATIC [OFF]Enables automatic incrementation control during analysis. {OFF/ATS}

OFF No automatic incrementation, user-defined timestep sequence isfollowed.

ATS Automatic timestep control is enabled, see MAXSUBD parameterbelow.

SOLVER [SPARSE]Selects the type of solution algorithm used to solve the equilibrium equation system.{SPARSE/ITERATIVE}

SPARSE A sparse-matrix solver is used.

ITERATIVE An iterative solution (incomplete Cholesky preconditioned conjugategradient method) is used.

TMC-CONTROL



Note: See command TMC-SOLVER ITERATIVE for input of parameters controlling theoperation of the iterative solver.

HEAT-MATRIX [CONSISTENT]Selects the type of heat capacity matrix to be used in transient analysis. {CONSISTENT/LUMPED}

CONSISTENT Consistent heat capacity matrix.

LUMPED Lumped (diagonalized) heat capacity matrix.

METHOD [BACKWARD-EULER]Time integration method used in transient analysis. {BACKWARD-EULER / FORWARD-EULER / TRAPEZOIDAL / ALPHA / ALPHA / COMPOSITE}

BACKWARD-EULER Euler backward integration.

FORWARD-EULER Euler forward integration.

TRAPEZOIDAL Trapezoidal rule.

ALPHA Alpha-family method.

COMPOSITE Bathe composite method.

MAXSUBD [10]Specifies the maximum permitted subdivision of any given timestep when AUTOMATIC =ATS, i.e., for a time step of magnitude ∆T, the algorithm will not attempt to subdivide below atime step of magnitude ∆T/2MAXSUBD.

ALPHA [1.0]

Time integration parameter for METHOD=ALPHA. {0 ≤ ALPHA ≤ 1.0}

TSTART [DEFAULT]Start time of the heat transfer solution. DEFAULT indicates a start time that is the start timefor the structural solution. {DEFAULT / TSTART ≥ 0.0}

GAMMA [0.5]Coefficient used for the Bathe composite time integration method.{0.0 < GAMMA < 1.0}

TMC-CONTROL


Chap. 5 Control data TMC-CONTROL

TEMP-CUTOFF [NO]If TEMP-CUTOFF = YES, temperature CUT-OFF will be used. {NO/YES}

CUTOFF [1.0D30]Temperature will be cut-off above CUT-OFF.

TEMP-RELAX [1.0]Temperature relaxation factor to overcome convergence difficulties.{0.0 ≤ TEMP-RELAX ≤ 1.0}

HEAT-RELAX [1.0]Generated heat relaxation factor to overcome convergence difficulties.{0.0 ≤ TEMP-RELAX ≤ 1.0}






ANALYSIS DYNAMIC-DIRECT-INTEGRATION METHOD DELTA ALPHATHETA TIMESTEP NCRSTEPCRSTEP MASS-SCALE DTMIN1DTMIN2 GAMMA

ANALYSIS DYNAMIC-DIRECT-INTEGRATION specifies time integration parameters for adynamic, direct time-integration, analysis.

METHOD [NEWMARK]Selects the method to be used for direct time integration, see Theory and Modeling Guide.{NEWMARK/CENTRAL-DIFFERENCE/WILSON/COMPOSITE}

NEWMARK Newmark method.

CENTRAL-DIFFERENCE Central difference method (explicit analysis).

WILSON Wilson-θ method.

COMPOSITE Bathe composite method.

Note: For the central-difference method:- substructures and cyclic symmetry cannot be used;- a lumped mass matrix is used automatically;- there are further restrictions on analysis features, material models and element

settings. See the Theory and Modeling Guide for more details.

Note: The Wilson-θ method cannot be used for nonlinear analysis.

DELTA [0.5]ALPHA [0.25]Coefficients for the Newmark method. {DELTA ≥ 0.5}{ALPHA > 0.0}The following choices are often employed:

DELTA = 0.5, ALPHA = 0.25 The constant-average-acceleration scheme(also termed the trapezoidal rule).

DELTA = 0.5, ALPHA = 0.5 Good for contact-impact problems.

Note: The Newmark method is unconditionally stable in linear analysis, if:DELTA ≥ 0.5, ALPHA ≥ 0.25 × (DELTA + 0.5)2

THETA [1.4]Coefficient for the Wilson-θ method. {1.39 ≤ THETA ≤ 2.01}

ANALYSIS DYNAMIC-DIRECT-INTEGRATION


Sec. 5.2 Analysis detailsANALYSIS DYNAMIC-DIRECT-INTEGRATION

TIMESTEP [TOTALTIME]Indicates the method of time step selection for explicit analysis (i.e., METHOD = CENTRAL-DIFFERENCE). {USER/AUTOMATIC/TOTALTIME}

USER User defined timesteps. (See TIMESTEP )

AUTOMATIC ADINA automatically calculates the time step magnitude in explicitanalysis based on stability considerations. The total number of timesteps specified in the TIMESTEP command will be used.

TOTALTIME The magnitude of the timesteps is calculated automatically by theprogram. The analysis runs until the total time specified in theTIMESTEP command is reached. The number of steps specified in theTIMESTEP command determines how often results are saved to theporthole file.

NCRSTEP [1]Defines how often the time step magnitude is updated in explicit analysis (the time stepmagnitude is updated every NCRSTEP step(s)). This parameter is not used ifTIMESTEP=USER.{NCRSTEP = 1, 2, 3, ...}

CRSTEP [0.0]Factor used to scale the calculated time step in transient explicit analysis. This parameter isnot used if TIMESTEP=USER. {0.0 ≤ CRSTEP ≤ 4.0}

For the default value CRSTEP = 0.0, CRSTEP will be set to 1.0 always.

MASS-SCALE [1.0]Specifies the factor to scale the mass (densities) of the entire model (at the beginning of theanalysis) to increase the critical time step size required for stability when the explicit timeintegration scheme is used. See caution below. {≥ 1.0}

DTMIN1 [0.0]The minimum time step size used to determine if mass scaling will be applied to elements (atthe beginning of the analysis) whose critical time step size is smaller than DTMIN1. Theamount of mass scaling is calculated for each element so that the critical time step size isequal to DTMIN1. See caution below. {≥ 0.0}

DTMIN2 [0.0]The minimum time step size used to determine if an element will be removed in an explicit timeintegration analysis. In explicit time integration, the smaller an element size is, the smaller will



the critical time step size be. If the critical time step size for an element is smaller thanDTMIN2, the element will be removed in the analysis. See caution below. {≥ 0.0}

Notes:� MASS-SCALE, DTMIN1 and DTMIN2 may be used together.� DTMIN1 and DTMIN2 are applied after MASS-SCALE is applied.� If DTMIN1 and DTMIN2 are both used, DTMIN1 should be greater than DTMIN2. If

DTMIN2 ≥ DTMIN1 is specified, DTMIN1 will be ignored.

CAUTION:Specifying MASS-SCALE > 1.0, DTMIN1 > 0.0 or DTMIN2 > 0.0 may change the modelsignificantly. Hence, extra care should be exercised in examining the results when any ofthese parameters are used.

GAMMA [0.5]Coefficient for the Bathe composite method. {0.0 < GAMMA < 1.0}

Note: The Bathe composite method uses Newmark coefficients with the additionalconstant GAMMA. It is recommended to use the default value of GAMMA(i.e., 0.5).

Auxiliary commands

LIST ANALYSISLists the data for the current analysis option.

ANALYSIS DYNAMIC-DIRECT-INTEGRATION






FREQUENCIES METHOD NEIGEN NMODE IPRINT RIGID-BODYRSHIFT CUTOFF NITEMM NVECTOR STURM-CHECKACCELERATE TOLERANCE STARTTYPE NSTVECTINTERVAL FMIN FMAX MODALSTRESSES STATICNSHIFT NSHIFT-BLOCK

FREQUENCIES specifies control data for a frequency solution to be carried out for thestructure linearized at time TSTART. In order to input data via this command the MASTERcommand ANALYSIS parameter should have been previously set to FREQUENCIES,MODAL-TRANSIENT, MODAL-PARTICIPATION-FACTORS or MODAL-STRESSES.

METHOD [SUBSPACE-ITERATION]Specifies the method of frequency calculation. {DETERMINANT-SEARCH/SUBSPACE-ITERATION/INPUT/LANCZOS-ITERATION}

Please consult the Theory and Modeling Guide for a further description of these methods.The selection METHOD = INPUT will cause ADINA to read frequencies and mode-shapesfrom file, e.g., for use in a subsequent mode superposition analysis; all other parameters ofthis command are ignored.

NEIGEN [1]The number of frequencies and corresponding mode shapes to be calculated. The actualnumber of frequencies calculated may be reduced whenever the maximum, specified either bythe cut-off frequency (CUTOFF) or the upper bound on the solution interval (FMAX � for thesubspace-iteration method), has been exceeded.

NMODE [0]The number of mode shapes to be printed in the results output file. Frequency results arealways printed. {≤ NEIGEN}

IPRINT [NO]Specifies whether or not intermediate solution information is printed. Such information maybe of interest in tracing the solution behavior. {YES/NO}

RIGID-BODY [NO]Specifies whether or not rigid-body modes are allowed. Should be used when the lowestfrequency may be zero, or any part of the model would be insufficiently supported if allcontact, mesh glueing and generalized constraints are removed. {YES/NO}

RSHIFT [0.0]The rigid body mode shift to be applied when RIGID-BODY = YES. RSHIFT = 0.0 will resultin a value being automatically determined by the analysis program. {≤ 0.0}

FREQUENCIES



CUTOFF [1.0E8]The cut-off circular frequency (unit = radians/time). The frequency calculation is stopped iffrequency CUTOFF has been exceeded.

NITEMM [24 or 60]The maximum number of iterations per eigenpair (frequency, mode shape) allowed duringsolution. Default = 60 if METHOD = DETERMINANT; otherwise, default = 24.

NVECTOR [DEFAULT]The number of iteration vectors to be used simultaneously by the subspace-iteration method.

DEFAULT = min(2×NEIGEN, NEIGEN+8) if INTERVAL = NO = 16 if INTERVAL = YES

STURM-CHECK [NO]Specifies whether or not a Sturm-sequence check is to be performed to verify that all thelowest frequencies have been found by the subspace-iteration method. {YES/NO}

ACCELERATE [NO]Specifies whether or not acceleration schemes (shifting and overrelaxation) are to be em-ployed during subspace-iteration. Note that if acceleration is applied, then theSturm-sequence check is automatically applied.Furthermore, if NVECTOR < min(2×NEIGEN, NEIGEN+8) then acceleration is always used.{YES/NO}

TOLERANCE [DEFAULT]The convergence tolerance used by the subspace-iteration and the Lanczos-iterationmethods in the iteration for frequency values.

DEFAULT = 1.0E-6 if INTERVAL = NO and METHOD = SUBSPACE-ITERATION = 1.0E-10 if INTERVAL = YES and METHOD = SUBSPACE-ITERATION = 1.0E-9 if METHOD = LANCZOS-ITERATION

STARTTYPE [LANCZOS]Specifies the method of generating starting vectors for the subspace-iteration method.

STANDARD Standard starting vectors are used.LANCZOS The Lanczos method is used to generate starting vectors.

NSTVECT [0]The number of user-provided starting iteration vectors for the subspace-iteration method.The NSTVECT vectors, read from file, replace the first NSTVECT starting vectors generatedby the analysis program.

FREQUENCIES



INTERVAL [NO]Specifies whether or not the lowest frequency calculation by the subspace-iteration methodand the Lanczos iteration method is confined to a specified interval (FMIN, FMAX). {YES/NO}

FMIN [0.0]If INTERVAL = YES, FMIN gives the lower bound frequency (unit = radians/time) of theinterval in which the subspace-iteration method and the Lanczos iteration method calculatesthe lowest frequencies.

FMAX [DEFAULT]If INTERVAL = YES, FMAX gives the upper bound frequency (unit = radians/time) of theinterval in which the subspace-iteration method and the Lanczos iteration method calculatesthe lowest frequencies. DEFAULT = CUTOFF.

MODALSTRESSES [NO]Indicates whether or not to calculate modal stresses for post-processing. {YES/NO}

STATIC [NO]Indicates whether or not to perform static analysis load-steps following the frequency/ mode-shape calculation. {YES/NO}

NSHIFT [AUTO]Specifies whether to use automatic shifting procedure for the Lanczos-iteration method.When the number of frequencies (NEIGEN) to be calculated is large, using the automaticshifting procedure can reduce the computation time significantly. If NSHIFT=AUTO, then theprocedure is used if (NSHIFT-BLOCK * 2) ≤ NEIGEN. Currently, this procedure is applicablefor frequency calculations for potential-based fluid only. {AUTO/YES/NO}

NSHIFT-BLOCK [50]Specifies the number of frequencies to be calculated for each shift in the Lanczos-iterationmethod. {>0}

Note: The parameters NVECTOR, ACCELERATE, STARTTYPE, and NSTVECT are appli-cable only to the subspace-iteration method. They are ignored by both the determi-nant-search and Lanczos methods. The parameters TOLERANCE, INTERVAL, FMIN,FMAX and STURM-CHECK are also ignored by the determinant-search method.

Auxiliary commands

LIST FREQUENCIESLists the current setting of parameters for a frequency solution if previously enabled viathe command MASTER ANALYSIS = FREQUENCIES.

FREQUENCIES






BUCKLING-LOADS NEIGEN NMODE IPRINT ITEMM NVECTORTOLERANCE S TARTTYPE NSTVECTMODALSTRESSES METHOD EIGENSOLVER

BUCKLING-LOADS specifies control data for evaluating static buckling loads and correspond-ing mode shapes based on the linearized state of stress and deformation of the model at timeTSTART+∆t, following an evaluation of the static response at the same time, i.e., after the firststep of the analysis. In order to input data via this command, the MASTER command ANALY-SIS parameter should have been previously set to BUCKLING-LOADS.

The restart option may be used to perform a buckling analysis for the linearized system at step�n�, where n > 1. The first run solves for the static response after (n-1) steps. The restart runthen enables the buckling analysis to solve for the buckling response linearized at step �n�.

The solution of the eigenvalue problem required for the determination of critical load factorsemploys the subspace-iteration or Lanczos-iteration method (see FREQUENCIES).The Sturm-sequence check is applied to verify that the lowest required buckling loads havebeen evaluated. The acceleration (shifting and over-relaxation) schemes are used if thesubspace-iteration method is chosen.

NEIGEN [1]The number of lowest positive critical buckling loads (i.e., acting in the direction of theapplied loads for the first solution step), and corresponding mode shapes to be calculated.

NMODE [0]The number of mode shapes to be printed in the results output file. The critical buckling loadfactors are always printed. {≤ NEIGEN}

IPRINT [NO]Specifies whether or not intermediate solution information is printed. Such information maybe of interest in tracing the solution behavior. {YES/NO}

NITEMM [40]The maximum number of iterations per eigenpair (frequency, mode shape) allowed duringsolution for the subspace-iteration method.

NVECTOR [DEFAULT]The number of iteration vectors to be used simultaneously for the subspace-iteration method.{≥ 0}DEFAULT = NEIGEN*3 + 18

BUCKLING-LOADS



TOLERANCE [1.0E-6]The convergence tolerance used by the subspace-iteration method in the iteration forfrequency values.

STARTTYPE [LANCZOS]Specifies the method of generating starting vectors for the subspace-iteration method.

STANDARD Standard starting vectors are used.

LANCZOS The Lanczos method is used to generate starting vectors.

NSTVECT [0]The number of user-provided starting iteration vectors for the subspace-iteration method.The NSTVECT vectors, read from file, replace the first NSTVECT starting vectors generatedby the analysis program.

MODALSTRESSES [NO]Indicates whether or not to calculate modal stresses for post-processing. {YES/NO}

METHOD [CLASSICAL]Buckling analysis method. {CLASSICAL/SECANT}

EIGENSOLVER [SUBSPACE]Eigenvalue solver method. {SUBSPACE/LANCZOS}

Auxiliary commands

LIST BUCKLING-LOADSLists the current setting of parameters for a buckling analysis if enabled via the commandMASTER ANALYSIS = BUCKLING-LOADS.

BUCKLING-LOADS



ANALYSIS MODAL-TRANSIENT NMODES ERROR-INTERVAL FREQUENCIES

ANALYSIS MODAL-TRANSIENT provides control data for a mode superposition analysis.

NMODES [0]Number of modes for a mode superposition analysis.

Note that when NMODES = 0 by default, the number of modal participation factors calculatedby ADINA is the number of requested modes in the FREQUENCIES command.

ERROR-INTERVAL [0]Interval of calculating error in external load representation in mode superposition analysis.

0 No external load error calculation.

> 0 Calculate relative error at this interval of timesteps.

FREQUENCIES [YES]Indicates whether ADINA is to first perform a frequency analysis (in the same run). Other-wise the frequencies and mode shapes are assumed available, on file, from a previousanalysis. See command FREQUENCIES for control of the frequency/mode-shape calcula-tions. {YES/NO}

ANALYSIS MODAL-TRANSIENT



ANALYSIS MODAL-PARTICIPATION-FACTORS EXCITATION NMODESSTATIC CORRECTIONFREQUENCIES DUSIZE

Provides control data for a modal participation factor analysis.

EXCITATION [GROUND-MOTION]Defines the type of excitation load. {GROUND-MOTION/APPLIED-LOAD}

NMODES [0]Number of modes for a modal participation factor analysis. Note that when NMODES = 0 bydefault, the number of modal participation factors calculated by ADINA is the number ofrequested modes in the FREQUENCIES command.

STATIC [NO]Indicates whether static load-step calculations are to be performed. {YES/NO}

CORRECTION [NO]Indicates whether static-correction calculations are to be performed. Calculations of residualdisplacements, accelerations, forces, and stresses will be made to evaluate the contribution tothe response from the remaining modes above NMODES included in a response spectrumanalysis assuming this contribution is static, thus not dynamically amplified. {YES/NO}

FREQUENCIES [YES]Indicates whether ADINA is to first perform a frequency analysis (in the same run). Other-wise the frequencies and mode shapes are assumed available, on file, from a previousanalysis. See command FREQUENCIES for control of the frequency/mode-shape calcula-tions. {YES/NO}

DUSIZE [0.0]This parameter is used in nonlinear analysis to specify the size of the displacement perturba-tion used in calculating nonlinear modal stresses. The unit of DUSIZE is length.

If DUSIZE=0.0, then ADINA computes the displacement perturbation factor automati-cally. If you specify DUSIZE, you should choose DUSIZE so that if the mode shapes arescaled to be of size DUSIZE, the deformations corresponding to the scaled mode shapes aresmall.

When the analysis is not a restart analysis, or if the displacements at restart time TSTARTare zero, it is recommended that you enter DUSIZE. This is because ADINA's automaticcalculation can lead to very small or very large displacement perturbations.

When the analysis is a restart analysis and the displacements at restart time TSTART arenonzero, ADINA's automatic calculation of DUSIZE is usually quite good, however you canalso enter DUSIZE if desired.

See the ADINA Theory and Modeling Guide, Section 6.2.4 for more information.

ANALYSIS MODAL-PARTICIPATION-FACTORS



ANALYSIS MODAL-STRESSES FREQUENCIES DUSIZE

ANALYSIS MODAL-STRESSES provides control data for modal stress calculations.

FREQUENCIES [YES]Indicates whether ADINA is to first perform a frequency analysis (in the same run). Otherwisethe frequencies and mode shapes are assumed available, on file, from a previous analysis.See command FREQUENCIES for control of the frequency/mode-shape calculations. {YES/NO}

DUSIZE [0.0]This parameter is used in nonlinear analysis to specify the size of the displacement perturba-tion used in calculating nonlinear modal stresses. The unit of DUSIZE is length.

If DUSIZE=0.0, then ADINA computes the displacement perturbation factor automatically.If you specify DUSIZE, you should choose DUSIZE so that if the mode shapes are scaled tobe of size DUSIZE, the deformations corresponding to the scaled mode shapes are small.

When the analysis is not a restart analysis, or if the displacements at restart time TSTART arezero, it is recommended that you enter DUSIZE. This is because ADINA's automatic calcula-tion can lead to very small or very large displacement perturbations.

When the analysis is a restart analysis and the displacements at restart time TSTART arenonzero, ADINA's automatic calculation of DUSIZE is usually quite good, however you canalso enter DUSIZE if desired.

See the ADINA Theory and Modeling Guide, Section 6.2.4 for more information.

ANALYSIS MODAL-STRESSES


Sec. 5.3 Options

KINEMATICS DISPLACEMENTS STRAINS PRESSURE-UPDATE INCOMPATIBLE-MODES UL-FORMULATION RIGIDLINK-6DOF

KINEMATICS defines the kinematic formulation. An individual element group may select adifferent formulation via the appropriate EGROUP command.

DISPLACEMENTS [SMALL]

SMALL Small displacements and rotations are assumed.

LARGE Large displacements and rotations are assumed.

STRAINS [SMALL]

SMALL Small strains are assumed.

LARGE Large strains are assumed.

Note: Large strains are only admissible for element groups of type TWODSOLID,THREEDSOLID and SHELL with certain material models � please refer to the descrip-tions of the MATERIAL parameter in the commands EGROUP TWODSOLID, EGROUPTHREEDSOLID AND EGROUP SHELL.

PRESSURE-UPDATE [NO]Specifies whether pressure correction terms are added to the shell stiffness matrix in fre-quency analysis. Note that this setting cannot be overridden at the element group level.{NO/YES}

INCOMPATIBLE-MODES [AUTOMATIC]Specifies whether incompatible modes are included in formulation of 4-node 2D and shellelements and 8-node 3D elements. The default AUTOMATIC sets INCOMPATIBLE-MODES =NO for explicit analysis, and otherwise sets INCOMPATIBLE-MODES = YES.{AUTOMATIC/NO/YES}

UL-FORMULATION [DEFAULT]Specifies the large strain formulation to be used for 2D solid, 3D solid and shell elements.{DEFAULT/ULH/ULJ}

DEFAULT ULJ is used if explicit transient analysis or rigid-target contact algorithm ofversion 8.3 is used. Otherwise, ULH is used.

ULH Updated Lagrangian Hencky formulation is used.

ULJ Updated Lagrangian Jaumann formulation is used.

KINEMATICS


Chap. 5 Control data KINEMATICS

RIGIDLINK-6DOF [NO]Specifies whether all six degrees of freedom are active for a master node on a rigid link whenthe node is also attached to an element (e.g., 3D solid) where not all six degrees of freedomare active. {NO/ALL}

NO Only the active degrees of freedom of the attached element are assigned tothe master node on a rigid link.

ALL All six degrees of freedom are active for the master nodes of a rigid link.


Sec. 5.3 Options




MASS-MATRIX TYPE ETA

MASS-MATRIX selects the type of mass matrix to be used in dynamic analysis.

For static analyses, the mass matrix type is used only in evaluating centrifugal and mass-proportional loads. See the Theory and Modeling Guide.

TYPE [CONSISTENT]Selects the type of mass matrix.

LUMPED Lumped (diagonalized) mass matrix.

CONSISTENT Consistent mass matrix.

Note: The lumped mass matrix is always used in explicit dynamic analysis, and insubstuctures.

Note: The element integration orders specified for element groups do not affect the calcula-tion of the mass matrix.

ETA [DEFAULT]Multiplier (≥ 0.0) for the lumped rotational masses of all BEAM, ISOBEAM, PLATE, SHELL,and PIPE elements. ETA is applicable only if a dynamic analysis is to be performed with alumped mass matrix, see Theory and Modeling Guide.

DEFAULT =0.0 for the NEWMARK or WILSON-θ integration method and forfrequency analysis

1.0 for the central difference (explicit) integration method.

Auxiliary commands

LIST MASS-MATRIXLists the current mass matrix type.

MASS-MATRIX


Sec. 5.3 Options

RAYLEIGH-DAMPING ALPHA BETA

egroupi αααααi βββββi

RAYLEIGH-DAMPING specifies coefficients which define a consistent damping matrix C as alinear combination of the system mass matrix M and the system stiffness matrix K, i.e.,

C M K C C= ⋅ + ⋅ + +α β conc gen

where

M = Total system mass matrix (lumped or consistent), including any specifiedconcentrated masses.

K = Stiffness matrix based on the elements in all element groups.

α, β = Rayleigh damping factors.

Cconc = Damping matrix contribution from concentrated dampers (see DAMPERS ).

Cgen = Damping matrix contribution from GENERAL or SPRING elements.

See the Theory and Modeling Guide for further details on the use of the damping matrix.

Different Rayleigh damping coeffients may be specified for individual element groups. Thedefault coefficients are given by parameters ALPHA, BETA.

ALPHA [0.0]The Rayleigh damping factor α.

BETA [0.0]The Rayleigh damping factor β.

Note: The specification of Rayleigh damping is ignored for both a frequency analysis and amode superposition analysis.

egroupiLabel number of an element group.

αααααi [ALPHA]Raleigh damping factor α for element group egroupi.

RAYLEIGH-DAMPING



βββββ i [BETA]Raleigh damping factor β for element group egroupi.

Auxiliary commands

LIST RAYLEIGH-DAMPINGLists the Rayleigh damping factors α, β.

DELETE RAYLEIGH-DAMPINGSets the Rayleigh damping factors α, β to 0.0.

RAYLEIGH-DAMPING


Sec. 5.3 Options

MODAL-DAMPING

modei factori

MODAL-DAMPING defines modal damping factors to be used in mode superpositionanalysis.

modeiThe mode number.

factoriDamping factor for mode �modei�, representing the fraction of critical damping. For example,factori = 0.1 gives 10% damping for the mode.

Note: The mode superposition analysis option must be enabled for the data from thiscommand to be considered. See MASTER.

Note: At least NMODES damping factors should be given, where NMODES is thenumber of modes participating in the mode superposition analysis. SeeANALYSIS MODAL-TRANSIENT.

Auxiliary commands

LIST MODAL-DAMPINGLists the assigned modal damping factors.

DELETE MODAL-DAMPINGDeletes all modal damping factors.

MODAL-DAMPING





Sec. 5.3 Options

FAILURE MAXSTRESS NAME SUBTYPE SIGAMT SIGAMC SIGBMTSIGBMC SIGCMT SIGCMC SIGABM SIGACMSIGBCM

FAILURE MAXSTRESS defines a failure criterion of maximum stress type for SHELL elements(EGROUP SHELL) in conjunction with material models: ISOTROPIC, ORTHOTROPIC,THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide fordetails.

NAME [(current highest failure label number) + 1]Label number of the failure criterion to be defined. If the label number of an existing failurecriterion is given, then the previous failure criterion definition is overwritten.

SUBTYPE [STRESS2]Indicates the stress/strain conditions.

STRESS2 Plane stress.

STRESS3 General 3-D stress.

SIGAMT [0.0]Maximum allowable tension stress in material a-direction.

SIGAMC [0.0]Maximum allowable compression stress in material a-direction.

SIGBMT [0.0]Maximum allowable tension stress in material b-direction.

SIGBMC [0.0]Maximum allowable compression stress in material b-direction.

SIGCMT [0.0]Maximum allowable tension stress in material c-direction.

SIGCMC [0.0]Maximum allowable compression stress in material c-direction.

SIGABM [0.0]Maximum allowable shear stress in the material ab-plane.

SIGACM [0.0]Maximum allowable shear stress in the material ac-plane.

FAILURE MAXSTRESS



SIGBCM [0.0]Maximum allowable shear stress in the material bc-plane.

Auxiliary Commands

LIST FAILURE FIRRST LASTDELETE FAILURE FIRST LAST

FAILURE MAXSTRESS


Sec. 5.3 Options

FAILURE MAXSTRAIN NAME SUBTYPE EPSAMT EPSAMC EPSBMTEPSBMC EPSCMT EPSCMC EPSABM EPSACMEPSBCM

FAILURE MAXSTRAIN defines a failure criterion of maximum strain type for SHELL elements( EGROUP SHELL ) in conjunction with material models: ISOTROPIC, ORTHOTROPIC,THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide fordetails.

NAME [current highest failure label number) + 1]Label number of the failure criterion to be defined. If the label number of an existing failurecriterion is given, then the previous failure criterion definition is overwritten.

SUBTYPE [STRESS2]Indicates the stress/strain conditions



EPSAMT [0.0]Maximum allowable tension strain in material a-direction.

EPSAMC [0.0]Maximum allowable compression strain in material a-direction.

EPSBMT [0.0]Maximum allowable tension strain in material b-direction.

EPSBMC [0.0]Maximum allowable compression strain in material b-direction.

EPSCMT [0.0]Maximum allowable tension strain in material c-direction.

EPSCMC [0.0]Maximum allowable compression strain in material c-direction.

EPSABM [0.0]Maximum allowable shear strain in the material ab-plane.

EPSACM [0.0]Maximum allowable shear strain in the material ac-plane.

FAILURE MAXSTRAIN



EPSBCM [0.0]Maximum allowable shear strain in the material bc-plane.

Auxiliary Commands

LIST FAILURE FIRST LASTDELETE FAILURE FIRST LAST

FAILURE MAXSTRAIN


Sec. 5.3 Options

FAILURE TSAI-HILL NAME SUBTYPE SIGAM SIGBM SIGCMSIGABM SIGACM SIGBCM

FAILURE TSAI-HILL defines a failure criterion of type Tsai-Hilltype for SHELL elements ( EGROUP SHELL ) in conjunction with material models: ISOTROPIC, ORTHOTROPIC,THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide fordetails.





SIGAM [0.0]Maximum allowable stress in material a-direction.

SIGBM [0.0]Maximum allowable stress in material b-direction.

SIGCM [0.0]Maximum allowable stress in material c-direction.




Auxiliary Commands


FAILURE TSAI-HILL



FAILURE TSAI-WU NAME SUBTYPE SIGAMT SIGAMC SIGBMTSIGBMC SIGCMT SIGCMC SIGABMSIGACM SIGBCM FAB FAC FBC HOFFMAN

FAILURE TSAI-WU defines a failure criterion of type Tsai-Wu type for SHELL elements ( EGROUP SHELL ) in conjunction with material models: ISOTROPIC, ORTHOTROPIC,THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide fordetails.









SIGCMT [0.0]Maximum allowable tension stress in material c-direction.

SIGCMC [0.0]Maximum allowable compression stress in material c-direction.



FAILURE TSAI-WU


Sec. 5.3 Options


FAB [0.0]Interaction strength between a- and b- material directions.

FAC [0.0]Interaction strength between a- and c- material directions.

FBC [0.0]Interaction strength between b- and c- material directions.

HOFFMAN [YES]Specifies whether or not the Hoffman convention should be used. {YES/NO}

Auxiliary Commands


FAILURE TSAI-WU



FAILURE HASHIN NAME SIGAMT SIGAMC SIGBMT SIGBMCSIGABM SIGTRM

FAILURE HASHIN defines a failure criterion of type Hashin for SHELL elements ( EGROUPSHELL ) in conjunction with material models: ISOTROPIC, ORTHOTROPIC,THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide fordetails.






SIGABM [0.0]Maximum allowable shear stress in ab-plane.

SIGTRM [0.0]Maximum allowable transverse stress.

Auxiliary Commands


FAILURE HASHIN


Sec. 5.3 Options

FAILURE USERSUPPLIED NAME NSURFACE

coef1k coef2k coef3k coef4k coef5k coef6k (k = 8×NSURFACE)

FAILURE USERSUPPLIED defines a user supplied failure criterion for SHELL elements ( EGROUP SHELL ) in conjunction with material models: ISOTROPIC, ORTHOTROPIC,THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide fordetails.


NSURFACE [1]The number of failure surfaces. {≤ 4}

coef1kcoef2kcoef3kcoef4kcoef5kcoef6kFor each failure surface 8 data input lines are entered in the following order:

1: α1...α6 Coefficients αi of the stress condition.

2: F1...F6 Linear terms coefficients Fi of the failure surface

3: F11...F16 Quadratic terms coefficients F1j of the failure surface.


...


Auxiliary Commands


FAILURE USERSUPPLIED



TEMPERATURE-REFERENCE TINIT TLOAD TGINIT TGLOAD NCURTL NCURTGL

TEMPERATURE-REFERENCE defines reference temperatures and temperature gradients, forboth initial thermal conditions and thermal loads.

TINIT [0.0]The initial temperature of a structure, in whatever temperature units you employ. Differinginitial temperatures may be specified by commands INITIAL-CONDITION, SET-INITCONDITION.

TLOAD [0.0]The prescribed reference temperature for a thermal load on a structure, in whatever tempera-ture units you employ. Differing prescribed temperatures may be specified by commandsLOAD TEMPERATURE, APPLY-LOAD.

TGINIT [0.0]The initial temperature gradient through the thickness of a shell type structure, in whatevertemperature/length units you employ. Differing initial temperature gradients may be specifiedby commands INITIAL-CONDITION, SET-INITCONDITION.

TGLOAD [0.0]The prescribed reference temperature gradient for a thermal load on a shell type structure, inwhatever temperature/length units you employ. Differing prescribed temperature gradientsmay be specified by commands LOAD TGRADIENT, APPLY-LOAD.

NCURTL [0]Timefunction label number for the reference load temperature.

NCURTGL [0]Timefunction label number for the reference load temperature gradient.

Auxiliary commands

LIST TEMPERATURE-REFERENCELists the reference temperatures and temperature gradients.

TEMPERATURE-REFERENCE


Sec. 5.4 Solver details

SOLVER ITERATIVE MAX-ITERATIONS EPSIA EPSIB EPSIISHIFT NVEC

SOLVER ITERATIVE defines control data for the iterative solution of the matrix system ofequilibrium equations.

This command is applicable when the iterative solver is used, i.e., SOLVER=ITERATIVE,MULTIGRID or 3D-ITERATIVE in the MASTER command.

MAX-ITERATIONS [0]The maximum number of iterations for the iterative solver to converge. If MAX-ITERA-TIONS=0, then MAX-ITERATIONS=1000 is used if SOLVER=ITERATIVE or MULTIGRIDand MAX-ITERATIONS=200 if SOLVER=3D-ITERATIVE. {MAX-ITERATIONS ≥ 0}

EPSIA [1.0E-6]EPSIB [1.0E-4]EPSII [1.0E-8]Convergence tolerances for the iterative solver, see the Theory and Modeling Guide forfurther details. Smaller tolerances than the defaults may be required for contact analysis.

Note: For the 3D-iterative solver, only EPSIB is used in the convergence checking.

SHIFT [1.0]Factor used to make preconditioning more effective within the iterative solver. Values ofSHIFT > 1.0 make the preconditioning matrix more diagonally dominant. (Not used for the3D-iterative solver.)

NVEC<not currently used>

Note: The shift factor SHIFT can be effective with an ill-conditioned stiffness matrix, such asmay be encountered with a shell structure, which is much stiffer in membrane actionthan in bending action. A typical value of SHIFT = 1.02 has proved beneficial in thissituation.

Auxiliary commands

LIST SOLVERLists the type of SOLVER (all types available as described in the MASTER command,SOLVER parameter) enabled, and gives the corresponding control parameters, if any.

SOLVER ITERATIVE



PPROCESS NPROC MINEL MAXEL

PPROCESS specifies control data for parallel processing solutions. It allows for the splittingup of element groups into smaller sub-groups, i.e., the model is partitioned for distributedsolution.

NPROC [0]Number of processors used. Equivalently, the number of subgroups generated for eachelement group. NPROC = 0 indicates single processor solution (equivalent to NPROC = 1), inwhich case this command has no effect - EGCONTROL may be used to effect group splittingin this case.

MINEL [0]Each element group with MINEL or more elements can be split into subgroups. Elementgroups with fewer than MINEL elements are not split. (MINEL = 0 is equivalent to MINEL =10 × NPROC).

MAXEL [999999]Each element group (with MINEL or more elements) is split into I × NPROC subgroups, wherethe multiplier I is chosen so that each subgroup contains no more than MAXEL elements.

Auxiliary commands

LIST PPROCESSLists the current parallel processing control data.

PPROCESS


Sec. 5.4 Solver details

TMC-SOLVER ITERATIVE MAX-ITERATIONS EPSIA EPSIB EPSII SHIFT

TMC-SOLVER ITERATIVE defines control data for the iterative solution of the matrix systemof equilibrium equations for heat transfer analysis. To enable the use of the iterative solver,TMC-CONTROL SOLVER = ITERATIVE must be specified.

MAX-ITERATIONS [1000]The maximum permitted number of iterations for the iterative solver to converge.

EPSIA [1.0E-6]EPSIB [1.0E-4]EPSII [1.0E-8]Convergence tolerances for the iterative solver.

SHIFT [1.0]Factor used to make preconditioning more effective within the iterative solver. Values ofSHIFT > 1.0 make the preconditioning matrix more diagonally dominant.

Auxiliary commands

LIST TMC-SOLVERLists the type of TMC-SOLVER (iterative) enabled, and gives the correspondingcontrol parameters, if any.

TMC-SOLVER ITERATIVE





Sec. 5.5 Automatic control

AUTOMATIC LOAD-DISPLACEMENT POINT DOF DISPLACEMENT ALPHADISPMAX CONTINUE RPRINT TYPENODE SUBDIVISIONS

AUTOMATIC LOAD-DISPLACEMENT defines parameters for the automatic load-displace-ment control (LDC) procedure, whereby the level of externally applied load is continuallyadjusted to solve for the nonlinear equilibrium path of a model until, or beyond, collapse.The LDC method can be used only for static analysis in which there are no thermal effects ortime-dependent material models (i.e., creep or strain rate dependent materials.)

The automatic load-displacement control procedure is enabled when MASTER AUTOMATIC= LDC is specified. (See Theory and Modeling Guide for further details on the operation ofthe LDC method.)

POINTThe label number of a geometry point at which a displacement for the first solution step isprescribed. Note that a node will have to be defined at the point location, otherwise an errormessage will result whenever the model is validated.

DOFIndicates which degree of freedom at the requested point or node has the prescribed valuegiven by parameter DISPLACEMENT. DOF refers to the degree of freedom system (global orskew) at the point or node. {1/2/3/4/5/6}

1 or X-translation2 or Y-translation3 or Z-translation4 or X-rotation5 or Y-rotation6 or Z-rotation

DISPLACEMENTThe prescribed displacement for the degree of freedom DOF at the point or node for the firstsolution step. The value input influences the establishment of successive equilibriumpositions using the LDC method. In particular, the sign (positive/negative) of the value oftenplays a critical role. (See Theory and Modeling Guide for further details).

ALPHA [3.0]Factor used to limit the maximum incremental displacement during a solution step. If theincremented displacements exceed 100 x ALPHA times the displacements in the first timestep, the current time step will be repeated with a reduced load factor.

DISPMAXThe maximum (absolute magnitude) of the displacement for degree of freedom DOF at the

AUTOMATIC LOAD-DISPLACEMENT



point or node which is allowed during analysis. ADINA stops if DISPMAX is exceeded whenthe LDC method is employed. {> 0.0}

CONTINUE [NO]Determines whether or not the solution is terminated when the first critical point on theequilibrium path is reached. {YES/NO}

RPRINT [NO]Determines whether or not the reference load vector corresponding to all mechanical loads isprinted during analysis. {YES/NO}

TYPE [POINT]Selects the type of entity (point or node) indicating the location of the controlling displace-ment. {POINT/NODE}

NODEThe label number of a node at which a displacement for the first solution step is prescribed.

SUBDIVISIONS [10]Number of subdivisions

Note: The LDC method terminates normally when one of the following conditions is met:

The maximum allowed displacement DISPMAX has been attained.The first critical point on the equilibrium path has been reached and (CONTINUE = NO).The requested time step sequence has been completed.The number of subdivisions has been reached without convergence.

Note: The LDC method cannot be used in conjunction with the following analysis types orfeatures:

Dynamic analysisLinearized buckling analysisTime-dependent material models (creep, strain rate dependent)Analysis including temperature effectsUser-supplied or pipe internal pressure loading

Auxiliary commands

LIST AUTOMATICLists the settings for automatic incrementation.

AUTOMATIC LOAD-DISPLACEMENT



AUTOMATIC TIME-STEPPING MAXSUBD ACCURACY DISTOL DTMAXRESTORE RESPS RESFAC DIVFACLSMASSF

AUTOMATIC TIME-STEPPING controls the automatic time-stepping procedure, wherebytimesteps are subdivided in the event of convergence failure within a prescribed number ofequilibrium iterations. See Section 7.2.1 of the Theory and Modeling Guide for further details.

The automatic time-stepping procedure is enabled when MASTER AUTOMATIC = ATS isspecified. When enabled, this procedure will cause ADINA to subdivide the time step whenno iteration convergence is reached in the solution (see commands ITERATION andTOLERANCES ). This procedure is applicable for nonlinear static and implicit transientanalysis.

MAXSUBD [10]

The maximum permitted subdivision of any given time step, i.e., for a time step of magnitude∆t, the algorithm will not attempt to subdivide below a time step of magnitude (∆t/2

MAXSUBD ).

ACCURACYThis parameter is obsolete.

DISTOL [0.001]Maximum allowed displacement difference, used in accuracy checking (i.e., whenACCURACY = YES).

DTMAX [3.0]A factor that limits the maximum time step that can be attained during analysis. If the user-specified time step is ∆t, then the ATS procedure will not use a time step larger than(DTMAX × ∆t). This option can only be used if the ATS setting is to return to the previoustime step before division (RESTORE=YES). {≥ 1.0}

Note:

1. This option is only used in static analysis. It cannot be used in a dynamic analysis or iflow speed dynamics is used (RESPS=YES).

2. This option is not used if more than one time step block has been specified (seeTIMESTEP ).

RESTORE [AUTOMATIC]Indicates whether the original time step, attempted before ATS subdivision occurred, will beused again for the next time step after convergence.

AUTOMATIC TIME-STEPPING



NO The ATS method will continue to use the reduced (subdivided)time step which gave convergence.

YES The ATS method will use the time step which was current prior tosubdivision.

AUTOMATIC The choice of time step restoration is made by ADINA dependent onother problem characteristics. Currently, RESTORE = YES is theautomatic choice for contact problems.

ORIGINAL The ATS method will use a time step size such that the time step willmatch the original next time step specified by the user.

RESPS [NO]Indicates whether or not the low-speed dynamics option is to be used. Applicable only fornonlinear statics analysis.{NO/YES}

RESFAC [1.0E-4]Low-speed dynamics smoothing factor, used when RESPS = YES.

DIVFAC [2.0]Specifies the division factor used to calculate time step subincrements.

LSMASSF [1.0]

Low-speed dynamics inertia factor used when RESPS=YES. {0.0 ≤ LSMASSF ≤ 1.0}

Auxiliary commands

LIST AUTOMATICLists the settings for automatic incrementation.

AUTOMATIC TIME-STEPPING



AUTOMATIC TOTAL-LOAD-APPLICATION NSTEPS MAXITE MAXDISPFSTABF LSDAMPF CTDAMPFLSMASSF

Controls the total-load-application (TLA) procedure. The TLA procedure is used whenAUTOMATIC = TLA or TLA-S is specified in the MASTER command.

The TLA procedure is useful for a nonlinear static analysis where the user does not need toexplicitly specify the time step sequence. The program uses a certain number of time steps (50by default) and automatically increases or reduces the next incremental load level dependingon how well the solution converges in the current step. In addition, stabilization options areapplied when TLA-S (TLA with stabilization) is selected.

When the TLA procedure is used, the program uses the following:

- 50 time steps of step size 0.2 each are used

- the ATS procedure is used with maximum permitted subdivision for any given stepMAXSUBD = 64 (see AUTOMATIC TIME-STEPPING command)

- maximum number of equilibrium iterations is 30

- line search is used

- maximum incremental displacement in each iteration is limited to 5% of largest model length

When TLA-S is selected, the program uses the following in addition to all the above TLAsettings:

- stiffness matrix stabilization factor of 1.0e-10 is used

- low-speed dynamics damping factor of 1.0e-4 is used

- contact damping (automatically calculated by the program) is used

The default values used by TLA and TLA-S that may be overridden are specified in thefollowing parameters.

NSTEPS [50]Specifies the number of time steps to use for the solution. The step size is automaticallyadjusted to obtain a total time of 10.0. {> 0}

MAXITE [30]Specifies the maximum number of equilibrium iterations allowed to achieve convergence in

AUTOMATIC TOTAL-LOAD-APPLICATION



any time step (subdivided or accelerated). {1 ≤ MAXITE ≤ 999}

MAXDISPF [0.05]Specifies the maximum displacement factor. The maximum incremental displacement allowed inany iteration is equal to MAXDISPF * (maximum model dimension) {≥ 0.0}

The default values used by TLA-S that may be overridden are specified in the followingparameters.

STABF [1.0e-10]Specifies the stiffness matrix stabilization factor. If STABF = 0.0, then the stiffness matrixstabilization feature is not used. {≥ 0.0}

LSDAMPF [1.0e-4]Specifies the low-speed dynamics damping factor. If LSDAMPF = 0.0, then the low-speeddynamics option is not used. {≥ 0.0}

CTDAMPF [1.0e-3]Specifies the contact damping factor. The amount of contact damping used in the solution isequal to CTDAMPF * (damping calculated by the program). If CTDAMPF = 0.0, then contactdamping is not used. {≥ 0.0}

LSMASSF [1.0]

Low-speed dynamics inertia factor. {0.0 ≤ LSMASSF ≤ 1.0}


Sec. 5.6 Time dependence

TIMESTEP NAME

nstepi ∆∆∆∆∆ti

TIMESTEP defines a time step sequence which controls the time/load-step incrementationduring analysis. The sequence is defined as a number of periods for which a given number ofconstant time steps is specified. The currently active time step sequence is set to that namedby the TIMESTEP command.

NAME [DEFAULT]Identifying time step sequence name. If the name of an existing time step sequence is given,then the previous sequence definition is appended to.

nstepiNumber of steps to be taken in the ith time step sequence period.

∆∆∆∆∆ti{∆t

i > 0}

Constant time step magnitude, in time units, for the ith time step sequence period.

Note: A database is initialized with a time step sequence named �DEFAULT� which initiallyspecifies a single time step of magnitude 1.0 time units.

Auxiliary commands

LIST TIMESTEP NAMELists a given time step sequence. If no name is specified, then a list of all defined timestep sequence names is given.

DELETE TIMESTEP NAMEDeletes a given time step sequence.

SET TIMESTEP NAMESets the currently active time step sequence, i.e., that which will be passed to the analysisprogram.

SHOW TIMESTEPLists the currently active time step sequence.

TIMESTEP



TIMEFUNCTION NAME IFLIB FPAR1 FPAR2 FPAR3 FPAR4 FPAR5 FPAR6

timei valuei

TIMEFUNCTION defines a timefunction, which may be referenced, e.g., by an applied load.The timefunction curve is defined as piecewise linear through the data points (timei, valuei),and may be multiplied by one of a set of modifying functions.

NAME [(current highest TIMEFUNCTION label number) + 1]Label number of the timefunction to be defined. If the label number of an existingtimefunction is given, then the previous curve definition is overwritten.

IFLIB [1]Indicator for the library modifying function, which multiplies the input timefunction curvevalues.

1 A constant multiplier equal to 1.0, i.e., the input timefunction is unmodified;

f t f t( ) = ( )*

2 A sinusoidal multiplier;

f t f t t( ) = ( ) ⋅ +( )* sin ω φ

3 A short circuit multiplier, type 1;

f t f t a b t( ) = ( ) ⋅ + ⋅ −( )( )* exp τ

4 A short circuit multiplier, type 2;

f t f t I t t( ) = ( ) ⋅ ⋅ ⋅ ⋅ − +( ) + −( ) ⋅ −( )( )

* sin exp sin

µπ

ω φ α τ φ α0

42

where f*(t) is interpolated from the input timefunction curve given by data points

(timei, valuei), and the resulting function f(t) is that used by ADINA.

IFLIB = 3,4 may be used to model the electromagnetic load due to a short circuit current.

FPAR1, ... , FPAR6Modifying function parameters:

TIMEFUNCTION


Sec. 5.7 Iteration

IFLIB = 2: [FPAR1 = 0.0, FPAR2 = 0.0]FPAR1 = Angular frequency, ω, in degrees/(unit time).FPAR2 = Phase angle, φ, in degrees.

IFLIB = 3: [FPAR1 = 0.0, FPAR2 = 0.0, FPAR3 = 1.0]FPAR1 = Constant a.FPAR2 = Constant b.FPAR3 = Constant τ, in time units.

IFLIB = 4: [FPAR5 = 1.0, FPAR6 = 4πππππ ×××××10-7]FPAR1 = RMS of short circuit current, I.FPAR2 = Angular frequency, ω, in degrees/(unit time).FPAR3 = Phase angle, φ, in degrees.FPAR4 = Impedance angle, α, in degrees.FPAR5 = Time constant, τ, in time units.FPAR6 = Magnetic permeability, µ0. (Volt.second / meter.Ampere).

timeiTime at data point �i�.

valueiValue at time �timei�.

Auxiliary commands

LIST TIMEFUNCTION FIRST LASTDELETE TIMEFUNCTION FIRST LAST

TIMEFUNCTION



ITERATION METHOD LINE-SEARCH MAX-ITERATIONS PRINTOUTPLASTIC-ALGORITHM

ITERATION selects the equilibrium iteration scheme to be employed for a non-linear ADINAanalysis.

METHOD [FULL-NEWTON]Selects one of the following iteration schemes (see the Theory and Modeling Guide for adiscussion of iteration schemes).

MODIFIED-NEWTON Modified Newton iteration method.

BFGS BFGS (Broyden-Fletcher-Goldfarb-Shanno) matrix update methodwith line-searches.

FULL-NEWTON Full Newton iteration method.

LINE-SEARCH [DEFAULT]Flags the use of line searches within the iteration scheme. {YES/NO/DEFAULT}

DEFAULT = NO METHOD = MODIFIED-NEWTON/FULL-NEWTON

YES METHOD = BFGS

MAX-ITERATIONS [15]Specifies the maximum number of iterations within a time step. ADINA will terminate execu-tion if this maximum number is reached without achieving convergence, unless one of thefollowing conditions is satisfied:

(a) The automatic time-stepping method has been enabled ( MASTER AUTOMATIC =ATS), whereby the time step is subdivided a given number of times to try to reachconvergence.

(b) The load-displacement control method has been enabled ( MASTER AUTOMATIC =LDC), whereby ADINA will automatically restart from the last step with establishedequilibrium, using different constraint conditions. (A maximum of 10 such restarts willbe attempted per step.)

{1 ≤ MAX - ITERATIONS ≤ 999}

PRINTOUT [LAST]Controls the printout of incremental energy, norms of unbalanced forces and moments, etc.,during equilibrium iteration.

ITERATION


Sec. 5.7 Iteration

NONE No printout.

LAST Printout for last iteration of step.

ALL Printout of intermediate values for each iteration.

Note: For the modified Newton and the BFGS methods of equilibrium iteration,STIFFNESS-STEPS and EQUILIBRIUM-STEPS may be used to restrict the reformationof the stiffness matrix and the equilibrium iteration to only be carried out at specificsolution steps. Otherwise, the stiffness matrix reformation and equilibrium iterationare carried out at every step.

Note: For the full Newton iteration method, equilibrium iteration and stiffness matrix reforma-tion are always carried out at each solution step, and input to STIFF-NESS-STEPS, EQUILIBRIUM-STEPS is effectively ignored.

Note: Full Newton iteration, without line-searches, will be used, regardless of the choicemade by this command, for the following situation: the automatic load-displacementcontrol method (see commands MASTER, AUTOMATIC LOAD-DISPLACEMENT )has been selected.

PLASTIC-ALGORITHM [1]This flag sets the algorithm used in plasticity.

1 Original algorithm

2 Modified algorithm

The PLASTIC-ALGORITHM flag is used under the following conditions:

Implicit time integration (static or dynamic), and

1) METHOD=FULL-NEWTON (with or without line searches), and

2) 2D solid elements, 3D solid elements or shell elements under the following conditions:

- Large displacement, large strain kinematics

- 2D solid elements: ULJ formulation, material PLASTIC-ORTHOTROPIC

- 3D solid elements: ULJ formulation, material PLASTIC-ORTHOTROPIC

- 3D solid elements: ULH formulation, materials MROZ-BILINEAR, PLASTIC-BILINEAR,

ITERATION



PLASTIC-MULTILINEAR

- Shell elements: ULJ formulation, material PLASTIC-ORTHOTROPIC

- Shell elements: ULH formulation, materials PLASTIC-BILINEAR, PLASTIC-MULTILINEAR

For a given load step size, convergence is affected by PLASTIC-ALGORITHM. If theiterations do not converge with PLASTIC-ALGORITHM=1 because the Jacobian determinantin the elements becomes non-positive, switching to PLASTIC-ALGORITHM=2 can some-times obtain convergence. Hence PLASTIC-ALGORITHM=2 allows larger load steps thanPLASTIC-ALGORITHM=1, in general.

But if the iterations already converge with PLASTIC-ALGORITHM=1, switching to PLAS-TIC-ALGORITHM=2 slows down convergence.

The converged solution is not affected by the choice of PLASTIC-ALGORITHM.

The typical use of PLASTIC-ALGORITHM=2 is in metal forming. In metal forming, the metalbeing formed is typically very thin and modeled either with shell elements or with thin 3Delements. PLASTIC-ALGORITHM=2 allows large load steps, and hence fewer load steps, toobtain the solution.

Auxiliary commands

LIST ITERATIONLists the current values of the ITERATION command parameters.


Sec. 5.7 Iteration

STIFFNESS-STEPS

blocki firsti lasti incrementi

STIFFNESS-STEPS controls the output timesteps at which the effective stiffness matrix isreformed by ADINA. This is achieved by specifying a sequence of time step blocks, each ofwhich determines a given frequency of stiffness matrix reformation over a given range oftimesteps.

blockiThe time step block number. The block number must be in the range 1 ≤ blocki ≤ 10, i.e., amaximum of 10 time step blocks can be defined.

firstiThe initial time step number for the time step block blocki. {≥ 1, ≥ last

i-1}

lastiThe final time step number for the time step block blocki. {≥ first

i}

incrementiThe time step increment for the time step block blocki. {≥ 1}

For each time step block, ADINA will re-form the effective stiffness matrix for timesteps

firsti, firsti + incrementi, firsti + (2 × incrementi), ...

and so on until the resulting time step number is greater than or equal to lasti.

Note that the stiffness matrix will be reformed at time step lasti only if (lasti - firsti) is aninteger multiple of incrementi.

The time step block data is checked to see that each block satisfies

lasti ≥ firsti (i = 1, ..., 10)

incrementi ≥ 1

and that adjacent blocks do not overlap, i.e.,

firsti ≥ lasti (i = 2, ..., 10)

If these input conditions are not satisfied, then an error message will be given and the inputwill not be accepted.

STIFFNESS-STEPS



Furthermore, it is required that the highest value for lasti (for the highest block number) begreater than or equal to the total number of solution timesteps (see TIMESTEP ). If not, thenit will be set to that value, with no resulting error condition.

Note: Command is only applicable when modified Newton or BFGS iterations method areused.

Auxiliary commands

LIST STIFFNESS-STEPSDELETE STIFFNESS-STEPS

STIFFNESS-STEPS


Sec. 5.7 Iteration

EQUILIBRIUM-STEPS


EQUILIBRIUM-STEPS controls the output timesteps at which equilibrium iterations areperformed when the modified-Newton or BFGS iteration method is used. This is achieved byspecifying a sequence of time step blocks, each of which determines a given frequency ofequilibrium iteration over a given range of timesteps.

blockiThe time step block number. The block number must be in the range 1 ≤ blocki ≤ 10, i.e., amaximum of 10 time step blocks can be defined.

firstiThe initial time step number for the time step block blocki. {≥ 1; ≥ last

i-1}

lastiThe final time step number for the time step block blocki. {≥ first

i}

incrementiThe time step increment for the time step block blocki. {≥ 1}

For each time step block, ADINA will carry out equilibrium iteration for time steps



Note that equilibrium iteration will be performed at time step lasti only if (lasti - firsti) is aninteger multiple of incrementi.


lasti ≥ firsti (i = 1, ..., 10)

incrementi ≥ 1

and that adjacent blocks do not overlap, i.e.,

firsti ≥ lasti (i = 2, ..., 10)

If these input conditions are not satisfied, then an error message will be given and the inputwill not be accepted.

EQUILIBRIUM-STEPS




Auxiliary commands

LIST EQUILIBRIUM-STEPSDELETE EQUILIBRIUM-STEPS

EQUILIBRIUM-STEPS


Sec. 5.8 Tolerances

TMC-ITERATION METHOD MAX-ITERATIONS STEP-REFORMINGSTEP-EQUILIBRIUM RTOL TMCTOL LINE-SEARCH

TMC-ITERATION selects the equilibrium iteration scheme to be employed for a heat transferanalysis.

METHOD [MODIFIED-NEWTON]Selects the iteration scheme. {MODIFIED-NEWTON /FULL-NEWTON}

MODIFIED-NEWTON Modified Newton iteration.

FULL-NEWTON Full Newton iteration.

MAX-ITERATIONS [15]The maximum number of iterations within a time step.

STEP-REFORMING [1]The maximum number of time steps between reforming conductivity, heat capacity,convection and radiation matrices.

STEP-EQUILIBRIUM [1]The maximum number of time steps between equilibrium iterations.Note: The FULL-NEWTON iteration scheme can be more effective when temperature-dependent material properties are used, or RADIATION elements are present.

RTOL [0.001]RTOL is the temperature convergence tolerance.

TMCTOL [0.0]TMC is the iteration tolerance. The default for TMCTOL is RTOL: this means that ifTMCTOL= 0.0, TMCTOL=RTOL.

LINE-SEARCH [NO]Flags the use of line searches within the iteration scheme. {NO/YES}

Auxiliary commands

LIST TMC-ITERATION

TMC-ITERATION



TOLERANCES GEOMETRIC COINCIDENCE EPSILON SHELL-ANGLEBOLT-ANGLE PHI-ANGLE EMF-DMINNCTOL-TYPE

TOLERANCES GEOMETRIC specifies certain geometric tolerances used during the construc-tion of a model.

COINCIDENCE [1.0E-5]Tolerance used when comparing two locations to see if they are coincident. The defaultvalue is usually sufficient for most models, but may be reduced, e.g, if distinct locations areextremely close in comparison to the overall dimension of the model.

EPSILON [1.0E-9]A small value representing zero in many geometry property tests. This value is not normallyrequired to be changed from the default value.

SHELL-ANGLE [5.0]A small angular measure, in degrees, used in comparing normal vectors to determine thenumber of degrees of freedom to be automatically assigned to a shell midsurface node atwhich shell elements meet.

BOLT-ANGLE [0.5]A small angular measure, in degrees, used in comparing shell element normal vectors todetermine whether any impinging beam-shaft elements give rise to additional constraintsrelating the rotational degree of freedom normal to the shell surface to adjacent translationaldegrees of freedom. If a shell element normal differs from the average normal at a node bymore than BOLT-ANGLE degrees, no additional bolt constraints will be generated.

PHI-ANGLE [30]This parameter is obsolete, but retained for backwards compatibility.Use the PHI-MODEL-COMPLETION command, PHI-ANGLE parameter instead.

EMF-DMIN [0.001]Specifies minmum distance between two electric conductors. If the distance between twoconducting nodes in the model is less than EMF-DMIN, EMF-DMIN will be used.

NCTOL-TYPE [RELATIVE-LOCAL]Option to determine the tolerance for node coincidence checking. {RELATIVE-LOCAL/RELATIVE-GLOBAL/ ABSOLUTE}

A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if

|XB-XA| ≤ COINCIDENCE * XLEN

TOLERANCES GEOMETRIC


Sec. 5.8 Tolerances

|YB-YA| ≤ COINCIDENCE * YLEN |ZB-ZA| ≤ COINCIDENCE * ZLEN

where, (XLEN, YLEN, ZLEN) are decided by the following:

RELATIVE-LOCAL (XLEN, YLEN, ZLEN) are the lengths of the bounding box for thecurrent geometry.

RELATIVE-GLOBAL (XLEN, YLEN, ZLEN) are the lengths of the bounding box for themodel.

ABSOLUTE (XLEN, YLEN, ZLEN) are (1.0, 1.0, 1.0).

Auxiliary commandsLIST TOLERANCES GEOMETRICLists the tolerance data for the model geometry.



TOLERANCES ITERATION CONVERGENCE ETOL RTOL RNORMRMNORM RCTOL DTOL DNORM DMNORMSTOL RCONSM ENLSTH LSLOWER LSUPPERMAXDISP

TOLERANCES ITERATION specifies the convergence criteria and corresponding tolerancescontrolling the equilibrium iteration scheme within the analysis program ADINA.

CONVERGENCE [ENERGY]Selects the convergence criterion to be used, and thereby which of the other parameters areconsidered.

ENERGY Energy convergence (ETOL, STOL).

EF Energy and force (moment) convergence (ETOL, RTOL, RNORM,RMNORM, STOL).

ED Energy and displacement (translation, rotation) convergence (ETOL,DTOL, DNORM, DMNORM, STOL).

FORCE Force (moment) convergence (RTOL, RNORM, RMNORM, STOL).

DISPLACEMENT Displacement (translation, rotation) convergence (DTOL, DNORM,DMNORM, STOL).

In addition, when contact is present, the RCTOL and RCONSM parameters are also used.

ETOL [0.0]Relative energy tolerance. ETOL=0.0 means ETOL=1.0E-6 when the load-displacementcontrol method (MASTER AUTOMATIC=LDC) is used and ETOL=1.0E-3 otherwise.

RTOL [0.01]Relative force and moment tolerance.

RNORM [0.0]Reference force. RNORM is automatically calculated by the program if RNORM=0.0.

RMNORM [0.0]Reference moment. RMNORM is automatically calculated by the program if RMNORM=0.0.

RCTOL [0.05]Relative contact force tolerance.

TOLERANCES ITERATION


Sec. 5.8 Tolerances

DTOL [0.01]Relative displacement (translation, rotation) tolerance.

DNORM [0.0]Reference translation. DNORM is automatically calculated by the program if DNORM=0.0.

DMNORM [0.0]Reference rotation. DMNORM is automatically calculated by the program if DMNORM=0.0.

STOL [0.5]Line search convergence tolerance.

RCONSM [0.01]Reference contact force.

ENLSTH [0.0]Line search energy threshold. This parameter is only used if line search is activated (e.g.,when ITERATION LINE-SEARCH=YES is specified). During each equilibrium iteration, if theunbalanced energy is less than ENLSTH, no line search will be performed. {>= 0.0}

Notes:1. RNORM and RMNORM cannot both be zero.2. DNORM and DMNORM cannot both be zero.

LSLOWER [1.0e-3]Lower bound for line search. {0.0 ≤ LSLOWER < 1.0}

LSUPPER [1.0 or 8.0]Upper bound for line search. If there is contact, the default is 1.0; otherwise, if there is nocontact, the default is 8.0. {LSUPPER ≥ 1.0}

MAXDISP [0.0]Specifies the maximum incremental displacement that is allowed in an iteration. This feature isgenerally useful for contact analysis where rigid body motion before the bodies come intocontact may result in excessive displacements. A value of 0.0 means there is no limit onincremental displacements. { ≥ 0.0 }

Auxiliary commands

LIST TOLERANCES ITERATIONLists the tolerance data for the iteration scheme within the analysis program ADINA.

TOLERANCES ITERATION



PRINTOUT VOLUME ECHO PRINTDEFAULT INPUT-DATAOUTPUT DISPLACEMENTS VELOCITIESACCELERATIONS IDISP ITEMP ISTRAIN IPIPESTORAGE LARGE-STRAINS ENERGIES

PRINTOUT controls the output printed by ADINA.

VOLUME [MINIMUM]Sets the defaults for the remaining parameters of this command.

MAXIMUM The following defaults are set:

ECHO = YESPRINTDEFAULT = YESINPUT-DATA = 0OUTPUT = ALLDISPLACEMENTS = YESVELOCITIES = YESACCELERATIONS = YESIDISP = YESITEMP = YESISTRAIN = YESIPIPE = YES

MINIMUM The following defaults are set:

ECHO = NOPRINTDEFAULT = NOINPUT-DATA = 4OUTPUT = SELECTEDDISPLACEMENTS = YESVELOCITIES = YESACCELERATIONS = YESIDISP = NOITEMP = NOISTRAIN = NOIPIPE = NO

ECHO [NO]Determines whether the input data file is echoed at the beginning of the ADINA results file.{YES/NO}

PRINTOUT


Sec. 5.9 Analysis output

PRINTDEFAULT [NO]Printing of individual element results is controlled by the data entry �print� of the elementdata commands. This parameter defines the default action for those elements with that dataentry left undefined.

YES Print element results.

NO No element results printed.

STRAINS Element strains are printed in addition to element stresses (only applicableto certain material models).

INPUT-DATA [4]Level of printout of input mesh data.

0 Detailed printing of all generated input data.1 As for 0, except equation numbers are not printed.2 As for 0, except nodal data are not printed.3 As for 0, except equation numbers and nodal data are not printed.4 No printing of input mesh data.

OUTPUT [SELECTED]

ALL All nodal point solution variables and requested element stresses, viaelement data commands, are printed at all solution steps.

SELECTED Results are printed as requested by the parameters of this command inconjunction with other commands, e.g., PRINT-STEPS, PRINTNODES.

DISPLACEMENTS [YES]Controls whether or not the program will print displacements (when OUTPUT =SELECTED). {YES/NO}

VELOCITIES [YES]Controls whether or not the program will print velocities (when OUTPUT = SELECTED).{YES/NO}

ACCELERATIONS [YES]Controls whether or not the program will print accelerations (when OUTPUT = SELECTED).{YES/NO}

PRINTOUT



IDISP [NO]Controls whether or not initial displacements, velocities and accelerations (as indicated byparameters DISPLACEMENTS, VELOCITIES, and ACCELERATIONS) are printed out.{YES/NO}

ITEMP [NO]Controls whether or not initial temperatures and temperature gradients are printed out.{YES/NO}

ISTRAIN [NO]Controls whether or not initial strains, flexural strains and strain gradients are printed out.{YES/NO}

IPIPE [NO]Controls whether or not initial pipe internal pressures are printed out. {YES/NO}

STORAGE [NO]Controls whether or not storage requirements are printed out. {YES/NO}

LARGE-STRAINS [NONE]Indicates whether or not extended results for element stresses and strains are to be printedfor large strain analyses. {NONE/PRINT}

ENERGIES [NO]Indicates whether the energies due to the use of low-speed dynamics option (inertia anddamping), contact damping or assigned stiffness to the normal rotational degree of freedomof shell nodes are printed. {NO/YES}

Auxiliary commands

LIST PRINTOUT

PRINTOUT



PRINT-STEPS SUBSTRUCTURE REUSE


PRINT-STEPS controls the output time steps at which results are printed by the analysisprogram. This is achieved by specifying a sequence of time step �blocks�, each of whichdetermines a given frequency of time step output over a given range of time steps.

Note that the results printout can be controlled independently for the main structure and anysubstructure reuses.

SUBSTRUCTURE [current substructure label number]The label number of the substructure to which the time step block data is assigned.

REUSE [current substructure reuse label number]The label number of the substructure reuse to which the time step block data is assigned.

blockiThe time step block number. The block number must be in the range 1 ≤ blocki ≤ 10, i.e., amaximum of 10 time step blocks can be defined for printout control.

firstiThe initial time step number for the time step block �blocki�. {≥ 1; ≥ last

i-1}

lastiThe final time step number for the time step block �blocki�. {≥ first

i}

incrementiThe time step increment for the time step block �blocki�. {≥ 1}

For each time step block, the analysis program will print results for time steps


etc., until the resulting time step number is greater than or equal to lasti.

Note that printout will be given at time step lasti only if (lasti - firsti) is an integer multiple ofincrementi.


lasti ≥ firsti (i = 1,...,10)incrementi ≥ 1

PRINT-STEPS



and that adjacent blocks do not overlap, i.e.:

firsti≥ last(i-1) (i = 2,...,10)

If these conditions are not satisfied, then an error message will be given and the input will notbe accepted.


Auxiliary commands

LIST PRINT-STEPSDELETE PRINT-STEPS

PRINT-STEPS



PORTHOLE VOLUME SAVEDEFAULT FILEUNIT FORMATTEDINPUT-DATA DISPLACEMENTS VELOCITIES ACCELERATIONSTEMPERATURES MAX-STEPS SHELLVECTORS ELEM-RESULT

PORTHOLE controls the saving, by ADINA, of input data and solution results on theporthole file for later post-processing by ADINA-PLOT.

VOLUME [MAXIMUM]Sets defaults for remaining parameters of this command.

MAXIMUM The following defaults are set:SAVEDEFAULT = YESINPUT-DATA = 1DISPLACEMENTS = YESVELOCITIES = YESACCELERATIONS = YESTEMPERATURES = YES

MINIMUM The following defaults are set:SAVEDEFAULT = NOINPUT-DATA = 0DISPLACEMENTS = NOVELOCITIES = NOACCELERATIONS = NOTEMPERATURES = NO

SAVEDEFAULT [YES]Saving of individual element results is controlled by the data entry �save� of the element datacommands. This parameter defines the default action for those elements with that data entryleft undefined. {YES/NO}

FILEUNITThis parameter is no longer used.

FORMATTED [NO]Controls whether the porthole file records are formatted or written in unformatted binary.{YES/NO}

INPUT-DATAThis parameter is obsolete and should not be used. This parameter is used only in restartanalysis.

PORTHOLE



0 Save only the master control information. Note that when INPUT-DATA = 0, theresulting porthole file cannot be read by ADINA-PLOT.

1 Save all input data on the porthole.

DISPLACEMENTS [YES]Controls whether or not initial and calculated displacements are saved. {YES/NO}

VELOCITIES [YES]Controls whether or not initial and calculated velocities are saved. {YES/NO}

ACCELERATIONS [YES]Controls whether or not initial and calculated accelerations are saved. {YES/NO}

TEMPERATURES [YES]Controls whether or not temperatures are saved on the porthole file. {YES/NO}

Note: TEMPERATURES is also used to control the saving of pipe internal pressures.

MAX-STEPS [0]Indicates the maximum number of time-step results saved in each porthole file. MAX-STEPS=0 means no limit on the number of steps that can be saved on the porthole file, i.e.,only one porthole file is created.

Notes:1. If MAX-STEPS > 0, multiple porthole file may be created with filenames jobname_1.por,

jobname_2.por, etc.

2. MAX-STEPS is also used to control the maximum number of time-step results saved ineach universal file.

SHELLVECTORS [NO]Indicates whether or not shell element node director vectors are to be saved on the portholefile. Note this only refers to those director vectors calculated in large displacement analysisduring the solution response, the initial shell element node director vectors will still be savedon the porthole file. These vectors are required to plot shell elements with a top-bottomdepiction, but can require considerable storage for large shell models with many output steps.When SHELLVECTORS=NORMALS, only the normals of the shell direction vectors are savedin the porthole file. {YES/NO/NORMALS}

PORTHOLE


Sec. 5.9 Analysis outputPORTHOLE

ELEM-RESULT [DEF-GRAD]Controls whether deformation gradients, stretches or strains are saved in the porthole file for2-D and 3-D solid elements with certain material models/kinematic formulations.{DEF-GRAD/STRETCH}

The following table lists the material models and kinematic formulations affected by thisparameter:

��Material model Output when ELEM-RESULT=STRETCH��ARRUDA-BOYCE Green-Lagrange strainsCAM-CLAY(*) StretchesCREEP (*) StretchesCREEP-VARIABLE (*) StretchesDRUCKER-PRAGER (*) StretchesGURSON (*) StretchesHYPER-FOAM Green-Lagrange strainsMOONEY-RIVLIN Green-Lagrange strainsMROZ-BILINEAR (*) StretchesMULTILINEAR-PLASTIC-CREEP (*) StretchesMULTILINEAR-PLASTIC-CREEP-VARIABLE (*) StretchesPLASTIC-BILINEAR (*) StretchesPLASTIC-CREEP (*) StretchesPLASTIC-CREEP-VARIABLE (*) StretchesPLASTIC-MULTILINEAR (*) StretchesOGDEN Green-Lagrange strainsUSER-SUPPLIED (+) Green-Lagrange strainsUSER-SUPPLIED (*) StretchesTHERMO-PLASTIC (*) StretchesVISCOELASTIC (*) Stretches��

* = KINEMATICS DISP=LARGE STRAINS = LARGE+ = KINEMATICS DISP=LARGE STRAINS = SMALL

When ELEM-RESULT = DEF-GRAD, then all of the material models/kinematic formulationsin the above table output deformation gradients.

Auxiliary commands

LIST PORTHOLELists the current settings for the PORTHOLE parameters.



NODESAVE-STEPS ELEMSAVE


NODESAVE-STEPS controls the output timesteps at which nodal results are saved on theporthole file by the analysis program. This is achieved by specifying a sequence of time step�blocks�, each of which determines a given frequency of time step output over a given rangeof time steps.

ELEMSAVE [NO]Indicates whether element results are also saved using the same time step blocks. {NO/COPY/OVERWRITE}

NO Time step blocks for saving element results are specified indepen-dently in ELEMSAVE-STEPS command.

COPY Time step blocks specified in this command are copied to theELEMSAVE-STEPS command if no time step block are specified in thatcommand.

OVERWRITE Time step blocks specified in this command will overwrite any time stepblocks in the ELEMSAVE-STEPS command.

blockiThe time step block number. The block number must be in the range 1 ≤ blocki ≤ 10, i.e., amaximum of 10 time step blocks can be defined for porthole control.

firstiThe initial time step number for the time step block �blocki�. {≥ 1; ≥ last

(i-1)}

lastiThe final time step number for the time step block �blocki�. {≥ first

i}


For each time step block, the analysis program will save nodal results for timesteps

firsti, firsti + incrementi, firsti+(2 × incrementi), ...


NODESAVE-STEPS



Note that nodal results will be saved at time step lasti only if (lasti - firsti) is an integer multipleof incrementi.




firsti ≥ last(i-1) (i = 2,...,10)

If these conditions are not satisfied, then an error message will be given and the input will notbe accepted.


Auxiliary commands

LIST NODESAVE-STEPSDELETE NODESAVE-STEPS

NODESAVE-STEPS



ELEMSAVE-STEPS NODESAVE


ELEMSAVE-STEPS controls the output timesteps at which element results are saved on theporthole file by the analysis program. This is achieved by specifying a sequence of time step�blocks�, each of which determines a given frequency of time step output over a given rangeof timesteps.

NODESAVE [NO]Indicates whether nodal results are also saved using the same time step blocks. {NO/COPY/OVERWRITE}

NO Time step blocks for saving nodal results are specified independentlyin NODESAVE-STEPS command.

COPY Time step blocks specified in this command are copied to theNODESAVE-STEPS command if no time step block are specified in thatcommand.

OVERWRITE Time step blocks specified in this command will overwrite any time stepblocks in the NODESAVE-STEPS command.

blockiThe time step block number. The block number must be in the range 1 ≤ blocki ≤ 10, i.e., amaximum of 10 time step blocks can be defined for porthole control.

firstiThe initial time step number for the time step block �blocki�. Note that firsti must be greaterthan or equal to 1.

lastiThe final time step number for the time step block �blocki�. {≥ 1; ≥ last

(i-1)}


For each time step block, the analysis program will save element results for timesteps:

firsti, firsti + incrementi, firsti+(2 × incrementi), ...

and so on, until the resulting time step number is greater than or equal to lasti.

ELEMSAVE-STEPS



Note that element results will be saved at time step lasti only if (lasti - firsti)is an integer multiple of incrementi.

The time step block data is checked to see that each block satisfies:



firsti ≥ last(i-1) (i = 2,...,10)

If these conditions are not satisfied, then an error message will be given and the input will notbe accepted.Furthermore it is required that the highest value for lasti (for the highest block number) begreater than or equal to the total number of solution timesteps (see TIMESTEP ). If not, thenit will be set to that value, with no resulting error conditions.

Auxiliary commands

LIST ELEMSAVE-STEPSDELETE ELEMSAVE-STEPS

ELEMSAVE-STEPS



PRINTNODES BLOCKS SUBSTRUCTURE REUSE


PRINTNODES POINTS SUBSTRUCTURE REUSE

pointi

PRINTNODES LINES SUBSTRUCTURE REUSE

linei

PRINTNODES SURFACES SUBSTRUCTURE REUSE

surfacei

PRINTNODES VOLUMES SUBSTRUCTURE REUSE

volumei

PRINTNODES EDGES SUBSTRUCTURE REUSE BODY

edgei

PRINTNODES FACES SUBSTRUCTURE REUSE BODY

facei

PRINTNODES BODIES SUBSTRUCTURE REUSE

bodyi

PRINTNODES NODESETS SUBSTRUCTURE REUSE

nodeseti

PRINTNODES selects nodes for which solution results shall be printed by ADINA. This isachieved by specifying a sequence of node blocks (sets of node labels) or by reference to aset of geometry entities to which the nodes are associated, i.e. via mesh generation.

SUBSTRUCTURE [(current substructure label number)]The label number of the substructure to which the nodal data is assigned.

REUSE [(current substructure reuse label number)]The label number of the substructure reuse to which the nodal data is assigned.

BODY [(currently active BODY)]A solid geometry body label number.

PRINTNODES



blockiA node block number.

firstiThe initial node number for the node block blocki. {≥ 1; ≥ last(i-1)

}

lastiThe final node number for the node block blocki. {≥ firsti

}

incrementiThe node increment for the node block blocki. {≥ 1}

pointiA point label number.

lineiA line label number.

surfaceiA surface label number.

volumeiA volume label number.

edgeiAn edge label number; an edge of a solid body �BODY�.

faceiA face label number; a face of a solid body �BODY�.

bodyiA body label number.

nodesetiA node set label number.

Auxilliary Commands

LIST PRINTNODES BLOCKS / POINTS / LINES / SURFACES / VOLUMES / EDGES /FACES / BODIES.

DELETE PRINTNODES BLOCKS / POINTS / LINES / SURFACES / VOLUMES /EDGES / FACES / BODIES.

PRINTNODES



CONTACT-OUTPUT-NODES TYPE

namei bodyi

This command is used to select nodes for output of contact results.

TYPEThe type of entity used for selecting nodes where the contact result is to be output.{NODE/NODESET/POINT/LINE-EDGE/SURFACE-FACE}

Note:If TYPE = NODE or NODESETor POINT , the second column bodyi is ignored.

When TYPE = LINE-EDGE or SURFACE-FACE, if bodyi = 0, this means that the geometryis a line or a surface.

nameiLabel number of the node for which the contact result is output.

bodyiLabel number of the body for namei.

CONTACT-OUTPUT-NODES


Sec. 5.9 Analysis outputREACTION-NODES

REACTION-NODES TYPE

namei bodyi

This command is used with the REACTIONS parameter in the MASTER command to selectthe reaction forces to be printed.

TYPEThe type of entity used for selecting nodes where the reaction force is to be printed.{NODE/NODESET/POINT/LINE-EDGE/SURFACE-FACE}

Note:If TYPE = NODE or NODESET or POINT , the second column bodyi is ignored.When TYPE = LINE-EDGE or SURFACE-FACE, if bodyi = 0, this means that the geometryis a line or a surface.

nameiLabel number of the node for which the reaction force is printed.

bodyiLabel number of the body for namei.






SAVENODES BLOCKS SUBSTRUCTURE REUSE


SAVENODES POINTS SUBSTRUCTURE REUSE

pointi

SAVENODES LINES SUBSTRUCTURE REUSE

linei

SAVENODES SURFACES SUBSTRUCTURE REUSE

surfacei

SAVENODES VOLUMES SUBSTRUCTURE REUSE

volumei

SAVENODES EDGES SUBSTRUCTURE REUSE BODY

edgei

SAVENODES FACES SUBSTRUCTURE REUSE BODY

facei

SAVENODES BODIES SUBSTRUCTURE REUSE

bodyi

SAVENODES NODESETS SUBSTRUCTURE REUSE

nodeseti

SAVENODES selects nodes for which solution results shall be saved by the ADINA on theporthole file. This is achieved by specifying a sequence of node blocks (set of node labels),or by reference to a set of geometry entities to which the nodes are associated, i.e. via meshgeneration.

SUBSTRUCTURE [(current substructure label number)]The label number of the substructure to which the nodal data is assigned.

REUSE [(current substructure reuse label number)]The label number of the substructure reuse to which the nodal data is assigned.

BODYA solid geometry body label number.

SAVENODES



blockiA node block number.

firstiThe initial node number for the node block blocki. {≥ 1; ≥ last(i-1)

}

lastiThe final node number for the node block blocki. {≥ firsti

}

incrementiThe node increment for the node block blocki. {≥ 1}

pointiA point label number.

lineiA line label number.

surfaceiA surface label number.

volumeiA volume label number.

edgeiAn edge label number; an edge of solid body �BODY�.

faceiA face label number; a face of solid body �BODY�.

bodyiA body label number.

nodesetiA node set label number.

Auxilliary Commands

LIST SAVENODES BLOCKS / POINTS / LINES / SURFACES / VOLUMES / EDGES /FACES / BODIES.

DELETE SAVENODES BLOCKS / POINTS / LINES / SURFACES / VOLUMES / EDGES/ FACES / BODIES.

SAVENODES



DISK-STORAGE FACTORIZED-MATRIX GLOBAL-MATRIXTEMPERATURES TGRADIENTS FORCESDISPLACEMENTS PIPE-INTERNAL-PRESSURESFDIRECTIONS NSTEPKM LARGE-STRAINS MEMOPT

DISK-STORAGE indicates auxiliary file storage and input/output control for program ADINA.

FACTORIZED-MATRIX [NONE]Indicates whether or not the factorized linear effective stiffness matrices are to be saved forsubsequent use in restart analyses. This option provides for improved solution efficiency forlarge problems for which the factorization calculations may be skipped for a restart.

NONE No factorized linear stiffness matrices are saved.

SAVE The factorized linear effective stiffness matrices are saved for futureuse by a restart of the analysis.

Note that this option of saving the linear factorized stiffness matrices is not allowed in aneigenvalue solution or when the central-difference method is used. Furthermore, static-to-dynamic or dynamic-to-static restarts are not allowed.

GLOBAL-MATRIX [NONE]Indicates whether or not the global, assembled, stiffness and mass matrices are to be saved toa file. For non-linear analyses the stiffness matrix can be saved at a selected time-step viaparameter NSTEPKM. Only available when SOLVER = SKYLINE in the MASTER command,and for analyses not involving contact conditions.

NONE The assembled global system matrices are not saved.

SAVE The global stiffness and mass matrices are written to file, in formattedform.

TEMPERATURES [NONE]Indicates whether or not nodal temperature data is to be input from a file. Material modelswhich are temperature dependent require the temperature field to be specified. Prescribed orinitial nodal temperatures may be simply described directly by LOAD TEMPERATURE,APPLY-LOAD, INITIAL-CONDITION, SET-INITCONDITION, but a more complex tempera-ture distribution may benefit from being input from file (e.g., created by the heat transferanalysis program ADINA-T). Note that any nodal temperature data input from file is added tothat already specified directly to the database, if any.

NONE No temperature data is input from file.

DISK-STORAGE



READ Temperatures are read from file. The data records of that file mustcontain the solution time and the nodal temperatures at that time. Thesolution times for this input case must correspond to the times of theADINA analysis given by time TSTART (see MASTER) and incrementsthereafter determined by the defined time step sequence.

INTERPOLATE Temperatures are read from file, but unlike the case TEMPERATURES =READ, the solution times need not correspond to the discrete solutiontimes of the ADINA analysis as given by TSTART and the time stepsequence � linear interpolation is performed to give the nodal tempera-tures at the ADINA solution times.

TGRADIENTS [NONE]This parameter acts in the same manner as parameter TEMPERATURES except thatthrough-thickness temperature gradients for shell mid-surface nodes are considered. Notethat any nodal temperature gradient data input from file is added to that already specifieddirectly to the database, if any. {NONE/READ/INTERPOLATE}

FORCES [NONE]This parameter acts in the same manner as parameter TEMPERATURES except that nodalforces are considered. The number and associated (possibly skew) degree-of-freedomdirections of the force components (with a maximum of 6 components) are specified byparameter FDIRECTIONS. Note that any nodal force data input from file is added to thatalready specified directly to the database, if any. {NONE/READ/INTERPOLATE}

DISPLACEMENTS [NONE]Indicates whether or not nodal displacements are written to file, e.g., for use by analysisprogram ADINA-F, to control a moving boundary in a fluid-structure-interaction analysis.

NONE No displacement vectors are written to file.

WRITE Displacement vectors will be written to file.

PIPE-INTERNAL-PRESSURES [NONE]This parameter acts in the same manner as parameter TEMPERATURES except that pipeinternal pressures are considered. Note that any nodal pipe internal pressure data input fromfile is added to that already specified directly to the database, if any. {NONE/READ /INTERPOLATE}

FDIRECTIONS [123456]Indicates which degree-of-freedom directions are to be associated with the nodal forcecomponents input from file (i.e., when parameter FORCES = READ or INTERPOLATE). Theparameter value is an integer number with up to six digits (and no embedded blanks) with the

DISK-STORAGE



associated directions given as follows:

1 X-translation (or a-translation for skew system).2 Y-translation (or b-translation for skew system).3 Z-translation (or c-translation for skew system).4 X-rotation (or a-rotation for skew system).5 Y-rotation (or b-rotation for skew system).6 Z-rotation (or c-rotation for skew system).

NSTEPKM [1]Indicates the time-step at which a non-linear stiffness matrix is written to file when GLOBAL-MATRIX = SAVE. The stiffness matrix at the start of the indicated step is stored � anyautomatic sub-increments are not counted, the time-step sequence specified by commandTIMESTEP is all that is considered by this parameter. Thus, NSTEPKM = 1 corresponds tosaving the initial stiffness matrix, corresponding to time TSTART.

LARGE-STRAINS [NONE]Indicates whether or not extended results of element stresses and strains are to be saved in afile for large strain analyses, and, if so, whether the file is formatted or binary. {NONE/FORMATTED/BINARY}

MEMOPT [AUTOMATIC]Specifies option to write element group data on disk to reduce memory required by theprogram. {AUTOMATIC/EG-OUT}

AUTOMATIC Program automatically decides when element group data iswritten on disk.

EG-OUT Element group data is written on disk to reduce memory usage.

Auxiliary commands

LIST DISK-STORAGE

DISK-STORAGE



MONITOR NAME DESCRIPTION TYPE VARIABLE STOPFLAGSTOPVALUE OPERATION SET1

Defines a monitor that can be used to print out the minimum or maximum value of a variableduring solution. In addition, there is an option to stop the program when the variable reachesa specified value. For element-based variables, only variables in 2D and 3D solid element canbe monitored.

NAME [(current highest monitor label number) + 1]The monitor label. {>0}

DESCRIPTIONDescription of this monitor.

TYPE [NONE]Type of quantity to be monitored. {NONE/ELAV-MODEL/ELAV-GROUP/NODE-MODEL}

NONE Monitoring is not active ELAV-MODEL Nodal averaged element quantity � whole model ELAV-GROUP Nodal averaged element quantity � element group NODE-MODEL Nodal quantity � whole model

VARIABLEName of variable just like post-processing.

For element-based variables, the choices areSTRESS-XX STRESS-XY STRESS-XZSTRESS-YY STRESS-YZ STRESS-ZZSTRESS-EFFECTIVE STRESS-PRINCIPALSTRAIN-XX STRAIN-YY STRAIN-ZZSTRAIN-XY STRAIN-XZ STRAIN-YZSTRAIN-PRINCIPAL

For nodal-based variables, the choices are:DISP-X DISP-Y DISP-Z DISP-MAGNITUDEROT-X ROT-Y ROT-Z ROT-MAGNITUDEVEL-X VEL-Y VEL-Z VEL-MAGNITUDEVEL-TX VEL-TY VEL-TZ VEL-T-MAGNITUDEACC-X ACC-Y ACC-Z ACC-MAGNITUDEACC-TX ACC-TY ACC-TZ ACC-T-MAGNITUDE

STOPFLAG [NO]Whether or not to stop analysis based on monitored value. {NO/YES}

MONITOR


Sec. 5.10 Solution monitoringMONITOR

NO No stopping. Variable used for informational use only (printed to .out file) YES Stop analysis once variable reaches STOPVALUE

STOPVALUEValue at which to stop analysis, used if STOPFLAG=YES.

OPERATION [AMAX]Operation for combining data. {AMAX/MAX/MIN}

AMAX Absolute maximum MAX Maximum MIN Minimum

SET1 [0]Additional data to define monitor. Format depends on TYPE. SET1 = element group number ifTYPE= ELAV-GROUP. Otherwise, it is not used.

Note that only the first 8 active monitors will be used.



MONITOR-CONTROL NSTEP-EXPLICIT

Sets control parameters for solution monitoring.

NSTEP-EXPLICIT [100]Frequency of solution monitoring in explicit analysis. {1 ≤ NSTEP-EXPLICIT ≤ 99999}

MONITOR-CONTROL

Chapter 6

Geometry definition


Chap. 6 Geometry definition

SYSTEM NAME TYPE MODE XORIGIN YORIGIN ZORIGIN PHITHETA XSI AX AY AZ BX BY BZ P1 P2 P3 MOVE

SYSTEM defines a local coordinate system. Coordinates of geometry points and nodes,input via COORDINATES, refer to the current local coordinate system, as defined by the lastpreceding use of command SYSTEM. The current system may also be changed via SETSYSTEM.

NAME [(highest system label number) + 1]Label number of the local coordinate system. Label number 0 is reserved to identify theglobal Cartesian coordinate system, and therefore can be used only with the SET SYSTEMcommand � you cannot redefine the global system.

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TYPE [CARTESIAN]The type of local coordinate system. Each type has an underlying base Cartesian system(XL, YL, ZL). See Figure.

CARTESIAN A local Cartesian system, with axes aligned with thebase system (XL, YL, ZL).

CYLINDRICAL A cylindrical local coordinate system with coordinates (r, Θ, z).

SPHERICAL A spherical local coordinate system with coordinates (r, Θ, φ).

SYSTEM



MODE [1]Selects the method of local coordinate system definition. This controls which parametersactually define the system � other parameters are ignored.

1 System defined by origin and direction vectors (XORIGIN,YORIGIN, ZORIGIN, AX, AY, AZ, BX, BY, BZ).

2 System defined by origin and Euler angles (XORIGIN,YORIGIN, ZORIGIN, PHI, THETA, XSI).

3 System defined by three geometry points (P1, P2, P3)

XORIGIN [0.0]YORIGIN [0.0]ZORIGIN [0.0]The global system coordinates of the origin of the local coordinate system.

PHI [0.0]THETA [0.0]XSI [0.0]Euler angles (in degrees) used to define the orientation of the basic system (XL, YL, ZL) withrespect to the global Cartesian coordinate system axes. See Figure. Parameters are used onlywhen MODE=2.

AX [1.0]AY [0.0]AZ [0.0]Global system components of a vector along the XL-direction.

BX [0.0]BY [1.0]BZ [0.0]Global system components of a vector in the XL-YL plane.

P1P2P3Label numbers of geometry points which define the local coordinate system. P1 is the originof the system, the XL axis is taken from P1 to P2. P3, together with P1, P2, then defines theXL-YL plane. The YL axis is taken orthogonal to the XL axis and points to the same side asP3 of the line between P1 and P2. The ZL axis is then defined by the right hand rule, i.e.,using a cross product of unit vectors along the XL,YL axes.

SYSTEM


Sec. 6.1 Coordinate systemsSYSTEM

MOVE [YES]If a local coordinate system is redefined, the geometry points and nodes which refer to thislocal system would ordinarily be moved to new global positions, since their coordinates referto the previous definition of the local coordinate system. However, when MOVE = NO thegeometry points and nodes can be made to retain their global position, with their localcoordinates modified accordingly. {YES/NO}

Auxiliary commands

SET SYSTEM NAME [0]Once a local coordinate system has been defined, it may be selected as being thecurrently active system by issuing the command SET SYSTEM. The currently active

system is initially the global Cartesian system.

SHOW SYSTEMLists the currently active system.

LIST SYSTEM FIRST LASTDELETE SYSTEM FIRST LAST

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COORDINATES POINT SYSTEM

(ENTRIES NAME X Y Z SYSTEM) (SYSTEM = global Cartesian (0))(ENTRIES NAME XL YL ZL SYSTEM) (SYSTEM = local Cartesian)(ENTRIES NAME R THETA XL SYSTEM) (SYSTEM = local cylindrical)(ENTRIES NAME R THETA PHI SYSTEM) (SYSTEM = local spherical)

ni xi yi zi sysi

COORDINATES POINT defines coordinates for geometry points. The coordinates given referto the local system specified by parameter SYSTEM.

SYSTEM [currently active system]Label number of the required local coordinate system. This specifies the coordinate systemto which any appended data line coordinates refer (and determines which column headingnames are allowed by any ENTRIES data line).

ENTRIESDefines, as column headings, the input for the subsequent tabular entries. The headingnames depend on the type of local coordinate system specified by parameter SYSTEM.

Note: Less than five entry column headings may be given (e.g., to specify points in acoordinate plane), with previous values retained for omitted entries, but thecolumn heading NAME must always be specified.

niLabel number for the desired geometry point, input under the column heading NAME.

xi [0.0]yi [0.0]zi [0.0]Coordinate values in local coordinate system �sysi�.

sysi [SYSTEM]Local coordinate system label number. Note �sysi� defaults to the system specified byparameter SYSTEM, which in turn defaults to the currently active coordinate system.

Auxiliary commands

LIST COORDINATES POINT FIRST LAST SYSTEM GLOBALLists the coordinates of geometry points with label numbers in a given range, and which are defined in terms of a specified local coordinate system. The coordinates maybe listed in terms of the global Cartesian system (GLOBAL = YES). If no range is speci-fied, only label numbers will be listed.

COORDINATES POINT


Sec. 6.2 Points

DELETE COORDINATES POINT FIRST LAST SYSTEMDeletes all geometry points, and their coordinate data, with label numbers in a givenrange. Note that a geometry point will not be deleted if it is referenced by a higher ordergeometry entity (e.g. it is the end point of a line), or a node or other model entity isassociated with that point.

COORDINATES POINT



LINE STRAIGHT NAME P1 P2

LINE STRAIGHT defines a straight geometry line between two geometry points.

NAME [(current highest geometry line label number) + 1]Label number of the straight geometry line to be defined.

P1P2Label numbers of the geometry points which are the ends of the straight geometry line. Thelabel numbers P1, P2 must be distinct, but the points may be coincident. A �null� geometryline is defined by this command when the end points P1, P2 are coincident, i.e., they haveidentical global coordinates. The line has zero length, but may be used in mesh generation,yielding coincident nodes and zero length element edges.

Auxiliary commands

LIST LINE FIRST LAST ALLDELETE LINE STRAIGHT FIRST LAST

COPY LINE NAME TRANSFORMATION NEWNAME PCOINCIDEPTOLERANCE

Copies line NAME to NEWNAME via transformation TRANSFORMATION. The end-points of the new line may optionally be checked for point coincidence.

MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCEMoves line NAME via transformation TRANSFORMATION. The end points of themoved line may optionally be checked for point coincidence.

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LINE STRAIGHT


Sec. 6.3 Lines

LINE ARC NAME MODE P1 P2 P3 CENTER RADIUS ANGLE CHORDPCOINCIDE PTOLERANCE MODIFY-LINES DELETE-POINTS

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LINE ARC defines a geometry line as a circular arc, or as an arc with varying radius.

NAME [(current highest line label number) + 1]Label number of the arc geometry line.

MODE [1]Selects the method of arc geometry line definition. This controls which parameters actuallydefine the arc, other parameters are ignored. See Figure. {1/2/3/4/5/6/7}

1 Arc defined by start point, end point, and center (P1, P2, CENTER).

2 Arc defined by start point, end point, and intermediate point (P1, P2, P3).

3 Arc defined by start point, center, included angle, and a point defining theplane of the arc (P1, CENTER, ANGLE, P3).

4 Arc defined by start point, center, chord length, and a point defining theplane of the arc (P1, CENTER, CHORD, P3).

LINE ARC



5 Arc defined by start point, end point, radius, and a point defining theplane of the arc (P1, P2, RADIUS, P3).

6 Arc defined by start point, end point, included angle, and a point definingthe plane of the arc (P1, P2, ANGLE, P3).

7 Arc defined by two co-planar, non-parallel straight or extruded lines andradius (RADIUS).

P1Label number of the geometry point at the start of the arc geometry line.

P2Label number of the geometry point at the end of the arc geometry line.

P3Label number of a geometry point either through which the arc geometry line passes (MODE= 2), or, together with the start point and end point or center, defines the plane of the arc(MODE = 3,4,5,6).

Note: P3 = 0 corresponds to the origin of the currently active local coordinate system.

CENTERLabel number of the geometry point at the center of the arc geometry line.

RADIUSRadius of the arc geometry line.

ANGLEIncluded angle of the arc geometry line.

CHORDChord length of the arc geometry line.

PCOINCIDE [YES]If MODE > 1 then a geometry point will be located at the center or end of the arc. Thisparameter indicates whether to check the location against existing geometry point coordi-nates, and use an existing point (YES), rather than generate a new geometry point (with anew label) (NO). {YES/NO}

PTOLERANCE [1.0E-5]If PCOINCIDE = YES, this parameter provides a tolerance value for checking the globalcoordinates of a location against those of existing geometry points.

LINE ARC


Sec. 6.3 Lines

MODIFY-LINES [YES]Indicates whether or not lines will be modified in order to connect with the created arc. Thisparameter is used only when MODE=7. {YES/NO}

DELETE-POINTS [YES]Indicates whether or not the original points on lines should be deleted if these points are notused after lines are modified. This parameter is used only when MODE=7 and MODIFY-LINES=YES. {YES/NO}

lineiLabel number of the lines to define the arc (MODE=7).

Notes:

All MODES

All geometry points referenced by this command � P1, P2, P3, CENTER � must be distinct.Thus the arc is open � to define a complete (closed) circle, command LINE CIRCLE should beused.

MODE = 1

The arc defined is circular only if P1 and P2 are equidistant from CENTER � otherwise an arcis defined in which the radius is linearly interpolated across the included angle.

The points P1, P2, and CENTER must not be collinear. The included angle is always chosento be less than 180 degrees � thus a different mode should be used if a semi-circle or an arcsubtending an angle greater than 180 degrees is required.

No other geometry points are required; the chord length, included angle, and radius (for acircular arc) are calculated.

MODE = 2

The arc is defined to pass through the intermediate point P3. A point at the center of the arcis generated. Parameter CENTER may be used to specify the label number of a newlygenerated point � it defaults to the next highest label number. If so specified, however,CENTER must not be the label number of an existing geometry point. Furthermore, ifPCOINCIDE = YES and a geometry point already exists at the arc center � the coincidencecheck is governed by the tolerance value PTOLERANCE � then that geometry point will betaken to be the center of the arc, ignoring any label specified via parameter CENTER.

LINE ARC



The points P1, P2, and P3 must not be collinear.

MODE = 3

The plane of the arc is defined by the points P1, CENTER, and P3, which must not be col-linear. Furthermore, ANGLE is measured positive in the direction from P1 to P3.

A point at the end of the arc is generated. Parameter P2 may be used to specify the labelnumber of a newly generated point � it defaults to the next highest label number. If sospecified, however, P2 must not be the label number of an existing geometry point. Further-more, if PCOINCIDE = YES and a geometry point already exists at the end of the arc � thecoincidence check is governed by the tolerance value PTOLERANCE � then that geometrypoint will be taken to be the end of the arc, ignoring any label specified via parameter P2.

MODE = 4

The plane of the arc is defined by the points P1, CENTER, and P3, which must not be col-linear. Furthermore, the end point of the arc is taken to be the same side of the line betweenthe points P1 and CENTER as the point P3.

A point at the end of the arc is generated � see MODE = 3.

MODE = 5

The plane of the arc is defined by the points P1, P2 and P3, which must not be collinear. Thecenter of the arc is taken to be the same side of the line between the points P1 and P2 as thepoint P3.

A point at the center of the arc is generated � see MODE = 2.

MODE = 6

The plane of the arc is defined by the points P1, P2, and P3, which must not be collinear.Furthermore, ANGLE is measured positive in the direction from P1 to P3.

A point at the center of the arc is generated � see MODE = 2.

Auxiliary commands

LIST LINE FIRST LAST ALLDELETE LINE ARC FIRST LAST

LINE ARC


Sec. 6.3 LinesLINE ARC



MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCEMoves line NAME via transformation TRANSFORMATION. The end points of themove line may optionally be checked for point coincidence.



LINE CIRCLE NAME MODE P1 P2 P3 CENTER RADIUS PCOINCIDEPTOLERANCE

LINE CIRCLE defines a circle geometry line.

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NAME [(current highest geometry line label number) + 1]Label number of the circle to be defined.

MODE [1]Selects the method of circle definition. This controls which parameters actually define thecircle, other parameters are ignored. See Figure.

1 Circle defined by center, starting point, and a point defining the plane ofthe circle (CENTER, P1, P3).

2 Circle defined through three points (P1, P2, P3).

3 Circle defined by center, radius, and by two points � one defining the�pole� direction (which intersects the circle at its starting point), and theother defining the plane of the circle (CENTER, RADIUS, P2, P3).

LINE CIRCLE


Sec. 6.3 Lines

P1P2P3Label numbers of the geometry points which define the circle.

CENTERLabel number of a geometry point at the center of the circle.

RADIUSThe radius of the circle.

PCOINCIDE [YES]A geometry point will be located at the center (MODE = 2), or the starting point (MODE = 3)of the circle. This parameter indicates whether to check the location against existing geom-etry point coordinates, and use an existing point (YES) rather than generate a new geometrypoint (with a new label) (NO). {YES/NO}


Note: A circle is a closed geometry line, a circular arc may be defined by command LINEARC.

Auxiliary commands

LIST LINE FIRST LAST ALLDELETE LINE CIRCLE FIRST LAST

COPY LINE NAME TRANSFORMATION NEW NAME PCOINCIDEPTOLERANCE

Copies line NAME to NEWNAME via transformation TRANSFORMATION. The endpoints of the new line may optionally be checked for point coincidence.

MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCEMove line name via transformation TRANSFORMATION. The end points of themoved line may optionally be checked for point coincidence.

LINE CIRCLE





Sec. 6.3 Lines

LINE CURVILINEAR NAME P1 P2 SYSTEM ANGLE

LINE CURVILINEAR defines a geometry line as an interpolated curve in a given localcoordinate system; coordinates of points on the curve are linearly interpolated between twogeometry points.

NAME [(current highest geometry line label number) + 1]Label number of the curvilinear geometry line to be defined.

P1P2Label numbers of the geometry points which are the ends of the curvilinear geometry line.

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SYSTEM [current coordinate system]The label number of a coordinate system in which the curve is to be interpolated.

ANGLE [THETA]In the case of a spherical coordinate system, if P1 = P2, a circle will be generated by interpo-lating through 360° in one of the coordinate angles. This parameter selects which angle touse. See Figure. {THETA/PHI}

Note: The geometry line will be a circle in the case where P1 = P2 with a cylindrical orspherical coordinate system. In the case of a Cartesian local system (including theglobal system) P1 = P2 is not allowed, and the geometry line will be straight.

Auxiliary commands

LIST LINE FIRST LAST ALLDELETE LINE CURVILINEAR FIRST LAST




LINE CURVILINEAR


Sec. 6.3 Lines

KNOTS NAME NKNOTS

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Defines a vector of knot values to be used for non-uniform rational B-spline definition, seeLINE POLYLINE (TYPE=NURBS).

NAME [(current highest knot vector label )+ 1]Label number of the knot vector.

NKNOTSThe number of input knot values. { ≥ 4 }

iIndex of the input knot value. { 1 ≤ i ≤ NKNOTS }

ui [0.0]Knot value for index �i�.

Auxiliary commands

LIST KNOTS FIRST LASTDELETE KNOTS FIRST LAST

KNOTS



LINE POLYLINE NAME TYPE DEGREE KNOTS

pointi tangxi tangyi tangzi (TYPE = BIARC)

pointi weighti (TYPE = NURBS)

pointi (TYPE = SEGMENTED, QBSPLINE,CBSPLINE, BEZIER, SPINE)

LINE POLYLINE defines a geometry line as a polyline, i.e., a curve controlled by a series ofgeometry points.

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LINE POLYLINE


Sec. 6.3 Lines

NAME [(current highest geometry line label number) + 1]Label number of the polyline geometry line to be defined.

TYPE [SEGMENTED]Selects the type of curve to be defined.

SEGMENTED The points are connected in sequence by a series of straight linesegments. At least two points must be specified.

QBSPLINE A quadratic B-spline is derived from the control points. Note thatthe curve passes through the first and last points but not neces-sarily through the intervening control points. At least three pointsmust be specified.

CBSPLINE A cubic B-spline is derived from the control points. Note that thecurve passes through the first and last points but not necessarilythrough the intervening control points. At least four points mustbe specified.

BIARC Each consecutive pair of points is connected by two circular arcs.The tangent direction of the curve may be specified at any givenpoint. The tangent directions are otherwise calculated by theprogram. At least three non-collinear points must be specified.Furthermore, all the control points must lie in the same plane, andany specified tangent vector must also lie in that plane � an errormessage is given if either of these conditions is violated.

BEZIER A Bezier curve is derived from the control points. Note that thecurve passes through the first and last points but not necessarilythrough the intervening control points. At least three points mustbe specified.

NURBS A non-uniform rational B-spline curve is derived from the controlpoints, weights, and knots.

SPLINE A spline is derivied from the control points. Note that thecurvarture of curve is continous at these points. At least twopoints must be specified.

DEGREEThe degree of the B-spline basis functions, must be input for TYPE = NURBS.

LINE POLYLINE



KNOTSThe label number of the knot vector (see command KNOTS). The total number of knots usedin the spline definition must equal (DEGREE+(number of control points)+1).

pointiLabel number of geometry point used to interpolate/control the desired curve. The data linesare input in the order of the sequence of points.

tangxi [0.0]tangyi [0.0]tangzi [0.0]Vector specifying, with reference to the global Cartesian coordinate system, the tangentdirection to the curve at point �pointi �. This vector only influences the shape of the polylineof type BIARC. Input of tangxi = tangyi = tangzi = 0.0 will result in the program automati-cally calculating the tangent direction from the slope of the quadratic curve interpolatedthrough the point and its immediate neighbors in the sequence.

Note: A polyline may be closed be selecting the first and last points in the sequence to referto the same geometry point.

Note: For BIARC interpolation a straight line segment may be defined by making thetangent line at a point pass through its neighbor point.

weightiThe weight at each control point.

Auxiliary commands

LIST LINE FIRST LAST ALLDELETE LINE POLYLINE FIRST LAST




LINE POLYLINE


Sec. 6.3 Lines

LINE SECTION NAME PARENT USTART UEND PCOINCIDEPTOLERANCE COUPLED P1 P2

LINE SECTION defines a geometry line to be part of another geometry line.

NAME [(current highest geometry line label number) + 1]Label number of the section geometry line to be defined.

PARENTThe line upon which the section line is defined.

USTART [0.0]The line parameter (0.0 ≤ USTART ≤ 1.0) indicating the starting position on the linePARENT.

UEND [1.0]The line parameter (0.0 ≤ UEND ≤ 1.0) indicating the end position on the line PARENT.

PCOINCIDE [YES]This parameter indicates whether or not to check the location of the section line end pointsagainst existing geometry point coordinates, and use an existing point (YES) rather thangenerate a new geometry point (with a new label) (NO). {YES/NO}

PTOLERANCE [TOLERANCES GEOMETRIC]If PCOINCIDE = YES, this parameter provides a tolerance value for checking the globalcoordinates of a location against those of existing geometry points.

COUPLED [YES]If COUPLED=YES, then the parent line cannot be modified. {YES/NO}

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P1 [0]Label number of the geometry point corresponding to USTART.

P2 [0]Label number of the geometry point corresponding to UEND.

Auxiliary commands

LIST LINE FIRST LAST ALLDELETE LINE SECTION FIRST LAST




LINE SECTION


Sec. 6.3 Lines

LINE COMBINED NAME COUPLED

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LINE COMBINED defines a geometry line as a combination of other geometry lines. Thedefining or �parent� lines must form a connected sequence. The combined line may beclosed, by virtue of having connected first and last line subsegments.

NAME [(current highest geometry line label number) + 1]Label number of the combined geometry line to be defined.


lineiLabel number of a parent geometry line.

Auxiliary commands

LIST LINE FIRST LAST ALLDELETE LINE COMBINED FIRST LAST


Copies line NAME to NEWNAME via transformation TRANSFORMATION. The endpoint of the new line may optionally be checked for point coincidence.


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LINE COMBINED



LINE REVOLVED NAME MODE POINT ANGLE SYSTEM AXIS ALINEAP1 AP2 X0 Y0 Z0 XA YA ZA PCOINCIDEPTOLERANCE

LINE REVOLVED defines a geometry line (a circular arc) by rotating a geometry point aboutan axis.

NAME [(current highest geometry line label number) + 1]Label number of the revolved geometry line.

MODE [AXIS]Selects the method of defining the axis of revolution used to define the geometry line. Thiscontrols which parameters actually define the revolved line, other parameters are ignored.

AXIS The axis of revolution is taken as a given axis of a coordinatesystem. (POINT, ANGLE, SYSTEM, AXIS).

LINE The axis of revolution is taken as the straight line between theend points of a given geometry line (which is not necessarilystraight, but must be open � i.e., have non-coincident end points).(POINT, ANGLE, ALINE).

POINTS The axis of revolution is taken as the straight line between twogiven (non-coincident) geometry points. (POINT, ANGLE, AP1,AP2).

VECTORS The axis of revolution is defined by a position vector and adirection vector. (POINT, ANGLE, X0, Y0, Z0, XA, YA, ZA).

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LINE REVOLVED


Sec. 6.3 Lines

POINTLabel number of the initial geometry point to be rotated about the desired axis.

ANGLEAngle of rotation (in degrees). Note ANGLE must be in the range -360 ≤ ANGLE ≤ 360(with ANGLE = 360 or -360 defining a closed line, i.e., a circle). The sign of the angle isgiven by considering the right hand rule � i.e., if you curl your fingers around the axis ofrevolution, with the thumb pointing along the axis, then a positive angle is in the direction ofthe curl of the fingers.

SYSTEM [currently active coordinate system]Label number of a coordinate system. One of the axes of this coordinate system may be usedto define the axis of revolution, via parameter AXIS, when MODE = AXIS.

AXIS [XL]Selects which of the base axes (XL, YL, ZL) of the local coordinate system, given by param-eter SYSTEM, is used as the axis of revolution. {XL/YL/ZL}

ALINELabel number of a geometry line which defines the axis of revolution. The direction of theaxis is taken from the start point of the line to the end point of the line.

AP1, AP2Label numbers of geometry points which define the axis of revolution. The direction of theaxis is taken from point AP1 to point AP2.

X0 [0.0]Y0 [0.0]Z0 [0.0]Global coordinates of the position vector defining a point on the axis of rotation when MODE= VECTORS.

XA [1.0]YA [0.0]ZA [0.0]Components (with respect to the global coordinate system) of the axis of rotation whenMODE = VECTORS.

PCOINCIDE [YES]A geometry point is to be located at the other end of the line from the initial point given byPOINT. This parameter indicates whether to check the location against existing geometrypoint coordinates, and use an existing point (YES) rather than generate a new geometry point(with a new label) (NO). {YES/NO}

LINE REVOLVED




Auxiliary commands

LIST LINE FIRST LAST ALLDELETE LINE REVOLVED FIRST LAST

COPY LINE NAME TRANSFORMATION NEWNAME PCOINCIDE PTOLERANCE



LINE REVOLVED


Sec. 6.3 Lines

LINE EXTRUDED NAME POINT DX DY DZ SYSTEM PCOINCIDEPTOLERANCE

LINE EXTRUDED defines a geometry line by displacing a geometry point in a given direction.

NAME [(current highest geometry line label number) + 1]Label number of the extruded geometry line.

POINTLabel number of the initial geometry point to be displaced.

DX [1.0]DY [0.0]DZ [0.0]Components of displacement vector with reference to the base coordinates (XL, YL, ZL) ofsystem SYSTEM. Note that this is the actual displacement vector, i.e., it specifies bothmagnitude and direction.

SYSTEM [currently active coordinate system]Label number of a coordinate system which is referenced by the displacement vector (DX,DY, DZ).

PCOINCIDE [YES]A geometry point is to be located at the other end of the line from the initial point given byPOINT. This parameter indicates whether to check the location against existing geometrypoint coordinates, and use an existing point (YES) rather than generate a new geometry point(with a new label) (NO). {YES/NO}


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Auxiliary commands

LIST LINE FIRST LAST ALLDELETE LINE EXTRUDED FIRST LAST




LINE EXTRUDED


Sec. 6.3 Lines

LINE TRANSFORMED NAME PARENT TRANSFORMATIONPCOINCIDE PTOLERANCE NCOPY

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LINE TRANSFORMED defines a geometry line to be a geometrical transformation of another(existing) geometry line. The transformed geometry line is identified by its label numberNAME. If NCOPY is greater than 1, the other newly defined transformed geometry lines areidentified by the current highest geometry line label number + 1.

