CONTENTSgc.nuaa.edu.cn/hangkong/doc/ziliao/MSC_PATRAN/MSC... · CONTENTS MSC.Patran ABAQUS Preference Guide ... - Beam Shape Display in Plane/Space, 109 ... The core of the product

C O N T E N T SMSC.Patran ABAQUS Preference Guide MSC.Patran ABAQUS Preference

Guide,

CHAPTER

1Overview ■ Purpose, 2

■ ABAQUS Product Information, 3

■ What is Included with this Product?, 3

■ MSC.Patran ABAQUS Integration with MSC.Patran, 4

■ Configuring the ABAQUS Submit File, 6

2Building A Model ■ Introduction to Building a Model, 8

■ Coordinate Frames, 16

■ Finite Elements, 17❑ Nodes, 18❑ Elements, 19❑ Multi-Point Constraints, 20

- MPC Types, 20- To create an MPC, you must first select the type of MPC you want to

create from an option menu. The types that will appear in this option menu are dependent on the current Analysis Type preference setting. The following table describes the MPC types that are supported.Degrees-of-Freedom, 21

■ Material Library, 43❑ Materials Form, 44

- Isotropic, 49- Elastic, 49- Hyperelastic, 51- Hyperelastic, 52- Hyperelastic, 53- Hyperelastic, 54- Hyperelastic, 55- Hyperelastic, 56- Hyperelastic, 57- Hyperelastic, 59- Viscoelastic, 60- Viscoelastic, 61- Viscoelastic, 62- Viscoelastic, 63- Deformation Plasticity, 64- Plastic, 65

- Plastic, 66- Plastic, 67- Plastic, 68- Plastic, 69- Creep, 70- Creep, 71

❑ 2D Orthotropic (Lamina), 72- Elastic, 72- 3D Orthotropic, 73- Elastic, 73- Elastic, 74- 3D Anisotropic, 75- Elastic, 75- Isotropic (Thermal) , 77- 3D Orthotropic (Thermal), 78- 3D Anisotropic (Thermal) , 79- Composite, 80- Laminate , 80

■ Element Properties, 81❑ Element Properties Form, 82

- Point Mass, 96- Rotary Inertia, 97- Linear Spring (Grounded), 98- Nonlinear Spring (Grounded), 99- Linear Damper (Grounded), 100- Nonlinear Damper (Grounded), 101- IRS (Single Node, Planar), 102- IRS (Single Node, Spatial), 104- General Beam in Plane, 106- Box Beam in Plane/Space , 108- Beam Shape Display in Plane/Space, 109- Additional Beam Shapes in Plane/Space, 110- General Beam in Space, 113- Arbitrary Beam in Space, 115- Curved Pipe in Space, 117- L-Section Beam in Space, 119- Open Beam in Space, 121- Truss , 123- Linear Spring (Axial), 124- Linear Spring (Fixed Direction), 125- Nonlinear Spring (Axial), 126- Nonlinear Spring (Fixed Direction), 127- Linear Damper (Axial), 128- Linear Damper (Fixed Direction), 129- Nonlinear Damper (Axial), 130- Nonlinear Damper (Fixed Direction), 131- Gap (Uniaxial), Gap (Cylindrical), 132- Gap (Spherical), 133- Axisymmetric Shell, 134- Axisymmetric Shell (Laminate) , 135- 1D Interface, 136- Planar ISL (In Plane), 138- Axisymmetric ISL (In Plane), 140