NAME [(current highest geometry line label number) + 1]Label number of the transformed geometry line.

PARENTThe line which, after transformation, gives the line to be defined.

TRANSFORMATIONLabel number of a geometrical transformation, see TRANSFORMATION.

PCOINCIDE [NO]This parameter indicates whether or not to check the location of the transformed line endpoints against existing geometry point coordinates, and use an existing point (YES) ratherthan generate a new geometry point (with a new label) (NO). {YES/NO}


NCOPY [1]Parameter defines number of lines to be generated by the transformation - transformation isrepeated NCOPY times.

lineiLine label number to be transformed.

Auxiliary commands

LIST LINE FIRST LAST ALLDELETE LINE TRANSFORMED FIRST LAST

LINE TRANSFORMED




Copies line NAME to NEWNAME via transformation TRANSFORMATION. The endpoint of the new line may optionally be checked for point coincidence.


LINE TRANSFORMED


Sec. 6.3 Lines

SPLIT-LINE NAME USPLIT LINE1 LINE2 COUPLED

SPLIT-LINE creates two geometry lines of type SECTION by �splitting� a given line into twoparts connected at some point on the given line, specified via a parameter value along theline.

NAMELabel number of the geometry line to be split. Note that this line is not altered by thiscommand. Two new lines are created coincident with the line NAME.

USPLIT [0.5]A parameter value indicating the point along line NAME at which splitting takes place. Theparameter value can range between 0.0 (the starting point of line NAME) to 1.0 (the endpoint of line NAME), but cannot be 0.0 or 1.0, i.e., the splitting point on the line mustcreate two new lines of non-zero length.

LINE1 [(highest line label number) + 1]The label number of the new line created ranging from the starting point of line NAME (u =0.0) to the splitting point (u = USPLIT). Note that LINE1 must not have been previouslydefined.

LINE2 [(highest line label number) + 2]The label number of the new line created ranging from the splitting point (u = USPLIT) to theend point (u = 1.0) of line NAME. Note that LINE2 must not have been previously defined.


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LNTHICKNESS

linei thicki dthick1i dthick2i

LNTHICKNESS defines line thicknesses (useful for defining axisymmetric shell thicknesses,for example).

lineiThe line label number.

thicki [0.0]The line thickness.

dthick1i [0.0]The deviation of the thickness at the start point of �linei�.

dthick2i [0.0]The deviation of the thickness at the end point of �linei�.

Note: For a constant thickness only the data line entry �thicki� need be specified. Thethickness may be varied linearly along the line by specifying non-zero deviationsand the ends of the line.

Auxiliary commands

LIST LNTHICKNESS FIRST LASTDELETE LNTHICKNESS FIRST LAST

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LNTHICKNESS


Sec. 6.4 Surfaces

SURFACE PATCH NAME EDGE1 EDGE2 EDGE3 EDGE4

SURFACE PATCH defines a geometry surface to be bounded by edges which are specifiedgeometry lines.

NAME [(current highest geometry surface label number) + 1]Label number of the geometry surface.

EDGE1 [existing surface edge, if any]EDGE2EDGE3EDGE4Label numbers of geometry lines comprising edges of the geometry surface. To indicate amissing edge, either the corresponding parameter is not specified or, equivalently, a zero labelnumber may be given. See Figure. Note: The edge geometry lines must form a connectedsequence, i.e., their end points must match. Otherwise an error condition results.

At least two edges must be specified. If two adjacent edges are specified, then a uniqueconnecting edge is searched for to form a triangular surface patch. If two opposite edges(EDGE1 and EDGE3, or EDGE2 and EDGE4) are specified then the missing two edges aresearched for to form a quadrilateral surface patch, unless the given edges are connected, inwhich case a single connecting edge is searched for to yield a triangular surface patch. Ifthree edges are specified, then a unique connecting edge is searched for, unless the threeedges by virtue of their connection already form a triangular surface patch.In each case of a �missing� edge, if no line is found to represent the surface edge, then astraight line will be created with label number incremented from the current highest line labelnumber.

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If more than one line could represent the missing surface edge, then a warning message isgiven with no surface created.

Auxiliary commands

LIST SURFACE FIRST LASTDELETE SURFACE FIRST LAST OPTION

When deleting surfaces, OPTION = ALL will delete any vertex points or edge lineswhich have no other dependent geometry; otherwise (OPTION = SURFACE), only thesurface itself will be deleted.

SURFACE PATCH


Sec. 6.4 Surfaces

SURFACE VERTEX NAME P1 P2 P3 P4 EDGE1 EDGE2 EDGE3 EDGE4

SURFACE VERTEX defines a geometry surface to be bounded by edges which are specifiedby their end geometry points � the vertices of the surface. This command is similar toSURFACE PATCH � the underlying surface representation is identical � only the method ofdefinition differs. If no geometry line exists between adjacent geometry points, then thecommand will automatically generate straight geometry lines between the appropriategeometry point pairs.

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NAME [(highest geometry surface label number) + 1]Label number of the geometry surface.

P1, P2, P3, P4Label numbers of geometry points which are the vertices of the geometry surface. SeeFigure. P1, P2, P3 must be specified, and correspond to existing geometry points. A triangu-lar surface patch is defined by repeating one pair of consecutive points (i.e., P2 = P1, P3 = P2,P4 = P3, or P1 = P4). Note that P4 defaults to P1, automatically giving a triangular surfacepatch if only P1, P2, P3 are specified.



EDGEi [existing surface edges, if any]Label numbers of the surface edges (i = 1, 2, 3, 4), i.e., geometry lines, input if required � seebelow. The parameters are related to the surface vertices as follows:

EDGE1 Line from P1 to P2.




If a pair of adjacent vertices is not connected by a geometry line, then a new straight line isgenerated between them. The label number of the new edge is given by the appropriateEDGEi parameter. Note that in this case the parameter must not refer to an existing line. If nolabel is given then the highest line label number successively incremented by 1 is used.

If more than one line connects a pair of adjacent vertices, then the choice of line may be madevia the appropriate EDGEi parameter. In this case the parameter must refer to one of the linesconnecting the relevant pair of vertices.

Auxiliary commands



SURFACE VERTEX


Sec. 6.4 Surfaces

SURFACE GRID NAME MPOINT NPOINT TYPE EDGE1 EDGE2 EDGE3EDGE4

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SURFACE GRID defines a geometry surface as a grid (array) of geometry points, whichcontrol the shape of the surface.

NAME [(current highest geometry surface label number) + 1]Label number of the geometry surface to be defined.

MPOINT [4]Number of rows in the array of surface grid control points.

NPOINT [4]Number of columns in the array of surface grid control points.

TYPE [POLYFACE]Selects the type of surface to be defined.

POLYFACE The grid of control points is connected by a quadrilateral polygonal mesh. MPOINT and NPOINT each have a minimum value of2 for this surface type.

QBSPLINE A quadratic B-spline surface is derived from the grid of controlpoints. MPOINT and NPOINT each have a minimum value of 3for this surface type.

CBSPLINE A cubic B-spline surface is derived from the grid of controlpoints. MPOINT and NPOINT each have a minimum value of 4for this surface type.

BEZIER A Bezier surface is derived from the grid of control points.MPOINT and NPOINT each have a minimum value of 3 for thissurface type.

SURFACE GRID



EDGEi [existing edge surfaces, if any]Label numbers of the surface edges (i = 1, 2, 3, 4), i.e., geometry lines, input if required � seebelow. The parameters are related to the surface control points as follows (see Figure):

EDGE1 Polyline defined by points (i, j): i = MPOINT, j = 1, 2, ..., NPOINT

EDGE2 polyline defined by points (i, j): i = 1, 2, ..., MPOINT, jcol = 1

EDGE3 polyline defined by points (i, j): i = 1, j = 1, 2, ..., NPOINT

EDGE4 polyline defined by points (i, j): i = 1,2,...,MPOINT, jcol = NPOINT

If a set of edge control points does not already define a polyline of the corresponding type(see note and table below) then a new polyline is generated. The label number of the newedge is given by the appropriate EDGEi parameter. Note that in this case the parameter mustnot refer to an existing line. If no label is given then the highest line label number succes-sively incremented by 1 is used.

If more than one polyline of the corresponding type is defined by a set of edge controlpoints, then the choice of polyline is made via the appropriate EDGEi parameter. In this casethe parameter must refer to one of the polylines defined by the relevant set of edge controlpoints.

SURFACE GRID

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Sec. 6.4 Surfaces

irowi, jcoliRow and column number, respectively, of the point �pointi� entry in the array of controlpoints. The following range of values are allowed:

1 ≤ irowi ≤ MPOINT1 ≤ jcoli ≤ NPOINT

pointiLabel number of geometry point used to interpolate/control the desired surface.

Note: A point label is required input for each entry (irow, jcol) in the array of points;irow = 1, 2, ..., MPOINT; jcol = 1, 2, ..., NPOINT.

Note: A line of type POLYLINE may be created at each edge of the surface, according tothe following rule:

Surface Grid Type Edge Polyline Type

POLYFACE SEGMENTED

QBSPLINE QBSPLINE

CBSPLINE CBSPLINE

BEZIER BEZIER

Auxiliary commands



SURFACE GRID



SURFACE EXTRUDED NAME LINE DX DY DZ SYSTEM PCOINCIDEPTOLERANCE NDIV OPTION ELINE

linei

SURFACE EXTRUDED defines a geometry surface by displacing a geometry line in a givendirection.

NAME [(current highest geometry surface label number) + 1]Label number of the extruded geometry surface.

LINELabel number of the initial geometry line to be displaced, thereby defining the extrudedsurface.

DX [1.0]DY [0.0]DZ [0.0]Components of displacement vector with respect to the base coordinates (XL, YL, ZL) ofcoordinate system SYSTEM. Note that this is the actual displacement vector, i.e., it specifiesboth magnitude and direction.

SYSTEM [currently active coordinate system]Label number of a coordinate system which is referenced by the displacement vector (DX,DY, DZ).

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Sec. 6.4 Surfaces

PCOINCIDE [YES]Geometry points are to be located at the other end of the surface from the initial line given byLINE. This parameter indicates whether to check point�s location against existing geometrypoint coordinates, and use an existing point (YES) rather than generate a new geometry point(with a new label) (NO). {YES/NO}


NDIV [DEFAULT]Number of subdivisions assigned to the surface in the extruded direction. The DEFAULTnumber of subdivisions is taken from the parameter NDIV in the command SUBDIVIDEDEFAULT. This parameter is only used when OPTION=VECTOR.

OPTION [VECTOR]This parameter offers options to the surface extrusion:

VECTOR surfaces are defined by displacing geometry lines in a given direction.

LINE surfaces are defined by displacing geometry lines along a line.

ELINEThe geometry line label. This parameter is only used when OPTION=LINE

lineiLabel numbers of geometry lines. The data line input allows for more than one line to beextruded.

Auxiliary commands


When deleting surface, OPTION = ALL will delete any vertex points or edge lineswhich have no other dependent geometry; otherwise (OPTION = SURFACE), only thesurface itself will be deleted.

SURFACE EXTRUDED



SURFACE REVOLVED NAME MODE LINE ANGLE SYSTEM AXISALINE AP1 AP2 X0 Y0 Z0 XA YA ZAPCOINCIDE PTOLERANCE NDIV

linei

SURFACE REVOLVED defines a geometry surface by rotating a geometry line about some axis.

NAME [(current highest geometry surface label number) + 1]Label number of the revolved geometry surface.

MODE [AXIS]Selects the method of defining the axis of revolution used to define the geometry surface.This controls which parameters actually define the revolved surface. Other parameters areignored.

AXIS The axis of revolution is taken as a given coordinate axisof a coordinate system. (LINE, ANGLE, SYSTEM, AXIS).

LINE The axis of revolution is taken as the straight line between theend points of a given geometry line (which is not necessarilystraight, but must be open, i.e., have non-coincident end points).(LINE, ANGLE, ALINE).

POINTS The axis of revolution is taken as the straight line between twogiven (non-coincident) geometry points. (LINE, ANGLE, AP1, AP2).

VECTORS The axis of revolution is defined by a position vector and adirection vector. (LINE, ANGLE, X0, Y0, Z0, XA, YA, ZA).

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Sec. 6.4 Surfaces

LINELabel number of the initial geometry line to be rotated about the axis thereby defining therevolved surface.

ANGLEAngle of rotation (in degrees). Note ANGLE must be in the range -360 ≤ ANGLE ≤ 360.The sign of the angle is given by considering the right hand rule � i.e., if you curl yourfingers around the axis of revolution, with the thumb pointing along the axis, then a positiveangle is in the direction of the curl of the fingers.


AXIS [XL]Selects which of the basic axes (XL, YL, ZL) of the local coordinate system, given by param-eter SYSTEM, is used as the axis of revolution. {XL/YL/ZL}





PCOINCIDE [YES]Geometry points/lines are to be located at the edges of the surface beside the initial line givenby LINE. This parameter indicates whether to check the edge point location against existinggeometry, and use an existing point (YES) rather than generate a new geometry point (with anew label) (NO). {YES/NO}

SURFACE REVOLVED




NDIV [DEFAULT]Number of subdivisions assigned to the surface in the revolved direction. The DEFAULTnumber of subdivisions is taken from the parameter NDIV in the command SUBDIVIDEDEFAULT.

lineiLabel numbers of geometry lines. The data line input allows for more than one line to berevolved.

Auxiliary commands


When deleting surface, OPTION = ALL will delete any vertex points or edge lineswhich have no other dependent geometry; otherwise (OPTION = SURFACE), only thesurface itself will be deleted.

SURFACE REVOLVED


Sec. 6.4 Surfaces

SURFACE TRANSFORMED NAME PARENT TRANSFORMATIONPCOINCIDE PTOLERANCE NCOPY

surfacei

SURFACE TRANSFORMED defines a geometry surface to be a geometrical transformation ofanother existing geometry surface. The transformed geometry surface is identified by its labelnumber NAME. If NCOPY is greater than 1, the other newly defined transformed geometrysurfaces are identified by the current highest geometry surface label number + 1.

NAME [(current highest geometry surface label number) + 1]Label number of the geometry surface to be defined.

PARENTThe surface which, after transformation, gives the surface being defined.

TRANSFORMATIONLabel number of a geometrical transformation, see commands TRANSFORMATION.

PCOINCIDE [NO]This parameter indicates whether to check the location of the transformed surface verticesagainst existing geometry point coordinates, and use an existing point (YES) rather thangenerate a new geometry point (with a new label) (NO). {YES/NO}


NCOPY [1]Parameter defines number of surfaces to be generated by the transformation - transformationis repeated NCOPY times.

surfaceiLabel numbers of surface to be transformed.

Auxiliary commands


SURFACE TRANSFORMED



SFTHICKNESS

namei thicki dthick1i dthick2i dthick3i dthick4i

SFTHICKNESS defines surface thicknesses. <Not applicable to ADINA-F.>

nameiThe surface label number.

thicki [0.0]The surface thickness.

dthick1i [0.0]The deviation of thickness for surface �surfacei� at surface vertex 1.




Note: Input of surface thickness is given as a constant thickness together with deviationsfrom that value at each of the vertices.

Thus the thickness at vertex1 = thick + dthick1.

To input constant surface thicknesses, only the first two entries on the data lineinput need be entered (since the default deviations are zero).

To input varying surface thickness you could enter a constant thickness of 0.0 andset the deviations to the vertex thicknesses, or use some median thickness withnon-zero deviations.

Note: Thickness is measured in the direction of the normal vector at the vertex,determined by the right-hand rule in relation to the ordering of the surface vertices.

Auxiliary commands

LIST SFTHICKNESS FIRST LAST

SFTHICKNESS


Sec. 6.4 Surfaces

CHECK-SURFACES

CHECK-SURFACES checks geometry surface connections looking for two adjoining surfaceswhich are oppositely oriented such that the surface normals would be opposite. Suchconditions would likely be the source of a modeling error when elements of type SHELL aregenerated on such surfaces.

The command has no parameters and reports geometry surface pairs which should be moreclosely examined and re-oriented if necessary.

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VOLUME PATCH NAME SHAPE FACE1 FACE2 FACE3FACE4 FACE5 FACE6

VOLUME PATCH defines a geometry volume to be bounded by faces which are specifiedgeometry surfaces.

NAME [(current highest geometry volume label number) + 1]Label number of the geometry volume.

VOLUME PATCH

SHAPE = HEX SHAPE = PRISM

SHAPE = TETRA SHAPE = PYRAMID

P1

P2

P3

P4

P1P2

P3

P5

P2 P1

P5

P7

P3

P6

FACE 1

FACE 4

FACE 3

FACE 2

P4

P8

FACE 6

P1P2

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P5

P6

FACE 5

FACE 4FACE

5

FACE 1

FACE 2

FACE 3

FACE 4

FACE 1

FACE 3

FACE 2FACE 4

FACE 1

FACE 3

FACE 5

P4

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Sec. 6.5 Volumes

SHAPE [HEX]Selects the shape of the volume to be defined. This controls which of the parameters(geometry surface label numbers) are actually used to define the volume, other parameters areignored. The faces of the volume must connect as shown in the Figures.

HEX Hexahedral �brick� volume (FACE1, FACE2, FACE3, FACE4,FACE5, FACE6). Note that each face must be a quadrilateralgeometry surface.

PRISM Prismatic volume (FACE1, FACE2, FACE3, FACE4, FACE5). Notethat faces FACE2 and FACE4 must be triangular geometry sur-faces, whilst faces FACE1, FACE3, and FACE5 must be quadrilat-eral geometry surfaces.

TETRA Tetrahedral volume (FACE1, FACE2, FACE3, FACE4). Note thateach face must be a triangular geometry surface.

PYRAMID 5-faced volume (FACE1, FACE2, FACE3, FACE4, FACE5). Notethat face FACE1 must be a quadrilateral geometry surface, whilstfaces FACE2, FACE3, FACE4, and FACE5 must be triangulargeometry surfaces.

FACE1FACE2FACE3FACE4FACE5FACE6Label numbers of geometry surfaces comprising the faces of the geometry volume. SeeFigure.

Note: The faces must be connected, i.e., the edges of adjacent faces (geometry surfaces)must coincide (i.e., refer to a common geometry line), otherwise an error conditionresults.

Auxiliary commands

LIST VOLUME FIRST LASTDELETE VOLUME FIRST LAST OPTION

When deleting volume, OPTION = ALL will delete any vertex points, edge lines orface surfaces which have no other dependent geometry; otherwise (OPTION =VOLUME), only the volume itself will be deleted.

VOLUME PATCH



VOLUME VERTEX NAME SHAPE VERTEX1 VERTEX2 VERTEX3VERTEX4 VERTEX5 VERTEX6 VERTEX7VERTEX8

VOLUME VERTEX defines a geometry volume in terms of its vertices. This command issimilar to VOLUME PATCH � the underlying volume geometry point representation isidentical, only the method of definition differs. If no geometry line exists between adjacentgeometry points, then the command will automatically generate straight geometry linesbetween the appropriate geometry point pairs. If the volume edges do not comprise theedges of existing geometry surfaces at the faces of the volume, then the command willautomatically generate geometry surfaces at the volume faces with the required edges(existing or generated).

VOLUME VERTEX

SHAPE = HEX SHAPE = PRISM

SHAPE = TETRA SHAPE = PYRAMID

P1

P2

P3

P4

P1P2

P3

P5

P2 P1

P5

P7

P3

P6

P4

P8

P1P2

P3 P4

P5

P6

P4


Sec. 6.5 Volumes


SHAPE [HEX]Selects the shape of the volume to be defined. This controls which of the parameters(geometry point label numbers) are actually used to define the volume � other parameters areignored. The vertices of the volume must connect as shown in the Figure.

HEX Hexahedral �brick� volume.

PRISM Prismatic volume.

TETRA Tetrahedral volume.

PYRAMID 5-faced volume.

VERTEXi (i = 1�8)Label numbers of geometry points which are the vertices of the geometry volume. See Figurefor vertex numbering.

Auxiliary commands


When deleting volumes, OPTION = ALL will delete any vertex points, edge lines orface surfaces which have no other dependent geometry; otherwise (OPTION =VOLUME), only the volume itself will be deleted.

VOLUME VERTEX



VOLUME REVOLVED NAME MODE SURFACE ANGLE SYSTEM AXISALINE AP1 AP2 X0 Y0 Z0 XA YA ZAPCOINCIDE PTOLERANCE NDIV

surfacei

VOLUME REVOLVED defines one or more geometry volumes by rotating one or moregeometry surfaces about an axis. The first newly defined geometry volume is identified by itslabel number NAME. The other newly defined geometry volumes are identified by thecurrent highest geometry volume label number + 1.

NAME [(current highest geometry volume label number) + 1]Label number of the revolved geometry volume.

MODE [AXIS]Selects the method of defining the axis of revolution used to define the geometry volume.This controls which parameters actually define the revolved volume. Other parameters areignored.

AXIS The axis of revolution is taken as a given coordinate axis of acoordinate system. (SURFACE, ANGLE, SYSTEM, AXIS).

LINE The axis of revolution is taken as the straight line between the end pointsof a given geometry line (which is not necessarily straight, but must beopen � i.e., have non-coincident end points). (SURFACE, ANGLE, ALINE).

POINTS The axis of revolution is taken as the straight line between two given(non-coincident) geometry points. (SURFACE, ANGLE, AP1, AP2).

VECTORS The axis of revolution is defined by a position vector and a directionvector. (SURFACE, ANGLE, X0, Y0, Z0, XA, YA, ZA).

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Sec. 6.5 Volumes

SURFACELabel number of the initial geometry surface to be rotated about the axis, thereby defining therevolved volume.ANGLEAngle of rotation (in degrees). Note ANGLE must be in the range -360 ≤ ANGLE ≤ 360(with ANGLE = 360 or -360 defining a closed line, i.e., a circle). The sign of the angle isgiven by considering the right hand rule � i.e., if you curl your fingers around the axis ofrevolution, with the thumb pointing along the axis, then a positive angle is in the direction ofthe curl of the fingers.


AXIS [XL]Selects which of the base axes (XL, YL, ZL) of the local coordinate system, given by param-eter SYSTEM, is used as the axis of revolution. {XL/YL/ZL}





PCOINCIDE [YES]Geometry point are to be located at the other end of the volume from the initial surface givenby SURFACE. This parameter indicates whether to check the location against existinggeometry point coordinates, and use an existing point (YES) rather than generate a newgeometry point (with a new label) (NO). {YES/NO}

VOLUME REVOLVED




NDIV [DEFAULT]Number of subdivisions assigned to the surface in the revolved direction. The DEFAULTnumber of subdivisions is taken from the parameter NDIV in the command SUBDIVIDEDEFAULT.

surfaceiLabel numbers of geometry surfaces. The data line input allows for more than one surface tobe revolved.

Auxiliary commands


When deleting volume, OPTION = ALL will delete any vertex points, edge lines orface surfaces which have no other dependent geometry; otherwise (OPTION =VOLUME), only the volume itself will be defined.

VOLUME REVOLVED


Sec. 6.5 Volumes

VOLUME EXTRUDED NAME SURFACE OPTION DX DY DZ SYSTEMPCOINCIDE PTOLERANCE NDIV LINE RATIOPROGRESSION CBIAS

surfacei

VOLUME EXTRUDED defines one or more geometry volumes by displacing geometrysurfaces in a given direction or along a line. Please refer to LINE description below forlimitations.

NAME [(current highest geometry volume label number) + 1]Label number of the extruded geometry volume.

SURFACELabel number of the initial geometry surface to be displaced, thereby defining the extrudedvolume.

OPTION [VECTOR]This parameter defines the type of extrusion. {VECTOR/LINE}

VECTOR volumes are defined by displacing geometry surfaces in a given direction.

LINE volumes are defined by displacing geometry surfaces along a line.

DX [1.0]DY [0.0]DZ [0.0]Components of displacement vector with respect to the base coordinates (XL, YL, ZL) ofcoordinate system SYSTEM. Note that this is the actual displacement vector, i.e., it specifies

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both magnitude and direction. These parameters are only used when OPTION=VECTOR.


PCOINCIDE [YES]Geometry point are to be located at the other end of the volume from the initial surface givenby SURFACE. This parameter indicates whether to check the location against existinggeometry point coordinates, and use an existing point (YES) rather than generate a newgeometry point (with a new label) (NO). {YES/NO}


NDIV [DEFAULT]Number of subdivisions assigned to the surface in the extruded direction. The DEFAULTnumber of subdivisions is taken from the parameter NDIV in the command SUBDIVIDEDEFAULT. This parameter is only used when OPTION=VECTOR.

LINEThe geometry line label. Only straight lines, extruded lines or combined lines are allowed. If acombined line is used, the combined line should be either straight or extruded. This parameteris only used when OPTION=LINE. For lines that do not meet these conditions, the com-mand VOLUME SWEEP should be used.

RATIO [1.0]Ratio of lengths of the last to first element edges along the extruded vector. The grading ofelement lengths is governed by parameter PROGRESSION. This parameter is only used whenOPTION=VECTOR.

PROGRESSION [GEOMETRIC]When element lengths are to be graded, the distribution of element lengths can be selectedfrom the following options. This parameter is only used when OPTION=VECTOR.{ARITHMETIC/GEOMETRIC}

ARITHMETIC The difference in length of each element edge from its adjacent edges isconstant.

GEOMETRIC The ratio of lengths of adjacent element edges is constant.

VOLUME EXTRUDED


Sec. 6.5 VolumesVOLUME EXTRUDED

CBIAS [NO]Indicates if central bias is used along the extruded vector. This parameter is only used whenOPTION=VECTOR. {NO/YES}

surfaceiLabel numbers of geometry surfaces. The data line input allows for more than one surface tobe extruded.

Auxiliary commands


When deleting volumes, OPTION = ALL will delete any vertex points, edge lines orface surfaces which have no other dependent geometry; otherwise (OPTION =VOLUME), only the volume itself will be defined.



VOLUME SWEEP NAME SURFACE LINE DELETE-LINE ALIGNMENTPCOINCIDE PTOLERANCE NPTS

surfacei

Defines one or more geometry volumes by sweeping one or more geometry surfaces along aline. The first newly defined geometry volume is identified by its label number NAME. Theother newly defined geometry volumes are identified by the current highest geometry volumelabel number + 1.

NAME [(current highest geometry volume label number) + 1]Label number of the swept geometry volume.

SURFACELabel number of the initial geometry surface to be displaced, thereby defining the sweptvolume.

LINEThe geometry line label. Unlike the command VOLUME EXTRUDED, there is no limitation tostraight lines, extruded lines or combined lines.

DELETE-LINE [YES]Indicates whether or not the lines are to be deleted after applying the command VOLUMESWEEP.

ALIGNMENT [NORMAL]This parameter specifies the direction of the surface during sweeping.

NORMAL Surface normal is at fixed angle to line tangent.

VOLUME SWEEP

SURFACE

P1P2

P3 P4

LINE


Sec. 6.5 Volumes

PARALLEL Surface normal always points to the same direction.

PCOINCIDE [YES]Geometry points are to be located at the other end of the volume from the initial surface givenby SURFACE. This parameter indicates whether to check locations against existing geometrypoint coordinates, and use existing points rather than generate new geometry points (withnew labels).

PTOLERANCE [Default given by TOLERANCES GEOMETRIC]If PCOINCIDE=YES, then this parameter provides a tolerance value for checking the globalcoordinates of a location against those of existing geometry points.

NPTS [3]The number of intermediate points of non-straight and non-arc lines.

surfaceiLabel numbers of geometry surfaces. The data line input allows for more than one surface tobe swept.

Auxiliary commands

LIST VOLUME FIRST LASTDELETE VOLUME FIRST LAST

VOLUME SWEEP



VOLUME TRANSFORMED NAME PARENT TRANSFORMATION PCOINCIDEPTOLERANCE NCOPY

volumei

The command VOLUME TRANSFORMED defines a geometry volume to be a geometricaltransformation of another existing geometry volume. The transformed geometry volume isidentified by its label number NAME. If NCOPY is greater than 1, the other newly definedtransformed geometry volumes are identified by the current highest geometry volume labelnumber + 1.

NAME [(current highest geometry volume label number) + 1]Label number of the transformed geometry volume to be defined.

PARENTThe volume which, after transformation, gives the volume being defined.

TRANSFORMATION [(current transformation label number)]Label number of a geometrical transformation defined by command TRANSFORMATION.

PCOINCIDE [NO]This parameter indicates whether to check the location of the transformed volume vertexpoints against existing geometry points, and use existing points (YES) rather than generatenew geometry points (NO) (with a new label) . {YES/NO}


NCOPY [1]Parameter defines number of volumes to be generated by the transformation - transformationis repeated NCOPY times.

volumeiLabel numbers of volume to be transformed.

Auxiliary commands

LIST VOLUME FIRST LASTDELETE VOLUME FIRST LAST

Note that no geometry volume is deleted which is referenced by any other model entity,e.g., as part of the definition of another volume or by virtue of a mesh generationcommand (i.e. there are nodes and/or elements associated with the volume).

VOLUME TRANSFORMED


Sec. 6.6 Solid models

BODY SURFACES NAME

surfacei sensei

This command is OBSOLETE and is available only for compatibility with old input files.

Defines a solid geometry body, as an oriented collection of geometry surfaces. The set ofsurfaces must form a complete boundary of a solid with the proper orientation such that theoriented surface normal points out of the body. In this way the surfaces yield a boundaryrepresentation of a solid � note that a manifold representation is assumed, thus each surfaceedge (line) must be connected to exactly two (2) surfaces. A body may be meshed directly viathe GBODY command (in which case free-form meshing is necessarily used - there is nointrinsic parametric description of the body to support mapped meshing).

NAME [(current highest geometry volume label number) + 1]Label number of the body to be defined.

surfaceiLabel number of a geometry surface.

sensei [+1]Sense indicator for surfacei:

+1 the surface normal points out of the body.

-1 the surface normal points into the body.

Auxiliary commands

LIST BODY FIRST LASTDELETE BODY FIRST LAST

BODY SURFACES


Chap. 6 Geometry definition BODY VOLUMES

BODY VOLUMES NAME

volumei

This commnad is OBSOLETE and is available only for compatibility with old input files.

Defines a solid geometry body, as a collection of geometry volumes. The internal faces of thebody resulting from connected volumes are �cancelled out� yielding a boundary representa-tion of a solid in terms of an oriented set of surface patches. A body may be meshed directlyvia the GBODY command (in which case free-form meshing is necessarily used - there is nointrinsic parametric description of the body to support mapped meshing).

NAME [(current highest geometry volume label number) + 1]Label number of the body to be defined.

volumeiLabel number of a geometry volume.

Auxiliary commands

LIST BODY FIRST LASTDELETE BODY FIRST LAST



FACE-THICKNESS BODY

facei thicki

FACE-THICKNESS defines solid geometry face thicknesses.

BODY [currently active solid body]Solid geometry body label number.

faceiThe face label number (for body BODY).

thicki [0.0]The face thickness (constant).

Auxiliary commands

LIST FACE-THICKNESS FIRST LAST

FACE-THICKNESS



FACELINK NAME OPTION BODY1 FACE1 BODY2 FACE2PCTOLERANCE

FACELINK establishes a link, for meshing purposes, between two faces of distinct solid bodies, orbetween a face of a solid body and a surface. Once the link is established, the program stores themesh triangulation of whichever of the two faces/surfaces is meshed first. The meshing of thecorresponding linked face/surface utilizes the same triangulation, thereby resulting in congruenttriangulations and compatible meshes �across� the linked faces/surfaces.

NAME [(highest face link label number) + 1]The label number of the face link.

OPTION [TWO]This parameter offers basic options for creating the facelinks:

ONE Facelinks are created between the faces of a given body and the remainingadjacent faces and surfaces.

TWO Facelinks are created between two bodies.

ALL Facelinks are created for all the faces and surfaces in the model.

BODY1The label number of the solid body of which FACE1 is a bounding face. Note: BODY1 = 0implies that FACE1 is a surface.

FACE1The label number of the first face/surface of the linked pair.

BODY2The label number of the solid body of which FACE2 is a bounding face. Note: BODY2 = 0implies that FACE2 is a surface.

FACE2The label number of the second face/surface of the linked pair.

PCTOLERANCE [DEFAULT]Tolerance used to determine whether two faces match.

DEFAULT value set by parameter COINCIDENCE of commandTOLERANCES GEOMETRIC

FACELINK


Sec. 6.6 Solid modelsFACELINK

Note: BODY1, FACE1, BODY2, FACE2 are used only when OPTION=ONE or TWO.

Note: BODY1 cannot equal BODY2, i.e., either two distinct bodies are given or onesolid body face and a surface are given.

Note: When a body is modified, the associated face links will be updated.When a body is deleted, the associated face links will be deleted.When a surface is deleted, the associated face link will be deleted

Auxiliary commands

LIST FACELINK FIRST LASTDELETE FACELINK FIRST LAST


Chap. 6 Geometry definition SPLIT-EDGE

SPLIT-EDGE NAME BODY USPLIT

SPLIT-EDGE splits an edge of a body into two edges by giving a parameter along the edge.

NAMELabel number of the geometry edge to be split.

BODY [current body label]Label number of the solid geometry body.

USPLIT [0.5]A parameter value indicating the point along edge NAME at which splitting takes place. Theparameter value can range between 0.0 (the starting point of edge NAME) to 1.0 (the endpoint of edge NAME), but cannot be 0.0 or 1.0, i.e. the splitting point on the edge mustcreate two new edges of non-zero length.


Sec. 6.6 Solid modelsSPLIT-FACE

SPLIT-FACE NAME BODY P1 P2

SPLIT-FACE splits a face of a body into two faces by giving two points on the face.

NAMELabel number of the geometry face to be split.

BODY [current body label]Label number of the solid geometry body.

P1Label number of the first geometry point.

P2Label number of the second geometry point.



BODY-DISCREP NAME

Creates a �discrete boundary representation� for a given body. The �discrete boundaryrepresentation� (�discrete brep� in short) of a body is simply a triangular surface mesh (of thebody) that has the advantage of being modifiable by command BODY-DEFEATURE.

NAMEBody label.

Auxiliary commands

LIST BODY-DISCREP FIRST LASTDELETE BODY-DISCREP FIRST LAST

BODY-DISCREP



BODY-DEFEATURE NAME SIZE DOMKEEP DOMREMV PREVIEWOPTION ANGLE SPREAD

After having obtained a �discrete boundary representation� (�discrete brep� in short) of abody with the command BODY-DISCREP, this command enables the modification of the�discrete brep�. The actual (geometric) body is never modified. The meshing is limited to 4/10/11-node tetrahedral elements.

The main purpose of this command is the removal of �small� features which can be of the�boss� type (protrusion) or the �cut� type (may extend to being a hole). The secondarypurpose is the removal of surface triangles (on the �discrete brep�) that have either a �small�length or height.

NAMEBody label.

SIZEAny surface triangle on the �discrete brep� whose shortest length or height is below SIZEshould be eliminated from the �discrete brep�.

DOMKEEP [0]Domain (see DOMAIN command) of body faces that should not be modified. More exactly,the surface triangles on the �discrete brep� that are classified on a body face in the domainshould not be modified.

DOMREMV [0]Domain (see DOMAIN command) of body faces that should be removed. More exactly, thesurface triangles on the �discrete brep� that are classified on a body face in the domainshould be removed. It is recommended to use one domain per feature to remove.

PREVIEW [NO]Preview flag. {YES/NO}

YES the command flags the surface triangles on the �discrete brep� that are targetedfor removal to enable their display. It does not actually remove them.

NO the command will remove the surface triangles that are targeted for removal.

OPTION [COARSEN]Method by which the body faces defined by DOMREMV are removed. {REMESH1/REMESH2/COARSEN}

REMESH1, REMESH2 the body faces in domain defined by DOMREMV are removedusing a remeshing algorithm. This option should be used only

BODY-DEFEATURE



when the frontier of the domain is convex. It has to be used whenthe feature is a hole (whose frontiers should be convex).With REMESH1, the normals used to remesh the domain comefrom the (boundary discrete representation) faces inside thedomain. With REMESH2, the normals used come from the facesimmediately adjacent to the domain.

COARSEN the body faces in the domain defined by DOMREMV are removedusing a coarsening algorithm that is incremental. It cannot be usedwhen the feature is a hole.

ANGLE [30.0]This is the angle in degrees used when using the incremental coarsening algorithm. Thelarger the angle, the more surface triangles can be removed but the more deformed the�discrete brep� will be. When attempting to remove a feature using the COARSEN option, itis recommended to set the ANGLE to 180.0 so that the feature can be completely removed.{0.0 ≤ ANGLE ≤ 180.0}

SPREAD [YES]Determines whether the removal of surface triangles in the �discrete brep� extends to othersurfaces triangles outside the feature indicated by DOMREMV. {YES/NO}

NO the command only attempts to remove surface triangles that are below SIZE or thatmake up a feature (as indicated by DOMREMV). Other surface triangles will not bemodified.

YES the command may also modify other surface triangles if necessary.

Notes:

If a DOMREMV domain is given, the command will only attempt to remove the surfacetriangles associated with the domain. The SIZE parameter is then only used to spread (seeSPREAD parameter).

If no DOMREMV domain is given, the command will attempt to remove all surface triangleswhose dimensions (shortest length or height) are below SIZE.

BODY-DEFEATURE





Chap. 6 Geometry definition BODY-CLEANUP

BODY-CLEANUP NAME SIZE DOMKEEP DOMREMV PREVIEW

The main purpose of this command is the removal of �short� body edges and/or �thin� bodyfaces. The actual (geometric) body is never modified but its AUI representation is.

NAMEBody label.

SIZEAny body edge whose length is below SIZE should be eliminated. Any body face whoseboundary is reduced to 2 edges (after the elimination of body edges) and whose width isbelow SIZE should be eliminated.

DOMKEEP [0]Domain (see DOMAIN command) of body edges and/or faces that should not be removed.

DOMREMV [0]Domain (see DOMAIN command) of body edges and/or faces that should be removed.

PREVIEW [NO]Preview flag. {YES/NO}

YES the command flags the body edges and/or faces that are targeted for removal toenable their display. It does not actually remove them.

NO the command will remove them.

Notes:

If a DOMREMV domain is given, the command will only attempt to remove the body edgesand/or faces that are given. The SIZE parameter is not used.

If no DOMREMV domain is given, the command will attempt to remove body edges and/orfaces whose dimensions are below SIZE.


Sec. 6.6 Solid modelsBODY-RESTORE

BODY-RESTORE BODY

Restores the AUI topological representation of the body corresponding to the state of thebody before commands such as BODY-CLEANUP, REM-EDGE or REM-FACE are executed(on that body).

BODYBody label.


Chap. 6 Geometry definition BODY-DSCADAP

BODY-DSCADAP NAME MAXNVARS MAXNVARC MAXDIST ADAPT

Adapts (according to the mesh densities set prior) the surface triangles that make up thegeometry of an STL body. The output is stored as a discrete representation (see the BODY-DISCREP command) which can be then meshed with the GBODY command. This commandshould only be used in conjunction with the LOAD-STL command.

NAMELabel of body.

MAXNVARS [30.0 (degrees)]Maximum normal variation used in edge swapping when adapting (improving quality of) thesurface mesh. When locally changing the topology of the surface mesh, the normal variations(before and after edge swapping) may not exceed MAXNVARS.Maximum normal variation used in vertex smoothing when adapting (improving quality of) thesurface mesh. When moving vertices of the surface mesh, the normal variations (before andafter vertex smoothing) may not exceed MAXNVARS. {0.0 ≤ MAXNVARS ≤ 180.0}

MAXNVARC [90.0 (degrees)]Maximum normal variation used in edge collapsing when adapting (coarsening) the surfacemesh. When locally changing the topology of the surface mesh, the normal variations (beforeand after edge collapsing) may not exceed MAXNVARC. {0.0 ≤ MAXNVARC ≤ 180.0}

MAXDIST [0.0]Maximum (absolute) distance allowed from new edge to "reference" mesh (STL body) whenperforming edge swaps. This distance threshold is used in conjunction with MAXNVARSduring edge swapping. By default, MAXDIST is set to 0.0 and therefore disabled.{MAXDIST ≥ 0.0}

ADAPT [YES]If set to NO, no adaptation will take place and the STL surface mesh will be stored directly asa discrete representation bypassing totally the adaptation process.






LINE-FUNCTION NAME TYPE DL1 DL2 DL3 NPOINT

i fvali (i = 1�NPOINT)

LINE-FUNCTION describes the variation of a quantity along a line. It may be used, forinstance, to indicate how a load is distributed along some geometry line of the model. Notethat the variation is spatial; variation of a quantity in time is described by TIMEFUNCTION.This command can be applied to edges.

NAMELabel number of the line-function.

TYPE [LINEAR]Selects the type of data variation, see Figure. This controls the actual parameters used �other parameters are ignored.

LINEAR A linear variation from value DL1 to DL2.

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Sec. 6.7 Spatial functions

QUADRATIC A quadratic variation from value DL1, through value DL3, tovalue DL2.

TABULAR The function values are given at a set of equally spaced pointsalong the line. The function is linearly interpolated

between the input values.DL1Value at the starting point of the line (u = 0 � see Figure).

DL2 [DL1]Value at the end point of the line (u = 1 � see Figure).

DL3 [DL1]Value at the middle point of the line (u = 0.5 � see Figure). This value should not be input forTYPE = LINEAR.

NPOINT [3]The number of input function values, used when TYPE = TABULAR. The values are as-signed at equally spaced points along the line, with linear interpolation used to determinevalues along the line. The first point corresponds to the starting point of the line (u = 0), andthe last point to the end point of the line (u = 1). Note that NPOINT must be at least 3(NPOINT = 2 would be equivalent to selecting TYPE = LINEAR).

iIndex of the input function point, which can take a value from 1 to NPOINT.

fvali [1.0]Value of the function at index point �i�.

Auxiliary commands

LIST LINE-FUNCTION FIRST LASTDELETE LINE-FUNCTION FIRST LAST

LINE-FUNCTION



SURFACE-FUNCTION NAME TYPE DS1 DS2 DS3 DS4 DS5 DS6 DS7DS8 DS9 MPOINT NPOINT

row col fvalij

SURFACE-FUNCTION describes the variation of a quantity across a surface. It may be used,for instance, to indicate how a load is distributed over some geometry surface of the model.Note that the variation is spatial; variation of a quantity in time is described byTIMEFUNCTION.

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NAMELabel number of the surface-function.

TYPE [LINEAR]Selects the type of data variation � see Figure. This controls the actual parameters used.

LINEAR A bilinear variation from surface vertex values DS1, DS2, DS3,DS4.

QUADRATIC A biquadratic variation from surface vertex values DS1 to DS4,and mid-side/internal surface point values DS5 to DS9.

TABULAR The function values are given at a grid of regularly spaced pointson the surface. The function is bilinearly interpolated betweenthe input values.

DS1Value at the (u = 1, v = 1) vertex point of the surface, see Figure.

DS2 [DS1]Value at the (u = 0, v = 1) vertex point of the surface, see Figure.



DS5 [DS1]Value at the (u = 0.5, v = 1) mid-side point of the surface, see Figure.

DS6 [DS1]Value at the (u = 0, v = 0.5) mid-side point of the surface, see Figure.

DS7 [DS1]Value at the (u = 0.5, v = 0) mid-side point of the surface, see Figure.

DS8 [DS1]Value at the (u = 1, v = 0.5) mid-side point of the surface, see Figure.

DS9 [DS1]Value at the (u = 0.5, v = 0.5) internal point of the surface, see Figure.

SURFACE-FUNCTION



MPOINT [3]The number of input points in the u-parametric direction of the surface, used when TYPE =TABULAR. The function values are assigned for a grid of points on the surface, with bilinearinterpolation used to determine values on the surface. MPOINT defines the number of�columns� for the input grid.

NPOINT [3]The number of input points in the v-parametric direction of the surface, used when TYPE =TABULAR. The function values are assigned for a grid of points on the surface, with bilinearinterpolation used to determine values on the surface. NPOINT defines the number of �rows�for the input grid.

rowRow index of the input function point, which can take a value from 1 to NPOINT.{1 ≤ row ≤ NPOINT}

colColumn index of the input function point, which can take a value from 1 to MPOINT.{1 ≤ col ≤ MPOINT}

fvalij [1.0]Value of the function at index point (i = row, j = col).

Auxiliary commands

LIST SURFACE-FUNCTION FIRST LASTDELETE SURFACE-FUNCTION FIRST LAST

SURFACE-FUNCTION



VOLUME-FUNCTION NAME TYPE DV1 DV2 DV3 DV4 DV5 DV6 DV7DV8 ... DV27

VOLUME-FUNCTION describes the variation of a quantity within a volume. It may be used,for instance, to indicate how a load is distributed within some geometry volume of the model.Note that the variation is spatial; variation of a quantity in time is described byTIMEFUNCTION.

NAMELabel number of the volume-function.

TYPE [LINEAR]Selects the type of data variation. This controls the actual parameters used.

LINEAR A trilinear variation from volume vertex values DV1 to DV8.

QUADRATIC A triquadratic variation from volume vertex values DV1 to DV8,and mid-side/internal volume point values DV9 to DV27.

DV1...DV27 [DVi = DV1 (i = 2...27)]

Values at the vertex, mid-side, and internal points of the volume, see table below.

Auxiliary commands

LIST VOLUME-FUNCTION FIRST LASTDELETE VOLUME-FUNCTION FIRST LAST

VOLUME-FUNCTION



Volume-function parametric locations:

Value u v w

DV1 1 1 1DV2 0 1 1DV3 0 0 1DV4 1 0 1DV5 1 1 0DV6 0 1 0DV7 0 0 0DV8 1 0 0DV9 0.5 1 1DV10 0 0.5 1DV11 0.5 0 1DV12 1 0.5 1DV13 0.5 1 0DV14 0 0.5 0DV15 0.5 0 0DV16 1 0.5 0DV17 1 1 0.5DV18 0 1 0.5DV19 0 0 0.5DV20 1 0 0.5DV21 0.5 0.5 0.5DV22 0.5 1 0.5DV23 0 0.5 0.5DV24 0.5 0 0.5DV25 1 0.5 0.5DV26 0.5 0.5 1DV27 0.5 0.5 0

VOLUME FUNCTION


Sec. 6.8 Transformations

TRANSFORMATION COMBINED NAME

positioni transformi

TRANSFORMATION COMBINED defines a general transformation as an ordered sequenceof existing transformations defined by command TRANSFORMATION. The associatedtransformation matrix is calculated by concatenating the matrices of the sequence of transfor-mations.

NAME [(current highest transformation label number) + 1]Label number of transformation being defined.

positioniIndex for the transformation, indicating its position in the order of transformation application.In the concatenation the transformation associated with �positioni� = 1 is applied first, thenthat for �positioni� = 2, and so on. If a transformation is not defined for a given index thenthe identity transformation is assumed. The index may also be used to delete a transforma-tion from the concatenating sequence.

transformi [0]Label number of an existing transformation defined by command TRANSFORMATION(provided that no recursion is implied). A zero value indicates the identity transformation.

Example

TRANSFORMATION TRANSLATION NAME=1 MODE=SYSTEM SYSTEM=1,DX=1.0

TRANSFORMATION ROTATION NAME=2 MODE=AXIS SYSTEM=1,AXIS=XL ANGLE=35.0

TRANSFORMATION TRANSLATION NAME=3 MODE=SYSTEM SYSTEM=1,DX=-1.0

...TRANSFORMATION COMBINED NAME=4 1 1 2 2 3 [email protected] COMBINED NAME=5 1 4 2 1@

TRANSFORMATION COMBINED



The last command is equivalent to

TRANSFORMATION COMBINED NAME=5 1 1 2 2 3 3 4 1@

Auxiliary commands

LIST TRANSFORMATION FIRST LASTDELETE TRANSFORMATION FIRST LAST

TRANSFORMATION COMBINED



TRANSFORMATION DIRECT NAME T11 T12 T13 T14 T21 T22 T23T24 T31 T32 T33 T34

TRANSFORMATION DIRECT defines a general 3-D transformation by directly specifying thetransformation matrix.

NAME [(current highest transformation label number) + 1]Label number of the transformation.

TijComponents of the 3-D transformation matrix:

Auxiliary commands


TRANSFORMATION DIRECT

T T T T

T T T T

T T T T

0 0 0 1

11 12 13 14

21 22 23 24

31 32 33 34



TRANSFORMATION POINTS NAME P1 P2 P3 Q1 Q2 Q3

TRANSFORMATION POINTS defines a rigid-body 3-D transformation by the specificationof 6 geometry points � 3 �initial� points P1, P2, P3, and 3 �target� points Q1, Q2, Q3.

The transformation is such that point P1 is transformed into point Q1, the direction from P1 toP2 is transformed into the direction from Q1 to Q2, and the plane defined by the 3 initialpoints is transformed into the plane defined by the 3 target points.


P1, P2, P3Label numbers of three non-coincident, non-collinear, initial geometry points.

Q1, Q2, Q3Label numbers of three target points, which must also be non-coincident and non-collinear.

Auxiliary commands


TRANSFORMATION POINTS



TRANSFORMATION REFLECTION NAME MODE SYSTEM PLANEP1 P2 P3

TRANSFORMATION REFLECTION defines a 3-D reflection (mirror) transformation about aplane.


MODE [SYSTEM]Selects the method of defining the plane of the transformation. This controls which param-eters actually define the transformation, other parameters are ignored.

SYSTEM The reflection is defined to be relative to one of the base coordinate planesof a given local coordinate system. (SYSTEM, PLANE)

POINTS The reflection plane is defined via three (non-collinear) points. (P1, P2, P3)

SYSTEM [currently active coordinate system]Local coordinate system label number. The reflection is made relative to one of the basecoordinate planes of this system.

PLANE [XZ]Selects a coordinate plane with respect to the base coordinate directions (XL, YL, ZL) of thecoordinate system �SYSTEM�.

XY XL-YL plane of coordinate system SYSTEM.

XZ XL-ZL plane of coordinate system SYSTEM.

YZ YL-ZL plane of coordinate system SYSTEM.

P1, P2, P3Label numbers of geometry points which define the plane of reflection for the trans-forma-tion. The points must be distinct, non-coincident, and non-collinear (in order to define aplane).

Auxiliary commands


TRANSFORMATION REFLECTION



TRANSFORMATION ROTATION NAME MODE SYSTEM AXIS LINEP1 P2 ANGLE X0 Y0 Z0 XA YA ZA

TRANSFORMATION ROTATION defines a 3-D rotation transformation, about an axis.


MODE [AXIS]Selects the method of defining the axis of rotation. This controls which parameters actuallydefine the rotation � other parameters are ignored.

AXIS The axis of rotation is taken as one of the basic axes (XL, YL, ZL)of the local coordinate system given by SYSTEM.(SYSTEM, AXIS, ANGLE)

LINE The axis of rotation is aligned with the straight line between theend points of a geometry line. Note that the geometry line is notnecessarily straight. (LINE, ANGLE)

POINTS The axis of rotation is taken to be the straight line between twogeometry points. (P1, P2, ANGLE)

VECTORS The axis of rotation is defined by a position vector (lying on theaxis), and a direction vector. (X0, Y0, Z0, XA, YA, ZA,ANGLE)

SYSTEM [currently active coordinate system]Local coordinate system label number. The rotation is relative to one of the base axes of thiscoordinate system.

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TRANSFORMATION ROTATION



AXIS [XL]Selects which of the base axes (XL, YL, ZL) of the local coordinate system given by SYSTEM,is used as the axis of rotation. {XL/YL/ZL}

LINELabel number of a geometry line. The axis of rotation is given by the straight line betweenthe starting point and ending point of the geometry line LINE.

P1P2Label numbers of two geometry points. The axis of rotation is the straight line betweengeometry points P1 and P2.

ANGLE [0.0]The angle of rotation, measured in degrees.

X0 [0.0]Y0 [0.0]Z0 [0.0]Global components of a position vector indicating a point lying on the axis of rotation.

XA [0.0]YA [0.0]ZA [0.0]Global components of a vector indicating the direction of the axis of rotation.

Auxiliary commands


TRANSFORMATION ROTATION



TRANSFORMATION SCALE NAME MODE SYSTEM POINT SX SY SZ

TRANSFORMATION SCALE defines a 3-D scaling transformation.


MODESelects the method of defining the transformation. This controls which parameters actuallydefine the transformation, other parameters are ignored.

SYSTEM The scaling transformation is defined by scale factors which are relative tothe origin of a given local coordinate system and which scale parallel toits base axes (XL, YL, ZL). (SYSTEM, SX, SY, SZ)

POINT The scaling transformation is defined with the origin at a given geometrypoint, and by scale factors which scale parallel to the global Cartesianaxes. (POINT, SX, SY, SZ)

SYSTEM [currently active coordinate system]Coordinate system label number. The scaling is relative to this coordinate system.

POINTGeometry point label number. The origin of the scaling transformation is taken as this point.

SX [1.0]SY [1.0]SZ [1.0]Scaling factors.

Auxiliary commands


TRANSFORMATION SCALE



TRANSFORMATION TRANSLATION NAME MODE SYSTEMDX DY DZ LINE P1 P2

TRANSFORMATION TRANSLATION defines a 3-D translation transformation.


MODE [SYSTEM]Selects the method of defining the translation. This controls which parameters actuallydefine the translation, other parameters are ignored.

SYSTEM The translation is defined by increments parallel to the base axes (XL, YL,ZL) of local coordinate system SYSTEM. (SYSTEM, DX, DY, DZ)

LINE The translation is defined as that which would translate the starting pointof a geometry line to the ending point of the same geometry line. (LINE)

POINTS The translation is defined as that which would translate one geometrypoint to another. (P1, P2)

SYSTEM [currently active coordinate system]Local coordinate system label number. For MODE = SYSTEM the translation is relative tothis coordinate system.

DX [0.0]DY [0.0]DZ [0.0]Translations parallel to the base Cartesian system (XL,YL,ZL) associated with local coordi-nate system SYSTEM.

LINELabel number of a geometry line. The translation is that which would translate the startingpoint of geometry line LINE to its ending point.

P1P2Label numbers of two geometry points. The translation is that which would translategeometry point P1 to geometry point P2.

Auxiliary commands


TRANSFORMATION TRANSLATION



TRANSFORMATION INVERSE NAME TINVERT

Defines a 3-D geometry transformation as the inverse of another transformation.

NAME [(current highest transformation label number) + 1]Label number of the transformation to be defined.

TINVERTLabel number of the transformation to be inverted to give the transformation being defined.

Auxiliary commands


TRANSFORMATION INVERSE


Sec. 6.9 Miscellaneous

DOMAIN NAME

typei namei bodyi

Defines a geometry �domain�, which is a collection of geometry entities. A domain may bereferenced, for example, by parameter NCDOMAIN of the mesh generation commands (e.g.GSURFACE) to restrict nodal coincidence checking to within a set of geometry entitiesthereby facilitating partitioning of the finite element model into topologically distinct butgeometrically adjacent regions.

NAME [(current highest domain label number) + 1]Label number of the domain to be defined.

typeiGeometry entity type for entry �i� in the list of geometry entities which comprise the domain.{�POINT�/�LINE�/�SURFACE�/�VOLUME�/�EDGE�/�FACE�/�BODY�}

nameiLabel number of the geometry entity of type typei

bodyi [0]Label number of a solid body, used to identify the entity when typei = EDGE or FACE.

Auxiliary commands

LIST DOMAIN FIRST LASTDELETE DOMAIN FIRST LAST

DOMAIN



MEASURE GTYPE P1 P2 P3 BODY EDGE LINE N1 N2 N3SUBSTRUCTURE REUSE RESPONSE PROGRAM FACE

Measures the distance between 2 points or 2 nodes, the length of an edge or a line, or theangle formed by 3 points or 3 nodes.

GTYPE [POINTS]Options for measurement. {POINTS/EDGE/LINE/POINT-ANGLE/NODES/NODE-ANGLE/FACE/BODY}

POINTS Distance between two points.

EDGE Length of an edge of a body.

LINE Length of a line.

POINT-ANGLE Angle between three points.

NODES Distance between two nodes.

NODE-ANGLE Angle between three nodes.

FACE Area of a face of a body

BODY Volume of a body

P1, P2, P3Label numbers of existing geometry points. P3 is only used when GTYPE=POINT-ANGLE.

BODYBody label number.

EDGEEdge label number.

LINELine label number.

N1, N2, N3Label numbers of existing nodes. N1 and N2 are only used when GTYPE=NODES or NODE-ANGLE. N3 is only used when GTYPE=NODE-ANGLE.

SUBSTRUCTURE [current substructure label number]The substructure number of the node in the model. Not applicable to ADINA- T/-F.

MEASURE


Sec. 6.10 ADINA - MMEASURE

REUSE [current reuse label number]The reuse number of the node in the model. Not applicable to ADINA-T/-F.

RESPONSE [DEFAULT]Specifies the response for which the node is evaluated.

PROGRAM [current finite element program]The current finite element program, used only if GTYPE=NODES or NODE-ANGLE.

FACEFace label number.



GET-EDGE-FACES NAME BODY

GET-EDGE-POINTS NAME BODY

GET-EDGE-FACES lists the body faces connected to a body edge.

GET-EDGE-POINTS lists theAUI points bounding a body edge.

NAMEEdge label. {1, 2, ...}

BODYLabel of body the edge belongs to. {1, 2, ...}

GET-EDGE-FACES



GET-FACE-EDGES NAME BODY

Lists the body edges bounding a body face.

NAMEFace label. {1, 2, ...}

BODYLabel of body the face belongs to. {1, 2, ...}

GET-FACE-EDGES



REM-EDGE NAME BODY POINT

Removes a body edge by collapsing one end point onto the other. The remaining point isgiven as POINT. If POINT is set to 0, the remaining point is chosen by the command.

NAMEBody edge label. {1, 2, ...}

BODYLabel of body the edge belongs to. {1, 2, ...}

POINTLabel of point that will remain. {0, 1, 2, ...}

REM-EDGE


Sec. 6.9 MiscellaneousREM-FACE

REM-FACE NAME BODY EDGE

Removes a body face (bounded by exactly 2 edges) by collapsing one bounding edge ontothe other. The remaining edge is given as EDGE. If EDGE is set to 0, the remaining edge ischosen by the command.

NAMEBody face label. {1, 2, ...}

BODYLabel of body the face belongs to. {1, 2, ...}

EDGELabel of edge that will remain. {0, 1, 2, ...}



BODY BLEND NAME OPTION R1 R2 EDGE POINT

edgei (OPTION=CONSTANT, LINEAR)

or

facei (OPTION=FACE)

The command BODY BLEND takes an existing solid geometry body and modifies specifiededges to have a �radius� blend. Two options allow for a constant or variable �radius� blend.This command is only active when ADINA-M has been licensed.

BODY BLEND

NAMELabel number of the body to be blended. An existing body label number must be specified.

OPTION [CONSTANT]This parameter offers basic options for blending the edges.

CONSTANT Multiple edges are blended by a constant radius.

LINEAR A single edge of the body is blended by two radii - one at each end(vertex) of the edge.

FACE Multiple faces are blended by a constant radius.

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Sec. 6.10 ADINA - M

R1The first radius of the blend. R1 must be input with a positive value (no default is assumed).

R2The second radius of the blend. R2 is only used when OPTION=LINEAR,and must be inputwith a non-negative value (no default is assumed).

EDGELabel number of the edge to be blended. This parameter is only used whenOPTION=LINEAR, in whch case an existing edge label number ust be specified (no default isassumed).

POINTLabel number of a point at which the blend radius is R1. This parameter is only used whenOPTION=LINEAR, in which case an existing point label number must be specified (no defaultis assumed).

edgeiLabel numbers of body edges to be blended with (constant) radius R1. This data is only usedwhen OPTION=CONSTANT.

faceiLabel numbers of body faces to be blended with (constatnt) radius R1. This data is only usedwhen OPTION=FACE.

BODY BLEND



BODY BLOCK NAME OPTION POSITION ORIENTATIONCX1 CX2 CX3 CENTER SYSTEM AX AY AZBX BY BZ DX1 DX2 DX3 P1 P2

The command BODY BLOCK defines a solid geometry block or �brick� shape. A number ofoptions allow for the position, orientation, and dimensions of the block shape. The blockbody may be used in conjunction with other body shapes to form more complex geometriesusing the Boolean operation commands BODY MERGE, BODY SUBTRACT, BODY INTER-SECT. A body may be meshed directly via the GBODY command (in which case free-formmeshing is necessarily used - there is no intrinsic parametric description of the body tosupport mapped meshing).This command is only active when ADINA-M has been licensed.

BODY BLOCK

NAME [(highest body label number) + 1]Label number of the body to be defined.

OPTION [CENTERED] This parameter offers basic options for defining the block:

CENTERED The block is defined by its center, orientation and dimensions.

DIAGONAL The block is defined by two diagonally opposite geometry points andits orientation.

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Sec. 6.10 ADINA - M

POSITION [VECTOR]Specifies how the block center is located. (This parameter is only used whenOPTION=CENTERED).

VECTOR The center of the block is specified by a position vector (CX1,CX2,CX3)with components in terms of a given coordinate system (SYSTEM).

POINT The center of the block is specified by an existing geometry point(CENTERED), possibly a vertex of another body.

ORIENTATION [SYSTEM]Specifies how the edges of the block are aligned:

SYSTEM The block is aligned with the base Cartesian axes of a local coordinatesystem (possibly the global coordinate system).

VECTORS The X,Y,Z directions of the block edges are input in terms of twonon-parallel direction vectors (AX,AY,AZ), (BX,BY,BZ). Thesevectors are used to form a right-handed system as described below.

CX1 [0.0]CX2 [0.0]CX3 [0.0]The position vector of the center of the block, given in terms of curvilinear components ofthe local coordinate system specified by SYSTEM. Note that these parameters are only usedwhen POSITION=VECTOR and OPTION=CENTERED.

CENTERThe center of the block - the label number of an existing geometry point. This parameter isonly used when POSITION=POINT and OPTION=CENTERED, in which case an existinggeometry point must be specified (no default is assumed).

SYSTEM [0]Label number of a local coordinate system which may be used to position the center of theblock and/or provide the orientation of the block. The center of the block may be given interms of the curvilinear coordinates (CX1,CX2,CX3) of this local system, whenPOSITION=VECTOR and OPTION=CENTERED. The local directions of the block are alignedwith the base Cartesian system (XL,YL,ZL) of this system, see command SYSTEM, whenORIENTATION=SYSTEM. This parameter is only used when POSITION=VECTOR (andOPTION=CENTERED), or when ORIENTATION=SYSTEM. Note that the default is chosen asthe global Cartesian coordinate system.

BODY BLOCK



AX [1.0]AY [0.0]AZ [0.0]Global Cartesian components of a direction vector specifying the local x-direction of theblock. If OPTION= CENTERED, then the component DX1 will be associated with thisdirection. Note that this vector need not be of unit length, and is only used ifORIENTATION=VECTOR.

BX [0.0]BY [1.0]BZ [0.0]Global Cartesian components of a direction vector, which specifies, in conjunction withvector (AX,AY,AZ), the local x-y plane of the block orientation. The vector product, or�cross� product, of (AX,AY,AZ) with (BX,BY,BZ) gives the local z-direction, and they-direction is then given by the right hand rule. If OPTION=CENTERED the componentsDX2, DX3 will be associated with the local y-direction and z-directions respectively. Note thatthis vector need not be of unit length, and is only used if ORIENTATION=VECTOR.

DX1DX2DX3The dimensions of the block, aligned with the local x, y and z-directions of the block, respec-tively. These lengths are only used if OPTION=CENTERED, in which case they must be inputwith positive values (no defaults are assumed).

P1P2Label numbers of two existing geometry points which define the opposite corners of a diagonalof the block. These parameters are only used when OPTION= DIAGONAL, and in that case twodistinct and non-coincident points must be specified (no defaults are assumed).

BODY BLOCK


Sec. 6.10 ADINA - M

BODY CHAMFER NAME R1 R2 OPTION

edgei facei (OPTION=EDGE)

or

facei (OPTION=FACE)

The command BODY CHAMFER applies chamfers to edges or faces of a solid geometrybody.This command is only active when ADINA-M has been licensed.

BODY CHAMFER

NAMELabel number of the body to be chamfered. (No default - an existing body name must begiven.)

R1The first range (depth) of the chamfer. R1 must be input with a positive value (no default isassumed).

R2 [R1]The second range (depth) of the chamfer. If R2 is input, it cannot be negative. If R2 = 0.0,then it is assumed that R2 = R1.

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OPTION [EDGE]This parameter offers basic options for chamfering the edges or faces:

EDGE Multiple edges are chamfered.

FACE Multiple faces are chamfered.

edgeiLabel numbers of edges to be chamfered. This parameters is used only when OPTION=EDGE.

faceiLabel numbers of faces to be chamfered with range R1. This data is only used when R2 is notequal to R1. (OPTION=EDGE)

faceiLabel numbers of faces to be chamfered. (OPTION=FACE)

BODY CHAMFER


Sec. 6.10 ADINA - M

BODY CONE NAME OPTION POSITION ORIENTATION X1X2 X3 APEX BASE SYSTEM AXIS AX AY AZSANGLE RADIUS LENGTH

The command BODY CONE defines a solid geometry cone shape. A number of options allowfor the position, orientation, and dimensions of the cone shape. The cone body may be usedin conjunction with other body shapes to form more complex geometries using the Booleanoperation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may bemeshed directly via the GBODY command (in which case free-form meshing is necessarilyused - there is no intrinsic parametric description of the body to support mapped meshing).This command is only active when ADINA-M has been licensed.

BODY CONE


OPTION [APEX]This parameter offers basic options for defining the cone:

APEX The cone is defined by its apex, semi-angle, orientation, and length.

BASE The cone is defined by its base center, orientation, radius and length.

ENDPOINTS The cone is defined by two end points (APEX, BASE) and its baseradius.

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Chap. 6 Geometry definition BODY CONE

POSITION [VECTOR]Specifies how the apex or base of the cone is located. (This parameter is only used whenOPTION=APEX or BASE.)

VECTOR The apex or base of the cone is specified by a position vector (X1,X2,X3)- with components in terms of a given coordinate system (SYSTEM).

POINT The apex or base of the cone is specified by an existing geometry point(APEX or BASE), possibly a vertex of another body.

ORIENTATION [SYSTEM]Specifies how the direction of the cone axis is defined. (This parameter is only used whenOPTION=APEX or BASE.)

SYSTEM The cone axis is aligned with one of the base Cartesian axes (AXIS) ofa local coordinate system (SYSTEM) (possibly the global coordinatesystem).

VECTOR The cone axis is defined via a direction vector (AX,AY,AZ) in theglobal coordinate system.

X1 [0.0]X2 [0.0]X3 [0.0]The position vector of the apex or base of the cone, given in terms of curvilinear componentsof the local coordinate system specified by SYSTEM. Note that these parameters are onlyused when POSITION=VECTOR, and OPTION=APEX or BASE.

APEXThe label number of an existing geometry point indicating the apex of the cone. This param-eter is only used when POSITION=POINT and OPTION=APEX, or whenOPTION=ENDPOINTS; in either case an existing geometry point must be specified (nodefault is assumed).

BASEThe label number of an existing geometry point indicating the base center of the cone. Thisparameter is only used when POSITION=POINT and OPTION=BASE, or whenOPTION=ENDPOINTS; in either case an existing geometry point must be specified (nodefault is assumed).

SYSTEM [0]Label number of a local coordinate system which may be used to position the apex or base ofthe cone and/or define the cone axis direction. The apex or base of the cone may be given in


Sec. 6.10 ADINA - MBODY CONE

terms of the curvilinear coordinates (X1,X2,X3) of this local system, whenPOSITION=VECTOR. For ORIENTATION=SYSTEM the cone axis direction is aligned withone of the base Cartesian system axes of this system (AXIS), see command SYSTEM . Thisparameter is only used when OPTION=APEX or BASE, and when POSITION=VECTOR or ORIENTATION=SYSTEM. Note that the default is chosen as the global Carte-sian coordinate system.

AXIS [XL]Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to beused for the direction of the cone axis. Note that both positive and negative coordinatesystem axial directions may be requested. This parameter is used only whenORIENTATION=SYSTEM and OPTION=APEX or BASE. {XL/YL/ZL/XL-/YL-/ZL-}



BODY CYLINDER NAME OPTION POSITION ORIENTATIONCX1 CX2 CX3 CENTER SYSTEM AXISAX AY AZ RADIUS LENGTH P1 P2 SHEET

The command BODY CYLINDER defines a solid geometry cylinder shape. A number ofoptions allow for the position, orientation, and dimensions of the cylinder shape. Thecylinder body may be used in conjunction with other body shapes to form more complexgeometries using the Boolean operation commands BODY MERGE, BODY SUBTRACT,BODY INTERSECT. A body may be meshed directly via the GBODY command (in which casefree-form meshing is necessarily used - there is no intrinsic parametric description of thebody to support mapped meshing).This command is only active when ADINA-M has been licensed.

BODY CYLINDER

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OPTION [CENTERED]This parameter offers basic options for defining the cylinder:

CENTERED The cylinder is defined by its center, orientation and dimensions.

ENDPOINTS The cylinder is defined by two end points and its radius.

POSITION [VECTOR]Specifies how the center of the cylinder is located. This parameter is only used whenOPTION=CENTERED.


Sec. 6.10 ADINA - M

VECTOR The center of the cylinder is specified by a position vector(CX1,CX2,CX3) - with components in terms of a givencoordinate system (SYSTEM).

POINT The center of the cylinder is specified by an existing geometrypoint (CENTER), possibly a vertex of another body.

ORIENTATION [SYSTEM]Specifies how the direction of the cylinder axis is defined. This parameter is only used whenOPTION=CENTERED.

SYSTEM The cylinder axis is aligned with one of the base Cartesian axes(AXIS) of a local coordinate system (SYSTEM) (possibly theglobal coordinate system).

VECTOR The cylinder axis is defined via a direction vector (AX,AY,AZ) inthe global coordinate system.

CX1 [0.0]CX2 [0.0]CX3 [0.0]The position vector of the center of the cylinder, given in terms of curvilinear components ofthe local coordinate system specified by SYSTEM. Note that these parameters are only usedwhen POSITION=VECTOR and OPTION=CENTERED.

CENTERThe label number of an existing geometry point indicating the center of the cylinder . Thisparameter is only used when POSITION=POINT and OPTION=CENTERED, and in that casean existing geometry point must be specified (no default is assumed).

SYSTEM [0]The number of a local coordinate system which may be used to position the center of thecylinder and/or define the cylinder axis direction. The center of the cylinder may be given interms of the curvilinear coordinates (CX1,CX2,CX3) of this local system, whenPOSITION=VECTOR. For ORIENTATION= SYSTEM the cylinder axis direction is alignedwith one of the base Cartesian system axes of this system (AXIS), see command SYSTEM.This parameter is only used when OPTION=CENTERED and POSITION=VECTOR or ORIEN-TATION= SYSTEM. Note that the default is chosen as the global Cartesian coordinatesystem.

AXIS [XL]Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to beused for the direction of the cylinder axis. This parameter is used only whenORIENTATION=SYSTEM and OPTION=CENTERED. {XL/YL/ZL}

BODY CYLINDER



AX [1.0]AY [0.0]AZ [0.0]Global Cartesian components of a direction vector specifying the cylinder axis direction. Thisvector is only used when ORIENTATION=VECTOR and OPTION=CENTERED.

RADIUSThe radius of the cylinder, which must be input with a positive value (no default is assumed).

LENGTHThe axial length of the cylinder. This parameter is used only when OPTION=CENTERED, inwhich case it must be input with a positive value (no default is assumed).

P1P2Label numbers of two existing geometry points which implicitly define the location, orienta-tion, and length of the cylinder - the only other required data to complete the cylinderdefinition is the radius (RADIUS). These parameters are only used whenOPTION=ENDPOINTS, in which case they must be distinct and non-coincident (also, nodefaults are assumed).

SHEET [NO]Create cylindrical sheet body instead of solid body. {NO, YES}

BODY CYLINDER


Sec. 6.10 ADINA - M

BODY HOLLOW NAME THICKNESS

facei thicknessi

The command BODY HOLLOW hollows a solid geometry body with thickness THICKNESS.This command is only active when ADINA-M has been licensed.

NAMELabel number of the body to be hollowed. An existing body name must be given.

THICKNESSThe thickness of all the faces except the faces listed in the table input.

faceiLabel numbers of faces.

thicknessiThickness for the given face label number.

Note: if thicknessi = 0.0, then facei is removed.

BODY HOLLOW



BODY INTERSECT NAME KEEP-TOOL

bodyi

The command BODY INTERSECT takes an existing solid body (the �target�) and modifies itby taking the intersection of it with a set of other (overlapping) solid bodies (tools). Thisdefinition corresponds to a Boolean �intersection� of several bodies.This command is only active when ADINA-M has been licensed.

NAMELabel number of the (target) body to be modified. (No default - an existing body name mustbe given.)

KEEP-TOOL [NO]Indicates whether or not the tools are to be kept after applying the command BODY INTER-SECT. {NO/YES}

bodyiLabel numbers of other bodies which are to be intersected with the target body. Note thatbodyi cannot be the same as that specified for parameter NAME, and repeated body namesare only counted once. Also, each body must overlap some part of each of the other bodies,including the target body - i.e. a solid body must result from the intersection operations - an�empty� body cannot be defined.

BODY INTERSECT


Sec. 6.10 ADINA - M

BODY LOFTED NAME ENTITY DELETE-ENTITIES

entityi bodyi pointi reversei

Creates a sheet body by lofting through a set of lines or edges, a solid body by loftingthrough a set of surfaces, faces, and sheet bodies.

NAME [(highest body label number)+1]Label number of the body to be defined.

ENTITYThe set of entities used in the lofting process. {LINE/EDGE/SURFACE/FACE/SHEET}

LINE To define a sheet body by lofting a set of lines.

EDGE To define a sheet body by lofting a set of edges.

SURFACE To define a solid body by lofting two surfaces.

FACE To define a solid body by lofting two faces.

SHEET To define a solid body by lofting two sheet bodies.

DELETE-ENTITIES [YES]Indicates whether the entities are to be deleted after applying the command.{YES/NO}

Entities are lines, surfaces or sheets if ENTITY=LINE, SURFACE or SHEET respectively.This parameter is only used when ENTITY=LINE, SURFACE, or SHEET.

entityiLabel of entities used to create the lofted body. Entity type depends on the ENTITY param-eter.

bodyiLabel of parent body of edge or face entity when ENTITY = EDGE or FACE. bodyi

i is not

used if ENTITY = LINE, SURFACE or SHEET.

pointiPoint label numbers of the start points on each entity.

reversei [NO]Indicates whether or not the orientation of the entities needs to be reversed. {NO/YES}

Please note that the normals of the surfaces/faces/sheets must be oriented in the samedirection as the loft direction. Parameter reversal can be used to reverse the direction ifnecessary.

BODY LOFTED



BODY MERGE NAME KEEP-TOOL

bodyi

The command BODY MERGE takes an existing solid body (the �target�) and modifies it byjoining it together with a set of other solid bodies (tools). This definition corresponds to aBoolean �union� of several bodies.This command is only active when ADINA-M has been licensed.


KEEP-TOOL [NO]Indicates whether or not the tools are to be kept after applying the command BODY MERGE.{NO/YES}

bodyiLabel numbers of other bodies which are to be merged with the target body. Note that bodyicannot be the same as that specified for parameter NAME, and repeated body names are onlycounted once.

BODY MERGE


Sec. 6.10 ADINA - MBODY MID-SURFACE

BODY MID-SURFACE NAME BODY SEW THICKNESS DELETE-BODYREDUNDANT SEWGAP

The command BODY MID-SURFACE creates sheet bodies from a thin-walled solid body.Each thin wall must have two faces and at least one of the following conditions must be met: 1. Both faces are planar. 2. The two faces are offsets of each other.

NAME [(current highest body label number)+1]Body label number to be created.

BODYBody label number of the thin-walled body that will be used to create sheet bodies.

SEW [NO]Indicates whether sheet bodies are to be sewn together.{NO/YES}

THICKNESS A sheet body will be created if the thickness of the thin wall is less than THICKNESS.

DELETE-BODY [NO] Indicates whether the thin-walled body is to be deleted when sheet bodies are created. {NO/YES}

REDUNDANT [KEEP]Indicates whether the redundant topology is to be removed.{KEEP/REMOVE}

SEWGAP [0.01]Factor used to determine the sewing gap value. The gap value used to sew the sheet bodiesis SEWGAP*(the largest of the maximum coordinate differences in each global coordinatedirection considering all the sheet bodies that are being sewn together). This parameter isused only when SEW=YES.


Chap. 6 Geometry definition BODY OPTION

BODY OPTION CHECK

This command provides the options for ADINA-M bodies.

CHECK [YES]Geometry checking for bodies in ADINA-M commands. {YES/NO}


Sec. 6.10 ADINA - M

BODY PARTITION NAME EXTEND

facei

The command BODY PARTITION takes an existing solid body and partition it with a set offaces of the body, resulting in two or more bodies.This command is only active when ADINA-M has been licensed.

BODY PARTITION

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NAMELabel number of the body to be partitioned. (No default - an existing body name must begiven.)

EXTEND [NO]Indicates whether or not the faces are extended. {NO/YES}

faceiLabel numbers of faces used to partition the body. Note that repeated face names will only becounted once. Also, when EXTEND=YES and more than one face is used to partition thebody, these extended faces should not intersect.



BODY PIPE NAME OPTION POSITION ORIENTATIONCX1 CX2 CX3 CENTER SYSTEM AXIS AX AY AZRADIUS LENGTH P1 P2 THICKNESS

The command BODY PIPE defines a solid geometry pipe shape. A number of options allowfor the position, orientation, and dimensions of the pipe shape. The pipe body may be usedin conjunction with other body shapes to form more complex geometries using the Booleanoperation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body can bemeshed directly via the GBODY command (in which case free-form meshing is necessarilyused - there is no intrinsic parametric description of the body to support mapped meshing).This command is only active when ADINA-M has been licensed.

NAME [(highest body label number)+1]

BODY PIPE

Label number of the body to be defined.

OPTION [CENTERED]This parameter offers basic options for defining the pipe:

CENTERED The pipe is defined by its center, orientation and dimensions.

ENDPOINTS The pipe is defined by two end points and dimensions.

POSITION [VECTOR]Specifies how the center of the pipe is located. This parameter is only used whenOPTION=CENTERED.

VECTOR The center of the pipe is specified by a position vector(CX1,CX2,CX3) - with components in terms of a givencoordinate system (SYSTEM).

POINT The center of the pipe is specified by an existing geometry point

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Sec. 6.10 ADINA - M

(CENTER), possibly a vertex of another body.

ORIENTATION [SYSTEM]Specifies how the direction of the pipe axis is defined. This parameter is only used whenOPTION=CENTERED.

SYSTEM The pipe axis is aligned with one of the base Cartesian axes(AXIS) of a local coordinate system (SYSTEM), possibly theglobal coordinate system.

VECTORS The pipe axis is defined via a direction vector (AX,AY,AZ) in theglobal coordinate system.

CX1 [0.0]CX2 [0.0]CX3 [0.0]The position vector of the center of the pipe, given in terms of curvilinear components of thelocal coordinate system specified by SYSTEM. Note that these parameters are only usedwhen POSITION=VECTOR and OPTION=CENTERED.

CENTERThe label number of an existing geometry point indicating the center of the pipe . Thisparameter is only used when POSITION=POINT and OPTION=CENTERED, and in that casean existing geometry point must be specified (no default is assumed).

SYSTEM [0]Label number of a local coordinate system which may be used to position the center of thepipe and/or define the pipe axis direction. The center of the pipe can be given in terms of thecurvilinear coordinates (CX1,CX2,CX3) of this local system, when POSITION=VECTOR. ForORIENTATION= SYSTEM the pipe axis direction is aligned with one of the base Cartesiansystem axes of this system (AXIS), see command SYSTEM. This parameter is only usedwhen OPTION=CENTERED and POSITION=VECTOR or ORIENTATION=SYSTEM. Notethat the default is chosen as the global Cartesian coordinate system.

AXIS [XL]Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to beused for the direction of the pipe axis. This parameter is used only whenORIENTATION=SYSTEM and OPTION=CENTERED. {XL/YL/ZL}

AX [1.0]AY [0.0]AZ [0.0]Global Cartesian components of a direction vector specifying the pipe axis direction. Thisvector is only used when ORIENTATION=VECTOR and OPTION=CENTERED.

BODY PIPE



RADIUSThe outer radius of the pipe, which must be input with a positive value (no default is as-sumed).

LENGTHThe axial length of the pipe. This parameter is used only when OPTION=CENTERED, inwhich case it must be input with a positive value (no default is assumed).

P1P2Label numbers of two existing geometry points which implicitly define the location, orienta-tion, and length of the pipe - the only other required data to complete the pipe definition isthe radius and thickness (RADIUS, THICKNESS). P1 and P2 are only used whenOPTION=ENDPOINTS, in which case they must be distinct and non-coincident (also, nodefaults are assumed).

THICKNESSThe thickness of the pipe, which must be input with a positive value less than RADIUS (nodefault is assumed).

BODY PIPE


Sec. 6.10 ADINA - M

BODY PRISM NAME OPTION POSITION ORIENTATION CX1 CX2 CX3CENTER SYSTEM AXIS POLE AX AY AZ BX BY BZRADIUS LENGTH P1 P2 P3 NSIDES SHEET

The command BODY PRISM defines a prismatic solid geometry shape, which is a cylinderwith a regular polygonal cross-section. A number of options allow for the position, orienta-tion, and dimensions of the prism shape. The prism body may be used in conjunction withother body shapes to form more complex geometries using the Boolean operation commandsBODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may be meshed directly viathe GBODY command (in which case free-form meshing is necessarily used - there is nointrinsic parametric description of the body to support mapped meshing).This command is only active when ADINA-M has been licensed.

BODY PRISM


OPTION [CENTERED]This parameter offers basic options for defining the prism:

CENTERED The prism is defined by its center, orientation, dimensions andnumber of sides.

POINTS The prism is defined by two end points, a point giving the poledirection, its radius and number of sides.

POSITION [VECTOR]Specifies how the center of the prism is located. This parameter is only used whenOPTION=CENTERED.

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VECTOR The center of the prism is specified by a position vector(CX1,CX2,CX3) - with components in terms of a givencoordinate system (SYSTEM).

POINT The center of the prism is specified by an existing geometry point(CENTER), possibly a vertex of another body.

ORIENTATION [SYSTEM]Specifies how both the axial and pole directions of the prism are defined (the pole directionpasses through a vertex of the polygonal cross-section). (This parameter is only used whenOPTION=CENTERED.

SYSTEM The prism axis is aligned with one of the base Cartesian axes(AXIS), and the pole with another axis (POLE), of a local coordinatesystem (SYSTEM), possibly the global coordinate system.

VECTORS The prism axis and pole directions are defined via direction vectors(AX,AY,AZ), (BX, BY, BZ) in the global coordinate system.

CX1 [0.0]CX2 [0.0]CX3 [0.0]The position vector of the center of the prism, given in terms of curvilinear components ofthe local coordinate system specified by SYSTEM. Note that these parameters are only usedwhen POSITION=VECTOR and OPTION=CENTERED.

CENTERThe label number of an existing geometry point indicating the center of the prism . Thisparameter is only used when POSITION=POINT and OPTION=CENTERED, and in that casean existing geometry point must be specified (no default is assumed).

SYSTEM [0]Label number of a local coordinate system which may be used to position the center of theprism and/or define both the axis and pole directions of the prism. The center of the prismcan be given in terms of the curvilinear coordinates (CX1,CX2,CX3) of this local system,when POSITION=VECTOR. For ORIENTATION=SYSTEM the prism axis and pole directionsare aligned with two of the base Cartesian system axes of this system (AXIS, POLE), seecommand SYSTEM. This parameter is only used when OPTION=CENTERED andPOSITION=VECTOR or ORIENTATION=SYSTEM. Note that the default is chosen as theglobal Cartesian coordinate system.

AXIS [XL]Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to beused for the direction of the prism axis. This parameter is used only when

BODY PRISM


Sec. 6.10 ADINA - M

ORIENTATION=SYSTEM and OPTION=CENTERED. {XL/YL/ZL}

POLE [YL]Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to beused for the pole direction of the prism. This parameter is used only whenORIENTATION=SYSTEM and OPTION=CENTERED. {XL/YL/ZL}

AX [1.0]AY [0.0]AZ [0.0]Global Cartesian components of a direction vector specifying the prism axis direction. Notethat this vector need not be of unit length, and is only used when ORIENTATION=VECTORand OPTION=CENTERED.

BX [0.0]BY [1.0]BZ [0.0]Global Cartesian components of a direction vector, which specifies, in conjunction withvector (AX,AY,AZ), the local axis-pole plane of the block orientation. The vector product, or�cross� product, of (AX,AY,AZ) with (BX,BY,BZ) gives the local z-direction, and the poledirection is then given by the right hand rule. Note that this vector need not be of unitlength, and is only used when ORIENTATION=VECTOR and OPTION=CENTERED.

RADIUSThe radius of the prism, i.e. the distance of the points of the polygonal cross-section from theprism axis. This value must be input with a positive value (no default is assumed).

LENGTHThe axial length of the prism. This parameter is used only when OPTION=CENTERED, inwhich case it must be input with a positive value (no default is assumed).

P1, P2, P3Label numbers of three non-collinear existing geometry points which implicitly define thelocation, orientation, and length of the prism - the only other required data to complete theprism definition is the radius (RADIUS). The points P1, P2 are taken to lie at the end pointson the axis of the prism, whilst point P3 determines the pole direction of the prism. Theseparameters are only used when OPTION=POINTS, in which case they must be distinct,non-coincident and non-collinear (also, no defaults are assumed).

NSIDES [3]The number of sides of the polygonal cross-section of the prism. NSIDES must be at least 3.

SHEET [NO]Create cylindrical sheet body instead of solid body. {NO, YES}

BODY PRISM



BODY PROJECT NAME FACE DIRECTION VECTOR P1 P2 DX DYDZ DELETE-LINE

linei

Projects lines onto a face of the body.

NAMELabel number of the body to be projected onto. An existing body name must be given.

FACELabel number of the face to be projected onto.

DIRECTION [NORMAL]Specifies the direction of projection. {NORMAL/VECTOR}

NORMAL Lines project to the face in the direction of the face normal. VECTOR Lines project to the face along the given vector direction.

VECTOR [VALUES]Specifies how the vector is defined. (This parameter is only used when OPTION=VECTOR.){COMPONENTS/POINTS}

COMPONENTS The vector is defined by DX, DY, and DZ. POINTS The vector is defined by two points (P1 and P2).

P1P2Label numbers of geometry points to define the projection vector. (These two parameters areonly used when VECTOR=POINTS.)

DXDYDZComponents of vector to define the projection vector. (These three parameters are only usedwhen VECTOR=COMPONENTS.)

DELETE-LINE [YES]Indicates whether or not the lines are to be deleted after projection is done. {YES/NO}

lineiLabel numbers of geometry lines used to project to the face.

BODY PROJECT


Sec. 6.10 ADINA - MBODY REVOLVED

BODY REVOLVED NAME MODE BODY FACE ANGLE SYSTEM AXISALINE AP1 AP2 X0 Y0 Z0 XA YA ZA MESHNODES SUBSTRUCTURE 2D-EGROUP 3D-EGROUP NDIVNCOINCIDE NCTOLERANCE DELETE-FACE-ELEMENT

Creates a revolved body on an existing body by rotating a face of the body about an axis.


MODE [AXIS]Selects the method of defining the axis of revolution used to create the body. This controlswhich parameters actually define the revolved body � other parameters are ignored.

AXIS The axis of revolution is taken as a given coordinate axis of a coordinatesystem (FACE, ANGLE, SYSTEM, AXIS).

LINE The axis of revolution is taken as the straight line between the end pointsof a given geometry line (which is not necessarily straight, but must beopen , i.e., have non-coincident end points) (FACE, ANGLE, ALINE).

POINTS The axis of revolution is taken as the straight line between two given (non-coincident) geometry points (FACE,ANGLE,AP1,AP2).

VECTORS The axis of revolution is defined by an position vector and a directionvector (FACE, ANGLE, X0, Y0, Z0, XA, YA, ZA).

BODYLabel number of the body to be revolved.

FACELabel number of the face to be revolved.

Body 1 before revolution Body 1 after revolutionFace 1 is revolved

Face 1



ANGLEAngle of rotation (in degrees). The sign of the angle is given by the right hand rule � i.e., ifyou curl your fingers around the axis of revolution, with the thumb pointing along the axis,then a positive angle is in the direction of the curl of the fingers. {-360 ≤ ANGLE ≤ 360}

SYSTEM [current active coordinate system]Label number of a coordinate system. One of the axes of this cartesian coordinate systemmay be used to define the axis of revolution, via parameter AXIS, when MODE=AXIS.

AXIS [XL]Selects which of the basic axes (XL,YL,ZL) of the local cartesian coordinate system, given byparameter SYSTEM, is used as the axis of revolution {XL/YL/ZL}.

ALINELabel number of a geometry line which defines the axis of revolution. The direction of the axisis taken from the start point of the line to the end point of the line.

AP1, AP2Label numbers of geometry points which define the axis of revolution. The direction of theaxis is taken from point AP1 topoint AP2.

X0, Y0, Z0 [0.0]Global coordinates of the position vector defining the axis of rotation whenMODE=VECTORS.

XA [1.0]YA, ZA [0.0]Components (with respect to the global coordinate system) of the axis of rotation whenMODE=VECTORS.

MESH [NO]Indicates whether or not the mesh is generated while a swept body is created. If MESH =YES, 3-D elements can be created if 2-D elements exist on the face.

NODES [0]The number of nodes per element of the mesh. {0/8/20/27}For the default 0, the program assigns the number of nodes per element in the resulting 3-Dmesh based on the corresponding number of nodes of the 2-D mesh on the face, as follows:

2-D 3-D 4 8 8 20 9 27

SUBSTRUCTURE [current substructure label number]The label number of the substructure (ADINA) in which the elements and nodes are created.

BODY REVOLVED


Sec. 6.10 ADINA - MBODY REVOLVED

2D-EGROUP [largest element group of the revolved face]The element group label of the elements on the revolved face.

3D-EGROUP [current group label number]The element group label of the elements on the revolved body.

NDIV [1]Number of elements created along the sweeping direction.

NCOINCIDE [BOUNDARIES]Selects the method of nodal coincidence checking.

ALL The global coordinates of all generated nodes are compared against thoseof existing nodes of the substructure (ADINA) or model (ADINA-T/-F). Ifthere is coincidence to within NCTOLERANCE * (max. difference in globalcoordinates between all previous nodes of the substructure or model), thenno new node is created at that location, i.e., the previous node label numberis assumed.

BOUNDARIES Coincidence checking is carried out for the nodes generated at vertices,edges, and faces of the geometry bodies.

NO No nodal coincidence checking is carried out.

NCTOLERANCE [TOLERANCES GEOMETRIC]Tolerance used to determine nodal coincidence.

DELETE-FACE-ELEMENT [ALL]Indicates whether elements on the 2-D mesh are deleted.

ALL Delete elements on 2-D mesh and also the element group if it does notcontain any elements.

ELEMENT Delete elements on 2-D mesh but do not delete the element group.

NO Do not delete any elements.



BODY SECTION NAME KEEP-SHEET KEEP-IMPRINT OPTION

namei bodyi

The command BODY SECTION partitions an existing solid body using a set of sheets(defined using SHEET PLANE) or faces of other bodies, resulting in two or more bodies. Thiscommand is only active when ADINA-M has been licensed.

NAMELabel number of the body to be partitioned. An existing body name must be given.

KEEP-SHEET [NO]Indicates whether sheets are to be kept after partitioning. This parameter is used only whenOPTION = SHEET. {NO/YES}

KEEP-IMPRINT [NO]Indicates whether imprinted edges created by the section operation are to be kept. {NO/YES}

OPTION [SHEET]Specifies whether sheets or faces are used to partition the body. {SHEET/FACE}

SHEET Use sheets to section the body.

FACE Use faces of bodies to section the body.

nameiLabel number of a sheet (OPTION=SHEET) or face (OPTION=FACE).

Note: The following remarks apply to faces also.- orientation of two adjacent sheets should be the same.- each sheet (or set of connected sheets) must divide the body into completely

separate bodies;- each sheet (or set of connected sheets) cannot have its boundary within the body

to be sectioned;- the sheets cannot intersect;- three or more sheets cannot meet at a common edge.

bodyiLabel number of a solid body. Used when OPTION=FACE.

BODY SECTION


Sec. 6.10 ADINA - M

BODY SEW NAME SOLID DELETE-BODY HEAL SEWGAP

bodyi

The command BODY SEW sews a set of sheet bodies into a sewn body.


SOLID [YES]Indicates whether a solid body is to be created. If SOLID=NO, the created sewn body is asheet body.{YES/NO}

DELETE-BODY [YES]Indicates whether the sheet bodies are deleted after the sewn body is created.{YES/NO}

HEAL [NO]If the resulting sewn body does not have a complete boundary, then any holes are treated aswounds which are healed as specified by HEAL. Only used when SOLID=YES.{NO/CAP/EXTEND}

NO Do not heal wounds. Any holes (gaps) will only be closed if they are smallerthan the sewing gap.

CAP Create a face formed by all edges of the hole to cover up (cap) the hole.

EXTEND Faces around the hole are extended until they cover the hole.

SEWGAP [0.01]Factor used to determine the sewing gap value. The gap value used to sew the body isSEWGAP * (the largest of the maximum coordinate differences in each global coordinatedirection considering all the bodies that are being sewn together).

bodyiLabel numbers of sheet bodies which are used to create the sewn body.

BODY SEW



BODY SHEET NAME LINE DELETE-LINE

linei

The command BODY SHEET defines a sheet body by a set of geometry lines.


LINELabel number of geometry line comprising the external loop of the sheet body.

DELETE-LINE [YES]Indicates whether or not the lines are to be deleted after applying the command BODYSHEET. {YES/NO}

lineiLabel numbers of geometry lines comprising the internal loops of the sheet body.

BODY SHEET


Sec. 6.10 ADINA - M

BODY SPHERE NAME POSITION DIMENSION CX1 CX2 CX3SYSTEM CENTER RADIUS POINT

The command BODY SPHERE defines a solid geometry sphere shape. The sphere body maybe used in conjunction with other body shapes to form more complex geometries using theBoolean operation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. Abody may be meshed directly via the GBODY command (in which case free-form meshing isnecessarily used - there is no intrinsic parametric description of the body to support mappedmeshing).This command is only active when ADINA-M has been licensed.

BODY SPHERE


POSITION [VECTOR]Specifies how the sphere center is located:

VECTOR The center of the sphere is specified by a position vector(CX1,CX2,CX3) - with components in terms of a givencoordinate system (SYSTEM).

POINT The center of the sphere is specified by an existing geometrypoint (CENTER), possibly a vertex of another body.

DIMENSION [RADIUS]Specifies the size of the sphere:

RADIUS The radius of the sphere is input via parameter RADIUS.

POINT An existing geometry point lying on the surface of the sphere isused to determine its radius.

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CX1 [0.0]CX2 [0.0]CX3 [0.0]The position vector of the center of the sphere, given in terms of curvilinear components ofthe local coordinate system specified by SYSTEM. Note that these parameters are only usedwhen POSITION=VECTOR.

SYSTEM [0]Label number of a local coordinate system which may be used to position the center of thesphere, in terms of the curvilinear coordinates (CX1,CX2,CX3) of this local system, whenPOSITION=VECTOR. This parameter is only used when POSITION=VECTOR. Note that thedefault is chosen as the global Cartesian coordinate system.

CENTERThe center of the sphere - the label number of an existing geometry point. This parameter isonly used when POSITION=POINT, and in that case an existing geometry point must bespecified (no default is assumed).

RADIUSThe radius of the sphere, used only when DIMENSION=RADIUS, in which case it must beinput with a positive value (no default is assumed).

POINTLabel number of an existing geometry point which implicitly defines the radius of the sphere(the point is assumed to be on the surface of the sphere). This parameter is only used whenDIMENSION=POINT, in which case it must be non-coincident with the sphere center (also,no default is assumed).

BODY SPHERE


Sec. 6.10 ADINA - M

BODY SUBTRACT NAME KEEP-TOOL KEEP-IMPRINT

bodyi

The command BODY SUBTRACT takes an existing solid body (the �target�) and modifies itby removing from it a set of other solid bodies (tools). This definition corresponds to aBoolean subtraction of one or more bodies from a given solid body. E.g. to �drill� a holethrough a body you could subtract a cylindrical body from it.This command is only active when ADINA-M has been licensed.


KEEP-TOOL [NO]Indicates whether or not the tools are to be kept after applying the command BODY SUB-TRACT. {NO/YES}

KEEP-IMPRINT [NO]Indicates whether or not the imprinted edges created by the Boolean operation are to bemerged with the target body. {NO/YES}

bodyiLabel numbers of other bodies which are to be subtracted from the target body. Note thatbodyi cannot be the same as that specified for parameter NAME, and repeated body namesare only counted once.

BODY SUBTRACT



BODY SWEEP NAME BODY FACE OPTION DX DY DZ SYSTEM LINE DELETE-LINE ALIGNMENT MESH NODES SUBSTRUCTURE2D-EGROUP 3D-EGROUP NDIV NCOINCIDE NCTOLERANCEDELETE-FACE-ELEMENT TWIST-ANGLE

BODY SWEEP

Creates a swept body on an existing body by sweeping a face of the body in a given direc-tion or along a line.


BODYLabel number of the body containing face to be swept.

FACELabel number of the face to be swept.OPTION [VECTOR]This parameter offers the options of body sweep.

VECTOR swept body is created by sweeping a geometry face in a given direction.

LINE swept body is created by sweeping a geometry face along a line.

DX [1.0]DY [0.0]DZ [0.0]Components of displacement vector with reference to coordinate system SYSTEM. Note thatthis is the actual displacement vector, i.e. it specifies both magnitude as well as direction.(This parameter is only used when OPTION=VECTOR)

Body before sweep Body after sweepFace 1 is swept along line 1

Line 1

Face 1


Sec. 6.10 ADINA - M

SYSTEM [current active coordinate system]Label number of a coordinate system which is referenced by the displacement vector (DX,DY, DZ). (This parameter is only used when OPTION=VECTOR)

LINEThe geometry line label. (This parameter is only used when OPTION=LINE)

DELETE-LINE [YES]Indicates whether or not the lines are to be deleted after applying the command BODYSWEEP. (This parameter is only used when OPTION=LINE). {YES/NO}

ALIGNMENT [NORMAL]This parameter specifies the direction of the face during sweeping.

NORMAL Face normal is at fixed angle to line tangent.

PARALLEL Face normal always points to the same direction.

MESH [NO]Indicates whether or not the mesh is generated while a swept body is created. If MESH =YES, 3-D elements can be created if 2-D elements exist on the face.

NODES [0]The number of nodes per element of the mesh. {0/8/20/27}For the default 0, the program assigns the number of nodes per element in the resulting 3-Dmesh based on the corresponding number of nodes of the 2-D mesh on the face, as follows:

2-D 3-D 4 8 8 20 9 27

SUBSTRUCTURE [current substructure label number]The label number of the substructure (ADINA) in which the elements and nodes are created.

2D-EGROUP [largest element group of the swept face]The element group label of the elements on the swept face.

3D-EGROUP [current group label number]The element group label of the elements on the swept body.

NDIV [1]Number of elements created along the sweeping direction.

BODY SWEEP




ALL The global coordinates of all generated nodes are compared against thoseof existing nodes of the substructure (ADINA) or model (ADINA-T/-F). Ifthere is coincidence to within NCTOLERANCE * (max. difference in globalcoordinates between all previous nodes of the substructure or model), thenno new node is created at that location, i.e., the previous node label numberis assumed.

BOUNDARIES Coincidence checking is carried out for the nodes generated at vertices,edges, and faces of the geometry bodies.



DELETE-FACE-ELEMENT [ALL]Indicates whether elements on the 2-D mesh are deleted.

ALL Delete elements on 2-D mesh and also the element group if it does notcontain any elements.

ELEMENT Delete elements on 2-D mesh but do not delete the element group.

NO Do not delete any elements.

TWIST-ANGLE [0.0]Indicates the twisted angle when the swept body is twisted along the swept line. Thisparameter is only used when OPTION=LINE.

BODY SWEEP


Sec. 6.10 ADINA - M

BODY TORUS NAME POSITION ORIENTATION CX1 CX2 CX3CENTER SYSTEM AXIS AX AY AZ RMAJOR RMINOR

BODY TORUS defines a solid geometry torus shape. The torus body may be used in con-junction with other body shapes to form more complex geometries using the Boolean opera-tion commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may bemeshed directly via the GBODY command (in which case free-form meshing is necessarilyused - there is no intrinsic parametric description of the body to support mapped meshing).This command is only active when ADINA-M has been licensed.


BODY TORUS

POSITION [VECTOR]Specifies how the center of the torus is located:

VECTOR The center of the torus is specified by a position vector (CX1,CX2, CX3) -with components in terms of a given coordinate system (SYSTEM).

POINT The center of the torus is specified by an existing geometry point(CENTER), possibly a vertex of another body.

ORIENTATION [SYSTEM]Specifies how the direction of the major torus axis is defined:

SYSTEM The torus axis is aligned with one of the base Cartesian axes (AXIS) of alocal coordinate system (SYSTEM), possibly the global coordinate system.

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Chap. 6 Geometry definition BODY TORUS

VECTOR The torus axis is defined via a direction vector (AX,AY,AZ) in the globalcoordinate system.

CX1 [0.0]CX2 [0.0]CX3 [0.0]The position vector of the center of the torus, given in terms of curvilinear components of thelocal coordinate system specified by SYSTEM. Note that these parameters are only usedwhen POSITION=VECTOR.

CENTERThe label number of an existing geometry point indicating the center of the torus. Thisparameter is only used when POSITION=POINT, and in that case an existing geometry pointmust be specified (no default is assumed).

SYSTEM [0]Label number of a local coordinate system which may be used to position the center of thetorus and/or define the major torus axis direction. The center of the torus may be given interms of the curvilinear coordinates (CX1,CX2,CX3) of this local system, whenPOSITION=VECTOR. For ORIENTATION= SYSTEM the torus axis direction is aligned withone of the base Cartesian system axes of this system (AXIS), see command SYSTEM. Thisparameter is only used when POSITION=VECTOR or ORIENTATION=SYSTEM. Note that thedefault is chosen as the global Cartesian coordinate system.

AXIS [XL]Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to beused for the direction of the major torus axis. This parameter is used only whenORIENTATION=SYSTEM. {XL/YL/ZL}

AX [1.0]AY [0.0]AZ [0.0]Global Cartesian components of a direction vector specifying the major torus axis direction.This vector is only used when ORIENTATION=VECTOR.

RMAJORThe major radius of the torus, which must be input with a positive value (no default isassumed).

RMINORThe minor radius of the torus, which must be input with a positive value (no default isassumed).


Sec. 6.10 ADINA - MBODY TORUS




BODY TRANSFORMED NAME OPTION PARENT TRANSFORMATIONNCOPY

bodyi

The command BODY TRANSFORMED defines a solid geometry by copying or moving anexisting Parasolid body. The transformed body may be used in conjunction with other bodyshapes to form more complex geometries using the Boolean operation commandsBODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may be meshed directly viathe GBODY command (in which case free-form meshing is necessarily used - there is nointrinsic parametric description of the body to support mapped meshing). The transformedbody is identified by its label number NAME. If NCOPY is greater than 1, the other newlydefined transformed bodies are identified by the current highest body label number + 1.This command is only active when ADINA-M has been licensed.


OPTION [COPY]This parameter offers two options for defining the body:

COPY The body is defined by coping an existing body.

MOVE The body is defined by moving an existing body.

PARENTThe label of the body to be copied (used only when OPTION=COPY). This parameter mustbe entered when copying a body.

TRANSFORMATIONLabel number of a geometrical transformation defined by one of the TRANSFORMATIONcommands. This parameter must be entered.

NCOPY [1]Parameter defines number of bodies to be generated by the transformation - transformation isrepeated NCOPY times.

bodyiLabel numbers of body to be transformed.

BODY TRANSFORMED


Sec. 6.10 ADINA - M

SHEET PLANE NAME OPTION POSITION OFFSET X Y ZPOINT NX NY NZ P1 P2 P3 SYSTEM

positioni pointi

The command SHEET PLANE defines a planar sheet. A number of options allow for theposition, orientation and dimensions of the planar sheet. The planar sheet may be used topartition a body into one or more bodies using the command BODY SECTION.This command is only active when ADINA-M has been licensed.

NAME [(current highest sheet label number)+1]The sheet label number.

OPTION [POLYGON]Selects the method for the planar sheet definition:

POLYGON Sheet defined by a set of co-planar points.

XPLANE Sheet defined by normal vector in X direction.

YPLANE Sheet defined by normal vector in Y direction.

ZPLANE Sheet defined by normal vector in Z direction.

POINT-NORMAL Sheet defined by a point and a normal vector.

THREE-POINT Sheet defined by three points.

POSITION [VECTOR]Selects the method to define origin point (only for OPTION=POINT-NORMAL):

VECTOR Origin is defined by a position vector (X,Y,Z).

POINT Origin is defined by an existing geometry point (POINT).

OFFSETDefines position of the planar sheet along the normal vector. This parameter is only usedwhen OPTION= XPLANE, YPLANE, or ZPLANE.

X [0.0]Y [0.0]Z [0.0]Defines origin of the vector normal to the sheet plane. These parameters are only used when

SHEET PLANE



POSITION=VECTOR and OPTION=POINT-NORMAL.

POINTDefines geometry point - origin of the planar sheet. This parameter is only used whenPOSITION=POINT and OPTION=POINT-NORMAL.

NX [1.0]NY [0.0]NZ [0.0]Defines vector normal to the planar sheet. These parameters are only used whenOPTION=POINT-NORMAL.

P1P2P3Label numbers of three existing geometry points which define planar sheet. This parametersare only used when OPTION=THREE-POINT (no defaults are assumed).

SYSTEM [0]Label number of a local coordinate system. This parameter is used only whenOPTION=XPLANE, YPLANE, ZPLANE, or POINT-NORMAL. Only the Cartesian coordi-nate system is allowed.

positioniPosition numbers of geometry points.

pointiLabel numbers of geometry points.

Note: positioni and pointi are only used when OPTION=POLYGON.

SHEET PLANE


Sec. 6.10 ADINA - M

VOLUME BODY NAME BODY DELETE-BODY DEG-EDGE NPTS LINE-TYPE

Converts a body into a geometry volume. Only body of the following geometries can beconverted into volume: tetrahedron, hexahedron, prism and pyramid. If more than one bodywill be converted into volumes and the bodies are from command LOADSOLID, in order notto create duplicated surfaces between connected volumes, make sure PCOINCIDE=YES incommand LOADSOLID.

This command is only active when ADINA-M has been licensed.


BODYLabel number of solid geometry body to be converted into a geometry volume.If BODY=ALL, all the bodies will be converted into volumes.

DELETE-BODY [YES]Indicates whether or not the body are to be deleted after applying the command VOLUMEBODY. {YES/NO}

DEG-EDGE [0]That parameter is used to degenerate edge of the body and body is a prism shape. Parametercan not be used when BODY= ALL.

NPTS [3]The number of intermediate points of non-straight and non-arc edges.

LINE-TYPE [BIARC-SEGMENT]This parameter specifies the line type when volume is created. {BIARC-SEGMENT /SPLINE}

BIARC-SEGMENT If line type is neither straight nor arc, polyline bi-arc is used whenall the control points are co-planar and polyline segmented is usedwhen the control points are not co-planar.

SPLINE If line type is neither straight nor arc, polyline spline is used.

Auxiliary commands

LIST VOLUME FIRST LASTDELETE VOLUME FIRST LASTNote that no geometry volume is deleted which has nodes and/or elements associatedwith it.

VOLUME BODY


Chap. 6 Geometry definition SURFACE FACE

SURFACE FACE NAME BODY FACE DELETE-BODY DEG-POINT NPTSREVERSE LINE-TYPE

Converts a face of a body into a geometry surface.

NAME [(current highest geometry surface label number) + 1]Label number of the geometry surface to be created.

BODYLabel number of the body that contains the face to be converted. If BODY=ALL, faces of allsheet bodies will be converted into surfaces.

FACELabel number of the face to be converted to a surface. If BODY=ALL or the specified body isa sheet body, then FACE=1 by default. Otherwise, a face label number has to be input.

DELETE-BODY [YES]Indicates whether the body will be deleted after executing this command. {YES/NO}

DEG-POINT [0]If the face is a triangle, this parameter indicates which point will be the degenerate vertex ofthe created triangular surface. Otherwise, this parameter is ignored. If BODY=ALL is speci-fied, this parameter is also ignored and the degenerate vertex is set by the program.

NPTS [3]The number of intermediate points used for interpolating edges that are not straight or notarcs.

REVERSE [NO]Reverses the orientation of the surface. {YES/NO}

LINE-TYPE [BIARC-SEGMENT]This parameter specifies the line type when surface is created. {BIARC-SEGMENT /SPLINE}

BIARC-SEGMENT If line type is neither straight nor arc, polyline bi-arc is used whenall the control points are co-planar and polyline segmented is usedwhen the control points are not co-planar.

SPLINE If line type is neither straight nor arc, polyline spline is used.



Auxiliary commands


When deleting surfaces, OPTION=ALL will delete any vertex points or edge lineswhich have no other dependent geometry; otherwise (OPTION=SURFACE), only thesurface itself will be deleted.

SURFACE FACE




Chapter 7

Model definition


Chap. 7 Model definition

MATERIAL ANAND NAME E NU DENSITY A1 QDR XSI M SHATN H0 A2 S0 ALPHA

Defines an Anand material model. This material model may be used with 2-D (plane strain andaxisymmetric) and 3-D solid elements.

NAME [ (current highest material label number) + 1]Label number of the material to be defined.

EYoung�s modulus. {>0.0}

NU [0.0]Poisson�s ratio. {-1.0 < NU < 0.5}

DENSITY [0.0]

Mass density. {≥0.0}

A1Pre-exponential factor. {>0.0}

QDRActivation energy normalized by the universal gas constant. {≥0.0}

XSIStress multiplier. {>0.0}

MStrain rate sensitivity of stress. {>0.0}

SHATCoefficient for the saturation value of the deformation resistance. {>0.0, onlychecked if H0>0}

NStrain rate sensitivity of the deformation resistance. {≥0.0}

H0Hardening / softening constant. {≥0.0}

A2Strain rate sensitivity of hardening or softening. {>0.0}

MATERIAL ANAND



S0Initial value of deformation resistance. {>0.0}

ALPHA [0.0]Mean coefficient of thermal expansion. ALPHA is only considered if thermal loading ismodeled.

MATERIAL ANAND


Sec. 7.1 Material models

MATERIAL ARRUDA-BOYCE NAME MU LAMDA KAPPA DENSITYFITTING-CURVE VISCOELASTIC-CONSTANTSTEMPERATURE-DEPENDENCE TREFRUBBER-TABLE RUBBER-VISCOELASTICRUBBER-MULLINS RUBBER-ORTHOTROPIC

Defines an Arruda-Boyce material model, which is a hyperelastic material model for rubbermaterials. This material model may be used with 2-D solid and 3-D solid elements.

NAME [(current highest material label number) + 1]Label number of the material to be defined. If the label number of an existing material is given,then the previous material definition is overwritten.

MU [12.6008]Initial shear modulus. MU > 0.

LAMDA [1.0]Locking stretch. LAMDA > 0.

KAPPA [63000.0]Bulk modulus. KAPPA > 0.

DENSITY [0]Mass density.

FITTING-CURVE [0]Fitting-curve label. The fitting curve is used to calculate the parameters MU and LAMDA.If FITTING-CURVE > 0 is specified, any values specified for MU and LAMDA will beignored.

VISCOELASTIC-CONSTANTS [0]Viscoelastic-constants label. This parameter is superseded by the RUBBER-VISCOELASTICparameter. However, this parameter is still supported for backwards compatibility.

TEMPERATURE-DEPENDENCE [NO]Specifies the temperature dependence of the material properties. {NO/TRS/FULL}

NO The material properties are not temperature dependent; thermal effects are notincluded.

TRS The material properties are not temperature dependent, but the material is assumedto be TRS (thermorheologically simple). Thermal effects are included.

MATERIAL ARRUDA-BOYCE



FULL The material properties are temperature dependent. Parameters C1 to KAPPA, andRUBBER-VISCOELASTIC to RUBBER-ORTHOTROPIC of this command are ignored.

The only parameters used when TEMPERATURE-DEPENDENCE = FULL are NAME,TEMPERATURE-DEPENDENCE, TREF and RUBBER-TABLE.

TREF [0.0]The material reference temperature, required if TEMPERATURE-DEPENDENCE = TRS orFULL.

RUBBER-TABLE [0]The label number of a rubber-table data set. The type of rubber-table depends uponTEMPERATURE-DEPENDENCE, as follows:

TEMPERATURE-DEPENDENCE = NO :Do not enter a rubber-table.

TEMPERATURE-DEPENDENCE = TRS :A rubber-table of type TRS must be entered. This rubber-table is a table of temperaturesand corresponding coefficients of thermal expansion.

TEMPERATURE-DEPENDENCE = FULL :A rubber-table of type Arruda-Boyce must be entered. This rubber-table is a table oftemperatures and corresponding material properties.

RUBBER-VISCOELASTIC [0]If RUBBER-VISCOELASTIC is zero, no viscoelastic effects are included. If RUBBER-VIS-COELASTIC is non-zero, viscoelastic effects are included, using the data set from thecorresponding RUBBER-VISCOELASTIC command. This parameter is not used whenTEMPERATURE-DEPENDENCE = FULL.

RUBBER-MULLINS [0]If RUBBER-MULLINS is zero, no Mullins effects are included. If RUBBER-MULLINS is non-zero, Mullins effects are included, using the data set from the correspondingRUBBER-MULLINS command. This parameter is not used when TEMPERATURE-DEPEN-DENCE = FULL.

RUBBER-ORTHOTROPIC [0]If RUBBER-ORTHOTROPIC is zero, no orthotropic effects are included. If RUBBER-ORTHOTROPIC is non-zero, orthotropic effects are included, using the data set from thecorresponding RUBBER-ORTHOTROPIC command. This parameter is not used whenTEMPERATURE-DEPENDENCE = FULL.




Auxiliary commands

LIST MATERIAL FIRST LASTDELETE MATERIAL FIRST LAST




MATERIAL CAM-CLAY NAME E NU LAMDA KAPPA GAMMAPNULL MIU OCR KNULL DENSITY SINITIAL

Defines a nonlinear Cam-Clay material model This material model may be used with 2-D solidand 3-D solid elements.

NAME [(current highest material label number)+1]

EInitial Young's modulus E. {> 0.0}

NU [0.0]Poisson's Ratio. {-1.0 < NU < 0.5}

LAMDAIsotropic normal consolidation slope. {> 0.0}

KAPPAUnloading-reloading slope. {> 0.0}

GAMMACritical state constant [1]. {> 0.0}

PNULL [0.0]Initial size of yield surface. {≥ 0.0}

MIU [1.0]Critical state constant [2]. {> 0.0}

OCR [0.0]Over-consolidation ratio. {≥ 0.0}

KNULL [0.0]The coefficient of earth pressure. {≥ 0.0}

DENSITY [0.0]Mass density

SINITIALApplied initial conditions : initial stresses SINITIAL=1.0, initial stiffness SINITIAL=0.0.{1.0/0.0}

Note: If an initial stiffness is applied, the initial size of the yield surface - PNULL >0.0.

MATERIAL CAM-CLAY



MATERIAL CONCRETE NAME OPTION E0 NU SIGMAT SIGMATPSIGMAC EPSC SIGMAU EPSU BETA C1 C2XSI STIFAC SHEFAC ALPHA TREF INDNU GFDENSITY SP11 SP12 SP13 SP14 SP15 SP16SP311 SP321 SP331 SP341 SP351 SP361 SP312SP322 SP332 SP342 SP352 SP362 SP313 SP323SP333 SP343 SP353 SP363TEMPERATAURE-DEPENDENT

thetai E0i nui alphai sigmati sigmaci epsci sigmaui epsui sigmatpi xsii gfi

Defines a nonlinear concrete material. This material model may be used with 2-D solid and 3-Dsolid elements.

NAME [(current highest material label number) + 1]Label number of the material to be defined.

OPTION [KUPFER]Selects triaxial failure curve input method. INPUT requires the specification of 24 values,SP11 to SP363, to represent the failure curves. {KUPFER/SANDIA/INPUT}

OPTION = KUPFER corresponds to:

BETA = 0.75SP11 = 0.0 SP12 = 0.25 SP13 = 0.5SP14 = 0.75 SP15 = 1.0 SP16 = 1.2SP311 = 1.0 SP321 = 1.4 SP331 = 1.7SP341 = 2.2 SP351 = 2.5 SP361 = 2.8SP312 = 1.3 SP322 = 1.5 SP332 = 2.0SP342 = 2.3 SP352 = 2.7 SP362 = 3.2SP313 = 1.25 SP323 = 1.45 SP333 = 1.95SP343 = 2.25 SP353 = 2.65 SP363 = 3.15

OPTION = SANDIA corresponds to:

BETA = 0.5SP11 = 0.0 SP12 = 0.1 SP13 = 0.2SP14 = 0.3 SP15 = 0.4 SP16 = 1.0SP311 = 1.0 SP321 = 1.62 SP331 = 2.1SP341 = 2.5 SP351 = 2.8 SP361 = 4.75SP312 = 1.2 SP322 = 2.25 SP332 = 2.75SP342 = 3.01 SP352 = 3.25 SP362 = 4.6SP313 = 1.2 SP323 = 2.06 SP333 = 2.32SP343 = 2.55 SP353 = 2.72 SP363 = 3.79

MATERIAL CONCRETE



E0Tangent modulus at zero strain.

NUPoisson�s ratio.

SIGMATUniaxial cut-off tensile stress. {> 0.0}

SIGMATPPost-cracking uniaxial cut-off tensile stress. {> 0.0}If SIGMATP=0, program sets SIGMATP=SIGMAT.

SIGMACUniaxial maximum compressive stress. {SIGMAC<SIGMAU< 0.0}

EPSCUniaxial compressive strain at SIGMAC. {EPSU<EPSC< 0.0}

SIGMAUUltimate uniaxial compressive stress. {SIGMAC<SIGMAU< 0.0}

EPSUUltimate uniaxial compressive strain. {EPSU<EPSC< 0.0}

BETA [0.75 (OPTION = KUPFER, INPUT)] [0.5 (OPTION = SANDIA)]

Principal stress ratio used for failure surface input. {0.0 < BETA < 1.0}

C1 [1.4]C2 [-0.4]Critical strain constants.

XSI [8.0]Constant used to define the tensile strain corresponding to zero stress in tensile failure.

STIFAC [0.0001]Normal stiffness reduction factor.

SHEFAC [0.5]Shear stiffness reduction factor.

ALPHA [0.0]Mean coefficient of thermal expansion.

MATERIAL CONCRETE



TREF [0.0]Reference temperature for thermal expansion calculation. See the Theory and Modeling Guide.

INDNU [CONSTANT]Selects one of the following options for Poisson�s ratio:

CONSTANT Poisson�s ratio remains constant.

VARIABLE Poisson�s ratio is allowed to vary (see Theory and Modeling Guide).

GF [0.0]Fracture energy.

DENSITY [0.0]Mass density.

SP11 ... SP363Principal stress ratios used to define compression failure envelope. Only used when OPTION= INPUT. See the Theory and Modeling Guide.

TEMPERATURE-DEPENDENT [NO]Indicates whether material is temperature dependent. If YES then material property variationwith temperature follows in the command data lines. Note that the maximum allowed numberof temperature points is 16. {YES/ NO}

thetaiTemperature at data point �i�.

E0iTangent modulus at zero strain at temperature �thetai�.

nuiPoisson�s ratio at temperature �thetai�.

alphaiMean coefficient of thermal expansion at temperature �thetai�.

sigmatiUniaxial cut-off tensile stress at temperature �thetai�.

sigmaciUniaxial maximum compressive stress at temperature �thetai�.

MATERIAL CONCRETE



epsciUniaxial compressive strain for stress sigmaci, at temperature �thetai�.

sigmauiUniaxial ultimate compressive stress at temperature �thetai�.

epsuiUniaxial ultimate compressive strain at temperature �thetai�.

sigmatpiPost-cracking tensile stress at temperature �thetai�.

Note: The material properties are automatically sorted in order of increasingtemperature. If the same temperature is given several times, only the last givenvalues are used.

xsiiConstant for the tensile strain failure at temperature �i�

gfiFracture energy at temperature �i�

Auxiliary commands


MATERIAL CONCRETE



MATERIAL CREEP NAME CREEP-LAW TEMP-UNIT E NU A0 A1A2 A3 A4 A5 A6 A7 ALPHA TOLIL DENSITYNRUPT1 NRUPT2 TIME-HARDENING A8 A9 A10A11 A12 A13 A14 A15

Defines a nonlinear creep material model. This model falls under the category of the moregeneral thermo-elastic-plastic and creep material model, which requires nodal temperatureinput. (A uniform zero nodal temperature is assumed otherwise). This model also assumesthat the effective stress remains below 104×(Young�s modulus) during the analysis. It may beused with truss, 2-D solid, 3-D solid, isobeam, shell and pipe elements.


CREEP-LAW [1]Selects type of the creep law. For details, please refer to the Theory and ModelingGuide,Section 3.6.3. {1/2/3/LUBBY2/BLACKBURN}

TEMP-UNIT [CELSIUS]Creep law 3 may refer to temperatures in degrees Celsius (the centigrade scale) or degreesKelvin (the absolute scale). {CELSIUS/KELVIN}

EYoung�s modulus. {> 0.0}


A0 ... A15 [0.0]Creep law constants, ai. A8 ... A15 are applicable only when CREEP-LAW = BLACKBURN.

ALPHA [1.0]Parameter for creep rate equation time integration. The limiting values are:

0.0 Euler forward method (explicit).1.0 Euler backward method (implicit).

Note: ALPHA = 1.0 must be used with large strain analyses.

TOLIL [1.0E-10]Solution tolerance for effective stress calculation. See the Theory and Modeling Guide forfurther details.


MATERIAL CREEP



NRUPT1 [0]NRUPT2 [0]Label numbers of rupture criteria, defined by command RUPTURE. Two rupture criteria canbe used simultaneously provided they are not of the same type. A zero value indicates thatno rupture criteria are to be used with the material definition.

TIME-HARDENING [NO]Indicates whether strain hardening (NO) or time hardening (YES) is used. {YES/NO}

Auxiliary commands


MATERIAL CREEP



MATERIAL CREEP-IRRADIATION NAME IRRADC NF TEMP-UNIT E NU A1A2 A3 A4 A5 ALPHA TOLIL DENSITYNRUPT1 NRUPT2 TIME-HARDENING TREF

Defines a irradiation creep material model with temperature and neutron fluence dependentproperties. This material model may be used with 2-D solid and 3-D solid elements.


IRRADCLabel number of the irradiation creep table used. The number refers to a definition made bythe command IRRADIATION_CREEP-TABLE.

NFLabel number of the fast neutron dose rate

TEMP-UNIT [CELSIUS]Creep law may refer to temperatures in degrees Celsius (the centigrade scale) or degreesKelvin (the absolute scale)

CELSIUS Celsius degrees KELVIN Kelvin degrees

EInitial Youngs modulus. (E must be > 0.0)

NU [0.0]Poisson�s ratio. (-1.0 < NU < 0.5).

A1 ... A5Creep law constants.


0.0 Euler forward method (explicit)

1.0 Euler backward method (implicit)


MATERIAL CREEP-IRRADIATION





NRUPT1, NRUPT2

Label numbers of rupture criteria used. The numbers refer to definitions made by the com-mand RUPTURE. Two rupture criteria can be used at the same time provided their types arenot the same.

TIME-HARDENING [NO]

NO The usual strain hardening method will be used in ADINA.

YES The time hardening method will be used in ADINA.

TREFThe reference temperature for thermal expansion coefficient

Auxiliary commands

LIST MATERIAL CREEP-IRRADIATION FIRST LAST

DELETE MATERIAL CREEP-IRRADIATION FIRST LAST

MATERIAL CREEP-IRRADIATION



MATERIAL CREEP-VARIABLE NAME NCOEF TEMP-UNIT E NU ALPHATOLIL DENSITY NRUPT1 NRUPT2TIME-HARDENING CREEP-LAW

Defines a nonlinear creep material model with temperature and/or effective-stress dependentcoefficients, see command CREEP-COEFFICIENTS . This model falls under the category ofthe more general thermo-elastic-plastic and creep material model, which requires nodaltemperature input. (A uniform zero nodal temperature is assumed otherwise). It may be usedwith truss, 2-D solid, 3-D solid, isobeam, shell and pipe elements.


NCOEFLabel number of the creep coefficient dependence function, defined by commandCREEP-COEFFICIENTS.

TEMP-UNIT [CELSIUS]Indicates the temperature unit for the creep model; degrees Celsius (the centigrade scale) ordegrees Kelvin (the absolute scale). {CELSIUS/KELVIN}




0.0 Euler forward method (explicit).

1.0 Euler backward method (implicit).




MATERIAL CREEP-VARIABLE



NRUPT1 [0]NRUPT2 [0]Label numbers of rupture criteria, defined by command RUPTURE. Two rupture criteria can beused simultaneously, provided they are not of the same type. A zero value indicates that norupture criteria are to be used with the material definition.


CREEP-LAW [LAW3]Specifies creep law to be used. {NONE/LAW3/LUBBY2}

NONE No creep.

LAW3 e S T ecH= ⋅ ⋅ −

LUBBY2 Lubby2 creep law.

Note: If CREEP-LAW=LAW3, the parameter NCOEF reference a creep-coefficient functiondefined by command CREEP-COEFFICIENTS TEMPERATURE-ONLY orCREEP-COEFFICIENTS MULTILINEAR.

If CREEP-LAW=LUBBY2, the parameter NCOEF reference a creep-coefficientfunction defined by command CREEP-COEFFICIENTS LUBBY2.

Auxiliary commands


MATERIAL CREEP-VARIABLE



MATERIAL CURVE-DESCRIPTION NAME OPTION GAMMA STIFACSHEFAC DENSITY

strainvi kloadi kunloadi gloadi (i = 1�6)

Defines a nonlinear geological material, with the option of tension cut-off or cracking.Moduli at 6 volume strain values must be provided. This material model may be used with 2-Dplane strain, axisymmetric and 3-D solid elements.


OPTION [NONE]Selects special options.

NONE No special options.

TENSION-CUT-OFF Tension cut-off is modeled.

CRACKING Material cracking is modeled.

GAMMA [0.0]The material density used to calculate the in-situ gravity pressure.

STIFAC [0.0]Normal stiffness reduction factor. {< 1.0}

SHEFAC [0.0]Shear stiffness reduction factor. {< 1.0}


strainviVolume strain at data point �i�.

kloadiLoading bulk modulus at strain �strainvi�.

kunloadiUnloading bulk modulus at strain �strainvi�.

gloadiLoading shear modulus at strain �strainvi�.

MATERIAL CURVE-DESCRIPTION



Note:

strainv1 = 0.0

strainvj > strainv(j-1)

kunloadj ≥ kloadj; gloadj < 1.5 × kloadj

The unloading shear modulus is calculated as

(kunload/kload) × gload

Auxiliary commands


MATERIAL CURVE-DESCRIPTION



MATERIAL DRUCKER-PRAGER NAME E NU ALPHA KYIELD WCAPDCAP TCUT ICPOS RCAP DENSITYBETA POTENTIAL

Defines a nonlinear Drucker-Prager material model with a hardening cap and tension cut-off.This material model may be used with 2-D solid and 3-D solid elements.



NU [0.0]Poisson�s ratio. {0.0 ≤ NU < 0.5}

ALPHA [0.0]Yield function parameter α. {≥ 10-5}

KYIELDYield function parameter, k. {> 0.0}

WCAPCap hardening parameter, W. {< 0.0}

DCAPCap hardening parameter, D. {< 0.0}

TCUT [0.0]Tension cut-off limit. {≥ 0.0}

ICPOS [0.0]Initial cap position. {≤ 0.0}

RCAP [0.0]Cap ratio. This is the ratio of the major/minor axes of the elliptical cap. RCAP = 0.0 corre-sponds to a planar cap. {≥ 0.0}


BETA [0.0]Potential function parameter β. {≥ 0.0}

MATERIAL DRUCKER-PRAGER


Chap. 7 Model definition MATERIAL DRUCKER-PRAGER

POTENTIAL [NO]Indicates whether to use or ignore the specified BETA. {YES/NO}If NO is specified, then BETA = ALPHA.

Auxiliary commands





MATERIAL DRUCKER-PRAGER



MATERIAL ELASTIC NAME E NU DENSITY ALPHA

Defines an isotropic linear elastic material. This material model may be used with all elementsexcept fluid elements.





ALPHA [0.0]Coefficient of thermal expansion.

Auxiliary commands


MATERIAL ELASTIC



MATERIAL FLUID NAME K DENSITY GRAVITY X0 Y0 Z0

Defines a linear fluid material. This material model may be used with 2-D and 3-D fluidelements.


KBulk modulus.


GRAVITY [0.0]The gravity constant used in calculating free surface effects.

Note: This parameter is used only when MASTER FLUIDPOTENTIAL=YES. Tospecify gravity loads when MASTER FLUIDPOTENTIAL=AUTOMATIC usecommands: APPLY-LOAD andLOAD MASSPROPORTIONAL INTERPRETATION=BODY-FORCE.

X0 [0.0]Y0 [0.0]Z0 [0.0]X's, Y�s and Z�s datum value for body force potential. See Theory and Modeling Guide.

Note: These parameters are used only when MASTER FLUIDPOTENTIAL=AUTOMATICand when there are gravity loads entered using commandLOAD MASSPROPORTIONAL INTERPRETATION=BODY-FORCE.See the ADINA Theory and Modeling Guide, Equation 2.11-35.

Auxiliary Commands


MATERIAL FLUID



MATERIAL GASKET NAME TREF DENSITY YIELD-CURVE G-G E-G ALPHA-GLEAKAGE-PRESSURE E-INPLANE NU-INPLANEALPHA-INPLANE NPOINTS

lcurvei

Defines a gasket material model. This material model may be used with low-order elements of2-D solid and 3-D solid elements.


TREF [0.0]Reference temperature for thermal expansion coefficient.


YIELD-CURVE [1]Label of yield (loading) curve. This curve is defined using the LCURVE command.

G-G [0.0]Transverse shear modulus. {G-G>=0.0}

E-G [0.0]Tensile Young's modulus in normal direction.{E-G>=0.0}

ALPHA-G [0.0]Mean coefficient of thermal expansion in normal direction. {ALPHA-G>=0.0}

LEAKAGE-PRESSURE [0.0]Leakage pressure.

E-INPLANE [0.0]Inplane Young's modulus. {E-INPLANE>=0.0}

NU-INPLANE [0.0]Inplane Poisson's ratio. {NU-INPLANE>=0.0}

ALPHA-INPLANE [0.0]Inplane mean coefficient of thermal expansion. {ALPHA-INPLANE>=0.0}

MATERIAL GASKET



NPOINTS [2]The point number on the yield curve which corresponds to the initial yield point. All previ-ous points are nonlinear elastic loading/unloading data.

lcurvei

Label numbers of loading-unloading curves. The curves are defined using the LCURVEcommand.

Note:All loading-unloading curves must have same number of points (=NPOINT) and their firstpoint must have Pressure = 0.0 and their last point must coincide with a yield point.

MATERIAL GASKET



MATERIAL GURSON-PLASTIC NAME E NU YIELD Q1 Q2 Q3F0 N FN SN EN TOL DENSITYALPHA TREF FC FF

Command MATERIAL GURSON-PLASTIC defines a Gurson plastic material. This materialmodel may be used with 2-D solid and 3-D solid elements.


EYoung=s modulus. {> 0.0}

NU [0.0]Poisson=s ratio. {-1.0 < NU < 0.5}

YIELDInitial yield stress in simple tension.

Q1 [1.5]Q2 [1.0]Q3 [2.25]Tvergaard parameters.

F0 [0.0]Initial void volume fraction.

N [0.1]Stress-strain curve constant.

FN [0.04]Volume fraction of void nucleating particles.

SN [0.1]Standard deviation of normal distribution.

EN [0.3]Mean plastic strain of normal distribution.

TOL [1.0E-7]Solution tolerance.

MATERIAL GURSON-PLASTIC


Sec. 7.1 Material modelsMATERIAL GURSON-PLASTIC



TREF [0.0]The reference temperature for thermal expansion coefficient. See the Theory and ModelingGuide.

Auxiliary commands




MATERIAL HYPERELASTIC NAME MODEL TENSION-CURVESHEAR-CURVE EQUIBIAXIAL-CURVEORDER WEIGHTING CURVE-TYPEALPHA1 ALPHA2 ALPHA3 ALPHA4ALPHA5 ALPHA6 ALPHA7 ALPHA8ALPHA9 KAPPA DENSITY METHODNSINGULAR MAX-SINGV MIN-SINGV ECHO

This material model will not be supported from ADINA version 8.0 onwards, but is retainedfor the convenience of users of previous versions.

Defines a hyperelastic material model, which is an incompressible nonlinear elastic materialmodel for rubber materials.

A least squares curve fitting technique is employed to determine the parameters for a general-ized Mooney-Rivlin or an Ogden material model from experimental stress versus strain (orstretch) data. The data can be input for any of three test cases: (i) simple tension, (ii) pureshear, or (iii) equibiaxial tension. A single test or combination of any two, or all three, can besupplied. The accuracy of the model curve thus fitted depends on the number of data points,and the desired approximation order of the model. The total number of data points, from allthree test cases, is subject to a minimum (equal to the input order for an Ogden model, and 2,5, 9 for a generalized Mooney-Rivlin model of input order 1, 2, 3 respectively). See theTheory and Modeling Guide for details.


MODEL [OGDEN]Specifies which type of material model is to be used.

OGDEN The Ogden constants µi are determined, from the inputdata curves and αi values.

MOONEY-RIVLIN The Mooney-Rivlin constants Ci are determined.

TENSION-CURVE [0]Indicates the label number of a (stress, strain) data curve, defined by command SCURVE,which provides data for the simple tension test case. A value of 0 indicates no simpletension data is supplied. The abscissae may be interpreted as strain or stretch as indicatedby parameter CURVE-TYPE.

SHEAR-CURVE [0]Indicates the label number of a (stress, strain) data curve, defined by command SCURVE,

MATERIAL HYPERELASTIC



which provides data for the pure shear test case. A value of 0 indicates no pure shear data issupplied. The abscissae may be interpreted as strain or stretch as indicated by parameterCURVE-TYPE.

EQUIBIAXIAL-CURVE [0]Indicates the label number of a (stress, strain) data curve, defined by command SCURVE,which provides data for the equibiaxial tension test case. A value of 0 indicates noequibiaxial tension data is supplied. The abscissae may be interpreted as strain or stretch asindicated by parameter CURVE-TYPE.

ORDER [3]Approximation order. Allowed values are:

1 ≤ ORDER ≤ 3 (MODEL = MOONEY-RIVLIN)

1 ≤ ORDER ≤ 9 (MODEL = OGDEN)

Note: If MODEL=MOONEY-RIVLIN, then the material constants derivied are as follows:

ORDER Constants1 C1 ÷ C22 C1 ÷ C53 C1 ÷ C9

WEIGHTING [NO]Specifies whether or not the least squares fitting scheme utilizes weighted data intervals.Their use may provide a better fit for data with very irregular spacing of the strain (or stretch)abscissae. {YES/NO}

CURVE-TYPE [STRAIN]Indicates the type of input curve data given by parameters TENSION-CURVE, SHEAR-CURVE, and EQUIBIAXIAL-CURVE. The option is given for the data abscissae to be eitherprincipal (engineering) strain, or principal stretch (= deformed length / undeformed length).The ordinate values in either case are values of nominal stress (= force / unit undeformedarea).

STRAIN Input principal engineering strain data.

STRETCH Input principal stretch data.

ALPHAi [i (1 ≤ i ≤ 9)]Ogden constants αi.




KAPPA [determined from the initial shear modulus,assuming near incompressibility ( ν=0.499)]

Bulk modulus.


METHOD [SVD]Specifies the least squares matrix equation solution method. Use of Gaussian elimination maywell result in model constants which alternate in sign and have very high magnitude. This isdue to the presence of near-singular terms in the least squares system. The �singular valuedecomposition� method attempts to remove these terms during solution, yielding morereasonable model constants without affecting the overall quality of the least squares fit. Thenumber of near-singular terms to be removed may be controlled by parameters MAX-SINGV,MIN-SINGV. Near-singular terms are removed by default until a monotone increasingsolution is obtained for all test cases.

SVD The singular value decomposition method.

GAUSS Standard Gaussian elimination technique.

NSINGULAR [AUTOMATIC]Indicates whether the number of near-singular terms to be removed in the singular valuedecomposition solution method is controlled automatically by the program, or is to bespecified by you via parameters MAX-SINGV, MIN-SINGV. This parameter is only applicablewhen METHOD = SVD.

AUTOMATIC The program controls the number of near-singular terms to beremoved by the singular value decomposition solution method.

CUSTOM You indicate the maximum and minimum number ofnear-singular terms to be removed.

MAX-SINGV [ORDER (MODEL=OGDEN)] [2 (ORDER=1, MODEL=MOONEY-RIVLIN)] [5 (ORDER=2, MODEL=MOONEY-RIVLIN)] [9 (ORDER=3, MODEL=MOONEY-RIVLIN)]

If NSINGULAR = CUSTOM, this parameter indicates the maximum number of near-singularterms which are permitted to be removed during the search for a monotone increasing set ofresult curves. MAX-SINGV may range from 0 (for which the resulting solution is identical tothat obtained by Gaussian elimination) to the total desired number of model constants, asindicated by parameter ORDER.

MIN-SINGV [0]If NSINGULAR = CUSTOM, this parameter indicates the minimum number of near-singular




terms which will be removed by the singular value decomposition method, i.e., the SVDalgorithm will remove at least MIN-SINGV terms even if a monotone solution set was ob-tained with fewer terms removed.

ECHO [ALL]Specifies the level of information reported by the command.

NONE The command behaves silently, except for a completion message.

MODEL The resulting Ogden / Mooney-Rivlin model constants are reported.

ALL As well as model constants, curve fitting statistics and comparison tablesof input and fitted stress values for the input strain/stretch points isreported.

Note: It is required that the initial shear modulus be positive, i.e.,

µ αi i⋅ > 0 0. for an Ogden model.or

C C1 2 0 0+ > . for a Mooney-Rivlin model.

Note: KAPPA is used in plane strain, axisymmetric and three-dimensional analyses.

Note: For a discussion on the singular value decomposition method and its application tothe least squares curve fitting algorithm, please consult the Theory and ModelingGuide.

Note: It is unwise to apply this command to a small set of data within a narrow range ofstrains (stretches). If possible, some values of strain (stretch) should be input forcompression, and it is recommended that the resulting material behavior always bechecked graphically with the MATERIALSHOW command.

Note: The generalized Mooney-Rivlin parameters C1 through C9 may be evaluated bythis command; the parameters D1, D2 are, however, set to zero by this command.

Auxiliary commands





MATERIAL HYPER-FOAM NAME NPOINTS MU1 MU2 ... MU9ALPHA1 ALPHA2 ... ALPHA9BETA1 BETA2 ... BETA9 DENSITY FITTING-CURVEISO-VISCOELASTIC-CONSTANTSVOL-VISCOELASTIC-CONSTANTSTEMPERATURE-DEPENDENCE TREFRUBBER-TABLE RUBBER-VISCOELASTICRUBBER-MULLINS RUBBER-ORTHOTROPIC

Defines a hyper-foam material model, which is a hyperelastic material model for rubbermaterials. This material model may be used with 2-D solid and 3-D solid elements.


NPOINTS [1]This parameter is not used in this version of the AUI.

MUi [1.85 (i=1); 9.2 (i=2); 0.0 (i=3,4,5,...,9)]ALPHAi [4.5 (i=1); -4.5 (i=2); 0.0 (i=3,4,5,...,9)]BETAi [9.2 (i=1); 9.2 (i=2); 0.0 (i=3,4,5,...,9)]Non-viscoelastic constants µi, αi, βi (i=1,2,3,...,9).


FITTING-CURVE [0.0]Fitting-curve label. The fitting curve is used to calculate the parameters MUi, ALPHAi andBETAi. If FITTING-CURVE > 0 is specified, any values specified for MUi, ALPHAi and BETAiwill be ignored.

ISO-VISCOELASTIC-CONSTANTS [0]Viscoelastic-constants label (isochoric) . This parameter is superseded by the RUBBER-VISCOELASTIC parameter. However, this parameter is still supported for backwards compat-ibility.

VOL-VISCOELASTIC-CONSTANTS [0]Viscoelastic-constants label (volumetric) . This parameter is superseded by the RUBBER-VISCOELASTIC parameter. However, this parameter is still supported for backwards compat-ibility.

MATERIAL HYPER-FOAM


Sec. 7.1 Material modelsMATERIAL HYPER-FOAM

Notes:1 µi * αi must be greater than zero.2 βi must be greater than -1/3.










TEMPERATURE-DEPENDENCE = FULL :A rubber-table of type Hyper-Foam must be entered. This rubber-table is a table of

temperatures and corresponding material properties.

RUBBER-VISCOELASTIC [0]If RUBBER-VISCOELASTIC is zero, no viscoelastic effects are included. If RUBBER-VIS-COELASTIC is non-zero, viscoelastic effects are included, using the data set from thecorresponding RUBBER-VISCOELASTIC command. This parameter is not used when



TEMPERATURE-DEPENDENCE = FULL.



Auxiliary commands


MATERIAL HYPER-FOAM



MATERIAL ILYUSHIN NAME E NU YIELD ET GAMMA DENSITY

Defines a nonlinear elastic-plastic material with the Ilyushin yield condition and isotropichardening. This material model may be used with plate elements.




YIELDYield stress in simple tension.

ET [0.0]Strain hardening modulus.

GAMMA [0.0]Ilyushin factor.


Auxiliary commands


MATERIAL ILYUSHIN



MATERIAL MOHR-COULOMB NAME E NU PHI PSI COH TCUT DENSITYDILATATION TEMPEFFECTS ECC ALPHA

Defines a nonlinear Mohr-Coulomb material model that may include temperature effects. Thismaterial model may be used with 2-D solid and 3-D solid elements



NU [0.0]Poisson�s ratio. {0.0 ≤ NU < 0.5}

PHIFriction angle in degrees. {> 0.0}

PSI [0.0]Dilatation angle in degrees. {0.0 ≤ PSI ≤ PHI}

COH [0.0]Cohesion. {≥ 0.0}

TCUT [1.0E10]Tension cut-off limit. {≥ 0.0}


DILATATION [YES]Indicates whether to use or ignore the specified dilatation angle. {YES/NO}

TEMPEFFECTS [NO]Indicates whether or not to apply temperature effects. Note that if temperature effects areincluded, then a different potential function will be used (see the Theory and Modeling Guidefor details). {YES/NO}

ECC [0.1]Eccentricity parameter at the apex of the Mohr-Coulomb yield surface. Applicable only whentemperature effects are included. {0.0 < ECC < 1.0}

MATERIAL MOHR-COULOMB



ALPHA [0.0]Mean coefficient of thermal expansion. Applicable only when temperature effects areincluded. {≥ 0.0}

Auxiliary commands




MATERIAL MOONEY-RIVLIN NAME C1 C2 C3 C4 C5 C6 C7 C8 C9 D1 D2KAPPA DENSITY FITTING-CURVEVISCOELASTIC-CONSTANTSTEMPERATURE-DEPENDENCE TREFRUBBER-TABLE RUBBER-VISCOELASTICRUBBER-MULLINS RUBBER-ORTHOTROPIC

Defines a Mooney-Rivlin material model, which is an incompressible nonlinear elastic materialmodel for rubber materials. This material model may be used with 2-D solid and 3-D solidelements.


Ci [0.0 (1 ≤ i ≤ 9)]Dj [0.0 (1 ≤ j ≤ 2)]Generalized Mooney-Rivlin constants Ci, Dj. See the Theory and Modeling Guide for details.


Bulk modulus.

Note: It is required that the initial shear modulus be positive, i.e.,

C1 + C2 + D1⋅D2 > 0.0

KAPPA is used in plane strain, axisymmetric and three-dimensional analyses.


FITTING-CURVE [0]Fitting-curve label. The fitting curve is used to calculate the parameters Ci and Di. IfFITTING-CURVE > 0 is specified, any values specified for Ci and Di will be ignored.



NO The material properties are not temperature dependent; thermal effects are not

MATERIAL MOONEY-RIVLIN



included.








TEMPERATURE-DEPENDENCE = FULL :A rubber-table of type Mooney-Rivlin must be entered. This rubber-table is a table oftemperatures and corresponding material properties.







Auxiliary commands





MATERIAL MROZ-BILINEAR NAME E NU YIELD BOUND ET ETBEPA DENSITY ALPHA TREF

Defines an elastic-plastic material with the Mroz yield criteria and bilinear hardening. Thismaterial model may be used with 2-D solid and 3-D solid elements.





BOUNDBounding stress.

ETStrain hardening modulus.

ETBHardening modulus of the bounding surface.

EPA [0.0]The maximum allowable effective plastic strain, which enables the modeling of rupture. Thestresses are set to zero when the effective plastic strain is greater than the rupture strain EPA.EPA = 0.0 corresponds to no rupture condition.


ALPHA [0.0]The mean coefficient of thermal expansion.

TREF [0.0]Reference temperature for calculation of ALPHA. See the Theory and Modeling Guide.

Auxiliary commands


MATERIAL MROZ-BILINEAR



MATERIAL MULTILINEAR-PLASTIC-CREEP NAME HARDENINGCREEP-LAW TEMP-UNITA0 A1 A2 A3 A4 A5 A6A7 TREF ALPHA TOLILDENSITY NRUPT1 NRUPT2TIME-HARDENING A8 A9 A10A11 A12 A13 A14 A15

thetai Ei nui alphai dcurvei

Defines a nonlinear thermo-elastic-plastic-multilinear and creep material, with von Mises yieldcondition and isotropic or kinematic strain hardening. This material model may be used withtruss, 2-D solid, 3-D solid, isobeam, shell and pipe elements.


HARDENING [ISOTROPIC]Selects the type of strain hardening used by the material.

ISOTROPIC Linear isotropic strain hardening.

KINEMATIC Linear kinematic strain hardening.

CREEP-LAW [0]Indicates type of the creep law. For details of the creep laws, please refer to Section 3.6.3 ofthe Theory and Modeling Guide.{0/1/2/3/LUBBY2/BLACKBURN}


A0 ... A15 [0.0]Creep law constants, ai. A8 ... A15 are applicable only when CREEP-LAW = BLACKBURN.

TREF [0.0]The reference temperature for thermal expansion calculation. See the Theory and ModelingGuide.

ALPHA [1.0]Time integration parameter {0.0 ≤ ALPHA ≤ 1.0}, used in the integration of the thermo-plastic and creep rate equations. The limiting values are:

MATERIAL MULTILINEAR-PLASTIC-CREEP





TOLIL [1.0E-10]Solution tolerance. See the Theory and Modeling Guide.


NRUPT1 [0]NRUPT2 [0]Label numbers of rupture criteria, defined by command RUPTURE. Two rupture criteria canbe used simultaneously provided that they are not of the same type. A zero value indicatesthat no rupture criteria are to be used with the material definition.



EiYoung�s Modulus at temperature �thetai�.



dcurveiStress vs. strain curve at temperature �thetai�. This data entry is the label number of a stress-strain curve defined via the SCURVE command.

When MASTER CONVERT-SSVAL=NO, stressi and straini are interpreted as true stresses andstrains. Stresses and strains entered in the SCURVE command are also intrepreted as truestresses and strains.

When MASTER CONVERT-SSVAL=YES, stressi and straini are interpreted as engineeringstresses and strains. Stresses and strains entered in the SCURVE command are alsointrepreted as engineering stresses and strains.

MATERIAL MULTILINEAR-PLASTIC-CREEP


Chap. 7 Model definition MATERIAL MULTILINEAR-PLASTIC-CREEP

Note: The material properties are automatically sorted in order of increasing temperature. Ifthe same temperature is given several times, only the last given values are used.

Auxiliary commands




MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLENAME HARDENING NCOEF TEMP-UNIT TREF ALPHA TOLILDENSITY NRUPT1 NRUPT2 TIME-HARDENING CREEP-LAW

thetai Ei nui alphai dcurvei

Defines a nonlinear thermo-elastic-plastic-multilinear and creep material, with temperatureand/or effective-stress dependent coefficients (see command CREEP-COEFFICIENTS ), vonMises yield condition, and isotropic or kinematic strain hardening. This material model maybe used with truss, 2-D solid, 3-D solid, isobeam, shell and pipe elements.


HARDENING [ISOTROPIC]Selects the type of strain hardening rule:










MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE



TOLIL [1.0E-10]Solution tolerance. See the Theory and Modeling Guide for further details.


NRUPT1 [0]NRUPT2 [0]Label numbers of rupture criteria, as defined by command RUPTURE. Two rupture criteria canbe used simultaneously, provided they are not of the same type. A zero value indicates thatno rupture criteria are to be used with the material definition.



NONE No creep.












dcurveiStress v strain curve at temperature �thetai�. This data entry is the label number of a stress-strain curve defined via SCURVE.




Auxiliary commands





MATERIAL NONLINEAR-ELASTIC NAME DENSITY DCURVE NU MATRIX

straini stressi

Defines a nonlinear elastic material. The model is uniaxial and the stress-strain curve isdefined as piecewise linear through the data points (straini, stressi) which can be entered asdata lines following the command or can be referenced via the DCURVE parameter (seeSCURVE ). For a given strain, the total stress and tangent modulus are interpolated from theinput curve. This material model may be used with truss elements, 2-D solid and 3-D solidelements.



DCURVE [0]Label number of a stress-strain curve defined by command SCURVE. This defines the stress-strain data points associated with this material model. If DCURVE is input as 0, then the datalines following the command define the stress-strain data points. Conversely, if DCURVE isgreater than zero then no data lines are expected.

NU [0.0]Poisson's ratio. Not applicable to truss element. {-1.0 < NU < 0.5}

MATRIX [TANGENT]This flag indicates whether the tangent or secant stress-strain matrix is used when the stress-strain curve enters into a softening region. Not applicable to truss element.{TANGENT/SECANT}

TANGENT Use tangent stress-strain matrixSECANT Use secant stress-strain matrix

strainiStrain at data point �i�.

stressiStress at strain �straini�.

Auxiliary commands


MATERIAL NONLINEAR-ELASTIC






MATERIAL OGDEN NAME MU1 ALPHA1 MU2 ALPHA2 MU3ALPHA3 MU4 ALPHA4 MU5 ALPHA5 MU6ALPHA6 MU7 ALPHA7 MU8 ALPHA8 MU9ALPHA9 KAPPA DENSITY FITTING-CURVEVISCOELASTIC-CONSTANTSTEMPERATURE-DEPENDENCE TREFRUBBER-TABLE RUBBER-VISCOELASTICRUBBER-MULLINS RUBBER-ORTHOTROPIC

Defines an Ogden material model, which is an incompressible nonlinear elastic material modelfor rubber materials. This material model may be used with 2-D solid and 3-D solid elements.


MUi [0.0 (1 ≤ i ≤ 9)]ALPHAi [0.0 (1 ≤ i ≤ 9)]Ogden constants µi, αi. See the Theory and Modeling Guide for details. Note that ifALPHAi = 0.0 and curve fitting is used (i.e., FITTING-CURVE > 0), ALPHAi = i will beassigned.


Bulk modulus.


Note: It is required that the initial shear modulus be positive, i.e., µi .νi > 0.0 .

KAPPA is used in plane strain, axisymmetric and three-dimensional analyses.

FITTING-CURVE [0]Fitting-curve label. The fitting curve is used to calculate the parameters MUi and ALPHAi.If FITTING-CURVE > 0 is specified, any values specified for MUi and ALPHAi will be ignored.



MATERIAL OGDEN











TEMPERATURE-DEPENDENCE = FULL :A rubber-table of type Ogden must be entered. This rubber-table is a table oftemperatures and corresponding material properties.



MATERIAL OGDEN




Auxiliary commands


MATERIAL OGDEN



MATERIAL ORTHOTROPIC NAME EA EB EC NUAB NUAC NUBCGAB GAC GBC DENSITY WRINKLEW-TIME ALPHA1 ALPHA2 ALPHA3

Defines an orthotropic linear elastic material. This material model may be used with 2-D solid,3-D solid, shell and plate elements.


EAa-direction modulus. {> 0.0}

EBb-direction modulus. {> 0.0}

EC [0.0]c-direction modulus. EC=0 is admissible only for PLATE elements ( EGROUP PLATE ).{≥ 0.0}

NUAB [0.0]a-b strain ratio.

NUAC [0.0]a-c strain ratio.

NUBC [0.0]b-c strain ratio.

GABa-b shear modulus. {> 0.0}

GAC [0.0]a-c shear modulus. GAC=0 is admissible only for PLATE and 2D solid elements( EGROUP PLATE and EGROUP TWODSOLID ). {≥ 0.0}

GBC [0.0]b-c shear modulus. GBC=0 is admissible only for PLATE and 2D solid elements( EGROUP PLATE and EGROUP TWODSOLID ). {≥ 0.0}


MATERIAL ORTHOTROPIC


Chap. 7 Model definition MATERIAL ORTHOTROPIC

WRINKLE [NO]Indicates whether wrinkling is to be modeled (e.g., for fabrics). {YES/NO}

Note: Modeling of wrinkling is only allowed for TWODSOLID plane stress elements.

W-TIME [0.0]Wrinkling time, i.e., the time at which wrinkling of the material is activated.

ALPHA1 [0.0]The coefficient. of thermal expansion for the a direction.

ALPHA2 [0.0]The coefficient. of thermal expansion for the b direction.

ALPHA3 [0.0]The coefficient. of thermal expansion for the c direction.

Auxiliary commands




MATERIAL PLASTIC-BILINEARNAME HARDENING E NU YIELD ET EPA STRAINRATEFUNCTIONDENSITY ALPHA TREF DEPENDENCY TRANSITION-STRAINRATEEP-STRAINRATE BCURVE BVALUE XM-INF XM0 ETA STRAINRATE-FIT

Defines a bilinear elastic-plastic material model with von Mises yield condition. This materialmodel may be used with truss, 2-D solid, 3-D solid, beam, iso-beam, shell and pipe elements.


HARDENING [ISOTROPIC]Selects the type of strain hardening used by the material. {ISOTROPIC/KINEMATIC/MIXED}

ISOTROPIC Linear isotropic strain hardening.KINEMATIC Linear kinematic strain hardening.MIXED Mixed hardening. See Theory and Modeling Guide, Section 3.4.1




ET [0.0]Strain hardening modulus.

EPA [0.0]Maximum allowable effective plastic strain. This allows for the modeling of material rupture,whereby the stresses are set to zero whenever the effective plastic strain is greater than therupture strain EPA. If EPA is input as 0.0, the rupture condition is not used. EPA is notapplicable to beam elements.

STRAINRATEFUNCTION [0]The parameter is currently not used. Replaced by STRAINRATE-FIT.


MATERIAL PLASTIC-BILINEAR




TREF [0.0]Reference temperature for calculations of ALPHA. See the Theory and Modeling Guide.

Note: The parameters ALPHA, TREF are not applicable to TRUSS elements.

DEPENDENCY [NO]Flag indicating strain rate dependency. {YES/NO}

TRANSITION-STRAINRATE [0.0001]Transition strain rate.

EP-STRAINRATE [0.0]Non-zero strainrate, used only if STRAINRATE-FIT = 0 and BCURVE > 0. This parameter isobsolete, but kept for backwards compatibility.

BCURVE [0]Label number of a stress-strain curve defined by command SCURVE. This parameter isobsolete, but kept for backwards compatibility.

BVALUE [0.0]Strain rate hardening parameter.

XM-INF [0.0]Hardening parameter M∞ , used only for mixed hardening.{0 ≤ XM-INF ≤ 1}

XM0 [0.0]Hardening parameter M0 , used only for mixed hardening.{0 ≤ XM0 ≤ 1}

ETA [0.0]Hardening parameter η , used only for mixed hardening. {ETA ≥ 0}If ETA >0, then 0< XM-INF < 1 and 0< XM0 <1.

STRAINRATE-FIT [0]The label number of a strainrate-fit describing the strain rate dependence of the yield stress.The function must have been defined using the STRAINRATE-FIT command. A zero valueindicates no strain rate dependence.

Notes on the STRAINRATE-FIT, TRANSITION-STRAINRATE, EP-STRAINRATE, BCURVEand BVALUE parameters:




These parameters are used only if DEPENDENCY=YES.

1) STRAINRATE-FIT = 0 and BCURVE = 0. The strainrate material parameters are TRANSI-TION-STRAINRATE and BVALUE. No curve-fitting is performed.

2) STRAINRATE-FIT = 0 and BCURVE > 0. The AUI uses the stress-strain curve entered inBCURVE, and the associated strainrate EP-STRAINRATE, to determine the overstress ratio atstrainrate EP-STRAINRATE.Then the AUI uses the input material parameter TRANSITION-STRAINRATE and theoverstress ratio in a curve-fitting procedure to determine material parameter BVALUE. Notethat the BCURVE>0 option is obsolete and kept only for backwards compatibility.

3) STRAINRATE-FIT > 0. There are two possibilities, depending upon how many strainratesare entered in the strainrate-fit.

a) One strainrate (strainrate1) and stress-strain curve (scurve1) in the strainrate-fit. The AUIdetermines the overstress ratio at strainrate1 using scurve1. Then the AUI uses the inputmaterial parameter TRANSITION-STRAINRATE and the overstress ratio in a curve-fittingprocedure to determine material parameter BVALUE.

b) More than one strainrate (strainratei) and stress-strain curve (scurvei)in the strainrate-fit.The AUI determines the overstress ratio at each strainratei using scurvei. Then the AUI usesthese strainrates and overstress ratios in a curve-fitting procedure to determine both materialparameters TRANSITION-STRAINRATE and BVALUE.

Auxiliary commands





MATERIAL PLASTIC-CREEP NAME HARDENING CREEP-LAW TEMP-UNIT A0A1 A2 A3 A4 A5 A6 A7 A8 A9 A10 A11 A12 A13A14 A15 TREF ALPHA TOLIL DENSITY NRUPT1NRUPT2 TIME-HARDENING

thetai Ei nui yieldi ETi alphai EPAi

Defines a nonlinear thermo-elastic-plastic and creep material, with von Mises yield conditionand isotropic or kinematic strain hardening. This material model may be used with truss, 2-Dsolid, 3-D solid, beam, iso-beam, shell and pipe elements.



ISOTROPIC Linear isotropic strain hardening.KINEMATIC Linear kinematic strain hardening.

CREEP-LAW [0]Indicates type of the creep law. Please refer to the Theory and Modeling Guide, Section 3.6.3for details of the formulation of these creep laws. {0/1/2/3/LUBBY2/BLACKBURN}


A0 ... A15 [0.0]Creep law constants, ai.


ALPHA [1.0]Time integration parameter { 0.0 ≤ ALPHA ≤ 1.0}, used in the integration of the thermo-plastic and creep rate equations. The limiting values are:

0.0 Euler forward method (explicit).1.0 Euler backward method (implicit).

TOLIL [1.0E-10]

MATERIAL PLASTIC-CREEP



Solution tolerance. See the Theory and Modeling Guide.


NRUPT1 [0]NRUPT2 [0]Label numbers of rupture criteria, defined by command RUPTURE. Two rupture criteria canbe used simultaneously provided that they are not of the same type. A zero value indicatesthat no rupture criteria are to be used with the material definition.





yieldiYield stress in simple tension at temperature �thetai�.

ETiStrain hardening modulus at temperature �thetai�.


EPAiMaximum allowable effective plastic strain at temperature �thetai� enabling the modeling ofrupture. If EPAi = 0.0 the rupture condition is not used at temperature �thetai�.


Auxiliary commands


MATERIAL PLASTIC-CREEP



MATERIAL PLASTIC-CREEP-VARIABLE NAME HARDENING NCOEF,TEMP-UNIT TREF ALPHA TOLILDENSITY NRUPT1 NRUPT2TIME-HARDENING CREEP-LAW


Defines a nonlinear thermo-elastic-plastic and creep material, with temperature and/oreffective-stress dependent coefficients (see command CREEP-COEFFICIENTS ), von Misesyield condition, and isotropic or kinematic strain hardening. This material model may be usedwith truss, 2-D solid, 3-D solid, beam, iso-beam, shell and pipe elements.












MATERIAL PLASTIC-CREEP-VARIABLE



TOLIL [1.0E-10]Solution tolerance. See the Theory and Modeling Guide for further details.


NRUPT1 [0]NRUPT2 [0]Label numbers of rupture criteria, as defined by command RUPTURE. Two rupture criteria canbe used simultaneously, provided they are not of the same type. A zero value indicates thatno rupture criteria are to be used with the material definition.














NONE No creep.





Auxiliary commands





MATERIAL PLASTIC-CYCLIC NAME E NU DENSITY ALPHAPLCYCL-ISOTROPIC PLCYCL-KINEMATICPLCYCL-RUPTURE BETA MAXITE RTOL

Defines a plastic-cyclic material, that is, a material model used to model cyclic plasticity. Thismaterial model can be used with 3-D solid elements.






PLCYCL-ISOTROPICThe number of a PLCYCL-ISOTROPIC definition. This definition specifies the dependence ofthe radius of the yield surface on the plastic strains. This parameter must be specified.

PLCYCL-KINEMATIC [0]The number of a PLCYCL-KINEMATIC definition. This definition specifies the dependenceof the back stresses on the plastic strains. This parameter can be set to 0 to specify nokinematic hardening.

PLCYCL-RUPTURE [0]The number of a PLCYCL-RUPTURE definition. This definition specifies the rupture criterion.This parameter can be set to 0 to specify no rupture.

BETA [AUTOMATIC]A factor used in the stress integration (0 ≤ BETA ≤ 1). If BETA=AUTOMATIC,ADINA automatically sets BETA based on the time integration method (=1 for static orimplicit dynamics, =0 for explicit dynamics).

MAXITE [100]The maximum number of stress integration iterations allowed per integration point.

MATERIAL PLASTIC-CYCLIC



RTOL [1E-12]A tolerance used to assess convergence of stress integration iterations. This is a relative

tolerance, i.e., dimensionless values are tested against RTOL.

Notes:

1) The simplest material that can be defined using this command is given by a commandsequence such as

PLCYCL-ISOTROPIC 1 BILINEAR YIELD=2E8MATERIAL PLASTIC-CYCLIC 1 E=2.07E11 NU=0.3 DENSITY=7800 PLCYCL-ISOTROPIC=1

This material is perfectly plastic. This material description is equivalent to

MATERIAL PLASTIC-BILINEAR 1 E=2.07E11 NU=0.3 DENSITY=7800 YIELD=2E8

2) The PLASTIC-CYCLIC material can be used to model bilinear isotropic hardening using acommand sequence such as

PLCYCL-ISOTROPIC 1 BILINEAR YIELD=2E8 EP=2.090909E09MATERIAL PLASTIC-CYCLIC 1 E=2.07E11 NU=0.3 DENSITY=7800 PLCYCL-ISOTROPIC=1

and this material description is equivalent to

MATERIAL PLASTIC-BILINEAR 1 E=2.07E11 NU=0.3 DENSITY=7800 YIELD=2E8ET=2.07E09

3) The plastic-cyclic material can be used to model multilinear isotropic hardening using acommand sequence such as

PLCYCL-ISOTROPIC 1 MULTILINEAR0 2E81E-3 2.5E82E-3 2.7E8MATERIAL PLASTIC-CYCLIC 1 E=2.07E11 NU=0.3 DENSITY=7800 PLCYCL-ISOTROPIC=1


MATERIAL PLASTIC-MULTILINEAR 1 E=2.07E11 NU=0.39.6618E-4 2E82.2077E-3 2.5E83.3043E-3 2.7E8




4) The plastic-cyclic material can be used to model bilinear kinematic hardening using acommand sequence such as

PLCYCL-ISOTROPIC 1 BILINEAR YIELD=2E8PLCYCL-KINEMATIC 1 ARMSTRONG-FREDRICK2.090909E9MATERIAL PLASTIC-CYCLIC 1 E=2.07E11 NU=0.3 DENSITY=7800 PLCYCL-ISOTROPIC=1,PLCYCL-KINEMATIC=1


MATERIAL PLASTIC-BILINEAR 1 E=2.07E11 NU=0.3 DENSITY=7800 YIELD=2E8ET=2.07E09,HARDENING=KINEMATIC

Auxiliary commands





MATERIAL PLASTIC-MULTILINEARNAME HARDENING E NU STRAINRATEFUNCTION DENSITYALPHA TREF DCURVE DEPENDENCY TRANSITION-STRAINRATEEP-STRAINRATE BCURVE BVALUE STRAINRATE-FIT

strain1 stress1 (stress1 = initial yield stress)...straini stressi

Defines a multilinear elastic-plastic material model with von Mises yield condition. Thestress-strain curve is defined as piecewise linear through the data points (straini, stressi)which can be entered as data lines following the command or can be referenced via theDCURVE parameter (see SCURVE ). This material model may be used with truss, 2-D solid, 3-D solid, beam, iso-beam, shell and pipe elements.





ISOTROPIC Linear isotropic strain hardening.KINEMATIC Linear kinematic strain hardening.

E [0.0]Young�s modulus. {> 0.0}


STRAINRATEFUNCTION [0]The parameter is currently not used. Replaced by STRAINRATE-FIT.



MATERIAL PLASTIC-MULTILINEAR



TREF [0.0]Reference temperature to calculations of ALPHA. See the Theory and Modeling Guide.

Note: Parameters ALPHA, TREF are not applicable to TRUSS elements.

DCURVE [0]Label number of a stress-strain curve defined by command SCURVE. This defines the stress-strain data points associated with this material model. If DCURVE is input as 0, then the datalines following the command define the stress-strain data points. Conversely, if DCURVE isgreater than zero then no data lines are expected.

DEPENDENCY [NO]Flag indicating strain rate dependency. {YES/NO}

TRANSITION-STRAINRATE [0.0001]Transition strain rate.

EP-STRAINRATE [0.0]Non-zero strainrate, used only if STRAINRATE-FIT = 0 and BCURVE > 0. This parameter isobsolete, but kept for backwards compatibility.

BCURVE [0]Label number of a stress-strain curve defined by command SCURVE. This parameter isobsolete, but kept for backwards compatibility.

BVALUE [0.0]Strain rate hardening parameter.

strain1Strain at data point 1. The input value here is overwritten by the calculated initial yield strain(stress1 / E).

stress1Stress at strain1, equal to the initial yield stress.

strainiStrain at data point i (i > 1).

stressiStress at straini.

Note: The strain-stress data points can be input in any strain order (they will beautomatically sorted in increasing strain order) but all input strains must be greaterthan or equal to strain1 = (stress1 / E).




Note: The stress is assumed to be zero when the effective plastic strain is greater than themaximum input strain value.

Note: The slope of the stress-strain curve (the tangent modulus, ET) must satisfy (for allpoints in the nonlinear part of the curve):

0 ≤ ET < E for isotropic hardening.0.0001 × E ≤ ET < E for kinematic hardening.

STRAINRATE-FIT [0]The label number of a strainrate-fit describing the strain rate dependence of the yield stress.The function must have been defined using the STRAINRATE-FIT command. A zero valueindicates no strain rate dependence.

Notes on the STRAINRATE-FIT, TRANSITION-STRAINRATE, EP-STRAINRATE, BCURVEand BVALUE parameters:

These parameters are used only if DEPENDENCY = YES.

1) STRAINRATE-FIT = 0 and BCURVE = 0. The strainrate material parameters are TRANSI-TION-STRAINRATE and BVALUE. No curve-fitting is performed.

2) STRAINRATE-FIT = 0 and BCURVE > 0. The AUI uses the stress-strain curve entered inBCURVE, and the associated strainrate EP-STRAINRATE, to determine the overstress ratio atstrainrate EP-STRAINRATE.Then the AUI uses the input material parameter TRANSITION-STRAINRATE and theoverstress ratio in a curve-fitting procedure to determine material parameter VALUE. Notethat the BCURVE > 0 option is obsolete and kept only for backwards compatibility.

3) STRAINRATE-FIT > 0. There are two possibilities, depending upon how many strainratesare entered in the strainrate-fit.

a) One strainrate (strainrate1) and stress-strain curve (scurve1) in the strainrate-fit. The AUIdetermines the overstress ratio at strainrate1 using scurve1. Then the AUI uses the inputmaterial parameter TRANSITION-STRAINRATE and the overstress ratio in a curve-fittingprocedure to determine material parameter BVALUE.

b) More than one strainrate (strainratei) and stress-strain curve (scurvei)in the strainrate-fit.The AUI determines the overstress ratio at each strainratei using scurvei. Then the AUI usesthese strainrates and overstress ratios in a curve-fitting procedure to determine both materialparameters TRANSITION-STRAINRATE and BVALUE.

Auxiliary commands





MATERIAL PLASTIC-ORTHOTROPICNAME EA EB EC NUAB NUAC NUBC GAB GAC GBCYIELDAA YIELDBB YIELDCC YIELDAB YIELDAC YIELDBCETAA ETBB ETCC ETAB ETAC ETBC EPLU EPA DENSITYALPHAA ALPHAB ALPHAC TREF OPTION METHODR0 R45 R90 F G H L M N C E0 NN

Defines a nonlinear orthotropic plastic material. This material model may be used with shell,2-D solid and 3-D solid elements.


EA, EB, ECa-, b- and c-direction modulus, respectively. {> 0.0}

NUAB [0.0]a-b strain ratio.

NUAC [0.0]a-c strain ratio.

NUBC [0.0]b-c strain ratio.

GABa-b shear modulus. {> 0.0}

GAC [0.0]a-c shear modulus. GAC=0 is admissible only for 2D solid elements ( EGROUP TWODSOLID ). {≥0.0}

GBC [0.0]b-c shear modulus. GBC=0 is admissible only for 2D solid elements ( EGROUP TWODSOLID ).{≥ 0.0}

YIELDAA, YIELDBB, YIELDCCInitial yield stress for a-, b- and c-direction, respectively. See notes at end of commanddescription.

YIELDABInitial yield stress for ab-plane. See notes at end of command description.

MATERIAL PLASTIC-ORTHOTROPIC



YIELDAC [0.0]Initial yield stress for ac-plane. See notes at end of command description.

YIELDBC [0.0]Initial yield stress for bc-plane. See notes at end of command description.

ETAA [0.0]Strain hardening modulus for a-direction. Used only for OPTION = 2.

ETBB [0.0]Strain hardening modulus for b-direction. Used only for OPTION = 2.

ETCC [0.0]Strain hardening modulus for c-direction. Used only for OPTION = 2.

ETAB [0.0]Strain hardening modulus for ab-plane. Used only for OPTION = 2.

ETAC [0.0]Strain hardening modulus for ac-plane. Used only for OPTION = 2.

ETBC [0.0]Strain hardening modulus for bc-plane. Used only for OPTION = 2.

EPLU [0.0]Universal plastic modulus; ratio of effective plastic stress to effective plastic strain (Hill).Used only for OPTION = 1.

EPA [0.0]Maximum allowable effective plastic strain. This allows for the modeling of material rupture,whereby the stresses are set to zero whenever the effective plastic strain is greater than therupture strain EPA. If EPA is input as 0.0, the rupture condition is not used.


ALPHAA [0.0]Mean coefficient of thermal expansion for a-direction.

ALPHAB [0.0]Mean coefficient of thermal expansion for b-direction.

ALPHAC [0.0]Mean coefficient of thermal expansion for c-direction.




TREF [0.0]Reference temperature for calculation of ALPHAA, ALPHAB and ALPHAC. See the Theoryand Modeling Guide.

OPTION [1]Indicates method to determine plastic moduli:

1 The universal plastic modulus EPLU is used to determine the plastic moduli. Anyinput values for the strain hardening moduli ETAA, ETBB, ETCC, ETAB, ETAC,ETBC are ignored.

2 The moduli EA, EB, EC, GAB, GAC, GBC are used with the strain hardeningmoduli ETAA, ETBB, ETCC, ETAB, ETAC, ETBC to determine the plasticmoduli. Any input value for the universal plastic modulus EPLU is ignored.

3 Constants C, E0 and NN are used to determine the plastic moduli. Any input valuesfor the strain hardening moduli ETAA, ETBB, ETCC, ETAB, ETAC, ETBC,EPLU are ignored.

METHOD [1]Indicates method to determine Hill�s anisotropy parameters f, g, h, l, m, n:

1 Anisotropy parameters are calculated by AUI based on yield stresses. Any inputvalues for R0, R45, R90, f, g, h, l, m, n are ignored.

2 Anisotropy parameters are calculated based on Lankford coefficients R0, R45, R90.Any input values for f, g, h, l, m, n are ignored.

3 Anisotropy parameters are directly defined - f, g, h, l, m, n. Any input values forR0, R45, R90 are ignored.

R0 [1.0]Lankford coefficient for 00 to rolling direction.



F [0.5]Hill's anisotropy parameter f.




G [0.5]Hill's anisotropy parameter g.

H [0.5]Hill's anisotropy parameter h.

L [1.5]Hill's anisotropy parameter l.

M [1.5]Hill's anisotropy parameter m.

N [1.5]Hill's anisotropy parameter n.

C [1.0]

Constant C of analytical stress-strain curve σ ε ε= ⋅ +( )C p

n

0 .

E0 [0.001]

Constant ε0 of analytical stress-strain curve σ ε ε= ⋅ +( )C p

n

0 .

NN [0.1]

Constant n of analytical stress-strain curve σ ε ε= ⋅ +( )C p

n

0 .

Note:

The initial yield stresses YIELDAA, ..., YIELDBC are used as follows:

If METHOD = 1, the initial yield stresses are directly used.

If METHOD = 2 or 3, and OPTION = 1 or 2, the initial yield stresses are only used tocalculate the quantity

σy = √[{(YIELDAA2 + YIELDBB2 + YIELDCC2 )/3 + YIELDAB2 + YIELDAC2 + YIELDBC2}/2]

For other combinations of METHOD and OPTION, the initial yield stresses are not used.

Auxiliary commands




Sec. 7.1 Material modelsMATERIAL SMA

MATERIAL SMA NAME EM EA NUM NUA ALPHAM ALPHAACM CA MS MF AS AF SIGMAR CRETMAX TOLIL DENSITY TREF VTM0

Defines a shape-memory alloy (SMA) material. An SMA material may be used with truss, 2-Dsolid, 3-D solid and isobeam elements.


EMElastic modulus for martensite. {> 0}

EAElastic modulus for austenite.{> 0}

NUM [0.0]Poisson�s ratio for martensite.{0 ≤ NUM < 0.5}

NUA [0.0]Poission�s ratio for austenite.{0 ≤ NUA < 0.5}

ALPHAM [0.0]Mean coefficient of thermal expansion for martensite. {≥ 0.0}

ALPHAA [0.0]Mean coefficient of thermal expansion for austenite.{≥ 0.0}

CMSlope of the martensite transformation conditions. {> 0}

CASlope of the austenite transformation conditions. {> 0}

MSTransformation temperature at the start of martensite. {real}

MFTransformation temperature at the end of martensite. {real}

ASTransformation temperature at the start of austenite. {real}



AFTransformation temperature at the end of austenite. {real}

SIGMAR [0.0]Martensite re-orientation yield property at temperature θ=0. If SIGMAR > 0.0, the martensitere-orientation calculation is performed.{≥ 0.0}

CR [0.0]Slope of the martensite re-orientation yield function.{≥ 0.0}

ETMAXMaximum residual transformation strain.{> 0.0}

TOLIL [1.0E-08]Solution tolerance for effective stress calculation. {> 0.0}


TREF [0]Reference temperature for thermal expansion calculation.

VTM0 [0.0]Initial twinned martensite fraction.{0.0 ≤ VTM0 ≤ 1.0}

MATERIAL SMA


Sec. 7.1 Material modelsMATERIAL SUSSMAN-BATHE

MATERIAL SUSSMAN-BATHENAME SSCURVE SSTYPE RELERROR KAPPA DENSITYTEMPERATURE-DEPENDENCE TREF RUBBER-TABLERUBBER-VISCOELASTIC RUBBER-MULLINS RUBBER-ORTHOTROPIC

straini stressi

Defines a Sussman-Bathe material model, which is an incompressible nonlinear elasticmaterial model for rubber materials. This material model can be used with 2-D solid and 3-Dsolid elements.


SSCURVE [0]Label number of a stress-strain curve defined by command SSCURVE. This defines the stress-strain data points associated with this material model. If SSCURVE is input as 0, then the datalines following the command define the stress-strain data points. Conversely, if SSCURVE isgreater than zero then no data lines are expected.

SSTYPE [ENGINEERING]The type of stress-strain data entered, either in the SSCURVE command or in the data inputlines. {ENGINEERING/TRUE/STRETCH}

ENGINEERING engineering strains, engineering stresses

TRUE true strains, true stresses

STRETCH stretches, engineering stresses

RELERROR [0.01]The relative error used to determine the number of splines. This value must be greater than0.0.

KAPPA [0.0]The bulk modulus, used for 3-D, plane strain and axisymmetric elements. If the bulk modulusis 0.0, then the AUI computes the bulk modulus using a Poisson�s ratio of 0.499.







FULL The material properties are temperature dependent. Parameters SSCURVE to KAPPA,and RUBBER-VISCOELASTIC to RUBBER-ORTHOTROPIC of this command areignored. No data input lines are expected.





TEMPERATURE-DEPENDENCE = TRS :A rubber-table of type TRS must be entered. This rubber-table is atable of temperatures and corresponding coefficients of thermal expansion.

TEMPERATURE-DEPENDENCE = FULL :A rubber-table of type Sussman-Bathe must be entered. This rubber-table is a table oftemperatures and corresponding material properties.

RUBBER-VISCOELASTIC [0]If RUBBER-VISCOELASTIC is zero, no viscoelastic effects are included.If RUBBER-VISCOELASTIC is non-zero, viscoelastic effects are included, using the data setfrom the corresponding RUBBER-VISCOELASTIC command.This parameter is not used when TEMPERATURE-DEPENDENCE = FULL.

RUBBER-MULLINS [0]If RUBBER-MULLINS is zero, no Mullins effects are included.

MATERIAL SUSSMAN-BATHE



If RUBBER-MULLINS is nonzero, Mullins effects are included, using the data set from thecorresponding RUBBER-MULLINS command.This parameter is not used when TEMPERATURE-DEPENDENCE = FULL.

RUBBER-ORTHOTROPIC [0]If RUBBER-ORTHOTROPIC is zero, no orthotropic effects are included.If RUBBER-ORTHOTROPIC is non-zero, orthotropic effects are included, using the data setfrom the corresponding RUBBER-ORTHOTROPIC command.This parameter is not used when TEMPERATURE-DEPENDENCE = FULL.

straini, stressiThe strain and stress at data point i. The strain and stress are interpreted according to theSSTYPE parameter.

The (strain,stress) data points are assumed to correspond to a uniaxial tension/compressionconditions.

Auxiliary commands


MATERIAL SUSSMAN-BATHE






MATERIAL THERMO-ISOTROPIC NAME TREF DENSITY

thetai Ei nui alphai

Defines a nonlinear isotropic thermo-elastic material model which considers the variation ofmaterial properties with temperature. Linear interpolation is performed to determine values atintermediate temperatures. This material model may be used with truss, 2-D solid, 3-D solid,isobeam, shell and pipe elements.


TREF [0.0]The reference temperature for expansion coefficient calculation. See the Theory and Model-ing Guide.


thetaiTemperature at data point �i�. (i ≤ 16)

EiYoung�s Modulus at temperature �thetai�. (i ≤ 16)

nuiPoisson�s ratio at temperature �thetai�. (i ≤ 16)

alphaiMean coefficient of thermal expansion at temperature �thetai�. (i ≤ 16)

Note: The material properties are automatically sorted in order of increasingtemperature. If the same temperature is given several times, only the last givenvalue is used.

Auxiliary commands


MATERIAL THERMO-ISOTROPIC



MATERIAL THERMO-ORTHOTROPIC NAME TREF DENSITY

thetai Eai Ebi Eci nuabi nuaci nubci Gabi Gaci Gbci alphaai alphabi alphaci

Defines a nonlinear orthotropic thermo-elastic material model which considers the variation ofmaterial properties with temperature. Linear interpolation is performed to determine values atintermediate temperatures. This material model may be used with shell, 2-D solid and 3-Dsolid elements.





Eaia-direction modulus at temperature �thetai�. (i ≤ 16)

Ebib-direction modulus at temperature �thetai�. (i ≤ 16)

Ecic-direction modulus at temperature �thetai�. (i ≤ 16)

nuabia-b strain ratio at temperature �thetai�. (i ≤ 16)

nuacia-c strain ratio at temperature �thetai�. (i ≤ 16)

nubcib-c strain ratio at temperature �thetai�. (i ≤ 16)

Gabia-b shear modulus at temperature �thetai�. (i ≤ 16)

MATERIAL THERMO-ORTHOTROPIC



Gacia-c shear modulus at temperature �thetai�. (i ≤ 16)

Gbcib-c shear modulus at temperature �thetai�. (i ≤ 16)

alphaaiMean coefficient of thermal expansion in a-direction at temperature �thetai�.

alphabiMean coefficient of thermal expansion in b-direction at temperature �thetai�.

alphaciMean coefficient of thermal expansion in c-direction at temperature �thetai�.

Note: The material properties are automatically sorted in order of increasingtemperature. If the same temperature is given several times, only the last given

values are used.

Auxiliary commands


MATERIAL THERMO-ORTHOTROPIC



MATERIAL THERMO-PLASTIC NAME HARDENING TREF TOLILDENSITY


Defines a nonlinear thermo-plastic material. This material model may be used with truss, 2-Dsolid, 3-D solid, isobeam, shell and pipe elements.






TOLIL [1.0E-10]Solution tolerance. See Theory and Modeling Guide.







MATERIAL THERMO-PLASTIC





Note: The material properties are automatically sorted in order of increasingtemperature. If the same temperature is given several times, only the last given

values are used.

Auxiliary commands


MATERIAL THERMO-PLASTIC



MATERIAL USER-SUPPLIED NAME INTEG NSUBD TREF DENSITYLENGTH1 LENGTH2 OPTION NCTI NSCP NCTDCTI1 ... CTI99 SCP1 ... SCP99 LENGTH3 LENGTH4AUTOLEN NONSYM DENSITY

tempi alphai ctd1i ctd2i ... CtdNCTDi

Defines a user-supplied material for use with ADINA, with options for piezoelectric orconsolidation analyses (requiring interaction with ADINA-T). This material model may beused with 2-D solid and 3-D solid elements.


INTEG [FORWARD]Stress integration scheme. {FORWARD/BACKWARD}

FORWARD Forward integration scheme.

BACKWARD Backward integration scheme.

NSUBD [10]Number of subdivisions of strain increments used in the integration of stresses. If INTEG =BACKWARD, NSUBD = 1 is always used regardless of this input. { > 0 }

TREF [0.0]Reference temperature for thermal expansion calculation. See the Theory and ModelingGuide.


LENGTH1 [60]Length of working real array for storing/retrieving history dependent variables. See theTheory and Modeling Guide for details.

LENGTH2 [2]Length of working integer array for storing/retrieving history dependent variables. SeeTheory and Modeling Guide for details.

OPTION [NONE]Special analysis options. {NONE/PIEZOELECTRIC/CONSOLIDATION/LINEAR}




NONE - No special analysis option

PIEZOELECTRIC - Piezoelectric analysis (involving interaction with ADINA-T)

CONSOLIDATION - Consolidation analysis.

LINEAR - Linear material model option

NCTINumber of active material property constants. {0 ≤ NCTI ≤ 99}

NSCPNumber of active solution control parameters. {0 ≤ NSCP ≤ 99}

NCTD [0]Number of active temperature dependent material properties. {0 ≤ NCTD ≤ 98}

CTI1 ... CTI99 [0.0]User defined material constants.

SCP1 ... SCP99 [0.0]User defined solution control parameters.

LENGTH3 [0]Number of parameters from the real working array to write to porthole file.{0 ≤ LENGTH3 ≤ LENGTH1}

LENGTH4 [0]Number of parameters from the integer working array to write to porthole file.{0 ≤ LENGTH4 ≤ LENGTH2}

AUTOLEN [0]Flag for setting the size of working and output arrays LENGTH1 - LENGTH4. {0 / 1}

0 Manually set via LENGTH1 - LENGTH4 variables

1 Automatically set by call to user coded material subroutine with KEY=0

NONSYM [NO]Flag for symmetry of stiffness matrix generated by this user-supplied material. {NO/YES}

Note: Nonsymmetric stiffness matrix can only be activated when a non-symmetric solver isselected.




DENSITY [1.0]Mass density. {≥ 0.0}

tempiTemperature at data point �i�.

alphaiMean coefficient of the thermal expansion at temperature �tempi�.

ctdJivalue of temperature-dependent material property �J� at temperature �tempi�.

Note: The material properties are automatically sorted in order of increasing temperature.If the same temperature is given several times, only the last given values are used.

Auxiliary commands








MATERIAL VISCOELASTIC NAME NSUBD TREF C1 C2 ALPHA G-FUNCTIONK-FUNCTION DENSITY SHIFT

thetai alphai

Defines a viscoelastic material with time dependent and temperature dependent materialproperties. This material model may be used with truss, 2-D solid, 3-D solid and shell ele-ments.

NAME [(current highest material label number) + 1]Label number of the material to be defined. If the label number of an existing material is given,the existing material definition is overwritten.

NSUBD [10]Number of subdivisions of strain increments used in the integration of stresses.

TREF [0.0]Reference temperature used by the WLF (Williams-Landell-Ferry) equation for temperature-time shift calculation.

C1 [0.0]C2 [0.0]Material constants used by the WLF (Williams-Landell-Ferry) equation or the Arrheniusequation for temperature-time shift calculation.

ALPHA [0.0]Constant mean coefficient of thermal expansion. If no temperature table is defined, alpha isassumed constant.

G-FUNCTIONLabel number of a table, defined by command FTABLE, containing a series of shear moduliand decay coefficients to represent the shear modulus relaxation function.

K-FUNCTIONLabel number of a table, defined by command FTABLE, containing a series of bulk moduliand decay coefficients to represent the bulk modulus relaxation function.


SHIFT [WLF]Specifies the time-temperature superposition law. {WLF/ARRHENIUS}

MATERIAL VISCOELASTIC



WLF Williams-Landell-Ferry equation

ARRHENIUS Arrhenius equation

The following data lines are used only when the coefficient of thermal expansion is tempera-ture-dependent:


alphaiMean coefficient of thermal expansion at temperature �thetai�. (i ≤ 16)

Auxiliary commands


MATERIAL VISCOELASTIC



TMC-MATERIAL ISOTROPIC NAME K C JOULE-HEAT ELECTRIC-K DENSITY

Defines a constant, isotropic, conductivity and constant specific heat material.

This command is used in ADINA thermal coupling for TRUSS, 2D/3D Solid, BEAM,ISOBEAM, PIPE elements only.


K [0.0]Thermal conductivity. {≥ 0.0}

C [0.0]

Heat capacity per unit volume. {≥ 0.0}

JOULE-HEAT [NO]Indicates whether this material is used for Joule heat analysis. { YES/NO }

ELECTRIC-K [0.0]Constant electrical conductivity (in chosen units, e.g., Siemens/m).{ ≥ 0.0 }


Auxiliary commands

LIST TMC-MATERIAL FIRST LASTDELETE TMC-MATERIAL FIRST LAST

TMC-MATERIAL ISOTROPIC


Sec. 7.1 Material modelsTMC-MATERIAL ORTHOTROPIC

TMC-MATERIAL ORTHOTROPIC NAME KA KB KC C JOULE-HEAT EKAEKB EKC DENSITY

Defines a constant, orthotropic, thermal conductivity and constant specific heat material.



KA [0.0]

Thermal conductivity in a-direction. {≥ 0.0}

KB [0.0]

Thermal conductivity in b-direction. {≥ 0.0}

KC [0.0]

Thermal conductivity in c-direction. {≥ 0.0}

C [0.0]


JOULE-HEAT [NO]Indicates whether this material is used for Joule heat analysis. {YES/NO}

EKA [0.0]EKB [0.0]EKC [0.0]Electrical conductivity in the a-, b- and c-directions. (units: electrical conductance/length,e.g., Siemens/m) {≥ 0.0}


Auxiliary commands




TMC-MATERIAL TEMPDEP-K NAME C JOULE-HEAT DENSITY

thetai ki electric-ki

Defines a material with temperature dependent thermal conductivity and constant specificheat.



C [0.0]





kiThermal conductivity at temperature thetai.

electric-kiElectrical conductivity at temperature thetai.

Note: The input data is automatically sorted in order of increasing temperature. If the sametemperature is given several times, only the last given value is used.

Auxiliary commands


TMC-MATERIAL TEMPDEP-K


Sec. 7.1 Material modelsTMC-MATERIAL TEMPDEP-C-ISOTROPIC

TMC-MATERIAL TEMPDEP-C-ISOTROPIC NAME K DENSITY

thetai ci

Defines a material with temperature dependent specific heat and constant, isotropic, thermalconductivity.



K [0.0]

Thermal conductivity. {≥ 0.0}



ciHeat capacity per unit volume at temperature thetai.


Auxiliary commands




TMC-MATERIAL TEMPDEP-C-ORTHOTROPIC NAME KA KB KCCONDUCTIVITY DENSITY

thetai ci kai kbi kci

Defines a material with temperature dependent specific heat and constant, orthotropic thermalconductivity.



KA [0.0]Thermal conductivity in a-direction. {≥ 0.0}

KB [0.0]

Thermal conductivity in b-direction. {≥ 0.0}

KC [0.0]Thermal conductivity in c-direction. {0.0}

CONDUCTIVITY [CONSTANT]Flags whether conductivity is constant or input in table. {CONSTANT/TABLE}




kai [value of parameter KA]Thermal conductivity in a-direction {≥ 0.0}

kbi [value of parameter KB]Thermal conductivity in b-direction {≥ 0.0}

TMC-MATERIAL TEMPDEP-C-ORTHOTROPIC



kci [value of parameter KC]Thermal conductivity in c-direction {≥ 0.0}


Auxiliary commands


TMC-MATERIAL TEMPDEP-C-ORTHOTROPIC



TMC-MATERIAL TEMPDEP-C-K NAME JOULE-HEAT DENSITY

thetai ki ci electric-ki

Defines a material with temperature dependent specific heat and thermal conductivity.






kiThermal conductivity at temperature thetai.


electric-kiElectrical conductivity at temperature thetai.


Auxiliary commands


TMC-MATERIAL TEMPDEP-C-K


Sec. 7.1 Material modelsTMC-MATERIAL TIMEDEP-K

TMC-MATERIAL TIMEDEP-K NAME C DENSITY

timei ki

Defines a material with time dependent thermal conductivity and constant specific heat.



C [0.0]




kiConductivity at timei.

Note: The input data is automatically sorted in order of increasing time. If the same time isgiven several times, only the last given value is used.

Auxiliary commands




CURVE-FITTING NAME ORDER TENSION-CURVE SHEAR-CURVEEQUIBIAXIAL-CURVE WEIGHTING CURVE-TYPEMETHOD NSINGULAR MAX-SINGV MIN-SINGV ECHO

Defines a fitting curve for hyperelastic material models.

A least squares curve fitting technique is employed to determine the parameters for aMooney-Rivlin, Ogden, Arruda-Boyce or hyper-foam material model from experimentalstress versus strain (or stretch) data. The data can be input for any of three test cases:(i) simple tension,(ii) pure shear, or(iii) equibiaxial tension.

A single test or combination of any two, or all three, can be supplied. The accuracy of themodel curve thus fitted depends on the number of data points, and the desired approximationorder of the model.

The total number of data points, from all three test cases, is subject to a minimum, as follows:� 2,5,9 for a Mooney-Rivlin model of input order 1, 2, 3 respectively;� the input order for the Ogden material;� 2 for the Arruda-Boyce material; and� the input order for the hyper-foam material.

NAME [(current highest curve-fitting label number) + 1]Label number of the curve-fitting to be defined. If the label number of an existing curve-fittingis given, then the previous curve-fitting definition is overwritten. This curve number can beassigned to the Mooney-Rivlin, Ogden, Arruda-Boyce or hyper-foam material model wherematerial constants for the model are evaluated form the input curves (see Notes at the end ofthis command).

ORDER [3]Approximation order. Allowed values are:� Mooney-Rivlin material: 1 to 3� Ogden material: 1 to 9� Arruda-Boyce material: 2� Hyper-foam material: 1 to 9

TENSION-CURVE [0]Indicates the label number of a (stress, strain) data curve, which provides data for the simpletension test case. This data curve is defined by command SSCURVE. A value of 0 indicatesno simple tension data is supplied. The abscissae may be interpreted as strain or stretch as

CURVE-FITTING



indicated by parameter CURVE-TYPE.

SHEAR-CURVE [0]Similar to TENSION-CURVE, except that this curve provides data for the pure shear test case.

EQUIBIAXIAL-CURVE [0]Similar to TENSION-CURVE, except that this curve provides data for the equilbiaxial tensiontest case.

WEIGHTING [NO]Specifies whether the least squares fitting scheme utilises weighted data intervals or not ---their use may provide a better fit for data with very irregular spacing of the strain (or stretch)abscissae. See the Theory and Modeling Guide for further details. Input values are YES orNO.

CURVE-TYPE [STRAIN]Indicates the type of input curve data given by parameters TENSION-CURVE, SHEAR-CURVE, and EQUIBIAXIAL-CURVE. The option is given for the data abscissae to be eitherprincipal (engineering) strain, or principal stretch (= deformed length /undeformed length).The ordinate values in either case are values of nominal stress (= force / unit undeformedarea). {STRAIN/STRETCH}

STRAIN -input principal engineering strain dataSTRETCH - input principal stretch data

METHOD [SVD]Specifies the least squares matrix equation solution method. Use of Gaussian elimination maywell result in model constants which alternate in sign and have very high magnitude. This isdue to the presence of near-singular terms in the least squares system. The "singular valuedecomposition" method attempts to remove these terms during solution, yielding morereasonable model constants without affecting the overall quality of the least squares fit. Thenumber of near-singular terms to be removed may be controlled by parameters MAX-SINGV,MIN-SINGV. Near-singular terms are removed by default until a monotone increasingsolution is obtained for all test cases.

This parameter is only used for the Mooney-Rivlin and Ogden material models.

SVD - The singular value decomposition methodGAUSS - Standard Gaussian elimination technique

NSINGULAR [AUTOMATIC]Indicates whether the number of near-singular terms to be removed in the singular valuedecomposition solution method is controlled automatically by the program, or is to be

CURVE-FITTING



user-specified via parameters MAX-SINGV, MIN-SINGV. This parameter is only applicablewhen METHOD=SVD.

AUTOMATIC - the program controls the number of near-singular terms to be removed by the singular value decomposition solution method.

CUSTOM - the user indicates the maximum and minimum number of near-singular terms to be removed.

MAX-SINGV [0]If NSINGULAR=CUSTOM, this parameter indicates the maximum number of near-singularterms which are permitted to be removed during the search for a monotone increasing set ofresult curves.

MAX-SINGV may range from 0 (for which the resulting solution is identical to that obtainedby Gaussian elimination) to the total desired number of model constants, as indicated byparameter ORDER.

This parameter is only applicable when METHOD=SVD.

MIN-SINGV [0]If NSINGULAR=CUSTOM, this parameter indicates the minimum number of near-singularterms which will be removed by the singular value decomposition method, i.e. the SVDalgorithm will remove at least MIN-SINGV terms even if a monotone solution set wasobtained with fewer terms removed.

This parameter is only applicable when METHOD=SVD.

ECHO [ALL]Specifies the level of information reported by the command:

NONE - the command behaves silently, except for a completion messageMODEL - the resulting material model constants are reportedALL - as well as model constants, curve fitting statistics and comparison tables

of input and fitted stress values for the input strain/stretch points is reported.

Notes:

1 For a discussion on the singular value decomposition method and its application to theleast squares curve fitting algorithm, please consult the Theory and Modeling Guide.

2 It is unwise to apply this command to a small set of data within a narrow range of strains/stretches. If possible, some values of strain/stretch should be input for compression, and

CURVE-FITTING



it is recommended that the resulting curve-fitting behavior always be checked with theMATERIALSHOW command.

3 The respective constants for each material model calculated from the input data curvesare as follows (see Section 3.8.5 of the Theory and Modeling Guide Volume I for more details):

Mooney-Rivlin:ORDER Constants 1 C1, C2 2 C1 - C5 3 C1 - C9

Ogden: The constants µi and αi are calculated from i = 1 to ORDER.

Arruda-Boyce: ORDER = 2 only, with constants C1 to C5.

Hyper-foam: The constants µi, αi and βi are calculated from i = 1 to ORDER.

CURVE-FITTING


Chap. 7 Model definition CURVE-FITTING




VISCOELASTIC-CONSTANTS NAME NPOINTS BETA1 BETA2 BETA3 BETA4BETA5 TAU1 TAU2 TAU3 TAU4 TAU5 ETA1 ETA2ETA3 ETA4 ETA5

Defines viscoelastic contants for a viscoelastic material model.

NAME [(current highest viscoelastic-constants labelnumber) + 1]

Label number of the viscoelastic-contants to be defined. If the label number of an existingviscoelastic-contants is given, then the previous definition is overwritten.

NPOINTS [2]Number of constants. {1<=NPOINTS<=5}

BETA1 [1.0]BETA2 [1.0]BETA3 [0.0]BETA4 [0.0]BETA5 [0.0]Free energy factors. {BETA>=0.0}

TAU1 [30.0]TAU2 [20.0]TAU3 [0.0]TAU4 [0.0]TAU5 [0.0]Relaxation time. {TAU>0.0}

ETA1 [4.002676E6]ETA2 [4.002676E6]ETA3 [0.0]ETA4 [0.0]ETA5 [0.0]{ETA>=0.0}

Auxiliary commands

LIST VISCOELASTIC-CONSTANTS FIRST LASTDELETE VISCOELASTIC-CONSTANTS FIRST LAST

VISCOELASTIC-CONSTANTS


Chap. 7 Model definition PHI-MODEL-COMPLETION

PHI-MODEL-COMPLETION CLOSE-TOL XTOL YTOL ZTOL CLOSE-NODE PHI-ANGLE NORMAL-ANGLE

This command controls certain parameters used during the phi model completion phase ofconstructing the data file. The phi model completion phase is performed only when there arepotential-based fluid elements in the model.

CLOSE-TOL [AUTOMATIC]This parameter controls which tolerances are used during when searching for structuralnodes coincident with potential-based fluid nodes.

AUTOMATIC The tolerances from the TOLERANCES GEOMETRIC command areused. The coincidence checks are the same as are used during meshgeneration.

CUSTOM The tolerances XTOL, YTOL, ZTOL of this command are used.

XTOL [0.0]YTOL [0.0]ZTOL [0.0]Tolerances used for coincident node checking during phi model completion, used only whenCLOSE-TOL = CUSTOM. Note that XTOL, YTOL, ZTOL are absolute tolerances. To bespecific, a structural node with coordinates (XS,YS,ZS) are coincident with a fluid node withcoordinates (XF,YF,ZF) when

XF-XTOL ≤ XS ≤ XF+XTOL YF-YTOL ≤ YS ≤ YF+YTOL ZF-ZTOL ≤ ZS ≤ ZF+ZTOL

CLOSE-NODE [CLOSEST]This parameter controls which node is taken if two or more nodes are coincident.

HIGHEST The node with the highest number is taken.

CLOSEST The closest node is taken.

PHI-ANGLE [30]This parameter, in degrees, is used in constructing the boundary conditions for a node on afree surface that is adjacent to the structure. When the angle between two adjacent faces ofthe structural boundary is greater than PHI-ANGLE, the AUI treats the intersection of thefaces as a sharp corner. When the angle between two adjacent faces of the structural bound-ary is less than or equal to PHI-ANGLE, the AUI considers the faces to approximate smoothboundary.

NORMAL-ANGLE [80]This parameter, in degrees, is the maximum angle between the unmodified and modified freenormals on a fluid free surface.



PLCYCL-ISOTROPIC BILINEAR NAME YIELD EP

Sets up a PLCYCL-ISOTROPIC definition of type bilinear. This definition can be used in theMATERIAL PLASTIC-CYCLIC command.

NAME [(current highest plcycl-isotropic label number) + 1]Label number of the plcycl-isotropic definition. If the label number of an existing plcycl-isotropic data set is defined, then the previous definition is overwritten.

YIELDYield stress (radius of yield surface).

EP [0.0]Hardening modulus, giving the change in yield stress with respect to the accumulatedeffective plastic strain.

Auxiliary commands

LIST PLCYCL-ISOTROPIC FIRST LASTDELETE PLCYCL-ISOTROPIC FIRST LAST

PLCYCL-ISOTROPIC BILINEAR



PLCYCL-ISOTROPIC MULTILINEAR NAME

aepsi stress-radiusi

Sets up a PLCYCL-ISOTROPIC definition of type multilinear. This definition can be used inthe MATERIAL PLASTIC-CYCLIC command.


aepsiAccumulated effective plastic strain, interpreted as a logarithmic strain in large strain analy-sis.

stress-radiusiAssociated radius of yield surface (yield stress).

During the analysis, if the accumulated effective plastic strain exceeds the largest value ofaepsi, then ADINA issues an error message and either stops or cuts back the time step (if theATS method is used).

Auxiliary commands


PLCYCL-ISOTROPIC MULTILINEAR



PLCYCL-ISOTROPIC EXPONENTIAL NAME YIELD Q B

Sets up a PLCYCL-ISOTROPIC definition of type exponential. This definition can be used inthe MATERIAL PLASTIC-CYCLIC command.


YIELDYield stress (radius of yield surface). This parameter must be entered.

Q [0.0]B [0.0]Parameters giving the change in yield stress with respect to the accumulated effective plasticstrain, see the Theory and Modeling Guide. If Q is positive, the material cyclically hardens,if Q is negative, the material cyclically softens. Q and B default to 0.0.

Auxiliary commands


PLCYCL-ISOTROPIC EXPONENTIAL



PLCYCL-ISOTROPIC MEMORY- EXPONENTIAL NAME YIELD Q0 QM MU B ETA

Sets up a PLCYCL-ISOTROPIC definition of type memory-exponential. This definition can beused in the MATERIAL PLASTIC-CYCLIC command.

The strain memory surface algorithm of Lemaitre and Chaboche is used, see the Theory andModeling Guide.


YIELDYield stress (radius of yield surface). This parameter must be entered.

Q0 [0.0]QM [0.0]MU [0.0]B [0.0]ETA [0.5]Parameters giving the change in yield surface radius with respect to the accumulated effectiveplastic strain and the strain memory, see the Theory and Modeling Guide. All of theseparameters, except for ETA, default to 0.0; ETA defaults to 0.5.

Auxiliary commands


PLCYCL-ISOTROPIC MEMORY-EXPONENTIAL



PLCYCL-KINEMATIC ARMSTRONG-FREDRICK NAME

hi zetai

Sets up a PLCYCL-KINEMATIC definition of type Armstrong-Fredrick. This definition can beused in the MATERIAL PLASTIC-CYCLIC command.

NAME [(current highest plcycl-kinematic label number) + 1]Label number of the plcycl-kinematic definition. If the label number of an existing plcycl-kinematic data set is defined, then the previous definition is overwritten.

hiLinear kinematic hardening constant.

zetai [0.0]Nonlinear kinematic hardening constant. It is allowed to set zetai=0.0.

Note:

When zetai=0.0, then hi is equal to the plastic hardening modulus Ep.

It is allowed to enter several values of hi and zetai, each with a different value of zetai.

Auxiliary commands

LIST PLCYCL-KINEMATIC FIRST LASTDELETE PLCYCL-KINEMATIC FIRST LAST

PLCYCL-KINEMATIC ARMSTRONG-FREDRICK



PLCYCL-RUPTURE AEPS NAME VALUE

Sets up a PLCYCL-RUPTURE definition of type AEPS (accumulated effective plastic strain).This definition can be used in the MATERIAL PLASTIC-CYCLIC command.

NAME [(current highest plcycl-rupture label number) + 1]Label number of the plcycl-rupture definition. If the label number of an existing plcycl-rupturedata set is defined, then the previous definition is overwritten.

VALUEThe value of accumulated effective plastic strain at which the material ruptures. It is allowedto enter nothing for this value, then the material will not rupture.

Auxiliary commands

LIST PLCYCL-RUPTURE FIRST LASTDELETE PLCYCL-RUPTURE FIRST LAST

PLCYCL-RUPTURE AEPS



RUBBER-TABLE MOONEY-RIVLIN NAME

thetai alphai c1i c2i c3i c4i c5i c6i c7i c8i c9i d1i d2i kappai fitting-curveirubber-viscoelastici rubber-mullinsi rubber-orthotropici

Defines a rubber-table data set of type Mooney-Rivlin. This data set can be used to describethe temperature dependence of the Mooney-Rivlin material constants in the MATERIALMOONEY-RIVLIN command.

NAME [(current highest rubber-table label number) + 1]Label number of the rubber-table data set to define. If the label number of an existing rubber-table data set is defined, then the previous definition is overwritten.

thetaiThe temperature corresponding to the material properties entered in this data input line.

alphai [0.0]The coefficient of thermal expansion.

c1i ... c9i [0.0]d1i ... d2i [0.0]kappai [0.0]The material properties.

fitting-curvei [0]If fitting-curvei is zero, no fitting curve is used.If fitting-curvei is nonzero, curve-fitting data from the CURVE-FITTING command is used tocompute the material properties, and c1i to d2i are ignored.

rubber-viscoelastici [0]If rubber-viscoelastici is zero, no viscoelastic effects are included.If rubber-viscoelastici is non-zero, viscoelastic effects are included, using the data set fromthe corresponding RUBBER-VISCOELASTIC command.

rubber-mullinsi [0]If rubber-mullinsi is zero, no Mullins effects are included.If rubber-mullinsi is non-zero, Mullins effects are included, using the data set from thecorresponding RUBBER-MULLINS command.

rubber-orthotropici [0]If rubber-orthotropici is zero, no orthotropic effects are included.If rubber-orthotropici is non-zero, orthotropic effects are included, using the data set from thecorresponding RUBBER-ORTHOTROPIC command.

RUBBER-TABLE MOONEY-RIVLIN



Auxiliary commands

LIST RUBBER-TABLE FIRST LASTDELETE RUBBER-TABLE FIRST LAST

RUBBER-TABLE MOONEY RIVLIN



RUBBER-TABLE OGDEN NAME

thetai alphai mu1i alpha1i mu2i alpha2i mu3i alpha3i mu4i alpha4imu5i alpha5i mu6i alpha6i mu7i alpha7i mu8i alpha8i mu9i alpha9ikappai fitting-curvei rubber-viscoelastici rubber-mullinsi rubber-orthotropici

Defines a rubber-table data set of type Ogden. This data set can be used to describe thetemperature dependence of the Ogden material constants in the MATERIAL OGDEN com-mand.




mu1i ... mu9i [0.0]alpha1i ... alpha9i [0.0]kappai [0.0]The material properties.

fittting-curvei [0]If fittting-curvei is zero, no fitting curve is used.If fittting-curvei is nonzero, curve-fitting data from the CURVE-FITTING command is used tocompute the material properties, and mu1i to alpha9i are ignored.




RUBBER-TABLE OGDEN



Auxiliary commands


RUBBER-TABLE OGDEN


Sec. 7.1 Material modelsRUBBER-TABLE ARRUDA-BOYCE

RUBBER-TABLE ARRUDA-BOYCE NAME

thetai alphai mui lambdai kappai fitting-curvei rubber-viscoelasticirubber-mullinsi rubber-orthotropici

Defines a rubber-table data set of type Arruda-Boyce. This data set can be used to describethe temperature dependence of the Arruda-Boyce material constants in the MATERIALARRUDA-BOYCE command.




mui [0.0]lambdai [0.0]kappai [0.0]The material properties.

fittting-curvei [0]If fittting-curvei is zero, no fitting curve is used.If fittting-curvei is nonzero, curve-fitting data from the CURVE-FITTING command is used tocompute the material properties, and mui , lambdai are ignored.






Auxiliary commands


RUBBER-TABLE ARRUDA-BOYCE



RUBBER-TABLE HYPER-FOAM NAME

thetai alphai mu1i alpha1i beta1i mu2i alpha2i beta2i mu3i alpha3i beta3imu4i alpha4i beta4i mu5i alpha5i beta5i mu6i alpha6i beta6imu7i alpha7i beta7i mu8i alpha8i beta8i mu9i alpha9i beta9ifitting-curvei rubber-viscoelastici rubber-mullinsi rubber-orthotropici

Defines a rubber-table data set of type hyper-foam. This data set can be used to describe thetemperature dependence of the hyper-foam material constants in the MATERIAL HYPER-FOAM command.




mu1i ... betai [0.0]The material properties.

fittting-curvei [0]If fittting-curvei is zero, no fitting curve is used.If fittting-curvei is nonzero, curve-fitting data from the CURVE-FITTING command is used tocompute the material properties, and mu1i to alpha9i are ignored.




RUBBER-TABLE HYPER-FOAM



Auxiliary commands


RUBBER-TABLE HYPER-FOAM


Sec. 7.1 Material modelsRUBBER-TABLE SUSSMAN-BATHE

RUBBER-TABLE SUSSMAN-BATHE NAME

thetai alphai sscurvei sstypei relerrori kappai rubber-viscoelasticirubber-mullinsi rubber-orthotropici

Defines a rubber-table data set of type Sussman-Bathe. This data set can be used to describethe temperature dependence of the Sussman-Bathe material model in the MATERIALSUSSMAN-BATHE command.




sscurveiThe uniaxial tension/compression stress-strain curve for this temperature, defined by theSSCURVE command.

sstypei [ENGINEERING]The interpretation of the stress-strain data. {ENGINEERING/TRUE/STRETCH}

ENGINEERING engineering strains, engineering stresses

TRUE true strains, true stresses

STRETCH stretches, engineering stresses

relerrori [0.01]The relative error, used to determine the number of splines for thistemperature. relerrori cannot equal 0.0.

kappai [0.0]The bulk modulus, used for 3-D, plane strain and axisymmetric elements.If kappai = 0.0, then the AUI computes the bulk modulus based on a Poisson�s ratio of 0.499.



Chap. 7 Model definition RUBBER-TABLE SUSSMAN-BATHE





RUBBER-TABLE TRS NAME

thetai alphai

Defines a rubber-table data set of type TRS. This data set can be used to specify the coeffi-cients of thermal expansion for the MATERIAL MOONEY-RIVLIN, MATERIAL OGDEN,MATERIAL ARRUDA-BOYCE and MATERIAL HYPER-FOAM materials, when the TRStemperature dependence option is used.




Auxiliary commands


RUBBER-TABLE TRS


Chap. 7 Model definition RUBBER-TABLE TRS




RUBBER-MULLINS OGDEN-ROXBURGH NAME R M GENERATION_FACTOR

Defines a data set of type rubber-Mullins, subtype Ogden-Roxburgh. This data set can bereferenced by the MATERIAL MOONEY-RIVLIN, MATERIAL OGDEN, MATERIALARRUDA-BOYCE and MATERIAL HYPER-FOAM commands to add the Mullins effect toany of these materials.

NAME [current highest rubber-mullins label number + 1]Label number of the rubber-Mullins data set to define. If the label number of an existingrubber-Mullins data set is defined, then the previous definition is overwritten.

R [0.0]M [0.0]The material constants of the Ogden-Roxburgh model for the Mullins effect, see the ADINATheory and Modeling Guide.

GENERATION_FACTOR [0.0]The fraction of energy dissipated by the Mullins effect model that is considered as heatgeneration. For example, if GENERATION_FACTOR = 1.0, then all energy dissipated by theMullins effect model is considered as heat generation. Heat generation can cause heating ina TMC (thermo-mechanical coupling) analysis.

Auxiliary commands:

LIST RUBBER-MULLINS FIRST LAST DELETE RUBBER-MULLINS FIRST LAST

RUBBER-MULLINS OGDEN-ROXBURGH




RUBBER-MULLINS OGDEN-ROXBURGH



RUBBER-VISCOELASTIC HOLZAPFEL NAME SHIFT C1 C2

betai taui generation_factori usagei

Defines a data set of type rubber-viscoelastic, subtype Holzapfel. This data set can bereferenced by the MATERIAL MOONEY-RIVLIN, MATERIAL OGDEN, MATERIALARRUDA-BOYCE and MATERIAL HYPER-FOAM commands to add the viscoelastic effectto any of these materials.

See the ADINA Theory and Modeling Guide for the meanings of the material parameters.

NAME [current highest rubber-viscoelastic label number + 1]Label number of the rubber-viscoelastic data set to define. If the label number of an existingrubber-viscoelastic data set is defined, then the previous definition is overwritten.

SHIFT [NONE]Specifies the time-temperature superposition shift law. {NONE/WLF/ARRHENIUS}

NONE Time-temperature superposition is not used.

WLF The WLF (Williams-Landel-Ferry) shift function is used for the time-temperature superposition.

ARRHENIUS The Arrhenius shift function is used for the time-temperature superposi-tion.

C1 [0.0]C2 [0.0]The material constants for the WLF or Arrhenius shift functions.

betai [0.0]Beta for chain (i) of the viscoelastic model.

taui [0.0]Tau for chain (i) of the viscoelastic model. Tau must be greater than 0.

generation_factori [0.0]The heat generation factor (fraction of dissipation energy convered into heat generation). Ifgeneration_factori = 0, the dissipation is not calculated and there is no heat generation.

usagei [DEVIATORIC]The usage of the chain. {COMBINED/DEVIATORIC/VOLUMETRIC/AORTHO/BORTHO/CORTHO}

RUBBER-VISCOELASTIC HOLZAPFEL



COMBINED The chain is based on the total strain energy.

DEVIATORIC The chain is based on the deviatoric strain energy.

VOLUMETRIC The chain is based on the volumetric strain energy.

AORTHO The chain is based on the A direction orthotropic strain energy.

BORTHO The chain is based on the B direction orthotropic strain energy.

CORTHO The chain is based on the C direction orthotropic strain energy(not supported in this version)

Auxiliary commands

LIST RUBBER-VISCOELASTIC FIRST LASTDELETE RUBBER-VISCOELASTIC FIRST LAST

RUBBER-VISCOELASTIC HOLZAPFEL



RUBBER-ORTHOTROPIC HOLZAPFEL NAME BETAA BETAB K1 K2COMPRESSION

Defines a data set of type rubber-orthotropic, subtype Holzapfel. This data set can bereferenced by the MATERIAL MOONEY-RIVLIN, MATERIAL OGDEN, MATERIALARRUDA-BOYCE and MATERIAL HYPER-FOAM commands to add the orthotropic effect toany of these materials.

See the ADINA Theory and Modeling Guide for the meanings of the material parameters.

NAME [current highest rubber-orthotropic label number + 1]Label number of the rubber-orthotropic data set to define. If the label number of an existingrubber-orthotropic data set is defined, then the previous definition is overwritten.

BETAA [0.0]The angle (in degrees) between the material a axis and the fiber A direction na.

BETAB [0.0]The angle (in degrees) between the material b axis and the fiber B direction nb. This parameteris not used if DIRECTION = AHOOP.

K1 [0.0]K1 [0.0]The material constants of the orthotropic strain energy function.

COMPRESSION [NO]If COMPRESSION = NO, then material fibers in compression do not contribute to theorthotropic strain energy (no strain energy in compression). If COMPRESSION = YES, thenmaterial fibers in compression contribute to the orthotropic strain energy.

DIRECTION [AB]If DIRECTION = AB, then the fiber directions are na and nb. If DIRECTION = AHOOP, then thefiber directions are na and x (the hoop direction). AHOOP is allowed only for axisymmetricelements.

Auxiliary commands

LIST RUBBER-ORTHOTROPIC FIRST LASTDELETE RUBBER-ORTHOTROPIC FIRST LAST

RUBBER-ORTHOTROPIC HOLZAPFEL




RUBBER-ORTHOTROPIC HOLZAPFEL



COEFFICIENTS-TABLE NAME

sigmai a0i a1i a2i a3i a4i a5i a6i a7i

Defines an effective-stress v creep-coefficients table, which can be referenced by commandCREEP-COEFFICIENTS MULTILINEAR to define the temperature and/or effective-stressdependence of creep material models with variable coefficients, see commands

MATERIAL CREEP-VARIABLE, MATERIAL PLASTIC-CREEP-VARIABLE,MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE.

See the Theory and Modeling Guide for further details.

NAME [(current highest COEFFICIENTS-TABLE label number) + 1]Label number of the stress v creep-coefficient table to be defined.

sigmaiStress at data point �i�.

a0iCreep law coefficient a0 at stress sigmai.








Auxiliary commands

LIST COEFFICIENTS-TABLE FIRST LASTDELETE COEFFICIENTS-TABLE FIRST LAST

COEFFICIENTS-TABLE



CREEP-COEFFICIENTS LUBBY2 NAME

thetai a0i a1i a2i a3i a4i a5i

Defines the dependency of creep law coefficients on temperature. This creep coefficientfunction is referenced by the NCOEF parameter in the commands:

MATERIAL CREEP-VARIABLE, MATERIAL PLASTIC-CREEP-VARIABLE,MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE

if CREEP-LAW=LUBBY2 is specified in those commands.

NAME [(current highest creep-coefficientfunction label number) + 1]

Label number of the creep-coefficient function to be defined.

thetaiTemperature at data point "i".

a0i [0.0]Creep law coefficient a0 at "thetai".



a3i [1.21e8]Creep law coefficient a3 at "thetai". {≠ 0.0}

a4i [188000]Creep law coefficient a4 at "thetai". {≠ 0.0}

a5i [251000]Creep law coefficient a5 at "thetai". {≠ 0.0}

Auxiliary commands:

LIST CREEP-COEFFICIENTS LUBBY2 FIRST LASTDELETE CREEP-COEFFICIENTS LUBBY2 FIRST LAST

CREEP-COEFFICIENTS LUBBY2



CREEP-COEFFICIENTS MULTILINEAR NAME

thetai ccurvei

Defines the temperature and/or effective-stress dependence of creep material models withvariable coefficients, see commands

MATERIAL CREEP-VARIABLE, MATERIAL PLASTIC-CREEP-VARIABLE,MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE, and COEFFICIENTS-TABLE.




ccurveiStress vs. creep-coefficient table at temperature thetai, see commandCOEFFICIENTS-TABLE.

Auxiliary commands

LIST CREEP-COEFFICIENTS MULTILINEAR FIRST LASTDELETE CREEP-COEFFICIENTS MULTILINEAR FIRST LAST

CREEP-COEFFICIENTS MULTILINEAR



CREEP-COEFFICIENTS TEMPERATURE-ONLY NAME

thetai a0i a1i a2i a3i a4i a5i a6i a7i

Defines the dependency of creep law coefficients on temperature. This creep coefficientfunction is referenced by the NCOEF parameter in the commands:

MATERIAL CREEP-VARIABLE, MATERIAL PLASTIC-CREEP-VARIABLE,MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE

if CREEP-LAW=LAW3 is specified in those commands.




a0iCreep law coefficient a0 at "thetai".








CREEP-COEFFICIENTS TEMPERATURE-ONLY


Sec. 7.1 Material modelsCREEP-COEFFICIENTS TEMPERATURE-ONLY

Auxiliary commands:

LIST CREEP-COEFFICIENTS TEMPERATURE-ONLY FIRST LASTDELETE CREEP-COEFFICIENTS TEMPERATURE-ONLY FIRST LAST



CREEP-COEFFICIENTS USER-SUPPLIED NAME

Defines the temperature and/or effective-stress dependence of creep material models withvariable coefficients, see commands:MATERIAL CREEP-VARIABLE, MATERIAL PLASTIC-CREEP-VARIABLE,MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE.The dependence is defined via a user-supplied function, see the Theory and Modeling Guidefor further details.



Auxiliary commands

LIST CREEP-COEFFICIENTS USER-SUPPLIED FIRST LASTDELETE CREEP-COEFFICIENTS USER-SUPPLIED FIRST LAST

CREEP-COEFFICIENTS USER-SUPPLIED



CURVATURE-MOMENT NAME

curvaturei momenti

Defines a curvature v moment curve which can be referenced by the commandMOMENT-CURVATURE-FORCE . The curve is defined as piecewise linear through the datapoints (curvaturei, momenti).

NAME [(current highest CURVATURE-MOMENTlabel number) + 1]

Label number of the curvature v moment curve to be defined.

curvatureiCurvature at data point �i�.

momentiMoment at curvaturei.

Auxiliary commands

LIST CURVATURE-MOMENT FIRST LASTDELETE CURVATURE-MOMENT FIRST LAST

CURVATURE-MOMENT



FTABLE NAME F0 OPTION WEIGHTING W1 W2 TAU

modulusi decayi (OPTION=DIRECT)

modulusi timei (OPTION=TEST)

Defines a series of modulus and decay coefficients to represent a modulus relaxation functionused by command MATERIAL VISCOELASTIC.F0 is 0th term of modulus and the corresponding decay coefficient is zero.If OPTION=TEST, input data are interpreted as the modulus response vs. time. The programwill convert time history curve into a Prony-Dirichlet series representation.

NAME [(current highest FTABLE label number) + 1]Label number of the modulus-decay function to be defined. If the label number of an existingfunction is given, existing function definition is overwritten.

F0 [0.0]The 0th term of modulus representation. Used only when OPTION=DIRECT

OPTION [DIRECT]

DIRECT Table data are input in Prony series

TEST Table data are input in pairs of modulus vs. time

WEIGHTING [NO]Specifies if least squares fitting scheme is used to smooth moduli terms. Used only ifOPTION=TEST. {NO/YES}

W1 [0.0]Weighting parameter 1. Active only if WEIGHTING=YES.

W2 [0.0]Weighting parameter 2. Active only if WEIGHTING=YES.

TAU [0.0]Relaxation parameter for calculating decayi.

modulusiModulus at term "i", or modulus corresponding to time "i"

FTABLE



decayiDecay coefficient at term "i"

timeiTime corresponding to modulusi.

Auxiliary commands

LIST FTABLE FIRST LASTDELETE FTABLE FIRST LAST

FTABLE



FORCE-STRAIN NAME

straini forcei

Defines a force-strain curve which can be referenced by the commandRIGIDITY-MOMENT-CURVATURE.

The curve is defined as piecewise linear through the data points (straini, forcei).

NAME [(current highest FORCE-STRAIN label number) + 1]Label number of the force-strain curve to be defined.

strainiAxial strain at data point �i�.

forceiAxial force at straini.

Note: The force is assumed to be zero when the effective plastic axial strain exceeds themaximum effective plastic axial strain on the yield curve (force vs. plastic-strain)obtained from the above force v total-strain curve.

Auxiliary commands

LIST FORCE-STRAIN FIRST LASTDELETE FORCE-STRAIN FIRST LAST

FORCE-STRAIN



IRRADIATION_CREEP-TABLE NAME

temperaturei neutron-tablei

Defines the dependency of irradiation creep variables on temperature and fast neutronfluence.

NAME [(current highest irradiation_creep-table label number)+ 1]

Label number of the irradiation creep table to be defined.

temperatureiTemperature at data point �i�.

neutron-tableiNeutron fluence table at temperature �thetai�.

Auxiliary commands

LIST IRRADIATION_CREEP-TABLE FIRST LASTDELETE IRRADIATION_CREEP-TABLE FIRST LAST

IRRADIATION_CREEP-TABLE




IRRADIATION_CREEP-TABLE



MOMENT-CURVATURE-FORCE NAME

forcei curvature-momenti

Defines a moment-curvature curve which can be referenced by the commandRIGIDITY-MOMENT-CURVATURE .

NAME [(current highest MOMENT-CURVATURE-FORCElabel number) + 1]

Label number of the curvature v moment curve to be defined.

forceiAxial force at data point �i�.

curvature-momentiLabel number of the curvature-moment at forcei. (See CURVATURE-MOMENT ).

Note: For plasticity models, the curves defined by the input data are transformed to yieldcurves which are linearly interpolated to obtain the yield curve corresponding tothe current axial force.

Note: The bending moment is assumed to be zero when the effective plastic curvatureexceeds the maximum effective plastic curvature reached by the interpolated yieldcurves.