- Parallel ISL (In Space), 142- Radial ISL (In Space), 145- Slide Line, 147- IRS (Planar), 148- IRS (Axisymmetric), 150- IRS (Beam/Pipe), 152- Rigid Surface (Segments), 154- Rigid Surface (Cylindrical), 155- Rigid Surface (Axisymmetric), 156- Rigid Surface (Bezier 2D), 157- Rigid Line (LBC) , 158- Rebar , 159- Mech Joint (2D Model) - ALIGN, 161- Mech Joint (3D Model) - ALIGN, 177- Axisym Link Gasket, 213- Axisym Link Gasket (Thick only), 215- Axisym Link Gasket (Material), 217- 3D Link Gasket, 219- 3D Link Gasket (Thick only), 222- 3D Link Gasket (Material), 224- 2D Link Gasket, 226- 2D Link Gasket (Thick only), 228- 2D Link Gasket (Material), 230- Thin Shell, 232- Thin Shell (Laminated) , 234- Thick Shell, 235- Thick Shell (Laminated) , 237- General Thin, 238- General Thin Shell (Laminated) , 240- General Thick, 241- General Thick Shell (Laminated), 243- Large Strain, 244- General Large Strain, 246- Plane Strain, 248- Generalized Plane Strain, 249- Plane Stress, 251- Axisymmetric Solid, 252- Axisymmetric Solid with Twist (General), 253- Membrane, 254- Planar 2D Interface, 255- Axisymmetric 2D Interface, 257- IRS (Shell/Solid), 259- Rigid Surface (Bezier 3D), 261- Rigid Surface (LBC) , 262- 2D Rebar , 263- Plane Strain Gasket, 265- Plane Strain Gasket (Material), 267- Plane Stress Gasket, 269- Plane Stress Gasket (Thick only), 271- Plane Stress Gasket (Material), 273- Axisymmetric Gasket, 275- Axisymmetric Gasket (Thick only), 277- Axisymmetric Gasket (Material), 279- 3D Line Gasket, 281

- 3D Line Gasket (Thick only), 283- 3D Line Gasket (Material), 285- Solid , 287- 3D Interface, 288- Thermal Link, 290- Thermal Axisymmetric Shell, 291- Thermal Axisymmetric Shell (Laminated), 292- Thermal 1D Interface, 293- Thermal Shell, 294- Thermal Shell (Laminated), 295- Thermal Planar Solid, 296- Thermal Preference (Planar), 297- Thermal Solid, 298- Thermal Preference (Solid), 299- Solid Gasket, 300- Solid Gasket (Thick only), 303- Solid Gasket (Material), 305

■ Loads and Boundary Conditions, 307❑ Loads & Boundary Conditions Form, 308

- Input Data, 310- Object Tables, 312

■ Load Cases, 326

■ Group, 327

3Running an Analysis

■ Review of the Analysis Form, 330❑ Analysis Form, 331

■ Translation Parameters, 332

■ Restart Parameters, 333

■ Optional Controls, 334

■ Direct Text Input, 335

■ Step Creation, 336❑ Select Load Cases, 337❑ Output Requests, 338❑ Direct Text Input, 339❑ Solution Types, 340

- Linear Static, 343- Read Temperature File, 343- Linear Static, 344- Natural Frequency, 346- Bifurcation Buckling, 349- Direct Linear Transient, 352- Direct Steady State Dynamics, 355- Modal Linear Transient, 359- Define Damping Direct, 363- Define Damping Rayleigh, 364- Base Motion, 365- Steady State Dynamics, 366

- Define Frequencies, 370- Response Spectrum, 371- Define Response Spectra (Response Spectrum), 372- Define Spectrum (Response Spectrum), 373- Random Vibration, 377- Define Spectrum (Random Vibration), 378- Nonlinear Static, 382- Nonlinear Transient Dynamic, 386- Creep, 390- Viscoelastic (Time Domain), 394- Viscoelastic (Frequency Domain), 398- Steady State Heat Transfer, 401- Transient Heat Transfer, 402

■ Step Selection, 404

■ Read Input File, 405

■ ABAQUS Input File Reader, 406❑ Input Deck Formats, 406

- Message File, 406❑ ABAQUS ELSET and NSET Entries, 406

- Supported Element Types, 406- Supported Keywords, 406

4Read Results ■ Review of the Read Results Form, 422

❑ Read Results Form, 423❑ Flat File Results, 424

■ Translation Parameters, 425❑ Attach Method, 425❑ Translate and Control File Methods, 425