Auxiliary commands

LIST MOMENT-CURVATURE-FORCE FIRST LASTDELETE MOMENT-CURVATURE-FORCE FIRST LAST

MOMENT-CURVATURE-FORCE



MOMENT-TWIST-FORCE NAME

forcei twist-momenti

Defines a moment-twist curve which can be referenced by the commandRIGIDITY-MOMENT-CURVATURE.

NAME [(current highest MOMENT-TWIST-FORCElabel number) + 1]

Label number of the moment-twist curve to be defined.

forceiAxial force at data point �i�.

twist-momentiLabel number of the twist-moment at forcei. (See TWIST-MOMENT ).

Note: For plasticity models, the curves defined by the input data are transformed to yieldcurves which are linearly interpolated to obtain the yield curve corresponding tothe current axial force.

Note: The bending moment is assumed to be zero when the effective plastic twist exceedsthe maximum effective plastic twist reached by the interpolated yield curves.

Auxiliary commands

LIST MOMENT-TWIST-FORCE FIRST LASTDELETE MOMENT-TWIST-FORCE FIRST LAST

MOMENT-TWIST-FORCE



PORE-FLUID-PROPERTY MATERIAL PX PY PZ COMPRESS FLUIDBULKPOROSITY

Defines pore fluid properties.

MATERIALLabel number of the material (must be existing).

PX [1.0E-9]PY [1.0E-9]PZ [1.0E-9]Permeability in X, Y and Z directions. Must be positive.

COMPRESS [NO]Indicates whether the fluid is compressible. {NO/YES}

FLUIDBULK [2.1E9]Bulk modulus of the pore fluid. Used only when COMPRESS = YES. {>0.0}

POROSITY [0.75]Porosity of the porous solid material. Used only when COMPRESS = YES. {>0.0}

PORE-FLUID-PROPERTY



NEUTRON-DOSE NAME

timei neutron-fluencei

Defines a neutron fluence as a function of time. The command defines a time dependent totalneutron fluence for the irradiation creep material model.

The time range input should cover the entire time interval required in the solution.

NAME [(current highest neutron dose label number) + 1]Label number of neutron dose to be defined. If the label number of an existing neutron doseis given, then the previous definition is overwritten.


neutron-fluenceiNeutron fluence at timei.

NEUTRON-DOSE



NEUTRON-TABLE NAME

neutron-fluencei irradiation-straini Ei alphai

Defines a neutron fluence table which can be referenced by an irradiation creep table.

NAME [(current highest NEUTRON-TABLE label number) + 1]Label number of the neutron fluence table to be defined.

neutron-fluenceiNeutron-fluence at data point �i�.

irradiation-strainiIrradiation-strain at �neutron-fluencei �.

EiYoung�s modulus at �neutron-fluencei �.

alphaiMean coefficient of thermal expansion at �neutron-fluencei �.

Auxiliary commands:

LIST NEUTRON-TABLE FIRST LASTDELETE NEUTRON-TABLE FIRST LAST

NEUTRON-TABLE



PROPERTY NONLINEAR-C NAME XC XN

Defines a nonlinear relationship between the damping force and the relative velocity of thenonlinear spring element. The relationship is of the form,

F C UD N= ⋅ ú

NAME [(current highest property label number) + 1]Label number of the property to be defined.

XCConstant �C� in the definition of function FD, see above.

XNExponent �N� in the definition of function FD, see above.

Auxiliary Commands

LIST PROPERTY NONLINEAR-C FIRST LASTDELETE PROPERTY NONLINEAR-C FIRST LAST

PROPERTY NONLINEAR-C



PROPERTY NONLINEAR-K NAME RUPTURE

relative-displacementi forcei

Defines a nonlinear relationship between relative-displacement and force from which thestiffness and force of a nonlinear spring element are obtained.


RUPTURE [NO]Indicates whether a spring ruptures if the relative displacement exceeds the limiting values ofthe input relative-displacements. If YES then the force is assumed zero beyond the minimum,maximum values of the relative-displacement. {YES/NO}

relative-displacementiRelative displacement (between spring nodes) at data point �i�.

forceiSpring force at relative-displacementi.

Auxiliary Commands

LIST PROPERTY NONLINEAR-K FIRST LASTDELETE PROPERTY NONLINEAR-K FIRST LAST

PROPERTY NONLINEAR-K



PROPERTY NONLINEAR-M NAME

timei massi

Defines the time-dependent total mass for nonlinear spring elements. The input time rangeshould cover that of the entire analysis.



massiSpring mass at timei.

Auxiliary Commands

LIST PROPERTY NONLINEAR-M FIRST LASTDELETE PROPERTY NONLINEAR-M FIRST LAST

PROPERTY NONLINEAR-M



PROPERTYSET NAME K M C S NONLINEAR NK NM NC

Defines stiffness, mass, damping, and stress transformation properties for SPRING elementsin a set termed a �propertyset�.

See the Theory and Modeling Guide for further details on the resulting spring elementstiffness, mass, damping, and stress transformation matrices evaluated from these constants.

NAME [(current highest property label number) + 1]Label number of the propertyset to be defined.

KLinear spring element stiffness. {> 0.0}

M [0.0]Total mass of linear spring element. The corresponding mass matrix is lumped or consistentaccording to the MASS-MATRIX command.

C [0.0]Linear spring element damping coefficient.

S [0.0]Stress transformation constant for a linear spring element. This constant is used to form astress transformation matrix, which when multiplied by the element nodal displacements givesa stress value.

NONLINEAR [NO]Indicates whether a nonlinear spring propertyset is to be defined. {YES/NO}

NK [0]Label number of a nonlinear stiffness property (see PROPERTY NONLINEAR-K ). ForNONLINEAR = YES a value must be supplied.

NM [0]Label number of a nonlinear mass property (see PROPERTY NONLINEAR-M ).

NC [0]Label number of a nonlinear damping property (see PROPERTY NONLINEAR-C ).

Note: If skew degree-of-freedom systems are applied at the nodes of a spring elementthen ADINA will make any necessary transformation to account for the skewsystem directions.

Note: For a grounded spring, with one nodal degree of freedom specified, the total mass

PROPERTYSET



of the element is lumped at the spring node degree of freedom.

Note: Stress calculations are carried out for spring elements only when RESULTS =STRESSES is set by the EGROUP SPRING command.

Auxiliary commands

LIST PROPERTYSET FIRST LASTDELETE PROPERTYSET FIRST LAST

PROPERTYSET



RIGIDITY-MOMENT-CURVATURE NONLINEAR-ELASTICNAME RIGIDITY-AXIAL MOMENT-RMOMENT-S MOMENT-T DENSITY MASS-AREA MASS-RINERTIAMASS-SINERTIA MASS-TINERTIA ALPHA

Defines a nonlinear-elastic rigidity for BEAM elements.

NAME [(current highest RIGIDITY-MOMENT-CURVATURElabel number) + 1]

Label number of the rigidity to be defined.

RIGIDITY-AXIALAxial rigidity.

MOMENT-R [0]Label number of a curve defined by MOMENT-TWIST-FORCE giving the torsional momentof inertia as a nonlinear elastic function of the twist per unit length.

MOMENT-S [0]Label number of a curve defined by MOMENT-CURVATURE-FORCE giving the bendingmoment of inertia about the s-axis of a beam element as a nonlinear elastic function of thecorresponding curvature.

MOMENT-T [0]Label number of a curve defined by MOMENT-CURVATURE-FORCE giving the bendingmoment of inertia about the t-axis of a beam element as a nonlinear elastic function of thecorresponding curvature.

DENSITY [0.0]Mass density (in units of mass/length3 ). Used in the calculation of the mass matrix.

MASS-AREACross-sectional area (in units of length2 ). Used only in the calculation of the mass matrix.

MASS-RINERTIASecond moment of area for torsion about the r-axis of a beam element, including warpingeffects (in units of length4 ). Used only in the calculation of the mass matrix.

MASS-SINERTIASecond moment of area for bending about the s-axis of a beam element (in units of length4 ).Used only in the calculation of the mass matrix.

RIGIDITY-MOMENT-CURVATURE NONLINEAR-ELASTIC



MASS-TINERTIASecond moment of area for bending about the t-axis of a beam element (in units of length4 ).Used only in the calculation of the mass matrix.

ALPHAThermal expansion coefficient.

Auxiliary commands

LIST RIGIDITY-MOMENT-CURVATURE FIRST LASTDELETE RIGIDITY-MOMENT-CURVATURE FIRST LAST

RIGIDITY-MOMENT-CURVATURE NONLINEAR-ELASTIC



RIGIDITY-MOMENT-CURVATURE PLASTIC-MULTILINEARNAME HARDENING BETA FORCE-AXIAL MOMENT-R MOMENT-SMOMENT-T AXIAL-CYCLIC-FACTORBENDING-CYCLIC-FACTORTORSION-CYCLIC-FACTOR DENSITYMASS-AREA MASS-RINERTIAMASS-SINERTIA MASS-TINERTIAACURVE-TYPE TCURVE-TYPEBCURVE-TYPE ALPHA

Defines a plastic-multilinear rigidity for BEAM elements.

NAME [(current highest RIGIDITY-MOMENT-CURVATURElabel number) + 1]

Label number of the rigidity to be defined.




MIXED Linear mixed strain hardening.

BETAFactor used in mixed hardening to determine the amounts of kinematic and isotropic harden-ing. BETA = 0 results in purely kinematic hardening while BETA = 1 results in purelyisotropic hardening. {0.0 < BETA < 1.0}

FORCE-AXIAL [0]Label number of a curve defined by FORCE-STRAIN giving the axial force as a multilinearplastic function of the axial strain.

MOMENT-R [0]Label number of a curve defined by MOMENT-TWIST-FORCE giving the torsional momentof inertia as a multilinear function of the twist per unit length.

MOMENT-S [0]Label number of a curve defined by MOMENT-CURVATURE-FORCE giving the bendingmoment of inertia about the s-axis of a beam element as a multilinear function of the corre-sponding curvature.

RIGIDITY-MOMENT-CURVATURE PLASTIC-MULTILINEAR



MOMENT-T [0]Label number of a curve defined by MOMENT-CURVATURE-FORCE giving the bendingmoment of inertia about the t-axis of a beam element as a multilinear function of the corre-sponding curvature.

AXIAL-CYCLIC-FACTOR [1.0]Ratio of the initial elastic axial rigidity and the elastic axial rigitity after first yield. {≥ 1.0}

BENDING-CYCLIC-FACTOR [1.0]Ratio of the initial elastic bending rigidity and the elastic bending rigidity after first yield.{≥ 1.0}

TORSIONAL-CYCLIC-FACTOR [1.0]Ratio of the initial elastic torsional rigidity and the elastic torsional rigidity after first yield.{≥ 1.0}

DENSITY [0.0]Mass density (in units of mass/length3 ). Used in the calculation of the mass matrix.

MASS-AREACross-sectional area (in units of length2 ). Used only in the calculation of the mass matrix.

MASS-RINERTIASecond moment of area for torsion about the r-axis of a beam element, including warpingeffects (in units of length4 ). Used only in the calculation of the mass matrix.

MASS-SINERTIASecond moment of area for bending about the s-axis of a beam element (in units of length4 ).Used only in the calculation of the mass matrix.

MASS-TINERTIASecond moment of area for bending about the t-axis of a beam element (in units of length4 ).Used only in the calculation of the mass matrix.

Note: For the curves input via FORCE-AXIAL, MOMENT-R, MOMENT-S, andMOMENT-T, the first data point corresponds to the yield point, all data pointsmust have positive coordinates, and the slope (hardening modulus) of any curvesegment cannot be greater than the elastic modulus of the curve.

Note: Softening is not modeled.




ACURVE-TYPE [SYMMETRIC]Indicates whether the axial force-strain curve is symmetric or not.{SYMMETRIC/UNSYMMETRIC}

TCURVE-TYPE [SYMMETRIC]Indicates whether the torsional moment-twist curves are symmetric or not.{SYMMETRIC/UNSYMMETRIC}

BCURVE-TYPE [SYMMETRIC]Indicates whether the bending moment-curvature curves are symmetric or not.{SYMMETRIC/UNSYMMETRIC}

ALPHAThermal expansion coefficient.

Auxiliary commands

LIST RIGIDITY-MOMENT-CURVATURE FIRST LASTDELETE RIGIDITY-MOMENT-CURVATURE FIRST LAST




RUPTURE MULTILINEAR NAME COMPRESS TRIAXIALITY

thetai rupture-curvei

Defines a rupture criterion in terms of a multilinear relationship between temperature andcreep rupture strain v. effective stress curves - see the Theory and Modeling Guide fordetails. The rupture criterion may be referenced by any of the creep material models, e.g. seecommand MATERIAL CREEP.

NAME [(current highest rupture criterion label number) + 1]

Label number of the rupture criterion to be defined.

COMPRESS [YES]Indicates whether creep rupture can occure in compression. {YES/NO}

TRIAXIALITY [YES]Indicates whether triaxiality factor is used. {YES/NO}


rupture-curveiCreep rupture-strain vs. effective stress curve at temperature thetai, defined by commandRUPTURE-CURVE.

Auxiliary commands

LIST RUPTURE MULTILINEAR FIRST LASTDELETE RUPTURE MULTILINEAR FIRST LAST

RUPTURE MULTILINEAR



RUPTURE THREE-PARAMETER NAME ALPHA BETA SIGMA

Defines a rupture criterion in terms of the first three stress invariants -- see the Theory andModeling Guide for details. The rupture criterion may be referenced by any of the creepmaterial models, e.g. see command MATERIAL CREEP.

NAME [(current highest rupture criterion label number) + 1]

Label number of the rupture criterion to be defined.

ALPHA [0.0]First coefficient of the three-parameter rupture law.

BETA [0.0]Second coefficient of the three-parameter rupture law.

SIGMA [0.0]Effective stress at rupture for the three-parameter rupture law.

Auxiliary commands

LIST RUPTURE THREE-PARAMETER FIRST LASTDELETE RUPTURE THREE-PARAMETER FIRST LAST

RUPTURE THREE-PARAMETER



RUPTURE-CURVE NAME

straini stressi

Defines a creep rupture strain v. effective stress curve which may be referenced by commandRUPTURE to define a rupture criterion for a creep material model. See the Theory andModeling Guide for further details.

NAME [(current highest RUPTURE-CURVE label number) + 1]

Label number of the creep rupture strain vs. effective stress curve to be defined.

strainiCreep rupture strain at data point �i�.

stressiStress at creep rupture strain straini.

Auxiliary commands

LIST RUPTURE-CURVE FIRST LASTDELETE RUPTURE-CURVE FIRST LAST

RUPTURE-CURVE



SCURVE NAME

straini stressi

Defines a stress-strain curve which can be referenced by a material model. The stress-straincurve is defined as piecewise linear through the data points (straini, stressi).

NAME [(current highest SCURVE label number) + 1]Label number of the stress-strain curve to be defined.

strainiStrain at data point �i�.

stressiStress at strain �straini�.

Auxiliary commands

LIST SCURVE FIRST LASTDELETE SCURVE FIRST LAST

SCURVE



SSCURVE NAME CONSTANT-NU NU

straini stressi strain2i

Defines a stress-strain curve which can be referenced by a material model. The stress-straincurve is defined as piecewise linear through the data points (straini , stressi ).This command is currrenlty used only for hyperelastic curve fitting.

NAME [(current highest SSCURVE label number) + 1]Label number of the stress-strain curve to be defined. If the label number of an existing curveis given, then the previous curve definition is overwritten.

CONSTANT-NU [NO]Flag indicate constant nu is used or not {YES/NO}This parameter is only used when this curve is referenced by the hyper-foam material model.

NUSpecifies the Poissons ratio when CONSTANT-NU=YES.This parameter is only used with the hyper-foam material model.Note that NU must be in one of the ranges:

-1 < NU < 0.0, 0.0 < NU < 0.5

strainiStrain at data point "i".

stressiStress at data point "i".

strain2iLateral strain at data point "i".strain2i is only used if CONSTANT-NU=NO is specified and this curve is used for a hyper-foam material model.

Auxiliary commands

LIST SSCURVE FIRST LASTDELETE SSCURVE FIRST LAST

SSCURVE


Sec. 7.1 Material modelsSSCURVE




LCURVE NAME

closurei pressurei

Defines a loading-unloading curve which can be referenced by the gasket material model. Theloading-unloading curve is defined as piecewise linear through the data points (pressurei ,closurei ).

NAME [(current highest LCURVE label number) + 1 ]Label number of the loading-unloading curve to be defined. If the label number of an existingcurve is given, then the previous curve definition is overwritten.

closureiClosure at data point "i".

pressureiPressure at data point "i".

Note: First point must have pressure =0.

Auxiliary commands

LIST LCURVE FIRST LASTDELETE LCURVE FIRST LAST

LCURVE






STRAINRATE-FIT NAME

strainratei scurvei

Defines a strainrate-fit. The strainrate-fit can be specified in the MATERIAL PLASTIC-BILINEAR and MATERIAL PLASTIC-MULTILINEAR commands, for the curve fitting ofstrainrate material parameters.

NAME [(current highest strainrate-fit label number) + 1]Label number of the strain-rate fit to be defined. If the label number of an existing strainrate-fitis given, then the previous strainrate-fit definition is overwritten.

strainrateiThe strainrate associated with scurvei. The strainrate must be greater than 0.0.

scurveiThe stress-strain curve, specified by the SCURVE command, for strainratei.

STRAINRATE-FIT


Sec. 7.2 Cross-sections / layers

TWIST-MOMENT NAME

twisti momenti

Defines a twist v moment curve which can be referenced by the MOMENT-TWIST-FORCEcommand. The curve is defined as piecewise linear through the data points (twisti, momenti).

NAME [(current highest TWIST-MOMENT label number) + 1]Label number of the twist v moment curve to be defined.

twistiTwist per unit length at data point �i�.

momentiMoment at twisti.

Auxiliary commands

LIST TWIST-MOMENT FIRST LASTDELETE TWIST-MOMENT FIRST LAST

TWIST-MOMENT



CROSS-SECTION BOX NAME WIDTH HEIGHT THICK1THICK2 SC TC TORFAC SSHEARFTSHEARF

CROSS-SECTION BOX defines a box cross-section which can be used to describe the cross-sectional characteristics of an elastic Hermitian BEAM element.

NAME [(current highest cross-section label number) + 1]Label number of the cross-section to be defined.

WIDTHHEIGHTTHICK1THICK2The dimensions of the box cross-section. See Figure.

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CROSS-SECTION BOX



SC [0.0]TC [0.0]Offset coordinates from the origin of the s-t beam axes to the centroid of the cross-section.Note that the principal axes x�-y� of the cross-section are assumed parallel to the s-t axes ofthe beam.

TORFAC [1.0]The torsional rigidity of the cross-section, corresponding to St. Venant torsion with freewarping, is multiplied by the factor TORFAC. (See Theory and Modeling Guide for details).

SSHEARF [0.0 (no s-direction shear effect)]TSHEARF [0.0 (no t-direction shear effect)]The shear areas corresponding to the beam s and t directions are calculated as the totalcross-sectional area multiplied by the factors SSHEARF, TSHEARF, respectively.

Auxiliary commands

LIST CROSS-SECTION FIRST LASTDELETE CROSS-SECTION FIRST LAST

CROSS-SECTION BOX



CROSS-SECTION I NAME WIDTH1 HEIGHT WIDTH2THICK1 THICK2 THICK3 SC TCTORFAC SSHEARF TSHEARF

CROSS-SECTION I defines an I cross-section which can be used to describe the cross-sectional characteristics of an elastic Hermitian BEAM element.

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CROSS-SECTION I


WIDTH1HEIGHTWIDTH2THICK1THICK2THICK3The dimensions of the I cross-section. See Figure.






Auxiliary commands


CROSS-SECTION I



CROSS-SECTION L NAME WIDTH HEIGHT THICK1 THICK2SC TC TORFAC SSHEARF TSHEARF

CROSS-SECTION L defines an L cross-section which can be used to describe the cross-sectional characteristics of an elastic Hermitian BEAM element.


WIDTH1HEIGHTTHICK1THICK2The dimensions of the L cross-section. See Figure.



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CROSS-SECTION L




Auxiliary commands


CROSS-SECTION L



CROSS-SECTION PIPE NAME DIAMETER THICKNESS SC TCTORFAC SSHEARF TSHEARF SOLID

CROSS-SECTION PIPE defines a pipe cross-section which can be used to describe the cross-sectional characteristics of a BEAM or PIPE element.


� ��

��

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CROSS-SECTION PIPE

DIAMETERTHICKNESSThe diameter and thickness dimensions, respectively, of the pipe cross-section. See Figure.






Note: The parameters SC, TC, TORFAC, SSHEARF, TSHEARF are only applicable toelastic Hermitian BEAM elements.

SOLID [NO]Indicates whether the cross section is solid, i.e. not hollow. If SOLID=YES, THICKNESSinput is ignored and the thickness is set to half the diameter value. {YES/NO}

Auxiliary commands


CROSS-SECTION PIPE



CROSS-SECTION RECTANGULAR NAME WIDTH HEIGHT SC TCTORFAC SSHEARF TSHEARFISHEAR SQUARE

CROSS-SECTION RECTANGULAR defines a rectangular cross-section which can be used todescribe the cross-sectional characteristics of a BEAM or ISOBEAM element.

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WIDTHHEIGHTThe width and height dimensions, respectively, of the rectangular cross-section. See Figure.


CROSS-SECTION RECTANGULAR





ISHEAR [NO]Indicates whether transverse shear effects are to be included. {YES/NO}

Note: The parameters SC, TC, TORFAC, SSHEARF, TSHEARF are applicable only toelastic Hermitian BEAM elements.

Note: The parameter ISHEAR is applicable only to plastic Hermitian BEAM elements.

SQUARE [NO]Indicates whether the cross section shape is square. If SQUARE=YES, HEIGHT input isignored and the height is set equal to the width.{YES/NO}

Auxiliary commands


CROSS-SECTION RECTANGULAR



CROSS-SECTION U NAME WIDTH HEIGHT THICK1 THICK2SC TC TORFAC SSHEARF TSHEARF

CROSS-SECTION U defines a U cross-section which can be used to describe the cross-sectional characteristics of an elastic Hermitian BEAM element.


WIDTHHEIGHTTHICK1THICK2The dimensions of the U cross-section. See Figure.

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CROSS-SECTION U






Auxiliary commands


CROSS-SECTION U



CROSS-SECTION PROPERTIES NAME RINERTIA SINERTIA TINERTIA AREASAREA TAREA CTOFFSET CSOFFSET STINERTIASRINERTIA TRINERTIA WINERTIA WRINERTIADRINERTIA

CROSS-SECTION PROPERTIES defines a general cross-section in terms of principal momentsof inertia and areas. This cross-section definition can be used to describe the cross-sectionalcharacteristics of an elastic Hermitian BEAM element. (See Figure for beam element coordi-nate system.)


RINERTIATorsional moment of inertia, about the beam r-axis. This includes warping effects.

SINERTIABending moment of inertia about the beam s-axis.

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TINERTIABending moment of inertia about the t-axis.

AREACross-sectional area.

SAREA [0.0]Effective shear area in the s-direction.

TAREA [0.0]Effective shear area in the t-direction.

CTOFFSET [0.0]Distance between the centroid and shear center of the cross section along the T direction(zero if section is symmetric about the local S axis).

CSOFFSET [0.0]Distance between the centroid and shear center of the cross section along the S direction(zero if section is symmetric about the local T axis).

STINERTIA [0.0]Inertia term causing coupling between bending about the S axis and bending about the T axis(zero if section is symmetric about either S or T axis).

SRINERTIA [0.0]Inertia term causing coupling between twist/warping and bending about the T axis (zero ifsection is symmetric about the T axis). This term is caused by the Wagner term in the kinemat-ics.

TRINERTIA [0.0]Inertia term causing coupling between twist/warping and bending about the S axis (zero if thesection is symmetric about the local S axis). This is caused by the Wagner term in thekinematics.

WINERTIA [0.0]Warping constant.{≥0}

WRINERTIA [0.0]Inertia term causing bi-moment due to warping (zero if the section is symmetric about either Sor T axis). It is caused by the Wagner term.

DRINERTIA [0.0]Inertia term causing nonlinear twist due to the Wagner effect. {≥0}




Notes:

1. The S-axis and T-axis are not the principal axes of the cross section. They are parallel tothe sides of the L-section, U-section and I-section and pass through the centroid of thecross section.

2. Warping beam should not be used as a bolt.

3. Warping beam should not be used as a rigid link.

4. Warping beam should not be used as a 2D beam.

5. SAREA and TAREA should not be used with the warping beam.

6. CTOFFSET, CSOFFSET, STINERTIA, SRINERTIA, TRINERTIA, WINERTIA,WRINERTIA and DRINERTIA should only be used with the warping beam.

Auxiliary commands








LAYER SUBSTRUCTURE GROUP PLY-DATA

namei materiali tinti pthicki maxesi phii iaxesi phiii printi savei intlocifailurei plydatai

LAYER defines the control parameters for each surface layer for use by multi-layer shellelements.

SUBSTRUCTURE [current substructure label number]Label number of the substructure.

GROUP [current element group]The label number of the element group.

PLY-DATA [NO]This flag determines whether ply data defined by the PLY-DATA command are used tocalculate layer thicknesses. {YES/NO}

YES The thickness of each layer are calculated using ply-datai.

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LAYER



NO The thickness of each layer are calculated using pthicki.

nameiLayer label number. {1 ≤ namei ≤ NLAYER, NLAYER = total number of layers, see EGROUPSHELL}

materiali [1]Material label number used for layer namei.

tinti [2]Integration order for the through-thickness direction (local t-direction) in layer namei.

2 ≤ tinti ≤ 6 Gauss formulas.

-7 ≤ tinti ≤ -3 Closed Newton-Cotes formulas.

pthicki [(1./NLAYER) ××××× 100]Percentage of element thickness assigned to this layer. (NLAYER is the total number oflayers, see EGROUP SHELL).

maxesi [0]Material axes for orthotropic model, for layer namei. <not currently used>

phii [0.0]Offset angle for orthotropic model, for layer namei.

iaxesi [0]Initial strain axes, for layer namei. <not currently used>

phiii [0.0]Offset angle for initial strains, for layer namei.

printi [DEFAULT]This parameter controls the printing of element results for the layer namei. {YES / NO /STRAINS / DEFAULT}

YES Print the element results for layer namei.

NO No results are printed for layer namei.

STRAINS Strains are printed in addition to the stresses for layer namei.

DEFAULT Layer printing is governed by element data commands.

LAYER



savei [DEFAULT]This parameter controls the saving of element results for the layer namei. {YES / NO /DEFAULT}

YES Save the element results on the porthole file for layer namei.

NO No saving of results for layer namei.

DEFAULT Layer saving is governed by element data commands.

intloci [DEFAULT]This parameter controls the printing of integration point coordinates for the layer namei.{YES / NO / DEFAULT}

YES Print integration point (global) coordinates for layer namei.

NO No printing of integration point data for layer namei.

DEFAULT Printout of integration point data is governed by element datacommands.

failurei [0]The label number of failure criterion. (See FAILURE ). A zero value indicates no failurecriterion for layer namei.

plydataiThe label number of the command PLY-DATA, from which the layer thickness is calculated. Ifthe parameter PLY-DATA = NO, or number of layers is equal 1, this parameter will be ignored.

Auxiliary commands

LIST LAYER FIRST LASTDELETE LAYER FIRST LAST

LAYER



PLY-DATA NAME WEIGHT DENSITY FRACTION

Command PLY-DATA defines the layer thickness for a fiber-matrix composite. It is used indefinition of shell elements by the LAYER command.

NAME [(current highest ply-data label number) + 1]Label number of the ply-data to be defined. If the label number of an existing ply-data isgiven, then the previous ply-data definition is overwritten.

WEIGHTWeight per unit surface of the fiber.

DENSITYDensity of the fiber.

FRACTIONFiber volume fraction of the fiber-matrix compound.

Auxiliary commands

LIST PLY-DATA FIRST LASTDELETE PLY-DATA FIRST LAST

PLY-DATA



LINE-ELEMDATA TRUSS

linei materiali areai printi savei tbirthi tdeathi gapwidthi intloci epsini

EDGE-ELEMDATA TRUSS BODY

edgei materiali areai printi savei tbirthi tdeathi gapwidthi intloci epsini

LINE-ELEMDATA TRUSS assigns data for TRUSS elements to geometry lines.

EDGE-ELEMDATA TRUSS assigns data for TRUSS elements to solid geometry edges.

BODY [current active BODY]The geometry body label number.

lineiLine label number.

edgeiEdge label number (for BODY).

materiali [0]Material label number. A zero input value indicates that elements generated on the line/ edgewill take the default material for the host element group.

areai [0]Cross-sectional area for each TRUSS element on the line/edge.

printi [DEFAULT]

YES Print results for TRUSS elements on line/edge.

NO No results are printed for TRUSS elements on the line/edge.

DEFAULT Element printing is governed by PRINTOUT PRINTDEFAULT.

savei [DEFAULT]

YES Save results for TRUSS elements on line/edge.

NO No saving of results for TRUSS elements on the line/edge.

LINE-ELEMDATA TRUSS


Sec. 7.3 Element properties

DEFAULT Saving of element results is governed by PORTHOLESAVEDEFAULT.

tbirthi [0.0]The time of element birth.

tdeathi [0.0]The time of element death.

gapwidthi [0.0]Gap width for each TRUSS element on the line/edge. A zero value indicates no gap.

intloci [NO]Indicates whether to print element integration point coordinates (global) in the undeformedconfiguration. {YES/NO}

epsini [0.0]Initial strain for each TRUSS element on the line/edge.

Auxiliary commands

LIST LINE-ELEMDATA TRUSS FIRST LASTDELETE LINE-ELEMDATA TRUSS FIRST LAST

LIST EDGE-ELEMDATA TRUSS FIRST LASTDELETE EDGE-ELEMDATA TRUSS FIRST LAST

LINE-ELEMDATA TRUSS



SURF-ELEMDATA TWODSOLID

surfacei materiali betai printi savei tbirthi tdeathi intloci gammai

FACE-ELEMDATA TWODSOLID BODY

facei materiali betai printi savei tbirthi tdeathi intloci gammai

SURF-ELEMDATA TWODSOLID assigns data for TWODSOLID elements to geometrysurfaces.

FACE-ELEMDATA TWODSOLID assigns data for TWODSOLID elements to solid geometryfaces.

BODY [current active BODY]The geometry body label number.

surfaceiSurface label number.

faceiFace label number (for BODY).

materiali [0]Material label number. A zero input value indicates that elements generated on the surface/face will take the default material for the host element group.

betai [0.0]Material angle, in degrees, for each TWODSOLID element on the surface/face. Used inconjunction with orthotropic material types.

printi [DEFAULT]

YES Print results as requested by EGROUP RESULTS.

NO No results are printed for TWODSOLID elements on the surface/face.

STRAINS In addition to stresses, strains are printed.

DEFAULT Printout is governed by PRINTOUT PRINTDEFAULT.




savei [DEFAULT]

YES Save, on the porthole file, element results as requested by EGROUPRESULTS.

NO No saving of results for TWODSOLID elements on the surface/face.

DEFAULT Saving of element results is governed by PORTHOLE SAVEDEFAULT.



intloci [NO]Specifies whether element integration point (global) coordinates, in the undeformed configu-ration are printed. {YES/NO}

gammai [0.0]Initial strain angle, in degrees, used in conjunction with any definition of element initialstrains.

Auxiliary commands

LIST SURF-ELEMDATA TWODSOLID FIRST LASTDELETE SURF-ELEMDATA TWODSOLID FIRST LAST

LIST FACE-ELEMDATA TWODSOLID FIRST LASTDELETE FACE-ELEMDATA TWODSOLID FIRST LAST




VOL-ELEMDATA THREEDSOLID

volumei materiali maxesi printi savei tbirthi tdeathi intloci maxesii ngeomi

BODY-ELEMDATA THREEDSOLID

bodyi materiali maxesi printi savei tbirthi tdeathi intlocii maxesii ngeomi

VOL-ELEMDATA THREEDSOLID assigns data for THREEDSOLID elements to geometryvolumes.

BODY-ELEMDATA THREEDSOLID assigns data for THREEDSOLID elements to solidgeometry bodies.

volumeiVolume label number.

bodyiBody label number.

materiali [0]Material label number. A zero input value indicates that elements generated in the volume/body will take the default material for the host element group.

maxesi [0]Material axes set for each THREEDSOLID element in the volume/body. Used in conjunctionwith orthotropic material types.

printi [DEFAULT]

YES Print element results as requested by EGROUP RESULTS.

NO No results are printed for THREEDSOLID elements in thevolume/body.

STRAINS Strains as well as stresses are printed for THREEDSOLIDelements in the volume/body.





savei [DEFAULT]

YES Save, on the porthole file, element results as requested byEGROUP RESULTS.

NO No saving of results for THREEDSOLID elements in the volume/body.

DEFAULT Saving of element results is governed by commandPORTHOLE SAVEDEFAULT.



intloci [NO]Determines whether or not element integration point (global) coordinates in the undeformedconfiguration are printed. {YES/NO}

maxesii [0]Initial strain axes set for each THREEDSOLID element in the volume/body. Used in conjunc-tion with element initial strains.

ngeomiThis parameter is obsolete.

Auxiliary commands

LIST VOL-ELEMDATA THREEDSOLID FIRST LASTDELETE VOL-ELEMDATA THREEDSOLID FIRST LAST

LIST BODY-ELEMDATA THREEDSOLID FIRST LASTDELETE BODY-ELEMDATA THREEDSOLID FIRST LAST




LINE-ELEMDATA BEAM

linei materiali sectioni endreleasei printi savei tbirthi tdeathi intloci epsini,moment-ri moment-si moment-ti rigid-starti rigid-endi

EDGE-ELEMDATA BEAM BODY

edgei materiali sectioni endreleasei printi savei tbirthi tdeathi intloci epsini,moment-ri moment-si moment-ti rigid-starti rigid-endi

LINE-ELEMDATA BEAM assigns data for BEAM elements to geometry lines.

EDGE-ELEMDATA BEAM assigns data for BEAM elements to solid geometry edges.

BODY [current active BODY]Body label number


edgeiEdge label number.

materiali [0]Material label number. A zero input value indicates that elements generated on the line/edgewill take the default material for the host element group.

sectioni [0]Cross-section label number for each BEAM element on the line/edge. See CROSS-SECTION.

endreleasei [0]End-release condition label number for each BEAM element on the line/edge. SeeENDRELEASE.

printi [DEFAULT]


NO No results are printed for BEAM elements on the line/edge.


LINE-ELEMDATA BEAM



savei [DEFAULT]


NO No saving of results for BEAM elements on the line/edge.




intloci [NO]Indicates whether to print element integration point (global) coordinates in the undeformedconfiguration. {YES/NO}

epsini [0.0]Initial axial strain for each BEAM element on the line/edge, or initial force if BEAMOPTION=BOLT is used.

moment-rimoment-simoment-ti<not currently active>

rigid-starti [0.0]Length of the rigid end-zone connected to the start-point (at u=0.0) of the geometry line/edge. Note that this zone can span at most one element meshed onto the line.

rigid-endi [0.0]Length of the rigid end-zone connected to the end-point (at u=1.0) of the geometry line/edge.Note that this zone can span at most one element meshed onto the line.

Auxiliary commands

LIST LINE-ELEMDATA BEAM FIRST LASTDELETE LINE-ELEMDATA BEAM FIRST LAST

LIST EDGE-ELEMDATA BEAM FIRST LASTDELETE EDGE-ELEMDATA BEAM FIRST LAST

LINE-ELEMDATA BEAM



LINE-ELEMDATA ISOBEAM

linei materiali sectioni printi savei tbirthi tdeathi intloci epaxli ephoopi

EDGE-ELEMDATA ISOBEAM BODY

edgei materiali sectioni printi savei tbirthi tdeathi intloci epaxli ephoopi

LINE-ELEMDATA ISOBEAM assigns data for ISOBEAM elements to geometry lines.

EDGE-ELEMDATA ISOBEAM assigns data for ISOBEAM elements to solid geometry edges.





sectioni [0]Cross-section label number for each ISOBEAM element on the line/edge. See CROSS-SEC-TION.

printi [DEFAULT]


NO No results are printed for ISOBEAM elements on the line/edge.


savei [DEFAULT]





NO No saving of results for ISOBEAM elements on the line/edge.





epaxli [0.0]Initial axial strain for each ISOBEAM element on the line/edge.

ephoopi [0.0]Initial hoop strain for each ISOBEAM element on the line/edge.

Auxiliary commands

LIST LINE-ELEMDATA ISOBEAM FIRST LASTDELETE LINE-ELEMDATA ISOBEAM FIRST LAST

LIST EDGE-ELEMDATA ISBEAM FIRST LASTDELETE EDGE-ELEMDATA ISOBEAM FIRST LAST




SURF-ELEMDATA PLATE

surfacei materiali betai printi savei tbirthi tdeathi intloci gammai, eps11i eps22ieps12i flex11i flex22i flex12i

FACE-ELEMDATA PLATE BODY

facei materiali betai printi savei tbirthi tdeathi intloci gammai, eps11i eps22ieps12i flex11i flex22i flex12i

SURF-ELEMDATA PLATE assigns data for PLATE elements to geometry surfaces.

FACE-ELEMDATA PLATE assigns data for PLATE elements to solid geometry faces.




materiali [0]Material label number. A zero input value indicates that elements generated on the surface/facve will take the default material for the host element group.

betai [0.0]Material angle, in degrees, for each PLATE element on the surface/face. Used in conjunctionwith orthotropic material types.

printi [DEFAULT]


NO No results are printed for PLATE elements on the surface/face.


savei [DEFAULT]


SURF-ELEMDATA PLATE



NO No saving of results for PLATE elements on the surface/face.




intloci [NO]Specifies whether or not element integration point (global) coordinates, in the undeformedconfiguration, together with direction cosines of stress reference axes are printed. {YES/NO}


eps11i [0.0]eps22i [0.0]eps12i [0.0]Initial membrane strain components in the element, assumed constant within the element.

flex11i [0.0]flex22i [0.0]flex12i [0.0]Initial flexural strain components in the element, assumed constant within the element.

Auxiliary commands

LIST SURF-ELEMDATA PLATE FIRST LASTDELETE SURF-ELEMDATA PLATE FIRST LAST

LIST FACE-ELEMDATA PLATE FIRST LASTDELETE FACE-ELEMDATA PLATE FIRST LAST

SURF-ELEMDATA PLATE



SURF-ELEMDATA SHELL

surfacei materiali betai printi savei tbirthi tdeathi ithsi intloci gammai,eps11i, eps22i eps12i eps13i eps23i geps11i geps22i geps12i geps13i, geps23i

FACE-ELEMDATA SHELL BODY

facei materiali betai printi savei tbirthi tdeathi ithsi intloci gammai eps11i,eps22i eps12i eps13i eps23i geps11i geps22i geps12i geps13i geps23i

SURF-ELEMDATA SHELL assigns data for SHELL elements to geometry surfaces.

FACE-ELEMDATA SHELL assigns data for SHELL elements to solid geometry faces.





betai [0.0]Material angle, in degrees, for each SHELL element on the surface/face. Used in conjunctionwith orthotropic material types.

printi [DEFAULT]

YES Print results as requested by EGROUP RESULTS.

NO No results are printed for SHELL elements on the surface/face.

STRAINS In addition to stresses, strains are printed.


SURF-ELEMDATA SHELL



savei [DEFAULT]

YES Save, on the porthole file, element results as requestedby EGROUP RESULTS.

NO No saving of results for SHELL elements on the surface/face.




ithsi [NO]Specifies whether or not the thick shell assumption is made for transverse shear behavior ofSHELL elements on the surface/face. {YES/NO}

intloci [NO]Specifies whether or not element integration point (global) coordinates, in the undeformedconfiguration, together with direction cosines of stress reference axes are printed. {YES/NO}


epsjki (jk = 11, 22, 12, 13, 23) [0.0]Initial strain components in the element, assumed constant within the element.

gepsjki (jk = 11, 22, 12, 13, 23) [0.0]Initial strain gradient components in the element, assumed constant within the element.

Auxiliary commands

LIST SURF-ELEMDATA SHELL FIRST LASTDELETE SURF-ELEMDATA SHELL FIRST LAST

LIST FACE-ELEMDATA SHELL FIRST LASTDELETE FACE-ELEMDATA SHELL FIRST LAST

SURF-ELEMDATA SHELL



ELAYER GROUP

elementi layeri materiali

ELAYER assigns material to individual elements on different layers for shell elements.

GROUP [Current element group]The label number of the element group.

elementiThe element label number.

layeriThe layer label number.

materiali [1]The material label number.

Auxiliary commands

LIST ELAYER GROUPDELETE ELAYER GROUP

ELAYER


Sec. 7.3 Element propertiesELAYER




LINE-ELEMDATA PIPE

linei materiali sectioni printi savei tbirthi tdeathi intloci epsini

EDGE-ELEMDATA PIPE BODY

edgei materiali sectioni printi savei tbirthi tdeathi intloci epsini

LINE-ELEMDATA PIPE assigns data for PIPE elements on geometry lines.

EDGE-ELEMDATA PIPE assigns data for PIPE elements on solid geometry edges.

BODY [current active BODY]Body label number.




sectioni [0]Cross-section label number for each PIPE element on the line/edge. See CROSS- SECTION.

printi [DEFAULT]


NO No results are printed for PIPE elements on the line/edge.


savei [DEFAULT]


NO No saving of results for PIPE elements on the line/edge.

LINE-ELEMDATA PIPE







epsini [0.0]Initial axial strain for each PIPE element on the line/edge.

Auxiliary commands

LIST LINE-ELEMDATA PIPE FIRST LASTDELETE LINE-ELEMDATA PIPE FIRST LAST

LIST EDGE-ELEMDATA PIPE FIRST LASTDELETE EDGE-ELEMDATA PIPE FIRST LAST

LINE-ELEMDATA PIPE



LINE-ELEMDATA GENERAL

linei mseti printi savei tbirthi tdeathi

EDGE-ELEMDATA GENERAL BODY

edgei mseti printi savei tbirthi tdeathi

SURF-ELEMDATA GENERAL

surfacei mseti printi savei tbirthi tdeathi

FACE-ELEMDATA GENERAL BODY

facei mseti printi savei tbirthi tdeathi

VOL-ELEMDATA GENERAL

volumei mseti printi savei tbirthi tdeathi

BODY-ELEMDATA GENERAL

bodyi mseti printi savei tbirthi tdeathi

LINE-ELEMDATA GENERAL assigns data for GENERAL elements on lines.

EDGE-ELEMDATA GENERAL assigns data for GENERAL elements to solid geometry edges.

SURF-ELEMDATA GENERAL assigns data for GENERAL elements to geometry surfaces

FACE-ELEMDATA GENERAL assigns data for GENERAL elements to solid geometry faces.

VOL-ELEMDATA GENERAL assigns data for GENERAL elements to geometry volumes.

BODY-ELEMDATA GENERAL assigns data for GENERAL elements to solid geometry bodies.

BODY [currently active BODY]Body label number.










mseti [0]Matrixset label number. A zero input value indicates that elements generated on the geometrywill take the default matrixset for the host element group.

printi [DEFAULT]


NO No results are printed for GENERAL elements on the geometry.


savei [DEFAULT]


NO No saving of results for GENERAL elements on the geometry.


tbirthi [0.0]Element birth time.

tdeathi [0.0]Element death time.




Note: tbirthi < tdeathi, or tbirthi = tdeathi = 0.0

Auxiliary commands

LIST LINE-ELEMDATA GENERAL FIRST LASTDELETE LINE-ELEMDATA GENERAL FIRST LAST

LIST EDGE-ELEMDATA GENERAL FIRST LASTDELETE EDGE-ELEMDATA GENERAL FIRST LAST

LIST SURF-ELEMDATA GENERAL FIRST LASTDELETE SURF-ELEMDATA GENERAL FIRST LAST

LIST FACE-ELEMDATA GENERAL FIRST LASTDELETE FACE-ELEMDATA GENERAL FIRST LAST

LIST VOL-ELEMDATA GENERAL FIRST LASTDELETE VOL-ELEMDATA GENERAL FIRST LAST

LIST BODY-ELEMDATA GENERAL FIRST LASTDELETE BODY-ELEMDATA GENERAL FIRST LAST




SURF-ELEMDATA FLUID2

surfacei materiali printi savei tbirthi tdeathi intloci

FACE-ELEMDATA FLUID2 BODY

facei materiali printi savei tbirthi tdeathi intloci

SURF-ELEMDATA FLUID2 assigns data for FLUID2 elements on surfaces.

FACE-ELEMDATA FLUID2 assigns data for FLUID2 elements on solid geometry faces.





printi [DEFAULT]


NO No results are printed for FLUID2 elements on the surface/face.


savei [DEFAULT]


NO No saving of results for FLUID2 elements on the surface/face.








Auxiliary commands

LIST SURF-ELEMDATA FLUID2 FIRST LASTDELETE SURF-ELEMDATA FLUID2 FIRST LAST

LIST FACE-ELEMDATA FLUID2 FIRST LASTDELETE FACE-ELEMDATA FLUID2 FIRST LAST




VOL-ELEMDATA FLUID3

volumei materiali printi savei tbirthi tdeathi intloci ngeomi

BODY-ELEMDATA FLUID3

bodyi materiali printi savei tbirthi tdeathi intloci ngeomi

VOL-ELEMDATA FLUID3 assigns data for FLUID3 elements in volumes.

BODY-ELEMDATA FLUID3 assigns data for FLUID3 elements in solid geometry bodies.



materiali [0]Material label number. A zero input value indicates that elements generated on the volume/body will take the default material for the host element group.

printi [DEFAULT]


NO No results are printed for FLUID3 elements on the volume/body.


savei [DEFAULT]


NO No saving of results for FLUID3 elements on the volume/body.


VOL-ELEMDATA FLUID3






ngeomiThis parameter is obsolete.

Auxiliary commands

LIST VOL-ELEMDATA FLUID3 FIRST LASTDELETE VOL-ELEMDATA FLUID3 FIRST LAST

LIST BODY-ELEMDATA FLUID3 FIRST LASTDELETE BODY-ELEMDATA FLUID3 FIRST LAST

VOL-ELEMDATA FLUID3



MATRIX STIFFNESS NAME ND

rowi ... kij ... (j = i, i + 1, ..., ND)

Defines a stiffness matrix for use by GENERAL elements. It may be referenced byMATRIXSET.

NAME [(current highest matrix label number) + 1]Label number of the matrix to be defined.

ND [1]The total number of rows entered in this matrix, equal to the number of nodes in the generalelement multiplied by the number of active degrees of freedom per node.{1 ≤ ND ≤ 600}

rowiRow index number for matrix.

kij [0.0]Entries in the stiffness matrix (kij = entry for row �i�, column �j�).

Note: Only the upper-diagonal part of the stiffness matrix is entered by this command.Thus, for rowi, only the first (ND - i + 1) entries are used - the rest are ignored dueto symmetry.

Auxiliary Commands

LIST MATRIX FIRST LASTDELETE MATRIX FIRST LAST

MATRIX STIFFNESS



MATRIX MASS NAME ND

rowi ... mij ... (j = i, (i + 1), ..., ND)

Defines a mass matrix for use by GENERAL elements. It may be referenced by MATRIXSET.




mij [0.0]Entries in the mass matrix (mij = entry for row �i�, column �j�).

Note: For a consistent mass matrix, only the upper-diagonal part of the mass matrix isentered by this command. Thus, for rowi, only the first (ND - i + 1) entries are

used. When the mass matrix is lumped, only the diagonal term, mij, should beentered - the rest are ignored due to symmetry.

Auxiliary Commands


MATRIX MASS



MATRIX DAMPING NAME ND

rowi ... cij ... (j = i, (i + 1), ..., ND)

Defines a damping matrix for use by GENERAL elements. It may be referenced byMATRIXSET.




cij [0.0]Entries in the damping matrix (cij = entry for row �i�, column �j�).

Note: Only the upper-diagonal part of the damping matrix is entered by this command.Thus, for rowi only the first (ND - i + 1) entries are used, the rest are ignored dueto symmetry.

Auxiliary Commands


MATRIX DAMPING



MATRIX STRESS NAME NS ND

rowi ... sij ... (i=1�NS; j=1�ND)

Defines a stress matrix for use by GENERAL elements. It may be referenced by MATRIXSET.


NS [1]The total number rows in the matrix, equal to the number of stress components.{1 ≤ NS ≤ 60}

ND [1]The number of nodes in the general element multiplied by the number of active degrees offreedom per node. {1 ≤ ND ≤ 600}

rowiRow index number.

sij [0.0]Entries in the stress-transformation matrix (sij = entry for row �i�, column �j�).

Note: The full matrix should be entered - no symmetry is assumed.

Auxiliary Commands


MATRIX STRESS



MATRIXSET NAME STIFFNESS MASS DAMPING STRESS

Defines a �matrixset� of stiffness, mass, damping and stress-transformation label numbers forgeneral elements. One stiffness, one mass, one damping and one stress-transformation labelnumber are grouped into a matrix set, which can be associated with the elements of anEGROUP GENERAL element group through its MATRIXSET parameter.

NAME [(current highest matrix label number) + 1]Label number of the matrixset to be defined.

STIFFNESS [0]Label number of stiffness matrix defined by MATRIX STIFFNESS.

MASS [0]Label number of mass matrix defined by MATRIX MASS.

DAMPING [0]Label number of damping matrix defined by MATRIX DAMPING.

STRESS [0]Label number of stress-transformation matrix defined by MATRIX STRESS.

Auxiliary commands

LIST MATRIXSET FIRST LASTDELETE MATRIXSET FIRST LAST

MATRIXSET



MATRIX USER-SUPPLIED NAME ELEMENT-SUBTYPE ELNDOFMATERIAL NUIPT NUIT1 NUIT2 NUIT3

Command MATRIX USER-SUPPLIED defines the element stiffness matrix and nodal forcevector in a general element group, to be provided in the ADINA subroutine CUSERG. Thematerial constants, variables and solution control parameters required in subroutine CUSERGcan be input via parameter MATERIAL. The element subtype must be input to predeterminethe sizes of arrays RE (element nodal forces) and AS (element stiffness) in CUSERG. If someelement results, e.g. stresses and strains, are to be displayed by ADINA-PLOT, the integra-tion scheme locations need to be provided through parameters NUIPT, NUIT1, NUIT2 andNUIT3.

NAME [(current highest matrix label number) + 1]Label number of the matrix to be defined. If the label of an existing matrix is given, then theprevious matrix definition is overwritten.

ELEMENT-SUBTYPEElement subtype indicator for assembling the general element stiffness. This parameter mustbe entered. {TWODSOLID/THREEDSOLID/BEAM/SHELL}

ELNDOF [subtype dependent]This parameter is not used. However, note that the number of active degrees of freedom pernode for a user-supplied element is set by the IDOF parameter of the MASTER command.

MATERIALThe label number of MATERIAL USER-SUPPLIED, in which material constants/variables andsolution control parameters to be used in the calculations of element stiffness matrices andforce vectors are entered. The material constants/variables can be temperature-independentor temperature-dependent.

NUIPT [NUIT1 ××××× NUIT2 ××××× NUIT3]Number of user-provided interior points used to assemble the element stiffness matrix and todisplay the element results at these locations.

NUIT1 [1]NUIT2 [1]NUIT3 [1]Integration orders in the first, second and third local directions of general elements (less thanor equal to 6).

MATRIX USER-SUPPLIED



MASSES POINTS

pointi mass1i mass2i mass3i mass4i mass5i mass6i

MASSES LINES

linei mass1i mass2i mass3i mass4i mass5i mass6i

MASSES SURFACES

surfacei mass1i mass2i mass3i mass4i mass5i mass6i

MASSES VOLUMES

volumei mass1i mass2i mass3i mass4i mass5i mass6i

MASSES NODESETS

nodeseti mass1i mass2i mass3i mass4i mass5i mass6i

MASSES EDGES BODY

edgei mass1i mass2i mass3i mass4i mass5i mass6i

MASSES FACES BODY

facei mass1i mass2i mass3i mass4i mass5i mass6i

MASSES POINTS assigns concentrated masses to the nodes at a set of geometry points.

MASSES LINES assigns concentrated masses to the nodes on a set of geometry lines.

MASSES VOLUMES assigns concentrated masses to the nodes in a set of geometry vol-umes.

MASSES NODESETS assigns concentrated masses to the nodes in a node set.

MASSES EDGES assigns concentrated masses to the nodes on solid geometry edges.

MASSES FACES assigns concentrated masses to the nodes on solid geometry faces.

MASSES




pointiLabel number of a geometry point. All nodes coincident with this geometry point are as-signed a value equal to the specified concentrated mass divided by the number of nodes.

lineiLabel number of a geometry line. All nodes on this line are assigned a value equal to thespecified concentrated mass divided by the number of nodes.

surfaceiLabel number of a geometry surface. All nodes on this surface are assigned a value equal tothe specified concentrated mass divided by the number of nodes.

volumeiLabel number of a geometry volume. All nodes in this volume are assigned a value equal tothe specified concentrated mass divided by the number of nodes.

nodesetiLabel number of a node set. All nodes in this node set are assigned a value equal to thespecified concentrated mass divided by the number of nodes.

edgeiLabel number of a solid geometry edge (for BODY). All nodes of this entity are assigned avalue equal to the specified concentrated mass divided by the number of nodes.

faceiLabel number of a solid geometry face (for BODY). All nodes of this entity are assigned avalue equal to the specified concentrated mass divided by the number of nodes.

mass1i [0.0]Mass assigned to the geometry entity for the nodal x-translation degree-of-freedom (global orskew).

mass2i [0.0]Mass assigned to the geometry entity for the nodal y-translation degree-of-freedom (globalor skew).

mass3i [0.0]Mass assigned to the geometry entity for the nodal z-translation degree-of-freedom (global orskew).

MASSES



mass4i [0.0]Mass moment of inertia assigned to the geometry entity for the nodal x-rotation degree-of-freedom (global or skew).

mass5i [0.0]Mass moment of inertia assigned to the geometry entity for the nodal y-rotation degree-of-freedom (global or skew).

mass6i [0.0]Mass moment of inertia assigned to the geometry entity for the nodal z-rotation degree-of-freedom (global or skew).

Auxiliary commands

LIST MASSES POINTS FIRST LASTDELETE MASSES POINTS FIRST LAST

LIST MASSES LINES FIRST LASTDELETE MASSES LINES FIRST LAST

LIST MASSES SURFACES FIRST LASTDELETE MASSES SURFACES FIRST LAST

LIST MASSES VOLUMES FIRST LASTDELETE MASSES VOLUMES FIRST LAST

LIST MASSES NODESETS FIRST LASTDELETE MASSES NODESETS FIRST LAST

LIST MASSES EDGES FIRST LASTDELETE MASSES EDGES FIRST LAST

LIST MASSES FACES FIRST LASTDELETE MASSES FACES FIRST LAST

MASSES



DAMPERS POINTS

pointi damp1i damp2i damp3i damp4i damp5i damp6i

DAMPERS LINES

linei damp1i damp2i damp3i damp4i damp5i damp6i

DAMPERS SURFACES

surfacei damp1i damp2i damp3i damp4i damp5i damp6i

DAMPERS VOLUMES

volumei damp1i damp2i damp3i damp4i damp5i damp6i

DAMPERS NODESETS

nodeseti mass1i mass2i mass3i mass4i mass5i mass6i

DAMPERS EDGES BODY

edgei damp1i damp2i damp3i damp4i damp5i damp6i

DAMPERS FACES BODY

facei damp1i damp2i damp3i damp4i damp5i damp6i

DAMPERS POINTS assigns concentrated dampers to the nodes at a set of geometry points.

DAMPERS LINES assigns concentrated dampers to the nodes on a set of geometry lines.

DAMPERS SURFACES assigns concentrated dampers to the nodes on a set of geometrysurfaces.

DAMPERS VOLUMES assigns concentrated dampers to the nodes on a set of geometryvolumes.

DAMPERS NODESETS assigns concentrated masses to the nodes in a node set.

DAMPERS EDGES assigns concentrated dampers to the nodes on solid geometry edges.

DAMPERS



DAMPERS FACES assigns concentrated dampers to the nodes on a set of solid geometryfaces.


pointiLabel number of a geometry point. All nodes coincident with this geometry point are as-signed a value equal to the specified concentrated damper divided by the number of nodes.

lineiLabel number of a geometry line. All nodes on this line are assigned a value equal to thespecified concentrated damper divided by the number of nodes.

surfaceiLabel number of a geometry surface. All nodes on this surface are assigned a value equal tothe specified concentrated damper divided by the number of nodes.

volumeiLabel number of a geometry volume. All nodes in this volume are assigned a value equal tothe specified concentrated damper divided by the number of nodes.

nodesetiLabel number of a node set. All nodes in this node set are assigned a value equal to thespecified concentrated mass divided by the number of nodes.

edgeiLabel number of a geometry edge (for BODY). All nodes on this entity are assigned a valueequal to the specified concentrated damper divided by the number of nodes.

faceiLabel number of a geometry face (for BODY). All nodes on this entity are assigned a valueequal to the specified concentrated damper divided by the number of nodes.

damp1i [0.0]Damper assigned to the geometry entity for the nodal x-translation degree-of-freedom (globalor skew).

damp2i [0.0]Damper assigned to the geometry entity for the nodal y-translation degree-of-freedom (globalor skew).

damp3i [0.0]Damper assigned to the geometry entity for the nodal z-translation degree-of-freedom (global

DAMPERS



or skew).

damp4i [0.0]Rotational damper assigned to the geometry entity for the nodal x-rotation degree-of-freedom(global or skew).

damp5i [0.0]Rotational damper assigned to the geometry entity for the nodal y-rotation degree-of-freedom(global or skew).

damp6i [0.0]Rotational damper assigned to the geometry entity for the nodal z-rotation degree-of-freedom(global or skew).

Auxiliary commands

LIST DAMPERS POINTS FIRST LASTDELETE DAMPERS POINTS FIRST LAST

LIST DAMPERS LINES FIRST LASTDELETE DAMPERS LINES FIRST LAST

LIST DAMPERS SURFACES FIRST LASTDELETE DAMPERS SURFACES FIRST LAST

LIST DAMPERS VOLUMES FIRST LASTDELETE DAMPERS VOLUMES FIRST LAST

LIST DAMPERS NODESETS FIRST LASTDELETE DAMPERS NODESETS FIRST LAST

LIST DAMPERS EDGES FIRST LASTDELETE DAMPERS EDGES FIRST LAST

LIST DAMPERS FACES FIRST LASTDELETE DAMPERS FACES FIRST LAST

DAMPERS


Sec. 7.4 Substructure and cyclic symmetry

SUBSTRUCTURE NAME

The model can consist of a main structure and one or more substructures. This commandsets the current substructure.

Substructuring cannot be used with

- multiple time step blocks

- explicit time integration

- rigid link constraint equations in substructure nodes, or between substructure nodes andthe main structure nodes

- potential-based fluid elements

- user-supplied elements, user-supplied loading

- temperature loading and other loading restrictions (see ADINA Theory and Modeling Guide,Section 11.1.3)

- FSI/TMC analysis

- cyclic symmetry structures

- mapping options

- consistent mass damping

- 3D-iterative solver, multigrid solver, iterative solver

- load penetration

- pressure-update (load stiffening effect of shells)

- frequency analysis, mode-superposition analysis, response analysis, response spectrumanalysis, harmonic analysis and random vibration analysis

- linearized buckling analysis

NAME [(current highest substructure label number) + 1]Label number of the current substructure.

Auxiliary commands

LIST SUBSTRUCTURE FIRST LASTDELETE SUBSTRUCTURE FIRST LAST

SUBSTRUCTURE



REUSE NAME LOAD-REUSE CONNECT TRANSFORM

slavenamei masternamei typei sbodyi mbodyi connecti transformationi

Connects the current substructure to the main structure. As the command name implies, eachsubstructure can be used several times and the command REUSE therefore defines the reuseidentifying number for the current substructure.

Input data provided to the following commands refers only to the current reuse number of thecurrent substructure: PRINT-STEPS, SET-INITCONDITION, APPLY-LOAD

NAME [(highest reuse label number) + 1]The label number of the reuse.

LOAD-REUSE [SAME]Loading indicator for the reuse.

SAME Same loading as for the previous (i.e. NAME-1) reuse of thecurrent substructure.

DIFFERENT Loading for this reuse of the current substructure is specified bysubsequent uses of command APPLY-LOAD.

CONNECT [PARAMETRIC]Default setting for how nodes on substructure are to be connected to nodes on main structurewhen connection is between geometry lines or surfaces. {PARAMETRIC/MATCHING}

Note: When connection is between geometry edges, faces or nodesets,CONNECT=MATCHING is always used.

Note: When connection is between lines or surfaces and CONNECT=PARAMETRIC, connec-tion between main structure and substructure is constructed between nodes at the corre-sponding parametric order on each entity. Parametric order is in the increasing u-parameterdirection for lines, increasing u- then v-parameter for surfaces.

TRANSFORM [0]Default coordinate transformation system to match nodes for connecting substructure tomain structure. When connection is between geometry edges, faces or nodesets, TRANS-FORM is always applicable. When connection is between geometry lines or surfaces, TRANS-FORM is only applicable if CONNECT=MATCHING. Transformation is defined from the mainstructure to the substructure.

slavenameiThe label number of the substructure boundary entity (point, line, surface, edge, face, node or

REUSE


Sec. 7.4 Substructure and cyclic symmetryREUSE

nodeset) for the ith term of the reuse.

masternameiThe label number of the main structure connection entity (point, line, surface, edge, face,node or nodeset) for the ith term of the reuse.

typeiThe type of entity. {POINT/LINE(EDGE)/SURFACE(FACE)/NODE/NODESET}

Note: A connection between main structure and substructure is constructed between nodesat the corresponding parametric order on each entity. Parametric order is in the in-creasing u-parameter direction for lines, increasing u- then v-parameter for surfaces. Inthis case the number of nodes on the slave and master geometry entity must be the same.

sbodyi [0]Body label number of slave geometry edge (typei=LINE) or face (typei=SURFACE). Forgeometry line or surface, sbodyi=0 must be specified. For other entities, sbodyi is ignored.

mbodyi [0]Body label number of master geometry edge (typei=LINE) or face (typei=SURFACE). Forgeometry line or surface, mbodyi=0 must be specified. For other entities, mbodyi is ignored.

connecti [from parameter CONNECT]Indicates how nodes on substructure are to be connected to nodes on main structure whenconnection is between geometry line or surface. {PARAMETRIC/MATCHING}

transformi [from parameter TRANSFORMATION]Specifies a coordinate transformation system to match nodes for connecting a substructureto the main structure. When connection is between geometry edges, faces or nodesets,transformi is always applicable. When connection is between geometry lines or surfaces,transformi is only applicable if connecti=MATCHING. Transformation is defined from the mainstructure to the substructure.

Auxiliary commands

LIST REUSE FIRST LASTDELETE REUSE FIRST LAST



CYCLIC-CONTROL CYCLICPARTS AXIS-CYCLIC PERIODIC LOW-HARMONICHIGH-HARMONIC FREQ-HARMONIC FREQ-HALFBOUND-ELEMENT

Specifies parameters that control cyclic symmetry analysis.

CYCLICPARTS [1]The number of cyclic symmetric parts of the main structure. If the value is greater than orequal to 2 then a cyclic symmetric analysis is performed. The maximum number of cyclicsymmetric parts allowed is 999. CYCLICPARTS = 1 indicates no cyclic symmetry.

AXIS-CYCLIC [0]Label number of cyclic symmetry axis defined by axis-rotation command. Default AXIS-CYCLIC = 0 means use global X axis.

PERIODIC [NO]Specifies whether the cyclic models are also under periodic symmetry. {NO/YES}

NO No periodic symmetry analysis. A full cyclic symmetry analysis will be performed.Different loads are used for different cyclic parts.

YES Periodic symmetry analysis. Only the 0 harmonic will be analyzed. Unlike basic cyclicsymmetry analysis, a periodic symmetry analysis can be nonlinear. It can also beused with explicit dynamic time integration. The load applied on the first cyclic partis rotated about the cyclic axis and applied to the other cyclic parts.

LOW-HARMONIC [0]Gives the lowest harmonic to use in cyclic symmetry frequency analysis.{0 ≤ LOW-HARMONIC ≤ N/2} where N is the number of cyclic parts.

HIGH-HARMONIC [DEFAULT] Gives the highest harmonic to use in cyclic symmetry frequency analysis.{0 ≤ HIGH-HARMONIC ≤ N/2} where N is the number of cyclic parts.HIGH-HARMONIC = DEFAULT sets the value to N/2.

FREQ-HARMONIC [0]

Gives the number of frequencies to calculate per harmonic. { ≥ 0}

FREQ-HALF [NO]This flag which tells the program to only calculate one of every two complex frequencypairs.{NO/YES}

CYCLIC-CONTROL


Sec. 7.4 Substructure and cyclic symmetryCYCLIC-CONTROL

BOUND-ELEMENT [SINGLE]Specifies whether structural elements lying completely on the cyclic boundary are definedonce or twice. Applies to beam, isobeam, plate and shell elements. {SINGLE/DOUBLE}

SINGLE Structural elements completely on the cyclic boundary will only be defined onceby the user. The elements may be defined on either the master or the slave cyclicboundaries, but not both. Some elements can be defined on the slave boundaryand others on the master.

DOUBLE Structural elements completely on the cyclic boundary will be define twice by theuser, once on each cyclic boundary. ADINA will handle the stiffness/mass matrixmodifications required for proper solution.






CYCLICLOADS NAME

A cyclic symmetry analysis can be performed by defining the finite element discretization ofthe fundamental part of the geometrically cyclic symmetric structure. This fundamental part isrotated M times about a cyclic axis to represent the complete structure. CYCLICLOADSindicates that the loads subsequently defined are to be on a particular one of these M parts.

NAMELabel number of the cyclic part to be loaded.

Auxiliary commands

LIST CYCLICLOADS FIRST LASTDELETE CYCLICLOADS FIRST LAST

CYCLICLOADS



CYCLICBOUNDARY POINTS / LINES / SURFACES / NODES / NODESET

slavenamei masternamei

CYCLICBOUNDARY is used to associate cyclic boundaries (defined by points, lines,surfaces, nodes, or nodesets) with each other. The command specifies the cyclic boundariesof the fundamental part of a cyclicaly symmetric structure termed the master cyclic boundaryand the slave cyclic boundary. When the nodes on the master cyclic boundary are rotated360/M (where M is the number of cyclic parts) degrees counter clockwise about the cyclicsymmetry axis, they should coincide with the nodes on the slave cyclic boundary.

slavenameiThe label number of the slave entity (point, line, surface, node, or nodeset) for the �i�th termof the cyclic boundary.

masternameiThe label number of the master entity (point, line, surface, node, or nodeset) for the �i�th termof the cyclic boundary.

Note: When cyclic boundaries are based on geometric entities, the number of nodes on boththe master and slave geometries must be the same. The cyclic boundaries are not restricted tostraight lines and flat surfaces.

Auxiliary commands

LIST CYCLICBOUNDARY POINTS / LINES / SURFACES / NODES / NODESETDELETE CYCLICBOUNDARY POINTS / LINES / SURFACES / NODES / NODESETMASTER ... AXIS-CYCLIC PERIODIC

CYCLICBOUNDARY

Master cyclic boundary

Fundamental cyclic part360

Mo

Cyclic symmetry axis

(Default: X axis)

Slave cyclic boundary



CYCLICBOUNDARY TWO-D

slavenamei sbody masternamei mbody

CYCLICBOUNDARY TWO-D is used to associate cyclic boundaries with each other (definedby lines or edges).The command specifies the cyclic boundary nodes of the fundamental partof a cyclically symmetric structure. The cyclic boundaries of the fundamental part consist oftwo sets of lines or edges, namely, the cyclic boundary 1 (master cyclic boundary) and thecyclic boundary 2 (slave cyclic boundary).



Mo


(Default: X axis)


slavenameiThe label number of the geometry slave entity (line or edge) for the �i��th independent termof the cyclic boundary.

sbodyGeometry body label of slave edge.

masternameiThe label number of the geometry master entity (line or edge) for the �i��th independent termof the cyclic boundary.

mbodyGeometry body label of master edge.

Auxiliary commands

LIST CYCLICBOUNDARY TWO-DDELETE CYCLICBOUNDARY TWO-DMASTER ... AXIS-CYCLIC PERIODIC

CYCLICBOUNDARY TWO-D


Chap. 7 Model definition CYCLICBOUNDARY THREE-D

CYCLICBOUNDARY THREE-D

slavenamei sbody masternamei mbody

Command CYCLICBOUNDARY THREE-D is used to associate cyclic boundaries with eachother (defined by surfaces or faces).The command specifies the cyclic boundary nodes of thefundamental part of a cyclically symmetric structure. The cyclic boundaries of the fundamen-tal part consist of two sets of surfaces or faces, namely, the cyclic boundary 1 (master cyclicboundary) and the cyclic boundary 2 (slave cyclic boundary).



Mo


(Default: X axis)


slavenameiThe label number of the geometry slave entity (line or edge) for the �i��th independent termof the cyclic boundary.

sbodyGeometry body label of slave edge.

masternameiThe label number of the geometry master entity (line or edge) for the �i��th independent termof the cyclic boundary.

mbodyGeometry body label of master edge.

Auxiliary commandsLIST CYCLICBOUNDARY THREE-DDELETE CYCLICBOUNDARY THREE-DMASTER ... AXIS-CYCLIC PERIODIC



AXIS-ROTATION NAME MODE SYSTEM AXIS ALINE AP1 AP2 X0 Y0 Z0XA YA ZA

Defines a rotational axis which can be referenced by other commands.

NAME [(current highest axis label number) + 1]Label number of the axis.

MODE [AXIS]Selects the method used to define the axis. The parameters (parenthesized) used to define theaxis depends on the method selected.

AXIS - The rotational axis is defined by a coordinate axis of a coordinate system.(SYSTEM, AXIS)

LINE - The rotational axis is defined by a straight line between the end points of ageometry line (which is not necessarily straight, but must be open - i.e.,have non-coincident end points). (ALINE)

POINTS - The rotational axis is defined by a straight line between two non-coincidentgeometry points. (AP1, AP2)

VECTOR - The rotational axis is defined by the coordinate position and direction of avector. (X0, Y0, Z0, XA, YA, ZA)

SYSTEM [current active coordinate system]Label number of a coordinate system. One of the axes of this coordinate system may be usedto define the rotational axis, via parameter AXIS, when MODE = AXIS.

AXIS [XL]Selects the axis of the coordinate system, given by parameter SYSTEM, to be used as the axisof rotation. {XL/YL/ZL}

ALINELabel number of the geometry line used to define the rotational axis. The direction of the axisis taken from the start point of the line to the end point of the line.

AP1, AP2Label numbers of the geometry points used to define the rotational axis. The direction of theaxis is taken from point AP1 to point AP2.

AXIS-ROTATION


Chap. 7 Model definition AXIS-ROTATION

X0, Y0, Z0 [0.0, 0.0, 0.0]The coordinates (in global coordinates) of the starting position of the vector that defines therotational axis.

XA, YA, ZA [1.0, 0.0, 0.0]The direction (in global coordinates) of the vector that defines the rotational axis.

Auxiliary commands

LIST AXIS-ROTATION FIRST LASTDELETE AXIS-ROTATION FIRST LAST



EG-SUBSTRUCTURE NEG

substructurei egi

Creates substructures as sets of existing element groups.

NEG [1]The maximum number of element groups to be allocated to one substructure.

substructureiLabel number of a new substructure.

egiLabel number of element group in main structure.

EG-SUBSTRUCTURE



ANALYTICAL-RIGID-TARGET ANALYTICAL X0 Y0 Z0 RADIUS GTYPE GNAME

Command ANALYTICAL-RIGID-TARGET defines parameters for analytical rigid targetcontact analysis.

Note:This command is only available for node-to-node contact (i.e., NODETONODE=YES in theCGROUP CONTACT... command).

ANALYTICAL [NONE]Analytical rigid target type:

NONE Analytical rigid target is not used.

PLANE Infinite plane.

SPHERE Sphere (3D), or circle (2D).

CYLINDER Infinite cylinder.

X0 [0.0]Y0 [0.0]Z0 [0.0]Global cartesian component of:

- initial plane normal verctor inside the target body (ANALYTICAL=PLANE).

- initial cylinder axis verctor (ANALYTICAL=CYLINDER).

RADIUS [0.0]Radius of sphere (ANALYTICAL=SPHERE) or cylinder (ANALYTICAL=CYLINDER).

GTYPE [POINT]Geometry type for reference node: node or point. {NODE/POINT}

GNAMELabel number of reference node or point. An existing label number must be specified.

Auxiliary commands

LIST ANALYTICAL-RIGID-TARGET

ANALYTICAL-RIGID-TARGET


Sec. 7.5 Contact conditions

CONTACT-CONTROL CONTACT -ALGORITHM XCONT-ALGORITHMDISPLACEMENT NSUPPRESS DAMPINGDAMP-NORMAL DAMP-TANGENTIALTENSION-CONSISTENT CSTYPE FRICTION-ALGORITHMPOST-IMPACT RT-SUBD SEGMENT-INNER-ITERATIONRT-ALGORITHM

Specifies certain parameters controlling the behavior of the algorithms used in modelingcontact. For further details on these parameters, please consult the Theory and ModelingGuide.

CONTACT-ALGORITHM [CONSTRAINT-FUNCTION]Selects the default algorithm used to solve contact problems in implicit analysis.{CONSTRAINT-FUNCTION / SEGMENT-METHOD / RIGID-TARGET}

XCONT-ALGORITHM [KINEMATIC-CONSTRAINT]Selects the default algorithm used to solve contact problems in explicit analysis.{KINEMATIC-CONSTRAINT / PENALTY / EXPLICIT-RIGID-TARGET}

DISPLACEMENT [LARGE]Specifies the default displacement formulation used for contact analysis. A different formula-tion may be selected for each individual contact group via the CGROUP command. {LARGE/SMALL}

LARGE Large displacement is assumed for contact where the contact search is per-formed in each iteration to generate new contact constraints.

SMALL Small displacement is assumed for contact. The contact constraints are gener-ated once in the beginning of the analysis and kept constant throughout theanalysis.

NSUPPRESS [0]Indicates the number of iterations for which previous target segments are stored for contactornodes -- in order to suppress oscillation between adjacent segments. Such oscillation canoccur when a contactor node approaches the junction between two adjacent target segments.Use of NSUPPRESS > 0 allows for such oscillation to be detected and eliminated.NSUPPRESS = 0 (the default) indicates that no such checking and associated storage isrequired. {≥ 0}

For NSUPPRESS >0, ADINA stores all target segments that have previously (during equilib-rium iterations) come into contact with a contactor node. To limit the amount of memoryrequired, NSUPPRESS is limited to a maximum value of 99.

CONTACT-CONTROL


Chap. 7 Model definition CONTACT-CONTROL

Notes:1 NSUPPRESS has no effect if the node-to-node contact algorithm is used.2 NSUPPRESS should be less than the maximum number of equilibrium iterations.

DAMPING [NO]Indicates whether damping stabilization is applied for contact analysis. This feature isgenerally useful when rigid body motion exists in a model. {NO/INITIAL/CONSTANT}

INITIAL Damping is applied at the first time step only. The specified dampingcoefficients are applied and ramped down to zero by the end of the first timestep.

CONSTANT The specified damping coefficients are applied at all time steps.

DAMP-NORMAL [0.0]

Specified the normal damping coefficient. { ≥ 0.0 }

DAMP-TANGENTIAL [0.0]

Specified the tangential damping coefficient. { ≥ 0.0 }

TENSION-CONSISTENT [NO] Specifies whether to allow tensile consistent contact forces (quadratic 3D elements only).{YES/NO}

CSTYPE [NEW]Selects the type of contact segment to use. {OLD/NEW}

OLD Use the old contact segment.

NEW Use the new contact segment.

FRICTION-ALGORITHM [CURRENT]Selects which friction algorithm is used in the solution. {V83/CURRENT}

POST-IMPACT [YES]Indicates whether the post-impact correction of velocities and accelerations is performedalong with the displacement constraint in dynamic contact problems. {YES/NO}

RT-SUBD [MAGNITUDE]Selects the subdivision scheme used in the rigid-target algorithm when the tensile contactforce (and penetration if selected) is too large. Used only for the rigid-target contact algo-rithm of version 8.3. {MAGNITUDE/ATS}


Sec. 7.5 Contact conditionsCONTACT-CONTROL

MAGNITUDE Subdivision is based on the magnitude of the tensile contact force (andpenetration), i.e., the larger the magnitude, the smaller will be thesubdivided time step size.

ATS Subdivision is based on the global automatic time stepping (ATS)subdivsion settings.

SEGMENT-INNER-ITERATION [YES]Indicates whether the inner iteration loop is to be performed for the segment method contactalgorithm. {YES/NO}

RT-ALGORITHM [CURRENT]Selects the rigid-target contact algorithm. Details are in Chapter 4 of the ADINA Theory andModeling Guide. {V83/CURRENT}

V83 Use the rigid-target contact algorithm of ADINA version 8.3 and earlier

CURRENT Use the rigid-target contact algorithm of the current ADINA version.

Auxiliary commands

LIST CONTACT-CONTROL






CGROUP CONTACT2

This command is split, for better readability, based on the contact algorithm. There are 6possibilities:

Implicit analysis1. Constraint Function Algorithm

- ALGORITHM=CONSTRAINT-FUNCTION- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-

CONTROL)=CONSTRAINT-FUNCTION2. Segment Method Algorithm

- ALGORITHM=SEGMENT- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-

CONTROL)=SEGMENT3. Rigid Target Algorithm

- ALGORITHM=RIGID-TARGET- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-

CONTROL)=RIGID-TARGET

Explicit analysis4. Kinematic Constraint Algorithm

- XALGORITHM=KINEMATIC-CONSTRAINT- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-

CONTROL)= KINEMATIC-CONSTRAINT5. Penalty Algorithm

- XALGORITHM=PENALTY- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-

CONTROL)=PENALTY6. Rigid Target Algorithm

- XALGORITHM=EXPLICIT-RIGID-TARGET- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-

CONTROL)=EXPLICIT-RIGID-TARGET

Note that:- Algorithms #1, #2, #4 support node-to-node contact (the default is node-to-

segment) via parameter NODETONODE=YES.- Algorithms #1, #2 support tied contact via parameter TIED=SMALL

Auxiliary Commands

LIST CGROUP2 FIRST LASTDELETE CGROUP2 FIRST LAST NODES

CGROUP CONTACT2



NODES = YES (the default) will remove nodes which were only attached to contactsegments in the deleted contact group.

The summary of parameters applicable for each contact algorithm is presented in two tablesfollowing the command descriptions for the 3D contact command (CGROUP CONTACT3).One table is for implicit analysis and the other for explicit analysis.

CGROUP CONTACT2



Case 1: Implicit � Constraint Function Algorithm

CGROUP CONTACT2 NAME ALGORITHM NODETONODE DISPLACEMENTFRICTION CFACTOR1 DEPTH TIED TIED-OFFSETOFFSET OFFSET-TYPE FORCES TRACTIONSCONTINUOUS-NORMAL DIRECTION

TBIRTH TDEATH INITIAL-PENETRATION TIME-PENETRATION GAP-VALUE CS-EXTENSION EPSNEPST CONSISTENT-STIFF FRIC-DELAY USER-FRICTIONSUBTYPE

HHATTMC FCTMC FTTMC EKTMC

Activated when:- ALGORITHM=CONSTRAINT-FUNCTION- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-

CONTROL)=CONSTRAINT-FUNCTION

The following superscripts are used for some of the parameters:

1. Only applicable to (the default) node-to-segment contact2. Only applicable to node-to-node contact

The absence of a superscript indicates general applicability.

The CGROUP parameters are divided into 3 subgroups: Basic, Advanced, and Multiphysics:

Basic parameters

NAME [(current highest contact group label number) + 1]Label number of the contact group to be defined.

ALGORITHM [DEFAULT]Selects the contact algorithm for current group if the analysis is implicit. If DEFAULT isselected the algorithm type is determined based on the CONTACT-ALGORITHM parameterof the MASTER command. See comment above for activating the current contact algorithm.{DEFAULT/ CONSTRAINT-FUNCTION/ SEGMENT-METHOD/ RIGID-TARGET}

NODETONODE [NO]Indicates whether node-to-segment or node-to-node contact algorithm is used by the contactgroup. {YES/NO}

CGROUP CONTACT2



NO - Use node-to-segment contactYES - Use node-to-node contact

DISPLACEMENT 1 [DEFAULT]Specifies the displacement formulation used for this contact group. {DEFAULT/LARGE/

SMALL}

DEFAULT - The displacement formulation specified in the CONTACT-CONTROLcommand is used.

LARGE - Large displacement is assumed for contact where the contact search isperformed in each iteration to generate new contact constraints.

SMALL - Small displacement is assumed for contact. The contact constraints aregenerated once in the beginning of the analysis and kept constantthroughout the analysis.

FRICTION [0.0]Default coefficient of Coulomb friction. FRICTION = 0.0 indicates frictionless contact.Contact pairs can set their own friction coefficient.

CFACTOR1 [0.0]Compliance factor for all contact surfaces in this contact group. {≥ 0.0}

DEPTH 1 [0.0] If DEPTH > 0.0, then penetration is detected when the penetration depth is less than orequal to DEPTH, and if the penetration distance is greater than DEPTH, penetration isdeemed not to occur.

TIED 1 [NO]Indicates the type of TIED contact. This parameter is ignored when PENETRATION-ALGORITHM = TWO. {NO/SMALL}

NO - No TIED contact.SMALL - Small displacement is used in TIED contact.

TIED-OFFSET 1 [0.0]If TIED = SMALL, contactor nodes are tied to target if the gap between them is less than orequal to this parameter. This parameter is ignored when TIED = NO.

OFFSET [0.001]Two contact surfaces are constructed for each defined contact surface, each contact surfaceplaced a distance OFFSET from the defined contact surface. { ≥ 0.0}

Note: The OFFSET parameter specifies the default offset distance. For each individual

CGROUP CONTACT2



contact surface, a different offset distance can be specified using the commandCS-OFFSET.

OFFSET-TYPE [CONSTANT]Specifies the type of offset to be used for contact surfaces belonging to this group.{CONSTANT/TRUE/NONE}

CONSTANT - Constant offset as specified by the parameter OFFSET is used.See note under OFFSET.

TRUE - The actual shell half thickness is used as the offset distance even forlarge strains.

NONE - No offset is used (regardless of the value of the parameter OFFSET).

FORCES 1 [YES]Indicates whether or not concentrated contact nodal forces are calculated for every contactsurface node of this contact group. The contact forces are evaluated with respect to theglobal Cartesian coordinate system. {YES/NO}

Note: - If NODETONODE = YES, nodal forces are always calculated and this parameter isignored.

- The combination FORCES = NO, TRACTIONS = NO is not permitted.

TRACTIONS 1 [YES]Indicates whether or not contactor segment tractions (and concentrated contact nodal forcesat solitary nodes in contact) are calculated for every contactor surface of this contact group.{YES/NO}

Note: The combination FORCES = NO, TRACTIONS = NO is not permitted.

CONTINUOUS-NORMAL 1 [YES if PENETRATION = ONE][NO if PENETRATION = TWO]

Indicates whether or not a continuous (interpolated) contact segment normal is to be used forcontact surfaces in the contact group. {YES/NO}

DIRECTION 2 [NORMAL]Specifies the vector used to describe the normal direction for a nodal pair in node-to-nodecontact. {NORMAL/VECTOR}

NORMAL - Use the normal vector inside the target body.VECTOR - Use the vector connecting target and contactor nodes.

CGROUP CONTACT2



Advanced parameters

TBIRTH 1 [0.0]TDEATH 1 [0.0]The birth and death times for the whole contact group. If TBIRTH=0.0 and TDEATH=0.0,the birth and death feature is not used.

INITIAL-PENETRATION 1 [ALLOWED]Initial contactor node penetration flag.{ALLOWED/PRINT/DISCARDED/GAP-OVERRIDE}

ALLOWED - Any initial penetration of a contactor node into a target surface iseliminated either in the first solution step or over a specified timeinterval (see TIME-PENETRATION parameter). In successive stepseach contactor node cannot penetrate.

PRINT - Same as ALLOWED, but a printout of the penetrating contactor nodesis produced.

DISCARDED - Any initial penetration of a contactor node into a target surface is noteliminated in the first solution step. In successive steps eachcontactor node is allowed to penetrate up to the initial penetration.

GAP-OVERRIDE - Initial penetrations or gaps are overridden by user-specified GAP-VALUE parameter.

TIME-PENETRATION 1 [0.0]Specifies the time used to eliminate any initial penetration. {≥ 0.0}

If INITIAL-PENETRATION = ALLOWED or PRINT, and TIME-PENETRATION=0.0, thenthe initial penetration is eliminated in the first time step. By specifying TIME-PENETRATION> 0.0, initial penetration can be eliminated gradually. This may help in the convergence ofthe solution.

GAP-VALUE 1 [0.0]Specifies a constant gap distance between the contactor and target surfaces when INITIAL-PENETRATION = GAP-OVERRIDE. This value overrides the value measured from thecontact surfaces. A negative GAP-VALUE means initial penetrations which will be eliminated.

CS-EXTENSION 1 [0.001]The maximum non-dimensional extension of target contact surfaces.{0.0 < CS-EXTENSION < 0.1}

EPSN [0.0]The normal contact w-function εΝ parameter. Guidelines for choosing this parameter areprovided in the ADINA-AUI Online Help. When EPSN = 0.0, ADINA automatically deter-mines this parameter.

CGROUP CONTACT2


Sec. 7.5 Contact conditionsCGROUP CONTACT2

EPST [0.0]The friction contact v-function εT parameter. Guidelines for choosing this parameter areprovided in the ADINA-AUI Online Help. When EPST = 0.0, ADINA automatically sets it to0.001.

CONSISTENT-STIFF 1 [DEFAULT]Indicates whether consistent contact stiffness is used. {DEFAULT/OFF/ON}

When CONSISTENT-STIFF = DEFAULT, consistent contact stiffness is used if the followingconditions are all satisfied: - the skyline direct equation solver is not used, i.e., SOLVER is not set to SKYLINE in the

MASTER command, - CONTINUOUS-NORMAL = NO is specified. - Old contact surfaces are used (CSTYPE=OLD in CONTACT-CONTROL command).Otherwise, the default is set to off.

Note that this option is not used in small displacement analysis (DISPLACEMENT=SMALL inthe KINEMATICS command). It is also not used if small displacements are selected in thecontact group (DISPLACEMENT parameter).

The use of consistent contact stiffness increases the size of the stiffness matrix. However, itcan improve the convergence rate in contact problems, especially in cases where the normalvector between the contacting surfaces frequently changes direction during the analysis.

FRIC-DELAY [NO]Indicates whether the application of friction is delayed, i.e., applied one time step aftercontact is established. {NO/YES}

USER-FRICTION 1 [NO]Indicates whether a user-supplied friction law is used for this contact group. If USER-FRICTION=YES is specified, additional parameters for defining the user-supplied friction lawcan be input using the USER-FRICTION command. {YES/NO}

SUBTYPE [DEFAULT]Indicates the type of CONTACT2 contact-surfaces, all defined in the global YZ plane.{DEFAULT/AXISYMMETRIC/STRAIN/STRESS}

DEFAULT - Subtype automatically determined based on underlying elements.AXISYMMETRIC - Axisymmetric contact-surfaces. The global Z axis is that of

rotational symmetry, and Y is the radial direction (Y ≥ 0).STRAIN - Planar contact-surfaces.STRESS - Planar contact-surfaces (identical to STRAIN).



Multiphysics parameters

HHATTMC 1 [0.0]Contact heat transfer coefficient used for thermo-mechanical coupling (TMC) analysis.{ ≥ 0.0}

FCTMC 1 [0.5]Friction contact heat distribution fraction coefficient for contactor used for thermo-mechani-cal coupling (TMC) analysis. {0.0 ≤ FCTMC ≤ 1.0}

FTTMC 1 [0.5]Friction contact heat distribution fraction coefficient for target used for thermo-mechanicalcoupling (TMC) analysis. {0.0 ≤ FTTMC ≤ 1.0}

EKTMC 1 [0.0]Electrical conductivity for current flow through contact surfaces in a thermo-mechanicalcoupling (TMC) analysis. (Units: electrical conductance/length, e.g., Siemens/m) {≥ 0.0}

CGROUP CONTACT2



Case 2: Implicit � Segment Method Algorithm

CGROUP CONTACT2 NAME ALGORITHM NODETONODE DISPLACEMENTFRICTION DEPTH TIED TIED-OFFSET OFFSETOFFSET-TYPE FORCES TRACTIONS CONTINUOUS-NORMAL DIRECTION

TBIRTH TDEATH INITIAL-PENETRATION TIME-PENETRATION GAP-VALUE CS-EXTENSIONCONSISTENT-STIFF FRIC-DELAY USER-FRICTIONSUBTYPE

Activated when:- ALGORITHM=SEGMENT-METHOD- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-

CONTROL)=SEGMENT-METHOD

All the parameters for the Segment Method Algorithm are described in Case 1: Implicit -Constraint Function Algorithm

CGROUP CONTACT2



Case 3: Implicit - Rigid Target Algorithm

CGROUP CONTACT2 NAME ALGORITHM FRICTION DEPTH TBIRTHTDEATH NORMAL-STIFFNESS TANGENTIAL-STIFFNESSPTOLERANCE OFFSET OFFSET-TYPE RESIDUAL-FORCELIMIT-FORCE ITERATION-LIMIT RTP-CHECK RTP-MAXSUBTYPE RIGID-TARGET

Activated when:- ALGORITHM=RIGID-TARGET- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-CONTROL)=

RIGID-TARGET

Note: This algorithm is equivalent to the Old 3D Implicit Rigid Target Algorithm.

For the following parameters, see description for Case 1: Implicit - Constraint FunctionAlgorithm

NAMEALGORITHMFRICTIONDEPTHTBIRTHTDEATHSUBTYPE

NORMAL-STIFFNESS [1.0E11]Contact stiffness in direction normal to the contact surface.

TANGENTIAL-STIFFNESS [0.0]Contact stiffness in direction tangential to the contact surface.

PTOLERANCE [1.0E-8]Maximum allowable penetration of target surface. If penetration is less than PTOLERANCE,contact is assumed to be not yet established for the node in consideration.

OFFSET [0.0]The actual contact surface is raised a distance OFFSET away from the surface defined by thenodes. { ≥ 0.0}

OFFSET-TYPE [CONSTANT]Specifies the type of offset to be used for contact surfaces belonging to this group.{CONSTANT/TRUE}

CGROUP CONTACT2



CONSTANT - Constant offset as specified by the parameter OFFSET is used. TRUE - The actual shell half thickness is used as the offset distance even for

large strains.

RESIDUAL-FORCE [0.001]Minimum tensile contact force required to change state of a contact node from "node incontact" to "free node". If the normal component of a tensile contact force is less thanRESIDUAL-FORCE, a "node in contact" remains in contact. If the normal tensile force isgreater than RESIDUAL-FORCE, a "node in contact" becomes a "free node".

LIMIT-FORCE [1.0]Limit (maximum) for the sum of all contact forces for nodes changing from the state of "nodein contact" to "free node". If the absolute value of the sum of the forces is bigger thanLIMIT-FORCE, then the automatic time stepping (ATS) method will be activated to subdividethe current time step into smaller time increments.

ITERATION-LIMIT [2]Maximum number of ATS time step subdivisions due to LIMIT-FORCE criterion describedabove.

RTP-CHECK [NO]Specifies whether penetration is checked (in addition to checking the tensile contact force)against the maximum allowable penetration when the rigid-target algorithm is used. {NO/RELATIVE/ABSOLUTE}

NO - Penetration is not checked. Note that with this setting, there is apossibility that the rigid target surface may excessively penetrate thecontactor surface.

RELATIVE - Penetration is checked and RTP-MAX is specified as a factor of theoverall model size.

ABSOLUTE - Penetration is checked and RTP-MAX is the absolute value ofpenetration allowed.

Note that if penetration check is selected, the program will perform subdivision of time stepsif the penetration exceeds the maximum allowable penetration. The subdivision scheme isspecified in the RT-SUBD parameter in the CONTACT-CONTROL command.

RTP-MAX [0.001]Specifies the maximum allowable penetration when the rigid target algorithm is used.RTP-MAX is either a factor of the model size or an absolute value depending on theRTP-CHECK parameter. {> 0.0}

CGROUP CONTACT2






RIGID-TARGET (obsolete) [NO]Indicates whether rigid target contact algorithm is used for current contact group. It ispreferable to set ALGORITHM instead. {NO/YES}

CGROUP CONTACT2



Case 4: Explicit - Kinematic Constraint Algorithm

CGROUP CONTACT2 NAME XALGORITHM NODETONODE DISPLACEMENTFRICTION DEPTH OFFSET OFFSET-TYPE FORCESTRACTIONS DIRECTION

TBIRTH TDEATH INITIAL-PENETRATIONTIME-PENETRATION GAP-VALUE CS-EXTENSIONSUBTYPE

Activated when:- XALGORITHM=KINEMATIC-CONSTRAINT- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CON-

TROL)= KINEMATIC-CONSTRAINT




The CGROUP parameters are divided into 2 subgroups: Basic and Advanced.

Basic parameters


XALGORITHM [DEFAULT]Selects the contact algorithm for current group if the analysis is explicit. If DEFAULT isselected the algorithm type is determined based on XCONT-ALGORITHM variable of theCONTACT-CONTROL command. See comment above for activating the current contactalgorithm.{DEFAULT/KINEMATIC-CONSTRAINT/PENALTY/EXPLICIT-RIGID-TARGET}



CGROUP CONTACT2




SMALL}




FRICTION [0.0]Default coefficient of Coulomb friction. FRICTION = 0.0 indicates frictionless contact.Contact pairs can set their own friction coefficients.

DEPTH 1 [0.0]If DEPTH > 0.0, then penetration is detected when the penetration depth is less than orequal to DEPTH, and if the penetration distance is greater than DEPTH, penetration isdeemed not to occur.

OFFSET [0.001]Two contact surfaces are constructed for each defined contact surface, each contact surfaceplaced a distance OFFSET from the defined contact surface. { ≥ 0.0}

Note: The OFFSET parameter specifies the default offset distance. For each individualcontact surface, a different offset distance can be specified using the commandCS-OFFSET.






CGROUP CONTACT2









Advanced parameters








CGROUP CONTACT2









CGROUP CONTACT2



Case 5: Explicit � Penalty Algorithm

CGROUP CONTACT2 NAME XALGORITHM DISPLACEMENT FRICTIONDEPTH OFFSET OFFSET-TYPE FORCES TRACTIONSXKN-CRIT XK-NORMAL XKT-CRIT XK-TANGENTXDAMP XNDAMP

TBIRTH TDEATH INITIAL-PENETRATIONTIME-PENETRATION GAP-VALUE CS-EXTENSIONSUBTYPE

Activated when:

- XALGORITHM=PENALTY- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)=

PENALTY

For the following parameters, see description for Case 4: Explicit - Kinematic constraintalgorithm

NAMEXALGORITHMDISPLACEMENTFRICTIONDEPTHOFFSETOFFSET-TYPEFORCESTRACTIONSTBIRTHTDEATHINITIAL-PENETRATIONTIME-PENETRATIONGAP-VALUECS-EXTENSIONSUBTYPE

XKN-CRIT [GLOBAL]Criterion for evaluation of normal penalty stiffness.{GLOBAL/USER}

GLOBAL - Penalty stiffness will be determined globally for the whole contact group.USER - The user sets the penalty stiffness.

CGROUP CONTACT2



XK-NORMAL [0.0]The normal stiffness. It must be greater than 0.0. It is only used for XKN-CRIT=USER.

XKT-CRIT [GLOBAL]Criterion for evaluation of tangential penalty stiffness. {GLOBAL/USER}


XK-TANGENT [0.0]The tangetial stiffness. It must be greater than 0.0. It is only used for XKT-CRIT=USER.

XDAMP [NO]Indicates whether normal damping (proportional to the rate of penetration) is used.{NO/RELATIVE/ABSOLUTE}

NO - Damping is not used, i.e., XNDAMP parameter is ignored.RELATIVE - Damping is used and XNDAMP is a factor of the critical damping, i.e., the

normal contact damping coefficient is given by XNDAMP multiplied bythe critical damping. This is the recommended choice if damping is used.

ABSOLUTE - Damping is included and the normal contact damping coefficient isspecified directly by XNDAMP.

XNDAMP [0.1]Specifies the relative or absolute normal damping coefficient (for normal penalty stiffness).{ ≥ 0.0}

CGROUP CONTACT2



Case 6: Explicit � Rigid Target Algorithm

CGROUP CONTACT2 NAME XALGORITHM FRICTION DEPTH TBIRTHTDEATH NORMAL-STIFFNESS TANGENTIAL-STIFFNESS PTOLERANCE OFFSET OFFSET-TYPESUBTYPE RIGID-TARGET

Activated when:- XALGORITHM=EXPLICIT-RIGID-TARGET- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)=

EXPLICIT-RIGID-TARGET

Note: This algorithm is equivalent to the old 3D Rigid Target Algorithm.


NAMEXALGORITHMFRICTIONDEPTHTBIRTHTDEATHSUBTYPE






CGROUP CONTACT2








RIGID-TARGET (obsolete) [NO]Indicates whether rigid target contact algorithm is used for current contact group. It ispreferable to set XALGORITHM instead. {NO/YES}

CGROUP CONTACT2





Chap. 7 Model definition CGROUP CONTACT3

CGROUP CONTACT3

This command is split, for better readability, based on the contact algorithm. There are 8possibilities:

Implicit analysis1. Constraint Function Algorithm

- ALGORITHM=CONSTRAINT-FUNCTION- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-

CONTROL)=CONSTRAINT-FUNCTION2. Segment Method Algorithm

- ALGORITHM=SEGMENT- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-

CONTROL)=SEGMENT3. Rigid Target Algorithm

- ALGORITHM=RIGID-TARGET- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-

CONTROL)=RIGID-TARGET4. Old Rigid Target Algorithm (version 8.3 � now obsolete)

- Same as Case #3 with RT-ALGORITHM (in CONTACT-CONTROL)=V83

Explicit analysis5. Kinematic Constraint Algorithm

- XALGORITHM=KINEMATIC-CONSTRAINT- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-

CONTROL)= KINEMATIC-CONSTRAINT6. Penalty Algorithm

- XALGORITHM=PENALTY- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-

CONTROL)=PENALTY7. Rigid Target Algorithm

- XALGORITHM=EXPLICIT-RIGID-TARGET- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-

CONTROL)=EXPLICIT-RIGID-TARGET8. Old Rigid Target Algorithm (version 8.3 � now obsolete)

- Same as Case #7 with RT-ALGORITHM (in CONTACT-CONTROL)=V83

Note that:- Algorithms #1, #2, #5 support node-to-node contact (the default is node-to-

segment) via parameter NODETONODE=YES.- Algorithms #1, #2 support tied contact via parameter TIED=SMALL- Algorithms #1, #2, #5, #6 support double-sided contact via parameter

PENETRATION-ALGORITHM=TWO



Auxiliary Commands

LIST CGROUP3 FIRST LASTDELETE CGROUP3 FIRST LAST NODES

NODES = YES (the default) will remove nodes which were only attached to contactsegments in the deleted contact group.

The summary of parameters applicable for each contact algorithm is presented in two tablesfollowing the command descriptions, one for implicit analysis and one for explicit analysis.


Chap. 7 Model definition CGROUP CONTACT3

Case 1: Implicit � Constraint Function Algorithm

CGROUP CONTACT3 NAME ALGORITHM NODETONODE DISPLACEMENTFRICTION CFACTOR1 PENETRATION-ALGORITHMDEPTH TIED TIED-OFFSET OFFSET OFFSET-TYPEFORCES TRACTIONS CONTINUOUS-NORMALDIRECTION

TBIRTH TDEATH INITIAL-PENETRATION TIME-PENETRATION GAP-VALUE CS-EXTENSION EPSNEPST CONSISTENT-STIFF FRIC-DELAY USER-FRICTION

HHATTMC FCTMC FTTMC EKTMC

Activated when:- ALGORITHM=CONSTRAINT-FUNCTION- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-

CONTROL)=CONSTRAINT-FUNCTION




The CGROUP parameters are divided into 3 subgroups: Basic, Advanced, and Multiphysics:

Basic parameters


ALGORITHM [DEFAULT]Selects the contact algorithm for current group if the analysis is implicit. If DEFAULT isselected the algorithm type is determined based on the CONTACT-ALGORITHM parameterof the MASTER command. See comment above for activating the current contact algorithm.{DEFAULT/ CONSTRAINT-FUNCTION/ SEGMENT-METHOD/ RIGID-TARGET}






SMALL}




FRICTION [0.0]Default coefficient of Coulomb friction. FRICTION = 0.0 indicates frictionless contact.Contact pairs can set their own friction coefficient.

CFACTOR1 [0.0]Compliance factor for all contact surfaces in this contact group. {≥ 0.0}

PENETRATION-ALGORITHM 1 [ONE]The penetration algorithm can be chosen as follows:

ONE - Each contact surface is single-sided. You must insure that each contact surfacehas proper orientation.

TWO - Each contact surface is double-sided. The contact surface orientation does notmatter. It is recommended that the nodal offset be greater than zero in this case.

DEPTH 1 [0.0]This parameter is used when PENETRATION-ALGORITHM=ONE. If DEPTH > 0.0, thenpenetration is detected when the penetration depth is less than or equal to DEPTH, and if thepenetration distance is greater than DEPTH, penetration is deemed not to occur.

TIED 1 [NO]Indicates the type of TIED contact. This parameter is ignored when PENETRATION-ALGORITHM = TWO. {NO/SMALL}

NO - No TIED contact.SMALL - Small displacement is used in TIED contact.



TIED-OFFSET 1 [0.0]If TIED = SMALL, contactor nodes are tied to target if the gap between them is less than orequal to this parameter. This parameter is ignored when TIED = NO.

OFFSET [0.0 if PENETRATION = ONE][0.001 if PENETRATION = TWO]

For PENETRATION-ALGORITHM=ONE, the actual contact surface is raised a distanceOFFSET away from the surface defined by the nodes. { ≥ 0.0}

For PENETRATION-ALGORITHM=TWO, two contact surfaces are constructed for eachdefined contact surface, each contact surface placed a distance OFFSET from the definedcontact surface. { ≥ 0.0}











CGROUP CONTACT3



CONTINUOUS-NORMAL 1 [YES if PENETRATION = ONE][NO if PENETRATION = TWO]

Indicates whether or not a continuous (interpolated) contact segment normal is to be used forcontact surfaces in the contact group. {YES/NO}



Advanced parameters









CGROUP CONTACT3





EPSN [0.0]The normal contact w-function εΝ parameter. Guidelines for choosing this parameter areprovided in the ADINA-AUI Online Help. When EPSN = 0.0, ADINA automatically deter-mines this parameter.

EPST [0.0]The friction contact v-function εT parameter. Guidelines for choosing this parameter areprovided in the ADINA-AUI Online Help. When EPST = 0.0, ADINA automatically sets it to0.001.

CONSISTENT-STIFF 1 [DEFAULT]Indicates whether consistent contact stiffness is used. {DEFAULT/OFF/ON}

When CONSISTENT-STIFF = DEFAULT, consistent contact stiffness is used if the followingconditions are all satisfied: - the skyline direct equation solver is not used, i.e., SOLVER is not set to SKYLINE in the

MASTER command, - CONTINUOUS-NORMAL = NO is specified. - Old contact surfaces are used (CSTYPE=OLD in CONTACT-CONTROL command).Otherwise, the default is set to off.

Note that this option is not used in small displacement analysis (DISPLACEMENT=SMALL inthe KINEMATICS command). It is also not used if small displacements are selected in thecontact group (DISPLACEMENT parameter).

The use of consistent contact stiffness increases the size of the stiffness matrix. However, itcan improve the convergence rate in contact problems, especially in cases where the normalvector between the contacting surfaces frequently changes direction during the analysis.

FRIC-DELAY [NO]Indicates whether the application of friction is delayed, i.e., applied one time step aftercontact is established. {NO/YES}

CGROUP CONTACT3



USER-FRICTION 1 [NO]Indicates whether a user-supplied friction law is used for this contact group. If USER-FRICTION=YES is specified, additional parameters for defining the user-supplied friction lawcan be input using the USER-FRICTION command. {YES/NO}

Multiphysics parameters

HHATTMC 1 [0.0]Contact heat transfer coefficient used for thermo-mechanical coupling (TMC) analysis.{ ≥ 0.0}

FCTMC 1 [0.5]Friction contact heat distribution fraction coefficient for contactor used for thermo-mechani-cal coupling (TMC) analysis. {0.0 ≤ FCTMC ≤ 1.0}

FTTMC 1 [0.5]Friction contact heat distribution fraction coefficient for target used for thermo-mechanicalcoupling (TMC) analysis. {0.0 ≤ FTTMC ≤ 1.0}

EKTMC 1 [0.0]Electrical conductivity for current flow through contact surfaces in a thermo-mechanicalcoupling (TMC) analysis. (Units: electrical conductance/length, e.g., Siemens/m) {≥ 0.0}

CGROUP CONTACT3



Case 2: Implicit � Segment Method Algorithm

CGROUP CONTACT3 NAME ALGORITHM NODETONODE DISPLACEMENTFRICTION PENETRATION-ALGORITHM DEPTH TIEDTIED-OFFSET OFFSET OFFSET-TYPE FORCESTRACTIONS CONTINUOUS-NORMAL DIRECTION

TBIRTH TDEATH INITIAL-PENETRATION TIME-PENETRATION GAP-VALUE CS-EXTENSIONCONSISTENT-STIFF FRIC-DELAY USER-FRICTION

Activated when:- ALGORITHM=SEGMENT-METHOD- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-

CONTROL)=SEGMENT-METHOD

All the parameters for the Segment Method Algorithm are described in Case 1: Implicit -Constraint Function Algorithm

CGROUP CONTACT3



Case 3: Implicit - Rigid Target Algorithm

CGROUP CONTACT3 NAME ALGORITHM FRICTION DEPTH TBIRTHTDEATH NORMAL-STIFFNESS TENSILE-FORCESLIDING-VELOCITY OSCILLATION-CHECKING GAP-BIASOFFSET OFFSET-TYPE OFFSET-DETECT TENS-CONTACTFREE-OVERLAP GAP-PUSH RIGID-TARGET

Activated when:- ALGORITHM=RIGID-TARGET- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-CON-

TROL)= RIGID-TARGET


NAMEALGORITHMFRICTIONDEPTHTBIRTHTDEATH


TENSILE-FORCE [0.001]The maximum tensile contact force allowed for a converged solution.{≥ 0.0}

SLIDING-VELOCITY [1E-10]The maximum sliding velocity used in modeling sticking friction. When the velocity is smallerthan SLIDING-VELOCITY, sticking is assumed; when the velocity is larger than SLIDING-VELOCITY, sliding is assumed. {>0.0}

OSCILLATION-CHECKING [5]The intent of this parameter is to increase the likelihood of convergence during the equilib-rium iterations. {≥ 0.0}

OSCILLATION-CHECKING=0 turns off oscillation checking.

OSCILLATION-CHECKING>0 signals oscillation checking after equilibrium iteration OSCIL-

CGROUP CONTACT3



LATION-CHECKING. For example, when OSCILLATION-CHECKING=5, then oscillationchecking is activated after equilibrium iteration 5.

Oscillation checking consists of two checks:

a) If a contactor node oscillates between two neighboring target segments during theequilibrium iterations, oscillation checking puts the contactor node into contact with theboundary edge between the target segments.

b) In analysis with friction, if the sliding velocity of a contactor node oscillates during theequilibrium iterations, oscillation checking puts the contactor node into sticking contact.

The oscillation check is only applied for the iteration in which the oscillation is detected.

GAP-BIAS [0.0]Contact is detected when the distance between the target and contactor (accounting for anyoffsets) is less than GAP-BIAS.

GAP-BIAS can be positive, negative or zero.




large strains.

OFFSET-DETECT [AUTOMATIC]This parameter determines the implementation of offsets for the current rigid-target contactalgorithm. {NORMALS/SPHERES/AUTOMATIC}

NORMALS - Two surfaces are constructed for each contactor surface: an uppersurface and a lower surface. These surface are constructed using theoffsets and the averaged contactor normals. Contact is then detectedbetween points on the constructed contactor surfaces and targetsurfaces.

SPHERES - A sphere with a radius equal to the offset is placed around eachcontactor node, and contact is detected between the spheres and thetarget surfaces.

CGROUP CONTACT3



AUTOMATIC - ADINA chooses the implementation based upon the shape of thetarget surfaces; if a target surface is flat or convex, spheres are used,otherwise normals are used.

TENS-CONTACT [NO]This parameter controls the use of the tensile contact feature. {NO/YES}

FREE-OVERLAP [NO]This parameter controls the use of the free overlap feature. {NO/YES}

GAP-PUSH [0.0]

This parameter controls the gap-push feature. { ≥ 0.0}


CGROUP CONTACT3



Case 4: Implicit - Old Rigid Target Algorithm (version 8.3 - now obsolete)

Note: This is an obsolete algorithm that should only be used for backward compatibility.

CGROUP CONTACT3 NAME ALGORITHM FRICTION DEPTH TBIRTHTDEATH NORMAL-STIFFNESS TANGENTIAL-STIFFNESSPTOLERANCE OFFSET OFFSET-TYPE RESIDUAL-FORCELIMIT-FORCE ITERATION-LIMIT RTP-CHECK RTP-MAXRIGID-TARGET

Activated when:- ALGORITHM=RIGID-TARGET- ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-CONTROL)=

RIGID-TARGET&- RT-ALGORITHM (in CONTACT-CONTROL)=V83


NAMEALGORITHMFRICTIONDEPTHTBIRTHTDEATH





CGROUP CONTACT3





large strains.

RESIDUAL-FORCE [0.001]Minimum tensile contact force required to change state of a contact node from "node incontact" to "free node". If the normal component of a tensile contact force is less thanRESIDUAL-FORCE, a "node in contact" remains in contact. If the normal tensile force isgreater than RESIDUAL-FORCE, a "node in contact" becomes a "free node".

LIMIT-FORCE [1.0]Limit (maximum) for the sum of all contact forces for nodes changing from the state of "nodein contact" to "free node". If the absolute value of the sum of the forces is bigger thanLIMIT-FORCE, then the automatic time stepping (ATS) method will be activated to subdividethe current time step into smaller time increments.

ITERATION-LIMIT [2]Maximum number of ATS time step subdivisions due to LIMIT-FORCE criterion describedabove.

RTP-CHECK [NO]Specifies whether penetration is checked (in addition to checking the tensile contact force)against the maximum allowable penetration when the rigid-target algorithm is used. {NO/RELATIVE/ABSOLUTE}

NO - Penetration is not checked. Note that with this setting, there is apossibility that the rigid target surface may excessively penetrate thecontactor surface.

RELATIVE - Penetration is checked and RTP-MAX is specified as a factor of theoverall model size.

ABSOLUTE - Penetration is checked and RTP-MAX is the absolute value ofpenetration allowed.

Note that if penetration check is selected, the program will perform subdivision of time stepsif the penetration exceeds the maximum allowable penetration. The subdivision scheme isspecified in the RT-SUBD parameter in the CONTACT-CONTROL command.

RTP-MAX [0.001]Specifies the maximum allowable penetration when the rigid target algorithm is used.

CGROUP CONTACT3



RTP-MAX is either a factor of the model size or an absolute value depending on theRTP-CHECK parameter. {> 0.0}


CGROUP CONTACT3



Case 5: Explicit - Kinematic Constraint Algorithm

CGROUP CONTACT3 NAME XALGORITHM NODETONODE DISPLACEMENTFRICTION PENETRATION-ALGORITHM DEPTHOFFSET OFFSET-TYPE FORCES TRACTIONSDIRECTION

TBIRTH TDEATH INITIAL-PENETRATIONTIME-PENETRATION GAP-VALUE CS-EXTENSION

Activated when:- XALGORITHM=KINEMATIC-CONSTRAINT- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CON-

TROL)= KINEMATIC-CONSTRAINT




The CGROUP parameters are divided into 2 subgroups: Basic and Advanced.

Basic parameters


XALGORITHM [DEFAULT]Selects the contact algorithm for current group if the analysis is explicit. If DEFAULT isselected the algorithm type is determined based on XCONT-ALGORITHM variable of theCONTACT-CONTROL command. See comment above for activating the current contactalgorithm.{DEFAULT/KINEMATIC-CONSTRAINT/PENALTY/EXPLICIT-RIGID-TARGET}



CGROUP CONTACT3




SMALL}




FRICTION [0.0]Default coefficient of Coulomb friction. FRICTION = 0.0 indicates frictionless contact.Contact pairs can set their own friction coefficients.

PENETRATION-ALGORITHM 1 [ONE]The penetration algorithm can be chosen as follows:

ONE - Each contact surface is single-sided. You must insure that each contact surface has proper orientation.

TWO - Each contact surface is double-sided. The contact surface orientation does not matter. It is recommended that the nodal offset be greater than zero in this case.

DEPTH 1 [0.0]This parameter is used when PENETRATION-ALGORITHM=ONE. If DEPTH > 0.0, thenpenetration is detected when the penetration depth is less than or equal to DEPTH, and if thepenetration distance is greater than DEPTH, penetration is deemed not to occur.

OFFSET [0.0 if PENETRATION = ONE][0.001 if PENETRATION = TWO]

For PENETRATION-ALGORITHM=ONE, the actual contact surface is raised a distanceOFFSET away from the surface defined by the nodes. { ≥ 0.0}

For PENETRATION-ALGORITHM=TWO, two contact surfaces are constructed for eachdefined contact surface, each contact surface placed a distance OFFSET from the definedcontact surface. { ≥ 0.0}


CGROUP CONTACT3














Advanced parameters



CGROUP CONTACT3











CGROUP CONTACT3



Case 6: Explicit � Penalty Algorithm

CGROUP CONTACT3 NAME XALGORITHM DISPLACEMENT FRICTIONPENETRATION-ALGORITHM DEPTH OFFSETOFFSET-TYPE FORCES TRACTIONS XKN-CRITXK-NORMAL XKT-CRIT XK-TANGENT XDAMPXNDAMP

TBIRTH TDEATH INITIAL-PENETRATIONTIME-PENETRATION GAP-VALUE CS-EXTENSION

Activated when:

- XALGORITHM=PENALTY- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)=

PENALTY


NAMEXALGORITHMDISPLACEMENTFRICTIONPENETRATION-ALGORITHMDEPTHOFFSETOFFSET-TYPEFORCESTRACTIONSTBIRTHTDEATHINITIAL-PENETRATIONTIME-PENETRATIONGAP-VALUECS-EXTENSION

XKN-CRIT [GLOBAL]Criterion for evaluation of normal penalty stiffness.{GLOBAL/USER}


CGROUP CONTACT3



XK-NORMAL [0.0]The normal stiffness. It must be greater than 0.0. It is only used for XKN-CRIT=USER.

XKT-CRIT [GLOBAL]Criterion for evaluation of tangential penalty stiffness. {GLOBAL/USER}


XK-TANGENT [0.0]The tangetial stiffness. It must be greater than 0.0. It is only used for XKT-CRIT=USER.

XDAMP [NO]Indicates whether normal damping (proportional to the rate of penetration) is used.{NO/RELATIVE/ABSOLUTE}

NO - Damping is not used, i.e., XNDAMP parameter is ignored.RELATIVE - Damping is used and XNDAMP is a factor of the critical damping, i.e., the

normal contact damping coefficient is given by XNDAMP multiplied bythe critical damping. This is the recommended choice if damping is used.

ABSOLUTE - Damping is included and the normal contact damping coefficient isspecified directly by XNDAMP.

XNDAMP [0.1]Specifies the relative or absolute normal damping coefficient (for normal penalty stiffness).{ ≥ 0.0}

CGROUP CONTACT3



Case 7: Explicit - Rigid Target Algorithm

CGROUP CONTACT3 NAME XALGORITHM FRICTION DEPTH TBIRTHTDEATH NORMAL-STIFFNESS SLIDING-VELOCITYGAP-BIAS OFFSET OFFSET-TYPE OFFSET-DETECTRIGID-TARGET

Activated when:- XALGORITHM=EXPLICIT-RIGID-TARGET- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CON-

TROL)= EXPLICIT-RIGID-TARGET


NAMEXALGORITHMFRICTIONDEPTHTBIRTHTDEATH


SLIDING-VELOCITY [1E-10]The maximum sliding velocity used in modeling sticking friction, used only when friction isincluded. When the velocity is smaller than SLIDING-VELOCITY, sticking is assumed; whenthe velocity is larger than SLIDING-VELOCITY, sliding is assumed. {>0.0}

GAP-BIAS [0.0]Contact is detected when the distance between the target and contactor (accounting for anyoffsets) is less than GAP-BIAS. GAP-BIAS can be positive, negative or zero.



CGROUP CONTACT3





OFFSET-DETECT [AUTOMATIC]This parameter determines the implementation of offsets for the current rigid-target contactalgorithm. {NORMALS/SPHERES/AUTOMATIC}

NORMALS - Two surfaces are constructed for each contactor surface: an uppersurface and a lower surface. These surface are constructed using theoffsets and the averaged contactor normals. Contact is then detectedbetween points on the constructed contactor surfaces and targetsurfaces.

SPHERES - A sphere with a radius equal to the offset is placed around eachcontactor node, and contact is detected between the spheres and thetarget surfaces.

AUTOMATIC - ADINA chooses the implementation based upon the shape of thetarget surfaces; if a target surface is flat or convex, spheres are used,otherwise normals are used.


CGROUP CONTACT3



Case 8: Explicit � Old Rigid Target Algorithm (version 8.3 � now obsolete)

Note: This is an obsolete algorithm that should only be used for backward compatibility

CGROUP CONTACT3 NAME XALGORITHM FRICTION DEPTH TBIRTHTDEATH NORMAL-STIFFNESS TANGENTIAL-STIFFNESS PTOLERANCE OFFSET OFFSET-TYPERIGID-TARGET

Activated when:- XALGORITHM=EXPLICIT-RIGID-TARGET- XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)=

EXPLICIT-RIGID-TARGET&- RT-ALGORITHM (in CONTACT-CONTROL)=V83


NAMEXALGORITHMFRICTIONDEPTHTBIRTHTDEATH





CGROUP CONTACT3







CGROUP CONTACT3



C O N TAC T ALGO RITHM

C O N STRAIN T-FUN C TIO N SEGM EN T-M ETHO D RIGID-TARGET

N AM EALGO RITHM

FRIC TIO NC FAC TO R1

O FFSETO FFSET- TYPE

EPSNEPST

FRIC -DELAYSUBTYPE 1

N AM EALGO RITHM

FRIC TIO NO FFSET

O FFSET-TYPE

FRIC - DELAYSUBTYPE 1

N AM EALGO RITHM

FRIC TIO NDEPTH

TBIRTH, TDEATHN O RM AL- STIFFN ESS

TEN SILE- FO RC EO FFSET

O FFSET-TYPESUBTYPE 1

SLIDIN G-VELO C ITY2

O SC ILLATIO N -C HEC K IN G2

GAPBIAS 2

O FFSET-DETEC T2

TEN S- C O N TAC T2

FREE-O VERLAP 2

GAP-PUSH2

TAN GEN TIAL-STIFFN ESS*PTO LERAN C E*

RESIDUAL-FO RC E*LIM IT- FO RC E*

ITERATIO N -LIM IT*RTP-C HEC K *

RTP- M AX*

N O DETO N O DE = N O

DISPLAC EM EN TPEN ETRATIO N -ALGO RITHM 2

DEPTHTIED

TIED-O FFSETFO RC ES

TRAC TIO N SC O N TIN UO US-N O RM AL

TBIRTH, TDEATHIN ITIAL- PEN ETRATIO N

TIM E-PEN ETRATIO NGAP-VALUE

C S-EXTEN SIO NC O N SISTEN T-STIFF

USER-FRIC TIO N

HHATTM CFC TM CFTTM CEK TM C

DISPLAC EM EN TPEN ETRATIO N -ALGO RITHM 2

DEPTHTIED

TIED-O FFSETFO RC ES

TRAC TIO N SC O N TIN UO US-N O RM AL

TBIRTH, TDEATHIN ITIAL-PEN ETRATIO N

TIM E-PEN ETRATIO NGAP-VALUE

C S-EXTEN SIO NC O N SISTEN T-STIFF

USER-FRIC TIO N

N O DETO N O DE = YES

DIREC TIO N DIREC TIO N

Summary of parameters applicable for each contact algorithm(Implicit analysis)

* in the case of 3D contact, denotes only applicable to the old Rigid Target Algorithm1 only applicable to 2D contact2 only applicable to 3D contact



Summary of parameters applicable for each contact algorithm(Explicit analysis)

* in the case of 3D contact, denotes only applicable to the old Rigid Target Algorithm1 only applicable to 2D contact2 only applicable to 3D contact

C O N TAC T ALGO RITHM

KIN EMATIC CO N STRAIN T PEN ALTY EXPLIC IT RIGID-TARGET

N AMEXALGO RITHM

FRICTIONO FFSET

O FFSET-TYPESUBTYPE 1

N AMEXALGO RITHM

DISPLACEMEN TFRICTIO N

PENETRATIO N -ALGORITHM 2

DEPTHO FFSET

O FFSET-TYPEFO RC ES

TRACTIO N SXK N -C RIT

XK -N O RMALXK T-CRIT

XK -TAN GEN TXDAMP

XN DAMP

TBIRTH, TDEATHIN ITIAL-PEN ETRATIO N

TIME-PEN ETRATIONGAP-VALUE

CS-EXTEN SIO NSUBTYPE 1

N AMEXALGO RITHM

FRICTIO NDEPTH

TBIRTH, TDEATHN O RMAL-STIFFN ESS

O FFSETO FFSET-TYPE

SUBTYPE 1

SLIDIN G-VELO C ITY2

GAPBIAS 2

O FFSET-DETEC T2

TAN GEN TIAL-STIFFN ESS*PTO LERANC E*

N O DETO N O DE = N O

DISPLAC EMEN TPEN ETRATIO N -ALGO RITHM 2

DEPTHFO RCES

TRACTIO N S

TBIRTH, TDEATHIN ITIAL-PENETRATIO N

TIME-PEN ETRATIO NGAP-VALUE

CS-EXTEN SIO N

NO DETO N O DE = YES

DIRECTIO N



CONTACTBODY NAME PRINT SAVE SOLID BODY

operationi typei labeli

Command CONTACTBODY defines a �contact body�, i.e. a geometry surface in 2Danalysis or a geometry volume in 3D analysis, which is expected to be in contact with adefined contactsurface (from the command CONTACTSURFACE). This allows all the nodesin the volume to potentially be in contact with a target surface. The target surface should stillbe defined using the CONTACTSURFACE command.

Each data input line specifies an operation, entity type and entity label. For example, you cancreate a contactbody composed of a geometry volume excluding a geometry point byspecifying two data input lines, the first line adding the volume and the second line subtract-ing the point.

NAME [(current highest contactbody/surface number) + 1]Label number of the contactbody to be defined. Note that the contactbody names are uniqueonly within a contact group, i.e. two different contact groups may each define its owncontactbody �1�. Note also that the name must be distinguished from that in theCONTACTSURFACE command, because a contactpair can be formed between a geometrydefined by the CONTACTBODY and a geometry defined by the CONTACTSURFACE.

PRINT [DEFAULT]Flag controlling printout of the results of the contact analysis as determined by the FORCESand TRACTIONS parameters of the CGROUP command. Choices are NO, YES and DE-FAULT; when PRINT=DEFAULT, printout is controlled by the PRINTOUT PRINTDEFAULTparameter.

SAVE [DEFAULT]Flag controlling saving (to the porthole file) of the results of the contact analysis asdetermined by the FORCES and TRACTIONS parameters of the CGROUP command. Choicesare NO, YES and DEFAULT; when SAVE=DEFAULT, saving is controlled by the PORTHOLESAVEDEFAULT parameter.

SOLID [NO]Flag indicating whether the contact body is defined on a B-Rep solid model body. {NO/YES}

BODYGeometry body label number of a B-Rep solid model. This parameter is required ifSOLID=YES.

CONTACTBODY



operationi [ADD]The entity specified in this data line is either added to or subtracted from the contactbody.{ADD/SUBTRACT}

typeiThe type of the entity specified in this data line. The entity can either be a geometry entity(POINT, LINE, SURFACE, VOLUME, EDGE, FACE, BODY) or a finite element entity (NODE).Command line parameter SOLID must be YES if the type is EDGE, FACE or BODY and thecommand line parameter BODY must be specified if the type is EDGE or FACE.

labeliThe label number of the entity.

Auxilary commands

LIST CONTACTBODY FIRST LASTDELETE CONTACTBODY FIRST LAST

CONTACTBODY



CONTACTSURFACE NAME PRINT SAVE SOLID BODY ORIENTATIONSENSE

namei sensei bodyi

CONTACTSURFACE defines a �contact-surface�, i.e., a set of boundary entities which areexpected to be in contact either initially or during analysis with another similarly definedcontact-surface.

NAME [(current highest contactsurface label number) + 1]Label number of the contact surface to be defined. Note that the contact-surface names areunique only within a contact group, i.e., two different contact groups may each define its owncontact-surface �1�.

PRINT [DEFAULT]Flag controlling printout of the results of the contact analysis as determined by the FORCESand TRACTIONS parameters of CGROUP. If DEFAULT is specified, printout is controlled byPRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT}

SAVE [DEFAULT]Flag controlling saving (to the porthole file) of the results of the contact analysis as deter-mined by the FORCES and TRACTIONS parameters of CGROUP. If DEFAULT is specified,saving is controlled by the PORTHOLE SAVEDEFAULT parameter. {YES/NO/DEFAULT}

SOLID [NO]Indicates whether the contact surface is defined on solid body (or bodies). {NO/YES/MULTI/BODY}

NO Contact surface is defined on native AUI geometry. Enter lines or surfaces inthe data input lines.

YES Contact surface is defined on a single solid body (specified by parameterBODY). Enter edges or faces in the data input lines.

MULTI Contact surface is defined on surfaces or faces of multiple bodies. (Only for3-D contact surface). Enter surfaces or faces (and parent bodies) in the datainput lines.

BODY Contact surface is defined on all boundary faces of a body (specified byparameter BODY). Do not enter data input lines.

BODY [currently active body]Geometry body label number.

CONTACTSURFACE



ORIENTATION [AUTOMATIC]Indicates contact surface orientation.

AUTOMATIC The sense flag for each component of the contact-surface isdetermined automatically.

INPUT The sense flag for contact-surface components is input in thefollowing data lines.

SENSE [+1]Default for the data line entry for contact-surface orientation. {+1/-1}

nameiLabel of geometric entities used to define this contact surface. The type of geometric entitydepends on the contact group and the parameter SOLID as indicated below.

Contact Group SOLID namei

2-D NO line label

2-D YES edge label3-D NO surface label3-D YES face label3-D MULTI surface or face label

sensei [SENSE]Orientation flag for geometry component:

+1 contact-surface uses same orientation as geometry.

-1 contact-surface uses opposite orientation to geometry.

bodyiLabel of the parent solid body when namei is an edge label or a face label.

Note: The label numbers for contact-surface definitions include those defined bycommands CONTACTSURFACE, CONTACTPOINT andCONTACT-FACENODES. Thus you cannot define CONTACTSURFACE �1� andCONTACTPOINT �1�, one would overwrite the prior definition.

Auxiliary commands

LIST CONTACTSURFACE FIRST LASTDELETE CONTACTSURFACE FIRST LAST

CONTACTSURFACE






CONTACTPOINT NAME PRINT SAVE POINT-TYPE

pointi tnxi tnyi tnzi

Defines a �contact-point�, i.e., a contact-surface defined as a set of geometry points or nodes(in 2-D or 3-D analysis) which are expected to be in contact, either initially or during analysis,with another similarly defined contact-point or contact-surface (see CONTACTSURFACE ).

Note:This command is only available for node-to-node contact (i.e., NODETONODE=YES in theCGROUP CONTACT... command).

NAME [(current highest contact point label number) + 1]Label number of the contact-point to be defined. Note that the contact-point names areunique only within a contact group, i.e., two different contact groups may each define its owncontact-point �1�.

PRINT [DEFAULT]Flag controlling printout of the results of the contact analysis as determined by the FORCESand TRACTIONS parameters of CGROUP. If DEFAULT is specified, printout is controlled byPRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT}

SAVE [DEFAULT]Flag controlling saving (to the porthole file) of the results of the contact analysis asdetermined by the FORCES and TRACTIONS parameters of CGROUP. If DEFAULT isspecified, saving is controlled by PORTHOLE SAVEDEFAULT. {YES/NO/DEFAULT}

POINT-TYPE [GEOMETRY]Specify whether geometry points or nodal points are used to define the contact surface.{GEOMETRY/NODAL/NODESET}

pointiGeometry point, nodal point, or node set label.

tnxiX-component of normal vector directed inside target body.

tnyiY-component of normal vector directed inside target body.

tnziZ-component of normal vector directed inside target body.

CONTACTPOINT



Note: The label numbers for contact-surface definitions include those defined bycommands CONTACTSURFACE , CONTACTPOINT andCONTACT-FACENODES. Thus you cannot define CONTACTSURFACE �1� andCONTACTPOINT �1�, one would overwrite the prior definition.

Auxiliary commands

LIST CONTACTPOINT FIRST LASTDELETE CONTACTPOINT FIRST LAST

CONTACTPOINT



DRAWBEAD NAME CONTACTOR TARGET1 TARGET2 HEIGHT R-FORCEU-FORCE PRINT SAVE DF-PRINT TBIRTH TDEATH GTYPESLIDING-VELOCITY

namei

Defines a drawbead for metal forming analysis. This command is only active if the currentcontact group is a rigid-target 3-D contact group.

NAME [(current highest DRAWBEAD label number) + 1 ]Label number of the drawbead to be defined.

CONTACTORSpecifies the contactor surface for the drawbead. A contactor surface is a contact surface thatis assigned as a contactor in a contactpair definition.

TARGET1Specifies the first target surface for the drawbead. A target surface is a contact surface that isassigned as a target in a contact pair definition.

TARGET2Specifies the second target surface for the drawbead.

HEIGHTSpecifies the drawbead height. {HEIGHT>0.0}

R-FORCESpecifies the restraining force per unit length of the drawbead. {R-FORCE>0.0}

U-FORCE [0.0]Specifies the uplifting force per unit length of the drawbead. {U-FORCE>=0.0}

PRINT [NO]Indicates whether drawbead segment nodal forces are printed.

NO - do not print drawbead forcesR-FORCE - print only restraining forcesRU-FORCE - print restraining and uplifting forces

SAVE [NO]

DRAWBEAD



Indicates whether drawbead segment nodal forces are saved.NO - do not save drawbead forcesR-FORCE - save only restraining forcesRU-FORCE - save restraining and uplifting forces

DF-PRINT [NO]Indicates whether drawbead segment distributed forces (traction) are printed and/or saved tothe porthole file.

NO - do not print/save distributed forcesYES - print/save distributed forces

Option DF-PRINT = YES takes effect only if drawbead segment nodal forces are printed/saved (parameter PRINT or SAVE is set to R-FORCE or RU-FORCE).

TBIRTH [TBIRTH of contact group]Specifies the birth time of the drawbead.

TDEATH [TDEATH of contact group]Specifies the death time of the drawbead.

GTYPE [LINE]Specifies the entity type used to define the drawbead. {LINE/NODE}

SLIDING-VELOCITY [1E-8]The minimum velocity of the contactor surface through the drawbead for which the drawbeaddevelops the full restraining traction. {>0}

This parameter is used only by the current rigid-target algorithm.

nameiSpecifies the geometry lines or nodes that defines the drawbead.

Auxiliary commands

LIST DRAWBEAD FIRST LASTDELETE DRAWBEAD FIRST LAST

DRAWBEAD





Sec. 7.5 Contact conditionsCOULOMB-FRICTION

COULOMB-FRICTION

cpairi modeli A1i A2i A3i

Specifies variable Coulomb friction coefficient for each contact pair under the current contactgroup. Note that this command is not available for rigid target contact (i.e., the parameterRIGID-TARGET=YES is specified in the CGROUP command).

cpairiContact pair label number. If zero is specified, the parameter specified in the other fields ofthis row will apply to all contact pairs.

modeliSpecifies the formula to define Coulomb friction coefficient µ. {LAW1/LAW2}

LAW1 µ = − −( )[ ]A A T Tn n1 21 0. exp

LAW2 µ = + − ⋅ −( ) ( )A A A A Tn2 1 2 3exp

where Tn is normal contact pressure and A1, A2, A3 are constants.

A1iConstant A1.

A2iConstant A2.

A3iConstant A3. This constant is only applicable if LAW2 is used.

Auxiliary commands

LIST COULOMB-FRICTIONDELETE COULOMB-FRICTION



USER-FRICTION

integeri reali

Specifies the integer and real parameters passed to the user-supplied friction subroutine(FUSER) for the current contact group. Note that this feature cannot be used with the rigidtarget contact option (i.e., RIGID-TARGET=YES is specified in the CGROUP command).

In the current implementation of FUSER, the first integer parameter is used to select a frictionmodel. Each friction model requires a number of real integer parameters as explained inSection 4.3.2 of the Theory and Modeling Guide, Volume I (ADINA).

integeriInteger number.

realiReal number.

Auxiliary commands

LIST USER-FRICTIONDELETE USER-FRICTION

USER-FRICTION


Sec. 7.5 Contact conditionsCS-OFFSET

CS-OFFSET

csurfi offseti

Specifies offset distances for individual contact-surfaces under the current contact group. Ifan individual contact surface is not specified here, the contact surface will use the defaultoffset distance specified by the OFFSET parameter in the CGROUP command.

csurfiContact surface label number.

offseti

Offset distance. { ≥ 0.0}

Note: This feature is not available for rigid target contact (i.e the parameterRIGID-TARGET=YES is specified in the CGROUP command).

Auxiliary commands

LIST CS-OFFSETDELETE CS-OFFSET



CONTACTPAIR NAME TARGET CONTACTOR FRICTIONTBIRTH TDEATH HHATTMC FCTMC FTTMCNX NY NZ OFFSET-CONTACT EKTMC

Defines a �contact pair,� i.e., two contact-surfaces (see CONTACTSURFACE ) which areeither initially in contact or are anticipated to come into contact during analysis. One contactsurface is termed the �contactor� contact-surface and must be deformable, i.e., has contactsegments associated with the boundary surfaces of deformable finite elements (i.e., withnodes with free displacement degrees of freedom) within the model. The other contact-surface which makes up the contact pair is termed the �target� contact-surface. The targetcontact-surface may be deformable or have prescribed displacement.

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CONTACTPAIR

Three contact surafces forming 2 contact pairs



NAME [(current highest contactpair label number) + 1]Label number of the contact pair to be defined. The contactpair numbering is independent foreach contact group.

TARGETTarget contact-surface, which must have been defined by the commandCONTACTSURFACE, CONTACTPOINT or CONTACT-FACENODES for the currently activegroup.

CONTACTORContactor contact-surface, defined by the CONTACTSURFACE, CONTACTPOINT orCONTACT-FACENODES for the currently active contact group.

Note: To specify �self-contact�, you may specify TARGET and CONTACTOR to be thesame contact-surface.

FRICTION [CGROUP FRICTION]Coefficient of friction between the target and contactor contact-surfaces. FRICTION = 0.0implies the default friction specified by CGROUP command is used.

Note: FRICTION is not used in node-to-node contact (parameter NODETONODE incommands CGROUP CONTACT2 and CGROUP CONTACT3 ). Contact groupfriction is used instead.

TBIRTH [0.0]TDEATH [0.0]The birth and death times for current contact pair. If TBIRTH=0.0 and TDEATH=0.0, thebirth and death feature is not used.

Note: TBIRTH and TDEATH options are not used in node-to-node contact (parameterNODETONODE in commands CGROUP CONTACT2 and CGROUP CONTACT3).

Note: If FRICTION, TBIRTH and TDEATH parameters are not specified, default valuesdefined by commands CGROUP CONTACT2 or CGROUP CONTACT3 are used.

HHATTMC [0.0]Contact heat transfer coefficient; used only when thermo-mechanical coupling is active.

FCTMC [0.5]Friction contact heat distribution fraction coef. for contactor; used only when thermo-mechanical coupling is active. {0.0 ≤ FCTMC ≤ 1.0}

CONTACTPAIR



FTTMC [0.5]Friction contact heat distribution fraction coef. for target; used only when thermo-mechanicalcoupling is active. {0.0 ≤ FTTMC ≤ 1.0}

NX [0]NYNZNumber of sorting buckets in X, Y, Z direction. For 2D contact groups (CGROUP CONTACT2)parameter NX is ignored. {≥ 0.0}

For rigid-target algorithm of version 8.3, �0� = �1� (set when writing data file).

For current rigid-target algorithm, �0� = automatically calculated by ADINA.

OFFSET-CONTACT [BOTH]This parameter is used only in the following special cases {LOWER/UPPER/BOTH}:

1) Current rigid-target algorithm, and2a) CGROUP OFFSET-DETECT=NORMALS, or2b) CGROUP OFFSET-DETECT=AUTOMATIC and ADINA chooses an offset implementation

using normals.

Then the contactor surface is split into two surfaces, an upper surface and a lower surface:

LOWER Only the lower surface can be in contact with the target.

UPPER Only the upper surface can be in contact with the target.

BOTH Both surfaces can be in contact with the target.

Note that OFFSETCONTACT is only used to provide a hint to the contact algorithm, to speedup the searching.

EKTMC [0.0]Electrical conductivity for current flow through contact surfaces in a thermo-mechanicalcoupling (TMC) analysis. Applicable only if the constraint function algorithm is used inimplicit analysis, i.e., ALGORITHM = CONSTRAINT-FUNCTION in CGROUP CONTACT2/3. (Units: electrical conductance/length, e.g., Siemens/m) {≥ 0.0}

Auxiliary commands

LIST CONTACTPAIR FIRST LASTDELETE CONTACTPAIR FIRST LAST

CONTACTPAIR



CONTACT3-SEARCH BODY1 BODY2 CGROUP CSURFACE CPAIR DIST-TYPEDIST-MAX DIST-MIN EXISTING

CONTACT3-SEARCH creates 3D contact surfaces and contact pairs between two bodieswithin the given distance range.

BODY1Label number of the first body. The contact surfaces defined by the faces of BODY1 will beused as target surfaces in contact pair.

BODY2Label number of the second body. The contact surfaces defined by the faces of BODY2 willbe used as contactor surfaces in contact pair. Please note that BODY1 and BODY2 cannot bethe same.

CGROUP [current 3D contact group label number]3D contact group label number. The given 3D contact group needs to be defined before thiscommand is used.

CSURFACE [(current contact surface label number) + 1]Contact surface label number. If the contact surface label number exists, it will be overwritten.

CPAIR [(current contact pair label number) + 1]Contact pair label number. If the contact pair label number exists, it will be overwritten.

DIST-TYPE [CLOSEST]Selects the type of distance that will be used to measure the distance between faces.

CLOSEST The shortest distance between faces

FACE-CENTER The distance between face centers

DIST-MAXDIST-MIN [0.0]Faces between BODY1 and BODY2 will be used to define contact surfaces and contact pairsif the distance is between DIST-MIN and DIST-MAX.

EXISTING [OVERWRITE]Indicates how existing contact surfaces and pairs in the contact group CGROUP are handled.{OVERWRITE/REMOVE/KEEP}

OVERWRITE Existing contact surfaces and pairs are overwritten if their labelnumbers are the same as the new contact surfaces and pairsspecified by CSURFACE and CPAIR parameters

CONTACT3-SEARCH



REMOVE All existing contact surfaces and pairs are removed

KEEP Existing contact surface and pairs are kept. Hence, if the label numbersspecified in CSURFACE or CPAIR already exist, this command will give anerror.

CONTACT3-SEARCH






FRACTURE TECHNIQUE METHOD DIMENSION TYPEPRESSURE TEMPERATURE DYNAMIC LVUS3

FRACTURE defines the controlling data for analysis of fracture mechanics problems.

TECHNIQUE [STANDARD]Defines whether standard or user-supplied fracture criteria / propagation models are used inthe analysis.

STANDARD Standard analysis model.

METHOD [VIRTUAL-CRACK-EXTENSION]The method of evaluating the J-parameter value. {VIRTUAL-CRACK-EXTENSION/LINE-CONTOUR/BOTH}

DIMENSION [2]Dimension of fracture analysis. {2/3}

2 2-D crack.

3 3-D crack.

TYPE [STATIONARY]Type of crack. {STATIONARY/PROPAGATION}

STATIONARY Analysis of a stationary crack.

PROPAGATION Analysis of a propagating crack.

PRESSURE [YES]Pressure correction for virtual crack extension method. {YES/NO}

YES Pressure correction applied.

NO No correction.

TEMPERATURE [YES]Temperature correction for virtual crack extension method. {YES/NO}

YES Temperature correction applied.

NO No correction.

FRACTURE


Sec. 7.6 Fracture mechanics

DYNAMIC [YES]Dynamic correction for virtual crack extension method. {YES/NO}

YES Dynamic correction applied.

NO No correction.

LVUS3 [0]This parameter is obsolete.

Auxiliary commands

LIST FRACTURE

FRACTURE



CRACK-GROWTH CONTROL-TYPE J-VERSION FACTOR R-CURVELOCTYPE DOF SHIFT-RELEASE POINT NODE

CRACK-GROWTH specifies parameters which govern the growth of a propagating crack.This command should be used whenever the FRACTURE command indicates a 2-D propagat-ing crack.

CONTROL-TYPE [FIXED]The type of crack growth control:

FIXED A fixed virtual material shift.

MOVING A moving virtual material shift.

NODAL A nodal degree of freedom.

J-VERSION [CORRECTIONS]The version of the J-parameter used in crack growth control.

CORRECTIONS J-parameter with thermal, pressure and dynamic corrections.

NONE J-parameter without thermal, pressure and dynamic corrections.

FACTOR [1.0]This parameter is not used any more, and is permanently set to 1.0 by the program.

R-CURVE [1]The identifying number of a resistance curve used in crack growth control (see command R-CURVE ). {POINT/NODE}

LOCTYPE [POINT]The type of location where a specified degree of freedom is used to control the crack propa-gation. {POINT/NODE}

DOFThe degree of freedom at the point (or node) used to control the crack propagation.

1 X-translation.

2 Y-translation.

3 Z-translation.

CRACK-GROWTH



SHIFT-RELEASE [SHIFT-RELEASE]Indicates the mesh updating method used for a propagating crack. See the Theory andModeling Guide for details.

SHIFT-RELEASE The node �shift & release� technique is used to modelthe propagation of the crack tip through the finiteelement mesh.

RELEASE Only the node �release� technique is applied, when thecrack opens.

POINTThe label number of a point where a specified degree of freedom is used to control the crackpropagation.

NODEThe label number of a node where a specified degree of freedom is used to control the crackpropagation.

Auxiliary commands

LIST CRACK-GROWTH

CRACK-GROWTH



CRACK-PROPAGATION defines the initial crack front position, or the virtual/actual crackpropagation path along which a crack would propagate.

This command should always be used in a fracture mechanics analysis, whether it is a

CRACK-PROPAGATION POINTS NAME

pointi nvshfti factori

CRACK-PROPAGATION LINES NAME

linei front-pointi nvshfti factori

CRACK-PROPAGATION SURFACES NAME

surfacei front-linei nvshfti factori

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CRACK-PROPAGATION


Sec. 7.6 Fracture mechanicsCRACK-PROPAGATION

stationary or a propagating crack analysis. Note that in 2-D analysis, the crack front corre-sponds to a single node � the crack tip node. The virtual propagation path corresponds to asingle point or line of nodes starting at the crack tip node. The crack propagation line mustbe parallel to the Y axis in 2D mode. In 3-D analysis, the crack front corresponds to a line ofnodes. The virtual/actual crack propagation path corresponds to a surface developed fromthe crack front line along �generator� lines originating from the crack front nodes. The crackpropagation surface must be in the X-Y plane in 3D mode.

NAME [1]The label number of the crack propagation surface. (At present only one crack is allowed.)

pointiThe label number of a geometry point.

lineiThe label number of a geometry line.

surfaceiThe label number of a geometry surface.

front-lineiThe label number of a line which defines initial crack front.

front-pointiThe label number of a point which defines the initial crack front.

nvshftiIn the case of fixed virtual material shift (CRACK-GROWTH CONTROL-TYPE = FIXED) thisspecifies the label number of virtual shift (defined by J-VIRTUAL-SHIFT command).

In the case of moving virtual material shift (CRACK-GROWTH CONTROL-TYPE = MOVING)this specifies the number of �rings� of elements about the (moving) crack tip on the generatorline.

Parameter nvshfti is used only in crack propagation analysis (FRACTURE TYPE =PROPAGA-TION).

factoriResistance factor. This parameter is no longer used.

Auxiliary commandsLIST CRACK-PROPAGATION FIRST LASTDELETE CRACK-PROPAGATION FIRST LAST



J-LINE POINT NAME POINT RADIUS PRINT SAVE START-FACEEND-FACE

J-LINE POINT defines a line contour by using a circle defined by its center and radius.

The line contour is defined by a series of elements intersected by the circle.

NAME [(current highest label number) + 1]Label number of the line contour to be defined. If the label number of an existing line contouris given, then the previous line contour definition is overwritten.

POINT [0]The point label number; the center of the circle.

RADIUS [0.0]The radius of the circle.

PRINT <not currently active>

SAVE <not currently active>

START-FACE [0]If the first element of the contour does not have a unique face on the mesh boundary thenthis parameter determines which face is selected to start the contour. START-FACE should

J-LINE POINT

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be an integer in the range 0 - 4, inclusive. A zero value (the default) will cause the program toselect the face opposite that of the second element in the contour definition.

1 face N1-N2.

2 face N2-N3.

3 face N3-N4.

4 face N4-N1.

(Where N1, N2, N3, N4 are the element vertex nodes.)

END-FACE [0]If the last element of the contour does not have a unique face on the mesh boundary then thisparameter determines which face is selected to terminate the contour. END-FACE should be aninteger in the range 0 - 4, inclusive. A zero value (the default) will cause the program to selectthe face opposite that of the penultimate element in the contour definition.

1 face N1-N2.

2 face N2-N3.

3 face N3-N4.

4 face N4-N1.


Auxiliary commands

LIST J-LINE POINT FIRST LASTDELETE J-LINE POINT FIRST LAST

J-LINE POINT



J-LINE RING NAME NRING POINT PRINT SAVE START-FACE END-FACE

J-LINE RING defines a line contour by using a �ring� number. A ring of elements is definedas follows. Given an origin node, ring number 1 consists of those elements connected at thatnode. Ring number 2 then consists of all elements connected to (and including) the elementsin ring number 1, and so on. The line contour is defined by a series of elements. The �origin�node of the ring is taken to be the one coincident with a given geometry point.

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NAME [(current highest label number) + 1]Label number of the line contour to be defined. If the label number of an existing line contouris given, then the previous line contour definition is overwritten.

NRING [0]Determines the number of rings of elements around the �origin� node.

POINT [0]The point label number. The node at this point is at the ring origin.

PRINT <not currently active>

SAVE <not currently active>

START-FACE [0]If the first element of the contour does not have a unique face on the mesh boundary thenthis parameter determines which face is selected to start the contour. START-FACE should

J-LINE RING



be an integer in the range 0 - 4, inclusive. A zero value (the default) will cause the program toselect the face opposite that of the second element in the contour definition.

1 face N1-N2.

2 face N2-N3.

3 face N3-N4.

4 face N4-N1.


END-FACE [0]If the last element of the contour does not have a unique face on the mesh boundary thenthis parameter determines which face is selected to terminate the contour. END-FACE shouldbe an integer in the range 0 - 4, inclusive. A zero value (the default) will cause the program toselect the face opposite that of the penultimate element in the contour definition.

1 face N1-N2.

2 face N2-N3.

3 face N3-N4.

4 face N4-N1.


Auxiliary commands

LIST J-LINE RING FIRST LASTDELETE J-LINE RING FIRST LAST

J-LINE RING



J-VIRTUAL-SHIFT POINT NAME VECTOR VX VY VZ N3DSHNORMAL NX NY NZ THICKNESSPOINT RADIUS

J-VIRTUAL-SHIFT POINT defines a virtual material shift by using a sphere defined by itscenter and radius.

NAME [(current highest label number) + 1]Label number of the virtual shift to be defined. If the label number of an existing virtual shiftis given, then the previous virtual shift definition is overwritten.

VECTOR [AUTOMATIC]Controls whether the actual material shift vector is calculated internally by ADINA, or isinput via the global component values VX, VY, VZ below.

AUTOMATIC The shift vector is calculated automatically by ADINA, from thecrack surface definition (see CRACK-PROPAGATION ). In thecase of a 3-D crack, N3DSH is used to explicitly select agenerator line associated with the automatic shift vectorcalculation.

INPUT The shift vector is input directly via VX, VY, VZ.

VX [0.0]VY [0.0]VZ [0.0]The global components of the material shift vector.

J-VIRTUAL-SHIFT POINT

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N3DSH [0]Identifies a generator line of the crack surface with automatic shift vector calculation for a 3-Dcrack. A zero value causes ADINA to calculate the shift vector based on the generator linewhose crack tip node appears first in the list of nodes which comprises the virtual shiftdefinition.

NORMAL [NONE]Controls (for 3-D virtual material shift) whether or not the nodes of the shift are required to liein a disk of given thickness.

NONE The nodes of the shift are not required to lie in a disk.

AUTOMATIC The central plane of the disk is determined automatically fromthe crack surface definition. The plane is taken to be perpendicular to the crack tip node for the generator line associated withparameter N3DSH.

INPUT The normal vector to the central plane of the disk is input viaNX, NY, NZ. The central plane of the disk passes through thecrack tip node for the generator line associated with parameterN3DSH.

NX [0.0]NY [0.0]NZ [0.0]The global components of the normal to the central plane of the disk in which shift nodesmust lie.

THICKNESS [1.0E-5]The thickness of the disk containing the shift nodes. If NORMAL ≠ NONE then a positivevalue for THICKNESS must be given.

POINT [0]The label number of the point which is the center of the sphere.

RADIUS [0.0]The radius of the sphere.

Auxiliary commands

LIST J-VIRTUAL-SHIFT POINT FIRST LASTDELETE J-VIRTUAL-SHIFT POINT FIRST LAST

J-VIRTUAL-SHIFT POINT



J-VIRTUAL-SHIFT LINE NAME VECTOR VX VY VZ N3DSH

linei

J-VIRTUAL-SHIFT LINE defines a virtual material shift. The shift is defined by those nodeslying on any of a given set of lines.



AUTOMATIC The shift vector is calculated automatically by ADINA, from thecrack surface definition (see CRACK-PROPAGATION ). In thecase of a 3-D crack, parameter N3DSH may be used to explicitlyselect a generator line associated with the automatic shift vectorcalculation.




lineiLabel number of a geometry line.

Auxiliary commands

LIST J-VIRTUAL-SHIFT LINE FIRST LASTDELETE J-VIRTUAL-SHIFT LINE FIRST LAST

J-VIRTUAL-SHIFT LINE






J-VIRTUAL-SHIFT SURFACE NAME VECTOR VX VY VZ N3DSH

surfacei

J-VIRTUAL-SHIFT SURFACE defines a virtual material shift. The shift is defined by thosenodes lying on any of a given set of surfaces.








Auxiliary commands

LIST J-VIRTUAL-SHIFT SURFACE FIRST LASTDELETE J-VIRTUAL-SHIFT SURFACE FIRST LAST

J-VIRTUAL-SHIFT SURFACE



J-VIRTUAL-SHIFT RING NAME VECTOR VX VY VZ N3DSH NORMALNX NY NZ THICKNESS RING-TYPERING-NUMBER

namei

J-VIRTUAL-SHIFT RING defines a virtual material shift by using a number of rings ofelements around the crack front points.

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J-VIRTUAL-SHIFT RING




NORMAL [NONE]Controls (for 3-D virtual material shift) whether or not the nodes of the shift are required to liein a disk of given thickness. {NONE/AUTOMATIC/INPUT}

NONE The nodes of the shift are not required to lie in a disk.

AUTOMATIC The central plane of the disk is determined automatically fromthe crack surface definition. The plane is taken to beperpendicular to the crack tip node for the generator lineassociated with parameter N3DSH.

INPUT The normal vector to the central plane of the disk is input viaNX, NY, NZ. The central plane of the disk passes through thecrack tip node for the generator line associated with parameterN3DSH.

NX [0.0]NY [0.0]NZ [0.0]The global components of the normal to the central plane of the disk in which shift nodesmust lie.

THICKNESS [1.0E-5]The thickness of the disk containing the shift nodes. If NORMAL ≠ NONE, a positive valuefor THICKNESS must be given.

RING-TYPE [POINT]The type of geometry on which the origin nodes lie. {POINT/LINE/SURFACE/NODE/AUTOMATIC}

POINT The origin nodes are taken to be those at a set of points.

LINE The origin nodes are taken to be those lying on a set of lines.

SURFACE The origin nodes are taken to be those lying on a set of surfaces.

NODE The origin nodes are directly specified in the data input lines.




AUTOMATIC The origin nodes are automatically taken from all vertex nodes,see notes at the end of this command description. See the

following note.

Note: When RING-TYPE=AUTOMATIC, the J-VIRTUAL-SHIFT RING commandcreates one virtual shift for each vertex node on the crack generator line. Thisgeneration is done by the ADINA command (creation of the .dat file).

RING-NUMBER [0]Controls the number of rings of elements around the origin nodes.

0 Corresponds to a shift comprised of the origin nodes alone.

1 Includes the nodes of elements connected to the origin nodes.

Higher values of RING-NUMBER recursively define the shift such that RING-NUMBER = (n +1) gives a shift including the nodes of elements containing any of the nodes defined in theshift given by RING-NUMBER = n.

nameiLabel number of the geometry entries (point, line or surface) or nodes according to the param-eter RING-TYPE. For 3-D material virtual shifts, if the geometry entities are points, these pointsmust be vertices of elements, i.e. no points located at mid-side nodes should be specified.

Auxiliary commands

LIST J-VIRTUAL-SHIFT RING FIRST LASTDELETE J-VIRTUAL-SHIFT RING FIRST LAST







R-CURVE NAME MPOINT

thetai x1i y1

i x2i y2

i . . . xmi ym

i

R-CURVE defines a resistance curve set which can be referenced by a crack growth analysis(see CRACK-GROWTH ). Note that (xj

i, yji) comprises a data point on the resistance curve

associated with temperature �thetai�. The curve data is first sorted by increasing temperature�thetai�, then by increasing crack increment �xj

i�.

If more than one data input line is entered, the values of �xji� must be the same for each data

input line.

NAME [(current highest R-CURVE label number) + 1]Label number of the resistance curve set to be defined. If the label number of an existingcurve set is given, then the previous curve set definition is overwritten.

MPOINTThe maximum number of data points in any single resistance curve, defined in the subsequentdata lines.

thetaiReference temperature for resistance curve �i�.

xji

Crack increment value at data point �j� on resistance curve �i�.

yji

Resistance value at crack-increment �j� on resistance curve �i�.

Auxiliary commands

LIST R-CURVE FIRST LASTDELETE R-CURVE FIRST LAST

R-CURVE



SINGULAR POINT Q-POINT

pointi

SINGULAR LINE Q-POINT

linei

SINGULAR defines a set of �singular� nodes on geometry points/lines. These are elementvertex nodes whose adjacent non-vertex nodes are moved to the �1/4 point� giving a singu-larity at the required nodes.

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Q-POINT [QUARTER]Controls whether non-vertex nodes adjacent to the desired vertex nodes are moved to the �1/4 point�, or the opposite action is taken.

QUARTER Nodes are moved to the �1/4 point�.

MID Nodes are moved from the �1/4 point� back to the relevant mid-side/face position.

pointiLabel number of a singular geometry point.

SINGULAR POINT



lineiLabel number of a geometry line defining a sequence of singular nodes, i.e., all element vertexnodes associated with the geometry line.

Auxiliary commands

LIST SINGULARDELETE SINGULAR

SINGULAR POINT






USER-RUPTURE NAME NR NI

reali integeri

Specifies user-defined rupture data.

NAME [(current highest USER-RUPTURE label number) + 1]USER-RUPTURE label name {> 0}.

NR [0]

Total number of user-defined real data. Note that NR + NI must be greater than zero. {≥ 0.0}

NI [0]Total number of user-defined integer data. Note that NR + NI must be greater than zero.{≥ 0.0}

reali [0]User-defined real data.

integeri [0]User-defined integer data.

Auxiliary commands

LIST USER-RUPTURE FIRST LASTDELETE USER-RUPTURE FIRST LAST

USER-RUPTURE



RIGIDLINK NAME SLAVETYPE SLAVENAME MASTERTYPEMASTERNAME DISPLACEMENTS OPTION SLAVEBODYMASTERBODY DOF DOFSI

slavenamei

Specifies rigid links between pairs of nodes on entities. As the nodes move under modeldeformation, the �slave� node is constrained to translate and rotate such that the distancebetween the �master� node and the slave node remains constant and the rotations at theslave node are the same as the corresponding rotations at the master node.

A rigid link can be specified only between nodes in the main structure, and the distancebetween the nodes must be greater than zero. The displacement degrees of freedom at themaster node must all be independent, i.e., they cannot be constrained to other degrees offreedom. Fixity conditions may, however, be specified for the master node.

Different skew degree-of-freedom systems may be assigned for the master and slave nodes.If either the master or slave node is a shell midsurface node, then six degrees of freedom isuesd for both nodes.

Only the displacement degrees of freedom (translations and rotations) are constrained by arigid link. Other degrees of freedom, e.g., pipe ovalization, warping, and fluid potential, arenot constrained by a rigid link.

NAME [(highest rigid link label number) + 1]The label number of the rigid link.

SLAVETYPE [POINT]Indicates the type of entity used to specify slave nodes. {POINT/LINE/SURFACE/EDGE/FACE/NODESET/VOLUME/BODY}

SLAVENAMEThe label number of the slave entity (point, line, etc. as directed by parameter SLAVETYPE).

MASTERTYPE [POINT]Indicates the type of the entity used to specify master nodes. {POINT/LINE/SURFACE/EDGE/FACE/NODESET}

MASTERNAMEThe label number of the master entity (point, line, etc. as directed by parameterMASTERTYPE).

RIGIDLINK


Sec. 7.7 Boundary conditions

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DISPLACEMENTS [DEFAULT]Specifies whether the constraint equations in ADINA are for kinematically linear (infinitesi-mal displacements), or large displacements. DISPLACEMENTS = DEFAULT indicates thatdisplacements are controlled by the KINEMATICS command. {SMALL/LARGE/DE-FAULT}

OPTION [0]{0/1/2/3/4}When multiple nodes exist on both the slave and master geometry entities, OPTION indicateshow the rigid link between nodes on each entity is defined.



0 A rigid link is constructed between nodes at the corresponding parametric order oneach entity. Parametric order is in the increasing u-parameter direction for lines,increasing u- then v-parameter for surfaces. In this case the number of nodes onthe slave and master geometry entities must be the same.

1 A rigid link is constructed for each node on the slave geometry entity to the closestnode on the master geometry entity. In this case, the number of nodes need not bethe same for the slave and master geometry entities.

2 A rigid link is constructed between slave node to master node using reverse uparametric order. Applies to line/edge and surface/face.

3 A rigid link is constructed between slave node to master node using reverse vparametric order. Applies to surface/face.

4 A rigid link is constructed between slave node to master node using reverse u and vparametric order. Applies to surface/face.

SLAVEBODY [currently active BODY]Indicates the solid geometry body used to reference a slave edge or face when SLAVETYPE= EDGE or FACE, respectively.

MASTERBODY [currently active BODY]Indicates the solid geometry body used to reference a master edge or face whenMASTERTYPE = EDGE or FACE, respectively.

Note: Only the following SLAVETYPE, MASTERTYPE combinations are allowed:

SLAVETYPE MASTERTYPEPOINT POINTLINE POINTLINE LINESURFACE POINTSURFACE SURFACEEDGE POINTEDGE EDGEFACE POINTFACE FACENODESET anyany NODESET

DOF [ALL]Indicates whether all relevant slave DOFs are constrained to the master node.{ALL/MASTER}

RIGIDLINK



ALL All relevant slave DOFs are constrained to the master node.

MASTER The slave DOF is only constrained where the corresponding master DOF isnot fixed. Note that DOF = MASTER is only used if DISPLACEMENTS =SMALL and all rotational degrees of freedom on the master node is fixed.

slavenameiSlave geometry label (TYPE = SLAVETYPE). If SLAVETYPE = EDGE or FACE , all Slavegeometry belongs to SLAVEBODY.

DOFSI [123456]Specifies the slave degrees of freedom (dof) to be constrained to the master node. DOFSImust contain 1 to 6 digits ranging from 1 to 6. Dofs 1, 2, 3 indicate X, Y, Z translations and 4,5, 6 indicate X, Y, Z rotations.

Auxiliary commandsLIST RIGIDLINK FIRST LASTDELETE RIGIDLINK FIRST LAST

RIGIDLINK



CONSTRAINT NAME SLAVETYPE SLAVENAME SLAVEDOF MASTERTYPESBODY OPTION GENERALIZED-CONSTRAINT TRANSFORMATION

masternamei masterdofi betai mbodyi

Specifies a constraint set which expresses a slave (dependent) degree of freedom as a linearcombination of a set of master (independent) degrees of freedom. The slave and masterdegrees of freedom are input by reference to geometry entities or node sets.

A constraint equation can only reference nodes in the main structure.

A constraint equation at a slave degree of freedom is unique. Therefore, if several constraintequations are input for the same slave degree of freedom, then only that for the highest labelnumber will be used.

A fluid potential slave degree of freedom can have only fluid potential master degrees offreedom, and a displacement (translation, rotation) slave degree of freedom can have onlydisplacement master degrees of freedom. Constraint equations cannot refer to pipeovalization or warping degrees of freedom.

Note that constraint equations necessary to enforce a rigid link between two geometryentities can be defined using the RIGIDLINK command.

NAME [(highest constraint set label number) + 1]The label number of the constraint set.

SLAVETYPE [POINT]Indicates the type of entity used to specify slave nodes. {POINT/LINE/SURFACE/VOLUME/EDGE/FACE/BODY/NODESET}

SLAVENAMEThe label number of the slave entity as directed by SLAVETYPE.

SLAVEDOFThe degree of freedom associated with the slave geometry entity. {X-TRANSLATION/ Y-TRANSLATION/Z-TRANSLATION/X-ROTATION/Y-ROTATION/Z-ROTATION/ALL-TRANSLATION/ALL-ROTATION/FLUID-POTENTIAL/TEMPERATURE}

SLAVEDOF = TEMPERATURE is only available when MASTER TMC = YES.

MASTERTYPE [POINT]Indicates the type of entity used to specify master nodes. {POINT/LINE/ SURFACE/

CONSTRAINT



EDGE/FACE/NODESET}

Note: Only the following SLAVETYPE, MASTERTYPE combinations are allowed:

SLAVETYPE MASTERTYPEPOINT POINT,NODESETLINE POINT,LINE,NODESETSURFACE POINT,SURFACE,NODESETEDGE POINT,EDGE,NODESETFACE POINT,FACE,NODESETNODESET anyVOLUME anyBODY any

SBODY [currently active body]The label number of the geometry slave body (used when SLAVETYPE=EDGE or FACE).

OPTION [0]When multiple nodes exist on both the slave and master geometry entities, OPTION indicateshow the constraint between nodes on each entity is defined. OPTION is only applicable whenconstraining line to line, edge to edge, surface to surface, and face to face. OPTION= 1 isused for all other cases. {0/1/2/3/4}

0 A constraint is constructed between nodes at the corresponding parametric orderon each entity. Parametric order is in the increasing u-parameter direction forlines, increasing u- then v-parameter for surfaces. In this case the number ofnodes on the slave and master geometry entities must be the same.

1 A constraint is constructed for each node on the slave entity to theclosest node on the master entity. In this case, the number of nodes neednot be the same for the slave and master entities.

2 Constrain slave node to master node using reverse u parametric order. Applies toline/edge and surface/face.

3 Constrain slave node to master node using reverse v parametric order. Applies tosurface/face.

4 Constrain slave node to master node using reverse u and v parametric order.

GENERALIZED-CONSTRAINT [NO]Generate generalized constraints instead of standard constraints.{NO/YES}

CONSTRAINT



TRANSFORMATION [0]Transformation label number which is applied to slave geometry entity when OPTION = 1.

masternameiThe label number of the master entity as directed by MASTERTYPE for the �i�th independentterm of the constraint.

masterdofiThe degree of freedom of the master entity for the �i�th independent term of the constraint.Possible values are the same as for SLAVEDOF.

betai [1.0]The coefficient of the �i�th independent term of the constraint. Note that this value remainsconstant throughout the time history of the response. A zero value is not accepted since itimplies no contribution to the linear combination of independent master degrees of freedom.

mbodyi [currently active body]The label number of the geometry master body (used when MASTERTYPE = EDGE orFACE).

Note: For a cyclic symmetric analysis, constraint equations may be applied to degrees offreedom within the fundamental part, but in this case similar constraint equationsfor corresponding degrees of freedom in all other cyclic parts of the structure willbe applied.

Auxiliary commands

LIST CONSTRAINT FIRST LASTDELETE CONSTRAINT FIRST LAST

CONSTRAINT






CONSTRAINT-MS NAME MASTERTYPE MASTERNAME MASTERDOFSLAVETYPE MBODY OPTION GENERALIZED-CONSTRAINT

slavenamei slavedofi betai sbodyi

This command is similar to the CONSTRAINT command. The difference between the CON-STRAINT-MS and CONSTRAINT commands is that CONSTRAINT-MS allows the specifica-tion of multiple slave entities for a single master entity.

Note that constraint equations that are necessary to enforce a rigid link between two geom-etry entities can be defined using the RIGIDLINK command.

NAME [(highest constraint-ms set label number) + 1]The label number of the constraint-ms set.

MASTERTYPE [POINT]Indicates the type of the geometry entity used to specify master nodes.{POINT/LINE/SURFACE/VOLUME/EDGE/FACE/BODY/NODESET}

MASTERNAMEThe label number of the master entity as directed by MASTERTYPE.

MASTERDOFThe degree of freedom associated with the master entity.{X-TRANSLATION/Y-TRANSLATION/Z-TRANSLATION/X-ROTATION/Y-ROTATION/Z-ROTATION/ALL-TRANSLATION/ALL-ROTATION/FLUID-POTENTIAL/TEMPERATURE}


SLAVETYPE [POINT]Indicates the type of entity used to specify slave nodes.{POINT/LINE/SURFACE/VOLUME/EDGE/FACE/BODY/NODESET}

MBODY [currently active body]The label number of the geometry master body (used when MASTERTYPE=EDGE or FACE).

OPTION [0]When multiple nodes exist on both the slave and master geometry entities, OPTION indicateshow the constraint between nodes on each entity is defined.

CONSTRAINT-MS



OPTION is only applicable when constraining line to line, edge to edge, surface to surface,and face to face. OPTION= 1 is used for all other cases.{0/1/2/3/4}

0 A constraint is constructed between nodes at the corresponding parametric orderon each entity. Parametric order is in the increasing u-parameter direction forlines, increasing u- then v-parameter for surfaces. In this case the number ofnodes on the slave and master geometry entities must be the same.

1 A constraint is constructed for each node on the slave geometry entity to theclosest node on the master geometry entity. In this case, the number of nodes neednot be the same for the slave and master entities.

2 Constrain slave node to master node using reverse u parametric order.

3 Constrain slave node to master node using reverse v parametric order. Applies tosurface/face.

4 Constrain slave node to master node using reverse u and v parametric order. Appliesto surface/face.

GENERALIZED-CONSTRAINT [NO]Generate generalized constraints instead of standard constraints.{NO/YES}

slavenameiThe label number of the slave entity as directed by SLAVETYPE for the �i�th independentterm of the constraint.

slavedofiThe degree of freedom of the slave geometry entity for the �i�th independent term of theconstraint. Possible values are the same as for MASTERDOF.

betai [1.0]The coefficient of the �i�th independent term of the constraint. Note that this value remainsconstant throughout the time history of the response. A zero value is not accepted since itimplies no contribution to the linear combination of independent master degrees of freedom.

sbodyi [currently active body]The label number of the geometry slave body (used when SLAVETYPE = EDGEor FACE).

CONSTRAINT-MS


Chap. 7 Model definition CONSTRAINT-MS

Auxiliary commands

LIST CONSTRAINT-MS FIRST LASTDELETE CONSTRAINT-MS FIRST LAST





Chap. 7 Model definition CONSTRAINT-G

CONSTRAINT-G NAME

nodei dofi betai

Defines a generalized linear constraint equation between specified degrees of freedom.

None of the degrees of freedom are made dependent (there are no slave degrees of freedom).The generalized constraints are imposed using Lagrange Multipliers, and can only be appliedto nodes and not geometric entities.

Note that GLUEMESH automatically creates generalized constraint equations that enforceglueing.

NAME [(highest generalized constraint label number) + 1]Label number of the generalized constraint.

nodeiNode label associated with the ith term (degree of freedom) in the generalized constraintequation.

dofiDegree of freedom (global or skew direction) at nodei.{X-TRANSLATION /Y-TRANSLATION / Z-TRANSLATION / X-ROTATION / Y-ROTATION /

Z-ROTATION}

betaiCoefficient for the ith term.



FIXITY NAME

dofi

FIXITY defines a fixity boundary condition which is referenced by FIXBOUNDARY, whichassigns the fixity to a given geometry entity. All degrees of freedom are assumed free unlessfixed by this command (subject to the overall control of active degrees of freedom as deter-mined by MASTER ).

NAMEThe identifying name of the fixity condition (1 to 30 alphanumeric characters).

Note: The following predefined fixities exist (and cannot be updated):

ALL All degrees of freedom are fixed.

NONE No degrees of freedom are fixed.

dofiDegree(s) of freedom to be fixed. {X-TRANSLATION/Y-TRANSLATION/Z-TRANSLATION/X-ROTATION/Y-ROTATION/Z-ROTATION/OVALIZATION/FLUID-POTENTIAL/PORE-FLUID-PRESSURE/BEAM-WARP}

Note: The fixity conditions will be applied to the nodes of the model, albeit indirectly,via the model geometry. The translations and rotations of the fixity thus refer tothe degree-of-freedom system at each node, which may be the global coordinatesystem or a skewsystem. (See SKEWSYSTEM, DOF-SYSTEM ).

Auxiliary commands

LIST FIXITY NAMEDELETE FIXITY NAME

FIXITY



FIXBOUNDARY POINTS FIXITY

pointi fixityi

FIXBOUNDARY LINES FIXITY

linei fixityi

FIXBOUNDARY SURFACES FIXITY

surfacei fixityi

FIXBOUNDARY VOLUMES FIXITY

volumei fixityi

FIXBOUNDARY EDGES FIXITY BODY

edgei fixityi

FIXBOUNDARY FACES FIXITY BODY

facei fixityi

FIXBOUNDARY BODIES FIXITY

bodyi fixityi

FIXBOUNDARY NODE-SETS FIXITY

node-seti fixityi

FIXBOUNDARY assigns fixity conditions to a set of geometry entities.

FIXITY [ALL]Default fixity condition (see command FIXITY ) for geometry entities given in the subsequentdata lines.


FIXBOUNDARY POINTS



pointiLabel number of a geometry point.


surfaceiLabel number of a geometry surface.volumeiLabel number of a geometry volume.

edgeiLabel number of a geometry edge (for BODY).

faceiLabel number of a geometry face (for BODY).

bodyiLabel number of a geometry body.

node-setiLabel number of a node-set.

fixityi [FIXITY]Fixity condition to be applied at the geometry entity.

Auxiliary commands

LIST FIXBOUNDARY POINTS FIRST LASTDELETE FIXBOUNDARY POINTS FIRST LAST

LIST FIXBOUNDARY LINES FIRST LASTDELETE FIXBOUNDARY LINES FIRST LAST

LIST FIXBOUNDARY SURFACES FIRST LASTDELETE FIXBOUNDARY SURFACES FIRST LAST

LIST FIXBOUNDARY VOLUMES FIRST LASTDELETE FIXBOUNDARY VOLUMES FIRST LAST

LIST FIXBOUNDARY EDGES FIRST LASTDELETE FIXBOUNDARY EDGES FIRST LAST

FIXBOUNDARY POINTS



LIST FIXBOUNDARY FACES FIRST LASTDELETE FIXBOUNDARY FACES FIRST LAST

LIST FIXBOUNDARY BODIES FIRST LASTDELETE FIXBOUNDARY BODIES FIRST LAST

LIST FIXBOUNDARY NODE-SETS FIRST LASTDELETE FIXBOUNDARY NODE-SETS FIRST LAST

FIXBOUNDARY POINTS



ZOOM-BOUNDARY NAME GTYPE

namei bodyi

Specifies the boundary of a mesh overlay model that is inside (internal to) the coarse model(see Figure A). Note that if no zoom boundary is defined, all the boundary of the meshoverlay model will be treated as being inside the coarse model (see Figure B, next page).

NAME [current highest ZOOM-BOUNDARY label number + 1]Label number of the ZOOM-BOUNDARY to be defined.

GTYPE [TWO-D]{TWO-D / THREE-D / NODESET}

The geometry type used to define ZOOM-BOUNDARY.

TWO-D line or edge THREE-D surface or face NODESET node set

ZOOM-BOUNDARY

Figure A: Internal boundary must be defined

Coarse modelMesh overlay model

This part of the boundary ofthe mesh overlay needs to bespecified as internal boundary



nameiList of geometry label numbers or node set numbers.

bodyiGeometry body label of edges and faces.

Auxiliary commands

LIST ZOOM-BOUNDARY FIRST LASTDELETE ZOOM-BOUNDARY FIRST LAST

ZOOM-BOUNDARY

Coarse ModelMesh Overlay Model

Figure B: No need to define internal boundary

Since the mesh overlay modelis completely inside the coarsemodel, there is no need to identifythe internal boundary.



ENDRELEASE NAME MOMENT1 MOMENT2 MOMENT3 MOMENT4MOMENT5 MOMENT6

Defines an �endrelease� condition for elements of type BEAM, which may be used toprescribe that selected end forces and/or moments of the elements are zero. The endreleasemay be referenced (e.g. by LINE-ELEMDATA ) to assign the endrelease to the elements (on agiven geometry line).

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NAME [(current highest endrelease label number) + 1]The label number of the endrelease condition to be defined.

MOMENTi [0]List of up to six identifiers (i = 1,...,6) indicating which of the element end forces on momentsare prescribed to be zero. See Figure.

1 Force in r-direction at local node 1 = 0.0.

2 Force in s-direction at local node 1 = 0.0.

3 Force in t-direction at local node 1 = 0.0.

ENDRELEASE


Chap. 7 Model definition ENDRELEASE

4 Moment about r-axis at local node 1 = 0.0.

5 Moment about s-axis at local node 1 = 0.0.

6 Moment about t-axis at local node 1 = 0.0.

7 Force in r-direction at local node 2 = 0.0.

8 Force in s-direction at local node 2 = 0.0.

9 Force in t-direction at local node 2 = 0.0.

10 Moment about r-axis at local node 2 = 0.0.

11 Moment about s-axis at local node 2 = 0.0.

12 Moment about t-axis at local node 2 = 0.0.

0 No selection.

Auxiliary commands

LIST ENDRELEASE FIRST LASTDELETE ENDRELEASE FIRST LAST



FSBOUNDARY LINES NAME

linei

FSBOUNDARY SURFACES NAME

surfacei

FSBOUNDARY EDGES NAME BODY

edgei

FSBOUNDARY FACES NAME BODY

facei

Defines a fluid-structure-interaction boundary, as a set of geometry lines/edges (2-D analy-sis), or as a set of geometry surfaces/faces (3-D analysis), which establish those areas of thestructure, which may interact with fluid flow.

Note that the FSBOUNDARY defined is not referenced by another ADINA-IN for ADINAcommand, but may be referenced by the BOUNDARY-CONDITION FLUID-STRUCTUREcommand for ADINA-F.

NAME [(current highest fsboundary label number) + 1]Label number of the fluid-structure-boundary to be defined.

BODYBody label number.

lineiGeometry line label number.

surfaceiGeometry surface label number.

edgeiGeometry edge label number (for BODY).

faceiGeometry face label number (for BODY).

Auxiliary commands

LIST FSBOUNDARY FIRST LASTDELETE FSBOUNDARY FIRST LAST

FSBOUNDARY


Chap. 7 Model definition FSBOUNDARY TWO-D

FSBOUNDARY TWO-D NAME

namei bodyi

Defines a fluid-structure-interaction boundary, as a set of geometry lines/edges (2D analysis)that establish those areas of the structure to be analysed using ADINA. This boundary mayinteract with a fluid flow analysed by ADINA-F.

Note that the FSBOUNDARY defined is not referenced by another ADINA-IN for ADINAcommand, but rather may be referenced by the BOUNDARY-CONDITION FLUID-STRUC-TURE command for ADINA-F.


nameiGeometry line/edge label number.

bodyiGeometry body label number.

Auxiliary commands




FSBOUNDARY THREE-D NAME

namei bodyi

Defines a fluid-structure-interaction boundary, as a set of geometry surfaces/faces (3Danalysis) that establish those areas of the structure to be analysed using ADINA. Thisboundary may interact with a fluid flow analysed by ADINA-F.

Note that the FSBOUNDARY defined is not referenced by another ADINA-IN for ADINAcommand, but rather may be referenced by the BOUNDARY-CONDITION FLUID-STRUC-TURE command for ADINA-F.


nameiGeometry line/edge label number.

bodyiGeometry body label number.

Auxiliary commands


FSBOUNDARY THREE-D



POTENTIAL-INTERFACE ADINA-F NAME GTYPE BODY

POTENTIAL-INTERFACE FLUID-FLUID NAME GTYPE BODY

POTENTIAL-INTERFACE FLUID-STRUCTUR NAME GTYPE BODY

POTENTIAL-INTERFACE FREE-SURFACE NAME GTYPE BODY

POTENTIAL-INTERFACE INLET-OUTLET NAME GTYPE BODY

POTENTIAL-INTERFACE RIGID-WALL NAME GTYPE BODY

namei bodyi

Defines an interface between potential-based fluid elements and structural elements.

NAME [(current potential-interface label number) + 1]Label number of the potential-interface to be defined.

GTYPE [LINES]The type of geometry used to define the potential-interface.{LINES/SURFACES/EDGES/FACES/THREE-D/NODES/NODESETS}

BODY [1]Label number of a solid geometry body. Must be specified when GTYPE=EDGES or FACES.

nameiLabel number of a geometry entity or node.

bodyi [0]Label number of a solid geometry body. Used when GTYPE=THREE-D and namei is a face.bodyi=0 means that namei is a surface.

POTENTIAL-INTERFACE



Auxiliary commands

LIST POTENTIAL-INTERFACE FIRST LASTDELETE POTENTIAL-INTERFACE FIRST LAST

POTENTIAL-INTERFACE



POTENTIAL-INTERFACE INFINITE NAME GTYPE BODY INFTYPE RADIUSPRESSURE VELOCITY ALL-EXT

namei bodyi

Defines an interface between potential-based fluid elements and an infinite boundary.

NAME [(current potential-interface label number) + 1]Label number of the potential-interface to be defined.

GTYPE [LINES]The type of geometry used to define the infinite potential-interface.{LINES/SURFACES/EDGES/FACES/THREE-D/NODESETS}

BODY [1]Label number of a solid geometry body. Must be specified when GTYPE=EDGES or FACES.

INFTYPE [PLANAR]The type of infinite boundary.{PLANAR/CYLINDRICAL/SPHERICAL}

RADIUS [1.0]The radius of cylinder or sphere.

PRESSURE [0.0]The pressure at infinity, used only for a planar infinite boundary in conjunction with thesubsonic formulation for the potential-based fluid elements.

VELOCITY [0.0]The velocity at infinity, used only for a planar infinite boundary in conjunction with thesubsonic formulation for the potential-based fluid elements. The velocity is assumed to benormal to the planar boundary and is positive for flow out of the planar boundary.

ALL-EXT

nameiLabel number of a geometry entity or node.

bodyi [0]Label number of a solid geometry body. Used when GTYPE=THREE-D and namei is a face.bodyi=0 means that namei is a surface.

POTENTIAL-INTERFACE INFINITE



Auxiliary commands

LIST POTENTIAL-INTERFACE FIRST LASTDELETE POTENTIAL-INTERFACE FIRST LAST

POTENTIAL-INTERFACE INFINITE



BOUNDARY-SURFACE SURFACE-TENSION NAME GTYPE ALL-EXT NODESSUBTYPE SIGMAT

namei bodyi

Defines a surface tension boundary for ADINA.

NAME [(current highest surface-tension label number) + 1]Label number of the surface-tension to be defined.

GTYPE [TWO-D]The type of geometry used to define the surface boundary condition.{TWO-D/THREE-D/ELEMENT-EDGESET/ELEMENT-FACESET}

ALL-EXT(Currently not used)

NODES [0]Number of nodes for each element. Only used if the surface tensionboundary is not attached to any finite elements. {0/2/3/4/8/9}

SUBTYPE [PLANE]The type of 2-D surface tension boundary. Only used if the boundary is not attached to anyfinite elements. If the boundary is attached to finite elements, the subtype of the 2-D finiteelements will be used. {AXISYMMETRIC/PLANE}

SIGMAT [0.0]Surface tension value.

nameiLabel number of a geometry entity or element edge/face set.

bodyi [0]Label number of a solid geometry body. Used when GTYPE=TWO-D/THREE-D and nameiis a face or edge. bodyi=0 means that namei is a surface or line.

Auxiliary commands

LIST BOUNDARY-SURFACE ALL FIRST LASTDELETE BOUNDARY-SURFACE ALL FIRST LAST

BOUNDARY-SURFACE SURFACE-TENSION




BOUNDARY-SURFACE SURFACE-TENSION



OVALIZATION-CONSTRAINT POINT TYPE

pointi

Enforces the zero-slope-of-skin in the longitudinal direction for pipe element nodes.

TYPE

FLANGE The flange condition is applied at the specified points. Bothovalization and warping at these points are suppressed.

SYMMETRY The symmetry condition is applied to the specified points. Theovalization at these points is left free but the warping suppressed.

pointiA point label number where the constraint of the ovalization derivative is enforced.

Auxiliary commands

LIST OVALIZATION-CONSTRAINT POINT FIRST LASTDELETE OVALIZATION-CONSTRAINT POINT FIRST LAST

OVALIZATION-CONSTRAINT POINT



FREESURFACE

linei (for FLUID2 element groups)

or

surfacei (for FLUID3 element groups)

Defines the free surface on the boundary lines (2-D) or surface (3-D) of previously-definedsurfaces (2-D) or volumes (3-D) consisting of potential-based elements.

lineiGeometry line label number.

surfaceiGeometry surface label number.

FREESURFACE


Chap. 7 Model definition BCELL

BCELL NAME REVERSE

celli n1i n2i n3i n4i

Defines a boundary cell using 4-node or 3-node cells. A boundary cell must be defined by all3-node cells or all 4-node cells. It cannot be defined by a mixture of 3-node and 4-node cells.

NAME [(current highest bcell label number) + 1]Label number of the boundary cell to be defined.

REVERSE [NO]{NO/YES}Normal direction reverse flag.

celliCell label number.

n1i n2i n3i n4iNode labels for celli .

Auxiliary commands

LIST BCELL FIRST LASTDELETE BCELL FIRST LAST




BCELL



LOAD CENTRIFUGAL NAME OMEGA FACTOR AX AY AZBX BY BZ ALPHA

Defines a combination of a centrifugal load and a tangential load.

The centrifugal load vector is calculated as

(mass) ××××× OMEGA2 ××××× FACTOR ××××× f(t) × × × × × (radius)

and the tangential load vector is calculated as

(mass) ××××× ALPHA ××××× FACTOR ××××× f(t) × × × × × (radius)

when ALPHA is non-zero.

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where �mass� is a concentrated nodal point mass or a differential mass element at a distance�radius� from the axis of revolution. The load may be applied to the model via APPLY-LOADwhereby it may also be assigned a time function, specifying how its magnitude varies in time.Only one centrifugal load may currently be applied to the model.

LOAD CENTRIFUGAL


Sec. 7.8 Loading

NAME [(current highest centrifugalload label number) + 1]

Label number of the centrifugal load to be defined.

OMEGAAngular velocity.

FACTORMultiplying factor.

AX [0.0]AY [0.0]AZ [0.0]Position vector (in global coordinate system) of one end of axis of revolution, see Figure.

BX [1.0]BY [0.0]BZ [0.0]Position vector (in global coordinate system) of other end of axis of revolution. See Figure.

ALPHA [0.0]Angular acceleration.

Auxiliary commands

LIST LOAD CENTRIFUGAL FIRST LASTDELETE LOAD CENTRIFUGAL FIRST LAST

LOAD CENTRIFUGAL



LOAD CONTACT-SLIP NAME OMEGA FACTOR AX AY AZ BX BY BZ

Defines a contact-slip load. The actual tangential slip of a contact surface is calculated as

OMEGA * FACTOR * (RADIUS) * F(t)

The load may be applied to a contact surface via command APPLY-LOAD whereby it may alsobe assigned a time function F(t), specifying how its magnitude varies with time.

NAME [(current highest contact-slip load label number) + 1]Label number of the contact-slip load to be defined. If the label number of an existing contact-slip load is given, then the previous contact-slip load definition is overwritten.

OMEGAAngular velocity.

FACTORMultiplying factor.

AX [0.0]AY [0.0]AZ [0.0]Position vector (in global coordinate system) of one end of axis of revolution.

BX [1.0]BY [0.0]BZ [0.0]Position vector (in global coordinate system) of other end of axis of revolution.

Auxiliary commands

LIST LOAD CONTACT-SLIP FIRST LASTDELETE LOAD CONTACT-SLIP FIRST LAST

LOAD CONTACT-SLIP


Sec. 7.8 LoadingLOAD CONVECTION

LOAD CONVECTION NAME MAGNITUDE C-PROP

Defines a convection load, i.e., prescribed environmental temperatures for convectionelement nodes. Note that the command only defines a convection load, to apply it to themodel you must use APPLY-LOAD.

NAME [(current highest convection load label number) + 1]Label number of the convection load to be defined.

MAGNITUDEEnvironmental temperature (in chosen units).

C-PROP [0]The label number of convection property command C-PROP. It is only used for ADINA TMCanalysis. In TMC analysis, if C-PROP = 0 means parameters TYPE = CONSTANT and H = 0.0in the C-PROP command.

Auxiliary commands

LIST LOAD CONVECTION FIRST LASTDELETE LOAD CONVECTION FIRST LAST





Sec. 7.8 Loading

LOAD DISPLACEMENT NAME DX DY DZ AX AY AZ

Defines a prescribed displacement load. This command defines prescribed displacementswhich may be assigned to certain degrees of freedom (global or skew) of the model. Note thatthis command only defines a displacement load, to apply it to the model you must useAPPLY-LOAD.

NAME [(current highest displacement load label number) + 1]Label number of the displacement load to be defined.

DX [FREE]Prescribed value for the X-translation (or a-translation for a skew dof-system) degree offreedom.

DY [FREE]Prescribed value for the Y-translation (or b-translation for a skew dof-system) degree offreedom.

DZ [FREE]Prescribed value for the Z-translation (or c-translation for a skew dof-system) degree offreedom.

AX [FREE]Prescribed value for the X-rotation (or a-rotation for a skew dof-system) degree of freedom, inradians.

AY [FREE]Prescribed value for the Y-rotation (or b-rotation for a skew dof-system) degree of freedom, inradians.

AZ [FREE]Prescribed value for the Z-rotation (or c-rotation for a skew dof-system) degree of freedom, inradians.

Note: For parameters DX, DY, DZ, AX, AY, AZ the value FREE may be specified,indicating that the corresponding degree of freedom is not prescribed.

Auxiliary commands

LIST LOAD DISPLACEMENT FIRST LASTDELETE LOAD DISPLACEMENT FIRST LAST

LOAD DISPLACEMENT



LOAD ELECTROMAGNETIC NAME

Defines an electromagnetic load. Note that the command only defines a electromagnetic load,to apply it to the model you must use APPLY-LOAD.

NAME [(current highest electromagneticload label number)+ 1]

Label number of the electromagnetic load to be defined.

Note: The magnitude of the load is governed by the currents specified by thetimefunction parameter of APPLY-LOAD.

Auxiliary commands

LIST LOAD ELECTROMAGNETIC FIRST LASTDELETE LOAD ELECTROMAGNETIC FIRST LAST

LOAD ELECTROMAGNETIC


Sec. 7.8 Loading

LOAD FORCE NAME MAGNITUDE FX FY FZ

Defines a force load. Note that the command only defines a force load, to apply it to themodel you must use APPLY-LOAD.

NAME [(current highest forceload label number) + 1]

Label number of the force load to be defined.

MAGNITUDEForce magnitude.

FX [1.0]FY [0.0]FZ [0.0]Force direction.

Note: The vector (FX, FY, FZ) specifies only the direction of the force.

Auxiliary commands

LIST LOAD FORCE FIRST LASTDELETE LOAD FORCE FIRST LAST

LOAD FORCE



LOAD LINE NAME MAGNITUDE

Defines a line load, i.e., a distributed load in terms of force / unit length. Note that thecommand only defines a line load, to apply it to the model you must use APPLY-LOAD.

Note that line loads may be applied to geometry lines or edges, in order to specify distributedloading to BEAM, ISOBEAM, and PIPE elements, and to edges of SHELL elements.

NAME [(current highest lineload label number) + 1]

Label number of the line load to be defined.

MAGNITUDEDistributed load magnitude [force / unit length].

Auxiliary commands

LIST LOAD FORCE FIRST LASTDELETE LOAD FORCE FIRST LAST

LOAD LINE


Sec. 7.8 Loading

LOAD MASS-PROPORTIONAL NAME MAGNITUDE AX AY AZINTERPRETATION

Defines a mass-proportional load. Such loads may be used to model gravity loading(including static analysis) or ground acceleration. The load acts uniformly on the entirestructure. APPLY-LOAD is used to apply a mass-proportional load to the model, at whichtime it may be assigned a time function specifying how its magnitude varies in time. Morethan one mass-proportional load may be applied to the model.

NAME [(current highest mass-proportionalload label number) + 1]

Label number of the mass-proportional load to be defined.

MAGNITUDEMagnitude of mass-proportional loading.

AX [0.0]AY [0.0]AZ [-1.0]Vector giving direction of mass-proportional load. Note the components of the mass-proportional loading are:

MAGNITUDE ××××× AXMAGNITUDE ××××× AYMAGNITUDE ××××× AZ

i.e., the magnitude of vector (AX, AY, AZ) is used together with MAGNITUDE to give thetotal load vector.

INTERPRETATION [BODY-FORCE]Flag indicating static or dynamic effect for potential-based fluid elements:

BODY-FORCE The load is interpreted as a physical body force

GROUND-ACCELERATION The load is interpreted as a ground motion acceleration,and is numerically integrated to obtain ground motionvelocities and displacements.

This parameter is used only by potential-based fluid elements and is not used by any of theother element types.

LOAD MASS-PROPORTIONAL



Auxiliary commands

LIST LOAD MASS-PROPORTIONAL FIRST LASTDELETE LOAD MASS-PROPORTIONAL FIRST LAST

LOAD MASS-PROPORTIONAL


Sec. 7.8 Loading

LOAD MOMENT NAME MAGNITUDE MX MY MZ

Defines a moment load. Note that the command only defines a moment load, to apply it to themodel you must use APPLY-LOAD.

NAME [(current highest moment load label number) + 1]Label number of the moment load to be defined.

MAGNITUDEMoment magnitude.

MX [1.0]MY [0.0]MZ [0.0]Components of moment vector.

Note: The vector (MX, MY, MZ) specifies only the direction of the moment axis.

Auxiliary commands

LIST LOAD MOMENT FIRST LASTDELETE LOAD MOMENT FIRST LAST

LOAD MOMENT



LOAD NODAL-PHIFLUX NAME MAGNITUDE

Defines a nodal-phiflux load. This command defines a prescribed nodal-phiflux which may beassigned to certain degrees of freedom of the model. Note that this command only defines anodal-phiflux load � to apply it to the model you must use command APPLY-LOAD.

NAME [(current highest nodal-phiflux load label number) + 1]Label number of the nodal-phiflux load to be defined. If the label number of an existing nodal-phiflux load is given, then the previous nodal-phiflux load definition is overwritten.

MAGNITUDEPrescribed value for the fluid potential degree of freedom.

Auxiliary commands

LIST LOAD NODAL-PHIFLUX FIRST LASTDELETE LOAD NODAL-PHIFLUX FIRST LAST

LOAD NODAL-PHIFLUX


Sec. 7.8 Loading

LOAD PHIFLUX NAME MAGNITUDE

Defines a phiflux load. Note that this command only defines a phiflux load � to apply it tothe model you must use command APPLY-LOAD.

NAME [(current highest phiflux load label number) + 1]Label number of the phiflux load to be defined. If the label number of an existing phiflux loadis given, then the previous phiflux load definition is overwritten.

MAGNITUDEPrescribed value for the fluid potential degree of freedom.

Auxiliary commands

LIST LOAD PHIFLUX FIRST LASTDELETE LOAD PHIFLUX FIRST LAST

LOAD PHIFLUX





Sec. 7.8 Loading

LOAD PIPE-INTERNAL-PRESSURE NAME MAGNITUDE

Defines a pipe-internal-pressure load. Note that the command only defines a pipe-internal-pressure load, to apply it to the model you must use APPLY-LOAD.

NAME [(current highest pipe-internal-pressureload label number) + 1]

Label number of the pipe-internal-pressure load to be defined.

MAGNITUDEPipe internal pressure magnitude (force / unit area).

Auxiliary commands

LIST LOAD PIPE-INTERNAL-PRESSURE FIRST LASTDELETE LOAD PIPE-INTERNAL-PRESSURE FIRST LAST

LOAD PIPE-INTERNAL-PRESSURE



LOAD POREFLOW NAME MAGNITUDE

Defines a poreflow load. Poreflow loads may be applied ( command APPLY-LOAD ) tosurfaces (element groups THREEDSOLID, TWODSOLID- subtype STRESS3 ) or lines( TWODSOLID element edges ).

NAME [(current highest poreflow load label number) + 1]Label number of the poreflow load to be defined. If the label number of an existing poreflowload is given, then the previous poreflow load definition is overwritten.

MAGNITUDEFlux magnitude (velocity).

Auxiliary commands

LIST LOAD POREFLOW FIRST LASTThe command LIST LOAD POREFLOW lists the loads of type POREFLOW with labelnumbers in a given range. If no range is specified, then a list of all the label numbers ofloads of type POREFLOW is given.

DELETE LOAD POREFLOW FIRST LASTThe command DELETE LOAD POREFLOW deletes all loads of type POREFLOW withlabel numbers in a given range.

Note: A load will not be deleted if it is referenced by the command APPLY-LOAD(i.e. the load has been applied to the model).

Note: For command DELETE LOAD POREFLOW, one of the parameters FIRST,LAST must be specified.

LOAD POREFLOW


Sec. 7.8 Loading

LOAD PORE-PRESSURE NAME MAGNITUDE

Defines a pore-pressure load, which may be assigned to certain degrees of freedom (global orskew) of the model. To apply a pore-pressure load to the model command APPLY-LOADshould be used.

NAME [(current highest pore-pressure load label number) + 1]

Label number of the pore-pressure load to be defined. If the label number of an existing pore-pressure load is given, then the previous pore-pressure load definition is overwritten.

MAGNITUDEPrescribed value for the pore pressure degree of freedom.

Auxiliary commands

LIST LOAD PORE-PRESSURE FIRST LASTDELETE LOAD PORE-PRESSURE FIRST LAST

LOAD PORE-PRESSURE



LOAD PRESSURE NAME MAGNITUDE BETA LINE

Defines a pressure load. Note that the command only defines a pressure load, to apply it tothe model you must use APPLY-LOAD.

Note: Pressure loads may be applied to:

Surfaces/Faces SHELL, THREEDSOLID, TWODSOLID (subtype STRESS3),THREEDFLUID elements.

Lines/Edges TWODSOLID, TWODFLUID element edges.

To apply distributed loads to uni-dimensional elements (e.g., beams) or to edges of shellelements, command LOAD LINE should be used to define such a load in terms of force/unitlength.

Note that for potential-based elements, pressure loads may be applied only on the boundaryof fluid-structure, free-surface, inlet-outlet or fluid-fluid interface elements.

NAME [(current highest pressureload label number) + 1]

Label number of the pressure load to be defined.

MAGNITUDEPressure magnitude [force / unit area].

BETA [0.0]Specifies the angle to the reference line (LINE) that will determine the direction of the tangen-tial traction. (in degrees)

LINE [0]Reference line for tangential traction direction. If LINE=0, the reference direction for thetangential traction will be the parametric u-dir of the surface or face.

Note: The parameters BETA and LINE are only applicable when applying pressure loadingon surface/face and the tangential pressure loading is specified (i.e. idirn=4 incommand APPLY-LOAD).

Auxiliary commands

LIST LOAD PRESSURE FIRST LASTDELETE LOAD PRESSURE FIRST LAST

LOAD PRESSURE


Sec. 7.8 Loading

LOAD RADIATION NAME MAGNITUDE R-PROP

Defines a radiation load, i.e., prescribed radiative source/sink temperatures, at radiationelement nodes. Note that the command only defines a radiation load, to apply it to the modelyou must use APPLY-LOAD.

NAME [(current highest radiation load label number) + 1]Label number of the radiation load to be defined.

MAGNITUDERadiative source/sink temperature (in chosen units).

R-PROP [0]The label number of convection property command R-PROP. It is only used for ADINA TMCanalysis. In TMC analysis, if R-PROP = 0 means parameters TYPE = CONSTANT and E = 0.0in the R-PROP command.

Auxiliary commands

LIST LOAD RADIATION FIRST LASTDELETE LOAD RADIATION FIRST LAST

LOAD RADIATION





Sec. 7.8 Loading

LOAD TEMPERATURE NAME MAGNITUDE

Defines a prescribed temperature load. Note that the command only defines a temperatureload, to apply it to the model you must use APPLY-LOAD.

NAME [(current highest temperatureload label number) + 1]

Label number of the temperature load to be defined.

MAGNITUDETemperature (in chosen units).

Auxiliary commands

LIST LOAD TEMPERATURE FIRST LASTDELETE LOAD TEMPERATURE FIRST LAST

LOAD TEMPERATURE



LOAD TGRADIENT NAME MAGNITUDE

Defines a prescribed temperature gradient load to specify the temperature gradient in thethickness direction of a surface (when applied to shell elements). Note that the command onlydefines a temperature gradient load, to apply it to the model you must use APPLY-LOAD.

NAME [(current highest temperature gradientload label number) + 1]

Label number of the temperature gradient load to be defined.

MAGNITUDETemperature gradient (degrees / unit length).

Auxiliary commands

LIST LOAD TGRADIENTDELETE LOAD TGRADIENT

LOAD TGRADIENT


Sec. 7.8 LoadingCPROP

C-PROP NAME TYPE H ITHETA TBIRTH TDEATH

ti hi

Defines convection properties for convection loading.

NAME [(Current highest label) + 1]The label number of the C-PROP to be defined.

TYPE [CONSTANT]The type of convection property. {CONSTANT/TEMP-DEP/TIME-DEP}

CONSTANT Property is constant

TEMP-DEP Property is temperature dependent

TIME-DEP Property is time dependent

H [0.0]

Convection coefficient. Used for TYPE = CONSTANT only. { ≥ 0.0}

ITHETA [TEMPERATURE]Indicates the dependence of the convection coefficient. Used for TYPE = TEMP-DEP only.{TEMPERATURE/DIFFERENCE}

TEMPERATURE Convection coefficient is a function of surface temperature

DIFFERENCE Convection coefficient is a function of temperature difference

TBIRTH [0.0]Birth time for convection boundary, i.e., time at which the convection boundary becomesactive.

TDEATH [0.0]Death time for convection boundary, i.e. time at which the convection boundary becomesinactive. Note that TDEATH=0.0 has no effect.

tiTemperature at data point i for ITHETA = TEMPERATURETemperature difference at data point i for ITHETA = DIFFERENCETime at data point i for TYPE = TIME-DEP

hiConvection coefficient at ti


Chap. 7 Model definition RPROP

R-PROP NAME TYPE E ISIGMA SIGMA TBIRTH TDEATH

ti ei

Define radiation properties for radiation loading.

NAME [(Current highest label) + 1]The label number of the R-PROP to be defined.

TYPE [CONSTANT]The type of radiation property. {CONSTANT/TEMP-DEP}

CONSTANT Property is constant

TEMP-DEP Property is temperature dependent

E [0.0]

Emissivity coefficient Used for TYPE = CONSTANT only. { ≥ 0.0}

ISIGMA [FAHRENHEIT]Unit of temperature. {FAHRENHEIT/CENTIGRADE/KELVIN/RANKINE}

SIGMA [0.0]

Stefan-Boltzmann constant. { ≥ 0.0}

TBIRTH [0.0]Birth time for radiation boundary, i.e., time at which the convection boundary becomes active.

TDEATH [0.0]Death time for radiation boundary, i.e. time at which the convection boundary becomesinactive. Note that TDEATH=0.0 has no effect.

titemperature at data point i

eiEmissivity coefficient at ti


Sec. 7.8 Loading

LOAD-CASE NAME

LOAD-CASE may be used in a linear static analysis to identify the current load case.

LOAD-CASE cannot be used in the analysis of a cyclic symmetric structure.

If load cases are specified, no reference to, or specification of, time functions can be made.Therefore, use of the commands TIMEFUNCTION, TIMESTEP, or any timefunction referenceby any APPLY-LOAD command, is not allowed.

NAME [(current highest load-caselabel number) + 1]

Label number of the load-case to be defined.

Auxiliary commands

LIST LOAD-CASE FIRST LASTDELETE LOAD-CASE FIRST LAST

LOAD-CASE



LCOMBINATION NAME

lcasei factori

May be used in a linear static analysis to define a new load case as a linear combination ofload cases previously defined by LOAD-CASE. The combination is performed so that

(combined load-case results) = Σ (results for lcasei) × factori

i=1

NAME [(highest lcombination label number) + 1]The label number of the load-combination.

lcaseiThe label number of a load case previously defined by command LOAD-CASE.

factori [1.0]The factor associated with lcasei.

Auxiliary commands

LIST LCOMBINATION FIRST LASTDELETE LCOMBINATION FIRST LAST

LCOMBINATION


Sec. 7.8 Loading

APPLY-LOAD BODY LCASE SHELLNODE

namei ltypei lnamei stypei snamei idvari ncuri artmi idirni

iddli pfocusi bodyi psenseiunloadi timeui forceui ncurui cgroupi shellnodei

(no load cases)

or

namei ltypei lnamei stypei snamei idvari lcasei idirni iddli pfocusi bodyi psenseiunloadi timeui forceui ncurui cgroupi shellnodei

(load cases)

Command APPLY-LOAD specifies the loads applied to a model. This command is used to applynamed loads (see commands LOAD FORCE, LOAD MOMENT, LOAD PRESSURE, etc.) to themodel geometry. The spatial variation of the load may be specified by reference to a data-line,data-surface, or data-volume as appropriate (see command LINE-FUNCTION,SURFACE-FUNCTION, VOLUME-FUNCTION ). The time dependence of the load may bespecified by reference to a time function (see command TIMEFUNCTION ).

BODY [currently active BODY]Solid geometry body label number.

LCASE [1]Load-case number (see LOAD-CASE, LCOMBINATION ).

nameiLabel number of a load application.

ltypeiThe type of load to be applied. {FORCE/MOMENT/PRESSURE/LINE/CENTRIFUGAL/MASS-PROPORTIONAL/DISPLACEMENT/TEMPERATURE/TGRADIENT/PIPE-INTERNAL-PRESSURE/ELECTROMAGETIC/POREFLOW/POREPRESSURE/CON-TACT-SLIP/PHIFLUX/NODAL-PHIFLUX}

In addition, for TMC analysis only, the following choices are available:

CONVECTIONRADIATIONNODAL-HEATFLOWHEATFLUXINTERNALHEATLATENT

A table of load types and the corresponding allowed application site types is given below.

APPLY-LOAD



lnameiLabel number of the load (defined by LOAD FORCE, etc.).

stypeiThe type of site where the load is to be applied. {POINT/LINE/SURFACE/VOLUME/EDGE/FACE/BODY/MODEL/NODE-SET/ELEMENT-EDGE-SET/ELEMENT-FACE-SET/CONTACT-SURFACE}

snameiThe label number of the application site, e.g., point label number, line label number, etc.

idvari [0]The label number of the spatial function (defined by LINE-FUNCTION, SURFACE- FUNC-TION, VOLUME-FUNCTION as appropriate). Enter 0 for the load to be considered constantin space (but not necessarily in time). If load ltypei=PRESSURE and stypei=FACE, idvari isthe surface spatial function for the reference surface (pfocusi).

Note:The spatial variation along the reference line is used to determine the spatial variation of theload on the face. For a point on the face, the closest point on the line is determined and thespatial value at that point is used.

ncuri [1]The label number of a time function, as defined by command TIMEFUNCTION.

artmi [0.0]The �arrival time� associated with time dependent loads. The load is considered zero fort ≤ artmi, and is governed by the time function �ncuri� for t > artmi. The time function iseffectively shifted along in the time direction. See the Theory and Modeling Guide.

idirni [0]Specifies the load direction for pressure load or distributed line load. {0/1/2/3/4/11/12/13}

0 total (normal) pressure load is applied. 1 only the X-component of the load is applied. 2 only the Y-component of the load is applied. 3 only the Z-component of the load is applied. 4 tangential traction.11 load acts in the global X-direction.12 load acts in the global Y-direction.13 load acts in the global Z-direction.

The following table lists the allows load types and application site types:

APPLY-LOAD


Sec. 7.8 Loading

Table: Allowed load type / application site types

Point Line Surface Volume Edge Face Body Others

Force1 ! ! ! × ! ! ×

Moment1 ! × × × × × ×

Pressure2 × ! ! × ! ! ×

Line × ! × × ! × ×

Centrifugal × × × × × × × Model

Mass × × × × × × × Modelproportional

Displacement1 ! ! ! ! ! ! !

Temperature1 ! ! ! ! ! ! !

Temperature ! ! ! × ! ! ×gradient1

Pipe-Internal ! ! × × ! × ×pressure1

Electro- × ! × × ! × ×magnetic

Pore flow2 × ! ! × ! ! ×

Pore ! ! ! ! ! ! !pressure1

Contact slip Contact surface

Phiflux2 × ! ! × ! ! ×

Nodal phiflux1 ! × × × × × ×

Convection1,3 ! ! ! × ! ! ×

Radiation1,3 ! ! ! × ! ! ×

Nodal-heatflow1,3! × × × × × ×

Heatflux2,3 × ! ! × ! ! ×

Internalheat1,3 × ! ! ! ! ! ! Group

Latent3 × × × × × × × Group

Notes:1. Can also be applied to Node Sets.2. Can also be applied to Element-Edge Sets and Element-Face Sets.3. Can only be applied in TMC analysis.

APPLY-LOAD


Chap. 7 Model definition APPLY-LOAD

iddli [-1]If ltypei={PRESSURE/LINE/CENTRIFUGAL/ELECTROMAGNETIC/PORE FLOW}, thisspecifies whether the load is deformation-dependent, i.e. the direction of the load changes inresponse to the (large displacement) deformation of the structure. {0/1/-1}

0 the load is independent of structural deformation. 1 the load is deformation-dependent.-1 the load is deformation-dependent for large displacement or large strain

formulation, otherwise the load is deformation independent.

iddli [0]If ltypei=DISPLACEMENT, this specifies whether the prescribed displacement is measuredrelative to the original configuration or to the deformed configuration {0/1}.

The �deformed� configuration is the configuration at the arrival time of the prescribeddisplacement (if the arrival time is not equal to zero), or the configuration at the start time ofthe current analysis (which can be a restart analysis).

0 Original configuration1 Deformed configuration

pfocusi [0]Specifies a point which determines the plane of load application for loads of type LINE. Itmay also be used to specify a �follower� force or moment, in which case the direction of theload application is determined by the relative positions of the point of application and thefocus point �pfocusi�. If point �pfocusi� is input, then a unique node must be defined at thesame location as the focus point. If load ltypei=PRESSURE and stypei=FACE, pfocusi meansthe reference surface for spatial function of surface.

bodyi [BODY]Body label number, used when stypei = FACE or EDGE.

psensei [0]Qualifies the direction of the distributed line load controlled by the point �pfocusi�. Ifpsensei=0 then the plane of action of the load is determined by the focal point and the endnodes of each element edge along the application line; in this case a single auxiliary node willbe generated at the focal point. If psensei=1 the load will act perpendicular to the planedefined by the focal point and the element edge end nodes; in this case an auxiliary node willbe generated for each element edge along the line (positioned �above� the plane defined bythe vertex nodes and the focal point). Furthermore, for psensei=0 (in-plane) a positive loadacts toward the element from the focal point. The convention for load direction whenpsensei=1 can be understood as follows: imagine walking along the line in its positiveparametric direction (i.e. from the start point to the end point) such that the focal point isalways above you - a positive load is then assumed to act from your left.


Sec. 7.8 Loading

unloadi [NO]Specifies the type of unloadng for prescribed displacement. {TIME/FORCE/NO}

timeui [0.0]If unloadi=TIME, this specifies the time at which unloading of prescribed displacement starts.

forceui [0.0]If unloadi=TIME and forceui = 0.0, then the prescribed force for time > timeui is equal to thereaction force multiplied by the value of time function ncurui.

If unloadi=TIME and forceui ≠ 0.0, then the prescribed force for time > timeui is equal toforceui multiplied by the value of time function ncurui.

If unloadi=FORCE, then the prescribed displacement becomes a prescribed force for thesolution step after the step in which the reaction force exceeds forceui. The value of theprescribed force is equal to forceui multiplied by the value of time function ncurui. forceuicannot equal 0.0 if unloadi=FORCE.

ncurui [1]Label number of a time function for the unloading of prescribed displacement.

cgroupi [0]Contact group label number.

shellnodei [MID]Specifies whether the loads is applied to the top, bottom or both top and bottom of shellsurface.{TOP/BOTTOM/MID}

TOP The load is applied to top surfaceBOTTOM The load is applied to bottom surface

. MID The load is applied to shell midsurface. This option is only usedfor temperature loading. If no temperature gradient is applied at theshell node, the top and bottom shell surface will have the sametemperature.

Note that this parameter is used only for temperature, heat flux, convection and radiationloading in TMC analysis

Auxiliary commands

LIST APPLY-LOADDELETE APPLY-LOAD

APPLY-LOAD




APPLY-LOAD


Sec. 7.8 Loading

LOAD-PENETRATION

groupi

Defines a region in terms of element groups where an initial pressure load can penetrate; i.e. ifan element in the region, to which a pressure load is applied ruptures or �dies�, the pressureload is distributed to its neighboring element faces. This command is only active if

MASTER LOAD-PENETRATION = YES.

Note: A pressure load must already be applied to the penetration region, seeAPPLY-LOAD or LOADS-ELEMENT.

groupiElement group label number.

Auxiliary commands

LIST LOAD-PENETRATIONDELETE LOAD-PENETRATION

LOAD-PENETRATION



INITIAL-CONDITION NAME INITIALSTRESS

variablei valuei

Defines an initial condition that can be referenced by SET-INITCONDITION to assign theinitial condition to geometry entities. All variables are assumed initially zero unless set bythis command in conjunction with SET-INITCONDITION.

NAMEThe identifying name of the initial condition (1 to 30 alphanumeric characters).

INITIALSTRESS [NO]Controls whether the initial strain input at nodes are to be interpreted initial stresses.

NO No change to nodal initial strain input.

YES Nodal initial strains are to be interpreted as initial stresses.

DEFORMATION Nodal initial strains are to be interpreted as initial stresseswhich result in deformations.

variableiDegree(s) of freedom or their time derivatives to be set initially. Possible values (strings) are:

INITIAL-CONDITION

X-TRANSLATIONY-TRANSLATIONZ-TRANSLATIONX-ROTATIONY-ROTATIONZ-ROTATIONX-VELOCITYY-VELOCITYZ-VELOCITY

OVALIZATION-1OVALIZATION-2OVALIZATION-3OVALIZATION-4OVALIZATION-5OVALIZATION-6

XROT-VELOCITYYROT-VELOCITYZROT-VELOCITYX-ACCELERATIONY-ACCELERATIONZ-ACCELERATIONXROT-ACCELERATIONYROT-ACCELERATIONZROT-ACCELERATION

WARPING-1WARPING-2WARPING-3WARPING-4WARPING-5WARPING-6

TEMPERATURETGRADIENTPIPE-INTERNAL-PRESSURESTRAIN-11STRAIN-22STRAIN-33STRAIN-12STRAIN-13STRAIN-23

FLUID-DOFFPOT-VELOCITYFPOT-ACCELERATIONSTRAIN-GRADIENT-11STRAIN-GRADIENT-22STRAIN-GRADIENT-12STRAIN-GRADIENT-13STRAIN-GRADIENT-23FLEXURAL-STRAIN-11FLEXURAL-STRAIN-22FLEXURAL-STRAIN-12


Sec. 7.9 Initial conditionsINITIAL-CONDITION

valueiThe value to be assigned to �variablei�.

Note: The initial conditions will be applied to the nodes of the model, albeit indirectly viathe model geometry. The variables of the initial condition thus refer to the degree-of-freedom system at each node, which may be the global coordinate system or askewsystem. See SKEWSYSTEM, DOF-SYSTEM.

Auxiliary commands

LIST INITIAL-CONDITION NAMEDELETE INITIAL-CONDITION NAME



SET-INITCONDITION POINTS CONDITION

pointi conditioni

SET-INITCONDITION LINES CONDITION

linei conditioni idvari

SET-INITCONDITION SURFACES CONDITION

surfacei conditioni idvari

SET-INITCONDITION VOLUMES CONDITION

volumei conditioni idvari

SET-INITCONDITION EDGES CONDITION BODY

edgei conditioni idvari

SET-INITCONDITION FACES CONDITION BODY

facei conditioni idvari

SET-INITCONDITION BODIES CONDITION BODY

bodyi conditioni

SET-INITCONDITION NODE-SET CONDITION

node-seti conditioni

SET-INITCONDITION POINTS assigns initial conditions to a set of geometry points.

SET-INITCONDITION LINES assigns initial conditions to a set of geometry lines.

SET-INITCONDITION SURFACES assigns initial conditions to a set of geometry surfaces.

SET-INITCONDITION VOLUMES assigns initial conditions to a set of geometry volumes.

SET-INITCONDITION


Sec. 7.9 Initial conditions

SET-INITCONDITION EDGES assigns initial conditions to a set of solid geometry edges.

SET-INITCONDITION FACES assigns initial conditions to a set of solid geometry faces.

SET-INITCONDITION BODIES assigns initial conditions to a set of solid geometry bodies.

SET-INITCONDITION NODE-SET assigns initial conditions to sets of nodes.

CONDITION [lowest (alphabetically) INITIAL-CONDITION]Default initial condition ( see command INITIAL-CONDITION ) for subsequent data lines.

BODY [currently active body]Label number of a solid geometry body.





edgeiLabel number of a solid geometry edge (for BODY).

faceiLabel number of a solid geometry face (for BODY).

bodyiLabel number of a solid geometry body.

conditioni [CONDITION]Initial condition to be applied at point �pointi�.

idvari [0]Label number of a spatial data variation, defined by LINE-FUNCTION, SURFACE-FUNCTIONor VOLUME-FUNCTION, as appropriate. A 0 value indicates the initial condition is assumedconstant over the geometry entity.

SET-INITCONDITION



Auxiliary commands

LIST SET-INITCONDITION POINTS FIRST LASTDELETE SET-INITCONDITION POINTS FIRST LAST

LIST SET-INITCONDITION LINES FIRST LASTDELETE SET-INITCONDITION LINES FIRST LAST

LIST SET-INITCONDITION SURFACES FIRST LASTDELETE SET-INITCONDITION SURFACES FIRST LAST

LIST SET-INITCONDITION VOLUMES FIRST LASTDELETE SET-INITCONDITION VOLUMES FIRST LAST

LIST SET-INITCONDITION EDGES FIRST LASTDELETE SET-INITCONDITION EDGES FIRST LAST

LIST SET-INITCONDITION FACES FIRST LASTDELETE SET-INITCONDITION FACES FIRST LAST

LIST SET-INITCONDITION BODIES FIRST LASTDELETE SET-INITCONDITION BODIES FIRST LAST

SET-INITCONDITION



STRAIN-FIELD NAME A B C D E F

Defines an initial geological strain field which varies in the global z-direction for 2-D and 3-Dsolid elements. This strain-field may be referenced by element groups using commandsEGROUP TWODSOLID and EGROUP THREEDSOLID (Section 8.1) in order to give initialelement strains.

NAME [(current highest strain-field label number) + 1]Label number of the strain-field to be defined.

A [0.0]B [0.0]C [0.0]D [0.0]E [0.0]F [0.0]Parameters used to evaluate an initial strain field as follows:

TWODSOLID elements:

e A B z

e C e D

e E e F

22

11 22

33 22

= + ⋅= ⋅ += ⋅ + (axisymmetric analysis only)

THREEDSOLID elements:

e A B z

e C e D

e E e F

33

11 33

22 33

= + ⋅= ⋅ += ⋅ +

where eij are the normal components of initial strain, and z is the global z-coordinate.

Auxiliary commands

LIST STRAIN-FIELD FIRST LASTDELETE STRAIN-FIELD FIRST LAST

STRAIN-FIELD



IMPERFECTION POINTS

bucklingmodei pointi directioni displacementi

Specifies imperfections based on the buckling mode shapes, which have been calculated andstored in a previous run. The total imperfection applied is a superposition of the imperfec-tions from each specified buckling mode. List of buckling modes has to be continous - allbuckling modes between the first and last mode have to be specified. For modes which arenot significant, displacementi should be set to 0.

bucklingmodeiThe number of the buckling mode-shape.

pointiPoint label number where the magnitude of imperfection is specified.

directioniTranslational degree of freedom for displacementi.

1 X-translation (a-translation if skew system).

2 Y-translation (b-translation if skew system).

3 Z-translation (c-translation if skew system).

displacementiMagnitude of imperfection in the same length unit as the global coordinates. ADINA scalesthe buckling mode shape indicated by bucklingmodei to have this value for the node at thepoint and in the direction specified.

Auxiliary commands

LIST IMPERFECTION POINTSDELETE IMPERFECTION POINTS

IMPERFECTION POINTS



IMPERFECTION SHAPE OPTION

Indicates when initial nodal displacements should be read for initial shape calculations (butnot for initial load vector or stress calculations) (OPTION = READ), or when ADINA shouldwrite out all nodal displacements (OPTION = WRITE).

OPTION [READ]The flag of initial imperfection input:

READ Read initial nodal displacements.

WRITE Save nodal displacements.

Auxiliary commands

LIST IMPERFECTION SHAPEDELETE IMPERFECTION SHAPE

IMPERFECTION SHAPE



INITIAL-MAPPING FILENAME EXTERNAL-NODE DISTANCE TIME ORDER

variablei

Loads an initial �mapping-file� and interpolates variable values at existing model nodes usingvariable values at another set of nodes for a mesh which is stored in the initial mapping file.

FILENAMEThe mapping file to be loaded. {Any filename accepted by the computer system (up to 80characters long)}.

EXTERNAL-NODE [ALL]The option for the treatment of external nodes (i.e., outside the boundary of the meshcontained in the mapping-file).

ALL Interpolation for all external nodes.

NONE No interpolation (extrapolation).

DISTANCE Interpolation for nodes which are within a maximumspecified distance from the mapping-file mesh.

DISTANCE [0.0]Maximum allowed distance from the mapping-file mesh (used when EXTERNAL-NODE =DISTANCE).

variableiDegree(s) of freedom or their time derivatives to be interpolated for as nodal initial conditions.These include the following:

X-TRANSLATION Y-TRANSLATION Z-TRANSLATIONX-VELOCITY Y-VELOCITY Z-VELOCITYX-ACCELERATION Y-ACCELERATION Z-ACCELERATION

X-ROTATION Y-ROTATION Z-ROTATIONXROT-VELOCITY YROT-VELOCITY ZROT-VELOCITYXROT-ACCELERATION YROT-ACCELERATION ZROT-ACCELERATION

TEMPERATURE TGRADIENT

STRAIN-11 STRAIN-22 STRAIN-33STRAIN-12 STRAIN-13 STRAIN-23

INITIAL-MAPPING



OVALIZATION-1 OVALIZATION-2 OVALIZATION-3OVALIZATION-4 OVALIZATION-5 OVALIZATION-6

WARPING-1 WARPING-2 WARPING-3WARPING-4 WARPING-5 WARPING-6

FLUID-POTENTIAL FPOT-VELOCITY FPOT-ACCELERATION

PIPE-INTERNAL-PRESSURE

INITIAL-MAPPING

TIME [0.0]Selects the solution time to be mapped.

Note that this parameter is used when the mapping file is from ADINA-F.

ORDER [2]Order of interpolation. {2/1}






THERMAL-MAPPING FILENAME EXTERNAL-NODE DISTANCE TIME

Creates a nodal temperature and temperature gradient file for the current finite element modelby interpolation from a �mapping-file� which contains a finite element mesh with nodaltemperatures / gradients for a range of solution times.

This command is useful for prescribing temperatures for the ADINA model from a temperaturesolution obtained from an independent mesh, e.g. from an ADINA-T model.

FILENAMEThe mapping-file to be read.

EXTERNAL-NODE [ALL]The option for the treatment of external nodes, i.e. those which lie outside the mesh con-tained within the mapping-file:

ALL Interpolation (extrapolation) for all external nodes.

NONE No interpolation (zero value assigned).

DISTANCE Interpolation for nodes which are within a maximumspecified distance from the mapping-file mesh.

DISTANCE [0.0]Maximum distance for external node interpolation.

TIME [0.0]Selects the solution time to be mapped.

Note that this parameter is used when the mapping file is from ADINA-F.

THERMAL-MAPPING



SKEWSYSTEMS CYLINDRICAL

ni xorigini yorigini zorigini xaxisi yaxisi zaxisi normali

Command SKEWSYSTEMS CYLINDRICAL defines a �skew� Cartesian coordinate system interms of a cylinder origin and axis direction. Skew systems can be referenced (via commandDOF-SYSTEM ) by geometry and nodes to indicate the local orientation of the nodal degreesof freedom.

Note that skew system definitions are distinct from coordinate systems defined via commandSYSTEM, which are used to indicate point and node locations.

niLabel number for the desired skew system.

xorigini [0.0]yorigini [0.0]zorigini [0.0]The global coordinates of the origin of the axis of the cylinder.

xaxisi [0.0]yaxisi [1.0]zaxisi [0.0]Global system components of the direction axis of the cylinder.

normali [B]normali indicates which of the skew system axes is to be aligned with the er (radial) direction.Valid choices are �A�, �B�. If normal = A, skew system axis C is aligned with the ez (axis)direction of the cylinder. If normal = B, skew system axis A is aligned with the ez direction ofthe cylinder.

Auxiliary commands

LIST SKEWSYSTEM FIRST LASTDELETE SKEWSYSTEM FIRST LAST

SKEWSYSTEMS CYLINDRICAL


Sec. 7.10 Systems

SKEWSYSTEMS EULERANGLES

ni phii thetai xsii

Defines �skew� Cartesian coordinate systems in terms of Euler angles. Skew systems can bereferenced, via DOF-SYSTEM, to indicate the local orientation of the nodal degrees offreedom.



phii [0.0]thetai [0.0]xsii [0.0]Rotations, in degrees, about the global Cartesian system axes, required to orient the localdirections of the skew system, see SYSTEM for Euler-angle definition.

Auxiliary commands


SKEWSYSTEMS EULERANGLES



SKEWSYSTEMS NORMAL NAME

Defines a skew Cartesian coordinate system to be such that one of its directions is normal toa given line or surface. Note that no other parameters are required to define this skewsystem.

When assigned via DOF-SYSTEM, each node referenced has a skew system defined suchthat a selected local axis is normal to the underlying geometry.


NAMELabel number of the skew coordinate system, which may be referenced by commands DOF-SYSTEM.

Auxiliary commands


SKEWSYSTEMS NORMAL


Sec. 7.10 Systems

SKEWSYSTEMS POINTS

ni p1i p2i p3i

Defines �skew� Cartesian coordinate systems in terms of geometry points. Skew systems canbe referenced, via DOF-SYSTEM, to indicate the local orientation of the nodal degrees offreedom.


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�

�

��

��

��

��

�!

�"

�#

��

��

��


p1i p2i p3iGeometry point label numbers. The vector from point p1i to point p2i defines the direction ofthe local X-axis of the skew system. The vector from p1i to p3i is taken to lie in the local XY-plane of the skew system. Note that points p1i, p2i, p3i must not be collinear.