■ Select Results File, 426❑ Results Created in MSC.Patran, 427

■ Data Translated from the Analysis Code Results File, 431

■ Key Differences between Attach and Translate Methods, 432❑ Result Type Naming Conventions, 432❑ Vector vs. Scalar Moment and Rotational Results, 432❑ Reaction Forces, 432

■ Delete Result Attachment Form, 433

5Files ■ Files, 436

6Errors/Warnings ■ Errors/Warnings, 438

INDEX ■ MSC.Patran ABAQUS Preference Guide, 439

MSC.Patran ABAQUS Preference Guide

CHAPTER

1 Overview

■ Purpose

■ ABAQUS Product Information

■ What is Included with this Product?

■ MSC.Patran ABAQUS Integration with MSC.Patran

■ Configuring the ABAQUS Submit File

1.1 PurposeMSC.Patran comprises a suite of products written and maintained by MSC.Software Corporation. The core of the product suite is a finite element analysis pre and postprocessor. The MSC.Patran system also includes several optional products such as advanced postprocessing programs, tightly coupled solvers, and interfaces to third party solvers. This document describes one of these interfaces. See the MSC.Patran User Manual for more information.

The MSC.Patran ABAQUS Application Preference Guide provides a communication link between MSC.Patran and ABAQUS. It also provides customization of certain features that can be activated simply by selecting ABAQUS as the analysis code preference in MSC.Patran.

MSC.Patran ABAQUS is integrated into MSC.Patran. The casual user will never need to be aware that separate programs are being used. For the expert user, there are three main components of MSC.Patran ABAQUS: several PCL files to provide the customization of MSC.Patran for ABAQUS, PAT3ABA to convert model data from the MSC.Patran database into the analysis code input file, and ABAPAT3 to translate results and⁄ or model data from the analysis code results file into the MSC.Patran database.

Selecting ABAQUS as the analysis code under the “Analysis Preference” menu customizes MSC.Patran in five main areas:

1. MPCs

2. Material Library

3. Element Library

4. Loads and Boundary Conditions

5. Analysis forms

PAT3ABA translates model data directly from the MSC.Patran database into the analysis code-specific input file format. This translation must have direct access to the originating MSC.Patran database. The program name indicates the direction of translation: from MSC.Patran to ABAQUS.

ABAPAT3 translates results and⁄ or model data from the analysis code-specific results file into the MSC.Patran database. This program can be run such that the data is loaded directly into the MSC.Patran database, or if incompatible computer platforms are being used, an intermediate file can be created. The program name indicates the direction of translation: from ABAQUS to MSC.Patran.

3CHAPTER 1Overview

1.2 ABAQUS Product InformationABAQUS is a general-purpose finite element computer program for structural and thermal analyses. It is developed, supported, and maintained by Hibbitt, Karlsson, and Sorensen, Inc., 1080 Main Street, Pawtucket, Rhode Island 02860, (401) 727-4200. See the ABAQUS User’s Manual for a general description of ABAQUS’ capabilities.

1.3 What is Included with this Product?The MSC.Patran ABAQUS product includes all of the following items:

1. A PCL library file, abaqus.plb, contains MSC.Patran ABAQUS-specific definitions.

2. The executable programs pat3aba and abapat3 which perform the forward and results translation of data. Although these programs are separate executables, they are run from within MSC.Patran, and are transparent to the user.

3. Script files are also included to drive the programs in item 2. These script files are started by MSC.Patran and control the running of the programs in MSC.Patran ABAQUS.

4. This Application Preference User’s Manual is included as part of the product. An on-line version is also provided to allow you direct access to this information from within MSC.Patran.

1.4 MSC.Patran ABAQUS Integration with MSC.PatranTwo diagrams are shown below to indicate how these files and programs fit into the MSC.Patran environment. In some cases, site customization of some of these files is indicated. Please see the MSC.Patran Installation and Operations Guide for more information on this topic.