Auxiliary commands


SKEWSYSTEMS POINTS



SKEWSYSTEMS SPHERICAL

ni xorigini yorigini zorigini

Command SKEWSYSTEMS SPHERICAL defines a �skew� Cartesian coordinate system interms of a sphere origin. Skew systems can be referenced (via command DOF-SYSTEM ) bygeometry and nodes to indicate the local orientation of the nodal degrees of freedom.

Note that skew system definitions are distinct from coordinate systems defined via commandSYSTEM, which are used to indicate point and node locations. The skew system axis A isaligned with the er direction of the sphere, axis B is aligned with the eΘ direction and axis C ischosen to create a right-handed orthogonal coordinate system.


xorigini [0.0]yorigini [0.0]zorigini [0.0]The global coordinates of the origin of the sphere.

Auxiliary commands


SKEWSYSTEMS SPHERICAL


Sec. 7.10 Systems

SKEWSYSTEMS VECTORS

ni axi ayi azi bxi byi bzi

Defines �skew� Cartesian coordinate systems in terms of direction vectors. Skew systemscan be referenced, via DOF-SYSTEM, to indicate the local orientation of the nodal degrees offreedom.


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�&�&$&%�

�

�

�

��

��

��

��


axi [1.0]ayi [0.0]azi [0.0]Vector aligned with the local X-axis of the skew system, defined with respect to the globalCartesian system. Note that for two-dimensional problems vector (axi,ayi,azi) must be parallelto the global Cartesian X-axis.

bxi [0.0]byi [1.0]bzi [0.0]Vector lying in the local XY-plane of the skew system, defined with respect to the globalCartesian system. Note that vector (bxi,byi,bzi) must not be parallel to vector (axi,ayi,azi).

Auxiliary commands


SKEWSYSTEMS VECTORS





Sec. 7.10 Systems

DOF-SYSTEM POINTS

namei skewsystemi

DOF-SYSTEM LINES

linei skewsystemi normali tangenti pfocusi nsensei tsensei

DOF-SYSTEM EDGES BODY

edgei skewsystemi normali tangenti pfocusi nsensei tsensei

DOF-SYSTEM SURFACES

namei skewsystemi normali tangenti pfocusi nsensei tsensei

DOF-SYSTEM FACES BODY

namei skewsystemi normali tangenti pfocusi nsensei tsensei

DOF-SYSTEM VOLUMES

namei skewsystemi

DOF-SYSTEM BODIES

namei skewsystemi

DOF-SYSTEM NODESETS

namei skewsystemi

DOF-SYSTEM POINTS assigns skew coordinate systems to the degrees of freedom associatedwith a set of geometry points.

DOF-SYSTEM LINES assigns skew coordinate systems to the degrees of freedom associatedwith a set of geometry lines. Furthermore, for skew coordinate systems defined to be of typeNORMAL, the local skew system axes to be aligned with the normal and tangent directions tothe line are specified. The normal vector may also be directed such that it points toward or

DOF-SYSTEM



away from a given �focal� point, and the sense of the tangent vector may be similarlyassigned.

DOF-SYSTEM EDGES assigns skew coordinate systems to the degrees of freedom associ-ated with a set of solid geometry edges. Furthermore, for skew coordinate systems defined tobe of type NORMAL, the local skew system axes to be aligned with the normal and tangentdirections to the edge are specified. The normal vector may also be directed such that itpoints toward or away from a given �focal� point, and the sense of the tangent vector may besimilarly assigned.

DOF-SYSTEM SURFACES assigns skew coordinate systems to the degrees of freedomassociated with a set of geometry surfaces. Furthermore, for skew coordinate systemsdefined to be of type NORMAL, the local skew system axis to be aligned with the normaldirection to the surface is specified along with the axis to be aligned with the surface tangentparallel to the local surface parametric u-coordinate direction. The normal vector may also bedirected such that it points toward or away from a given �focal� point, and the sense of thetangent vector may be similarly assigned.

DOF-SYSTEM FACES assigns skew coordinate systems to the degrees of freedom associ-ated with a set of solid geometry faces. Furthermore, for skew coordinate systems defined tobe of type NORMAL, the local skew system axis to be aligned with the normal direction tothe face is specified along with the axis to be aligned with the face tangent parallel to the localface parametric u-coordinate direction. The normal vector may also be directed such that itpoints toward or away from a given �focal� point, and the sense of the tangent vector may besimilarly assigned.

DOF-SYSTEM VOLUMES assigns skew coordinate systems to the degrees of freedomassociated with a set of geometry volumes.

DOF-SYSTEM BODIES assigns skew coordinate systems to the degrees of freedom associ-ated with a set of geometry bodies.

DOF-SYSTEM NODESETS assigns skew coordinate systems to the degrees of freedomassociated with a node set.


namei / linei / edgeiLabel number of a geometry entity or nodeset. All nodes associated with the geometry orcontained in the nodeset are assigned the specified skew system.

DOF-SYSTEM


Sec. 7.10 Systems

skewsystemiLabel number of a skew coordinate system, as defined by SKEWSYSTEM. Settingskewsystemi = 0 assigns the global Cartesian system to the nodal degrees of freedom.

The following parameters are applicable only to skew systems of type NORMAL applied togeometry lines, edges, surfaces and faces.

normaliIndicates which of the skew system axes is to be aligned with the normal direction of thegeometry. The default is C when applied to lines or edges, and A when applied to surfaces orfaces. {A/B/C}

tangenti [B]Indicates which of the skew system axes is to be aligned with the tangential direction of thegeometry. {A/B/C}

pfocusiLabel number of a geometry point which is the �focal� point for directing the normal vector,when skewsystemi is of type NORMAL. The principal normal vector at a point on the line isdetermined to point away from the local center of curvature. The opposite direction is alsonormal to the line, and thus a �focal point� may be used so that the actual normal direction usedpoints toward or away from this point, the selection of which is made by nsensei. If input as 0,then no focus is specified, and the principal normal direction is used.

Note:

For straight lines, straight line segments, or points of inflection on a curve, forwhich the curvature is zero, the normal vector is taken to be either:

(a) when pfocusi = 0, or when pfocusi >0 and the tangent points directly toward or awayfrom point pfocusi; the cross product of the tangential direction with the global X-direction (or Y-direction if the tangent is parallel to the X-direction)

(b) otherwise, a binormal vector is calculated as the cross product of the tangent vector andthe vector directed from the point on the curve to the focal point (the �focal vector�).The normal vector is then taken as the cross product of the binormal and the tangentvectors. In this way the normal vector lies in the plane formed by the tangent and focalvectors, and is directed toward the focal point (or away from the focal point, ascontrolled by nsensei).

DOF-SYSTEM



nsensei [+1]Indicates the direction of the normal vector with reference to the focal point. It is used inconjunction with the pfocusi to orient the normal direction.

+1 Normal direction points toward point pfocusi.

-1 Normal direction points away from point pfocusi.

tsensei [+1]Indicates the direction of the tangent vector. It is used in conjunction with tangenti to orientthe skew system tangent direction.

+1 Follow tangent direction of the geometry.

-1 Opposite to tangent direction of the geometry.

Auxiliary commands

LIST DOF-SYSTEM POINTS FIRST LASTDELETE DOF-SYSTEM POINTS FIRST LAST

LIST DOF-SYSTEM LINES FIRST LASTDELETE DOF-SYSTEM LINES FIRST LAST

LIST DOF-SYSTEM EDGES FIRST LASTDELETE DOF-SYSTEM EDGES FIRST LAST

LIST DOF-SYSTEM SURFACES FIRST LASTDELETE DOF-SYSTEM SURFACES FIRST LAST

LIST DOF-SYSTEM FACES FIRST LASTDELETE DOF-SYSTEM FACES FIRST LAST

LIST DOF-SYSTEM VOLUMES FIRST LASTDELETE DOF-SYSTEM VOLUMES FIRST LAST

LIST DOF-SYSTEM NODESETS FIRST LASTDELETE DOF-SYSTEM NODESETS FIRST LAST

DOF-SYSTEM


Sec. 7.10 SystemsDOF-SYSTEM




SHELLNODESDOF POINTS

pointi nsdofi

SHELLNODESDOF LINES

linei nsdofi

SHELLNODESDOF SURFACES

surfacei nsdofi

SHELLNODESDOF NODESETS

nodeseti

SHELLNODESDOF EDGES BODY

edgei nsdofi

SHELLNODESDOF FACES BODY

facei nsdofi

SHELLNODESDOF POINTS specifies the number of degrees of freedom for shell midsurfacenodes associated with a set of geometry points.

SHELLNODESDOF LINES specifies the number of degrees of freedom for shell midsurfacenodes associated with a set of geometry lines.

SHELLNODESDOF SURFACES specifies the number of degrees of freedom for shellmidsurface nodes associated with a set of geometry surfaces.

SHELLNODESDOF NODESETS specifies the number of degrees of freedom for shellmidsurface nodes associated with a node set.

SHELLNODESDOF EDGES specifies the number of degrees of freedom for shell midsurfacenodes associated with a set of solid geometry edges.

SHELLNODESDOF


Sec. 7.10 Systems

SHELLNODESDOF FACES specifies the number of degrees of freedom for shell midsurfacenodes associated with a set of solid geometry faces.

BODY [currently active body]Solid geometry body label number.

pointiGeometry point label number.



nodesetiNodeset label number.



nsdofi [AUTOMATIC]Number of degrees of freedom for shell midsurface nodes at the geometry entity.

FIVE Three translation, and two rotation degrees of freedom (in localmidsurface system). See the Theory and Modeling Guide.

SIX Three translation and three rotation (global or skew) degrees offreedom.

AUTOMATIC The program automatically decides on the number of degrees offreedom to be assigned to shell nodes based on certain modelingconsiderations. See the Theory and Modeling Guide.

Auxiliary commands

LIST SHELLNODESDOFPOINTS/LINES/SURFACES/NODESETS/EDGES/FACES FIRST LAST

SHELLNODESDOF



DELETE SHELLNODESDOFPOINTS/LINES/SURFACES/NODESETS/EDGES/FACES FIRST LAST


Sec. 7.10 Systems

AXES CONSTANT NAME AX AY AZ BX BY BZ

Defines an �axes-system� in terms of constant direction vectors. Axes-systems can bereferenced by SET-AXES-MATERIAL, SET-AXES-STRAIN to indicate the local orien-tationof the orthotropic material properties and/or initial strain, respectively.

NAMELabel number for the axes-system to be defined.

AX [1.0]AY [0.0]AZ [0.0]Vector aligned with the local x-axis of the axes-system, defined with respect to the globalCartesian coordinate system.

BX [0.0]BY [1.0]BZ [0.0]Vector lying in the local xy-plane of the axes-system, defined with respect to the globalCartesian coordinate system. Note that vector (BX, BY, BZ) must not be parallel to vector(AX, AY, AZ).

Auxiliary commands

LIST AXES FIRST LASTDELETE AXES FIRST LAST

AXES CONSTANT



AXES LINE1 NAME LINE

Defines an �axes-system� via a geometry line. Axes-systems can be referenced bySET-AXES-MATERIAL, SET-AXES-STRAIN to indicate the local orientation of theorthotropic material properties and/or initial strain, respectively.

��

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� �

��

�()�

�** ��+


LINELabel number of the geometry line defining the axes-system.

Note: The axes-system at an element centroid C is determined by calculating the tangentvector at the nearest point P on the geometry line. This gives the local x-directionof the axes-system. The local xy-plane of the axes-system is calculated to includeboth the tangent vector to the line and the vector from the element centroid to thenearest point on the line. See Figure.

Auxiliary commands


AXES LINE1


Sec. 7.10 Systems

AXES LINE2 NAME LINE1 LINE2

Defines an �axes-system� via two geometry lines. Axes-systems can be referenced bySET-AXES-MATERIAL, SET-AXES-STRAIN to indicate the local orientation of theorthotropic material properties and/or initial strain, respectively.


LINE1Label number of the first geometry line defining the axes-system.

LINE2Label number of the second geometry line defining the axes-system.

Note: The axes-system at an element centroid C is determined by calculating the tangentvector at the nearest point P1 on the first geometry line. This gives the local x-direction of the axes-system. The local xy-plane of the axes-system is determinedto include this tangent vector and the tangent vector at the nearest point P2 on thesecond geometry line. See Figure.

Auxiliary commands


AXES LINE2

�

�()�#

��

��'��

+

��!�

�#�#

�()�!

�!

�!

� � ** �#��!�

� ** �#�


Chap. 7 Model definition AXES NODES

AXES NODES NAME NODE1 NODE2 NODE3

Defines an �axes-system� using three nodes.

Axes-systems can be referenced by commands SET-AXES-MATERIAL, SET-AXES-STRAIN,by elements to indicate the local orientation of the orthotropic material properties and/orinitial strain, respectively.

NAMELabel number for the desired axes-system.

NODE1Label number of the first axes-system defining node.

NODE2

Label number of the second axes-system defining node.

NODE3Label number of the third axes-system defining node.

Note:The local x-direction of the axes-system is determined by the vector from the first node�NODE1� to the second node NODE2. The local z-direction of the axes-system is determinedas the normal to the plane defined by the three nodes NODE1, NODE2, and NODE3. The localy-direction of the axes-system is then given by the right-hand rule. See figure.

x (a)C

centroid

element

z (axb) y (axb) xa

NODE3

NODE2NODE1

(axb)

a

b


Sec. 7.10 Systems


AXES NODES



AXES POINT2 NAME POINT1 POINT2

Defines an �axes-system� via two geometry points. Axes-systems can be referenced bySET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of theorthotropic material properties and/or initial strain, respectively.

� ��&� �

��(),!

��(),#

�+

��

��'��

&


POINT1Label number of the first geometry point defining the axes-system.

POINT2Label number of the second geometry point defining the axes-system, which must not becoincident with point �POINT1�.

Note The local x-direction of the axes-system at an element centroid C is determined bythe vector from the centroid to POINT1. The local z-direction of the axes-systemis determined as the normal to the plane defined by the centroid, POINT1 andPOINT2. The local y-direction of the axes-system is then given by the right-handrule. See Figure.

Auxiliary commands


AXES POINT2


Sec. 7.10 Systems

AXES POINT3 NAME POINT1 POINT2 POINT3

Defines an �axes-system� via three geometry points. Axes-systems can be referenced bySET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of theorthotropic material properties and/or initial strain, respectively.

��+

��

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� ��&� � ��&��

��(),"

��(),!

��(),#

��&�

�

&


POINT1Label number of the first geometry point defining the axes-system.

POINT2Label number of the second geometry point defining the axes-system.

POINT3Label number of the third geometry point defining the axes-system.

Note: The local x-direction of the axes-system is determined by the vector from POINT1to POINT2. The local z-direction of the axes-system is determined as the normalto the plane defined by the three points POINT1, POINT2, and POINT3. Thelocal y-direction of the axes-system is then given by the right-hand rule. See Figure.

Auxiliary commands


AXES POINT3



AXES POINT-LINE NAME LINE POINT

Defines an �axes-system� via a geometry line and a geometry point. Axes-systems can bereferenced by SET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientationof the orthotropic material properties and/or initial strain, respectively.


LINELabel number of the geometry line defining the axes-system. Note that the line must not beclosed, i.e., it must have non-coincident end-points.

POINTLabel number of the geometry point defining the axes-system. The point must not becollinear with the end-points of line LINE.

Note: The axes-system at an element centroid C is determined by calculating the tangentvector at the nearest point P on the geometry line. This gives the local x-direction ofthe axes-system. The local xy-plane of the axes-system is defined by the end-pointsof the geometry line �LINE�, and the given geometry point �POINT�. Thus, in orderto determine this plane, the line must have distinct end-points P1 and P2, i.e., itcannot be closed or degenerate, and the geometry point must not be collinear withthose end-points. See Figure.

Auxiliary commands


�#

��(),

�!

�()��

�

�

� � **��&�

+

�� '��

� ** � �

��&

�

&

�

AXES POINT-LINE


Sec. 7.10 Systems

AXES SURFACE NAME SURFACE

Defines an �axes-system� via a geometry surface. Axes-systems can be referenced bySET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of theorthotropic material properties and/or initial strain, respectively.


SURFACELabel number of the geometry surface defining the axes-system.

Note: The axes-system at an element centroid C is determined by calculating the surfacetangent and normal vectors at the nearest point P on the geometry surface. Thelocal x-direction of the axes-system is given by the tangent vector in the localparametric u-direction of the surface. The local z-direction of the axes-system isgiven by the surface normal direction and the local y-direction of the axes-system isthen given by the right-hand rule. See Figure.

Auxiliary commands


� � **��

+

��

� � **��

� **��

��

-�

��'��

AXES SURFACE



AXES EDGE NAME EDGE BODY

Defines an �axes-system� via a geometry edge. Axes-systems can be referenced by SET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of theorthotropic material properties and/or initial strain, respectively.


EDGELabel number of the geometry edge defining the axes-system.

BODY [currently active body]Label number of the geometry body containing the edge.

Note: The axes-system at an element centroid C is determined by calculating the edgetangent and normal vectors at the nearest point P on the geometry edge. The local x-direction of the axes-system is given by the edge tangent vector (in the localparametric u-direction of the edge). The local z-direction of the axes-system is givenby the edge normal direction and the local y-direction of the axes-system is thengiven by the right-hand rule. See Figure.

Auxiliary commands


+

��

� ** � �

�.��

��

��'��

��

�

�

AXES EDGE


Sec. 7.10 Systems

AXES FACE NAME FACE BODY

Defines an �axes-system� via a geometry face. Axes-systems can be referenced bySET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of theorthotropic material properties and/or initial strain, respectively.


FACELabel number of the geometry face defining the axes-system.

BODY [currently active body]Label number of the geometry body containing the face.

Note: The axes-system at an element centroid is determined by calculating the facetangent and normal vectors at the nearest point on the geometry face. The local x-direction of the axes-system is given by the tangent vector in the local parametricu-direction of the face. The local z-direction of the axes-system is given by theface normal direction and the local y-direction of the axes-system is then given bythe right-hand rule. See Figure for AXES SURFACE.

Auxiliary commands


AXES FACE



AXES CYLINDRICAL NAME XORIGIN YORIGIN ZORIGIN XAXIS YAXISZAXIS

Defines a cylindrical axes system in terms of an origin and an axis direction. This axes systemcan be referenced by SET-AXES-MATERIAL and SET-AXES-STRAIN to indicate the localorientation of the orthotropic material properties and/or initial strain, respectively.

In this axes system, the local x direction is aligned with the er (radial) direction, the local ydirection is aligned with the eθ direction, and the local z direction is aligned with the eh(cylindrical axis) direction.

AXES-CYLINDRICAL

NAMELabel number for the axes system to be defined.

XORIGIN, YORIGIN, ZORIGIN [0.0,0.0,0.0]The global coordinates of the origin of the cylindrical axis.

XAXIS, YAXIS, ZAXIS [0.0,0.0,1.0]The global components of the direction vector of the cylindrical axis.

Auxiliary commands


X

Y

Z

θ

XL er

YLZL

eh

r

h

eθ


Sec. 7.10 Systems

AXES SPHERICAL NAME XORIGIN YORIGIN ZORIGIN XAXIS YAXISZAXIS

Defines a spherical axes system in terms of an origin. This axes system can be referenced bySET-AXES-MATERIAL and SET-AXES-STRAIN to indicate the local orientation of theorthotropic material properties and/or initial strain, respectively.

In this axes system, the local x direction is aligned with the er (radial) direction of the sphere,the local y direction is aligned with the eφ direction, and the local z direction is aligned withthe eθ direction.

AXES-SPHERICAL

NAMELabel number for the axes system to be defined.

XORIGIN, YORIGIN, ZORIGIN [0.0,0.0,0.0]The global coordinates of the origin of the spherical axis.

XAXIS, YAXIS, ZAXIS [0.0,0.0,1.0]The global components of the direction vector of the spherical axis.

Auxiliary commands


X

Y

Z

φ

θ

XL

ZL

YL

er

eθ

eφ



SET-AXES-MATERIAL SURFACES

surfacei axesi adiri bdiri

SET-AXES-MATERIAL VOLUMES

volumei axesi adiri bdiri

SET-AXES-MATERIAL FACES BODY

facei axesi adiri bdiri

SET-AXES-MATERIAL BODIES

bodyi axesi adiri bdiri

SET-AXES-MATERIAL ELEMENTSETS

elementseti axesi adiri bdiri

SET-AXES-MATERIAL SURFACES assigns axes-systems, as defined by AXES, to a set ofgeometry surfaces.

SET-AXES-MATERIAL VOLUMES assigns axes-systems, as defined by AXES, to a set ofgeometry volumes.

SET-AXES-MATERIAL FACES assigns axes-systems, as defined by AXES, to a set of solidgeometry faces.

SET-AXES-MATERIAL BODIES assigns axes-systems, as defined by AXES, to a set of solidgeometry bodies.

SET-AXES-MATERIAL ELEMENTSETS assigns axes-systems, defined by command AXES,to a set of element sets.



SET-AXES-MATERIAL


Sec. 7.10 Systems



bodyiLabel number for a solid geometry body.

Note: Any elements generated for the referenced geometry will adopt orthotropicmaterial directories as calculated by the assigned axes-system.

elementsetiLabel number of a element set. Any elements generated in this element set will calculateorthotropic material directions from the assigned the axes-system �axesi�.

axesiLabel number of an axes-system defined by AXES.

adiri [1]The material a-direction is selected to be determined from one of the calculated local x-, y-, orz-directions of the axes-system.

1 a-direction coincides with local x-direction of axis-system.

2 a-direction coincides with local y-direction of axis-system.

3 a-direction coincides with local z-direction of axis-system.

-1 a-direction coincides with local negative x-direction of axis-system.

-2 a-direction coincides with local negative y-direction of axis-system.

-3 a-direction coincides with local negative z-direction of axis-system.

bdiri [2]The material b-direction is selected to be determined from one of the calculated local x-, y-, orz-directions of the axes-system.

1 b-direction coincides with local x-direction of axis-system.

SET-AXES-MATERIAL



2 b-direction coincides with local y-direction of axis-system.

3 b-direction coincides with local z-direction of axis-system.

-1 b-direction coincides with local negative x-direction of axis-system.

-2 b-direction coincides with local negative y-direction of axis-system.

-3 b-direction coincides with local negative z-direction of axis-system.

Note: abs(adiri) must differ from abs(bdiri).

Auxiliary commands

LIST SET-AXES-MATERIAL SURFACES FIRST LASTDELETE SET-AXES-MATERIAL SURFACES FIRST LAST

LIST SET-AXES-MATERIAL VOLUMES FIRST LASTDELETE SET-AXES-MATERIAL VOLUMES FIRST LAST

LIST SET-AXES-MATERIAL FACES FIRST LASTDELETE SET-AXES-MATERIAL FACES FIRST LAST

LIST SET-AXES-MATERIAL BODIES FIRST LASTDELETE SET-AXES-MATERIAL BODIES FIRST LAST

SET-AXES-MATERIAL

LIST SET-AXES-MATERIAL ELEMENTSETS FIRST LASTDELETE S ET-AXES-MATERIAL ELEMENTSETS FIRST LAST


Sec. 7.10 Systems

SET-AXES-STRAIN SURFACES

surfacei axesi adiri bdiri

SET-AXES-STRAIN VOLUMES

volumei axesi adiri bdiri

SET-AXES-STRAIN FACES BODY

facei axesi adiri bdiri

SET-AXES-STRAIN BODIES

bodyi axesi adiri bdiri

SET-AXES-STRAIN ELEMENTSETS

elementseti axesi adiri bdiri

SET-AXES-STRAIN SURFACES assigns axes-systems, defined by AXES, to a set of geom-etry surfaces.

SET-AXES-STRAIN VOLUMES assigns axes-systems, defined by AXES, to a set of geometryvolumes.

SET-AXES-STRAIN FACES assigns axes-systems, defined by AXES, to a set of solidgeometry faces.

SET-AXES-STRAIN BODIES assigns axes-system, defined by AXES, to a set of solidgeometry bodies.

SET-AXES-STRAIN ELEMENTSETS assigns axes-systems, defined by command AXES, to aset of element sets.



SET-AXES-STRAIN






Note: Any elements generated for the referenced geometry will adopt initial-straindirections as calculated by the assigned axes-system.

elementsetiLabel number of a element set. Any elements generated in this element set will calculateorthotropic strain directions from the assigned the axes-system �axesi�.

axesiLabel number of an axes-system defined by AXES.

adiri [1]The strain a-direction is selected to be determined from one of the calculated local x-, y- or z-directions of the axes-system.

1 a-direction coincides with local x-direction of axis-system.

2 a-direction coincides with local y-direction of axis-system.

3 a-direction coincides with local z-direction of axis-system.

-1 a-direction coincides with local negative x-direction of axis-system.

-2 a-direction coincides with local negative y-direction of axis-system.

-3 a-direction coincides with local negative z-direction of axis-system.

bdiri [2]The strain b-direction is selected to be determined from one of the calculated local x-, y- or z-directions of the axes-system.

1 b-direction coincides with local x-direction of axis-system.

SET-AXES-STRAIN


Sec. 7.10 Systems

2 b-direction coincides with local y-direction of axis-system.

3 b-direction coincides with local z-direction of axis-system.

-1 b-direction coincides with local negative x-direction of axis-system.

-2 b-direction coincides with local negative y-direction of axis-system.

-3 b-direction coincides with local negative z-direction of axis-system.

Note: abs(adiri) must differ from abs(bdiri).

Auxiliary commands

LIST SET-AXES-STRAIN SURFACES FIRST LASTDELETE SET-AXES-STRAIN SURFACES FIRST LAST

LIST SET-AXES-STRAIN VOLUMES FIRST LASTDELETE SET-AXES-STRAIN VOLUMES FIRST LAST

LIST SET-AXES-STRAIN FACES FIRST LASTDELETE SET-AXES-STRAIN FACES FIRST LAST

LIST SET-AXES-STRAIN BODIES FIRST LASTDELETE SET-AXES-STRAIN BODIES FIRST LAST

SET-AXES-STRAIN

LIST SET-AXES-STRAIN ELEMENTSETS FIRST LASTDELETE SET-AXES-STRAIN ELEMENTSETS FIRST LAST


Chapter 8

Finite element representation


Sec. 8.1 Element groups

EGROUP TRUSS NAME SUBTYPE DISPLACEMENTS MATERIAL INTGAPS INITIALSTRAIN CMASS TIME-OFFSET OPTIONRB-LINE AREA PRINT SAVE TBIRTH TDEATHTMC-MATERIAL GAPWIDTH

Defines an element group consisting of truss elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number of an existing elementgroup can only be given if it is of type TRUSS. Hence, to re-define the type of a namedelement group you must first delete that group using command DELETE EGROUP TRUSS.

SUBTYPE [GENERAL]Indicates the type of TRUSS element.

GENERAL General 3-D truss elements with 2-4 nodes.

AXISYMMETRIC Axisymmetric truss (ring) elements with 1 node in theglobal YZ plane. Z is the axis of rotational symmetryand Y is the radial direction (Y ≥ 0).

DISPLACEMENTS [DEFAULT]Indicates whether large displacements are assumed for the kinematic formulation for theelement group.

SMALL Small displacements only.

LARGE Effects of large displacements are included.

DEFAULT Formulation for element group defaults to that specifiedby KINEMATICS.

MATERIAL [1]The label number of the default material for an element group. Elements within the group mayuse a different material as specified by an element data command, but each material specifiedmust be of the same model type as that of the material given by this parameter.

Note: Elements of type TRUSS can use materials of the following types:

ELASTIC THERMO-PLASTICTHERMO-ISOTROPIC CREEPPLASTIC-BILINEAR PLASTIC-CREEPPLASTIC-MULTILINEAR NONLINEAR-ELASTIC

EGROUP TRUSS


Chap. 8 Finite element representation

INT [DEFAULT]Numerical integration order. {1 ≤ INT ≤ 4}

DEFAULT =1 when SUBTYPE = AXISYMMETRIC, or maximum number ofelement nodes is 2.

2 when maximum number of nodes per element is 3.3 when maximum number of nodes per element is 4.

GAPS [NO]

YES All elements in this (nonlinear) group have gaps, i.e., no elementin the group can resist tensile force. The gap width for elementsmay be specified via the element data commands. This optionmay only be used when material models PLASTIC- BILINEAR orPLASTIC-MULTILINEAR are employed, in conjunction with2-node general truss elements.

NO The gap element option is inactive for this element group, and allelements can resist tensile as well as compressive forces.

INITIALSTRAIN [NONE]Indicates whether initial strains are to be applied to this element group.

NONE No initial strains for elements of this group.

NODAL Only the nodal strains input via INITIAL-CONDITION areaccounted for.

ELEMENT Only the element strains input via the element data commandsare accounted for.

BOTH Both nodal and element strains are taken into consideration.

CMASS [MASTER CMASS]Requests the calculation of the following mass properties for the element group: total mass,total volume, moments and products of inertia, centroid, and center of mass. {YES/NO}

TIME-OFFSET [0.0]With this parameter, a creep law can be modified as follows (example given for creep lawnumber 1) :

e a t tca a= ⋅ ⋅ −( )0 01 2σ

EGROUP TRUSS



where t is the absolute time and t0=TIME-OFFSET represents a shift in the time scale.

Note: When TIME-OFFSET is used, the same shift is applied to all time dependent terms.The TIME-OFFSET value can be negative or positive and can be modified for arestart run.

OPTION [NONE]Special option for this element group.

NONE - No special option. Elements are regular truss elements.REBAR - Elements are used as rebar elements.

RB-LINE [1]Rebar label number as defined by the command REBAR-LINE. Only used if OPTION=REBAR.

AREA [1.0]Specifies the default cross-section area for elements in the group.

PRINT [DEFAULT]Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULTparameter of the PRINTOUT command. {DEFAULT/NO/YES}

SAVE [DEFAULT]Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULTparameter of the PORTHOLE command. {DEFAULT/NO/YES}

TBIRTH [0.0]Default element birth time.

TDEATH [0.0]Default element birth time.

TMC-MATERIAL [1]Label number of ADINA-T material used for thermal coupling.

GAPWIDTH [0.0]Specifies the default gap width for truss element.

Auxiliary commands

LIST EGROUP TRUSS FIRST LASTDELETE EGROUP TRUSS FIRST LAST

EGROUP TRUSS



EGROUP TWODSOLID NAME SUBTYPE DISPLACEMENTS STRAINSMATERIAL INT RESULTS DEGEN FORMULATIONSTRESSREFERENCE INITIALSTRAIN FRACTURE CMASSSTRAIN-FIELD PNTGPS NODGPS LVUS1 LVUS2 SEDRUPTURE INCOMPATIBLE-MODES TIME-OFFSETPOROUS WTMC OPTION THICKNESS PRINT SAVETBIRTH TDEATH TMC-MATERIAL RUPTURE-LABEL

Defines an element group consisting of planar or axisymmetric elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number on an existing elementgroup can only be given if it is of type TWODSOLID. Hence, to re-define the type of anamed element group, you must first delete that group using command DELETE EGROUPTWODSOLID.

SUBTYPEIndicates the type of TWODSOLID element. (See the Theory and Modeling Guide).

AXISYMMETRIC Axisymmetric elements in the global YZ plane. Z is theaxis of rotational symmetry and Y is the radial direction (Y≥0).

STRAIN Plane strain elements in the global YZ plane.

STRESS2 Plane stress elements in the global YZ plane.

STRESS3 3-D plane stress (membrane) elements.

STRAIN3 Generalized plane strain in the global YZ plane.




DEFAULT Formulation for element group defaults to that specified byKINEMATICS.

STRAINS [DEFAULT]Indicates whether large strains are assumed for the kinematic formulation for the elementgroup.

EGROUP TWODSOLID



SMALL Small strains only.

LARGE Effects of large strains are included.


Note: DISPLACEMENTS = LARGE is automatically set if STRAINS = LARGE is input.


Note: Elements of type TWODSOLID can use materials of the following types. Onlyelements marked with an asterisk (*) can be used with large strains.

ELASTIC THERMO-ISOTROPICORTHOTROPIC THERMO-ORTHOTROPIC*PLASTIC-BILINEAR *PLASTIC-MULTILINEAR*THERMO-PLASTIC *PLASTIC-ORTHOTROPICDRUCKER-PRAGER *MROZ-BILINEARGURSON *CREEP*CREEP-VARIABLE *PLASTIC-CREEP-VARIABLE*PLASTIC-CREEP *MULTILINEAR-PLASTIC-CREEPCURVE-DESCRIPTION *MULTILINEAR-PLASTIC-CREEP-VARIABLECONCRETE CAM-CLAY*ARRUDA-BOYCE *MOONEY-RIVLIN*OGDEN *SUSSMAN-BATHE*USER-SUPPLIED


DEFAULT Full Gauss integration order, dependent on the polynomial orderof the elements, i.e., the number of nodes per element side.

RESULTS [STRESSES]The calculated element response from the ADINA analysis.

FORCES Element nodal forces are calculated, but stresses are not. Theseforces are equivalent, in the virtual work sense, to the internalelement stresses. The reference system is that of the degree-of-freedom system associated with the node (global or skew).

EGROUP TWODSOLID



STRESSES Element stresses and strains are calculated at all integrationpoints, but forces are not.

DEGEN [DEFAULT]Indicator for spatial isotropy correction for degenerate (triangular) 8-node elements. Whentrue 6-node triangular elements are defined in this element group through ENODES command,DEGEN = UNUSED should be specified. The DEFAULT option means that the default is takenfrom the parameter DEGEN of the MASTER command. {DEFAULT/NO/YES/UNUSED}

FORMULATION [DEFAULT]Indicates use of displacement or mixed interpolation formulation.

DISPLACEMENT [1] Displacement interpolation only.

MIXED [2] Mixed pressure-displacement interpolation.

DEFAULT [0] See note below.

-N N is the number of pressure degrees of freedom for eachelement.

Note: The mixed formulation cannot be used for material models CAM-CLAY, GURSON,CURVE-DESCRIPTION, CONCRETE, DRUCKER-PRAGER, MOHR-COULOMB andHYPER-FOAM. Furthermore, it is only applicable for plane strain, generalized planestrain and axisymmetric analyses.

Note: The value DEFAULT assumes a MIXED formulation for element groups withmaterial models OGDEN, MOONEY-RIVLIN, ARRUDA-BOYCE and SUSSMAN-BATHE. For all other material models the value assumed for DEFAULT is that ofDISPLACEMENT formulation.

Note: When using the mixed formulation, 1 pressure degree of freedom is used forelements with 8 or fewer nodes, and 3 pressure degrees of freedom are used for the9-node element. In general, the 9-node element is the most effective, and is thusrecommended. To explicitly set the number of pressure degrees of freedom, inputFORMULATION = -N, where N is the desired number of pressure degrees offreedom within each element.

STRESSREFERENCE [GLOBAL]Indicates the reference system for calculated stresses.

GLOBAL The global Cartesian coordinate system (X, Y, Z).

MATERIAL The element material system, for orthotropic materials.

EGROUP TWODSOLID



INITIALSTRAIN [NONE]Indicates whether initial strains are to be applied to this element group.



ELEMENT Only the element strains input via the STRAIN-FIELD parameterare accounted for.


FRACTURE [NO]This parameter is obsolete.


STRAIN-FIELD [0]Label number of a �strain-field� defined by STRAIN-FIELD command (Section7.9). A 0 valueindicates no initial element strains, and any initial element strains selected by input ofSTRAIN-FIELD > 0 will only be considered if INITIALSTRAIN = ELEMENT or BOTH.

PNTGPS [0]Label number of a geometry point at which the auxiliary node for generalized plane strainelements (SUBTYPE = STRAIN3) is located.

NODGPS [0]Label number of the auxiliary node for generalized plane strain elements.

Note: For SUBTYPE = STRAIN3, PNTGPS = NODGPS = 0 is not allowed (an auxiliarynode must be specified). If PNTGPS and NODGPS are both > 0, then the input forPNTGPS is used.



EGROUP TWODSOLID



SED [NO]Indicate whether or not to compute, and output, the strain energy density at all integrationpoints of elements within the group. {NO/YES}

RUPTURE [ADINA]Indicates whether the program rupture criteria or user-supplied rupture criteria to be appliedto the material used in this element group.

ADINA Use the program criteria.

USER User must provide fortran-coded subroutine CURUP2 to decidethe element rupture.

Note that material models available for this option are:PLASTIC-BILINEAR, PLASTIC-MULTILINEAR, MROZ-BILINEAR,PLASTIC-ORTHOTROPIC, THERMO-PLASTIC, CREEP, PLASTIC-CREEP,MULTILINEAR-PLASTIC-CREEP, USER-SUPPLIED

INCOMPATIBLE-MODES [DEFAULT]Specifies whether incompatible modes are included in the formulation of 4-node 2D solidelements.

NO Incompatible modes are not included.

YES Incompatible modes are included.

DEFAULT Choice of formulation is controled by the KINEMATICS command.


e a t tca a= ⋅ ⋅ −( )0 01 2σ



POROUSThis parameter is now obsolete. It is replaced by the parameter OPTION.

EGROUP TWODSOLID



WTMC [1.0]Plastic work to heat factor for thermo-mechanical coupling. Must be in the range<0.0,1.0>

OPTION [NONE]{NONE/POROUS/USER-CODED/GASKET-SIMPLE/GASKET-GENERAL}

NONE No special option.

POROUS This element group is used with porous media properties.

USER-CODED User-supplied code is used for this element group.

GASKET-SIMPLE This element group is used with a simple gasket material.

GASKET-GENERAL This element group is used with a general gasket material.

THICKNESS [1.0]Defines the default element thickness.






RUPTURE-LABEL [0]User-rupture label number which is defined by the USER-RUPTURE command.Used only for RUPTURE = USER.

Auxiliary commands

LIST EGROUP TWODSOLID FIRST LASTDELETE EGROUP TWODSOLID FIRST LAST

EGROUP TWODSOLID



EGROUP THREEDSOLID NAME DISPLACEMENTS STRAINS MATERIALRSINT TINT RESULTS DEGEN FORMULATIONSTRESSREFERENCE INITIALSTRAIN FRACTURECMASS STRAIN-FIELD LVUS1 LVUS2 SEDRUPTURE INCOMPATIBLE-MODES TIME-OFFSETPOROUS WTMC OPTION PRINT SAVE TBIRTHTDEATH TMC-MATERIAL RUPTURE-LABEL

Defines an element group consisting of three-dimensional solid elements.

NAME [(current highest element group label number )+ 1]Label number of the element group to be defined. The label number of an existing elementgroup can only be given if it is of type THREEDSOLID. Hence, to re-define the type of anamed element group you must first delete that group using command DELETE EGROUPTHREEDSOLID.







LARGE Effects of large strains are included.



MATERIAL [1]The label number of the default material for an element group. Elements within the group mayuse a different material, as specified by an element data command, but each material specifiedmust be of the same model type as that of the material given by this parameter.

EGROUP THREEDSOLID



Note: Elements of type THREEDSOLID can use materials of the following types. Onlyelements marked with an asterisk (*) can be used with large strains.

ELASTIC THERMO-ISOTROPICORTHOTROPIC THERMO-ORTHOTROPIC*PLASTIC-BILINEAR *PLASTIC-MULTILINEAR*THERMO-PLASTIC *PLASTIC-ORTHOTROPICDRUCKER-PRAGER *MROZ-BILINEARGURSON *CREEP*CREEP-VARIABLE *PLASTIC-CREEP-VARIABLE*PLASTIC-CREEP *MULTILINEAR-PLASTIC-CREEPCURVE-DESCRIPTION *MULTILINEAR-PLASTIC-CREEP-VARIABLECONCRETE CAM-CLAY*ARRUDA-BOYCE *MOONEY-RIVLIN*OGDEN *SUSSMAN-BATHE*USER-SUPPLIED

RSINT [DEFAULT]Numerical integration order for the r- and s- element coordinate directions. {2 ≤ RSINT ≤ 6}


TINT [DEFAULT]Numerical integration order for the t-element coordinate direction. {2 ≤ TINT ≤ 6}





DEGEN [DEFAULT]Indicator for spatial isotropy correction of degenerate 20-node elements. When true 10-nodetetrahedral elments are defined in this element group through ENODES command, DEGEN =UNUSED should be specified. The DEFAULT option means that the default is taken from theparameter DEGEN of the MASTER command.{DEFAULT/NO/YES/UNUSED}

EGROUP THREEDSOLID



FORMULATION [DEFAULT]Indicates use of displacement or mixed interpolation formulation.

DISPLACEMENT [1] Displacement interpolation only.

MIXED [2] Mixed pressure-displacement interpolation.

DEFAULT [0] See note below.

-N N is the number of pressure degrees of freedom for eachelement.

Note: The mixed formulation cannot be used for material models CAM-CLAY, GURSON,CURVE-DESCRIPTION, CONCRETE, DRUCKER-PRAGER, MOHR-COULOMB, andHYPER-FOAM.

Note: The value DEFAULT assumes a MIXED formulation for element groups withmaterial models OGDEN, MOONEY-RIVLIN, ARRUDA-BOYCE and SUSSMAN-BATHE. For all other material models the value assumed for DEFAULT is that ofDISPLACEMENT formulation.

Note: When using the mixed formulation, 1 pressure degree of freedom is used forelements with 8 to 21 nodes, and 4 pressure degrees of freedom are used for the27-node element. In general, the 27-node element is the most effective, and is thusrecommended. To explicitly set the number of pressure degrees of freedom, inputFORMULATION = -N, where N is the desired number of pressure degrees offreedom within each element.

STRESSREFERENCE [GLOBAL]Indicates the reference system for calculated stresses.



INITIALSTRAIN [NONE]Indicates initial strains applied to this element group.


NODAL Only the nodal strains input via INITIAL-CONDITIONare accounted for.

ELEMENT Only the element strains input via the STRAIN-FIELDparameter are accounted for.

EGROUP THREEDSOLID



BOTH Nodal and element strains are taken into consideration.

FRACTURE [NO]This parameter is obsolete.


STRAIN-FIELD [0]Label number of a �strain-field� defined by STRAIN-FIELD command (Section7.9). A 0 valueindicates no initial element strains, and any initial element strains selected by input ofSTRAIN-FIELD > 0 will only be considered if INITIALSTRAIN = ELEMENT or BOTH.



SED [NO]Indicate whether or not to compute, and output, the strain energy density at all integrationpoints of elements within the group. {YES/NO}




Note: Material models available for this option are:PLASTIC-BILINEAR, PLASTIC-MULTILINEAR, MROZ-BILINEAR,PLASTIC-ORTHOTROPIC, THERMO-PLASTIC, CREEP, PLASTIC-CREEP,MULTILINEAR-PLASTIC-CREEP, USER-SUPPLIED

INCOMPATIBLE-MODES [DEFAULT]Specifies whether incompatible modes are included in the formulation of 8-node 3D solidelements.

NO Incompatible modes are not included.

EGROUP THREEDSOLID



YES Incompatible modes are included.DEFAULT Choice of formulation is controled by the KINEMATICS command


e a t tca a= ⋅ ⋅ −( )0 01 2σ



POROUS [NO]Indicates whether porous media properties are used for elements in this group. {NO/YES}

WTMC [1.0]Plastic work to heat fator for thermo-mechanical coupling. Must be in the range <0.0,1.0>

OPTION [NONE]{NONE,POROUS,USER-CODED, GASKET-SIMPLE,GASKET-GENERAL}

NONE No special option.

USER-CODED User-supplied code is used for this element group.

GASKET-SIMPLE This element group is used with a simple gasket material.

GASKET-GENERAL This element group is used with a general gasket material.




EGROUP THREEDSOLID


Sec. 8.1 Element groupsEGROUP THREEDSOLID




Auxiliary commands

LIST GROUP THREEDSOLID FIRST LASTDELETE EGROUP THREEDSOLID FIRST LAST






EGROUP BEAM NAME SUBTYPE DISPLACEMENTS MATERIALRINT SINT TINT RESULTS INITIALSTRAIN CMASSRIGIDENDTYPE MOMENT-CURVATURE RIGIDITYMULTIPLY BOLT RUPTURE OPTION BOLT-TOLSECTION PRINT SAVE TBIRTH TDEATH SPOINTBOLTFORCE BOLTNCUR TMC-MATERIALBOLT-NUMBER BOLT-LOAD WARP

Defines an element group consisting of Hermitian beam elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number of an existing elementgroup can be given only if it is of type BEAM. Hence, to re-define the type of a namedelement group, you must first delete that group using DELETE EGROUP BEAM.

SUBTYPE [THREE-D]Indicates the type of BEAM element.

TWO-D Two-dimensional action beam elements, defined parallel to one of the X-Y,Y-Z, or X-Z global coordinate planes.

THREE-D Three-dimensional action beam elements.




DEFAULT Formulation for element group defaults to that specified by KINEMATICS.

MATERIAL [1]The label number of the default material for an element group. Elements within the group mayuse a different material, as specified by an element data command, but each material specifiedmust be of the same model type as that of the material given by this parameter.

Note: Elements of type BEAM can use materials of the following types:ELASTICPLASTIC-BILINEAR

EGROUP BEAM



RINT [5]Numerical integration order along the centroidal axis of each element, the local element r-direction. {1 ≤ RINT ≤ 7}

SINT [DEFAULT]Numerical integration order for the local s-direction of each element, which lies in the elementplane defined by the element nodes including the auxiliary node. {1 ≤ SINT ≤ 7}

DEFAULT = 7 for 3-D action elements of rectangular cross-section, 3 otherwise.

TINT [DEFAULT]Numerical integration order for the local t-direction of each general 3-D beam element, normalto the plane of the element. {1 ≤ TINT ≤ 8}

DEFAULT = 1 for 2-D action elements of rectangular cross-section. 7 for 3-D action elements of rectangular cross-section. 5 for 2-D action elements of pipe cross-section. 8 for 3-D action elements of pipe cross-section.

Note: The element matrices are integrated exactly when used in conjunction with a linearelastic material, and, therefore, parameters RINT, SINT, TINT are not considered.

RESULTS [STRESSES]The calculated element response from the ADINA analysis. {STRESSES/FORCES/SFORCES}

FORCES Element nodal forces are calculated, but stresses are not. Theseforces are equivalent, in the virtual work sense, to the internalelement stresses.

STRESSES Element stresses and strains are calculated at all integration points, butforces are not.

SFORCES Element forces and moments are calculated at equidistant sectionpoints along the length of the element. The number of section points isset by the parameter SPOINT. This option is only available for static,linear analysis.

Note: When an elastic material model is used, the choice STRESSES is not consideredsince no integration point data are available. In this case, the default ouput choice isFORCES.

EGROUP BEAM






ELEMENT Only the element strains input via the EDATA commandare accounted for.



RIGIDENDTYPE [NONE]Specifies whether rigid end-zones exist for elements of the group. See the Theory andModeling Guide.

NONE No rigid end-zones are defined.

ABSOLUTE Rigid end-zones are defined in terms of dimensions in length units.

INFINITE Rigid end-zones with infinite stiffness are defined in terms ofdimensions in length units.

MOMENT-CURVATURE [NO]Specifies whether or not moment-curvature properties are to be utilized by elements in thegroup. {YES/NO}

RIGIDITY [0]Label number of a rigidity moment-curvature property set to be used for elements of thegroup. See RIGIDITY-MOMENT-CURVATURE. Used when MOMENT-CURVATURE = YES.

MULTIPLY [1.0E6]This parameter is only applicable if RIGIDENDTYPE=ABSOLUTE. It specifies a multiplier tothe stiffness properties of the element in case of rigid ends. The multiplier is used to computethe stiffness of the rigid ends. {>=0.0}

BOLT [NO]This parameter in now obsolete. It is replaced by the parameter OPTION.

EGROUP BEAM






Note that the only material model available for this option is:


OPTION [NONE]Option for the behaviour of beam elements in this group. {NONE/BOLT}

BOLT-TOL [0.0]Bolt force tolerance used to determine convergence. During solution iterations, the elementinternal force is compared with the preload force. If the difference is within the tolerance, theconverged solution is obtained. BOLT-TOL=0.0 means the default bolt tolerance specified inBOLT-OPTIONS command will be used.

SECTION [1]Specifies the default cross section label for elements in the group.





SPOINT [4]Specifies the number of section points for output of section forces whenRESULTS=SFORCES. The points are located equidistant along length of the element.{ 2 ≤ SPOINT ≤ 7 }

EGROUP BEAM



Note: SPOINT is only considered when the option SFORCES is used in the parameterRESULTS.

BOLTFORCE [0.0]This parameter is obsolete.

BOLTNCUR [0]This parameter is obsolete.


BOLT-NUMBER [0]Specifies the bolt number for the current group. It can be used in the command BOLT-TABLE.

BOLT-LOAD [0.0]The parameter BOLTFORCE is obsolete. BOLT-LOAD takes it place, and specifies the defaultbold load for each element. A bolt can be either be of the type force-tensioning or length-reducing.

WARP [NO]Specifies whether warping degress of freedom are active. {NO/YES}

NO No warping DOF

YES Warping DOF is active.

Auxiliary commands

LIST EGROUP BEAM FIRST LASTDELETE EGROUP BEAM FIRST LAST

EGROUP BEAM



EGROUP ISOBEAM NAME SUBTYPE DISPLACEMENTS MATERIAL RINTSINT TINT RESULTS INITIALSTRAIN CMASSRUPTURE TIME-OFFSET OPTION SECTION THICKNESSPRINT SAVE TBIRTH TDEATH TMC-MATERIAL

Defines an element group consisting of isoparametric beam elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number of an existing elementgroup can be given only if it is of type ISOBEAM. Hence, to re-define the type of a namedelement group, you must first delete that group using DELETE EGROUP ISOBEAM.

SUBTYPE [GENERAL]Indicates the type of ISOBEAM element.

GENERAL General three-dimensional beam elements.

PLSTRAIN Plane strain elements in the global YZ plane.

PLSTRESS Plane stress elements in the global YZ plane.

AXISYMMETRIC Axisymmetric elements in the global YZ plane. Z is theaxis of rotational symmetry and Y is the radial direction(Y ≥ 0).






Note: Elements of type ISOBEAM can use materials of the following types:

EGROUP ISOBEAM



ELASTIC THERMO-ISOTROPICPLASTIC-BILINEAR PLASTIC-MULTILINEARTHERMO-PLASTIC CREEPPLASTIC-CREEP MULTILINEAR-PLASTIC-CREEPCREEP-VARIABLE PLASTIC-CREEP-VARIABLEMULTILINEAR-PLASTIC-CREEP-VARIABLE

RINT [DEFAULT]Numerical integration order along the centroidal axis of each element (the local element r-direction). Negative values imply the closed Newton-Cotes integration method, and zero orpositive values the Gauss integration method. Possible values/orders include:

RINT Method No. of integration points

-1 Newton-Cotes 3-2 Newton-Cotes 3-3 Newton-Cotes 3-4 Newton-Cotes 5-5 Newton-Cotes 5-6 Newton-Cotes 7-7 Newton-Cotes 70 Gauss DEFAULT (see below)1 Gauss 12 Gauss 23 Gauss 34 Gauss 4

DEFAULT The Gauss integration order such that the element matrix obtained isequivalent to the mixed formulation for this element. With this integrationorder, the elements do not contain any spurious zero energy modes, do notlock and are efficient in general nonlinear analysis.

SINT [DEFAULT]Numerical integration order for the local s-direction of each element, which lies in the elementplane defined by the element nodes (including the auxiliary node). The same input conven-tion for RINT is assumed. (Note, however, that ADINA will currently employ the 4-pointGauss or the 7-point Newton-Cotes method for general 3-D isobeam elements, overridingyour input value).

For plane stress/strain beams or axisymmetric shell elements, we have:

2 ≤ SINT ≤ 4 Gauss method.

EGROUP ISOBEAM



-7 ≤ SINT ≤ -3 Newton-Cotes method.

DEFAULT = 4 for general 3-D elements.2 for plane stress/strain, axisymmetric elements.

TINT [4]Numerical integration order for the local t-direction of each general 3-D beam element, normalto the plane of the element. The same input convention for RINT, SINT is used, but note thatADINA employs either the 4-point Gauss or the 7-point Newton-Cotes method, overridingthe input value.


FORCES Element nodal forces are calculated, but stresses are not. Theseforces are equivalent, in the virtual work sense, to the internalelement stresses.




NODAL Only the nodal strains are accounted for; these can be inputwith the INITIAL-CONDITION or ELEMENT-DATA commands.

ELEMENT Only the element strains are accounted for; these can be inputwith the INITIAL-CONDITION or ELEMENT-DATA commands.





EGROUP ISOBEAM




Note that material models available for this option are:

PLASTIC-BILINEAR, PLASTIC-MULTILINEAR, THERMO-PLASTIC,CREEP, PLASTIC-CREEP, MULTILINEAR-PLASTIC-CREEP


e a t tca a= ⋅ ⋅ −( )0 01 2σ



OPTION [NONE]Indicates whether user-supplied code is used for this element group.{NONE / USER-CODED}

If OPTION = USER-CODED, then {SUBTYPE, INITIALSTRAIN, CMASS, RUPTURE} arenot applicable

SECTION [1]Specifies the default cross-section label for elements (excluding axisymmetric shell) in thegroup.

THICKNESS [1.0]Specifies the default thickness of axisymmetric shell elements in the group.




EGROUP ISOBEAM





Auxiliary commands

LIST EGROUP ISOBEAM FIRST LASTDELETE EGROUP ISOBEAM FIRST LAST

EGROUP ISOBEAM



EGROUP PLATE NAME DISPLACEMENTS MATERIAL INTRESULTS INITIALSTRAIN CMASS THICKNESS PRINTSAVE TBIRTH TDEATH

Defines an element group consisting of plate elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number of an existing elementgroup can be given only if it is of type PLATE. Hence, to re-define the type of a namedelement group, you must first delete that group using DELETE EGROUP PLATE.





MATERIAL [1]The label number of the default material for the element group. Elements within the groupmay use a different material, but each material specified must be of the same model type asthat of the material given by this parameter.

Note: Elements of type PLATE can use materials of the following types:ELASTICORTHOTROPICILYUSHIN

INT [2]Integration scheme indicator. See the Theory and Modeling Guide for the triangular elementintegration schemes. {1 ≤ INT ≤ 4}

1 1-point (centroid).2 3-point (interior).3 3-point (mid-side).4 7-point (interior).

Note: For linear analysis (small displacement, elastic material) ADINA uses theintegration scheme given by INT = 2; the input value for parameter INT is thusignored.

EGROUP PLATE



RESULTS [STRESS-RESULTANTS]The calculated element response from the ADINA analysis.

FORCES Element nodal forces and moments are calculated, butstresses are not. These forces/moments are equivalent, inthe virtual work sense, to the internal element stresses.The reference system is that of the degree-of-freedomsystem associated with the node (global or skew).

STRESS-RESULTANTS Element stress resultants are calculated at all integrationpoints, but forces are not.



NODAL Only the nodal strains input via INITIAL-CONDITIONare accounted for.

ELEMENT Only the element strains input via element datacommands are accounted for.

BOTH Both nodal and element strains are taken intoconsideration.


THICKNESS [1.0]Defines the default element thickness.




EGROUP PLATE




Auxiliary commands

LIST EGROUP PLATE FIRST LASTDELETE EGROUP PLATE FIRST LAST

EGROUP PLATE






EGROUP SHELL NAME DISPLACEMENTS MATERIAL RINT SINTTINT RESULTS STRESSREFERENCE PRINTVECTORSNLAYERS INITIALSTRAIN FAILURE SECTIONRESULTCMASS STRAINS RUPTURE TIME-OFFSET OPTIONTHICKNESS INCOMPATIBLE-MODES PRINT SAVETBIRTH TDEATH TINT-TYPE TMC-MATERIAL WTMCRUPTURE-LABEL RELROT-PENALTY

Defines an element group consisting of shell elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number of an existing elementgroup can be given only if it is of type SHELL. Hence, to re-define the type of a namedelement group, you must first delete that group using DELETE EGROUP SHELL.




DEFAULT Formulation for element group defaults to that specified by KINEMATICS.

MATERIAL [1]The label number of the default material for the element group. Elements within the groupmay use a different material, but each material specified must be of the same model type asthat of the material given by this parameter.

Note: Elements of type SHELL can use materials of the following types. Only elementsmarked with an asterisk (*) can be used with large strains, but are restricted to 3-, 4-,9-, or 16-node single layer shell elements, in which the shell geometry is described interms of midsurface nodes.

ELASTIC *PLASTIC-MULTILINEARORTHOTROPIC CREEPTHERMO-ISOTROPIC THERMO-PLASTIC*PLASTIC-BILINEAR PLASTIC-CREEP*PLASTIC-ORTHOTROPIC MULTILINEAR-PLASTIC-CREEPCREEP-VARIABLE PLASTIC-CREEP-VARIABLEMULTILINEAR-PLASTIC-CREEP-VARIABLE

EGROUP SHELL



RINT [DEFAULT]Integration order for the local r-direction of the elements. {1 ≤ RINT ≤ 6}

DEFAULT Full Gauss integration order, the reliable integration order,dependent on the polynomial order of the elements, i.e., thenumber of nodes per element side.

SINT [DEFAULT]Integration order for the local s-direction of the elements. {1 ≤ SINT ≤ 6}

DEFAULT same as RINT.

Note: For a triangular shell element, the integration scheme uses the following numberof sampling points. See the Theory and Modeling Guide.

NRS = RINT × SINTNo. of integration points 1 11 < NRS ≤ 4 44 < NRS ≤ 9 79 < NRS ≤ 36 13

TINT [2]Integration order for the local t-direction (through thickness) of the elements.

TINT > 0 Gauss, Newton-Cotes or trapezoidal rule integration, see parameterTINT-TYPE

-7 ≤ TINT ≤ -3 Newton-Cotes integration (for backwards compatibility withprevious versions of the AUI)

Note: For multilayer shell elements this integration order is applied to each layer.


FORCES Element nodal forces and moments are calculated, but stresses arenot. These forces/moments are equivalent, in the virtual worksense, to the internal element stresses. The reference system isthat of the degree-of-freedom system associated with the node(global or skew).

STRESSES Element stresses and strains are calculated at all integration

EGROUP SHELL



points, but forces are not.

STRESSREFERENCE [GLOBAL]Indicates the reference system for calculated stresses. {GLOBAL/LOCAL/MATERIAL/MIDSURFACE }


LOCAL The local element system (r, s, t).


MIDSURFACE The mid-surface coordinate system ( �� , ,r s t ).See Theory andModeling Guide.

PRINTVECTORS [0]Indicator for printing, by ADINA, of the direction cosines of the element midsurface vectors(at the nodal points).

0 No printing.

1 Initial direction cosines printed.

2 Initial and updated direction cosines printed.

NLAYERS [1]The number of layers for elements of the group. See LAYER.




ELEMENT Only the element strains input via element data commands areaccounted for.


FAILURE [0]Label number of the default failure criterion assigned to elements of this group. Elements

EGROUP SHELL



within the group may use a different failure criterion, but each failure criterion specified mustbe of the same type as that of the failure criterion given by this parameter, see FAILURE. A 0value indicates no failure criterion to be used.

Note that material models available for this option are:ISOTROPIC ORTHOTROPICTHERMO-ISOTROPIC THERMO-ORTHOTROPIC

SECTIONRESULT [0]Indicates which of the following are calculated at integration point midsurface locations:element force and moment resultants (per unit length), membrane strains and curvatures andpositions of the neutral axes. Printing and saving of this data for each element may bespecified by the element data commands.

-2 Calculation of force/moment resultants, strains/curvatures,neutral axes.

-1 Calculation of force/moment resultants, strains/curvatures.

0 No calculation.

1 Calculation of force/moment resultants.

2 Calculation of force/moment resultants, neutral axes.

Note: Parameter SECTIONRESULT takes effect only if parameter RESULTS =STRESSES, and if the calculated data refers to the local element (r, s, t) system.




LARGE Effects of large strains are included. For details of restrictions,please refer to the note under the parameter MATERIAL.


EGROUP SHELL


Sec. 8.1 Element groupsEGROUP SHELL





Note that material models available for this option are:

PLASTIC-BILINEAR, PLASTIC-MULTILINEAR, PLASTIC-ORTHOTROPIC,THERMO-PLASTIC, CREEP, PLASTIC-CREEP, MULTILINEAR-PLASTIC-CREEP


e a t tca a= ⋅ ⋅ −( )0 01 2σ



OPTION [NONE]Indicates whether user-supplied code is used for this element group.{NONE / USER-CODED}

if OPTION = USER-CODED, then {STRESSREFERENCE, PRINTVECTORS, NLAYERS,INITIALSTRAIN, FAILURE, SECTIONRESULT, CMASS, STRAINS, RUPTURE} are notapplicable

THICKNESS [1.0]Specifies the default thickness of elements in the group.

INCOMPATIBLE-MODES [DEFAULT]Specifies whether incompatible modes are included in the formulation of 4-node shell ele-ments. {NO/YES/DEFAULT}

NO Incompatible modes are not included



YES Incompatible modes are included

DEFAULT Choice of formulation is set by the KINEMATICS command

Incompatible modes are only applicable to quadrilateral MITC4 elements. They are notapplicable to triangular collapsed MITC4 elements.





TINT-TYPE [GAUSS]Parameter TINT-TYPE controls the type of numerical integration through the shell thickness.

GAUSS Gauss integration is used with TINT points. (2 ≤ TINT ≤ 6)

NEWTON-COTES Newton-Cotes integration is used with TINT points. (TINT =3,5,7)

TRAPEZOIDAL Trapezoidal rule integration is used with TINT points. Can only beused with MITC3, MITC4, MITC6, MITC9, MITC16 single layer shellelements. ( 2 ≤ TINT ≤ 20)

If TINT < 0, then Newton-Cotes integration is always used regardless of the value of TINT-TYPE (for backwards compatibility with previous versions of the AUI).


WTMC [1.0]

Plastic work to heat factor for the thermo-mechanical coupling. ( 0.0 ≤ WTMC ≤ 1.0)

EGROUP SHELL


Sec. 8.1 Element groupsEGROUP SHELL


Auxiliary commands

LIST EGROUP SHELL FIRST LASTDELETE EGROUP SHELL FIRST LAST



EGROUP PIPE NAME DISPLACEMENTS MATERIAL RINT SINTTINT RESULTS OVALIZATION INITIALSTRAINICALRA RADTOL CMASS RUPTURE TIME-OFFSETOPTION BOLT-TOL SECTION PRINT SAVE TBIRTHTDEATH BOLTFORCE BOLTNCUR TMC-MATERIAL

Defines an element group consisting of pipe elements. See the Theory and Modeling Guidefor a complete description of pipe elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number of an existing elementgroup can only be given if it is of type PIPE. Hence, to re-define the type of a named elementgroup, you must first delete that group using DELETE EGROUP PIPE.





MATERIAL [1]The label number of the default material for an element group. Elements within the group mayuse a different material, as specified by element data command, but each material specifiedmust be of the same model type as that of the material given by this parameter.

Note: Elements of type PIPE can use materials of the following types:ELASTIC, THERMO-ISOTROPIC, PLASTIC, PLASTIC-MULTILINEAR, THERMO-PLASTIC, CREEP, PLASTIC-CREEP, CREEP-VARIABLE, MULTILINEAR-PLAS-TIC-CREEP, PLASTIC-CREEP-VARIABLE, MULTILINEAR-PLASTIC-CREEP-VARIABLE

RINT [DEFAULT]Numerical integration order along the centroidal axis of each element (the local element r-direction). Negative values imply the closed Newton-Cotes integration method, and zero orpositive values the Gauss integration method.

DEFAULT Full Gauss integration order � the reliable integration order,dependent on the polynomial order of the elements, i.e., themaximum number of nodes per element.

EGROUP PIPE



RINT Method No. of integration points

-1 Newton-Cotes 3-2 Newton-Cotes 3-3 Newton-Cotes 3-4 Newton-Cotes 5-5 Newton-Cotes 5-6 Newton-Cotes 7-7 Newton-Cotes 7 0 Gauss DEFAULT (see above) 1 Gauss 1 2 Gauss 2 3 Gauss 3 4 Gauss 4

SINT [DEFAULT]Numerical integration order for the local s-direction of each element, which is the radialdirection of the pipe). The same input convention for RINT is assumed.

TINT [DEFAULT]Numerical integration order for the local t-direction or circumferential direction used in thecomposite trapezoidal rule. Only 4, 8, 12 or 24 integration points can be employed and thefollowing default values are used by ADINA when other values of TINT are specified.

4 < TINT ≤ 7 88 < TINT ≤ 11 12

12 < TINT ≤ 24 24

If element warping/ovalization is enabled then

TINT ≥ 12 must be used for MASTER OVALIZATION = IN-PLANE.TINT = 24 must be used for MASTER OVALIZATION = OUT-OF-PLANE or ALL.

DEFAULT = 8 when MASTER OVALIZATION = NO.= 12 when MASTER OVALIZATION = IN-PLANE.= 24 when MASTER OVALIZATION = OUT-OF-PLANE or ALL.


FORCES Element nodal forces are calculated, stresses are not. These forcesare equivalent, in the virtual work sense, to the internal elementstresses.

EGROUP PIPE



STRESSES Element stresses and strains are calculated at all integrationpoints, but no forces.

OVALIZATION [DEFAULT]Flag that indicates whether or not the pipe nodes in this element group have ovalization/warping degrees of freedom.

NO Pipe element nodes do not have ovalization/warping degrees offreedom.

DEFAULT Warping/Ovalization based on MASTER command.NO if MASTER OVALIZATION = NOYES if MASTER OVALIZATION = IN-PLANE,

OUT-OF-PLANEor ALL.




ELEMENT Only the element strains input via element data commands areaccounted for.


ICALRA [0]Flag for the calculation of internal radii and internal areas at pipe nodes.

0 Internal radii and internal areas are not calculated.

1 Internal radii and internal areas are calculated and stored on theporthole file.

2 Internal radii and internal areas are calculated, stored on theporthole file and printed out.

RADTOL [0.001]For 4-node, circular bend pipe elements, the nodes should lie on a circular arc with the auxiliarynode at the center of that arc. RADTOL provides a relative tolerance for checking this.

EGROUP PIPE



CMASS [MASTER CMASS]Requests the calculation of the following mass properties for the element group: total mass,total volume, moments and products of inertia, centroid, and center of mass.{YES/NO}




Note: Material models available for this option are:PLASTIC-BILINEAR, PLASTIC-MULTILINEAR, THERMO-PLASTIC,CREEP, PLASTIC-CREEP, MULTILINEAR-PLASTIC-CREEP


e a t tca a= ⋅ ⋅ −( )0 01 2σ



OPTION [NONE]This parameter is obsolete.

BOLT-TOL [0.01]This parameter is obsolete.

SECTION [1]Specifies the default cross-section label for elements in the group.


SAVE [DEFAULT]Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT

EGROUP PIPE



parameter of the PORTHOLE command. {DEFAULT/NO/YES}



BOLTFORCE [0.0]Specify default bolt force for each element.

BOLTNCUR [0]Specify time function for bolt element.


Auxiliary commands

LIST EGROUP PIPE FIRST LASTDELETE EGROUP PIPE FIRST LAST

EGROUP PIPE



EGROUP SPRING NAME PROPERTYSET RESULTS NONLINEARSKEWSYSTEM BOLT OPTION PRINT SAVETBIRTH TDEATH

Defines an element group consisting of spring elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number of an existing elementgroup can be given only if it is of type SPRING. Hence, to re-define the type of a namedelement group, you must first delete that group using DELETE EGROUP SPRING.

PROPERTYSET [1]The label number of the default property set (giving the stiffness, mass, damping properties)for the element group, defined via command PROPERTYSET. Elements within the group mayuse a different property set, as specified, e.g., by SPRING-POINTS.

RESULTS [FORCES]The calculated element response from the ADINA analysis.

FORCES Element nodal forces are calculated. The reference system is thatof the degree-of-freedom system associated with the node (globalor skew).

STRESSES Element stresses are calculated using the specified stresstransformation (see command PROPERTYSET).

NONLINEAR [NO]Specifies whether springs in this group has nonlinear effects. {NO/MNO/GEOM/MNO-G}

NO Spring is linear

MNO Spring properties may be nonlinear but geometric nonlinearitiesare not taken into account

GEOM Spring properties may be nonlinear and geometric nonlinearitiesare taken into account

MNO-G Spring with general nonlinear spring properties, with option ofusing skewsystem at the spring nodes

SKEWSYSTEM [NO]Skewsystem usage, only applicable to springs with option NONLINEAR = NO or MNO-G.

EGROUP SPRING



NO All property sets are assumed to be with respect to the globalCartesian system. ADINA performs all necessarytransformations for any skewsystems at spring element nodes.

YES Property sets are assumed to be with respect to the coordinatesystems at the element nodes. Thus, in this case, ADINA doesnot perform any transformation between global and skew system.

BOLT [NO]This parameter is now obsolete. It is replaced by the parameter OPTION.

OPTION [NONE]Specifies special options for springs in this group. {NONE/TIED/TRANSVERSE}

NONE No special options

TIED Springs used to tie closely spaced shell surfaces

TRANSVERSE Spring may act in the transverse direction (instead of axial). Onlyapplicable when NONLINEAR=MNO





Auxiliary commands

LIST EGROUP SPRING FIRST LASTDELETE EGROUP SPRING FIRST LAST

EGROUP SPRING



EGROUP GENERAL NAME MATRIXSET RESULTS SKEWSYSTEMSUSER-SUPPLIED PRINT SAVE

Defines an element group consisting of linear general elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number of an existing elementgroup can only be given if it is of type GENERAL. Hence to re-define the type of a namedelement group, you must first delete that group using DELETE EGROUP GENERAL.

MATRIXSET [1]The label number of the default matrix set giving element stiffness, mass, damping and stressmatrices for an element group, defined via command MATRIXSET. Elements within the groupmay use a different matrix set, as specified by element data commands.



STRESSES Element stresses and strains are calculated at all integrationpoints, but forces are not calculated.

SKEWSYSTEM [NO]

NO All matrix sets are assumed to be with respect to the globalCartesian system. ADINA performs all necessarytransformations for any skewsystems at general element nodes.

YES Matrix sets are assumed to be with respect to the coordinatesystems at the element nodes. Thus, in this case, ADINA doesnot perform any transformation between global and skewsystems.

USER-SUPPLIED [NO]If USER-SUPPLIED=YES, then use the MATRIX USER-SUPPLIED command to input therequired information, which will be used in the ADINA subroutine CUSERG for calculatingthe element stiffness, mass and damping matrices, and nodal forces. Note that if the stiffness,mass or damping matrices are constants, then they can instead be provided by the MATRIXSTIFFNESS, MATRIX MASS or MATRIX DAMPING commands, respectively. If theMATRIX STIFFNESS command is used, then obviously USER-SUPPLIED=NO. Only one

EGROUP GENERAL



matrix set (specified by MATRIXSET) is allowed when USER-SUPPLIED=YES.

NO Element stiffness is directly input through the commandsMATRIX STIFFNESS and MATRIXSET.

YES Element stiffness is to be provided by the user from ADINAsubroutine CUSERG, and the element nodal forces is to becalculated too. The command MATRIX USER-SUPPLIED mustbe input and the MATRIXSET command is used to combine thestiffness, mass and damping effects.



Auxiliary commands

LIST EGROUP GENERAL FIRST LASTDELETE EGROUP GENERAL FIRST LAST

EGROUP GENERAL



EGROUP FLUID2 NAME SUBTYPE DISPLACEMENTS IPOMATERIAL INT RESULTS DEGENFORMULATION CMASS

Defines an element group consisting of 2-D planar or axisymmetric fluid elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number of an existing elementgroup can only be given if it is of type FLUID2. Hence to re-define the type of a namedelement group, you must first delete that group using DELETE EGROUP FLUID2.

SUBTYPE [AXISYMMETRIC]Indicates the type of FLUID2 element.

AXISYMMETRIC Axisymmetric elements (which cannot be used in a cyclicsymmetric analysis).

PLANE 2-D Planar elements.

DISPLACEMENTS [DEFAULT]Indicates whether large displacements are assumed for the kinematic formulation for theelement group. Only applicable for FORMULATION = 0 or 1.




IPO [0]Each fluid region may required one point at which a hydrostatic pressure degree of freedom isspecified. See the Theory and Modeling Guide. If required, IPO specifies the appropriategeometry point. IPO = 0 indicates no such requirement.

MATERIAL [1]The label number of the default material for an element group. Elements within the group mayuse a different material, as specified by element data commands, but each material specifiedmust be of the same model type as that of the material given by this parameter.

Note: Elements of type FLUID2 can only use a material of the type: FLUID.

EGROUP FLUID2




DEFAULT Full Gauss integration order, the reliable integration order,dependent on the polynomial order of the elements, i.e., thenumber of nodes per element side.

RESULTS [PRESSURES]The calculated element response from the ADINA analysis.

FORCES Element nodal forces are calculated, but pressures are not. Theseforces are equivalent, in the virtual work sense, to the internalelement pressures. The reference system is that of the degree-of-freedom system associated with the node (global or skew).

PRESSURES Element pressures are calculated at all integration points, butforces are not.

Note: RESULTS=FORCES can not be applied to the potential based fluids.

DEGEN [DEFAULT]Indicator for spatial isotropy correction for degenerate (triangular) 8-node elements. Whentrue tetrahedral elements are defined in this element group, DEGEN = UNUSED should bespecified. The DEFAULT option means that the default is taken from the parameter DEGEN ofthe MASTER command. {DEFAULT/NO/YES/UNUSED}

FORMULATION [DEFAULT]Indicates which fluid element to use:

0 Displacement-based element without rotation penalty.1 Displacement-based element with rotation penalty.2 Potential-based element, acoustic formulation.3 Potential-based infinite element4 Potential-based element, subsonic formulation

Notes on the formulations:

The potential-based formulations can only be used in conjunction with small displacements(DISPLACEMENTS=SMALL).

Formulation 3 is obsolete and is maintained only for backwards compatibility with ADINA 7.5and lower.

EGROUP FLUID2



Formulation 4 is allowed only when MASTER FLUIDPOTENTIAL=AUTOMATIC.

DEFAULT = 2= 1 (cyclic symmetric analysis)

CMASS [MASTER CMASS]Requires the calculation of the following mass properties for the element group: total mass,total volume, moments and products of inertia, centroid, and center of mass. {YES/NO}

Auxiliary commands

LIST EGROUP FLUID2 FIRST LASTDELETE EGROUP FLUID2 FIRST LAST

EGROUP FLUID2



EGROUP FLUID3 NAME DISPLACEMENTS IPO MATERIAL RSINTTINT RESULTS DEGEN FORMULATION CMASS

Defines an element group consisting of three-dimensional fluid elements.

NAME [(current highest element group label number) + 1]Label number of the element group to be defined. The label number of an existing elementgroup can only be given if it is of type FLUID3. Hence, to re-define the type of a namedelement group, you must first delete that group using DELETE EGROUP FLUID3.

DISPLACEMENTS [DEFAULT]Indicates whether large displacements are assumed for the kinematic formulation for theelement group. Only applicable for FORMULATION = 0 or 1.




IPO [0]Each fluid region may required one point at which a hydrostatic pressure degree of freedom isspecified. See the Theory and Modeling Guide. If required, IPO specifies the appropriategeometry point. IPO = 0 indicates no such requirement.

MATERIAL [1]The label number of the default material for an element group. Elements within the group mayuse a different material, as specified by element data commands, but each material specifiedmust be of the same model type as that of the material given by this parameter.

Note: Elements of type FLUID3 can only use a material of type: FLUID.

RSINT [DEFAULT]Numerical integration order for the element r-, s-directions. {1 ≤ INT ≤ 6}

DEFAULT Full Gauss integration order, the reliable integration order,dependent on the polynomial order of the elements, i.e. thenumber of nodes per element side.

TINT [DEFAULT]Numerical integration order in the element t-direction. Same input convention as RSINT.

EGROUP FLUID3



RESULTS [PRESSURES]The calculated element response from the ADINA analysis.

FORCES Element nodal forces are calculated, but pressures are not. Theseforces are equivalent, in the virtual work sense, to the internalelement pressures. The reference system is that of the degree-of-freedom system associated with the node (global or skew).

PRESSURES Element pressures are calculated at all integration points, butforces are not.The calculated element response from the ADINAanalysis.

Note: RESULTS=FORCES can not be applied to the potential based fluids.

DEGEN [DEFAULT]Indicator for spatial isotropy correction for degenerate 20-node elements. Whentrue 10-node tetrahedral elements are defined in this element group through ENODEScommand, DEGEN = UNUSED should be specified. The DEFAULT option means that thedefault is taken from the parameter DEGEN of the MASTER command. {DEFAULT/NO/YES/UNUSED}

FORMULATION [DEFAULT]Indicates which fluid element to use:

0 Displacement-based element without rotation penalty.1 Displacement-based element with rotation penalty.2 Potential-based element, acoustic formulation.3 Potential-based infinite element4 Potential-based element, subsonic formulation

Notes on the formulations:

The potential-based formulations can only be used in conjunction with small displacements(DISPLACEMENTS=SMALL).

Formulation 3 is obsolete and is maintained only for backwards compatibility with ADINA 7.5and lower.

Formulation 4 is allowed only when MASTER FLUIDPOTENTIAL=AUTOMATIC.

DEFAULT = 2= 1 (cyclic symmetric analysis)

EGROUP FLUID3



CMASS [MASTER CMASS]Requests the calculation of the following mass properties for the element group; total mass,total volume, moments and products of inertia, centroid, and center of mass. {YES/NO}

Auxiliary commands

LIST EGROUP FLUID3 FIRST LASTDELETE EGROUP FLUID3 FIRST LAST

EGROUP FLUID3



EGCONTROL MAXELG

EGCONTROL specifies general control data for element groups.

MAXELG [9999]Maximum number of elements in a single element subgroup. If the number of elements in agroup is greater than MAXELG it will be split into subgroups such that each subgroup hasMAXELG or fewer elements. This parameter has no effect if PPROCESS NPROC is greaterthan 1, for which element group splitting is handled independently of MAXELG.

Auxiliary commands

LIST EGCONTROL

EGCONTROL



BOLT-OPTIONS TYPE TABLES STEPS TIME TOLERANCE DAMPING

Defines bolt options for use with the EGROUP BEAM command.

TYPE [FORCE]Specifies the type of bolt. {FORCE/LENGTH}

FORCE Force-tensioning bolt

LENGTH Length-reducing bolt

TYPE can be overwritten by the BOLT-TABLE command.

TABLES [NO]Indicates whether bolt tables (BOLT-TABLE command) are used to specify the bolt loadingsequence. If TABLES=YES, at least one BOLT-TABLE command must be specified in themodel. {NO/YES}

STEPS [1]Specifies number of bolt steps used to apply the full bolt load. Not used if TABLES=YES isspecified.

TIME [0]Specifies bolt time. Not used if TABLES=YES is specified.

TOLERANCE [0.01]Specifies the default bolt convergence tolerance. A different tolerance value may be specifiedfor a group of bolts with the BOLT-TOL parameter in EGROUP BEAM command.

DAMPING [0.0]Specifies bolt damping.

BOLT-OPTIONS


Sec. 8.1 Element groupsBOLT-TABLE

BOLT-TABLE NAME TYPE TIME

sequencei bolt-numberi factori savei

Specifies the bolt loading sequence.

NAME [current highest label + 1]Bolt-table label number.

TYPE [FORCE]Specifies the type of bolt. {FORCE/LENGTH}

FORCE Force-tensioning bolt

LENGTH Length-reducing bolt

The specification of TYPE in this command overwrites any from the BOLT-OPTIONS com-mand.

TIME [0]Specifies bolt time.

sequenceiBolt sequence number.

bolt-numberiBolt number assigned in the EGROUP BEAM command.

Note that if bolt-number=0, it means all bolts are loaded in same sequence.

factoriBolt factor.

savei [DEFAULT]Save flag. {DEFAULT/NO/YES}When the setting is DEFAULT, the save flag is NO, except for last bolt in the table, for whichthe save flag = YES.

Note that the same sequence with different bolt numbers must have the same save flag. Ifmultiple entries have the same sequence and the same bolt number, only the last one will betaken. Sequence numbers must start at number 1 and have no gaps. Bolt time must bedifferent for each bolt-table. The same sequence must have the same save flags.



TRANSITION-ELEMENT BODY1 FACE1 EDGE GROUP1 BODY2 FACE2GROUP2 SUBSTRUCTURE

Converts a set of shell elements along an edge of a face/surface into shell transition elements.

BODY1 [0]Label number of the body of FACE1 that has a shell mesh.

FACE1 [1]Label number of the face on BODY1. If BODY1 is 0, FACE1 is a surface label number.

EDGELabel number of the edge where the shell transition elements are to be created. If BODY1 is 0,EDGE is a line label number.

GROUP1 [Highest shell element group number of mesh on FACE1]Element group number of the shell mesh on FACE1.

BODY2 [0]Label number of the body that has a 3-D solid mesh.

FACE2 [1]Label number of face on BODY2 where the shell transition elements are to be created. IfBODY2 is 0, FACE2 is a surface label number.

GROUP2 [Highest 3-D solid element group number of mesh onBODY2]

Element group number of the 3-D solid mesh on BODY2.

SUBSTRUCTURE [Currently active substructure]Substructure number for the nodes created by this command.

TRANSITION-ELEMENT


Sec. 8.2 Mesh generation

BLAYER SUBSTRUC GROUP GEOM

bodyi facei edgei ptypei thick0i nlayeri thickti

Command BLAYER generates boundary layers on specified body faces for the specified(substructure, group). In 3D, boundary layers are grown normal to body faces. In 2D,boundary layers are grown normal to body edges along body faces.

Notes for 3D models:

1 BLAYER is active only if: number of bodies > 0 and number of volumes = 0and all bodies have been meshed.

2 BLAYER executes only if number of nodes per element is 4.3 In case of multiple bodies, "interface" body faces must be linked.4 Linked body faces cannot have boundary layers on both sides.5 Once boundary layers have been generated and in case of multiple bodies,

do not delete body meshes unless you intend to delete all of them.6 There can be only one element group.7 As a rule of thumb, the total thickness should be less than the element size on

the body face.

Notes for 2D models:

1 BLAYER is active only if number of body faces > 0 and number of surfaces = 0and all body faces have been meshed.

2 BLAYER executes only if number of nodes per element is 3.3 In case of multiple bodies, "interface" body edges must have same nodes.4 Interface body edges cannot have boundary layers on both sides.5 Once boundary layers have been generated and in case of multiple bodies,

do not delete body meshes unless you intend to delete all of them.6 There can be only one element group.7 As a rule of thumb, the total thickness should be less than the element size on the

body edge.

SUBSTRUC [current substructure label number]Element substructure.

GROUP [current group label number]Element group.

GEOM [YES]Option to use the geometric modeler for placement of nodes on body faces/edges. {YES/NO}

BLAYER



YES The geometric modeler (parasolid) is used to place nodes on body faces/edges.

NO The mesh is used to place nodes on body faces/edges.

bodyiLabel number of the body.

faceiLabel number of the face.

edgeiLabel number of the edge. In 3D, this is a dummy argument.

ptypeiProgression type for boundary layers. {GEOMETRIC/ARITHMETIC}

thick0iThickness of first layer (off face).

nlayeriNumber of layers.

thicktiTotal thickness.

BLAYER


Sec. 8.2 Mesh generationCOPY-TRIANGULATION

COPY-TRIANGULATION BODY1 FACE1 BODY2 FACE2TRANSFORMATION PCTOLERANCE

Copies face triangulation which can be later be used by meshing commands like GFACE orGBODY. Enables the creation of identical meshes on similar faces.

BODY1 [NONE]Label number of body where the face triangulation(s) is to be copied from. {> 0}

FACE1 [0]Label number of face on BODY1 where the triangulation is to be copied from. See notes belowif FACE1=0. {≥ 0}

BODY2 [NONE]Label number of body where the face triangulation(s) is to be copied to. {> 0}

FACE2 [0]Label number of face on BODY2 where the triangulation is to be copied from. See notes belowif FACE2=0. {≥ 0}

TRANSFORMATION [0]Label number of the transformation from BODY1 (FACE1) to BODY2 (FACE2).

PCTOLERANCE [as set in TOLERANCES GEOMETRIC]Relative tolerance to be used to check if faces are matched using the provided transforma-tion.

Notes:If FACE1>0 and FACE2>0, it is assumed FACE1 transforms into FACE2 and the triangulationstored internally for FACE1 is copied onto FACE2 if they match.

If FACE1=0 and FACE2=0, any face of BODY1 is checked against any face of BODY2 for amatch using the provided transformation. The face triangulations are copied for all matchingfaces.



DELETE-TRIANGULATION OPTION BODY FACE

Deletes face triangulations created by the COPY-TRIANGULATION command.

OPTION [ALL]Indicates whether triangulation is deleted for all relevant faces on all bodies or for selectedfaces on a body. {ALL/SELECT}

BODYBody label where triangulation is to be deleted. {>0}

FACE [0]Face label where triangulation is to be deleted. If FACE=0, then triangulation on all relevantfaces of BODY will be deleted. {≥0}

DELETE-TRIANGULATION



LIST-TRIANGULATION

Lists all faces (body and face labels) which have triangulation created by the COPY-TRIAN-GULATION command.

LIST-TRIANGULATION



SUBDIVIDE DEFAULT MODE PROGRESSION SIZE NDIV PSIZE MINCUR

Defines default mesh subdivision data for subsequent model geometry definitions. Modelgeometry created or imported will initially have the subdivision data given by this command.Note that this command does not update any current geometry subdivision data, it onlyspecifies defaults for subsequent geometry definitions.

SUBDIVIDE DEFAULT has a similar syntax, but quite distinct action, to SUBDIVIDE MODEL,which assigns a given subdivision data to all currently defined geometry.

MODE [NONE]Selects the method of model subdivision data specification.

NONE no default mode. Subdivision mode will depend on theSUBDIVIDE commands for each individual geometry type

LENGTH An element size is input corresponding to the length ofan element edge.

DIVISIONS A geometry line or edge is assigned a number of equalsubdivisions.

POINTWISE A geometry line or edge is subdivided according to thedesired element size at its end-points.

PROGRESSION [GEOMETRIC]Sets the method of element edge length distribution along a line or edge of the geometry model.

ARITHMETIC The difference in length of each element edge from itsadjacent edges is constant.

GEOMETRIC The ratio of lengths of adjacent element edges isconstant.

APPROXIMATE The distribution of edge lengths is made such that agiven ratio of end-lengths is only approximately satisfied.

Note: PROGRESSION = APPROXIMATE is only provided for compatibility with earlierversions of ADINA-IN. It is recommended that ARITHMETIC or GEOMETRICnormally be used.

SIZE [0.0]If MODE=LENGTH, this parameter specifies the element edge length. Then SIZE=0.0 means

SUBDIVIDE DEFAULT



that the element edge length is the length of the edge (i.e. every edge will have 1 subdivsion).If MODE=POINTWISE, this parameter specifies the maximum element edge length.

NDIV [1]Number of subdivisions assigned to a geometry line/edge.

PSIZE [0.0]Element size at geometry points.

MINCUR [1]Minimum number of subdivisions for curved lines and edges used whenMODE=POINTWISE.

Auxiliary commands

LIST SUBDIVIDE DEFAULTLists the current default subdivision data.

SUBDIVIDE DEFAULT



SUBDIVIDE MODEL MODE SIZE NDIV PROGRESSION MINCUR

Assigns mesh subdivision data to the entire current model geometry. The data can be in theform of a specified element size, or the number of subdivisions along each line.

MODE [POINTWISE]Selects the method of model subdivision data specification.

LENGTH An element size is input corresponding to the length ofan element edge.

DIVISIONS Each model geometry line or edge is assigned the samenumber of equal subdivisions.

POINTWISE Each model geometry line or edge is subdividedaccording to the element size at its end-points.

SIZE [0.0]If MODE=LENGTH, this parameter specifies the element edge length. Then SIZE=0.0 meansthat the element edge length is the length of the edge (i.e. every edge will have 1 subdivsion).If MODE=POINTWISE, this parameter specifies the maximum element edge length.

NDIV [1]Number of subdivisions assigned to each geometry line or edge.

PROGRESSION [GEOMETRIC]Sets the method of element edge length distribution along each line or edge of the geometrymodel.



APPROXIMATE The distribution of edge lengths is made such that agiven ratio of end-lengths is only approximately satisfied.


MINCUR [1]Minimum number of subdivisions for curved lines and edges used when MODE =POINTWISE.

Auxiliary commands

LIST SUBDIVIDE MODEL

SUBDIVIDE MODEL



SUBDIVIDE POINT NAME SIZE

pointi

Assigns mesh subdivision data (element sizes) to a set of geometry points.

NAMELabel number of a geometry point. Other points may be specified in subsequent accompany-ing data lines.

SIZERequested element size. The size of an element is defined to be the maximum length of anedge of that element. {≥ 0.0}

Note: The element size at a geometry point may be used to determine the subdivisiondata of geometry entities: lines and edges, and thereby that of surfaces, volumes,faces and bodies.


Note: A zero element size at a point indicates that any line or edge for which the point isa vertex (end-point) will have only a single element edge if the mode of that line/edge is POINTWISE.

Auxiliary commands

LIST SUBDIVIDE POINT FIRST LAST

SUBDIVIDE POINT



SUBDIVIDE LINE NAME MODE SIZE NDIV RATIO PROGRESSIONCBIAS

linei

Assigns mesh subdivision data to a set of geometry lines. The data can be in the form of aspecified element size, or the number of subdivisions along the line.

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SUBDIVIDE LINE

NAMELabel number of a geometry line. Other geometry lines to have the same subdivision datamay be given on accompanying data-lines.

MODE [DIVISIONS]Selects the method of mesh subdivision data specification. This controls the actual param-eters used, other parameters are ignored.

DIVISIONS The geometry lines are assigned a number of subdivisions whichcan be graded in size according to the selected progression rule(NDIV, RATIO, PROGRESSION).

LENGTH An element size is input corresponding to the length of anelement edge (SIZE).

POINTWISE The number of subdivisions, and any necessary grading, for thegeometry line is calculated from the element size specified at theend points of the geometry line. See SUBDIVIDE POINT,POINT-SIZE (SIZE, PROGRESSION).



COMBINED For lines of type COMBINED (COUPLED=YES), the subdivisiondata assigned to the parent lines (which are combined to definethe line) are transferred to the combined line, overwriting anyexisting subdivision for the combined line. This mode guaranteesthat the �junctions� where parent lines meet is assigned a subdivi-sion location, i.e. a node will be generated at these positionsduring mesh generation.


NDIV [1]Number of subdivisions assigned to the geometry lines.

RATIO [1.0]Ratio of lengths of the last to the first element edges along the geometry line. The grading ofelement lengths is governed by PROGRESSION. �Last� refers to the end of the line corre-sponding to parametric coordinate u = 1.0, whilst �first� refers to the end of the line corre-sponding to parametric coordinate u = 0.0.

PROGRESSION [GEOMETRIC]When element edges are to be graded along a geometry line, i.e., when RATIO ≠ 1.0, thedistribution of element edge lengths can be selected from:

ARITHMETIC The difference in length of each element edge from its adjacentedges is constant.


APPROXIMATE The distribution of edge lengths is made such that RATIO is onlyapproximately satisfied.


CBIAS [NO]Indicates if central bias is used. {NO/YES}


SUBDIVIDE LINE



Auxiliary commands

LIST SUBDIVIDE LINE FIRST LAST

SUBDIVIDE LINE



SUBDIVIDE SURFACE NAME MODE SIZE NDIV1 NDIV2 RATIO1RATIO2 PROGRESSION CBIAS1 CBIAS2

surfacei

Assigns mesh subdivision data to a set of geometry surfaces. The data can be in the form ofa specified element size, or the number of divisions along the edges of the geometry surface.The subdivision data is actually assigned to the geometry lines which comprise the edges ofthe geometry surfaces.

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NAMELabel number of a geometry surface. Other geometry surfaces to have the same subdivisiondata may be given on accompanying data-lines.


LENGTH An element size is input corresponding to the length of anelement edge. Each edge of the geometry surfaces is subdividedseparately so as to give element edges which are approximately oflength SIZE (SIZE).

DIVISIONS Each parametric direction of the geometry surfaces is assigned anumber of subdivisions which can be graded in size according tothe selected progression rule (NDIV1, NDIV2, RATIO1, RATIO2,PROGRESSION).

SUBDIVIDE SURFACE



POINTWISE Each edge of the geometry surfaces is assigned a number ofsub-divisions which is calculated, along with any necessarygrading, from the element size specified at the end points of theedge. See SUBDIVIDE POINT, POINT-SIZE (SIZE, PROGRESSION).


NDIV1 [1]Number of subdivisions assigned to the first parametric direction, u, of the geometry surfaces.

NDIV2 [1]Number of subdivisions assigned to the second parametric direction, v, of the geometry surfaces

RATIO1 [1.0]Ratio of lengths of the last to the first element edges along the edges corresponding to thefirst parametric direction, u, of the geometry surfaces. The grading of element edge lengths isgoverned by PROGRESSION.

RATIO2 [1.0]Ratio of lengths of the last to the first element edges along the edges corresponding to thesecond parametric direction, v, of the geometry surfaces. The grading of element edgelengths is governed by PROGRESSION.

PROGRESSION [GEOMETRIC]When element edges are to be graded, the distribution of element edge lengths can beselected from:



APPROXIMATE The distribution of edge lengths is made such that RATIO is onlyapproximately satisfied.


CBIAS1 [NO]

SUBDIVIDE SURFACE


Sec. 8.2 Mesh generationSUBDIVIDE SURFACE

Indicates if central bias is used along the parametric u direction. {NO/YES}

CBIAS2 [NO]Indicates if central bias is used along the parametric v direction. {NO/YES}


Auxiliary commands

LIST SUBDIVIDE SURFACE FIRST LAST



SUBDIVIDE VOLUME NAME MODE SIZE NDIV1 NDIV2 NDIV3 RATIO1RATIO2 RATIO3 PROGRESSION CBIAS1 CBIAS2CBIAS3

volumei

Assigns mesh subdivision data to a set of geometry volumes. The data can be in the form ofa specified element size, or the number of divisions along the edges of the geometry volume.The subdivision data is actually assigned to the geometry lines which comprise the edges ofthe geometry volumes.

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NAMELabel number of a geometry volume. Other volumes to have the same subdivision data maybe given on accompanying data-lines.


LENGTH An element size is input corresponding to the length of anelement edge. Each edge of the geometry volumes is subdividedseparately so as to give element edges which are approximately oflength SIZE (SIZE).

SUBDIVIDE VOLUME



DIVISIONS Each parametric direction of the geometry volumes is assigned anumber of subdivisions, which can be graded in size according tothe selected progression rule (NDIV1, NDIV2, NDIV3,RATIO1, RATIO2, RATIO3, PROGRESSION).

POINTWISE Each edge of the geometry volumes is assigned a number ofsubdivisions, which is calculated, along with any necessarygrading, from the element size specified at the end points of theedge. See SUBDIVIDE POINT, POINT-SIZE (SIZE,PROGRESSION).


NDIV1 [1]Number of subdivisions assigned to the first parametric direction, u, of the geometry vol-umes.

NDIV2 [1]Number of subdivisions assigned to the second parametric direction, v, of the geometryvolumes.

NDIV3 [1]Number of subdivisions assigned to the third parametric direction, w, of the geometryvolumes.

RATIO1 [1.0]Ratio of lengths of the last to the first element edges along the edges corresponding to thefirst parametric direction, u, of the geometry volumes. The grading of element edge lengths isgoverned by PROGRESSION.

RATIO2 [1.0]Ratio of lengths of the last to the first element edges along the edges corresponding to thesecond parametric direction, v, of the geometry volumes. The grading of element edgelengths is governed by PROGRESSION.

RATIO3 [1.0]Ratio of lengths of the last to the first element edges along the edges corresponding to thethird parametric direction, w, of the geometry volumes. The grading of element edge lengthsis governed by PROGRESSION.

SUBDIVIDE VOLUME



PROGRESSION [GEOMETRIC]When element edges are to be graded the distribution of element edge lengths can beselected from:



APPROXIMATE The distribution of edge lengths is made such that theratio of first to last edge lengths (RATIO1, RATIO2, orRATIO3) is only approximately satisfied.

Note: PROGRESSION = APPROXIMATE is only provided for compatibility withearlier versions of ADINA-IN. It is recommended that ARITHMETIC orGEOMETRIC normally be used.

CBIAS1 [NO]Indicates if central bias is used along the parametric u direction. {NO/YES}

CBIAS2 [NO]Indicates if central bias is used along the parametric v direction. {NO/YES}

CBIAS3 [NO]Indicates if central bias is used along the parametric w direction. {NO/YES}


Auxiliary commands

LIST SUBDIVIDE VOLUME FIRST LAST

SUBDIVIDE VOLUME



SUBDIVIDE EDGE NAME BODY MODE SIZE NDIV RATIOPROGRESSION

edgei

Assigns mesh subdivision data to edges of a solid geometry body. The data can be in theform of a specified element size, or the number of subdivisions along the edge.

NAMELabel number of a geometry edge of BODY. Other edges (of BODY) to have the samesubdivision data may be given in accompanying data-lines.

BODY [currently active body]Label number of the solid geometry body.

MODE [LENGTH]Selects the method of mesh subdivision data specification. This controls the actual param-eters used, other parameters are ignored.

DIVISIONS The geometry edge is assigned a number of subdivisions, whichcan be graded in size according to the selected progression rule(NDIV, RATIO, PROGRESSION).

LENGTH An element size is input corresponding to the length of anelement edge (SIZE).

POINTWISE The number of subdivisions, and any necessary grading, for thegeometry edges is calculated from the element size specified atthe end points of the geometry edge. See SUBDIVIDE POINT,

POINT-SIZE (SIZE, PROGRESSION).


NDIV [1]Number of subdivisions assigned to a geometry edges.

RATIO [1.0]Ratio of lengths of the last to the first element edges along the geometry edges. The gradingof element lengths is governed by PROGRESSION.

SUBDIVIDE EDGE



PROGRESSION [GEOMETRIC]When element edges are to be graded along the geometry edges (i.e., when RATIO ≠ 1.0),then the distribution of element edge lengths can be selected from the following.



edgeiLabel number of a geometry edge (of BODY).

Auxiliary commands

LIST SUBDIVIDE EDGE FIRST LAST

SUBDIVIDE EDGE



SUBDIVIDE FACE NAME BODY MODE SIZE NDIV PROGRESSIONMAX-SIZE

facei

Assigns mesh subdivision data to faces of a solid geometry body. The data can be in theform of a specified element size, or the number of divisions along the edges of the geometryfaces.

NAMELabel number of the geometry face (of BODY). Other faces (of BODY) to have the samesubdivision data may be given on accompanying data lines.

BODY [currently active body]Label number of the solid geometry body.


DIVISIONS The edges of the geometry faces are assigned a number ofsubdivisions (NDIV).

LENGTH An element size is input corresponding to the length of anelement face. Each edge of the geometry face is subdividedseparately so as to give element edges approximately the lengthof SIZE (SIZE).

POINTWISE The number of subdivisions, and any necessary grading, for theedges of geometry faces calculated from the element size specifiedat the end points of the geometry edges. See SUBDIVIDE POINT,POINT-SIZE (SIZE, PROGRESSION).


NDIV [1]Number of subdivisions assigned to the edges of the geometry faces.

PROGRESSION [GEOMETRIC]When element edges are to be graded, the distribution of element edge lengths can be

SUBDIVIDE FACE



selected from the following:



MAX-SIZE [0.0]If set to a value greater than 0.0, free-form meshing will be allowed to create elements greaterin size than the max size on the face�s boundary. Free-form meshing will however not beallowed to create elements with a size greater than MAX-SIZE. Relevant only withMESHING=FREE-FORM and METHOD=DELAUNAY in the GFACE command. {≥ 0.0}

faceiLabel number of a geometry face (of BODY).

Auxiliary commands

LIST SUBDIVIDE FACE FIRST LAST

SUBDIVIDE FACE



SUBDIVIDE BODY NAME MODE SIZE NDIV PROGRESSION MAX-SIZE

bodyi

Assigns mesh subdivision data to a set of solid geometry bodies. The data can be in the formof a specified element size or the number of divisions along the edges of the geometrybodies. The subdivision data is assigned to the edges of the geometry bodies.

NAMELabel number of a solid geometry body. Other geometry bodies to have the same subdivisiondata may be given in accompanying data lines.


DIVISIONS Each edge of the geometry bodies is assigned a number ofsubdivisions (NDIV).

LENGTH An element size is input corresponding to the length of anelement edge. Each edge of the geometry bodies is subdividedseparately so as to give element edges which are approximately oflength SIZE (SIZE).

POINTWISE Each edge of the geometry bodies is assigned a number ofsubdivisions, which are calculated, along with any necessarygrading, from the element size specified at the end points of theedge. See SUBDIVIDE POINT, POINT-SIZE (SIZE,PROGRESSION).


NDIV [1]Number of subdivisions assigned to the edges of the geometry bodies.

PROGRESSION [GEOMETRIC]When element edges are to be graded the distribution of element edge lengths can beselected from the following

SUBDIVIDE BODY





MAX-SIZE [0.0]If set to a value greater than 0.0, free-form meshing will be allowed to create elements greaterin size than the max size on the face�s boundary. Free-form meshing will however not beallowed to create elements with a size greater than MAX-SIZE. Relevant only withMESHING=FREE-FORM and METHOD=DELAUNAY in the GBODY command. {≥ 0.0}

Note that MAX-SIZE is passed down to the bounding faces.


Auxiliary commands

LIST SUBDIVIDE BODY FIRST LAST

SUBDIVIDE BODY



POINT-SIZE OPTION INPUT SIZE-FUNCTION MAXSIZEMINSIZE BODY

namei sizei

Specifies the mesh-size (element edge length) for a set of geometry points, either directly, orby a size-function, or by evaluation from the lengths of the lines/edges which meet at thepoints. The set of points can be given by label or by reference to other geometry entities inthe model.

OPTION [DIRECT]Indicates how the mesh-size is to be evaluated:

DIRECT The mesh-size is input in the data lines.

ATTACHED The lengths of the lines/edges which meet at a point, togetherwith input minimum, maximum values are used to determine themesh-size at that point.

FUNCTION A pre-defined size-function is used to calculate the mesh size at apoint, dependent on its location.

INPUT [POINT]Indicates how the set of points is defined:

MODEL All geometry points.

POINT The geometry points will be explicitly identified by label number.

LINE The end-points of a set of geometry lines.

SURFACE The vertices of a set of geometry surfaces.

VOLUME The vertices of a set of geometry volumes.

EDGE The end-points of a set of solid geometry edges.

FACE The vertices of a set of solid geometry faces.

BODY The vertices of a set of solid geometry bodies.

SIZE-FUNCTION [1]Label number of a size-function, input when OPTION = FUNCTION. See commandSIZE-FUNCTION.

POINT-SIZE



MAXSIZE [0.0]The maximum mesh-size for the input points. This is used in two cases:

OPTION = DIRECT, INPUT = MODEL The mesh-size at every geometry pointin the model will be set to MAXSIZE.

OPTION = ATTACHED The mesh-size computed from theattached lines/edges will be subject to amaximum value of MAXSIZE.

MINSIZE [0.0]The minimum mesh-size for the input points, used to provide a lower bound on the computedmesh-size when OPTION = ATTACHED.

BODY [currently active body]Label number of a solid geometry body. Used when INPUT = EDGE or FACE.

nameiEntity label number.

sizeiMesh-size, (element edge length) for entity namei. (Used when OPTION = DIRECT).

Note: If there is any ambiguity in the input, e.g. INPUT = LINE, OPTION = DIRECTwith two different mesh-sizes assigned to two lines which meet at a point, the

mesh size at the point is taken from the entity (line) with the higher label number.

POINT-SIZE



SIZE-FUNCTION BOUNDS NAME XMIN YMIN ZMIN XMAXYMAX ZMAX SIZE1 SIZE2 SIZE3SIZE4 SIZE5 SIZE6 SIZE7 SIZE8

SIZE-FUNCTION BOUNDS defines a mesh-size function in terms of a bounding box withfaces parallel to the global coordinate planes and the mesh-sizes at the vertices of the box.The mesh-size at any other point is interpolated from this bounding box.

A size-function may be used to set point mesh-sizes, via POINT-SIZE, and may also be useddirectly by the free-form mesh generation commands GFACE, GBODY to control the gener-ated element sizes.

In 8.3 and earlier versions, the size of a point outside the bounding box is given by the size ofthe point�s closest location on the bounding box (that size is interpolated from the sizes at the8 corners).

In version 8.4, inside the bounding box, the size is interpolated from the sizes at the 8 corners(same as version 8.3 and earlier). Outside the bounding box, the size follows a geometricprogression (see SIZE-FUNCTION POINT for geometric progression definition) with a fixedfactor of 1.4.

NAME [(current highest size-function label number) + 1]Label number of the size-function to be defined.

XMIN, YMIN, ZMIN [current minimum coordinates of model]Minimum coordinates of the bounding box.

XMAX, YMAX, ZMAX [current maximum coordinates of model]Maximum coordinates of the bounding box.

SIZE1Mesh-size (element edge length) at (XMAX,YMAX,ZMAX).

SIZE2Mesh-size (element edge length) at (XMIN,YMAX,ZMAX).

SIZE3Mesh-size (element edge length) at (XMIN,YMIN,ZMAX).

SIZE4Mesh-size (element edge length) at (XMAX,YMIN,ZMAX).

SIZE-FUNCTION BOUNDS



SIZE5Mesh-size (element edge length) at (XMAX,YMAX,ZMIN).

SIZE6Mesh-size (element edge length) at (XMIN,YMAX,ZMIN).

SIZE7Mesh-size (element edge length) at (XMIN,YMIN,ZMIN).

SIZE8Mesh-size (element edge length) at (XMAX,YMIN,ZMIN).

Auxiliary commands

LIST SIZE-FUNCTION FIRST LASTDELETE SIZE-FUNCTION FIRST LAST

SIZE-FUNCTION BOUNDS



SIZE-FUNCTION HEX NAME X1 Y1 Z1 X2 Y2 Z2 X3 Y3 Z3 X4 Y4Z4 X5 Y5 Z5 X6 Y6 Z6 X7 Y7 Z7 X8 Y8 Z8SIZE1 SIZE2 SIZE3 SIZE4 SIZE5 SIZE6 SIZE7SIZE8

SIZE-FUNCTION HEX defines a mesh-size function in terms of a bounding hexahedralvolume, specified by its vertex coordinates, and the mesh size at those vertices. The mesh-size at any other point is interpolated from this bounding box.

A size-function may be used to set point mesh-sizes, via POINT-SIZE, and may also be useddirectly by the free-form mesh generation commands GFACE, GBODY to control the gener-ated element sizes.

In 8.3 and earlier versions, the size of a point outside the bounding hexahedral volume isgiven by the size of the point�s closest location on the bounding hexahedral volume (that sizeis interpolated from the sizes at the 8 corners).

In version 8.4, inside the bounding hexahedral volume, the size is interpolated from the sizesat the 8 corners (same as version 8.3 and earlier). Outside the bounding hexahedral volume,the size follows a geometric progression (see SIZE-FUNCTION POINT for geometric progres-sion definition) with a fixed factor of 1.4.

NAME [(current highest size-function label number) + 1]Label number of the size-function to be defined.

X1, Y1, Z1Global Cartesian coordinates of vertex 1 of the bounding hexahedral volume.

. . .

X8, Y8, Z8Global Cartesian coordinates of vertex 8 of the bounding hexahedral volume.

SIZE1Mesh-size (element edge length) at vertex 1.



SIZE4

SIZE-FUNCTION HEX



Mesh-size (element edge length) at vertex 4.





Auxiliary commands


SIZE-FUNCTION HEX



SIZE-FUNCTION POINT NAME MODE POINT X Y Z SIZE DISTANCESCALE TYPE A1 A2 A3 PROGRESS

Defines a mesh-size function of source type where the element size is dependent on thedistance from a given location.

The size-function may be used to set point mesh-sizes, via command POINT-SIZE, and alsomay be used directly by the free-form mesh generation commands GFACE, GBODY to controlelement sizes during the meshing process.

NAME [(current highest size-function label) + 1]The identifying label number of the size-function.

MODEIndicates how the source location is defined:

POINT The source location is given by a geometry point.

POSITION The source location is given by a position vector (X,Y,Z).

POINTLabel number of a geometry point.

X [0.0]Y [0.0]Z [0.0]Global Cartesian system components of the position vector giving the source location.

SIZEConstant (minimum) element size. The size function will yield this value within the distancegiven by parameter DISTANCE from the specified location. Further away, the element sizegradually increases as determined by this command. {> 0.0}

DISTANCEDistance from location for which the size function is constant, giving element size SIZE.{> SIZE}

SCALE [1.0]Scaling factor for the distance from the source location.

SIZE-FUNCTION POINT



TYPE [LINEAR]Indicates the type of growth function for the element size away from the source location. Letd=distance from source location, R = MAX[ 0.0, ((d-DISTANCE)/SCALE)], δ= element size, thenthe following function types are available:

A1 [0.0]A2 [0.0]A3 [0.0]Function coefficients. {≥ 0.0 for TYPE = LINEAR, QUADRATIC, CUBIC}

PROGRESS [NONE]This option controls the progression of the meshing from the defined point. {NONE/ARITHMETIC/GEOMETRIC}

NONE TYPE, A1, A2, A3 are used according to the existing description (8.3 andearlier versions).

ARITHMETIC Only A1 is used. Sizing follows an arithmetic progression, in other words,past the sphere of radius DISTANCE, sizes increase (as the distance tothe sphere increases) by a constant value given by A1. Start withsize=SIZE, then next size is the previous size+A1.

GEOMETRIC Only A1 is used. Sizing follows a geometric progression, in other words,past the sphere of radius DISTANCE, sizes increase (as the distance tothe sphere increases) by a constant factor given by A1. Start withsize=SIZE, then next size is the previous size*A1.

Auxiliary commands


LINEAR

QUADRATIC

CUBIC

POWER

EXPONENTIAL

δ

δ

δ

δ

δ

= × + ×[ ]= × + × + ×[ ]= × + × + × + ×[ ]= × +[ ]= ×[ ]×( )

SIZE A R

SIZE A R A R

SIZE A R A R A R

SIZE R

SIZE e

A

A R

10 1

10 1 2

10 1 2 3

10

2

2 3

1

1

.

.

.

.

SIZE-FUNCTION POINT



SIZE-FUNCTION AXIS NAME MODE SYSTEM AXIS LINE P1 P2 X0Y0 Z0 XA YA ZA SIZE DISTANCE SCALETYPE A1 A2 A3 PROGRESS

Defines a mesh-size function of source type where the element size is dependent on thedistance from a given axis (an unbounded straight line).



MODESelects the method of defining the axis. This controls which parameters actually define theaxis - other parameters are ignored.

AXIS - The axis is taken as a coordinate axis of a given coordinate system.LINE - The axis is taken as the straight line passing through the end

points of a given geometry line (which is not necessarily straight, but must be open - i.e. have non-coincident end points).

POINTS - The axis is taken as the straight line between two given (non- coincident) geometry points.

VECTORS - The axis is defined by a position and a direction vector.

SYSTEM [current active coordinate system]Label number of a coordinate system. One of the axes of this coordinate system may be usedto define the axis, via parameter AXIS, when MODE=AXIS.

AXIS [XL]Selects which of the basic axes (XL,YL,ZL) of the local coordinate system, given by param-eter SYSTEM, is used to define the axis. {XL/YL/ZL}

LINELabel number of a geometry line defining the axis.

P1, P2Label numbers of geometry points used to define the axis.

X0 [0.0]Y0 [0.0]Z0 [0.0]Global coordinates of the position vector defining the axis when MODE=VECTORS.

SIZE-FUNCTION AXIS



XA [1.0]YA [0.0]ZA [0.0]Components (with respect to the global coordinate system) of the axis direction whenMODE=VECTORS.

SIZEConstant (minimum) element size. The size function will yield this value within the distancegiven by parameter DISTANCE from the specified axis. Further away, the element sizegradually increases as determined by this command. {> 0.0}

DISTANCEDistance from the axis for which the size function is constant, giving element size SIZE.{> SIZE}

SCALE [1.0]Scaling factor for the distance from the source axis.

TYPE [LINEAR]Indicates the type of growth function for the element size away from the source axis. Letd=distance from axis, R = MAX[ 0.0, ((d-DISTANCE)/SCALE)], δ = element size, then thefollowing function types are available:


LINEAR

QUADRATIC

CUBIC

POWER

EXPONENTIAL

δ

δ

δ

δ

δ

= × + ×[ ]= × + × + ×[ ]= × + × + × + ×[ ]= × +[ ]= ×[ ]×( )

SIZE A R

SIZE A R A R

SIZE A R A R A R

SIZE R

SIZE e

A

A R

10 1

10 1 2

10 1 2 3

10

2

2 3

1

1

.

.

.

.





ARITHMETIC Only A1 is used. Sizing follows an arithmetic progression, in other words,past the cylinder of radius DISTANCE, sizes increase (as the distance tothe cylinder increases) by a constant value given by A1. Start withsize=SIZE, then next size is the previous size+A1.

GEOMETRIC Only A1 is used. Sizing follows a geometric progression, in other words,past the cylinder of radius DISTANCE (where size is given by SIZE),sizes increase (as the distance to the cylinder increases) by a constantfactor given by A1. Start with size=SIZE, then next size is the previoussize*A1.

Auxiliary commands


SIZE-FUNCTION AXIS






SIZE-FUNCTION PLANE NAME MODE X Y Z NX NY NZ P1 P2P3 SYSTEM COORDINATE SIZEDISTANCE SCALE TYPE A1 A2 A3 PROGRESS

Defines a mesh-size function of source type where the element size is dependent on thedistance from a given plane.



MODEThis controls the origin and direction of the size-function source plane as follows:

POSITION-NORMAL The origin is given by a position vector (X,Y,Z), and theplane normal by a direction vector (NX,NY,NZ).

POINT-NORMAL The origin is given by a geometry point P1, and the planenormal by a direction vector (NX,NY,NZ).

THREE-POINT The origin is given by a geometry point P1, and the planenormal is determined from two other points, P2, P3, lyingin the plane. The points cannot be collinear.

XPLANE The size-function source plane passes through theYPLANE specified coordinate value (COORDINATE) for a givenZPLANE coordinate system (SYSTEM).

X [0.0]Y [0.0]Z [0.0]The position vector of a point lying in the source plane. Used when MODE=POSITION-NORMAL.

NX [1.0]NY [0.0]NZ [0.0]The direction vector of the normal to the source plane. Used when MODE=POSITION-NORMAL or POINT-NORMAL.

SIZE-FUNCTION PLANE



P1P2P3Label numbers of three non-collinear geometry points lying in the source plane. P1 is usedwhen MODE=POINT-NORMAL or THREE-POINT, and P2, P3 are only used whenMODE=THREE-POINT.

SYSTEM [current active coordinate system]Label number of a coordinate system. The source plane passes through the base Cartesiancoordinate value as determined by parameters MODE and COORDINATE. Used whenMODE=XPLANE, YPLANE, or ZPLANE.

COORDINATE [0.0]The position of the size-function sourc plane along the specified coordinate direction ofcoordinate system SYSTEM. Used when MODE=XPLANE, YPLANE, or ZPLANE.

SIZEConstant (minimum) element size. The size function will yield this value within the distancegiven by parameter DISTANCE from the specified plane. Further away, the element sizegradually increases as determined by this function. {> 0.0}

DISTANCEDistance from the plane for which the size function is constant, giving element size SIZE.{> SIZE}

SCALE [1.0]Scaling factor for the distance from the source plane.

TYPE [LINEAR]Indicates the type of growth function for the element size away from the source plane. Letd=distance from plane, R = MAX[ 0.0, ((d-DISTANCE)/SCALE)], δ = element size, then thefollowing function types are available:

LINEAR

QUADRATIC

CUBIC

POWER

EXPONENTIAL

δ

δ

δ

δ

δ

= × + ×[ ]= × + × + ×[ ]= × + × + × + ×[ ]= × +[ ]= ×[ ]×( )

SIZE A R

SIZE A R A R

SIZE A R A R A R

SIZE R

SIZE e

A

A R

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10 1 2

10 1 2 3

10

2

2 3

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.

.

.

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SIZE-FUNCTION PLANE






ARITHMETIC Only A1 is used. Sizing follows an arithmetic progression, in other words,sizes increase (as the DISTANCE to the plane increases) by a constantvalue given by A1. Start with size=SIZE, then next size is the previoussize+1.0*A1, etc.

GEOMETRIC Only A1 is used. Sizing follows a geometric progression, in other words,sizes increase (as the DISTANCE to the plane increases) by a constantvalue given by A1. Start with size=SIZE, then next size is the previoussize*A1, etc.

Auxiliary commands


SIZE-FUNCTION PLANE



SIZE-FUNCTION COMBINED NAME

szfunci

Defines a mesh-size function as a combination of other size-functions. The element size atany given location is taken as the minimum of all the size-functions which contribute to thiscombination.



szfunciLabel number of an existing size-function. This function cannot be the same as NAME, or oftype COMBINED - i.e. recursive combinations are not allowed.

Auxiliary commands


SIZE-FUNCTION COMBINED



SIZE-LOCATIONS BODY FACE

loci xi yi zi sizei

Specifies the mesh-size (element edge length) at coordinate locations (i.e. independent ofany geometry point positions). These size-locations may be utilized by the free-meshingcommands GFACE, GBODY to locally set element sizes within the bounds of a solid geometryface or body.

The points along with the sizes are inserted into a �size octree� which will be used for meshdensity purposes in GFACE and GBODY.

BODY [currently active body]Label number of a solid geometry body to which the size-locations are to be associated.

FACE [0]Label number of a the solid geometry face (of BODY) to which the size-locations are to beassociated. If FACE = 0, the size-locations are to be associated with the solid geometry bodyinterior and not with any particular one of its faces. Conversely, if FACE > 0, then the size-locations are only associated with that face alone, and not with the interior of the body orany other of its faces.

lociLocation identifier.

xi, yi, ziGlobal Cartesian coordinates of the size-location loci.

sizeiMesh-size, element edge length at (xi, yi, zi).

Auxiliary commands

LIST SIZE-LOCATIONS BODY FACEDELETE SIZE-LOCATIONS BODY FACE

SIZE-LOCATIONS



NLTABLE NAME BODY

gtypei ent1i ent2i nlayeri

Creates a table which specifies the minimum number of layers across thin setions in a body oron a face. Each thin section is specified by 2 opposing faces or edges.Tables can be used by commands GBODY and GFACE.

NAMELabel number of a table - NLTABLE.

BODYGeometry body label.

gtypeiSpecifies the entity type for entries ent1i and ent2i.

EDGE ent1i and ent2i are edges on face.

FACE ent1i and ent2i are faces.

ent1iFirst face or edge label.

ent2iSecond face or edge label.

nlayeriMinimum number of elements across the 2 faces or edges.

Note: This command allows the user to control where the thin sections should beconsidered at the face/face level and also at the edge/edge level for a given face.

NLTABLE



GPOINT NAME NODE NCOINCIDE NCTOLERANCE SUBSTRUCTURE

Creates a node at a geometry point.

NAMEThe label number of a geometry point at which a node is to be created.

NODE [(highest node label number) + 1]The label number of node to be created.

NCOINCIDE [NO]Selects the method of nodal coincidence checking.

ALL The global coordinates of the generated node is compared against those ofexisting nodes of the substructure. If there is coincidence to within

NCTOLERANCE × (max. difference in global coordinates between allcurrent nodes of the substructure)

then no new node is created at that location.



SUBSTRUCTURE [current substructure label number]Label number of the substructure in which the node is created.

GPOINT



GLINE NAME NODES AUXPOINT NCOINCIDE NCENDSNCTOLERANCE SUBSTRUCTURE GROUP NCDOMAINMIDNODES

linei

Generates elements along a set of geometry lines. Elements can be created within elementgroups of type: TRUSS, BEAM, ISOBEAM, PIPE, GENERAL, or FLUID2 (interface).

The number of elements, and the distribution of their lengths, is governed by the subdivisiondata assigned to the geometry lines, e.g., via SUBDIVIDE LINE.

Note that either a single line or multiple lines may be specified for generation of elements,using the same control parameters.

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NAMEThe label number of a geometry line along which elements are to be generated.

NODES [2]The number of nodes per element.

2, 3, 4 for TRUSS, ISOBEAM and GENERAL elements.2 for BEAM elements.2, 4 for PIPE elements.2, 3 for FLUID2 (interface) elements.

GLINE



AUXPOINTThe label number of the auxiliary geometry point used to orient BEAM, ISOBEAM, and PIPEelements. A node is generated at this point, unless one already exists at that location, whichbecomes the auxiliary node for each element generated on the geometry line.

NCOINCIDE [ALL]Selects the method of nodal coincidence checking.

Coincidence checking is used to determine whether to place a new node at a geometriclocation when there is already at least one node close to that geometric location.

A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB-XA| ≤ COINCIDENCE * XLEN |YB-YA| ≤ COINCIDENCE * YLEN |ZB-ZA| ≤ COINCIDENCE * ZLEN

where NCTOLERANCE is a parameter of this command and (XLEN, YLEN, ZLEN) are decidedby the following:

If NCTOL-TYPE = RELATIVE-LOCAL in command TOLERANCES GEOMETRIC, (XLEN,YLEN, ZLEN) are the lengths of the bounding box for the volume before generation.

If NCTOL-TYPE = RELATIVE-GLOBAL in command TOLERANCES GEOMETRIC, (XLEN,YLEN, ZLEN) are the lengths of the bounding box for the model before generation.

If NCTOL-TYPE = ABSOLUTE in command TOLERANCES GEOMETRIC or no bounding boxin the model, (XLEN, YLEN, ZLEN) are taken as (1.0, 1,0, 1.0).

ALL The global coordinates of all generated nodes are compared againstthose of existing nodes of the substructure.

ENDS Coincidence checking is carried out only for the nodes generated atthe end points of the geometry lines. The end point(s) participatingin this checking process may be selected via NCENDS.

LINE Coincidence checking is carried out for all generated nodes, butcomparison is made only against those nodes already generated onthe line under consideration.

SELECTED Coincidence checking is carried out at the end points of thegeometry lines, but comparison is made only against the nodesgenerated for the input set of lines for the current commandexecution and those already generated for the geometry domainindicated by NCDOMAIN.

GLINE




NCENDS [12]Selects which end points of the geometry lines participate in nodal coincidence checking.NCENDS is an integer of up to two distinct digits, either 1 or 2, indicating which end pointsof the geometry line are subject to nodal coincidence checking. NCENDS is only used whenNCOINCIDE = ENDS.


SUBSTRUCTURE [current substructure label number]Label number of the substructure in which the elements and nodes are generated.

GROUP [current element group]The label number of the element group into which the elements are generated. The grouptype must be one of those listed above.

NCDOMAIN [0]Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN.Used only when NCOINCIDE = SELECTED. NCDOMAIN = 0 indicates that no domain is tobe used.

MIDNODES [CURVED]Indicates whether the mid-side nodes for higher order elements are to be placed on thestraight line between the relevant vertex nodes, or on the underlying curved geometry.{CURVED/STRAIGHT}


Note: Elements are generated in order, in the direction from the starting point P1 to theending point P2 of the geometry line.

GLINE



GSURFACE NAME NODES PATTERN NCOINCIDE NCEDGENCVERTEX NCTOLERANCE SUBSTRUCTURE GROUPPREFSHAPE MESHING SMOOTHING DEGENERATECRACK-TYPE TIP-POINT TIP-OPTION RADIUSQ-POINT CPOINT1 CPOINT2 COLLAPSED NCDOMAINMIDNODES METHOD FLIP

surfacei

Generates elements on a set of geometry surfaces. Elements can be created within elementgroups of type: TWODSOLID, PLATE, SHELL, GENERAL, FLUID2, or FLUID3 (interface).

The distribution of elements, including their size, is governed by the subdivision data assignedto the edges of the geometry surfaces, e.g., via SUBDIVIDE SURFACE.

Note that either a single surface or multiple surfaces may be specified for generation of ele-ments, with the same control parameters.

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NAMEThe label number of a geometry surface on which elements are to be generated.

NODES [8 (3 for plate elements)]The number of nodes per element. {3/4/6/7/8/9/16}

PATTERN [AUTOMATIC]Selects the type of pattern used to further subdivide quadrilateral surface cell subdivisions.Allowable values for PATTERN are integer numbers 0 through 11, or the string valueAUTOMATIC. PATTERN=1 to 9 is allowed for triangular elements (NODES=3, 6, 7) andPATTERN=10, 11 is allowed only for NODES=4. See Figure.

PATTERN OPTIONS:

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NCOINCIDE [ALL]Selects the method of nodal coincidence checking.


A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if|XB - XA| ≤ NCTOLERANCE*XLEN|YB - YA| ≤ NCTOLERANCE*YLEN|ZB - ZA| ≤ NCTOLERANCE*ZLEN

where where NCTOLERANCE is a parameter of this command and (XLEN, YLEN, ZLEN) aredecided by the following:

If NCTOL-TYPE = RELATIVE-LOCAL in command TOLERANCES GEOMETRIC, (XLEN,YLEN, ZLEN) are the lengths of the bounding box for the body before generation.



If there are no nodes close to that geometric location, a new node is placed at that geometriclocation.

Otherwise, parameter NCOINCIDE governs whether a new node is placed at that geometriclocation, or whether a close node is used instead, as shown in the following table:

NCOINCIDE Which nodes to Which nodes toconsider for coincidence check against

ALL all all

BOUNDARIES those on all vertices alland edges of the face

SELECTED those on all vertices those within theand edges of the face geometry domain

specified by parameterNCDOMAIN

GSURFACE



GROUP those on all vertices those that are inand edges of the face the same elementor faces meshed by the groupcurrent command

NO none none

NCEDGE [1234]Selects which edges of the geometry surfaces participate in nodal coincidence checking.NCEDGE is an integer of up to four distinct digits in the range 1 through 4. NCEDGE is onlyused when NCOINCIDE = BOUNDARIES.

NCVERTEX [1234]Selects which vertices of the geometry surfaces participate in nodal coincidence checking.NCVERTEX is an integer of up to four distinct digits in the range 1 through 4. NCVERTEX isonly used when NCOINCIDE = BOUNDARIES.



GROUP [current element group]The label number of the element group into which the generated elements are generated.

PREFSHAPE [AUTOMATIC]This specifies the preferred shape of the cells created when the surface subdivision isirregular.

If MESHING=MAPPED, AUTOMATIC - The command selects the appropriate cell shape depending on

the surface geometry and element (group) type. QUADRILATERAL - A quadrilateral cell shape is preferred. TRIANGULAR - A triangular cell shape is preferred.

If MESHING=FREE-FORM, AUTOMATIC - QUADRILATERAL if METHOD=ADVFRONT,

TRIANGULAR if METHOD=DELAUNAY. QUADRILATERAL - A quadrilateral cell shape is preferred. TRIANGULAR - A triangular cell shape is preferred. QUAD-DIRECT - Quadrilateral only meshing.

GSURFACE


Sec. 8.2 Mesh generationGSURFACE

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MESHING [MAPPED]Selects the type of mesh generation to be employed.

MAPPED Rule-based mapping of surface edge subdivisions.

FREE-FORM Free-form mesh generation based on advancing front or Delaunayscheme.

SMOOTHING [NO]Indicates whether or not Laplacian smoothing is employed to improve mesh quality.{YES/NO}

GSURFACE

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DEGENERATE [NO]Indicates whether triangular surfaces (with coincident vertices) are to be treated as degener-ate quadrilaterals or triangles (with a special consideration for the degenerate edge, seeFigure) for irregular rule-based mapped meshing. {YES/NO}

CRACK-TYPE [NONE]Selects the type of crack propagation on surfaces, which controls mesh generation. See Figures.

NONE No crack propagation.

LINE Crack propagation along line.

POINT Crack is stationary at a point.

Note: When CRACK-TYPE ≠ NONE, GSURFACE will adjust the mesh generated for aset of input surfaces (i.e., more than one surface is typically required) for use infracture mechanics problems, as shown in the Figures.

TIP-POINT [1]The label number of the crack tip point.

TIP-OPTION [SINGULAR]Allows the crack tip region to be represented as a single point or a circular arc.

SINGULAR The tip region is a single point.

RIGHT-ARC The tip region is a 90° arc quadrant to the right of the tip.

LEFT-ARC The tip region is a 90° arc quadrant to the left of the tip.

CIRCULAR-ARC The tip region is semi-circular.

RADIUS [0.0]The radius of the circular arc generated about the crack tip.

Q-POINT [QUARTER]Controls the placement of mid-side nodes in elements adjacent to the crack-tip.

MID The nodes are generated without any special placement.

QUARTER Mid-side nodes are generated at the �¼� point adjacentto crack tip.

GSURFACE


Chap. 8 Finite element representation GSURFACE

CPOINT1 [0]CPOINT2 [0]Allows for the specification of the points that are to be generated at key positions. Thisprovides the ability to subsequently refer to these locations and any lines they belong to.Note that the point label numbers CPOINT1 and CPOINT2 must not have been defined priorto this command. See Figures.

COLLAPSED [NO]Selects whether triangular TWODSOLID, FLUID2 or FLUID-3 (interface) elements are to betreated as collapsed quadrilateral elements by ADINA. {YES/NO}



METHOD [ADVFRONT]Indicates the type of free-form meshing algorithm to be used.There are two available methods:

ADVFRONT - Based upon advancing front methodology.DELAUNAY - Based upon Delaunay insertion methodology.

FLIP [NO]Reverses the orientation of shell elements on the surface. This parameter is only used whenthe element type is SHELL for ADINA or SHELL CONDUCTION for ADINA-T. {NO/YES}

surfaceiLabel numbers of geometry surfaces.



GVOLUME NAME NODES PATTERN NCOINCIDE NCFACENCEDGE NCVERTEX NCTOLERANCE SUBSTRUCTUREGROUP MESHING PREFSHAPE DEGENERATENCDOMAIN MIDNODES METHOD BOUNDARY-METHOD

volumei

Generates elements on a set of geometry volumes. Elements can be created within elementgroups of type THREEDSOLID or FLUID3.

The distribution of elements, including their size, is governed by the subdivision dataassigned to the edges of the geometry volumes, e.g., via SUBDIVIDE VOLUME.

NAMEThe label number of a geometry volume on which elements are to be generated.

NODES [20]The number of nodes per element. {4/8/10/11/20/27}

PATTERN [0]Selects the pattern used to subdivide hexahedral volume into tetrahedral elements (usedwhen NODES=4, 10 or 11) - see Figures. PATTERN=0 indicates that one of the patterns 1through 4 is to be automatically selected so as to match the patterns already used foradjacent volumes. If no pattern is suitable, for PATTERN=0, then a warning message is givenand no elements are generated - in this case existing pattern usage must be examined care-fully to avoid pattern mismatches which would result in incompatible meshes. (This param-eter is only used when MESHING=MAPPED)

NCOINCIDE [BOUNDARIES]Selects the method of nodal coincidence checking. {ALL/BOUNDARIES/SELECTED/BOUNDEXSEL/GROUP/NO}




GVOLUME



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Otherwise parameter NCOINCIDE governs whether a new node is placed at that geometriclocation, or whether a close node is used instead, as shown in the following table:


ALL all all

BOUNDARIES those on the selected allvertices, edges and faces ofthe volume. Vertices,edges and faces are selectedby parameters NCVERTEX,NCEDGE and NCFACE

SELECTED those on all vertices, those withinedges and faces of the the geometry domainvolume or volumes meshed selected by parameterby the current command NCDOMAIN

BOUNDEXSEL those on all vertices, alledges and faces of thevolume except surfacesin the domain specified byNCDOMAIN

GROUP those on all vertices, those that are inedges and faces of the the same elementvolume or volumes meshed groupby the current command

NO none none

GVOLUME



NCFACE [123456]Selects which faces of the geometry volumes participate in nodal coincidence checking.NCFACE is an integer of up to six distinct digits in the range 1 through 6. NCFACE is onlyused when NCOINCIDE = BOUNDARIES. Refer to the follwoing figure for numbering (F1,F2, etc.)

NCEDGE [123456789ABC]Selects which edges of the geometry volumes participate in nodal coincidence checking.NCEDGE is an alphanumeric string which can include the digits 1-9 and the characters A, B,C. NCEDGE is only used when NCOINCIDE = BOUNDARIES. Refer to the follwoing figurefor numbering (E1, E2, etc.)

GVOLUME

V1

V2

V3

V4

V1V2

V3

V4

V2 V1

V5

V7

V3

V6

F1

F4

F3

F2

V4

V8

F6

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V3 V4

V5

V6

F5

F4

F5

F1

F2

F3

F4

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F3

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F5

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E2

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E7 E8E9

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E11

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E2

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E2

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NCVERTEX [12345678]Selects which vertices of the geometry volumes participate in nodal coincidence checking.NCVERTEX is an integer of up to eight distinct digits in the range 1 through 8. NCVERTEX isonly used when NCOINCIDE = BOUNDARIES. Refer to the follwoing figure for numbering(V1, V2, etc.)



GROUP [current element group]The label number of the element group in which the generated elements are created.

MESHING [MAPPED]Selects the type of mesh generation to be employed.

MAPPED Rule-based mapping based on volume edge subdivisions.

FREE-FORM Free-form mesh generation.

When MESHING = MAPPED, and the volume subdivision is regular, the resulting mesh willconsist entirely of hexahedral (brick) cells. If the subvision is irregular, the resulting mesh willbe a mix of hexahedra and prisms, and the parameter PREFSHAPE (following) can be used. Ifthe subdivision is neither regular nor irregular, an error message will be given.

Example:In the case of the rectangular volume shown in the figure accompanying the commandNCVERTEX (see preceding page), if we define Ni as the number of subdivisions on edge Ei(i = 1, 2, ...12), and set

N2 = N4 = N12 = N10; N1 = N3 = N11 = N9; and N5 = N6 = N7 = N8,

we have the volume set up with regular subdivisions, and the resulting mesh will be all-hexahedral. If, however, we set

N5 = N6 = N7 = N8; N1 = N9; N2 = N10; N3 = N11; and N4 = N12,

the volume is set up with irregular subdivisions.

PREFSHAPE [AUTOMATIC]Specifies the preferred shape of the cells created when the volume subdivision is irregular,

GVOLUME



whereby the command employs a rule-based scheme for mapped meshing.

AUTOMATIC The appropriate cell shape is determined by the program,depending on the volume geometry and element group type.

HEXAHEDRAL A brick cell shape is preferred.

PRISMATIC A prism cell shape is preferred.

DEGENERATE [YES]Indicates whether or not volumes of shape PRISM, TETRA or PYRAMID are to be treated asdegenerate hexahedra with special consideration of the degenerate edges. {YES/NO}

NCDOMAIN [0]Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN.Used only when NCOINCIDE = SELECTED or NCOINCIDE = BOUNDEXSEL. NCDOMAIN= 0 indicates that no domain is to be used.


METHOD [DELAUNAY]Indicates the type of free-form meshing algorithm to be used. There are two available meth-ods: advancing front and Delaunay. This parameter is used only when MESHING=FREE-FORM. {ADVFRONT/DELAUNAY}

BOUNDARY-METHOD [ADVFRONT]Indicates the type of free-form meshing algorithm to be used for triangular elements onvolume�s boundary. There are two available methods: advancing front and Delaunay. Thisparameter is only used when MESHING=FREE-FORM. {ADVFRONT / DELAUNAY}




GEDGE NAME NODES AUXPOINT NCOINCIDE NCTOLERANCESUBSTRUCTURE GROUP BODY NCDOMAINMIDNODES

edgei

Generates elements along a set of solid geometry edges. Elements can be created withinelement groups of types TRUSS, BEAM, ISOBEAM, PIPE, GENERAL or FLUID2- interface.

The number of elements, and the distribution of their lengths, is governed by the subdivisiondata assigned to the geometry edges, e.g., via SUBDIVIDE EDGE.

Note that either a single edge or multiple edges may be specified for generation of elements.

NAME

The label number of a geometry edge along which elements are to be generated.

NODES [2]The number of nodes per element.

2, 3, 4 for TRUSS, ISOBEAM and GENERAL elements.2 for BEAM elements.2, 4 for PIPE elements.2, 3 for FLUID2 (interface) elements.

GEDGE

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Chap. 8 Finite element representation GEDGE

AUXPOINTThe label number of the auxiliary geometry point used to orient BEAM, ISOBEAM, and PIPEelements. A node is generated at this point, unless one already exists at that location, whichbecomes the auxiliary node for each element generated on the geometry edge.

NCOINCIDE [ENDS]Selects the method of nodal coincidence checking.


A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB-XA| ≤ COINCIDENCE * XLEN |YB-YA| ≤ COINCIDENCE * YLEN |ZB-ZA| ≤ COINCIDENCE * ZLEN

where NCTOLERANCE is a parameter of this command and (XLEN, YLEN, ZLEN) are decidedby the following:

If NCTOL-TYPE = RELATIVE-LOCAL in command TOLERANCES GEOMETRIC, (XLEN,YLEN, ZLEN) are the lengths of the bounding box for the volume before generation.



ALL The global coordinates of all generated nodes are compared againstthose of existing nodes of the substructure.

ENDS Coincidence checking is carried out only for the nodes generatedat the end points of the geometry edges.

SELECTED Coincidence checking is carried out at the end points of thegeometry edges, but comparison is made only against those nodesgenerated for the input set of edges for the current commandexecution and those already generated for the geometry domainindicated by NCDOMAIN.





SUBSTRUCTURE [current substructure]Label number of the substructure in which the elements and nodes are generated.

GROUP [current element group]The label number of the element group into which the elements are generated. The grouptype must be one of those listed above.

BODY [currently active body]The solid geometry part (body) label number.

NCDOMAIN [0]Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN.Used only when NCOINCIDE = SELECTED. NCDOMAIN = 0 indicates that no domain isto be used.


edgeiLabel number of a geometry edge.

GEDGE


Chap. 8 Finite element representation GFACE

GFACE NAME NODES NCOINCIDE NCTOLERANCE SUBSTRUCTUREGROUP PREFSHAPE BODY COLLAPSED SIZE-FUNCTIONNCDOMAIN MIDNODES METHOD NLAYER NLTABLEGEO-ERROR SAMPLING MIN-SIZE AUTO-GRADING SIMULATE

facei

Generates elements on a set of solid geometry faces. Elements can be created within elementgroups of type TWODSOLID, PLATE, SHELL, FLUID2, FLUID3-interface or GENERAL.

There are two methods for quadrilateral mesh generation (controlled by PREFSHAPE param-eter). If PREFSHAPE=QUAD-DIRECT,a proprietary algorithm is used to generate an all-quad mesh. This methodology requires an even number of subdivisions for each boundingedge (enforced automatically). If PREFSHAPE=QUADRILATERAL, an advancing frontmethod is used which may leave some triangles in the mesh.

Two triangular free-form meshing methods (controlled by METHOD parameter) are available:advancing front and Delaunay.

The distribution of elements, including their size, is governed by the subdivision dataassigned to the edges of geometry faces, e.g. via SUBDIVIDE FACE.

NAMEThe label number of a solid geometry face on which elements are to be generated.

NODES [8 (3 for PLATE elements)]The number of nodes per element. {3/4/6/7/8/9/16}



NCOINCIDE [BOUNDARIES]Selects the method of nodal coincidence checking. {ALL/BOUNDARIES/BOUNDEXSEL/GROUP/EXSELECTED/NO/SELECTED}








Otherwise, parameter NCOINCIDE governs whether a new node is placed at that geometriclocation, or whether a close node is used insted, as shownin the following table:


ALL all all

BOUNDARIES those on all vertices alland edges of the face

BOUNDEXSEL those on all vertices, alledges and faces of thegeometry body exceptedges in the domain specifiedby NCDOMAIN

GFACE


Chap. 8 Finite element representation GFACE

GROUP those on all vertices those that are inand edges of the face the same elementor faces meshed by the groupcurrent command

EXSELECTED those on all vertices, all, except those comingedges and faces of the from the entities in thegeometry body or bodies in the DOMAIN provided.meshed by the current Similar in concept tocommand BOUNDEXSEL (the DOMAIN

provided contains entitiesbounding the body to bemeshed)

NO none none

SELECTED nodes on boundary nodes coming from the entitiesin domain NCDDOMAIN


SUBSTRUCTURE [current substructure]Label number of the substructure in which the elements and nodes are generated.

GROUP [current element group]The label number of the element group into which the elements are generated.

PREFSHAPE [TRIANGULAR]Specifies the shape or preferred shape of the elements generated. {QUADRILATERAL/TRIANGULAR/QUAD-DIRECT}

QUADRILATERAL Quadrilateral elements are preferred.

TRIANGULAR Triangular elements are generated.

QUAD-DIRECT Quadrilateral elements are generated.

BODY [currently active solid body]The solid geometry body label number.

COLLAPSED [NO]Selects whether triangular TWODSOLID, FLUID2 or FLUID3-interface elements are to betreated as collapsed quadrilateral elements by ADINA. {YES/NO}



SIZE-FUNCTION [0]Label number of a mesh-size function (see command SIZE-FUNCTION) which may be used tocontrol the element sizes away from the boundary edges of the face. SIZE-FUNCTION = 0implies a size function is not to be used. Was not used in 8.3 and earlier (or if used withadvancing front, was not giving the expected results). It is now functional if METHOD =DELAUNAY and BOUNDARY = DELAUNAY. (ADINA)



METHOD [ADVFRONT]Indicates the type of free-form meshing algorithm to be used. There are two availablemethods: advancing front and Delaunay. {ADVFRONT/DELAUNAY}

NLAYER [1]Specifies a minimum number of elements across. By default, this option is off. To be turnedon, NLAYER must be greater than 1.If NLAYER > 1 the distribution of elements, including their size, is also governed by thepresence of thin sections on the face.

NLAYER > 1 and NLTABLE = 0 NLAYER is taken as the minimum number ofelements across anywhere in the body.

NLAYER > 1 and NLTABLE > 0 the minimum number of elements across is takenfrom the table NLTABLE (see commandNLTABLE).

GFACE

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When NLAYER = 2, the program will make sure that there are NO interior mesh edges(segments) with both end vertices located on the boundary.Notes:1) Only the first face (if more than one) will be affected by NLTABLE.2) This option works best if a given bounding edge is NOT close to more than one other

bounding edges within a small area, e.g., case of a small sphere close to the corner of asquare.

3) The number of requested thin layers will be present in the thin sections but there is noguarantee near side boundaries.

NLTABLE [0]Table which indicates the thin sections of face.

GEO-ERROR [0.0]Relative geometric discretization error (see picture). If GEO-ERROR > 0.0 the distribution ofelements, including their size, is also governed by the curvature of the geometry body'sbounding edges and faces. (Only applicable if METHOD=DELAUNAY.)

SAMPLINGNumber of sampling points on edge Meaningful only if GEO-ERROR option turned on.For edges: number of sampling points = SAMPLINGFor faces: number of sampling points = SAMPLINGxSAMPLING

MIN-SIZEMinimum size allowed. Meaningful only if GEO-ERROR option turned on. It is important togive a meaningful value to MIN-SIZE to avoid overrefinement and, as a consequence, highCPU times for this command. (Only applicable if METHOD=DELAUNAY.)

AUTO-GRADING [NO]Mesh densities required to satisfy smooth gradation. {NO/YES}If AUTO-GRADING=YES the distribution of elements, including their size, is also governedby the requirement for smoothly graded mesh densities.

SIMULATE [NO]This parameter can be used (SIMULATE=YES) to see the effect on the body edge subdivi-sions of the GFACE command without actually meshing. It is relevant for the following cases:

- MESHING= FREE-FORM, and GEO-ERROR > 0.0 or AUTO-GRADING = YES

- MESHING=FREE-FORM and PREFSHAPE=QUAD-DIRECT (will modify body edgesubdivisions so that the body face has an even number of subdivisions; necessary conditionfor quadrilateral meshing on the body face)

GFACE




GFACE


Chap. 8 Finite element representation GBODY

GBODY NAME NODES NCOINCIDE NCTOLERANCE SUBSTRUCTUREGROUP PREFSHAPE SIZE-FUNCTION DELETE-SLIVERANGLE-MIN MIDNODES METHOD PATTERN MESHINGDEGENERATE BOUNDARY-METHOD DEG-EDGE GEO-ERRORSAMPLING MIN-SIZE NLAYER NLTABLE AUTO-GRADINGNCDOMAIN PYRAMIDS DANGMAXB DANGMAXCDANGMAXD HEXALAYER SIMULATE EVEN MIDFACENODES

bodyi deg-edgei

Command GBODY creates elements for a solid geometry body. Elements can be created withinelement groups of type THREEDSOLID or FLUID3.

There are two tetrahedral free-form meshing METHODs available: advancing front andDelaunay. There are two triangular free-form meshing BOUNDARY-METHODs available:advancing front and Delaunay.

Mapped meshing is available only when the body type is a Parasolid® body and the geometryof the body is either tetrahedron, hexahedron, prism or pyramid.

NAMEThe label number of a solid geometry body for which elements are to be generated.




NCOINCIDE [BOUNDARIES]Selects the method of nodal coincidence checking. {ALL/BOUNDARIES/BOUNDEXSEL/GROUP/EXSELECTED/NO/SELECTED}







If there are no nodes close to that geometric location, a new node is placed at that geometriclocation. Otherwise parameter NCOINCIDE governs whether a new node is placed at thatgeometric location, or whether a close node is used instead, as shown in the following table:


ALL all all

BOUNDARIES those on all vertices, alledges and faces of thegeometry body

BOUNDEXSEL those on all vertices, alledges and faces of thegeometry body except facesin the domain specified byNCDOMAIN

GBODY


Chap. 8 Finite element representation GBODY

GROUP those on all vertices, those that are inedges and faces of the the same elementgeometry body or bodies groupmeshed by the currentcommand

EXSELECTED those on all vertices, all, except those comingedges and faces of the from the entities in thegeometry body or bodies in the DOMAIN provided.meshed by the current Similar in concept tocommand BOUNDEXSEL (the DOMAIN

provided contains entitiesbounding the body to bemeshed)

NO none none

SELECTED nodes on boundary nodes coming from the entitiesin domain NCDDOMAIN


SUBSTRUCTURE [current substructure]Label number of the substructure in which the elements and nodes are created.


PREFSHAPE [AUTOMATIC]Specifies the preferred shape of the cells created when the body subdivision is irregular,whereby the command employs a rule-based scheme for mapped meshing.

AUTOMATIC The appropriate cell shape is determined by the program,depending on the body geometry and element group type.

HEXAHEDRAL A brick cell shape is preferred.

PRISMATIC A prism cell shape is preferred.

This parameter is used only when MESHING=MAPPED.



SIZE-FUNCTION [0]Selects an auxiliary mesh-size function which controls the element sizes within the body. Seecommand SIZE-FUNCTION. SIZE-FUNCTION = 0 indicates that a size-function is not to beused. Was not used in 8.3 and earlier (or if used with advancing front, was not giving theexpected results). It is now functional if METHOD = DELAUNAY and BOUNDARY =DELAUNAY. (ADINA)

DELETE-SLIVER [NO]Controls whether triangular �sliver� element faces are to be removed from the body boundarybefore generating volume elements. Such slivers can arise from small geometry features suchas fillets or rounds with small curvature, or by inappropriate edge subdivision data. Thepresence of such slivers can result in poor quality elements and a degradation of the meshingprocess. Enabling the prior removal of such slivers may result in a mesh which smoothestover small geometric features - if these features are important then the local subdivision datashould be refined about them. {YES/NO}

Note: This parameter is ignored if METHOD=DELAUNAY.

ANGLE-MIN [5.0]Provides an angle-tolerance for detecting boundary slivers. A triangular element face isconsidered a sliver if one of its internal angles is less than ANGLE-MIN (in degrees). {0.0≤ ANGLE-MIN ≤ 10.0} (The upper bound precludes unrealistic sliver definitions).


METHOD [DELAUNAY]Indicates the type of free-form meshing algorithm to be used. There are two availablemethods: advancing front and Delaunay. This parameter is only used whenMESHING=FREE-FORM. {ADVFRONT/DELAUNAY}

PATTERN [0]Selects the pattern used to subdivide the hexahedral body cells into tetrahedral elements(used when NODES=4, 10 or 11) - see figures - GVOLUME command. PATTERN=0 indi-cates that one of the patterns 1 through 5 is to be automatically selected so as to match thepatterns already used for adjacent volumes. If no pattern is suitable, for PATTERN=0, then awarning message is given and no elements are generated - in this case existing pattern usagemust be examined carefully to avoid pattern mismatches which would result in incompatiblemeshes. This parameter is only used when MESHING=MAPPED.

GBODY



body�s boundary. There are two available methods: advancing front and Delaunay.{ADVFRONT/DELAUNAY}

ADVFRONT distribution of elements, including their size, is governed by thesubdivision data assigned to the geometry bodies, e.g. viacommand SUBDIVIDE BODY, and by any auxiliary size-function.

GBODY

MESHING [FREE-FORM]Selects the type of mesh generation to be employed. {MAPPED/FREE-FORM}

MAPPED A rule based mapping of body edge subdivisions. Mappedmeshing is available only when the body is a Parasolid body andthe topology of the body is similar to a hexahedron, prism,pyramid, or tetrahedron.

FREE-FORM when NODES=4,10,11 free-form mesh generation based onadvancing front or Delaunay scheme creates tetrahedral elements.when NODES=8,27 free-form mesh generation based on advanc-ing front creates a mix of hexahedral and tetrahedral elements, withhexahedral elements occupying most of the volume space.

DEGENERATE [NO]Indicates how bodies with triangular faces are to be handled:

NO The triangular face is not given any special consideration for itsdegenerate edge.

YES The volume is treated as a degenerate hexahedral shape.

Note: This parameter is only used when MESHING=MAPPED.

BOUNDARY-METHOD [ADVFRONT]Indicates the type of free-form meshing algorithm to be used for triangular elements on

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Sec. 8.2 Mesh generationGBODY

DELAUNAY the distribution of elements, including their size, is governed bythe subdivision data assigned to the geometry bodies, e.g. viacommand SUBDIVIDE BODY and by the rules of smooth grada-tion. This means subdivisions on body edges may be overwrittento allow for smooth gradation of element sizes.

Note: This parameter is only used when MESHING=FREE-FORM.

DEG-EDGE [0]The degenerate edge of the body. This parameter is only used if the body is a prism body,MESHING=MAPPED, and DEGENERATE = YES.

GEO-ERROR [0.0]Relative geometric discretization error (see picture). If GEO-ERROR > 0.0 the distribution ofelements, including their size, is also governed by the curvature of the geometry body'sbounding edges and faces. (Only applicable if BOUNDARY-METHOD=DELAUNAY.)

SAMPLINGNumber of sampling points on edge Meaningful only if GEO-ERROR option turned on.For edges: number of sampling points = SAMPLINGFor faces: number of sampling points = SAMPLINGxSAMPLING

MIN-SIZEMinimum size allowed. Meaningful only if GEO-ERROR option turned on. It is important togive a meaningful value to MIN-SIZE to avoid overrefinement and, as a consequence, highCPU times for this command. (Only applicable if BOUNDARY-METHOD=DELAUNAY.)

NLAYER [1]When NODES = 4,10,11 and MESHING = FREE-FORM, specifies a minimum number ofelements across. By default, this option is off. To be turned on, NLAYER must be greater than1. If BOUNDARY-METHOD = DELAUNAY, this option also applies to any bounding face (ofthe body). If no NLTABLE is specified, NLAYER is used as the minimum number of elementsacross anywhere in body. When NLAYER = 2, the program will make sure that there are NOinterior mesh edges (segments) with both end vertices located on the boundary.

NLTABLE [0]Table which indicates the thin sections of body and/or body faces.

AUTO-GRADING [NO]Mesh densities required to satisfy smooth gradation. {NO/YES}If AUTO-GRADING=YES the distribution of elements, including their size, is also governed



by the requirement for smoothly graded mesh densities.

NCDOMAIN [0]Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN.Used only when NCOINCIDE=SELECTED or NCOINCIDE=BOUNDEXSEL.NCDOMAIN=0 indicates that no domain is to be used.

PYRAMIDS [NO]When NODES = 8,20,27 and MESHING = FREE-FORM, indicates whether pyramidelements should be used to transition from hexahedra to tetrahedra.If PYRAMIDS = ONLY, no hexahedra are created and pyramids are created for each boundaryquadrilateral cell. In order to guarantee (if possible) quadrilateral surface meshes on all facesof a body (as opposed to possible triangles among the quads), it is necessary to setPYRAMIDS=ONLY or YES. Note that when PYRAMIDS=YES, pyramids may be created notonly for boundary quad facets but also for interior quad facets (if those facets connectdirectly to tetrahedra), meaning that a possibly large number of pyramids may be created. Ifthe program fails to create all the pyramids that are needed, an error message will be displayedand the command will be cancelled. In this case, it is recommended to decrease the maximumdihedral angle allowed for quad facets (see DANGMAXC parameter), use PYRAMIDS=ONLYor change the mesh density. {NO/YES/ONLY}

DANGMAXB [80]Max angular deviation (from 90 degrees) for the angle at corners of hex side faces.

DANGMAXC [60/20]Max angular deviation (from 180 degrees) for the dihedral angle at diagonals of hex side facesDefault = 60 degrees (20 degrees if PYRAMIDS = YES).

DANGMAXD [80]Max angular deviation (from 90 degrees) for the dihedral angle at hex edges.

HEXALAYER [NO]When NODES = 8,20,27 and MESHING = FREE-FORM, specifies the number ofhexahedral element layers to be grown from body�s boundary faces (0 or 1).By default, thisnumber is set to 0. To be turned on, HEXALAYER must be equal to YES.

SIMULATE [NO]This parameter can be used (SIMULATE=YES) to see the effect on the body edge subdivi-sions of the GBODY command without actually meshing. It is relevant for the following cases:

- MESHING= FREE-FORM, and GEO-ERROR>0.0 or AUTO-GRADING=YES

GBODY



- MESHING=FREE-FORM and NODES=8,20,27 (brick elements)

EVEN [SUM]When GBODY is used with NODES=8,20,27, the command pre-processes the subdivisionsto make sure the all-quad mesher will produce all-quad meshes on the body faces. Thisparameter controls the number of subdivisions as follows. {SUM/LINK/ALL}

SUM For each body face, the program forces the sum of the subdivisions of the boundingedges to be even.

LINK The program forces any bounding edge of a linked face (FACELINK) to have aneven number of subdivisions. Note that the program also forces the sum of thesubdivisions of the bounding edges of non-linked faces to be even.

ALL The program forces any edge to have an even number of subdivisions.

MIDFACENODES [TRIA]Determines where the mid-face node on a quadrilateral facet (of an hexahedral or pyramidelement) should be placed. TRIA places the mid-face nodes mid-way on the diagonal of thetwo triangles making up the facet. QUAD places the mid-face node at the centroid of the fourfacet vertices. {TRIA/QUAD}

When elements with quad facets connect with tetrahedral elements, TRIA should be se-lected. Otherwise, QUAD should be selected. This only concerns free form meshing (higherorder mixed meshing) and quadrilateral facets on linked body faces.

bodyiLabel numbers of geometry bodies. The data line input allows for more than one body to bemeshed via a single GBODY command call.

deg-edgeiThe degenerate edge of bodyi . This data is only used if the body is a prism body,MESHING=MAPPED, and DEGENERATE=YES.

GBODY



NAMELabel number of geometry body.

NODES [8]The number of nodes per element. {8/20/27}

GHEXA NAME NODES NCOINCIDE NCDOMAIN NCTOLERANCE GROUPMIDNODES SIZE MINSIZE PROJECT SMOOTH DANGMAXAOPTIONA SHIFTX SHIFTY SHIFTZ MAX-REF

Generates brick element (hexahedron) dominant free-form meshes for a given body.

Note that this command- meshes the boundary as well as the inside of the given body- does not take into account edge subdivisions (see SIZE parameter)- does not update edge subdivisions- should only be used on near-primitive bodies

Any body connected (typically via a face) to a body meshed with GHEXA must be meshedwith GBODY in order to produce compatible meshes (at the interface). However, becauseGHEXA does not guarantee that nodes classified on the body's boundary are actually on thebody's boundary, it is not always possible to mesh connected bodies. This is due to the factthat GBODY (unlike GHEXA) always assumes that nodes classified on the body's boundaryare actually on the body's boundary.

Because GHEXA does not guarantee the creation of an all-quad surface mesh, it may benecessary to mesh connected bodies with tetrahedral elements only.

GHEXA

cover (cutaway)

gear (cutaway)

pulley



NCOINCIDE [BOUNDARIES]Selects the method of nodal coincidence checking.{ALL/BOUNDARIES/BOUNDEXSEL/GROUP/NO}



|XB - XA| ≤ NCTOLERANCE*XLEN|YB - YA| ≤ NCTOLERANCE*YLEN|ZB - ZA| ≤ NCTOLERANCE*ZLEN

where NCTOLERANCE is a parameter of this command and (XLEN,YLEN,ZLEN) are thelengths of the bounding box for the model before generation. If there is no bounding box,then XLEN,YLEN,ZLEN are taken as (1.0,1.0,1.0).



ALL all all

BOUNDARIES those on all boundaries allas defined by the inputboundary cell sets

BOUNDEXSEL those on boundaries allas defined by the inputboundary cell sets exceptthose in the domain specifiedby NCDOMAIN

GROUP those on boundaries those that are inas defined by the input the same elementboundary cell sets group

NO none none

GHEXA



NCDOMAIN [0]Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN.Used only when NCOINCIDE = BOUNDEXSEL. NCDOMAIN = 0 indicates that no domain isto be used.


GROUP [current element group]The label number of the element group in which the generated elements are created.

MIDNODES [STRAIGHT]Indicates whether the mid-side nodes for higher order elements are to be placed on thestraight line between the relevant vertex nodes (STRAIGHT), or on the underlying curvedgeometry using either mapping from parameter space to real space (CURVED), or projection(PROJECT). {CURVED/STRAIGHT/PROJECT}

SIZEDesired (uniform) mesh density for elements to be created. The generated element size willonly approximately be equal to SIZE.

MIN-SIZE [0.0]This parameter is obsolete.

PROJECT [YES]Mesh vertices on the body�s boundary are projected onto the corresponding body�s entities.It refers to the mesh obtained after subdividing the body�s polyhedral representation. It doesnot relate to MIDNODES. {YES/NO}

SMOOTH [NO]Mesh vertices on the body�s boundary are smoothed. It refers to the mesh obtained aftersubdividing the body�s polyhedral representation. {YES/NO}

DANGMAXA [20.0]Maximum angle allowed for face normals before and after collapsing of edges, consideringthe body�s polyhedral representation. The polyhedral representation is obtained by intersect-ing the body with a regular grid (with cell size equal to 2 x SIZE), which is then subdivided(once) to obtain the final mesh topology. {0.0 ≤ DANGMAXA ≤ 180.0}

OPTIONA [YES]Option to allow faces to share more than one edge during the collapsing of edges consider-ing the body�s polyhedral representation (see DANGMAXA). {YES/NO}

GHEXA



NO Allows faces to share more than one edge during collapsing of edges. MIN-SIZEwill more likely be respected, but the body may not be successfully meshed.

YES Does not allow faces to share more than one edge during collapsing of edges. MIN-SIZE is less likely to be respected, but successful meshing of the body is moreprobable.

SHIFTX [0.0]SHIFTY [0.0]SHIFTZ [0.0]Shifts along the X, Y and Z directions the bounding box used for the grid (whose intersectionwith the body gives the body's polyhedral representation).

MAX-REF [5]When problems are detected, the grid can be locally refined to resolve those problems. MAX-REF indicates how many times the program is allowed to subdivide the problem grid cells andrestart. If the problems can not be resolved, it is suggested to reduce SIZE (uniformly).

GHEXA



GADAPT NAME NODES NCOINCIDE NCTOLERANCE SUBSTRUCTUREGROUP MIDNODES NCDOMAIN COLLAPSED

bodyi facei

Functionality of this command is as follows:

In 3D, facei =0Takes a finite element mesh attached to a body or set of bodies, deletes it (keeping theboundary mesh intact), adapts the boundary mesh based on the provided mesh densities andremeshes the interior(s).

In 2D, facei ≠ 0Takes a finite element mesh attached to a body face or set of body faces, deletes it (keepingthe boundary mesh intact), adapts the boundary mesh based on the provided mesh densitiesand remeshes the interior(s).

Desired (new) mesh densities are provided to the program using the SIZE-LOCATIONScommand. The SIZE-LOCATIONS entries would typically correspond to node locations alongwith mesh densities. Note that they do not have to be as long as they are inside the geomet-ric entity given in the argument. If there are no SIZE-LOCATIONS entries, the quality of theboundary mesh is optimized without changing the mesh density.

NAMEThe label number of a solid geometry body for which elements are to be generated.





GADAPT


Sec. 8.2 Mesh generationGADAPT

where NCTOLERANCE is a parameter of this command and (XLEN,YLEN,ZLEN) are thelengths of the bounding box for the body before generation. If there is no bounding box,then XLEN,YLEN,ZLEN are taken as (1.0,1.0,1.0).



ALL all all


BOUNDEXSEL those on all vertices, alledges and faces of thegeometry body exceptfaces in the domainspecified by NCDOMAIN


NO none none

NCTOLERANCE [TOLERANCES GEOMETRIC]Tolerance used to determine nodal coincidence.then XLEN,YLEN,ZLEN are taken as(1.0,1.0,1.0).







COLLAPSED [NO]Selects whether tetrahedral THREEDSOLID, or FLUID3 elements are to be treated as col-lapsed hexahedral elements by ADINA. {NO/YES}

bodyiLabel numbers of geometry bodies. The data line input allows for more than one body to bemeshed via a single GADAPT command call.



Sec. 8.2 Mesh generationGBCELL

GBCELL SUBSTRUCTURE GROUP NODES NCOINCIDENCTOLERANCE NCDOMAIN COLLAPSED PYRAMIDS BCELL

bcelli

Creates 3D elements from boundary cells. Boundary cells are grouped into sets using theBCELL command. The boundary cells must form a water-tight domain andmust be oriented towards the domain. This command creates node sets and element face setscorresponding to each boundary cell set.

SUBSTRUCTURE [current substructure label number]Label number of the substructure in which the elements and nodes are created. The defaultvalue is defined by the last preceding SUBSTRUCTURE command.

GROUP [current element group number]The label number of the element group in which the generated elements are created. Thedefault value is determined by the last preceding SET EGROUP command. The group typemust be one of those listed above.

NODES [4]The number of nodes per element. Allowable values for each analysis program are

ADINA - 4, 8, 10, 11, 20, 27ADINA-T - 4, 8, 10, 11, 20, 27ADINA-F - 4, 8, 27

Note that if NODES=8, 20, or 27, boundary cells must be made up of all 4-node quadrilateralcells.

NCOINCIDE [BOUNDARIES]Selects the method of nodal coincidence checking. {ALL/BOUNDARIES/GROUP/NO}



|XB - XA| ≤ NCTOLERANCE * XLEN|YB - YA| ≤ NCTOLERANCE * YLEN|ZB - ZA| ≤ NCTOLERANCE * ZLEN

where NCTOLERANCE is a parameter of this command and (XLEN,YLEN,ZLEN) are thelengths of the bounding box for the model before generation. If there is no bounding box,then XLEN,YLEN,ZLEN are taken as (1.0,1.0,1.0).




NCOINCIDE Which nodes to consider Which nodes tofor coincidence check against

ALL all all

BOUNDARIES those on all boundaries allas defined by the inputboundary cell sets

GROUP those on boundaries those that are inas defined by the input the same elementboundary cell sets group

NO none none

NCTOLERANCE [value set by parameter COINCIDENCE ofcommand TOLERANCES GEOMETRIC]

Tolerance used to determine nodal coincidence.

NCDOMAIN [0]Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN.Used only when NCOINCIDE = SELECTED or NCOINCIDE = BOUNDEXSEL.NCDOMAIN = 0 indicates that no domain is to be used.

COLLAPSED [NO]Selects whether tetrahedral THREEDSOLID, or FLUID3 elements are to be treated as col-lapsed hexahedral elements by ADINA.

NO - Tetrahedral elements are not collapsed YES - Tetrahedral elements are treated as collapsed hexahedra

PYRAMIDS [NO]When NODES = 8,20,27, this parameter indicates whether pyramid elements should be usedto transition from hexahedral to tetrahedral elements. If PYRAMIDS = ONLY, no hexahedralelements are created and pyramid elements are created for each boundary quadrilateral cell.{NO/YES/ONLY}

GBCELL



BCELL [ALL]Indicates whether all boundary cells are used to create the 3-D mesh. {ALL/SELECT}

ALL All boundary cells are used.

SELECT Selected boundary cells as specified by bcelli are used.

bcelliLabel number of boundary cell. Boundary cells specified in the list are used to create the 3-Dmesh.

GBCELL



ELDELETE LINE NAME GROUP SUBSTRUCTURE NODE-DELETE

linei

ELDELETE SURFACE NAME GROUP SUBSTRUCTURE NODE-DELETE

surfacei

ELDELETE VOLUME NAME GROUP SUBSTRUCTURE NODE-DELETE

volumei

ELDELETE EDGE NAME GROUP SUBSTRUCTURE NODE-DELETE BODY

edgei

ELDELETE FACE NAME GROUP SUBSTRUCTURE NODE-DELETE BODY

facei

ELDELETE BODY NAME GROUP SUBSTRUCTURE NODE-DELETE

bodyi

ELDELETE deletes elements generated on a given geometry entity for a specific elementgroup. The nodes connected to the deleted elements may also be optionally deleted (pro-vided they are not connected to other elements or define other model features).

NAMELabel number of the geometry entity for which generated elements are to be deleted.

GROUP [current group number]Element group label number.

SUBSTRUCTURE [current substructure number]Substructure label number.

NODE-DELETE [YES]Node deletion option. {YES/NO}

BODY [currently active body]Label number of a solid geometry body. Used for edge/face references in ELDELETE EDGE/FACE

ELDELETE

linei /surfacei /volumei /edgei /facei /bodyiLine/Surface/Volume/Edge/Face/Body label number.


Sec. 8.2 Mesh generationCOPY-MESH-BODY

COPY-MESH-BODY BODY1 BODY2 SUBSTRUCTURE GROUP NCOINCIDENCDOMAIN NCTOLERANCE TRANSFORMATION

Copies a mesh from one body to another body via affine transformation.

BODY1Body whose mesh is to be copied. {>0}

BODY2Target body. {>0}












Chap. 8 Finite element representation COPY-MESH-BODY


ALL all all


BOUNDEXSEL those on all vertices, alledges and faces of thegeometry body exceptthose in the domain specifiedby NCDOMAIN


NO none none


NCTOLERANCE [1.0E-5]Tolerance used to determine nodal coincidence.

TRANSFORMATIONTransformation used to match BODY1 to BODY2. Using this transformation, all faces onBODY1 must match all faces on BODY2. {>0}









CSURFACE NAME NODES PATTERN NCOINCIDE NCTOLERANCESUBSTRUCTURE GROUP

Generates a set of contact segments on a contact-surface, see CONTACTSURFACE. Contactsegments are normally created by default from associated finite elements defined on thegeometry of the contact-surface. However, a target contact-surface which is rigid (or has acompletely known displacement), may be defined to consist of contact segments with noassociated finite elements.

The distribution of segments, including their size, is governed by the subdivision dataassigned to the geometry components of the contact-surface, e.g., via SUBDIVIDE LINE,SUBDIVIDE SURFACE.

NAMEThe label number of a contact-surface on which contact segments are to be generated.

NODES [2 (2-D); 4 (3-D)]1

[3 (2-D); 9 (3-D)]2

The number of nodes per contact segment.

The default value is indicated by the superscripts 1 or 2 as follows:

1. CONTACT-CONTROL CSTYPE=OLD2. CONTACT-CONTROL CSTYPE=NEW

The permitted values depend on whether the contact-surface is 2-D or 3-D:

2-D contact-surface � {2/3}.3-D contact-surface � {3/4/6/9}.

PATTERN [1]Selects the type of triangulation pattern used to further subdivide the quadrilateral surfacesubdivisions into triangular segments, only used when NODES = 3, i.e., for 3-D contactsegments. (See GSURFACE for PATTERN options).

NCOINCIDE [SURFACE]Controls nodal coincidence checking. If SURFACE is selected, nodal coincidence is carriedout, but comparison is made against only those nodes already generated on the contact-surface. {YES/NO/SURFACE}


SUBSTRUCTURE [current substructure number]Label number of the substructure in which the contact segments and nodes are generated.

GROUP [current contact group number]The label number of the contact group into which the contact segments are generated.

CSURFACE



CSDELETE LINE NAME GROUP CONTACTSURFACE NODE-DELETE

CSDELETE SURFACE NAME GROUP CONTACTSURFACE NODE-DELETE

CSDELETE EDGE NAME GROUP CONTACTSURFACE NODE-DELETEBODY

CSDELETE FACE NAME GROUP CONTACTSURFACE NODE-DELETEBODY

Deletes contact segments generated on a given geometry entity for a specified contactgroup. Nodes connected to the contact segments may be optionally deleted (provided theydo not connect to other elements or define other model features).

NAMELabel number of the geometry entity for which generated elements are to be deleted.

GROUP [current active contact group number]Contact group label number. Contact segments should have already been generated ongeometry entity "NAME".

CONTACTSURFACE [1]Contact surface label number.

NODE-DELETE [YES]Node deletion option:

NO No nodes are deleted as a result of this command

YES Nodes which are only connected to elements in the deleted set (i.e. thosegenerated on the line for the particular element group) will be deleted.

BODYThe body label number.

CSDELETE


Sec. 8.3 ElementsGLUEMESH

GLUEMESH NAME EXTENSION

stypei namei bodyi sidei

Glues two dissimilar meshes together. The mesh on each side (master or slave) may span overseveral sites.

NAMELabel number of GLUEMESH.

EXTENSION [0.01]

Extension for the master surface (as a ratio of element length). {0.00 < EXTENSION ≤0.25 }This extension is only applied to glueing of 3-D meshes.

stypeiType of site the gluing is applied to. Sites must be either all 2-D types (line, edge, element-edge) or all 3-D types (surface, face, element-face).{�LINE�/�SURFACE�/�EDGE�/�FACE�/�ELEMENT-EDGE�/�ELEMENT-FACE�}

For example,

GLUEMESH NAME=1�SURFACE� 1 0 SLAVE�SURFACE� 5 0 MASTER

nameiSite label number.

bodyiBody label number when stypei = EDGE or FACE.

sideiIndicates whether site is on the master or slave side. {SLAVE/MASTER}



TRUSS-POINTS

namei pointi materiali areai printi savei tbirthi tdeathi epsini

Defines axisymmetric truss elements at geometry points. Coincidence checking is used whengenerating nodes at the geometry points, with tolerance adjusted by the commandTOLERANCES GEOMETRIC. Note: The current element group must be of type TRUSS, withaxisymmetric subtype, for this command to be active.

nameiLabel number of an axisymmetric truss element.

pointiLabel number of the geometry point associated with the axisymmetric truss element.

materiali [0]Label number for the material to be used with element �namei�. A zero value indicates that theelement group default material is to be used.

areai [1.0]The cross-sectional area of the element.

printi [DEFAULT]Printing flag for the element. If DEFAULT is specified, printout is controlled by PRINTOUTPRINTDEFAULT. {YES/NO/DEFAULT}

savei [DEFAULT]Saving (to the porthole file) flag for the element. If DEFAULT is specified, saving is con-trolled by PORTHOLE SAVEDEFAULT. {YES/NO/DEFAULT}

tbirthi [0.0]Time of element birth.

tdeathi [0.0]Time of element death.

epsini [0.0]Element initial strain.

Auxiliary commands

LIST TRUSS-POINTS FIRST LASTDELETE TRUSS-POINTS FIRST LAST

TRUSS-POINTS


Sec. 8.3 Elements

SPRING POINTS

namei p1i dof1i p2i dof2i pseti printi savei axi ayi azi tbirthi tdeathi

Defines spring elements either between two degrees of freedom at distinct geometry points,or a �grounded� degree of freedom at a single geometry point. Coincidence checking is usedwhen generating nodes at the geometry points, with tolerance adjusted by the commandTOLERANCES GEOMETRIC.

Note: The current element group must be of type SPRING for this command to be active.

nameiLabel number of a spring element.

p1iLabel number of the first (or only) geometry point at one end of the spring element.

dof1iThe degree of freedom selected for the spring element at the first point �p1i�.

1 X translation.2 Y translation.3 Z translation.4 X rotation.5 Y rotation.6 Z rotation.

p2iLabel number of the second geometry point at the opposite end of the spring element frompoint �p1i�. Input of p2i = 0 implies that the degree of freedom �dof1i� at point �p1i� isconnected to ground.

dof2iThe degree of freedom for the spring element at point �p2i�. The choice of input values is thesame as for entry �dof1i�. If p2i = 0, then input for dof2i is ignored.

pseti [1]Label number of the spring property set for element springi. See PROPERTYSET.


SPRING POINTS




axi, ayi, azi [0.0]Global coordinate system components of the spring element direction, used if the springconnects two coincident points, or one point to ground. Note that this vector is only used fornonlinear spring elements.




Auxiliary commands

LIST SPRING POINTS FIRST LASTDELETE SPRING POINTS FIRST LAST

SPRING POINTS


Sec. 8.3 Elements

SPRING LINES

namei line1i dof1i line2i dof2i pseti printi savei axi ayi azi tbirthi tdeathi option

Defines �spring-lines�, i.e. a set of spring elements either between two degrees of freedomalong distinct geometry lines, or a �grounded� degree of freedom along a single geometryline.

nameiLabel number of a spring-line.

line1iLabel number of the first (or only) geometry line at one end of the spring-line.

dof1iThe degree of freedom selected for the spring elements along the first line �line1i�.

1 X translation.2 Y translation.3 Z translation.4 X rotation.5 Y rotation.6 Z rotation.

line2iLabel number of the second geometry line at the opposite end of the spring-line from �line1i�.Input of line2i = 0 implies that the degree of freedom �dof1i� at line �line1i� is connected toground.

dof2iThe degree of freedom selected for the spring elements along the second line �line2i�.If line2i = 0, then input for dof2i is ignored.

pseti [1]Label number of the spring property set for spring-line �namei�. See PROPERTYSET.



SPRING LINES



axi, ayi, azi [0.0]Global coordinate system components of the spring-line direction, used if the spring-lineconnects two coincident nodes, or one node to ground.




option [SAME]{SAME / REVERSE}When multiple nodes exist on the line1 and line2, this flags how the spring element betweennodes on each entity is defined.

SAME - A spring is constructed between nodes at the corresponding parametricorder on each line. Parametric order is in the increasing u-parameterdirection for lines.

REVERSE - A spring is constructed between nodes at the corresponding parametricorder on each line, but for line2 the parametric order is reversed.

Auxiliary commands

LIST SPRING LINES FIRST LASTDELETE SPRING LINES FIRST LAST

SPRING LINES


Sec. 8.3 Elements

REBAR-LINE NAME NCOINCIDE

linei

Defines a rebar using lines. The rebar defined is then referenced in the EGROUP TRUSScommand to model rebar elements.

NAME [(current highest rebar-line label number) + 1]Label number of the rebar-line to be defined. This label is referenced in the EGROUP TRUSScommand.

NCOINCIDE [NO]Coincidence checking is used to determine whether to place a new node at end point ofgeometry line. {NO/YES}

lineiList of geometry line label numbers used for defining the rebar.

Auxiliary commands

LIST REBAR-LINE FIRST LASTDELETE REBAR-LINE FIRST LAST

REBAR-LINE



TRUSS-LINE

name line1 line2 material area print save tbirth tdeath gapwidth intloc epsin option

Creates 2-node general truss elements between line1 and line2 or 1-node axisymmetric trusselements on line1 at the line subdivision locations.

nameLabel number of a truss-line

line1Line1 label number

line2Line2 label number. Specify line2=0 for axisymmetric truss element.

material [0]Material label number. A zero input value indicates that elements generated on the line willtake the default material for the host element group.

area [1.0]Cross-sectional area for each TRUSS element on the line.

print [DEFAULT]Printing flag for the element. If DEFAULT is specified, printout is controlled by PRINTOUTPRINTDEFAULT. {YES/NO/DEFAULT}

YES Print element results as requested by parameter RESULTS of the relevantEGROUP command.

NO No results are printed for TRUSS elements on the line.

DEFAULT Element printing is governed by parameter PRINTDEFAULT of thePRINTOUT command.

save [DEFAULT]Saving (to the porthole file) flag for the element. If DEFAULT is specified, saving is con-trolled by PORTHOLE SAVEDEFAULT. {YES/NO/DEFAULT}

YES Save, on the porthole file, element results as requested by parameterRESULTS of the relevant EGROUP command.

NO No saving of results for TRUSS elements on the line.

TRUSS-LINE


Sec. 8.3 Elements

DEFAULT Saving of element results is governed by parameter SAVEDEFAULT ofthe PORTHOLE command.

tbirth [0.0]The time of element birth.

tdeath [0.0]The time of element death.

Note: tbirth < tdeath, or tbirth = tdeath = 0.0

gapwidth [0.0]Gap width for each TRUSS element on the line.

intloc [NO]Option to print the location of the integration point. {YES/NO}

YES Print the element integration point (global) coordinates, in the undeformedconfiguration.

NO No printing of integration point data for TRUSS elements on the line.

epsin [0.0]Initial strain for each TRUSS element on the line.

option [SAME]{SAME/REVERSE}

When multiple nodes exist on the line1 and line2, this flags how the truss element betweennodes on each entity is defined.

SAME A truss is constructed between nodes at the corresponding parametricorder on each line. Parametric order is in the increasing u-parameterdirection for lines.

REVERSE A truss is constructed between nodes at the corresponding parametricorder on each line. For line2 the parametric order is reversed.

Auxiliary commands

LIST TRUSS-LINE FIRST LASTDELETE TRUSS-LINE FIRST LAST

TRUSS-LINE





Sec. 8.3 Elements

ELTHICKNESS

namei thick1i thick2i thick3i ... thick16i

Defines thickness for 3D shell elements and axisymmetric shell elements (EGROUP ISOBEAMSUBTYPE =AXISYMMETRIC).

nameiThe element label number, in the current element group.

thick1i [0.0]Thickness of shell element �i� at local node number 1.

thick2i [thick1i]

Thickness of shell element �i� at local node number 2.

.

.

.

thick16i [thick1i]

Thickness of shell element �i� at local node number 16.

Note: Thickness is measured in the direction of the director/normal vector at the node.

Note: The thicknesses �thickni� are defined for midsurface nodes, ignoring top/bottomnodes of transition elements.

Auxiliary commands

LIST ELTHICKNESS FIRST LASTDELETE ELTHICKNESS FIRST LAST

ELTHICKNESS

Chapter 9

Direct finite element data input


Sec. 9.1 Nodal data

COORDINATES NODE SYSTEM

(ENTRIES NAME X Y Z SYSTEM) (SYSTEM = global Cartesian (0))(ENTRIES NAME XL YL ZL SYSTEM) (SYSTEM = Cartesian)(ENTRIES NAME R THETA XL SYSTEM) (SYSTEM = cylindrical)(ENTRIES NAME R THETA PHI SYSTEM) (SYSTEM = spherical)

ni xi yi zi sysi

Defines coordinates for current substructure nodes. The coordinates given refer to the localsystem specified by parameter SYSTEM.

SYSTEM [currently active system]Label number of the required local coordinate system. This specifies the coordinate systemto which any appended data line coordinates refer and determines which column headingnames are allowed by any ENTRIES data line.

ENTRIESDefines, as column headings, the input for the subsequent tabular entries. The headingnames depend on the type of local coordinate system specified by SYSTEM.

Note: Less than five entry column headings may be given e.g., to specify nodes in acoordinate plane, but the column heading NAME must always be specified.

niLabel number for the desired current substructure node, input under the column headingNAME.

xi [0.0]yi [0.0]zi [0.0]Coordinate values in local coordinate system �sysi�.

sysi [SYSTEM]Local coordinate system label number. Note �sysi� defaults to the system specified bySYSTEM, which in turn defaults to the currently active coordinate system.

Auxiliary commands

LIST COORDINATES NODE FIRST LAST SYSTEM GLOBALDELETE COORDINATES NODE FIRST LASTIf GLOBAL = YES the coordinates are listed in terms of the global Cartesian system.

COORDINATES NODE


Chap. 9 Direct finite element data input

SKEWSYSTEMS NODES

ni node1i node2i node3i

Defines �skew� Cartesian coordinate systems in terms of nodes. Skew systems can bereferenced via DOF-SYSTEM to indicate the local orientation of nodal degrees of freedom.

niLabel number for the skew system to be defined.

node1inode2inode3iNode label numbers. The vector from node1i to node2i defines the direction of the local X-axisof the skew system. The vector from node1i to node3i is taken to lie in the local XY-plane ofthe skew system. Note that the three nodes must not be collinear.

Auxiliary commands


SKEWSYSTEM NODES


Sec. 9.1 Nodal data

DOF-SYSTEM NODES SUBSTRUCTURE

nodei skewsystemi

Assigns skew coordinate systems to the degrees of freedom associated with a set of nodes inthe current substructure.

SUBSTRUCTURE [current substructure]Label number of the substructure for the nodes referenced in the accompanying data lines.

nodeiLabel number of a node in the current substructure given by SUBSTRUCTURE.

skewsystemiLabel number of a skew coordinate system, as defined by SKEWSYSTEM. Settingskewsystemi = 0 assigns the global Cartesian system to the nodal degrees of freedom.

Auxiliary commands

LIST DOF-SYSTEM NODES FIRST LAST SUBSTRUCTUREDELETE DOF-SYSTEM NODES FIRST LAST SUBSTRUCTURE

DOF-SYSTEM NODES



MASSES NODES

nodei mass1i mass2i mass3i mass4i mass5i mass6i

Assigns concentrated masses to a set of nodes in the current substructure.

nodeiLabel number of a node.

mass1i [0.0]The mass assigned to nodei for the x-translational degree of freedom (global or skew).

mass2i [0.0]The mass assigned to nodei for the y-translational degree of freedom (global or skew).

mass3i [0.0]The mass assigned to nodei for the z-translational degree of freedom (global or skew).

mass4i [0.0]The mass moment of inertia assigned to nodei for the x-rotational degree of freedom (global orskew).

mass5i [0.0]The massmoment of inertia assigned to nodei for the y-rotational degree of freedom (global orskew).

mass6i [0.0]The mass moment of inertia assigned to nodei for the z-rotational degree of freedom (global orskew).

Auxiliary commands

LIST MASSES NODES FIRST LASTDELETE MASSES NODES FIRST LAST

MASSES NODES


Sec. 9.1 Nodal data

DAMPERS NODES

nodei damp1i damp2i damp3i damp4i damp5i damp6i

Assigns concentrated dampers to a set of nodes in the current substructure.


damp1i [0.0]The damper assigned to nodei for the x-translational degree of freedom (global or skew).

damp2i [0.0]The damper assigned to nodei for the y-translational degree of freedom (global or skew).

damp3i [0.0]The damper assigned to nodei for the z-translational degree of freedom (global or skew).

damp4i [0.0]The rotational damper assigned to nodei for the x-rotational degree of freedom (global orskew).

damp5i [0.0]The rotational damper assigned to nodei for the y-rotational degree of freedom (global orskew).

damp6i [0.0]The rotational damper assigned to nodei for the z-rotational degree of freedom (global orskew).

Auxiliary commands

LIST DAMPERS NODES FIRST LASTDELETE DAMPERS NODES FIRST LAST

DAMPERS NODES



SHELLNODESDOF NODES SUBSTRUCTURE

nodei nsdofi ndirvi

Specifies the number of degrees of freedom and the director vector number, if applicable, formidsurface shell element nodes. This specification overrides the global default set byMASTER SHELLNDOF.

SUBSTRUCTURE [current substructure]The substructure for each node specified in this command.

nodeiThe node number.

nsdofi [MASTER SHELLNDOF]Number of degrees of freedom for nodei, if the node is a shell node.

FIVE Shell midsurface rotational degrees of freedom are used.

SIX Global or skew degrees of freedom are used.

AUTOMATIC The program chooses the number of degrees of freedom to beused based on certain modeling considerations. See Theory andModeling Guide.

ndirviNumber of a director vector defined by the SHELLDIRECTORVECTOR.

Auxiliary commands

LIST SHELLNODESDOF NODES FIRST LAST SUBSTRUCTUREDELETE SHELLNODESDOF NODES FIRST LAST

SHELLNODESDOF NODES


Sec. 9.1 Nodal data

SHELLDIRECTORVECTOR OPTION SUBSTRUCTURE

ni vxi vyi vzi (OPTION = COMPONENTS)

or

ni phii thetai (OPTION = EULERANGLES)

Defines director vectors that can be applied to shell element nodes in the model via commandSHELLNODESDOF. Director vectors are used in shell analysis to define the shell directorvectors for those nodes with five (5) degrees of freedom. It is not necessary to specifydirector vectors for these nodes, however, as the program will automatically compute directorvectors for those nodes for which you do not assign director vectors.

OPTION [COMPONENTS]

COMPONENTS Director vectors are input in the form of vector components inthe global coordinate system. Input vx, vy and vz in the data lines.

EULERANGLES Director vectors are input in the form of Euler rotation angles inthe global coordinate system. Input phi and theta in the data lines.

SUBSTRUCTURE [current substructure]The substructure for the director vector specified by this command.

niDirector vector number.

vxi [0.0]vyi [0.0]vzi [0.0]Components of the director vector. This vector need not be normalized.

phii [0.0]thetai [0.0]Euler rotation angles measured in degrees.

Auxiliary commands

LIST SHELLDIRECTORVECTOR FIRST LAST OPTION SUBSTRUCTUREDELETE SHELLDIRECTORVECTOR FIRST LAST OPTION SUBSTRUCTURE

SHELLDIRECTORVECTOR



NODESET NAME ALL-EXT OPTION GROUP ZONE ELSET TARGET ANGLE

nodei substructurei reusei (OPTION = NODE)

namei (OPTION = MERGE/SUBTRACT/INTERSECT)

namei bodyi (OPTION = LINE-EDGE/SURFACE-FACE)

Defines a collection of nodes by label number. The NODESET may be referenced by othercommands such as CONSTRAINT, RIGIDLINK, BEAMSET, and SPRINGSET.

NAME [(current highest nodeset label number) + 1]Label number of NODESET.

ALL-EXT [NO]Indicates whether this node set includes all nodes on the external boundary of the model. IfALL-EXT=YES, then "nodei" is a list of nodes which will be excluded in this node set. Notethat parameter ALL-EXT is used only for OPTION = NODE. {YES/NO}

OPTION [NODE]The option to define the NODESET. {NODE/GROUP/ZONE/ELEDGESET/ELFACESET/MERGE/SUBTRACT/INTERSECT/LINE-EDGE/SURFACE-FACE/CHAIN}

NODE NODESET is defined from table input.

GROUP NODESET is defined from given Element Group.

ZONE NODESET is defined from given Zone name. Note that all nodes areadded only from zone entities that contain element information.

ELEDGESET NODESET is defined from given element edge set in parameterELSET.

ELFACESET NODESET is defined from given element face set in parameterELSET.

MERGE NODESET is defined by merging nodesets specified in the table.

SUBTRACT NODESET is defined by subtracting from the TARGET nodeset thenodesets specified in the table.

NODESET


Sec. 9.1 Nodal data

INTERSECT NODESET is defined as the intersection of all nodesets specified inthe table.

LINE-EDGE NODESET is defined from nodes currently on geometry lines andedges.

SURFACE-FACE NODESET is defined from nodes currently on geometry surfaces andfaces.

CHAIN NODESET is defined according to the normal direction of the firstelement face in the table. All element faces of continuous normaldirection with the same element type will be selected. All nodes onthese element faces will be filled in the table.

GROUP [0]If GROUP > 0 all element nodes of this group will be included in this NODESET. Used onlyfor OPTION = GROUP.

ZONEZone name. Used only for OPTION = ZONE.

ELSET [0]Label number of element edge set if OPTION = ELEDGESET.Label number of elfaceset if OPTION = ELFACESET.Ignored for other values of OPTION.

TARGET [0]Label number of target nodeset for OPTION = SUBTRACT.

ANGLE [0.0]Angle (in degrees) used to determine all continuous normal directions.

nodeiNode label number. Used only for OPTION = NODE.

substructurei [current substructure]Substructure label number for nodei. Used only for OPTION = NODE.

reusei [current reuse]Reuse label number for nodei. Used only for OPTION = NODE.

NODESET



nameiLabel number of element node set. Used only for OPTION = MERGE/SUBTRACT/INTER-SECT/LINE-EDGE/SURFACE-FACE.

bodyiLabel number of element node set. Used only for OPTION = LINE-EDGE/SURFACE-FACE.

Auxiliary commands

LIST NODESET FIRST LASTDELETE NODESET FIRST LAST


Sec. 9.1 Nodal data

RIGIDNODES SHELL

nodei

Specifies shell midsurface nodes for which the rotation normal to the shell is constrained tothe perpendicular translations of neighboring shell midsurface nodes. This effectivelyremoves the usual singularity associated with the lack of stiffness for the shell normalrotation degree of freedom.

This condition may be used, for example, in conjunction with beam or spring elements toconnect two or more offset shell surfaces.

Note that any node specified cannot have 5 or 6 degrees-of-freedom explicitly assigned(either directly or to any attached geometry); i.e. they must have an �automatic� number ofdegrees-of-freedom assignment. Thereafter, if the automatic calculation otherwise results in 5degrees-of-freedom, the actual number of degree-of-freedom will be output as 6 and therequired constraint will be applied.

nodeiThe label number of a shell midsurface node. The node must belong to the main structure (notany substructure).

Auxiliary commands

LIST RIGIDNODES SHELL

RIGIDNODES SHELL



AXES-NODES NAME NODE1 NODE2 NODE3

Defines an �axes-system� via three model nodes. Axes-systems can be referenced byelement data commands (e.g., EDATA) to indicate the local orientation of the orthotropicmaterial properties and/or initial strain.

NAMELabel number for the desired axes-system. This is numbered independently for each elementgroup.

NODE1Label number of the first node defining the axes-system.

NODE2Label number of the second node defining the axes-system.

NODE3Label number of the third node defining the axes-system.

Note: The local x-direction of the axes-system is determined by the vector from NODE1to NODE2. The local z-direction of the axes-system is determined as the normalto the plane defined by the three nodes NODE1, NODE2, and NODE3. The localy-direction of the axes-system is then given by the right-hand rule.

Auxiliary commands

LIST AXES-NODES FIRST LAST SUBSTRUCTURE GROUPDELETE AXES-NODES FIRST LAST SUBSTRUCTURE GROUP

AXES-NODES


Sec. 9.2 Element data

AXES-INITIALSTRAIN NAME LINE ALFA GROUP

elei

This command defines sets of axes to be used with the definition of the directions of theinitial strains in each element. Elements are input in the data lines. A geometry line labeledLINE and an angle ALFA (in degrees) are used to define the initial strain axes orientations.The elements can belong to the current element group or an element group input through theGROUP parameter.Axes initial strain system can be referenced by commands INITIAL STRAINS and INITIALSGRADIENTS to specify initial strains or initial strain gradients.This command is applicable to 2D, 3D, plate and shell elements.

NAME [(current highest defined label) + 1]Label number for the desired axes-initial strain system to apply to the specified elements..

LINELabel number of the defined geometry line. The geometry line must either be a straight line oran arc line.

ALFA [0.0]An angle (in degrees) is used together with the geometry line.

GROUP [current element group]Element group number which this axes-initial strain system is applied to.

eleiElement number which this axes-initial strain system is applied to.

Auxiliary commands

LIST AXES-INITIALSTRAIN FIRST LASTDELETE AXES-INITIALSTRAIN FIRST LAST

AXES-INITIALSTRAIN



AXES-ORTHOTROPIC NAME LINE ALFA GROUP

elei

This command defines sets of principal material axes orientations for the elements used withthe orthotropic material model. Elements are input in the data input lines. A geometry linelabeled LINE and an angle ALFA (in degrees) are used to define the principal material axesorientations. The elements can belong to the current element group or an element group inputthrough the GROUP parameter.This command is applicable for 2D, plate and shell elements.

NAME [(highest axes-orthotropic system) + 1]Label number for the desired axes-orthotropic system.

LINELabel number of the defined geometry line. The geometry line must be a straight line or an arcline.

ALFA [0.0]An angle (in degrees) is used together with the geometry line.

GROUP [current element group]Element group number which this axes-orthotropic system is applied to.

eleiElement number which this axes-orthotropic system is applied to.

Auxiliary commands

LIST AXES-ORTHOTROPIC FIRST LASTDELETE AXES-ORTHOTROPIC FIRST LAST

AXES-ORTHOTROPIC


Sec. 9.2 Element dataELEDGESET

ELEDGESET NAME ALL-EXT OPTION TARGET

edgei eli groupi (OPTION = ELEDGE)


namei bodyi (OPTION = LINE-EDGE)

Defines an element edge set containing edges of 2-D elements. An element edge set can beused for load application (APPLY-LOAD command) such as pressure, normal traction andheat flux. It can also be used in the definition of a 2-D contact surface (see commandCONTACT-ELEMSET ).

NAME [(current highest eledgeset label number) + 1]Label number of the element edge set.

ALL-EXT [NO]Indicates whether this element edge set includes all external boundary element edges. IfALL-EXT=YES, then edgei is a list of element edges which will be excluded in this elementedge set. Note that parameter ALL-EXT is used only for OPTION = ELEDGE. {YES/NO}

OPTION [ELEDGE]The option to define the element edge set.{ELEDGE/LINE-EDGE/MERGE/SUBTRACT/INTERSECT}

ELEDGE Define an element edge set by specifying element edges in the table

LINE-EDGE Define an element edge set from geometry lines or edges

MERGE Merge element edge sets specified in the table

SUBTRACT Subtract from the TARGET element edge set the element edge setsspecified in the table

INTERSECT Obtain the intersection of all element edge sets specified in the table

TARGET [0]Label number of target element face set for OPTION = SUBTRACT .

edgeiEdge number of the element. Used only for OPTION = ELEDGE.



eliLabel number of the element. Used only for OPTION = ELEDGE.

groupiLabel number of the element group. Used only for OPTION = ELEDGE.

nameiLabel number of element edge set. Used only for OPTION = MERGE/SUBTRACT/INTER-SECT (without bodyi) or OPTION = LINE-EDGE (with bodyi).

bodyiLabel number of body; if bodyi = 0 , this means that the geometry is a line. Used only forOPTION = LINE-EDGE.

Auxiliary commands

LIST ELEDGESET FIRST LASTDELETE ELEDGESET FIRST LAST

ELEDGESET



ELEMENTSET NAME GROUP

eli groupi

Defines an element set containing elements specified in the parameter GROUP and in the tableentries.

Element sets containing beam or truss elements can be referenced in the SWEEP and RE-VOLVE commands to generate reinforcement beam or truss elements.

Element sets containing 3-D solid, 2-D solid, and shell elements can be referenced in the SET-AXES-MATERIAL and SET-AXES-STRAIN commands to specify the orientation oforthotropic material properties or initial strains for the elements.

NAMELabel number of ELEMENTSET.

GROUP [0]Specifies an element group to be included in this element set. If GROUP > 0 is specified, allelements in the group will be included in this element set.

eliLabel number of the element.

groupiLabel number of the element group for element eli.

Auxiliary commands

LIST ELEMENTSET FIRST LASTDELETE ELEMENTSET FIRST LAST

Example

ELEMENTSET NAME=2 GROUP=53 2TO10 2@

The above command will create an element set 2 which contains all elements in element group5 and elements 3 to 10 in element group 2.

ELEMENTSET



ELFACESET NAME ALL-EXT OPTION GROUP ZONE ANGLE TARGET

facei eli groupi (OPTION = ELFACE)


namei bodyi (OPTION = SURFACE-FACE)

Defines an element face set containing faces of 3-D and shell elements. An element face setcan be used for load application ( APPLY-LOAD command) such as pressure, normal tractionand heat flux. It can also be used in the definition of a 3-D contact surface (see commandCONTACT-ELEMSET ).

NAME [(current highest elfaceset label number + 1)]Label number of the element face set.

ALL-EXT [NO]Indicates whether this element face set includes all external boundary element faces. If ALL-EXT=YES, then facei is a list of element faces which will be excluded in this element face set.Note that parameter ALL-EXT is used only for OPTION = ELFACE.{YES/NO}

OPTION [ELFACE]The option to define the ELFACESET. {ELFACE/GROUP/ZONE-3D/ZONE-SHELL/CHAIN/SURFACE-FACE/MERGE/SUBTRACT/INTERSECT}

ELFACE ELFACESET is defined from table input.

GROUP ELFACESET is defined from given Element Group.

ZONE-3D ELFACESET is defined from given ZONE name and only external 3Delement faces are selected.

ZONE-SHELL ELFACESET is defined from given ZONE name and only SHELLelement faces are selected.

CHAIN ELFACESET is defined according to the normal direction of firstelement face in the table. All element faces of continuous normaldirection with same element type will be filled in table.

SURFACE-FACE ELFACESET is defined from geometry sufaces or faces.

MERGE ELFACESET is defined by merging element face sets specified in thetable.

ELFACESET



SUBTRACT ELFACESET is defined by subtracting from the TARGET element faceset the element face sets specified in the table.

INTERSECT ELFACESET defined by obtaining the intersection of all element facesets specified in the table.

GROUP [0]If GROUP > 0 and the GROUP is a SHELL element group, all element faces of thisgroup will be included in this ELFACESET. Used only for OPTION = GROUP.

ZONEZone name. Used only for OPTION = ZONE-3D/ZONE-SHELL.

ANGLE [0.0]Angle (in degrees) used to determine all continuous normal directions.{0.0 ≤ ANGLE ≤ 90.0}

TARGET [0]Label number of target element face set for OPTION = SUBTRACT .

faceiFace number of the element. Used only for OPTION = ELFACE.

eliLabel number of the element. Used only for OPTION = ELFACE.

groupiLabel number of the element group. Used only for OPTION = ELFACE.

nameiLabel number of element face set. Used only for OPTION = MERGE/SUBTRACT/INTER-SECT (without bodyi) or OPTION = SURFACE-FACE (with bodyi).

bodyiLabel number of body; if bodyi = 0 , this means that the geometry is a surface. Used only forOPTION = SURFACE-FACE.

Auxiliary commands

LIST ELFACESET FIRST LASTDELETE ELFACESET FIRST LAST

ELFACESET






ENODES SUBSTRUCTURE GROUP NNODES

(ENTRIES EL AUX N1 N2 ... NK)

eli auxi n1i n2i n3i n4i ... nki

ENODES defines element nodal connectivity for the substructure and element group speci-fied. The defaults are the currently active substructure and element group. NNODES is onlyused for specifying maximum number of nodes allowed for ADINA GENERAL elements

SUBSTRUCTURE [currently active substructure]Label number for the substructure to which subsequent nodal and element data refer.

GROUP [currently active element group]Element group label number.

NNODES [32]Maximum number of nodes allowed for ADINA GENERAL elements. (command line inputonly).

ENTRIESDefines, as column headings, the input for the subsequent tabular entries. Specifies theelement nodes for which the global node numbers shall be input. The column heading ELmust always be specified first, and the essential and optional nodal headings for each type ofelement are:

eli n1

i ... n4

iTRUSS elements.

eli n1

i ... n9

iTWODSOLID elements.

eli n1

i ... n9

iFLUID2 elements.

eli n1

i ... n27

iTHREEDSOLID elements.

eli n1

i ... n27

iFLUID3 elements.

eli aux

i n1

i n2

iBEAM elements.

eli aux

i n1

i ... n4

iISOBEAM elements.

eli aux

i n1

i ... n4

iPIPE elements.

eli n1

i ... n3

iPLATE elements.

eli n1

i ... n32

iSHELL elements.

eli n1

i ... n32

iGENERAL elements.

eli n1

i id1

i n2

i id2

iSPRING elements.

eliElement number within the current substructure and element group.

ENODES



auxin1i , n2i , n3i ,... , nki

The global node numbers defining the element in the order given by ENTRIES.

Note: Node auxi is required by the BEAM, ISOBEAM and PIPE elements.

Note: The spring element is defined by n1i, id1i, n2i and id2i, where id1i and id2i are theglobal degrees of freedom. Parameter id2i is ignored when n2i=0

Node numbering

The node numbering convention and other pertinent information for the truss, beam,isobeam, pipe, plate and general elements are described in the corresponding sections in theTheory and Modeling Guide, Volume I: ADINA, as follows:

Element SectionTRUSS 2.1BEAM 2.4ISOBEAM 2.5PIPE 2.8PLATE 2.6GENERAL 2.9.1

The node numbering for the TWODSOLID/FLUID2, THREEDSOLID/FLUID3, SHELL andSPRING elements is explained in the following sections.

1. TWODSOLID/FLUID2 elements

The TWODSOLID/FLUID2 elements are triangles and quadrilaterals. Their nodes arenumbered as shown in Fig. ENODES-1.

2. THREEDSOLID/FLUID3 elements

The THREEDSOLID/FLUID3 elements fall into two categories based on node numbering:

(a) the brick elements (4-, 8-, 20-, 21- and 27-node) and degenerate elements formed bycollapsing the 8-, 20- and 27-node brick elements, and

(b) the tetrahedral elements (4-, 10- and 11-node).

Fig. ENODES-2 shows the node numbering convention of the 27-node brick element. Notethat node 21 is in the center of the element. The elements that are based on the 27-node brickmust be numbered according to the convention shown in the figure, e.g., a node number thatis reserved for a vertex cannot be used to number a node on an edge.

Fig. ENODES-3 shows the node numbering for elements based on the 27-node brick.

ENODES



• The 21-, 20-, and 8-node bricks (Fig. ENODES-3(f), (d) and (a) respectively) result whenthe nodes on the element faces, the node at the element center, and the nodes on theelement edges are progressively left out.

• The 6-node prism (Fig. ENODES-3(b)) and its corresponding numbering are obtained bycollapsing one face (1-4-8-5) of the 8-node brick.

• The 15-node prism (Fig. ENODES-3(c)) and its corresponding numbering are obtained bycollapsing one face (1-4-8-5) of the 20-node brick.

• The 13-node pyramid (Fig. ENODES-3(e)) and its corresponding numbering are obtainedfrom the 20-node brick by collapsing one face (1-2-3-4), and then collapsing the edge soformed into the apex of the pyramid.

• The 14-node pyramid (Fig. ENODES-3(g)) and its corresponding numbering are obtainedfrom the 27-node brick by collapsing one face (1-2-3-4), and then collapsing the edge soformed into the apex of the pyramid; nodes 21 � 26 are not used, leaving only the lastnode (27) on the base of the pyramid.

The 4-, 10- and 11-node tetrahedral elements are numbered as shown in Fig. ENODES-4.

3. SHELL elements

Fig. ENODES-5 shows the node numbering conventions for SHELL elements.

• In midsurface nodes representation (Fig. ENODES-5(a)), node numbers 13 � 16 arealways reserved for element interior nodes. Therefore, in the case of a 9-node shellelement defined using midsurface nodes, the nodes defined are the 1 � 4 at the vertices, 5� 8 on the edges and 13 in the center of the element. The center node is defined bynodes 13 and 29 if the 9-node shell element is defined using top-bottom nodes represen-tation.

• In top-bottom nodes representation (Fig. ENODES-5(b)), the element interior nodes arenumbered 13 � 16 on the top surface and 29 � 32 on the bottom surface. Each top surfacenode has a dual bottom surface node. Nodes 1 � 16 are on the top surface, or on themiddle surface if the dual node on the bottom surface is not present. Nodes 17 � 32 areon the bottom surface.

• Triangular shell elements are obtained by degeneration of these quadrilateral shellelements, that is, by assigning nodes 1 and 4 (also nodes 17 and 20 if applicable) to thesame global number. Note that for triangular shell elements, nodes 8 and 12 (also nodes24 and 28 if applicable) are not used. Further, interior nodes are not allowed. Someexamples of triangular shell elements using midsurface node representation are shown inFig. ENODES-6.

4. Nonlinear SPRING elements

For nonlinear springs, the stiffness of the spring can change as functions of the displacement

ENODES



between 2 nodes (or node to ground). The 2 categories of nonlinear spring are

-- material nonlinear only (MNO) spring (specify NONLINEAR=MNO in EGROUPSPRING command)

-- geometric nonlinear spring (specify NONLINEAR=GEOM in EGROUP SPRING com-mand)

Option 1 (MNO):

The 2 nodes of the spring are initially coincident. The spring action is assumed to act alwaysin the global directions regardless of the current relative positions of the 2 nodes. FigureENODES-7 illustrates the use, where n1 and n2 have moved apart but the spring stiffnesscontinues to act into the global directions.

To use this spring option, specify

ENODESel n1 id1 n2

where id1 = 1, 2 and 3 indicates global X, Y and Z directions respectively. id1 = 4, 5, and 6for torsional springs.

If n2 = 0, then a grounded spring is defined.

Option 2 (MNO):

The 2 nodes of the spring are initially coincident. The spring action is assumed to act alwaysin an arbitrary direction specified by the user. Figure ENODES-8 illustrates the use of thisoption.

To use this spring option, the EDATA command is used to specify the spring action direction.

ENODESel n1 id1 n2 id2

EDATAel ax ay az

ax, ay, az are vector components in the global X, Y, Z directions.

If n2 = 0, then a grounded spring is defined.

For translational spring, specify id1 = 0 and id2 = 0. For torsional spring, specify id1 = 0 andid2 = 1.

ENODES



Option 3 (MNO):

The 2 nodes of the spring are initially not coincident. The spring action is assumed to actalways in the direction connecting the original positions of the two nodes. Figure ENODES-9illustrates the use of this option.


ENODESel n1 id1 n2

id1 = 1 for translational spring and id1 = 4 for torsional spring. If OPTION=TRANSVERSE isspecified in EGROUP SPRING command, then the spring action acts in the transversedirections to n1 to n2 direction.

Option 4 (Geometric Nonlinear):

The 2 nodes of the spring are initially not coincident. The spring action is assumed to act inthe direction connecting the current positions of the two nodes. Hence, the spring directionchanges as the position of the two nodes changes. Figure ENODES-10 illustrates the use ofthis option.


ENODESel n1 id1 n2

id1 = 1 for translational spring and id1 = 4 for torsional spring.

Examples of input for options 1 to 3 are given in the following tables. Table ENODES-1 coversthe translational spring elements, and the Table ENODES-2 covers the torsional springelements.

Auxiliary commands

LIST ENODES FIRST LAST SUBSTRUCTURE GROUPDELETE ENODES FIRST LAST SUBSTRUCTURE GROUP

NODE-DELETE

NODE-DELETE {YES/NO} allows for the deletion of unattached nodes along with theelement deletion. The default is YES.

ENODES



��

�

��

��

�

�

��

�

��

(b) 4-, 8- & 9-node quadrilaterals

�

�

�

�

�

��

��

�

(a) 3-, 6- & 7-node triangles

Fig. ENODES-1: Node numbering of 2-D elements

�

� ��

��

�

�

�

��1 2

3

12

3 4

12

3

4

56

1

2

3

4

56 7

12

34

12

3 4

8

5

6

7

8

5

6

7

9

�

�

�

�

�

��

�

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�

��

�

�

�

�

�

�

�

�

�

�

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�

��

4

8

Figure ENODES-2: Node numbering convention for

the 27-node brick element

6

13

5

16

15

714

17

9

1 18

2

103

20

11

19

12

21

22

23

24

25

26

27

Nodes 1 to 8 are at element vertices.

Nodes 9 to 20 are on element edges.

Node 21 is at the center of the element.

Nodes 22 to 27 are on the element faces.

10

1819

14

15 13

5, 8, 16 17, 20, 25

911

23

67

1, 4, 12

�

�

�

�

��

��

�

�

��

�

�

�26

�2221�

27�

�

24

23�

ENODES



(e) 20-node brick

(b) 8-node brick

Figure ENODES-3: Node numbering of the elements derived from the 27-node brick

�

�

�

�

�

�

�

�

�

�

4

8

6

13

16

157 14

17

91

18

5

103

20

11

19

12

21

� �

� �

� �

�

2

�

�

�

�

�

�

�

�

�

4

8

6

13

16

157 14

17

91

18

5

103

20

11

19

12� �

� �

� �

�

2

4

8

67

1

5

3

� �

� �

� �

�

2

(g) 21-node brick

1,2,3,4,9,10,11,12

19 18

20

17

1415

7

8

16

13

5

6�

�

�

�

�

�

�

�

�

�

�

�

�

(f) 13-node pyramid

1,2,3,4,9,10,11,12

19 18

20

17

1415

7

8

16

13

5

6�

�

�

�

�

�

�

�

�

�

�

�

�

(h) 14-node pyramid

�27

23

67

5, 8

1, 4

�

�

�

�

� �

(c) 5-node pyramid

10

1819

14

15 13

5, 8, 16

17, 20

911

(d) 15-node prism

23

67

1, 4, 12

�

�

�

�

� �

��

�

�

�

��

�

�

�

� �

�

�

�

��

�

(a) 6-node prism

1,2,3,4

7

8

5

6

�

�

�

�

�

ENODES



1

17

1

5

21

5

9

25

9

2

18

2

6

22

6

10

26

10

3

19

3

7

23

7

11

27

11

4

20

4

8

24

8

12

28

12

15

31

15

16

32

16

13

29

13

14

30

14

a) Midsurface nodes

b) Top-bottom nodes

Figure ENODES-5: Node numbering conventions for the shell element

For the 9-node shell, themidsurface center nodeis local node number 13.

For the 9-node shell, thetop-bottom center nodesare local node numbers13 and 29.

�

�

�

�

�

��

�

�

��

Figure ENODES-4: Node numbering of tetrahedral elements

�

�

�

��

�

�

��

�

� �

1 2

3

4

1 2

3

4

5

67

810

9

1 2

3

4

5

67

8

9

10 11

(a) 4-node tetrahedron (b) 10-node tetrahedron (c) 11-node tetrahedron

ENODES



X, u

Y, v

Z, w

Figure ENODES-7: Nonlinear Spring, Option 1

n (0)1

n (0)2

n1

n2

kz

ky

kx

n and n initially coincident

k = f (u), k = f (v), k = f (w) and always

acting in global directions X, Y, Z.

Here, 3 spring elements are defined for

spring action in X, Y and Z directions.

1 2

x 1 y 2 z 3

X, u

Y, v

Z, w


n1

n2

ax, ay, az

direction

k

n (0)1

n (0)2

d n and n initially coincident

k = f(d)

spring stiffness between nodes always act

in the specified direction ax, ay, az.

1 2

5

9

26

10

37

111, 4

Figure ENODES-6: Node numbering for some triangular shell elements, midsurface nodes

�

�

�

�

��

�

�

�

5

2

6

3 71, 4

�

�

�

�

�

�

(c) 9-node triangular shell(b) 6-node triangular shell

1, 4�

2�

3 �

(a) 3-node triangular shell

ENODES



X, u

Y, v

Z, w


n (0)1

n (0)2

n1

n2

k

n (p)2

n (0) and n (0) indicate the original

positions of the two spring nodes.

spring stiffness always acts in direction

n (0) to n (0).

line joining n to n (p) is parallel to line

joining n (0) to n (0).

1 2

1 2

1 2

1 2

X, u

Y, v

Z, w


n (0)1

n (0)2

n1

n2

k

ENODES



Globaldirection

Z

X

Y

Differentnode numbers

and noncoincidentcoordinates

Different nodenumbers and

initially coincidentcoordinates

Groundednode

Globaldirection

Z

X

Y

n1

n2

id1 = 1

n1

n2id1 = 3

n1 n2

id1 = 2

ENODESel n1 id1 n2(id2 not used)

n1id1 = 1

n1id1 = 3

n1

id1 = 2

ENODESel n1 id1 0(id2 not used)

n1

n2

ENODESel n1 0 n2 0EDATAel ax ay az

Arbitrary direction Arbitrary direction

ENODESel n1 0 0 0EDATAel ax ay az

n1n1

n2

ENODESel n1 1 n2(id2 not used)

Table ENODES-1: Input cases for translational nonlinear spring elements

U1

U2

U1

U2

U2

U1

n1,n2

n1,n2

n1,n2

U1

U2 U

1

U1

U1

n1,n2 U1

U2

U1

a

a

ENODES



Globaldirection

Z

X

Y

Differentnode numbers

and noncoincidentcoordinates

Different nodenumbers and

initially coincidentcoordinates

Groundednode

Globaldirection

Z

X

Y

n1

n2

id1 = 4

n1

n2id1 = 6

n1 n2

id1 = 5

ENODESel n1 id1 n2(id2 not used)

n1id1 = 4

n1id1 = 6

n1

id1 = 5

ENODESel n1 id1 0(id2 not used)

n1

n2

ENODESel n1 0 n2 0EDATAel ax ay az

Arbitrary direction Arbitrary direction

ENODESel n1 0 0 1EDATAel ax ay az

n1n1

n2

ENODESel n1 4 n2(id2 not used)

Table ENODES-2: Input cases for torsional nonlinear spring elements

U1

U2

U1

U2

U2

U1

n1,n2

n1,n2

n1,n2

U1

U2

U1

U1

U1

n1,n2 U1

U2

U1

a

a

ENODES






MESH-CONVERT IN OUT ELEMENT-TYPE GROUP SKEW LOAD-INITNCOINCIDE

Converts 2-D solid, 3-D solid or shell elements by changing the number of nodes of theelement.

INOUTThese parameters are currently not used.

ELEMENT-TYPE [TWODSOLID]Selects the type of element to be converted. {TWODSOLID/THREEDSOLID/SHELL/ALL}

GROUP [ALL]Selects the element group to be converted. GROUP = ALL means all element groups will beconverted. {ALL/>0}

SKEW [NO]Indicates whether skew system is assigned to newly created nodes if all other nodes on theelement face are assigned a skew system.{NO/YES}

LOAD-INIT [NO]Indicates whether existing nodal-based prescribed loads (e.g., displacement, temperature,velocity) and initial conditions are applied on the newly created nodes.{NO/YES}

Note: - Load or initial condition will only be applied on a created mid-surface node if allthe eight nodes on the element face have the load or initial condition applied.

- If a load or initial condition is applied after this command, it will not be applied onthe newly created nodes. Hence, this command should normally be used at theend of model creation.

NCOINCIDE [NEW]Indicates whether nodal coincidence is checked with newly generated nodes or all existingnodes. When a node already exists at a location, no new node will be created. {NEW/ALL}NEW Check only with newly generated nodes.ALL Check with all existing nodes.

MESH-CONVERT

Element Type Original Element Converted Element8-node quadrilateral 9-node quadrilateral6-node triangular 7-node triangular

Shell 8-node quadrilateral 9-node quadrilateral20-node brick 27-node brick10-node tetrahedral 11-node tetrahedral

2-D Solid

3-D Solid



ENODES-INTERFACE SUBSTRUCTURE GROUP

(ENTRIES EL N1 N2 N3 ... NK)

eli n1i n2i n3i ... nki

Defines fluid-structure interface elements when potential-based fluid elements are connectedto solid elements.

SUBSTRUCTURE [currently active substructure]Label number for the substructure to which subsequent nodal and element data refer.

GROUP [currently active element group]Element group label number.

ENTRIESDefines, as column headings, the input for the subsequent tabular entries. Specifies theelement nodes for which the global node numbers shall be input. The column heading ELmust always be specified first, and the essential and optional nodal headings for each type ofelement are:

eli n1

i ... n3

iFLUID2-interface elements

eli n1

i ... n9

iFLUID3-interface elements

eliElement number within the current substructure and element group.

n1in2in3i...nkiThe global node numbers defining the element in the order given by ENTRIES.

Auxiliary commands

LIST ENODES-INTERFACE FIRST LAST SUBSTRUCTURE GROUPDELETE ENODES-INTERFACE FIRST LAST SUBSTRUCTURE GROUP

ENODES-INTERFACE



EDATA SUBSTRUCTURE GROUP UNDEFINED

eli materiali areai printi savei tbirthi tdeathi epsini gapwidthi intloci(for TRUSS elements)

eli materiali thicki beti printi savei tbirthi tdeathi intloci betii itrii(for TWODSOLID elements)

eli materiali ielxi printi savei tbirthi tdeathi intloci maxesi maxesii itrii(for THREEDSOLID elements)

eli materiali sectioni endreleasei printi savei tbirthi tdeathi intloci epsinirigid1i rigid2i(for BEAM elements)

eli materiali sectioni printi savei tbirthi tdeathi intloci epaxli ephoopi(for ISOBEAM elements)

eli materiali thicki beti printi savei tbirthi tdeathi intloci betii meps11i meps22imeps12i flex11i flex22i flex12i(for PLATE elements)

eli materiali beti printi savei tbirthi tdeathi intloci betii ithsi eps11i eps22ieps12i eps13i eps23i geps11i geps22i geps12i geps13i geps23i failurei(for SHELL elements)

eli materiali sectioni printi savei tbirthi tdeathi intloci epsini(for PIPE elements)

eli matrixseti printi savei(for GENERAL elements)

eli propertyseti printi savei axi ayi azi tbirthi tdeathi(for SPRING elements)

eli materiali printi savei tbirthi tdeathi intloci ifrei itrii(for FLUID2 elements)

eli materiali ielxi printi savei tbirthi tdeathi intloci ifrei itrii(for FLUID3 elements)

Specifies property data associated with individual elements in a group.

EDATA


Sec. 9.2 Element dataEDATA

SUBSTRUCTURE [currently active substructure]Label number for the substructure to which subsequent element data refer.

GROUP [currently active group]Element group label number.

UNDEFINED [IGNORE]Indicates what action is taken if element specified in data line is not defined.{IGNORE/ERROR}

IGNORE - Program ignores any undefined element specified.ERROR - Program issues input error for undefined element and continues.

eliElement label number.

materiali [element group default]Material number. The material type must be the same as the default material type for theelement group.

printi [DEFAULT]Controls printout of element results. The value DEFAULT corresponds to that given forPRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT}

savei [DEFAULT]Controls saving of element results to porthole file. The value DEFAULT corresponds to thatgiven for PORTHOLE SAVEDEFAULT.

tbirthi [0.0]tdeathi [0.0]Element birth and death times, respectively.

intloci [0]Integration point coordinates printout flag.

0 No printing of integration point coordinates.

1 Print integration point global coordinates.

areai [0.0]Cross-sectional area. A 0.0 value indicates the element has the same cross-sectional area asthe element with the lowest label number in the group.


Chap. 9 Direct finite element data input EDATA

thicki [0.0]Element thickness. A 0.0 value indicates the element has the same thickness as the elementwith the lowest label number in the group.

ielxiThis parameter is obsolete.

ithsi [0]Indicates whether the transverse shear adjustment feature is used (1) or not (0). This featureis only available for elastic shells. {0/1}

maxesi [0]Material axes label number. See AXES-NODES.

beti [0.0]Material angle for orthotropic materials.

sectioni [0]Cross-section label number. See CROSS-SECTION.

endreleasei [0]End release label number. See ENDRELEASE.

propertyseti [element group default]Propertyset label number. See PROPERTYSET.

matrixseti [element group default]Matrix set label number. See MATRIXSET.

maxesii [0]Initial strain axes label number. See AXES-NODES.

betii [0.0]Initial strain angle.

epsini [0.0]Initial axial strain (TRUSS, BEAM, PIPE elements), or initial force if BEAM OPTION=BOLTis used.

epaxli [0.0]Initial axial strain (ISOBEAM elements).


Sec. 9.2 Element dataEDATA

ephoopi [0.0]Initial hoop strain.

meps11i [0.0]meps22i [0.0]meps12i [0.0]Initial membrane strains.

flex11i [0.0]flex22i [0.0]flex12i [0.0]Initial flexural strains.

eps11i [0.0]eps22i [0.0]eps12i [0.0]eps13i [0.0]eps23i [0.0]Initial strains.

geps11i [0.0]geps22i [0.0]geps12i [0.0]geps13i [0.0]geps23i [0.0]Initial strain gradients.

gapwidthi [0.0]Initial gap width of element. The gap option is used only for the 2-node TRUSS element witha PLASTIC-BILINEAR or PLASTIC-MULTILINEAR material model.

failurei [0]Label number of failure model.

ifrei [0]This option is not supported from Version 8.0 onwards.

itrii [0]Collapsed element indicator.

0 Collapsed quadrilateral or hexahedral element.

-1 True triangular or tetrahedral element.



axi [0.0]ayi [0.0]azi [0.0]Direction of grounded spring element.

rigid1i [0.0]rigid2i [0.0]Length of rigid end zones at the start (rigid1) and/or end (rigid2) of a BEAM element. SeeEGROUP BEAM.

Note: To define shell element thickness command ELTHICKNESS should be used.

EDATA



COPY-ELEMENT-NODES FROM TO

Copies over all elements and nodes from one finite element analysis program to another finiteelement analysis program, creating new element groups for the destination program. If, for aparticular element group type, there is no equivalent group type available in the destinationprogram the source group will not be copied.

FROM [ADINA]The source finite element analysis program. {ADINA/ADINA-T/ADINA-F}

TOThe destination finite element analysis program. {ADINA/ADINA-T/ADINA-F}

The following table indicates the source-destination element type mapping used by thiscommand:

SOURCE DESTINATION

ADINA ADINA-T ADINA-F

TRUSS ONEDCONDUCTION <not copied>TWODSOLID TWODCONDUCTION TWODFLUIDTHREEDSOLID THREEDCONDUCTION THREEDFLUIDBEAM ONEDCONDUCTION <not copied>ISOBEAM ONEDCONDUCTION <not copied>PLATE SHELLDCONDUCTION <not copied>SHELL SHELLCONDUCTION <not copied>PIPE ONEDCONDUCTION <not copied>SPRING <not copied> <not copied>GENERAL <not copied> <not copied>FLUID2 TWODCONDUCTION TWODFLUIDFLUID3 THREEDCONDUCTION THREEDFLUID

ADINA-T ADINA ADINA-F

ONEDCONDUCTION TRUSS <not copied>TWODCONDUCTION TWODSOLID TWODFLUIDTHREEDCONDUCTION THREEDSOLID THREEDFLUIDCONVECTION <not copied> CONVECTIONRADIATION <not copied> RADIATIONSHELLCONDUCTION SHELL <not copied>

COPY-ELEMENT-NODES



ADINA-F ADINA ADINA-T

TWODFLUID TWODSOLID TWODCONDUCTIONTHREEDFLUID THREEDSOLID THREEDCONDUCTIONCONVECTION <not copied> CONVECTIONRADIATION <not copied> RADIATION

COPY-ELEMENT-NODES



DELETE-FE-MODEL PROGRAM

Deletes all finite element data associated with a particular analysis program from the modeldatabase - including element groups, elements, nodes, contact groups, contact-surfaces, andcontact segments.

PROGRAM [ADINA]The finite element analysis program for which all data is to be deleted. {ADINA/ADINA-T/ADINA-F}

DELETE-FE-MODEL



REVOLVE NAME EGROUP XA YA ZA X0 Y0 Z0 ANGLE NEREVNODES NFIRST EFIRST NCOINCIDE NTOLERANCEDELETE-EGROUP LOADS-ELEMENT AXES-ORTHOTROPICAXES-INITIAL BC-FIXITY RBAR-NODESETRBAR-ELEMSET RBAR-EGROUP RBAR-TYPERBAR-SECTION RBAR-MATERIAL CGROUP CNAMEDELETE-CGROUP RBAR-AREA ALL-GROUP

Generates THREEDSOLID or FLUID3 elements by revolving 2D elements about an axis.The rule for generating a new element group type is

TWODSOLID > THREEDSOLID

FLUID2 > FLUID3

NAME [current highest element group label + 1]Element group label number of the volume elements. If NAME already exists, it must be aTHREEDSOLID or FLUID3 element group.

EGROUPPreviously defined 2D element group label.

XA [0.0]YA [0.0]ZA [0.0]Components of the rotation axis direction.

X0 [0.0]Y0 [0.0]Z0 [0.0]Global coordinates of the origin of the axis of rotation.

ANGLEAngle of rotation (in degrees).Note: ANGLE must be in the range <-360,360>. The sign of the angle is given by

considering the right hand rule.

NEREV [1]The number of elements in the direction of rotation.

NODES [0]Number of nodes for the revolved 3D elements. {0/8/20/27}

REVOLVE


Sec. 9.2 Element dataREVOLVE

If NODES=0, then the following rule applies:

Max. number of nodes Number of nodesin 2D element group in 3D element group

4 88 209 27

NFIRST [1]The starting node label for the generated nodes.

EFIRST [1]The starting element label for the generated elements.

NCOINCIDE [NO]Indicates whether the locations of new nodes generated are compared with existing nodes. IfNCOINCIDE=YES, then the location of generated generated nodes will be checked againstexisting nodes. For each generated node, if it lies within the tolerance (specified byNTOLERANCE) of an existing node, no new node will be created. {YES/NO}

NTOLERANCE [1.0E-5]If NCOINCIDE=YES parameter provides a tolerance for checking the global coordinates of alocation againts existing nodes.