Figure 1-1 shows the process of running an analysis. The abaqus.plb library defines the various Translation Parameter, Solution Type, Solution Parameter, and Output Request forms called by the Analysis form. When the Apply button is selected on the Analyze form, a.jba file is created, and the script AbaqusSubmit is started. This script may need to be modified for your site installation. The script, in turn, starts the PAT3ABA forward translation. MSC.Patran operation is suspended at this time. PAT3ABA reads data from the database and creates the ABAQUS input deck. A message file is also created to record any translation messages. If PAT3ABA finishes successfully, and you have requested it, the script will then start ABAQUS.

Figure 1-1 Forward Translation

MSC.Patran

Analyze

abaqus.plb

AbaqusSubmit

PAT3ABA

MSC.Patrandatabase

jobname.inp ABAQUS

jobname.msg

5CHAPTER 1Overview

Figure 1-2 shows the process of reading information from an analysis results file. When the Apply button is selected on the Read Results form, a .jbr file is created, depending on whether model or results data is to be read. The ResultsSubmit script is also started. This script may need to be modified for your site installation. The script, in turn, starts the ABAPAT3 results translation. The MSC.Patran database is closed while this translation occurs. A message file is created to record any translation messages. ABAPAT3 reads the data from the ABAQUS results file. If ABAPAT3 can find the desired database, the results will be loaded directly into it. If, however, it cannot find the database (for example, if you are running on several incompatible platforms), ABAPAT3 will write all the data into a flat file. This flat file can be taken to wherever the database is and read in using the read file selections.

Figure 1-2 Results Translation

MSC.Patran

ReadResults

MSC.Patrandatabase

ResultsSubmit

jobname.jbr

ABAPAT3

jobname.fil

jobname.flat

jobname.msg

ABAQUS

1.5 Configuring the ABAQUS Submit FileThe AbaqusSubmit script file controls the execution of the PAT3ABA translator and the ABAQUS analysis code. It is located in the MSC.Patran directory called

<installation_dir>/patran/patran3/bin/exe/

The information that AbaqusSubmit uses to perform its operations can be categorized as specific to the job and the site. The job specific information is automatically supplied by MSC.Patran as command line arguments at run time. The site specific information is set within the script file at the time of installation.

Host=LOCALScratchdir=”Acommand=’abaqus’

The Host parameter defines the machine that is used to perform the ABAQUS analysis. When this parameter is set to LOCAL, the analysis is performed on the same machine as the MSC.Patran session (PAT3ABA translations are always performed on the same machine as the MSC.Patran session.)

The Scratchdir parameter defines the directory on the host machine that temporarily holds the analysis files as they are created. The advantage of having a scratch directory is that the contents of the analysis scratch files are never transferred across the network. This benefit is not achieved when the Host parameter is set to LOCAL, so the Scratchdir parameter is ignored for this condition.

The Acommand is the ABAQUS analysis code executable. If the Host is not LOCAL then the executable should include the complete pathname.


CHAPTER

2 Building A Model

■ Introduction to Building a Model

■ Coordinate Frames

■ Finite Elements

■ Material Library

■ Element Properties

■ Loads and Boundary Conditions

■ Load Cases

■ Group

2.1 Introduction to Building a ModelThere are many aspects to building a finite element analysis model. In several cases, the forms used to create the finite element data are dependent on the selected analysis type. Other parts of the model are created using standard forms.

Under Preferences on the MSC.Patran main form is a selection for Analysis Settings. Analysis Settings defines the intended analysis code which is to be used for this mode.

The specified code may be changed at any time during model creation. As much data as possible will be converted if the analysis code is changed after the modeling process has already begun. The setting of this option defines what will be presented in several areas during the subsequent modeling steps.