DELETE-EGROUP [YES]Allows to preserve or delete original 2D element group, after the volume element group isgenerated. {YES/NO}

LOADS-ELEMENT [NO]Indicates whether element loading acting on the edges of the 2D elements will be convertedto element loadings on the faces of the 3D elements. {NO/YES}

AXES-ORTHOTROPIC [NO]Indicates whether the material axis systems of the 2D elements will be converted to initialstrain axis systems for 3D elements. {NO/YES}

AXES-INITIALSTRAIN [NO]Indicates whether the initial strain axis systems of the 2D elements to 3D elements will beconverted to initial strain axis systems for the 3D elements. {NO/YES}

BC-FIXITY [NO]Indicates whether fixity boundary conditions will be assigned to the generated nodescorresponding to the fixity conditions on the original nodes. {NO/YES}



RBAR-NODESET [0]Label number of a node set defined by the command NODESET. If this parameter references anode set that is defined, truss or beam elements (as specified by parameter RBAR-TYPE) willbe generated by connecting the nodes along the revolved direction.

RBAR-ELEMSET [0]Label number of an element set defined by the command ELEMENTSET. If this parameterreferences an element set that is defined, the elements in the element set will be duplicated inthe revolved direction.

RBAR-EGROUP [(current highest element group label number) + 1]Label number of an element group for the elements generated from parameter RBAR-NODESET. Note that elements generated from parameter RBAR-ELEMSET are appended tothe existing element group.

RBAR-TYPE [TRUSS]Specifies the type of element to be generated from parameter RBAR-NODESET. {TRUSS/BEAM}

RBAR-SECTION [1]Label number of a cross section to be assigned to beam elements generated from parameterRBAR-NODESET. Note that cross sections can be defined by the command CROSS-SEC-TION.

RBAR-MATERIAL [1]Label number of a material to be assigned to elements generated from parameter RBAR-NODESET.

CGROUPSpecifies a 2-D contact group to be used for generating 3-D contact surfaces. Note that only2-D contact surface elements which are attached to the mesh to be revolved will be used forgenerating 3-D contact surface elements.

CNAME [(current highest contact group label number) + 1]Label number of 3-D contact group that will contain the generated 3-D contact surfaceelements. If CNAME already exists (it must be a 3-D contact group), the generatedcontact surface elements will be added to the existing contact group.

DELETE-CGROUP [NO]Indicates whether the 2-D contact group will be deleted after the 3-D contact surface ele-ments are generated. When all the contact surfaces in the 2-D contact group has been usedto generate the necessary 3-D contact surfaces, the parameter should be set to YES. {YES/NO}

REVOLVE



RBAR-AREA [1.0]Specifies the cross-section area for truss elements generated from parameter RBAR-NODESET.

REVOLVE

ALL-GROUP [NO]Defines whether all groups are acted upon by this command.{NO/YES}

NO Revolve only the specified group

YES Revolve all applicable element groups and contact groups. Parameters NAME,EGROUP, CGROUP and CNAME are ignored.



SWEEP NAME EGROUP DX DY DZ NESWP NODES NFIRST EFIRSTNCOINCIDE NTOLERANCE DELETE-EGROUPLOADS-ELEMENT AXES-ORTHOTROPIC AXES-INITIALBC-FIXITY RBAR-NODESET RBAR-ELEMSETRBAR-EGROUP RBAR-TYPE RBAR-SECTIONRBAR-MATERIAL CGROUP CNAMEDELETE-CGROUP RBAR-AREA LINE ALIGNMENT ALL-GROUP

Generates a volume of 3D elements by extruding 2D elements along a vector or a line.The rule for generating a new element group type is

TWODSOLID > THREEDSOLID

FLUID2 > FLUID3

NAME [current highest element group label + 1]Element group label number of the volume elements. If NAME already exists, it must be aTHREEDSOLID or FLUID3 element group.

EGROUPPreviously defined 2D element group label.

DX [0.0]DY [0.0]DZ [0.0]Vector components defining the direction of extrusion.

NESWP [1]The number of elements in the direction of extrusion.

NODES [0]Number of nodes for the extruded 3D elements. {0/8/20/27}If NODES=0, then the following rule applies

Max. number of nodes Number of nodesin 2D element group in 3D element group

4 88 209 27

NFIRST [1]The starting node label for the generated nodes.

SWEEP



EFIRST [1]The starting element label for the generated elements.

NCOINCIDE [NO]Indicates whether the locations of new nodes generated are compared with existing nodes. IfNCOINCIDE=YES, then the location of generated generated nodes will be checked againstexisting nodes. For each generated node, if it lies within the tolerance (specified byNTOLERANCE) of an existing node, no new node will be created. {YES/NO}

NTOLERANCE [1.0E-5]If NCOINCIDE=YES parameter provides a tolerance for checking the global coordinates of alocation againts existing nodes.

DELETE-EGROUP [YES]Allows to preserve or delete original 2D element group, after the volume element group isgenerated. {YES/NO}

LOADS-ELEMENT [NO]Indicates whether element loading acting on the edges of the 2D elements will be convertedto element loadings on the faces of the 3D elements. {NO/YES}

AXES-ORTHOTROPIC [NO]Indicates whether the material axis systems of the 2D elements will be converted to initialstrain axis systems for 3D elements. {NO/YES}

AXES-INITIALSTRAIN [NO]Indicates whether the initial strain axis systems of the 2D elements to 3D elements will beconverted to initial strain axis systems for the 3D elements. {NO/YES}

Note: We use the command SWEEP to be consistent with BODY SWEEP command forextrusion along a vector or sweeping along a line. Using the more general termSWEEP allows this command to be extended for sweeping 2D elements along a lineto form 3D elements.

BC-FIXITY [NO]Indicates whether fixity boundary conditions will be assigned to the generated nodescorresponding to the fixity conditions on the original nodes. {NO/YES}

RBAR-NODESET [0]Label number of a node set defined by the command NODESET. If this parameter references anode set that is defined, truss or beam elements (as specified by parameter RBAR-TYPE) willbe generated by connecting the nodes along the swept direction.

SWEEP


Chap. 9 Direct finite element data input SWEEP

RBAR-ELEMSET [0]Label number of an element set defined by the command ELEMENTSET. If this parameterreferences an element set that is defined, the elements in the element set will be duplicated inthe swept direction.

RBAR-EGROUP [(current highest element group label number) + 1]Label number of an element group for the elements generated from parameter RBAR-NODESET. Note that elements generated from parameter RBAR-ELEMSET are appended tothe existing element group.

RBAR-TYPE [TRUSS]Specifies the type of element to be generated from parameter RBAR-NODESET. {TRUSS/BEAM}

RBAR-SECTION [1]Label number of a cross section to be assigned to beam elements generated from parameterRBAR-NODESET. Note that cross sections can be defined by the command CROSS-SEC-TION.

RBAR-MATERIAL [1]Label number of a material to be assigned to elements generated from parameter RBAR-NODESET.

CGROUPSpecifies a 2-D contact group to be used for generating 3-D contact surfaces. Note that only2-D contact surface elements which are attached to the mesh to be swept will be used forgenerating 3-D contact surface elements.

CNAME [(current highest contact group label number) + 1]Label number of 3-D contact group that will contain the generated 3-D contact surfaceelements. If CNAME already exists (it must be a 3-D contact group), the generated contactsurface elements will be added to the existing contact group.

DELETE-CGROUP [NO]Indicates whether the 2-D contact group will be deleted after the 3-D contact surface ele-ments are generated. When all the contact surfaces in the 2-D contact group has been usedto generate the necessary 3-D contact surfaces, the parameter should be set to YES. {NO/YES}

RBAR-AREA [1.0]Specifies the cross-section area for truss elements generated from parameter RBAR-NODESET.



LINELine label of the line used for sweeping.

ALIGNMENT [NORMAL]Specifies the alignment of the 2D meshed face during sweeping.

NORMAL : 2D face normal is at fixed angle to line tangent. PARALLEL : 2D face normal always points to the same direction.

ALL-GROUP [NO]Defines whether all groups are acted upon by this command.{NO/YES}

NO Revolve only the specified group

YES Revolve all applicable element groups and contact groups. Parameters NAME,EGROUP, CGROUP and CNAME are ignored.

SWEEP



BOUNDARIES SUBSTRUCTURE

nodei uxi uyi uzi rxi ryi rzi phii ovalizationi warpingi porei temperaturei beam-warpi

Assigns fixed/free boundary conditions to nodes. All of the nodes belong to the specifiedsubstructure.

SUBSTRUCTURE [current substructure]Substructure label number.

nodeiNode label number.

uxi [FREE]uyi [FREE]uzi [FREE]Boundary conditions applied to displacement degrees of freedom. {FIXED/FREE}

rxi [FREE]ryi [FREE]rzi [FREE]Boundary conditions applied to rotation degrees of freedom. {FIXED/FREE}

phii [FREE]Boundary conditions applied to the fluid potential degree of freedom. {FIXED/FREE}

ovalizationi [FREE]warpingi [FREE]Boundary conditions applied to the pipe ovalization and warping degrees of freedom.{FIXED/FREE}

porei [FREE]Boundary conditions applied to pore pressure degree of freedom. {FIXED/FREE}

temperaturei [FREE]Boundary conditions applied to temperature degree of freedom. Temperature degree offreedom applies only to heat transfer or thermo-mechanical coupled analysis. {FIXED/FREE}

BOUNDARIES



beam-warpi [FREE]Boundary conditions applied to beam-warp degree of freedom. {FIXED/FREE}

Auxiliary commands

LIST BOUNDARIES FIRST LAST SUBSTRUCTURE OPTIONOption defines listing nodes: input nodes or all model nodes. {INPUT/MODEL}

DELETE BOUNDARIES FIRST LAST SUBSTRUCTURE

BOUNDARIES






CONSTRAINT-NODE NAME SLAVENODE SLAVEDOF GENERALIZED-CONSTRAINT

masternodei masterdofi betai slavenodei slavedofi

Specifies a constraint equation which expresses a slave (dependent) degree of freedom as alinear combination of a set of master (independent) degrees of freedom.

A constraint equation can only reference nodes in the main structure.

NAME [(highest constraint equation label number) + 1]The label number of the constraint equation.

SLAVENODEThe label number of the slave node.

SLAVEDOFThe degree of freedom associated with the slave node.{X-TRANSLATION/Y-TRANSLATION/Z-TRANSLATION/X-ROTATION/Y-ROTATION/Z-ROTATION/FLUID-POTENTIAL/TEMPERATURE}


GENERALIZED-CONSTRAINT [NO]Generate generalized constraints instead of standard constraints. {NO/YES}

masternodeiThe label number of the master node for the �i�th independent term of the constraint equation.

masterdofiThe degree of freedom of the master node for the �i�th independent term of the constraintequation. Allowable values are the same as for SLAVEDOF.

betai [1.0]The coefficient of the �i�th independent term of the constraint equation.

slavenodeiThe label number of the slave node.

slavedofiThe degree of freedom associated with the slave node.

CONSTRAINT-NODE



Auxiliary commands

LIST CONSTRAINT-NODE FIRST LASTDELETE CONSTRAINT-NODE FIRST LAST



RIGIDLINK-NODE NAME SLAVENODE MASTERNODE DISPLACEMENTSDOFSI

slavenodei masternodei displacementsi

Specifies a rigid link between two nodes. A rigid link can only be specified between nodes inthe main structure.

NAME [(highest rigid link label number) + 1]The label number of the rigid link.

SLAVENODEThe label number of the slave node.

MASTERNODEThe label number of the master node.

DISPLACEMENTS [DEFAULT]Selects kinematic formulation for rigid link. See the Theory and Modeling Guide.

SMALL Small displacement formulation.

LARGE Large displacement formulation.

DEFAULT As set by KINEMATICS.

slavenodeiThe label number of the slave node.

masternodeiThe label number of the master node.

displacementsi [DEFAULT]Selects kinematic formulation for rigid link. Note that displacementi = DEFAULT means thatthe formulation specified in the KINEMATICS command is used. See the Theory andModeling Guide. {DEFAULT/SMALL/LARGE}

DOFSI [123456]Specifies the slave degrees of freedom (dof) to be constrained to the master node. DOFSImust contain 1 to 6 digits ranging from 1 to 6. Dofs 1, 2, 3 indicate X, Y, Z translations and 4,5, 6 indicate X, Y, Z rotations.

Auxiliary commands

LIST RIGIDLINK-NODE FIRST LASTDELETE RIGIDLINK-NODE FIRST LAST

RIGIDLINK-NODE



OVALIZATION-CONSTRAINT NODE TYPE GROUP

nodei elementi

Enforces the zero-slope-of-pipe-skin condition in the longitudinal direction for pipe elementnodes. This condition is applicable in the case of a rigid flange (TYPE = FLANGE) or whensymmetry is to be enforced (TYPE = SYMMETRY). These conditions apply to pipe elementnodes for the element group specified. See the Theory and Modeling Guide.

TYPE [FLANGE]

FLANGE The flange condition is applied at the specified nodes. Bothovalization and warping at these nodes are suppressed.

SYMMETRY The symmetry condition is applied at the specified nodes. Theovalization at these nodes is left free but the warping is suppressed.

GROUP [currently active group]The element group for each pipe element node specified in this command.


elementiLabel number of the element that contains the node.

Auxiliary commands

LIST OVALIZATION-CONSTRAINT NODE FIRST LAST TYPEGROUP

DELETE OVALIZATION-CONSTRAINT NODE FIRST LAST TYPEGROUP

OVALIZATION-CONSTRAINT NODE



FSI-FACE NAME DIMENSION

celli n1i n2i � n16i

Defines fsi boundary using element face node for ADINA.

NAME [(current highest fsi boundary label number) + 1]Label number of the fluid-structure-boundary to be defined.

DIMENSION [3]Dimension of FSI boundary. {3/2}

celliLabel of a cell on FSI boundary.

n1i�n16iCell�s node numbers.

Auxiliary commands

LIST FSI-FACE FIRST LASTDELETE FSI-FACE FIRST LAST

FSI-FACE



APPLY CONCENTRATED-LOADS SUBSTRUCTURE REUSE

nodei directioni factori ncuri artmi nodauxi

Applies concentrated loads to nodes.

The magnitude of the load is given by entry �factori�, which may be modified (except whenload cases are employed) via a timefunction given by entry �ncuri�.

Several concentrated loads can be defined for the same node and direction. In this case theloads are added.

SUBSTRUCTURE [currently active substructure]Identifying number for the substructure to which subsequent nodes refer.

REUSE [currently active reuse]Identifying number for the reuse to which subsequent nodes refer.

nodeiThe label number of a node to which the load is to be applied.

directioniThe direction in which the load acts.

1 x-translation force (global or skew).2 y-translation force (global or skew).3 z-translation force (global or skew).4 x-rotation moment (global or skew).5 y-rotation moment (global or skew).6 z-rotation moment (global or skew).7 Follower force acting from nodauxi to nodei.8 Follower moment about the direction from nodauxi to nodei.

factori [1.0]Multiplying factor, giving load intensity.

ncuri [1]The label number of a time function.

artmi [0.0]The arrival time associated with time dependent loads. See the Theory and Modeling Guide.

APPLY CONCENTRATED-LOADS


Sec. 9.4 Loads

nodauxi [0]Auxiliary node used to control follower loads. See the Theory and Modeling Guide.

Auxiliary Commands

LIST APPLY CONCENTRATED-LOADS SUBSTRUCTURE RESUSEDELETE APPLY CONCENTRATED-LOADS SUBSTRUCTURE REUSE

APPLY CONCENTRATED-LOADS



APPLY DISPLACEMENTS SUBSTRUCTURE REUSE

nodei directioni factori ncuri artmi iddli unloadi timeui forceui ncurui

Specifies prescribed displacements applied to nodes.

The magnitude of the displacement is given by entry �factori�, which may be modified (exceptwhen load cases are employed) via a timefunction given by entry �ncuri�.

Several prescribed displacements can be defined for the same node and direction; in this casethe displacements are averaged.

SUBSTRUCTURE [currently active substructure]Identifying number for the substructure to which subsequent nodes refer.

REUSE [currently active reuse]Identifying number for the reuse to which subsequent nodes refer.

nodeiThe label number of the node for which the displacement is to be prescribed.

directioniThe direction in which the displacement is prescribed. See the Theory and Modeling Guide.

1 x-translation (global or skew)2 y-translation (global or skew)3 z-translation (global or skew)4 x-rotation (global or skew)5 y-rotation (global or skew)6 z-rotation (global or skew)

11 - 16 Ovalization degrees of freedom.21 - 26 Warping degrees of freedom.

factori [1.0]Multiplying factor, giving displacement magnitude.


artmi [0.0]The arrival time associated with time dependent prescribed displacements.

APPLY DISPLACEMENTS


Sec. 9.4 Loads

iddli [0]Specifies whether the prescribed displacement is applied to the original configuration or thedeformed configuration for a restart analysis.

0 original configuration1 deformed configuration

unloadi [NO]Specifies the type of unloadng for prescribed displacement.{TIME/FORCE/NO}

timeui [0.0]If unloadi=TIME, this specifies the time at which unloading of prescribed displacementstarts.

forceuiIf unloadi=FORCE, this specifies the force (or reaction) value at the prescribed displacementat which unloading starts.

ncurui [1]Label number of a time function for the unloading of prescribed displacement.

Auxiliary commands

LIST APPLY DISPLACEMENTS SUBSTRUCTURE REUSEDELETE APPLY DISPLACEMENTS SUBSTRUCTURE REUSE

APPLY DISPLACEMENTS



APPLY ELECTROMAGNETIC-LOADS

node1i node2i ncuri artmi iddli

Applies electromagnetic loads to nodes.

The nodes must be part of the main structure. The load corresponds to electromagneticforces induced by short-circuit currents flowing between pairs of nodes. The magnitude ofthe short-circuit current is governed by a timefunction given by entry �ncuri�.

node1inode2iA pair of nodes between which a short-circuit current flows.

ncuri [1]The label number of a time function, giving the time dependent value of the short-circuitcurrent.

artmi [0.0]The arrival time associated with time dependent loads.

iddli [0]Indicator for deformation-dependent loading. {0/1}

0 Deformation-independent.

1 Deformation-dependent.

Auxiliary commands

LIST APPLY ELECTROMAGNETIC-LOADSDELETE APPLY ELECTROMAGNETIC-LOADS

APPLY ELECTROMAGNETIC-LOADS


Sec. 9.4 Loads

APPLY PIPE-INTERNAL-PRESSURES

nodei factori ncuri artmi

Applies internal pressures to pipe element nodes. The nodes must be part of the mainstructure.

The magnitude of the pipe internal pressure is given by entry �factori�, which may bemodified by a time function given by entry �ncuri�. Pipe internal pressure loading cannot beused in a load case, nor when automatic load displacement control is employed.

Several pipe internal pressure loads can be defined for the same node; in this case the loadsare averaged.

nodeiThe label number of the node to which the load is to be applied.

factori [1.0]Multiplying factor giving the internal pressure magnitude.



Auxiliary commands

LIST APPLY PIPE-INTERNAL-PRESSURESDELETE APPLY PIPE-INTERNAL-PRESSURES

APPLY PIPE-INTERNAL-PRESSURES



APPLY TEMPERATURES


This command defines temperatures applied to nodes. The actual applied temperature is thereference temperature plus the temperature applied in this command. The reference tempera-ture is defined in command TEMPERATURE-REFERENCE..

Several temperatures can be defined for the same node; in this case the temperatures areaveraged.

nodeiThe label number of the node at which the temperature is to be prescribed.

factori [1.0]Multiplying factor.


artmi [0.0]The arrival time associated with time dependent temperatures.

Auxiliary commands

LIST APPLY TEMPERATURESDELETE APPLY TEMPERATURES

APPLY TEMPERATURES


Sec. 9.4 Loads

APPLY TGRADIENTS


Prescribes temperature gradients at shell element midsurface nodes of the main structure.

The magnitude of the temperature gradient (degrees/unit length) is given by entry �factori�,and may be modified by a time function given by entry �ncuri�. Shell midsurface nodeswhich have no temperature gradient specified will take the value given by TEMPERATURE-REFERENCE.

Several temperature gradients can be defined for the same node; in this case the temperaturegradients are averaged.

nodeiThe label number of a shell midsurface node at which the temperature gradient is prescribed.

factori [1.0]Multiplying factor, giving the temperature gradient at the node.


artmi [0.0]The arrival time associated with time dependent temperature gradients.

Auxiliary commands

LIST APPLY TGRADIENTSDELETE APPLY TGRADIENTS

APPLY TGRADIENTS



APPLY USER-SUPPLIED-LOADS NODE-DEPENDENCE NICONS NRCONS

iconsi rconsi

Establishes the presence of user-supplied loads, which are computed using the user-suppliedsubroutines USERSL and IUSER. See the Theory and Modeling Guide for details regardingthese subroutines.

NODE-DEPENDENCE [1]

1 Load contribution calculated in the user-supplied load subroutine for a nodedepends only on nodal quantities at that node.

2 Load contribution calculated in the user-supplied load subroutine may depend onnodal quantities at other nodes.

NICONS [0]Number of integer constants to be input in the accompanying data lines.

NRCONS [0]Number of real constants to be input in the accompanying data lines.

iconsi [0]Integer constant passed to user-supplied subroutine USERSL.

rconsi [0.0]Real constant passed to user-supplied subroutine USERSL.

Auxiliary commands

LIST APPLY USER-SUPPLIED-LOADSDELETE APPLY USER-SUPPLIED-LOADS

APPLY USER-SUPPLIED-LOADS


Sec. 9.4 Loads

LOADS-ELEMENT SUBSTRUCTURE REUSE GROUP LOAD-TYPE

eli facei p1i p2i ncuri artmi idirni iddli(TWODSOLID elements, LOAD-TYPE = IN-PLANE)

eli facei p1i p2i p3i p4i ncuri artmi idirni iddli(TWODSOLID elements, LOAD-TYPE = OUT-PLANE)

eli facei p1i p2i p3i p4i ncuri artmi idirni iddli(THREEDSOLID elements)

eli facei p1i p2i ncuri artmi idirni iddli(BEAM elements)

eli facei p1i p2i p3i p4i ncuri artmi idirni iddli(ISOBEAM elements)

eli facei p1i p2i p3i ncuri artmi idirni iddli(PLATE elements)

eli facei p1i p2i p3i p4i ncuri artmi idirni iddli(SHELL elements, LOAD-TYPE = SURFACE)

eli facei p1i p2i p3i p4i ncuri artmi idirni iddli nodauxi(SHELL elements, LOAD-TYPE = LINE)

eli facei p1i p2i p3i p4i ncuri artmi idirni iddli(PIPE elements)

eli facei p1i p2i ncuri artmi idirni iddli(FLUID2 elements)

eli facei p1i p2i p3i p4i ncuri artmi idirni iddli(FLUID3 elements)

Applies distributed loads onto elements, either line loads or pressure loads.

SUBSTRUCTURE [currently active substructure]The substructure number for all elements referenced by this command.

REUSE [currently active reuse]The reuse number for all elements referenced by this command.

LOADS-ELEMENT



GROUP [currently active element group]The element group number for all elements referenced by this command.

LOAD-TYPE [IN-PLANE (TWODSOLID elements)] [SURFACE (SHELL elements)]

A subtype load indicator for TWODSOLID elements and SHELL elements.

IN-PLANE In-plane line loads for TWODSOLID elements edges.

OUT-PLANE Out-of-plane surface loads for TWODSOLID elements.

SURFACE Surface loads for SHELL elements.

LINE Line loads for SHELL element edges.

eliThe label number of the element to which the load is applied.

faceiA number giving the location onto which the load is applied. See Tables 1 and 2 below.

p1i [0.0]p2i [0.0]p3i [0.0]p4i [0.0]Load magnitude at element vertex nodes. The sign convention used is such that the load ispositive if directed into/toward the element.



idirni [0]Load direction filter.

0 Total load is applied.

1 x-component of load is applied.

2 y-component of load is applied.

3 z-component of load is applied.

LOADS-ELEMENT


Sec. 9.4 Loads

iddli [0]Deformation dependent loading flag.

0 Load is independent of structural deformation.

1 Load depends on structural deformation.

nodauxi [0]An auxiliary node used when a line load is applied to shell elements, giving the plane of lineload application.

Auxiliary commands

LIST LOADS-ELEMENT SUBSTRUCTURE REUSE GROUPLOAD-TYPE

DELETE LOADS-ELEMENT SUBSTRUCTURE REUSE GROUPLOAD-TYPE

Face parameter conventions:

Table 1: True triangular and tetrahedral elements

Face Applicable element types Location

1 TWODSOLID, THREEDSOLID opposite node 1



4 THREEDSOLID opposite node 4

LOADS-ELEMENT



Table 2: Elements including degenerated elements, but excluding true triangular and truehexahedron elements (r, s, t refer to local element coordinates)

Face Applicable element types Location

1 TWODSOLID, THREEDSOLID r = 1 side/faceFLUID2, FLUID3BEAM, ISOBEAM, PIPE r-s plane load

2 TWODSOLID, THREEDSOLID s = 1 side/faceFLUID2, FLUID3BEAM, ISOBEAM, PIPE r-t plane load

-1 TWODSOLID, THREEDSOLID r = -1 side/faceFLUID2, FLUID3

-2 TWODSOLID, THREEDSOLID s = -1 side/faceFLUID2, FLUID3

3 TWODSOLID, THREEDSOLID t = 1 side/faceFLUID3, PLATE, SHELL

-3 TWODSOLID, THREEDSOLID t = -1 side/faceFLUID3, PLATE, SHELL

4 SHELL line load, N4-N1 side,r-s plane load

5 SHELL line load, N1-N2 side,r-s plane load

-4 SHELL line load, N2-N3 side,r-s plane load

-5 SHELL line load, N3-N4 side,r-s plane load

6 SHELL line load, N4-N1 side,r-t plane load

7 SHELL line load, N1-N2 side,r-t plane load

-6 SHELL line load, N2-N3 side,r-t plane load

-7 SHELL line load, N3-N4 side,r-t plane load

LOADS-ELEMENT



INITIAL ACCELERATIONS SUBSTRUCTURE REUSE

nodei uxi uyi uzi rxi ryi rzi fi

Specifies initial accelerations at nodes. Only nonzero initial accelerations need be assigned.


REUSE [current reuse]The reuse for each node specified in this command.

nodeiLabel number of a node at which initial accelerations are given.

uxi [0.0]uyi [0.0]uzi [0.0]The initial accelerations for the displacement degrees of freedom at nodei.

rxi [0.0]ryi [0.0]rzi [0.0]The initial accelerations for the rotational degrees of freedom at nodei.

fi [0.0]The initial 2nd time derivative of fluid potential or hydrostatic pressure at nodei.

Auxiliary commands

LIST INITIAL ACCELERATIONSDELETE INITIAL ACCELERATIONS

INITIAL ACCELERATIONS



INITIAL DISPLACEMENTS SUBSTRUCTURE REUSE


Specifies initial displacements to nodes. Only nonzero initial displacements need be as-signed.



nodeiLabel number of a node at which initial displacements are given.

uxi [0.0]uyi [0.0]uzi [0.0]The initial displacements for the translational degrees of freedom at nodei.

rxi [0.0]ryi [0.0]rzi [0.0]The initial displacements for the rotational degrees of freedom at nodei.

fi [0.0]The initial fluid potential or hydrostatic pressure at nodei.

Auxiliary commands

LIST INITIAL DISPLACEMENTSDELETE INITIAL DISPLACEMENTS

INITIAL DISPLACEMENTS



INITIAL FLEXURALSTRAINS

nodei kappa-11i kappa-22i kappa-12i

Specifies initial flexural strains at plate element nodes. Only nonzero flexural strains need beassigned.

nodeiLabel number of a plate element at which initial flexural strains are given.

kappa-11i [0.0]kappa-22i [0.0]kappa-12i [0.0]Flexural strain components kappa11, kappa22, kappa12. See the Theory and Modeling Guide.

Auxiliary commands

LIST INITIAL FLEXURALSTRAINSDELETE INITIAL FLEXURALSTRAINS

INITIAL FLEXURALSTRAINS



INITIAL OVALIZATIONS SUBSTRUCTURE REUSE

nodei ov1i ov2i ov3i ov4i ov5i ov6i

Specifies initial ovalizations at pipe element nodes. Only nonzero ovalizations need beassigned.



nodeiLabel number of a pipe element node at which initial ovalizations are given.

ov1i [0.0]ov2i [0.0]ov3i [0.0]ov4i [0.0]ov5i [0.0]ov6i [0.0]The initial ovalization magnitudes at nodei. See the Theory and Modeling Guide.

Auxiliary commands

LIST INITIAL OVALIZATIONSDELETE INITIAL OVALIZATIONS

INITIAL OVALIZATIONS



INITIAL PINTERNALPRESSURES

nodei pini

Specifies initial pipe internal pressures at pipe element nodes. Only nonzero pipe internalpressures need be assigned.

nodeiLabel number of a pipe element node at which initial internal pressure is given.

pini [0.0]The initial pipe internal pressure at nodei.

Auxiliary commands

LIST INITIAL PINTERNALPRESSURESDELETE INITIAL PINTERNALPRESSURES

INITIAL PINTERNALPRESSURES



INITIAL STRAINS

nodei stran-11i stran-22i stran-33i stran-12i stran-13i stran-23i

Specifies initial strains at nodes. Only nonzero initial strains need be assigned.Orientation of initial strain axes is defined by command AXES-INITIALSTRAIN.

nodeiLabel number of a node at which initial strains are given.

stran-11i [0.0]stran-22i [0.0]stran-33i [0.0]stran-12i [0.0]stran-13i [0.0]stran-23i [0.0]The strain components at nodei, in the coordinate system of the element(s) to which nodei isattached. See the Theory and Modeling Guide.

Auxiliary commands

LIST INITIAL STRAINSDELETE INITIAL STRAINS

INITIAL STRAINS



INITIAL SGRADIENTS

nodei sgrad-11i sgrad-22i sgrad-12i sgrad-13i sgrad-23i

Specifies initial strain gradients at shell element midsurface nodes. Only nonzero straingradients need be assigned. Orientation of initial strain gradient axes is defined by commandAXES-INITIALSTRAIN.

nodeiLabel number of a shell element midsurface node at which initial strain gradients are given.

sgrad-11i [0.0]sgrad-22i [0.0]sgrad-12i [0.0]sgrad-13i [0.0]sgrad-23i [0.0]The strain gradient components at nodei. See the Theory and Modeling Guide.

Auxiliary commands

LIST INITIAL SGRADIENTSDELETE INITIAL SGRADIENTS

INITIAL SGRADIENTS



INITIAL TEMPERATURES

nodei tempi

Specifies initial temperatures at nodes. Only temperatures that are different from the initialreference temperature, defined by TEMPERATURE REFERENCE, need be assigned.

nodeiLabel number of a node at which initial temperature is given.

tempi [0.0]The initial temperature at nodei.

Auxiliary commands

LIST INITIAL TEMPERATURESDELETE INITIAL TEMPERATURES

INITIAL TEMPERATURES



INITIAL TGRADIENTS

nodei tgradienti

Specifies initial temperature gradients at shell element midsurface nodes. Only initial tempera-ture gradients that are different than the reference temperature gradient, defined by TEM-PERATURE-REFERENCE, need be assigned.

nodeiLabel number of a shell element midsurface node at which initial temperature gradient isgiven.

tgradienti [0.0]The initial temperature gradient at nodei, measured in degrees/unit length in the shell normaldirection.

Auxiliary commands

LIST INITIAL TGRADIENTSDELETE INITIAL TGRADIENTS

INITIAL TGRADIENTS



INITIAL VELOCITIES SUBSTRUCTURE REUSE


Specifies initial velocities at nodes. Only nonzero initial velocities need be assigned.



nodeiLabel number of a node at which initial velocities are given.

uxi [0.0]uyi [0.0]uzi [0.0]The initial velocities for the displacement degrees of freedom at nodei.

rxi [0.0]ryi [0.0]rzi [0.0]The initial velocities for the rotational degrees of freedom at nodei.

fi [0.0]The initial 1st time derivative of fluid potential or hydrostatic pressure at nodei.

Auxiliary commands

LIST INITIAL VELOCITIESDELETE INITIAL VELOCITIES

INITIAL VELOCITIES



INITIAL WARPINGS SUBSTRUCTURE REUSE

nodei warp1i warp2i warp3i warp4i warp5i warp6i

Specifies initial warpings at pipe element nodes. Only nonzero warpings need be assigned.



nodeiLabel number of a pipe element node at which initial warpings are given.

warp1i [0.0]warp2i [0.0]warp3i [0.0]warp4i [0.0]warp5i [0.0]warp6i [0.0]The initial warping magnitudes at nodei. See the Theory and Modeling Guide.

Auxiliary commands

LIST INITIAL WARPINGSDELETE INITIAL WARPINGS

INITIAL WARPINGS



IMPERFECTION NODES

bucklingmodei nodei directioni displacementi

Specifies imperfections based on buckling mode shapes which have been calculated in aprevious run. The total imperfection applied to the nodal coordinates is a superposition ofthe imperfections from each specified buckling mode. List of buckling modes has to becontinous - all buckling modes between the first and last mode have to be specified. Formodes which are not significant, displacementi should be set to 0.

bucklingmodeiThe number of the buckling mode shape.

nodeiNode label number where the magnitude of the imperfection associated with bucklingmodei isspecified.

directioniTranslational degree of freedom for nodei.

1 X-translation (global or skew).

2 Y-translation (global or skew).

3 Z-translation (global or skew).

displacementi [0.0]Magnitude of imperfection in the same length unit as the global coordinates. ADINA scalesbucklingmodei to have this value at the node and in the direction specified.

Auxiliary commands

LIST IMPERFECTION NODESDELETE IMPERFECTION NODES

IMPERFECTION NODES


Sec. 9.6 Contact

CONTACT-ELEMSET NAME PRINT SAVE

eledgeseti sensei (2-D contact groups)

elfaceseti sensei (3-D contact groups)

Defines a contact surface using element edge or face set defined by the ELEDGESET orELFACESET command.

NAME [(current highest contact surface label number) + 1]Label number of the contact surface to be defined. Note that the contact surface names areunique only within a contact group, i.e. two different contact groups may each define its owncontact surface "1".

PRINT [DEFAULT]Flag controlling printout of the results of the contact analysis as determined by the FORCESand TRACTIONS parameters of the CGROUP command. If DEFAULT is specified, printout iscontrolled by PRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT}

SAVE [DEFAULT]Flag controlling saving (to the porthole file) of the results of the contact analysis as deter-mined by the FORCES and TRACTIONS parameters of the CGROUP command. If DEFAULTis specified, saving is controlled by the PORTHOLE SAVEDEFAULT parameter. {YES/NO/DEFAULT}

eledgesetiElement edge set label number.

elfacesetiElement face set label number.

sensei [+1]Orientation flag.

+1 contact surface follows the orientation of the element edges or faces.

-1 contact surface uses opposite orientation to the element edges or faces.

Auxiliary commands

LIST CONTACT-EELEMSET FIRST LASTDELETE CONTACT-EELEMSET FIRST LAST

CONTACT-ELEMSET



CONTACT-FACENODES NAME PRINT SAVE

segi n1i n2i n3i n4i n5i n6i n7i n8i n9i

This command defines a contact surface within the current contact group using face nodenumbers. Command can be applied only to 3-D contact.

NAMELabel number of the contact surface to be defined.

PRINTFlag controlling printout of the results, see command CONTACTSURFACE.

SAVEFlag controlling saving of the results, see command CONTACTSURFACE.

segiLabel number of segment i.

n1i...n4iThe corner nodes for segment i.

n5i...n8iThe midside nodes for segment i.

n9iThe midsurface node for segment i.

Auxiliary commands

LIST CONTACT-FACENODES FIRST LAST GROUPDELETE CONTACT-FACENODES FIRST LAST GROUP

CONTACT-FACENODES


Sec. 9.6 Contact

CONTACT-NODES NAME PRINT SAVE MODE MASTER

ni (2-D contact groups)

segi n1i n2i n3i n4i (3-D contact groups)

Defines a contact surface within the current contact group. Contact surfaces are defined bythe end-nodes of the segments.

NAME [(current highest contact-surface label number) + 1]Label number of the contact-surface to be defined. Contact-surface numbering is shared withCONTACTSURFACE, CONTACTPOINT and CONTACT-FACENODES.

PRINT [DEFAULT]Controls printout of results for the contact-surface. Input of DEFAULT implies the setting ofPRINTOUT PRINTDEFAULT is used. {YES/NO/DEFAULT}

SAVE [DEFAULT]Controls saving of results (to the porthole file) for the contact-surface. Input of DEFAULTimplies the setting of PORTHOLE SAVEDEFAULT is used. {YES/NO/DEFAULT}

MODE [INPUT]

INPUT The contact segments are defined exactly as input.

REVERSE The contact segments are reversed.

ALIGN The contact segments are aligned to have the same sense as thefirst segment.

MASTER [0]Master Point Label used for creating rigid link between this Master Point and all thesecontact nodes.

niLabel numbers of nodes on a 2-D contact-surface, see the Theory and Modeling Guide for theorientation convention used. Segments are defined by successive node numbers; that is,segment 1 is defined by the first two nodes, segment 2 is defined by the second and third node,etc.

segiLabel number of an area-segment on a 3-D contact surface. Each data input line defines a newsegment.

CONTACT-NODES



n1i,...,n4iLabel numbers of nodes defining the area segment, see the Theory and Modeling Guide forthe orientation convention used.

Auxiliary commands

LIST CONTACT-NODES FIRST LAST GROUPLIST CONTACT-NODES lists the definitions of contactsurfaces with label numbers in agiven range. If no range is specified a list of all contactsurfaces label numbers within thegiven contact group is listed. GROUP is set to the current active contact group if novalue is input for this parameter.

DELETE CONTACT-NODES FIRST LAST GROUPDELETE CONTACT-NODES deletes the contactsurfaces with label numbers in a givenrange. Note that a contactsurface will not be deleted if it is referenced by a contactpairdefinition (see command CONTACTPAIR ). GROUP is set to the current active contactgroup if no value is input for this parameter.

CONTACT-NODES


Sec. 9.7 Fracture

CRACK-PROPAGATION NODES NAME NCRACK

node-1i ... node-NCRACKi nvshfti factori

Defines the initial crack front position and/or the virtual/actual crack propagation path alongwhich a crack would propagate.

For 2-D analysis, the crack front corresponds to a single node - the crack tip node. the virtualcrack propagation path corresponds to a single line of nodes starting at the crack tip node.

For 3-D analysis, the crack front corresponds to a line of nodes - the first node given for each�generator� line of nodes. The virtual/actual crack propagation path corresponds to asurface developed from the crack front along generator lines originating at the crack frontnodes.

NAME [1]The label number of the crack propagation surface. At present only one crack surface isallowed.

NCRACK [1]The number of vertex nodes along the generator lines. {1 ≤ NCRACK ≤ 999}

node-1i ... node-NCRACKiLabel numbers of nodes along generator line �i� of the crack propagation surface.

nvshfti [0]Virtual material shift associated with generator line �i� of the crack propagation surface:For a fixed virtual material shift, this is the label number of a virtual shift defined by commandJ-VIRTUAL-SHIFT.

For a moving virtual material shift, this is the number of �rings� of elements about the(moving) crack tip on the generator line.

Parameter nvshfti is used only in crack propagation analysis (FRACTURE TYPE =PROPAGA-TION).

factori [0.0]Resistance factor. See the Theory and Modeling Guide.

Auxiliary commands

LIST CRACK-PROPAGATION FIRST LASTDELETE CRACK-PROPAGATION FIRST LAST

CRACK-PROPAGATION NODES



J-VIRTUAL-SHIFT NODE NAME VECTOR VX VY VZ N3DSH

nodei

Defines a fixed virtual-crack-extension material shift via a set of nodes.

NAME [(current highest virtual shift label number) + 1]Label number of the virtual shift to be defined.

VECTOR [AUTOMATIC]

AUTOMATIC The shift vector is calculated automatically, from the cracksurface definition (see CRACK-PROPAGATION). In the case ofa 3-D crack, N3DSH is used to select a generator line associatedwith the automatic shift vector calculation.

INPUT The shift vector is input directly via VX, VY and VZ.


N3DSH [0]Generator line number of the crack surface for automatic shift vector calculation (for a 3-Dcrack).

nodeiThe label number of a node contained within the virtual material shift.

Auxiliary commands

LIST J-VIRTUAL-SHIFT NODE FIRST LASTDELETE J-VIRTUAL-SHIFT NODE FIRST LAST

J-VIRTUAL-SHIFT NODE


Sec. 9.7 Fracture

J-VIRTUAL-SHIFT ELEMENT NAME GROUP VECTOR VX VY VZN3DSH

elementi groupi

Defines a fixed virtual-crack-extension material shift via a set of elements.

NAME [(current highest virtual shift label number) + 1]Label number of the virtual shift to be defined.

GROUP [current active group]Element group label number.

VECTOR [AUTOMATIC]

AUTOMATIC The shift vector is calculated automatically, from the cracksurface definition (see CRACK-PROPAGATION ). In the case ofa 3-D crack, N3DSH is used to select a generator line associatedwith the automatic shift vector calculation.

INPUT The shift vector is input directly via VX, VY and VZ.


N3DSH [0]Generator line number of the crack surface for automatic shift vector calculation, (for a3-D crack).

elementiThe label number of an element contained in the virtual material shift.

groupi [GROUP]The label number of the element group, containing elementi.

Auxiliary commands

LIST J-VIRTUAL-SHIFT ELEMENT FIRST LASTDELETE J-VIRTUAL-SHIFT ELEMENT FIRST LAST

J-VIRTUAL-SHIFT ELEMENT



J-LINE ELEMENT NAME GROUP PRINT SAVE START-FACE END-FACE

elementi groupi

Defines a line contour connected by a series of element faces.

NAME [(current highest line contour label number) + 1]Label number of the line contour to be defined.

GROUP [currently active group]Element group label number.

PRINT <not currently active>SAVE <not currently active>

START-FACE [0]Determines which face of the first element is selected to start the contour, if the element hasmore than one boundary face.

0 Face number automatically selected.1 Face N1-N2.2 Face N2-N3.3 Face N3-N4.4 Face N4-N1.

where N1, N2, N3, N4 are the element vertex nodes.

END-FACE [0]Determines which face of the last element is selected to terminate the contour, if the elementhas more than one boundary face.

0 Face number automatically selected.1 Face N1-N2.2 Face N2-N3.3 Face N3-N4.4 Face N4-N1.

elementiThe label number of an element which forms the line contour.

groupi [GROUP]The label number of the element group, containing elementi.

J-LINE ELEMENT


Sec. 9.7 Fracture

Auxiliary commands

LIST J-LINE ELEMENT FIRST LASTDELETE J-LINE ELEMENT FIRST LAST

J-LINE ELEMENT



SINGULAR NODES Q-POINT

nodei

Defines a set of vertex nodes whose adjacent non-vertex nodes are to be moved to formsingularities. See the Theory and Modeling Guide.

Q-POINT [QUARTER]Selects whether non-vertex nodes adjacent to the desired vertex nodes are moved to the �1/4point�, or the opposite action is taken.

QUARTER Nodes are moved to the �1/4 point�.

MID Nodes are moved from the �1/4 point� back to the relevant mid-side/face position.

nodeiLabel number of a singular node.

Auxiliary commands

LIST SINGULAR NODES FIRST LASTDELETE SINGULAR NODES FIRST LAST

SINGULAR NODES


Sec. 9.8 Substructures and cyclic symmetry

REUSE-NODES SUBSTRUCTURE REUSE LOAD-REUSE

iconai iretni

Defines the nodal connectivity between a substructure and the main structure. Each sub-structure can be used several times and this command sets the current �reuse� label identify-ing number for the active substructure.

SUBSTRUCTURE [currently active substructure]Identifying number for the substructure to which subsequent reuse data refer.

REUSE [currently active reuse]Label number of the reuse to be defined.

LOAD-REUSE [SAME]Reuse loading indicator.

SAME The loading for this reuse is the same as for the previous reuse,REUSE-1, of the same substructure.

DIFFERENT The loading for this reuse is specified by subsequent loadingcommands, e.g., APPLY-LOAD.

iconaiThe main structure connection node for the substructure reuse. Note that the same numberof data input lines must be entered for each reuse of the substructure.

iretni [0]The substructure connection node for the substructure reuse.

Auxiliary commands

LIST REUSE-NODES SUBSTRUCTURE REUSEDELETE REUSE-NODES SUBSTRUCTURE REUSE

REUSE-NODES



CYCLICBOUNDARIES NODES

sbnodei mbnodei

Specifies the cyclic boundary nodes of the fundamental part of a cyclic symmetric structure.The cyclic boundaries of the fundamental part consist of two boundaries, namely, the masterand slave cyclic boundaries.

When the nodes on the master cyclic boundary are rotated 360/M (where M is the number ofcyclic parts) degrees counter clockwise about the cyclic symmetry axis, they should coincidewith the nodes on the slave cyclic boundary.

sbnodeiLabel number of a node on the slave cyclic boundary.

mbnodeiLabel number of the corresponding node on the master cyclic boundary.

Auxilary commands

LIST CYCLICBOUNDARIES NODES FIRST LASTDELETE CYCLICBOUNDARIES NODES FIRST LAST

CYCLICBOUNDARIES NODES

ADINA R & D, Inc. Index-1

Command index

Command index

A

ADINA, 3-9

ANALYSIS DYNAMIC-DIRECT-INTEGRA-

TION, 5-22

ANALYSIS MODAL-PARTICIPATION-

FACTORS, 5-33

ANALYSIS MODAL-STRESSES, 5-34

ANALYSIS MODAL-TRANSIENT, 5-32

ANALYTICAL-RIGID-TARGET, 7-238

APPLY CONCENTRATED-LOADS, 9-62

APPLY DISPLACEMENTS, 9-64

APPLY ELECTROMAGNETIC-LOADS, 9-66

APPLY PIPE-INTERNAL-PRESSURES, 9-67

APPLY TEMPERATURES, 9-68

APPLY TGRADIENTS, 9-69

APPLY USER-SUPPLIED-LOADS, 9-70

APPLY-LOAD, 7-395

AUTOMATIC LOAD-DISPLACEMENT, 5-57

AUTOMATIC TIME-STEPPING, 5-59

AUTOMATIC TOTAL-LOAD-APPLICATION,

5-61

AXES CONSTANT, 7-429

AXES EDGE, 7-438

AXES FACE, 7-439

AXES LINE1, 7-430

AXES LINE2, 7-431

AXES NODES, 7-432

AXES POINT-LINE, 7-436

AXES POINT2, 7-434

AXES POINT3, 7-435

AXES SURFACE, 7-437

AXES-CYLINDRICAL, 7-440

AXES-INITIALSTRAIN, 9-15

AXES-NODES, 9-14

AXES-ORTHOTROPIC, 9-16

AXES-SPHERICAL, 7-441

AXIS-ROTATION, 7-235

B

BCELL, 7-366

BLAYER, 8-59

BODY BLEND, 6-102

BODY BLOCK, 6-104

BODY CHAMFER, 6-107

BODY CONE, 6-109

BODY CYLINDER, 6-112

BODY HOLLOW, 6-115

BODY INTERSECT, 6-116

BODY LOFTED, 6-117

BODY MERGE, 6-118

BODY MID-SURFACE, 6-119

BODY OPTION, 6-120

BODY PARTITION, 6-121

Index-2 AUI Command Reference Manual: Vol. I � ADINA Structures Model Definition

Command index

BODY PIPE, 6-122

BODY PRISM, 6-125

BODY PROJECT, 6-128

BODY REVOLVED, 6-129

BODY SECTION, 6-132

BODY SEW, 6-133

BODY SHEET, 6-134

BODY SPHERE, 6-135

BODY SUBTRACT, 6-137

BODY SURFACES, 6-63

BODY SWEEP, 6-138

BODY TORUS, 6-141

BODY TRANSFORMED, 6-144

BODY VOLUMES, 6-64

BODY-CLEANUP, 6-74

BODY-DEFEATURE, 6-71

BODY-DISCREP, 6-70

BODY-DSCADAP, 6-76

BODY-ELEMDATA FLUID3, 7-211

BODY-ELEMDATA GENERAL, 7-206

BODY-ELEMDATA THREEDSOLID, 7-192

BODY-RESTORE, 6-75

BOLT-OPTIONS, 8-56

BOLT-TABLE, 8-57

BOUNDARIES, 9-54

BOUNDARY-SURFACE SURFACE-TENSION,

7-362

BUCKLING-LOADS, 5-30

C

CGROUP CONTACT2, 7-243

CGROUP CONTACT3, 7-264

CHECK-SURFACES, 6-49

COEFFICIENTS-TABLE, 7-131

COMMANDFILE, 3-34

CONSTRAINT, 7-338

CONSTRAINT-G, 7-346

CONSTRAINT-MS, 7-342

CONSTRAINT-NODE, 9-57

CONTACT-CONTROL, 7-239

CONTACT-ELEMSET, 9-87

CONTACT-FACENODES, 9-88

CONTACT-NODES, 9-89

CONTACT-OUTPUT-NODES, 5-92

CONTACT3-SEARCH, 7-307

CONTACTBODY, 7-291

CONTACTPAIR, 7-304

CONTACTPOINT, 7-296

CONTACTSURFACE, 7-293

CONTROL, 4-3

COORDINATES NODE, 9-3

COORDINATES POINT, 6-6

COPY-ELEMENT-NODES, 9-43

COPY-MESH-BODY, 8-147

COPY-TRIANGULATION, 8-61

COULOMB-FRICTION, 7-301

CPROP, 7-391


Command index

CRACK-GROWTH, 7-312

CRACK-PROPAGATION, 7-314

CRACK-PROPAGATION NODES, 9-91

CREEP-COEFFICIENTS LUBBY2, 7-132

CREEP-COEFFICIENTS MULTILINEAR,

7-133

CREEP-COEFFICIENTS TEMPERATURE-

ONLY, 7-134

CREEP-COEFFICIENTS USER-SUPPLIED,

7-136

CROSS-SECTION BOX, 7-168

CROSS-SECTION I, 7-170

CROSS-SECTION L, 7-172

CROSS-SECTION PIPE, 7-174

CROSS-SECTION PROPERTIES, 7-180

CROSS-SECTION RECTANGULAR, 7-176

CROSS-SECTION U, 7-178

CS-OFFSET, 7-303

CSDELETE, 8-152

CSURFACE, 8-151

CURVATURE-MOMENT, 7-137

CURVE-FITTING, 7-100

CYCLIC-CONTROL, 7-228

CYCLICBOUNDARIES NODES, 9-98

CYCLICBOUNDARY, 7-232

CYCLICBOUNDARY THREE-D, 7-234

CYCLICBOUNDARY TWO-D, 7-233

CYCLICLOADS, 7-231

D

DAMPERS, 7-222

DAMPERS NODES, 9-7

DATABASE ATTACH, 3-7

DATABASE DETACH, 3-8

DATABASE NEW, 3-3

DATABASE OPEN, 3-4

DATABASE SAVE, 3-6

DATABASE WRITE, 3-5

DELETE-FE-MODEL, 9-45

DELETE-TRIANGULATION, 8-62

DISK-STORAGE, 5-97

DOF-ACTIVE, 5-17

DOF-SYSTEM, 7-421

DOF-SYSTEM NODES, 9-5

DOMAIN, 6-95

DRAWBEAD, 7-298

E

EDATA, 9-38

EDGE-ELEMDATA BEAM, 7-194

EDGE-ELEMDATA GENERAL, 7-206

EDGE-ELEMDATA ISOBEAM, 7-196

EDGE-ELEMDATA PIPE, 7-204

EDGE-ELEMDATA TRUSS, 7-188

EG-SUBSTRUCTURE, 7-237

EGCONTROL, 8-55

EGROUP BEAM, 8-19


Command index

EGROUP FLUID2, 8-49

EGROUP FLUID3, 8-52

EGROUP GENERAL, 8-47

EGROUP ISOBEAM, 8-24

EGROUP PIPE, 8-40

EGROUP PLATE, 8-29

EGROUP SHELL, 8-33

EGROUP SPRING, 8-45

EGROUP THREEDSOLID, 8-12

EGROUP TRUSS, 8-3

EGROUP TWODSOLID, 8-6

ELAYER, 7-202

ELDELETE, 8-146

ELEDGESET, 9-17

ELEMENTSET, 9-19

ELEMSAVE-STEPS, 5-88

ELFACESET, 9-20

ELTHICKNESS, 8-163

END, 3-37

ENDRELEASE, 7-353

ENODES, 9-23

ENODES-INTERFACE, 9-37

EQUILIBRIUM-STEPS, 5-71

EXPORT NASTRAN, 3-26

EXPORT UNIVERSAL, 3-27

F

FACE-ELEMDATA FLUID2, 7-209

FACE-ELEMDATA GENERAL, 7-206

FACE-ELEMDATA PLATE, 7-198

FACE-ELEMDATA SHELL, 7-200

FACE-ELEMDATA TWODSOLID, 7-190

FACE-THICKNESS, 6-65

FACELINK, 6-66

FAILURE HASHIN, 5-50

FAILURE MAXSTRAIN, 5-45

FAILURE MAXSTRESS, 5-43

FAILURE TSAI-HILL, 5-47

FAILURE TSAI-WU, 5-48

FAILURE USERSUPPLIED, 5-51

FEPROGRAM, 5-3

FILEECHO, 3-32

FILELIST, 3-31

FILELOG, 3-33

FILEREAD, 3-29

FILESESSION, 3-30

FIXBOUNDARY, 7-348

FIXITY, 7-347

FORCE-STRAIN, 7-140

FRACTURE, 7-310

FREESURFACE, 7-365

FREQUENCIES, 5-26

FSBOUNDARY, 7-355

FSBOUNDARY THREE-D, 7-357

FSBOUNDARY TWO-D, 7-356

FSI-FACE, 9-61

FTABLE, 7-138


Command index

G

GADAPT, 8-140

GBCELL, 8-143

GBODY, 8-128

GEDGE, 8-119

GET-EDGE-FACES, 6-98

GET-EDGE-POINTS, 6-98

GET-FACE-EDGES, 6-99

GFACE, 8-122

GHEXA, 8-136

GLINE, 8-102

GLUEMESH, 8-153

GPOINT, 8-101

GSURFACE, 8-105

GVOLUME, 8-113

H

HEADING, 5-4

I

IMPERFECTION NODES, 9-86

IMPERFECTION POINTS, 7-408

IMPERFECTION SHAPE, 7-409

INITIAL ACCELERATIONS, 9-75

INITIAL DISPLACEMENTS, 9-76

INITIAL FLEXURALSTRAINS, 9-77

INITIAL OVALIZATIONS, 9-78

INITIAL PINTERNALPRESSURES, 9-79

INITIAL SGRADIENTS, 9-81

INITIAL STRAINS, 9-80

INITIAL TEMPERATURES, 9-82

INITIAL TGRADIENTS, 9-83

INITIAL VELOCITIES, 9-84

INITIAL WARPINGS, 9-85

INITIAL-CONDITION, 7-402

INITIAL-MAPPING, 7-410

IRRADIATION_CREEP-TABLE, 7-141

ITERATION, 5-66

J

J-LINE ELEMENT, 9-94

J-LINE POINT, 7-316

J-LINE RING, 7-318

J-VIRTUAL-SHIFT ELEMENT, 9-93

J-VIRTUAL-SHIFT LINE, 7-322

J-VIRTUAL-SHIFT NODE, 9-92

J-VIRTUAL-SHIFT POINT, 7-320

J-VIRTUAL-SHIFT RING, 7-325

J-VIRTUAL-SHIFT SURFACE, 7-324

K

KINEMATICS, 5-35

KNOTS, 6-19

L

LAYER, 7-184

LCOMBINATION, 7-394

LCURVE, 7-164


Command index

LINE ARC, 6-9

LINE CIRCLE, 6-14

LINE COMBINED, 6-25

LINE CURVILINEAR, 6-17

LINE EXTRUDED, 6-29

LINE POLYLINE, 6-20

LINE REVOLVED, 6-26

LINE SECTION, 6-23

LINE STRAIGHT, 6-8

LINE TRANSFORMED, 6-31

LINE-ELEMDATA BEAM, 7-194

LINE-ELEMDATA GENERAL, 7-206

LINE-ELEMDATA ISOBEAM, 7-196

LINE-ELEMDATA PIPE, 7-204

LINE-ELEMDATA TRUSS, 7-188

LINE-FUNCTION, 6-78

LIST-TRIANGULATION, 8-63

LNTHICKNESS, 6-34

LOAD CENTRIFUGAL, 7-368

LOAD CONTACT-SLIP, 7-370

LOAD CONVECTION, 7-371

LOAD DISPLACEMENT, 7-373

LOAD ELECTROMAGNETIC, 7-374

LOAD FORCE, 7-375

LOAD LINE, 7-376

LOAD MASS-PROPORTIONAL, 7-377

LOAD MOMENT, 7-379

LOAD NODAL-PHIFLUX, 7-380

LOAD PHIFLUX, 7-381

LOAD PIPE-INTERNAL-PRESSURE, 7-383

LOAD PORE-PRESSURE, 7-385

LOAD POREFLOW, 7-384

LOAD PRESSURE, 7-386

LOAD RADIATION, 7-387

LOAD TEMPERATURE, 7-389

LOAD TGRADIENT, 7-390

LOAD-CASE, 7-393

LOAD-CLOUD, 3-19

LOAD-PENETRATION, 7-401

LOAD-STL, 3-20

LOADDXF, 3-12

LOADIGES, 3-14

LOADS-ELEMENT, 9-71

LOADSOLID, 3-17

M

MASS-MATRIX, 5-38

MASSES, 7-219

MASSES NODES, 9-6

MASTER, 5-6

MATERIAL ANAND, 7-3

MATERIAL ARRUDA-BOYCE, 7-5

MATERIAL CAM-CLAY, 7-8

MATERIAL CONCRETE, 7-9

MATERIAL CREEP, 7-13

MATERIAL CREEP-IRRADIATION, 7-15

MATERIAL CREEP-VARIABLE, 7-17

MATERIAL CURVE-DESCRIPTION, 7-19


Command index

MATERIAL DRUCKER-PRAGER, 7-21

MATERIAL ELASTIC, 7-24

MATERIAL FLUID, 7-25

MATERIAL GASKET, 7-26

MATERIAL GURSON-PLASTIC, 7-28

MATERIAL HYPER-FOAM, 7-34

MATERIAL HYPERELASTIC, 7-30

MATERIAL ILYUSHIN, 7-37

MATERIAL ISOTROPIC, 7-92

MATERIAL MOHR-COULOMB, 7-38

MATERIAL MOONEY-RIVLIN, 7-40

MATERIAL MROZ-BILINEAR, 7-43

MATERIAL MULTILINEAR-PLASTIC-

CREEP, 7-44

MATERIAL MULTILINEAR-PLASTIC-

CREEP-VARIABLE, 7-47

MATERIAL NONLINEAR-ELASTIC, 7-50

MATERIAL OGDEN, 7-52

MATERIAL ORTHOTROPIC, 7-55

MATERIAL PLASTIC-BILINEAR, 7-57

MATERIAL PLASTIC-CREEP, 7-60

MATERIAL PLASTIC-CREEP-VARIABLE,

7-62

MATERIAL PLASTIC-CYCLIC, 7-65

MATERIAL PLASTIC-MULTILINEAR, 7-68

MATERIAL PLASTIC-ORTHOTROPIC, 7-71

MATERIAL SMA, 7-75

MATERIAL SUSSMAN-BATHE, 7-77

MATERIAL TEMPDEP-C-ISOTROPIC, 7-95

MATERIAL TEMPDEP-C-ORTHOTROPIC,

7-96

MATERIAL TEMPDEP-K, 7-94

MATERIAL THERMO-ISOTROPIC, 7-81

MATERIAL THERMO-ORTHOTROPIC, 7-82

MATERIAL THERMO-PLASTIC, 7-84

MATERIAL TIMEDEP-K, 7-99

MATERIAL USER-SUPPLIED, 7-86

MATERIAL VISCOELASTIC, 7-90

MATRIX DAMPING, 7-215

MATRIX MASS, 7-214

MATRIX STIFFNESS, 7-213

MATRIX STRESS, 7-216

MATRIX USER-SUPPLIED, 7-218

MATRIXSET, 7-217

MEASURE, 6-96

MESH-CONVERT, 9-36

MODAL-DAMPING, 5-41

MOMENT-CURVATURE-FORCE, 7-143

MOMENT-TWIST-FORCE, 7-144

MONITOR, 5-100

MONITOR-CONTROL, 5-102

N

NASTRAN-ADINA, 3-23

NEUTRON-DOSE, 7-146

NEUTRON-TABLE, 7-147

NLTABLE, 8-100

NODESAVE-STEPS, 5-86


Command index

NODESET, 9-10

O

OVALIZATION-CONSTRAINT NODE, 9-60

OVALIZATION-CONSTRAINT POINT, 7-364

P

PARAMETER, 3-38

PAUSE, 3-36

PHI-MODEL-COMPLETION, 7-106

PLCYCL-ISOTROPIC BILINEAR, 7-107

PLCYCL-ISOTROPIC EXPONENTIAL, 7-109

PLCYCL-ISOTROPIC MEMORY-EXPONEN-

TIAL, 7-110

PLCYCL-ISOTROPIC MULTILINEAR, 7-108

PLCYCL-KINEMATIC ARMSTRONG-

FREDRICK, 7-111

PLCYCL-RUPTURE AEPS, 7-112

PLY-DATA, 7-187

POINT-SIZE, 8-83

PORE-FLUID-PROPERTY, 7-145

PORTHOLE, 5-83

POTENTIAL-INTERFACE ADINA-F, 7-358

POTENTIAL-INTERFACE FLUID-FLUID,

7-358

POTENTIAL-INTERFACE FLUID-

STRUCTUR, 7-358

POTENTIAL-INTERFACE FREE-SURFACE,

7-358

POTENTIAL-INTERFACE INFINITE, 7-360

POTENTIAL-INTERFACE INLET-OUTLET,

7-358

POTENTIAL-INTERFACE RIGID-WALL,

7-358

PPROCESS, 5-54

PRINT-STEPS, 5-81

PRINTNODES, 5-90

PRINTOUT, 5-78

PROPERTY NONLINEAR-C, 7-148

PROPERTY NONLINEAR-K, 7-149

PROPERTY NONLINEAR-M, 7-150

PROPERTYSET, 7-151

R

R-CURVE, 7-329

RAYLEIGH-DAMPING, 5-39

REACTION-NODES, 5-93

READ, 3-28

REBAR-LINE, 8-159

REBUILD-MODEL, 3-10

REDO, 4-10

REM-EDGE, 6-100

REM-FACE, 6-101

REUSE, 7-226

REUSE-NODES, 9-97

REVOLVE, 9-46

RIGIDITY-MOMENT-CURVATURE NONLIN-

EAR-ELASTIC, 7-153


Command index

RIGIDITY-MOMENT-CURVATURE PLASTIC-

MULTILINEAR, 7-155

RIGIDLINK, 7-334

RIGIDLINK-NODE, 9-59

RIGIDNODES SHELL, 9-13

RPROP, 7-392

RTOFILE, 3-35

RUBBER-MULLINS OGDEN-ROXBURGH,

7-125

RUBBER-ORTHOTROPIC HOLZAPFEL,

7-129

RUBBER-TABLE ARRUDA-BOYCE, 7-117

RUBBER-TABLE HYPER-FOAM, 7-119

RUBBER-TABLE MOONEY-RIVLIN, 7-113

RUBBER-TABLE OGDEN, 7-115

RUBBER-TABLE SUSSMAN-BATHE, 7-121

RUBBER-TABLE TRS, 7-123

RUBBER-VISCOELASTIC HOLZAPFEL,

7-127

RUPTURE MULTILINEAR, 7-158

RUPTURE THREE-PARAMETER, 7-159

RUPTURE-CURVE, 7-160

S

SAVENODES, 5-95

SCURVE, 7-161

SET-AXES-MATERIAL, 7-442

SET-AXES-STRAIN, 7-445

SET-INITCONDITION, 7-404

SFTHICKNESS, 6-48

SHEET PLANE, 6-145

SHELLDIRECTORVECTOR, 9-9

SHELLNODESDOF, 7-426

SHELLNODESDOF NODES, 9-8

SINGULAR, 7-330

SINGULAR NODES, 9-96

SIZE-FUNCTION AXIS, 8-91

SIZE-FUNCTION BOUNDS, 8-85

SIZE-FUNCTION COMBINED, 8-98

SIZE-FUNCTION HEX, 8-87

SIZE-FUNCTION PLANE, 8-95

SIZE-FUNCTION POINT, 8-89

SIZE-LOCATIONS, 8-99

SKEWSYSTEM NODES, 9-4

SKEWSYSTEMS CYLINDRICAL, 7-414

SKEWSYSTEMS EULERANGLES, 7-415

SKEWSYSTEMS NORMAL, 7-416

SKEWSYSTEMS POINTS, 7-417

SKEWSYSTEMS SPHERICAL, 7-418

SKEWSYSTEMS VECTORS, 7-419

SOLVER ITERATIVE, 5-53

SPLIT-EDGE, 6-68

SPLIT-FACE, 6-69

SPLIT-LINE, 6-33

SPRING LINES, 8-157

SPRING POINTS, 8-155

SSCURVE, 7-162


Command index

STIFFNESS-STEPS, 5-69

STRAIN-FIELD, 7-407

STRAINRATE-FIT, 7-166

SUBDIVIDE BODY, 8-81

SUBDIVIDE DEFAULT, 8-64

SUBDIVIDE EDGE, 8-77

SUBDIVIDE FACE, 8-79

SUBDIVIDE LINE, 8-68

SUBDIVIDE MODEL, 8-66

SUBDIVIDE POINT, 8-67

SUBDIVIDE SURFACE, 8-71

SUBDIVIDE VOLUME, 8-74

SUBSTRUCTURE, 7-225

SURF-ELEMDATA FLUID2, 7-209

SURF-ELEMDATA GENERAL, 7-206

SURF-ELEMDATA PLATE, 7-198

SURF-ELEMDATA SHELL, 7-200

SURF-ELEMDATA TWODSOLID, 7-190

SURFACE EXTRUDED, 6-42

SURFACE FACE, 6-148

SURFACE GRID, 6-39

SURFACE PATCH, 6-35

SURFACE REVOLVED, 6-44

SURFACE TRANSFORMED, 6-47

SURFACE VERTEX, 6-37

SURFACE-FUNCTION, 6-80

SWEEP, 9-50

SYSTEM, 6-3

T

TEMPERATURE-REFERENCE, 5-52

THERMAL-MAPPING, 7-413

TIMEFUNCTION, 5-64

TIMESTEP, 5-63

TMATERIAL TEMPDEP-K, 7-94

TMC-CONTROL, 5-18

TMC-ITERATION, 5-73

TMC-MATERIAL ISOTROPIC, 7-92

TMC-MATERIAL ORTHOTROPIC, 7-93

TMC-MATERIAL TEMPDEP-C-ISOTROPIC,

7-95

TMC-MATERIAL TEMPDEP-C-K, 7-98

TMC-MATERIAL TEMPDEP-C-

ORTHOTROPIC, 7-96

TMC-MATERIAL TEMPDEP-K, 7-94

TMC-MATERIAL TIMEDEP-K, 7-99

TMC-SOLVER ITERATIVE, 5-55

TOLERANCES GEOMETRIC, 5-74

TOLERANCES ITERATION, 5-76

TRANSFORMATION COMBINED, 6-85

TRANSFORMATION DIRECT, 6-87

TRANSFORMATION INVERSE, 6-94

TRANSFORMATION POINTS, 6-88

TRANSFORMATION REFLECTION, 6-89

TRANSFORMATION ROTATION, 6-90

TRANSFORMATION SCALE, 6-92

TRANSFORMATION TRANSLATION, 6-93


Command index

TRANSITION-ELEMENT, 8-58

TRUSS-LINE, 8-160

TRUSS-POINTS, 8-154

TWIST-MOMENT, 7-167

U

UNDO, 4-9

USER-FRICTION, 7-302

USER-RUPTURE, 7-333

V

VISCOELASTIC-CONSTANTS, 7-105

VOL-ELEMDATA FLUID3, 7-211

VOL-ELEMDATA GENERAL, 7-206

VOL-ELEMDATA THREEDSOLID, 7-192

VOLUME BODY, 6-147

VOLUME EXTRUDED, 6-57

VOLUME PATCH, 6-50

VOLUME REVOLVED, 6-54

VOLUME SWEEP, 6-60

VOLUME TRANSFORMED, 6-62

VOLUME VERTEX, 6-52

VOLUME-FUNCTION, 6-83

Z

ZOOM-BOUNDARY, 7-351

Error messages

ADINA R & D, Inc. A-1

Appendix 1 Error Messages General errors

Error Number Description

1002 Stiffness matrix not positive definite, boundary conditions or model collapsed 1003 Either the ADINA input file (*.dat) is missing or is incorrect 1004 Program not able to open the restart file, please check your input 1005 Not enough memory on the system to be allocated for the ADINA program 1006 Not enough memory allocated, sparse matrix indexes cannot fit into memory 1007 Node label cannot be zero or larger that the maximum label number 1008 Wrong input data, this is ADINA-F input data 1009 Wrong input data, this is ADINA-T input data 1010 Input data from an unsupported program version 1011 Restart from static to dynamic cannot be used if factorized K is reused 1012 Restart from dynamic analysis to static cannot be used if LDC is used 1013 Number of time functions in restart cannot be smaller than in the previous run 1014 Temperature loading used in a previous run but not in restart 1015 Model contains features not available in explicit time integrations 1016 Number of nonlinear element groups changed in the restart run 1017 Number of substructures changed in restart analysis 1018 Incorrect number of substructure stiffness blocks in the restart run 1019 Errors in reading restart file 1020 Element group data is changed in restart analysis 1021 Material model is changed in restart analysis 1022 Substructure reused different number of times in restart analysis 1023 The total number of DOFs changed for restart and substructure analysis 1024 Zero effective mass input in explicit time integration 1025 Restart time mismatch, please check your input data 1026 Temperature file cannot be opened 1027 Temperature gradient file cannot be opened

Appendix 1

A-2 AUI Command Reference Manual: Vol. I − ADINA- Model Definition

1028 External force file (IT58) cannot be opened 1029 Automatic time stepping not available for options used 1030 Program cannot find a license file or is not allowed to run on this platform 1031 Density cannot be set to zero in explicit time integration 1032 ISOBEAM, only 2-node elements can be used in explicit time integration 1033 Pipe elements cannot be used in explicit time integration 1034 Explicit time integration, material model cannot be used in this element group 1035 Potential based fluid elements cannot be used in explicit time integration 1036 User-supplied material model cannot be used in explicit time integration 1037 Material model in this element group cannot be used with initial stresses 1038 Number of nodal points equal to zero is not allowed 1039 The restricted number of nodes exceeded - 900 nodes maximum allowed 1040 Incorrect entry for temperatures, pipe pressure or forces read from a file 1041 Nodal forces provided on an external file cannot be used with substructures 1042 Wrong input for extended results printout for large strains 1043 Wrong input data for file provided forces, see DISK-STORAGE 1044 Fracture flag out of range, please check your input data 1045 Rigid beam-bolts cannot be used with cyclic symmetry 1046 Static correction for response spectrum can be used in linear analysis only 1047 Wrong formulation used, fluid potential and response spectrum 1048 Wrong formulation used, fluid potential and mode- superposition 1049 Solution (iteration) method is out of range, please see ITERATION METHOD 1050 Wrong flag for the automatic time-stepping method 1051 Input for number of subdivisions is wrong (negative!), see AUTOMATIC

TIME-ST 1052 Large strains extended printing flag is wrong see PRINTOUT LARGE-

STRAINS 1053 Automatic load displacement (LDC) method cannot be used in crack

propagation 1054 Incorrect main fracture input flags (see FRACTURE...) 1055 Frequency calculation cannot be done in static analysis 1056 Determinant search cannot be used to calculate frequencies within interval 1057 Frequency file is missing, it is required to perform modal analysis

Error messages


1058 Number of frequencies and mode shapes stored on file is smaller than requested

1059 Response spectrum analysis cannot be used with cyclic symmetry 1060 Number of frequencies requested is larger than number frequencies calculated 1061 Response spectrum analysis cannot be performed without translational DOFs 1062 Automatic load-displacement (LDC) method can only be used in static

analysis 1063 Automatic load-displacement (LDC) method can only be used in nonlinear

analysis 1064 Automatic load-displacement (LDC) method cannot be used in linearized

buckling 1065 LDC method, wrong node label used in the first step loading 1066 LDC method � DOF used for the prescribed first step displacement is incorrect 1067 LDC method � maximum allowable displacement(DISPMAX) cannot be

negative 1068 Incorrect input data for fluid-structure analysis (FSI) 1069 Error in STIFFNESS-STEPS or EQUILIBRIUM-STEPS input data 1070 Error in printing or saving block input data 1071 Number of linear, nonlinear and substructure element groups is equal to zero 1072 Potential based fluid element flag is incorrect 1073 Potential based fluid elements cannot be used with substructures 1074 Potential based fluid elements cannot be used with lumped damping 1075 Potential based fluids cannot be used with the subspace iteration method.

Only determinant search or Lanczos method can be used. Note: For large problems or mid-size problems with a large number of frequencies requested, the Lanczos method should be used.

1076 Potential based fluid elements can not be used with lumped mass matrix 1077 Input error, time step cannot be equal to or smaller than zero 1078 Flag to request reaction calculations is incorrect 1079 Damping can only be included in dynamic analysis 1080 Wilson method cannot be used with the automatic time stepping (ATS) method 1081 Lumped mass has to be used for the explicit time integration 1082 Frequency calculation cannot be used with explicit time integration 1083 Damping flag is incorrect

Appendix 1


1084 Only lumped damping can be used in explicit time integration 1085 Consistent mass matrix cannot be used with substructures 1086 Damping cannot be used with substructuring 1087 Mode superposition analysis cannot be used with substructuring 1088 Linearized buckling cannot be used in dynamic analysis 1089 Frequency calculation cannot be requested when substructuring is used 1090 Initial imperfections cannot be used with substructures 1091 Explicit time integration cannot be used with substructures 1092 Mode superposition can be performed if mass matrix assemblage is requested 1093 Automatic load-displacement (LDC) method cannot be used with thermal

loading 1094 User-supplied loading cannot be used with automatic load-displacement

method 1095 Contact surfaces cannot be present in mode superposition analysis 1096 Factorized stiffness matrix cannot be stored, explicit time integration used 1097 Displacements cannot be prescribed in mode superposition analysis 1098 Linearized buckling cannot be performed in linear analysis 1099 Centrifugal loading cannot be used with substructures 1101 Mesh too distorted, Jacobian determinant not positive 1102 Contact conditions inadmissible (either wrong contact orientation or

divergence) 1103 No convergence, concrete material model, stresses outside the failure curve 1104 Mixed (u/p) formulation � an internal matrix cannot be inverted 1105 No convergence in the iterative solver 1106 No convergence in plasticity (bisection algorithm) 1107 No convergence in the Drucker-Prager material model 1108 No convergence in the creep material model 1109 No convergence in orthotropic plasticity (bisection) 1110 No convergence in rubber-like material model 1111 Green-Lagrange strains beyond theoretical limit 1112 No convergence in the moment-curvature material model 1113 Strains out-of-range � nonlinear elastic material model 1114 No stress convergence in the Gurson material model

Error messages


1115 FSI load calculation problem, time step reduced 1116 Insufficient memory for double-sided contact (could be due to divergence) 1117 Mesh too distorted � BEAM distributed load calculation 1118 Zero pivot � probably wrong boundary conditions 1119 No convergence in Mohr-Coulomb material model 1120 Divergence, energy greater than 1.E30, model crushed, time step probably too

large 1121 Rigid contact, time step reduced due to tensile contact 1122 BEAM elements, program stopped in material model calculations 1123 Solution is diverging, time step reduced, solution continues 1124 No convergence in the concrete material model 1125 Invalid energy value (either NaN or Inf) in the convergence check 1126 A division by zero in the BEAM element, program might be diverging 1127 3-D solid elements, ULH � eigenvector cannot be calculated 1128 Incompatible mode elements � an internal matrix cannot be inverted 1130 No convergence in the foam material model (bisection algorithm) 1131 No convergence in element pressure calculations, mixed u/p elements 1132 SHELL elements � mesh too distorted

1133 Rigid target contact algorithm, time step reduced due to excessive penetration 1197 Probably too many nodes suddenly in contact, program takes a smaller step 1198 Rigid contact internal error, non-unique contact surface definition 1199 Program internal error 1201 Not enough memory to store nodal coordinates, probably gaps in node

numbering 1202 Total number of constraint equations is incorrect 1203 Constraint equations are out of order 1204 Node numbers input for constraints is incorrect 1205 Constraint equations � Incorrect number of degrees of freedom 1206 Constraint equations � incorrect number of independent degrees of freedom 1207 An independent degree of freedom is used as a dependent in constraints 1208 Fluid DOF can only be constrained to another fluid DOF 1209 An independent DOF has to be an active DOF, i.e., cannot be a "fixed" DOF 1210 Rigid links must be input in ascending order

Appendix 1


1211 Incorrect input for a rigid link number 1212 Flag indicating type of rigid link (linear or nonlinear) is incorrect 1213 Nonlinear rigid links cannot be used in linear analysis 1214 Linear rigid links must be input before nonlinear links 1215 Rigid links cannot be used with SHELL having 5 DOFs 1216 Independent DOFs are not allowed on slave rigid links nodes 1217 Master rigid link nodes must have all independent DOFs 1218 Number of constraint equations with bolts is incorrect 1219 Rigid bolts cannot be connected to shell elements with 5 DOFs 1220 Slave nodes of rigid bolts must have all DOFs constrained 1221 A constrained degree of freedom (DOF) by a rigid bolt must be free 1222 Bolt constraints cannot be generated, independent DOFs are missing 1223 There are no potential fluid degrees of freedom for marked structural DOFs 1224 Allocated memory too small to store stiffness matrix 1225 Insufficient allocated memory 1226 Insufficient allocated memory. More than 1000 blocks need to be created. 1227 Rigid bolt, translational DOFs are constrained 1228 SHELL elements, an averaged director vector has zero magnitude 1229 Rigid bolt, translational DOFs are constrained 1230 Incorrect flag for convergence criteria, see TOLERANCES ITERATION

CONVERGENCE 1231 Incorrect convergence criteria in mode superposition, only energy can be used 1232 Reference force in force convergence criteria must be greater than zero 1233 Reference translation in displacement convergence must be greater than zero 1234 Reference moment in force convergence criteria must be greater than zero 1235 Reference rotation in displacement convergence must be greater than zero 1236 Reference value of initial imperfections cannot be specified on constrained

DOF 1237 Initial strain flag is incorrect 1238 Time on temperature tape does not match solution starting time 1239 Temperature tape steps do not match steps in ADINA, use DISK-S

TEMP=INTERPOLATE 1240 Director vectors can only be generated if Euler angles are used

Error messages


1241 Incorrect input for SHELL director vectors 1242 Skew system number in nodal input data is incorrect 1243 Coordinate system type is incorrect 1244 Mid-surface vector number is greater than total number of director vectors 1245 Number of degrees of freedom allowed in analysis is incorrect 1246 The fluid DOF is incorrect, it can be free, fixed or constrained 1247 SHELL 5/6 DOF indicator is incorrect. It should be 0 or 1. 1248 End-of-file when reading, temperature or pipe pressure external file 1249 No fluid (PHI) DOF for marked structural degrees of freedom 1250 Total number of equations is zero. At least one equation is required. 1251 Incorrect element type input, please check your data 1252 Contact element groups must be input after ALL element group data 1253 Specified number of element groups is different than the number read from

input 1254 Specified number of contact groups is different than the number read from

input 1255 Crack growth, stiffness must be reformed every step 1256 A node with assigned pressure DOF has not been used in any element group 1257 Incorrect input data for rigid-bolt element 1258 Number of elements connected to 1 node exceeds the value specified in input 1259 LDC-initial displacement imposed on a deleted or constrained DOF 1260 Substructure identification number incorrect 1261 Substructures � local X vector has zero length, please check your input 1262 Substructures � local Y vector has zero length, please check your input 1263 Substructures � local X&Y vectors are not orthogonal, please check your input 1264 Substructures � incorrect connectivity array, please check your input 1265 Substructures � error in printing or saving block input data 1266 Time integration method incorrect, can be implicit or explicit 1267 Wilson-theta method, theta incorrect, see ANALYSIS DYNAMIC METHOD 1268 Newmark method, incorrect parameters, see ANALYSIS DYNAMIC

METHOD 1269 Dynamic analysis, time step too small 1270 An unsuccessful attempt has been made to read a direct access file

Appendix 1


1271 An unsuccessful attempt has been made to write into a direct access file 1272 Incorrect maximum number of DOF per node, input probably is not correct 1273 Mode superposition analysis requires number of modes greater than zero 1274 Program internal error, very likely memory corrupted 1275 Slave DOFs cannot be connected to multiple rigid links 1276 Incompatible options for centrifugal force calculation

Element-based centrifugal force calculation option cannot be used if a lumped mass matrix is specified for the problem.

1277 Incompatible options for centrifugal force calculation. Deformation-dependent centrifugal loading cannot be used with element-based centrifugal force calculation option.

1278 PHI massflux loads can only be used with potential-based elements 1279 The number of elements in the restart run is different than in the previous run 1280 Explicit analysis TOTALTIME option, can only be used with one time step

block 1281 Explicit time integration method cannot be used with potential fluid elements 1282 Constraint equation cannot be defined along prescribed direction 1283 Incompatibility between time functions in the fluid and structural models 1284 Rigid target, different number of processors used in restart than in a previous

run 1285 No active degrees of freedom (DOF) are present 1286 The number of time step blocks limit has been exceeded 1287 Error in the reading of time function input data. Please check your input. 1288 Error in the skew coordinate system input (inadmissible direction cosines) 1289 Incorrect input data for substructures 1290 Substructure � no. of condensed and retained nodes is not equal to total no. of

nodes 1291 No convergence. Invalid energy value (either NaN or Inf) in the convergence

check 1292 Incorrect displacement vector, invalid displacement values (either NaN or Inf

entries) 1293 Error in closing a porthole file (porthole splitting option) 1294 Explicit time integration cannot be used with thermal loading provided via tape 1295 Damping elements can only be used if damping is requested in the master

input

Error messages


1296 TMC, different meshes for heat transfer and structure analysis cannot be used 1297 Nodal mass input, non-existing node numbers(labels) are used 1298 Nodal damping input, non-existing node numbers(labels) are used 1299 Incorrect domain decomposition, contact nodes belong to a wrong subdomain

Appendix 1


Element error messages (during element group input)


1301 Incorrect kinematic formulation used for element group 1302 Element death/birth option flag is out of range 1303 Truss element type out-of-range 1304 Truss-gap element flag is incorrect 1305 Incorrect maximum number of nodes per element 1306 Incorrect number of element integration points 1307 Incorrect material model number for an element group 1308 Incorrect number of material constants 1309 The total number of elements in an element group is ZERO 1310 Element death/birth cannot be used with linear elements 1311 Gap elements cannot be used as linear elements 1312 Material model used requires nonlinear element groups 1313 Truss-ring element cannot have more than 1 node 1314 Truss-ring element cannot be used with skew systems 1315 Truss-ring element cannot have gap options 1316 Incompatible (bubble function) elements cannot be defined as mixed (u/p)

elements 1317 No skew system defined, elements cannot have nodes referred to a skew

systems 1318 Temperature is required for the specified material model 1319 The gap option can only be used with 2-node elements 1320 Input error in element group control parameters 1321 Young�s modulus must be greater than zero 1322 Young�s modulus must be greater than zero for all temperatures 1323 Incorrect material properties, nonlinear elastic model 1324 Incorrect material constants for a plastic material model 1325 Incorrect input data for plastic-multilinear material 1326 Incorrect input for strain rate effects 1327 Incorrect input for creep material model 1328 Material type number is out of range

Error messages


1329 Element birth time must be smaller than death time 1330 Incorrect flag for spatial isotropy correction 1331 Energy release rate cannot be performed with fracture mechanics 1332 Mixed formulation cannot be used for some material models 1333 Wrong number of pressure points for mixed elements 1334 Incorrect number of temperature points-creep/plasticity 1335 Stress table flag out of range 1336 Soil material models cannot be used in plane stress analysis 1337 Incorrect number of curve points- user-supplied material 1338 Large strain analysis is not allowed for material model used 1339 Energy release rate can only be calculated in linear analysis 1340 Fabric material model can only be used in plane stress analysis 1341 Mixed elements cannot be used for plane stress analysis 1342 Temperature flag incorrect for concrete material model 1343 Stress tables cannot be used with the specified material 1344 Initial strains/stresses cannot be used in linear analysis or flags are incorrect 1345 Incorrect flags for user-supplied creep coefficients 1346 Incorrect flag to calculate strain energy densities 1347 Incorrect number (negative) of axes of orthotropy sets 1348 SHELLs - incorrect number of nodes in the surface direction 1349 Incorrect number of integration points through the thickness 1350 Total number of nodes must be greater or equal than number of midsurface

nodes 1351 Multi-layer SHELL can only have mid-surface nodes 1352 Improper section type specified for a BEAM element group 1353 Incorrect flag for stress output tables 1354 Moment-curvature law cannot be used with this material model 1355 Incorrect ISOBEAM element cross section type 1356 Incorrect thickness table number for ISOBEAM elements 1357 PLATE element � requested material model is not available 1358 PLATE element � initial flexural strains input is required 1359 Elements require nodal initial strain/stress input which is not provided

Appendix 1


1360 PIPE internal pressure cannot be used with linear pipe elements 1361 PIPE with ovalization is requested but ovalization DOFs are specified 1362 Improper input for a PIPE element 1363 Flange conditions used, which requires Newton-Cotes integration along PIPE

axis 1364 Only 4-node PIPE element can be used with warping/ovalization DOFs 1365 Full Newton iteration must be used in contact analysis 1366 CONTACT � at least three contact surface nodes must be specified 1367 CONTACT � at least one contact surface must be specified 1368 CONTACT � at least one contact surface pair must be specified 1369 Total number of contact nodes must be GT or EQ to the number of contactor

nodes 1370 2-D CONTACT can only be: plane stress, plane strain or axisymmetric 1371 No skew system defined, contact surface nodes cannot refer to skew systems 1372 CONTACT model out-of-range, can be: frictionless or with friction 1373 Friction in explicit analysis cannot be used with selected contact algorithm 1374 3-D CONTACT � number of contactor nodes must be greater or equal to 1 1375 3-D CONTACT � total number of contact nodes must be greater or equal to 5 1376 3-D CONTACT � at least one segment must be attached to a contact surface

node 1377 Generalized plane strain-skew system cannot allow rotations around the

X-axis 1378 Incorrect number of material data sets, please check your material input data 1379 Incorrect node number input for strain energy release calculation 1380 Triangular elements can only have 3 or 6 or 7 nodes 1381 Maximum number of nodes exceeded for a 2-D element 1382 Incorrect material data set number, please check your input data 1383 Element birth time must be smaller than element death time 1384 Porous solid elements cannot be used with explicit time integration 1385 SHELL � maximum number of nodes per element exceeded 1386 Nonsymmetric moment-curvature cannot be used with this beam model 1387 Cyclic elastic rigidity not permitted for this beam model 1388 Cannot use more than one pressure DOF in 3-node triangular elements

Error messages


1389 Cannot use more than one pressure DOF in 4-node tetrahedral elements 1390 Rigid target contact can only be used with ATS method 1391 Errors in contact segment definitions 1392 Consistent contact linearization cannot be used with direct solver 1392 Tied contact is not available in explicit time integration 1394 Large strain formulation cannot be used with multilayered shell element 1395 Incompatible modes elements: integration order must be greater than 1 1396 Error in the shell element group data, please see the *.out file for details 1397 Error in the element group control parameters, skew systems not indicated 1398 One (or more) of the element node numbers is either negative or undefined 1399 Incorrect number of nodes in a TRUSS element, program stops

Appendix 1


Temperature error messages, rigid links, loadings, etc.


1401 Time mismatch between temperature file and program, use option interpolate 1402 Time mismatch between temperature gradient file and the program, use option

interpolate 1403 Time mismatch, pipe internal pressure file, use option interpolate 1404 Time mismatch between nodal force file and the program, use option

interpolate 1405 Rigid links � fixities applied to a slave node conflicts with a motion of a

master node 1406 Pipe internal pressure is either missing or should not be present in the restart

file Note: if pipe internal pressure is present in the first run, the it has to be present in subsequent restart runs. The opposite also holds. I f there is no pipe internal pressure in the first rune, then the pipe internal pressure cannot be applied in subsequent runs.

1407 Empty 1408 Program internal error � true cyclic symmetry and computing nonlinear

constraints 1409 Rigid links � one rotation free and different skew systems used for M&S

nodes 1410 Rigid links � only 2 translations free and different skew systems for M&S

nodes 1411 Rigid links � only 1 translation free and different skew systems for M&S

nodes 1412 Temperature outside range of material property temperatures 1413 BEAM pressure loading input error, incorrect component indicator 1414 Concentrated load input data, loading cannot be generated 1415 BEAM pressure loading input error, zero length between nodes 1416 FSI, temperature file incorrect. Time span for structure is smaller than for

fluid. The time span is equal to the total number of time steps multiplied by the time step value.

1417 FSI, temperature gradient file incorrect. Time span for structure is smaller than for fluid

1418 FSI, pipe int. pr. file incorrect. Time span for structure is smaller than for fluid

Error messages


1419 Fracture, ratio of J-integral/(nodal displacement) is larger than the resistant curve

1420 Fracture, the crack increment is negative, program stops 1421 Fracture, the J-integral number is out of range, program stops 1422 Fracture � internal error, please see *.out file for more information 1423 Fracture, the number of crack nodes or rings is negative 1424 Fracture, the flag for virtual vector calculation is out of range 1425 Fracture, a crack node cannot be smaller or equal to zero 1426 Fracture, a crack node degree of freedom cannot be smaller or equal to zero 1427 Fracture, no J-integral specified for crack growth control 1428 Fracture, the number of nodes in the material shift is too small 1429 Fracture, no temperature input for temperature-dependent resistance curves 1430 Fracture, temperature at crack tip node out-of-range of resistance curves 1431 Fracture, nodes on the crack propagation surface cannot be constrained 1432 Fracture, a negative crack increment, please check the resistance curve 1433 Fracture, the end of propagation surface has been reached 1434 Fracture, crack increment is zero, please check your input 1435 Mixed-interpolated (u/p) elements cannot be used with incompatible modes 1436 Shells - element temperatures are outside material property parameters 1437 Initial temperature is outside the range of material property temperatures 1438 Fracture mechanics, incorrect crack front node number 1439 Concrete model, initial temperature must be equal to reference temperature 1440 Curve description material, gravitational strain is outside the material curve 1441 Curve description material, error in pressure-volumetric strain calculations 1442 Curve description material model cannot be used with plane stress elements 1443 Crack front node number is out of range, please check your input data 1444 Zooming, incorrect solution starting time for the zoomed model 1445 Unit containing pipe internal pressure can not be opened as requested by input 1446 Input error in temperature loading data 1447 A file unit could not be opened as requested by the input 1448 Temperature gradients can only be specified on SHELL midsurface nodes 1449 BEAM pressure load cannot be generated. Incorrect input.

Appendix 1


1450 Deformation dependent loading cannot be imposed on substructures 1451 Pressure (distributed) load is applied on non-existing nodes 1452 Pressure (distributed) loading, illegal face number 1453 Incorrect time function number specified for a load 1454 A distance between points defining an axis of rotation is zero or too small 1455 Contact slip load, contact surface, on which load is applied, does not exist 1456 Incorrectly applied contact slip load 1457 Input error in contact slip load 1458 Input error in concentrated load data 1459 Follower concentrated loading, incorrect input data 1460 Input error in electromagnetic load 1461 Ground motion loading is used with conflicting options 1462 Incorrectly applied load on a generalized plane strain element 1463 Prescribed displacements cannot be generated between two load sets 1464 A prescribed displacement is applied on a non-existing node 1465 Isobeam pressure load, incompatibility between face and auxiliary node

numbers 1466 Incorrect pressure load data 1467 Pressure loading, incorrect load direction (x-axis) for y-z plane elements 1468 Input error in pipe internal pressure loading data 1469 Input error in pressure loading data 1470 FSI stress loading � FSI boundaries cannot be applied on substructures 1471 FSI (Fluid-Structure-Interaction) cannot be used with cyclic symmetry 1472 Input error in FSI boundaries (structural model) 1473 FSI forces, incorrect FSI boundaries in the structural model 1474 Potential-based fluid elements, loading used with conflicting options 1475 Potential-based fluids, error in load calculations due to mass fluxes 1476 Potential fluids, error in load calculations due to element face pressure 1477 Constrain equations cannot be applied to non-existing nodes 1478 Constrain equations, degree of freedom not marked as constrained 1479 Constrains, the independent degree of freedom is either fixed or constrained 1480 Rigid links cannot be applied to non-existing nodes

Error messages


1481 A potential-based fluid interface element is not attached to a fluid element 1482 Incorrect input for 2-D flow load data 1483 Incorrect input for 3-D flow load data 1484 Input error in user-supplied loading data 1485 Incorrect input for fracture mechanics data 1486 A temperature file is requested but is either missing or not correct 1487 Error in shell element stress calculations 1488 Error in TMC analysis, only 2D and 3D elements are allowed 1489 Some of the master nodes used in constraints should be retained (shared)

nodes

Appendix 1


Initial stress & element group error messages


1501 TRUSS-initial stresses can be used for linear elastic material only 1502 2-D SOLID � initial stresses can only be used for elastic & soil materials 1503 3-D SOLID � initial stresses can only be used for elastic & soil materials 1504 BEAM � initial stresses can only be used for linear elastic material model 1505 ISOBEAM � initial stresses can only be used for linear elastic material model 1506 PLATE � initial stresses can only be used for linear elastic material model 1507 SHELL � initial stresses can only be used for linear (iso & ortho) materials 1508 PIPE � initial stresses can only be used for linear elastic material model 1509 2-D POROUS � initial stresses can only be used with elastic and soil

materials 1510 3-D POROUS � initial stresses can only be used with elastic and soil

materials 1511 PLATE � initial strains cannot be used with the Ilyushin material model 1512 Material model used is not permitted in CDM with mixed u/p elements 1513 Program internal error, KPP matrix is not invertible, mixed u/p elements 1514 Program internal error, a matrix is not invertible, mixed nonlinear u/p

elements 1515 2-D solid elements, incorrectly collapsed nodes, numbering sequence should

be changed 1516 Plane stress elements have to have thickness provided via input(positive

value) 1517 Energy release rate cannot be requested for more than three nodes 1518 Node numbers cannot be negative, please check your input data 1519 Incorrect 3-D transition element, nodes 22 & 27 can only be used in 27-node

bricks 1520 Incorrect 3-D transition element, node 21 can only be used in 21-node bricks 1521 Axes of orthotropy and initial strains axes have to be orthogonal 1522 Maximum number of nodes exceeded for a 3-D solid (or fluid) element 1523 Incorrect number of nodes describing a 3-D solid (or fluid) element 1524 A transition elements cannot be a true tetrahedral element 1525 BEAM elements � incorrect input for a stress table

Error messages


1526 BEAM elements � incorrect input for rigid end offsets 1527 BEAM (or ISOBEAM or PIPE) elements- incorrect auxiliary node number 1528 BEAM elements � zero cross-sectional area 1529 BEAM elements-negative rigidity input, the value must be greater or equal

zero 1530 BEAM elements � incorrect input in the nonlinear elastic material data 1531 3-D solid elements, ULH � eigenvector cannot be computed 1532 Curve-description material, gravitational strain is too large 1533 Incompatible mode elements � a matrix is not invertible 1534 Ogden material model, initial strains are too large 1535 Mooney-Rivlin model, initial strains are larger than a maximum allowable

value 1536 Foam material model, initial strains are larger than a maximum allowable

value 1537 Invalid contact algorithm type 1538 Curve-description material model, incorrect volumetric pressure 1539 Curve-description material, current volumetric strain is outside the table input 1540 2D contact surface offsets cannot be based on shell thickness 1541 Layered shell elements, incorrect input for a layer number 1542 Layered shells, incorrect input data, pleas see the *.out file for details 1543 Specified material model or failure criterion is not used by any layered shell 1544 Error in the layered-shell input data, please see the *.out file for details 1545 Incorrect number of shell thickness tables for layered-shell elements 1546 Truss elements with gap, gap width cannot be negative 1547 Initial strains are too large 1548 BEAM element, error in the end release, very likely rigid body motion 1549 Incorrect thickness for isobeam axisymmetric or plane stress or strain

elements 1550 Incorrect number of nodes describing an ISOBEAM (or PIPE) element 1551 ISOBEAM or PIPE elements � incorrect input for a stress table 1552 Stress printing or saving flag is incorrect 1553 isobeam(axisymmetric, plane stress/strain) elements must lie in the y-z plane 1554 Incorrect element configuration, the length cannot be smaller than zero

Appendix 1


1555 ISOBEAM, both section dimensions have to have values greater than zero 1556 BEAM, ISOBEAM or PIPE elements � auxiliary node is not specified 1557 Element is not in a plane as required 1558 Auxiliary node cannot coincide or lie on a straight line with element nodes 1559 BEAM, ISOBEAM or PIPE � element nodes cannot have the same

coordinates 1560 Incorrect number of nodes describing PIPE element 1561 Incorrect kinematic formulation requested for surface tension elements 1562 Surface tension elements, zero distance between nodes 1563 Incorrect number of composite shell failure sets 1564 SHELL elements, incorrect stress table input data 1565 Incorrect composite shell failure criterion number 1566 Incorrect number of nodes specified for a SHELL element 1567 Incorrect thickness table number for a SHELL element 1568 Incorrect transition SHELL element 1569 Error in the pressure-load shell-stiffness option 1570 Input error in shell stress resultant calculations 1571 Incorrect node definition for a SHELL element 1572 SHELL � director vectors cannot be created, incorrect element nodal data 1573 Incorrect bend radius for a PIPE element 1574 Incorrect input for a PIPE flange data 1575 Incorrect PIPE cross section dimensions 1576 Incorrect input data for 2-D contact elements 1577 Variable contact friction requested for contact pair & not specified for

CGROUP 1578 Contact nodes refer to skew systems which is not indicated in control input 1579 Node-to-node cont, prescribed displacements cannot be applied to contactor

nodes 1580 Zero mass on contact nodes is not allowed in explicit time integration 1581 Post-impact calculation, zero mass on contact nodes is not allowed 1582 Incorrect input data for 2-D rigid target contact 1583 Incorrect input data for 3-D contact elements 1584 3-D contact, incorrect contact segment number

Error messages


1585 3-D contact, program internal error 1586 Incorrect input data for 3-D rigid-target contact 1587 General spring elements � input data errors 1588 Input error in 2-D fluid elements, please see *.out for details 1589 Input error in 3-D fluid elements, please see *.out for details 1590 Memory corrupted in 2-D fluid elements 1591 Memory corrupted in 3-D fluid elements 1592 Incorrect number of nodes for a spring element 1593 Potential-based infinite elements cannot be triangular 1594 Potential-based interface elements, incorrect number of nodes in an element 1595 Potential-based fluid elements, input error in material data 1596 General (spring, damping or mass) elements, incorrect property set number 1597 Incorrect input data for general (spring, damping or mass) elements 1598 Incorrect input data for a user-supplied general element 1599 Incorrect input data for a CGAP element

Appendix 1


Frequency solution and element group error messages


1601 Frequency � negative/zero diagonal element before decomposition. Incorrect model.

1602 Frequency � too many negative diagonal elements, please check your model 1603 Number of mass DOFs is smaller than the number of requested frequencies 1604 Frequency � rigid body shift input must be negative

(FREQUENCIES...RSHIFT=-...) 1605 Frequency � zero pivot after decomposition, rigid body shift should be applied 1606 Frequency cannot be calculated for a single DOF, mass is not greater than

zero. 1607 Frequency, determinant search method � rigid body mode found 1608 Determinant search method � lower bound of the first frequency not found,

incorrect model 1609 Determinant search method � non-positive calculated shift, probably incorrect

model 1610 Frequency calculation � no eigenvalue computed, please check your model 1611 Frequency-no eigenvalue computed, check for rigid body without fluid effects 1612 Determinant search method � upper bound of current eigenvalue not found,

incorrect model 1613 Frequency � non-positive or too small calculated shift, probably incorrect

model 1614 Frequency, potential based fluids � no convergence to rigid body mode 1615 Multi-block solution cannot be used if mass/stiffness are imported from file 1616 Could not factorize A*F=B � frequency and potential based fluid elements 1617 No convergence in eigensolver, please check your model or solution

parameters 1618 Solution for linearized buckling failed, please check your model 1619 No convergence, subspace iteration, increase no. of iterations/starting vectors 1620 Upper bound for the first critical buckling load not found 1621 FREQUENCIES, interval too narrow, use higher value for FMAX or lower

for FMIN 1622 Sturm sequence failed, no eigenvalue found, please check your model 1623 Frequencies, matrices not positive and no shift applied

Error messages


1624 Frequency calculations failed, matrices not positive 1625 Frequencies, matrices not positive after a sweep or no shift applied 1626 Frequencies, JACOBI iteration could not converge, please check your model 1627 Lanczos method, stiffness matrix not positive definite, please check your

model 1628 Lanczos method, not enough memory, please increase allocation for ADINA 1629 Lanczos method � internal error, please check your model 1630 Mode superposition, potential based fluid elements- program internal error 1631 Sturm sequence shows that incorrect number of frequencies has been

calculated 1632 Mode superposition cannot be done with rigid body motions and potential

fluids 1650 Estimated storage less than actual storage for element group - internal error

Appendix 1


Material data errors


1701 BEAM � bending table (R-T plane) input data cannot have negative values 1702 BEAM � bending table (R-T plane) input data cannot have zero values 1703 BEAM � multiplier used to compute stiffness of rigid end zones is negative 1704 BEAM � axial force table input data cannot have negative values 1705 BEAM � axial force table input data cannot have zero values 1706 BEAM � torsion table input data cannot have negative values 1706 BEAM � torsion table input data cannot have zero values 1708 BEAM � bending table (R-T plane) input data is not in ascending order 1709 BEAM � axial force table input data is not in ascending order 1710 BEAM � torsion table input data is not in ascending order 1711 BEAM � bending table (R-S plane) input data cannot have negative values 1712 BEAM � bending table (R-S plane) input data cannot have zero values 1713 BEAM � bending table (R-S plane) input data is not in ascending order 1714 BEAM � axial, bending, torsional cyclic factors must be greater or equal to

1.0 1715 Isotropic elastic material, Young's modulus and/or Poisson ratio is incorrect 1716 BEAM, rigidity, FORCE-AXIAL table, curve n-th slope is larger than the n-1

slope 1717 BEAM, rigidity, MOMENT-R (twist) table, n-th slope is larger than the n-1

slope 1718 BEAM, rigidity, MOMENT-S table, curve n-th slope is larger than the n-1

slope 1719 BEAM, rigidity, MOMENT-T table, curve n-th slope is larger than the n-1

slope 1720 Material creep-variable, effective stress is out of the stress range input 1721 Material creep-variable, yield curve cannot be interpolated, incorrect input 1722 Integration point temperature is outside material temperature range 1723 Material creep, integration point initial temperature is outside material

temperature 1724 Material concrete, cut-off tensile stress SIGMAT has to be greater than zero

Error messages


1725 Material concrete, incorrect input for SIGMAC, SIGMAU and/or EPSC, EPSU

1726 Zero point in axial force table not found 1727 Zero point in torsion table not found 1728 Position of zero point in torsion table varies with axial force 1729 Zero point in bending (R-T plane) table not found 1730 Position of zero point in bending (R-T) table varies with axial force 1731 Zero point in bending (R-S plane) table not found 1732 Position of zero point in bending (R-S) table varies with axial force 1733 Insufficient data points in axial force table (positive side) 1734 Insufficient data points in axial force table (negative side) 1735 Insufficient data points in torsion table (positive side) 1736 Insufficient data points in torsion table (negative side) 1737 Insufficient data points in bending (R-T plane) table (positive side) 1738 Insufficient data points in bending (R-T plane) table (negative side) 1739 Insufficient data points in bending (R-S plane) table (positive side) 1740 Insufficient data points in bending (R-S plane) table (negative side) 1741 Visco-elastic shear model, decay constants in Prony series cannot be equal to

zero 1742 Visco-elastic shear model, number of terms in Prony series cannot be greater

than 5 1743 Visco-elastic bulk mass, decay constants in Prony series cannot be equal to

zero 1744 Visco-elastic bulk mass, number of terms in Prony series cannot be greater

than 5 1745 User-supplied material, no convergence in effective plastic strain 1746 No convergence in plasticity. Using automatic time stepping might help. 1747 No convergence in the creep model. Using automatic time stepping might

help. 1748 Strains outside input data, nonlinear elastic material model, truss elements 1749 Input error in irradiation creep property table input 1750 Input of mixed hardening parameters for von-Mises plasticity is incorrect 1751 Error in the optional printing for the large strain (ULH) formulation 1752 Input error in the material property data for 2-D solid elements

Appendix 1


1753 Input error in the gasket material property data set 1754 Input error in the material property data for 3-D solid elements 1755 BEAM elements � error in the elasto-plastic moment- curvature input 1756 BEAM elements � error in the user-supplied material data 1757 BEAM elements � incorrect cross-section input data 1758 Orthotropic material model, incorrect material data 1759 Error in the truss material data input 1760 Fabric material model, material axis angle larger than 2*PI 1761 Incorrect material data input for the fabric model 1762 Incorrect material properties for a thermo-orthotropic material model 1763 BEAM element, plasticity, shear reduction factor must be smaller than 1.0 1764 Isotropic elastic material, coefficient of thermal expansion is negative 1765 Input error in the material property data for isobeam elements 1766 Input error in the material property data for plate elements 1767 Input error in the material property data for SHELL elements 1768 Input error in (composite) shell failure criteria 1769 Input error in the material property data for pipe elements 1770 Input error, SHELL orthotropic plasticity, constituent matrix not positive

definite 1771 User-supplied material model, material axis angle larger than 2*PI 1772 thermo-orthotropic material model, material axis angle larger than 2*PI 1773 Orthotropic material model, material axis angle larger than 2*PI 1774 Porous elements, porous properties not available for material model used 1775 Input error in the material property data for 2-D porous elements 1776 Input error in the material property data for 3-D porous elements 1777 Incorrect material model for the gap element 1778 No initial stress input for Cam-Clay material model

Error messages


General errors, messages


1801 No convergence, iteration limit reached, automatic time stepping might help 1802 No convergence, out-of-balance load too large, automatic time stepping might

help 1803 Zero (or almost zero) length between element nodes 1804 Zero (or almost zero) length of the orthotropic material axes vector 1805 Number of nodes exceeds the limit (900) 1806 Mapping Interface error, please contact ADINA R&D, Inc. 1807 Mapping program internal error, please contact ADINA R&D, Inc. 1808 Incorrect displacement boundary conditions for cyclic symmetry 1809 Incorrectly prescribed displacements on cyclic parts 1810 the number of prescribed displacements is greater than requested in the input 1811 Prescribed displacement unloading option cannot be used in linear analysis 1812 Incorrect degree of freedom (DOF) entry in the prescribed displacement input 1813 Arrival time cannot be negative. This holds for all load cases. 1814 Incorrectly prescribed displacements in cyclic symmetry analysis 1815 Internal error in cyclic symmetry, program stops 1816 A shell node on the cyclic boundary cannot have 5 degrees of freedom 1817 Cyclic symmetry, Y direction for nodes on the center line is not constrained 1818 Error(s) in cyclic symmetry 1819 Number of prescribed displacements is changed from one cyclic part to

another 1820 Skyline solver (COLSOL) cannot be used with consistent contact algorithm 1821 Periodic symmetry cannot be used with explicit dynamic analysis 1822 Insufficient memory for double-sided contact algorithm 1823 Insufficient memory - FSI analysis. Use -R option (maximum memory for

solution). 1824 Internal error in GASKET material, program stops 1825 Master degrees of freedom are modified in the restart run, which cannot be

done 1826 Error in user-supplied friction model calculations

Appendix 1


1827 Internal error in surface tension boundary, program stops 1828 Bad key in NASTRAN-OP2 stress output, program stops 1829 Error in NASTRAN-OP2 principal stress calculations, program stops 1830 EXP( ) is too large in Mooney-Rivlin material 1831 Non-positiveitive stretch in Ogden material 1832 Non-positiveitive stretch in hyper-foam material 1833 Bad isotropic model number in rubber 1834 Non-positive volume in 3-D rubber 1835 Bad orthotropic model number in rubber 1836 Zero pivot in stress-strain matrix for viscoelastic rubber 1837 Could not determine eigenvalues for viscoelastic rubber 1838 Could not determine actual J3 for Arruda-Boyce material 1839 Actual J3 out of range for Arruda-Boyce material 1840 Cannot use U/P formulation with hyper-foam material 1841 Bad isotropic model number in rubber 1842 Thermal strain less than -1.0 in rubber 1843 Too many orthotropic directions for orthotropic viscoelastic rubber 1844 EXP( ) is too large in orthotropic rubber 1845 Non-positive in-plane area in compressive plane stress rubber 1846 Bad isotropic model number in rubber 1847 Bad orthotropic model number in rubber 1848 Cannot find bounding out-of-plane stretches in rubber 1849 Cannot begin Newton iterations in rubber 1850 Zero slope in Newton iterations in rubber 1851 No convergence in Newton iterations in rubber 1852 Bad isotropic model number in rubber 1853 Non-positive stretch in compressive plane stress rubber 1854 Zero denominator in WLF shift function in rubber 1855 Bad isotropic model number in rubber 1856 Bad isotropic model number in rubber 1857 Bad isotropic model number in rubber 1858 Bad isotropic model number in rubber

Error messages


1859 Non-positive in-plane area in incompressible plane stress rubber 1860 Invalid value for element STYPE in axisymmetric/plane strain rubber 1861 Non-positive volume in axisymmetric/plane strain rubber 1862 Non-positive stretch in incompressible plane stress rubber 1863 Non-positive in-plane area in incompressible plane stress rubber 1864 Invalid value for element STYPE in axisymmetric/plane strain rubber 1865 Non-positive stretch in axisymmetric/plane strain rubber 1866 Non-positive in-plane area in axisymmetric/plane strain rubber 1867 Non-positive volume in axisymmetric/plane strain rubber 1868 Non-positive in-plane area in orthotropic compressible plane stress rubber 1869 Excessive penetration in rigid target contact algorithm 1870 Fracture mechanics cannot be used in a distributed memory parallel

processing 1871 ADINA trap error, program stops 1872 Excessive displacements in explicit analysis, probably due to unstable time

step 1873 Material model not allowed in explicit analysis 1874 Mismatch of element parameters in 3-D restart analysis 1875 Mismatch of element parameters in 2-D restart analysis 1876 Mismatch of element parameters in shell restart analysis 1877 General constrains (or mesh gluing) cannot be used in explicit time

integration 1878 Number of components in a general constraint equation is larger than the

maximum specified value by the input 1879 Non-positive elastic Finger tensor in ULH shells 1880 Non-positive Finger tensor in ULH shells 1881 Invalid deformation tensor (from displacements) in ULH shells 1882 Invalid deformation tensor in ULH shells 1883 Non-positive volume in ULH shells 1884 Non-positive updated Jacobian determinant in ULH shells

Appendix 1


Sparse solver messages


1901 Problem too large for the 32-bit version, no. of matrix elements larger than 2E31

1902 Sparse solver could not open a file, please check your write permission 1903 Sparse solver, write file failed, please check your disk space 1904 Reading the L-matrix failed, please check the disk space the file size 1905 Sparse solver, write file failed, please check the disk space 1906 Sparse solver, write file failed, please check the disk space 1907 Sparse solver, read file failed, please check the disk space 1908 Sparse solver, read file failed, please check the disk space 1909 Not enough memory for in-core analysis, solver switches to out-of-core 1911 Sparse solver internal error, please contact ADINA R&D, Inc. 1940 Not enough memory on the system to be allocated for the solver 1941 Error in the multi-grid solver, program stops 1942 AMG iterative solver failed, please check your model or use another solver

Error messages


Errors with specific information


2001 BEAM: group=� element=�, nodes 1 and 2 are too close to each other 2002 BEAM: group=� element=�, auxiliary node is not positioned correctly 2003 Error in closing a file (file probably does not exist), file=� 2004 No convergence in Gurson model, element group=�, element number=� 2005 Input ERROR, element group number=�, material property set number=� 2009 Stiffness matrix not positive definite, eqn=�, pivot=� 2010 Duplicate input in electromagnetic loading, nodes �

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Adina Command Referece Manual