MSC.Patran

hp, 2

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File Group Viewport Display Preferences Tools HelpInsight Control

Geometry© FEM LBCs Matls Properties© ©© © Load Cases© Fields Analysis Results Insight© ©© © XYPlot©

Viewing

Preferences

Analysis...Global...Graphics...

Mouse...Key Map...Picking...

Report...

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9CHAPTER 2Building A Model

These areas include the material and element libraries (including multi-point constraints), the applicable loads and boundary conditions, and the analysis forms. The selected Analysis Type may also affect the allowable selections in these same areas. For more details, see Analysis Codes (p. 338) in the MSC.Patran Reference Manual, Part 1: Basic Functions.

Supported ABAQUS Commands. The following tables summarize all the ABAQUS commands supported by the MSC.Patran ABAQUS Preference Guide. The tables indicate where in this guide you can find more information on how the commands are supported.

To use the MSC.Patran ABAQUS Preference guide, this should be set to ABAQUS.

MSC.Patran ABAQUS includes libraries for both Structural and Thermal analysis types.

Analysis Preferences

ABAQUSAnalysis Code Selection:

StructuralAnalysis Type:

.inp

Input

.fil

Output

Reset

-Apply- Cancel

Indicates the file suffixes used in creating file names for ABAQUS input and output files.

Table 2-1 Supported ABAQUS Model Definition Options

History Definition Options

CommandMSC.Patran ABAQUS Preference Guide

Page No.

ABAQUS/ Standard Section #

Initial Options ∗ HEADING ❏ p. 334 7.2.1Node Definition ∗ NODE ❏ p. 18 7.3.6

∗ NSET ❏ p. 18 7.3.8∗ TRANSFORM ❏ p. 16 7.3.11

Element Definition ∗ ELEMENT ❏ p. 19 7.4.2∗ ELSET ❏ p. 327 7.4.2∗ RIGID SURFACE ❏ p. 154, p. 155, p. 156 p. 261 7.4.7∗ SLIDE LINE ❏ p. 147 7.4.8

Property Definition ∗ BEAM GENERAL SECTION ❏ p. 106, p. 113, p. 121 7.5.2∗ BEAM SECTION ❏ p. 108, p. 115 to p. 119, 7.5.3*CENTROID ❏ p. 114 7.5.2∗ DASHPOT ❏ p. 100, p. 101, p. 128 to p. 131 7.5.5∗ FRICTION ❏ p. 102 to p. 104, p. 132, p. 133, 7.5.7

p. 136 to p. 145, p. 148 to p. 152p. 255 to p. 259, p. 288

Property Definition (continued)

∗ GAP ❏ p. 132, p. 133, p. 293, p. 297 7.5.8p. 299

*GAP CONDUCTANCE*GAP RADIATION

❏ p. 293, p. 297, p. 299

∗ HOURGLASS STIFFNESS ❏ p. 232, p. 235, p. 238, p. 241, 7.5.13p. 244, p. 246, p. 248, p. 251,p. 252, p. 254, p. 287

∗ INTERFACE ❏ p. 102, p. 104, p. 136, p. 138, 7.5.14p. 140, p. 142, p. 145, p. 148,p. 150, p. 152, p. 255, p. 257,p. 259, p. 288, p. 293, p. 297,p. 299

∗ MASS ❏ p. 96 7.5.17∗ ROTARY INERTIA ❏ p. 97 7.5.18∗ SHELL GENERAL SECTION ❏ p. 238, p. 241, p. 246 7.5.19∗ SHELL SECTION ❏ p. 80, p. 134, p. 135, p. 232, 7.5.20

p. 234, p. 235, p. 237, p. 244,p. 291, p. 292, p. 294, p. 295

∗ SOLID SECTION ❏ p. 123, p. 248, p. 251, p. 252, 7.5.21p. 254, p. 287, p. 290, p. 296,p. 298

∗ SPRING ❏ p. 98, p. 99, p. 124 to p. 127∗ SURFACE CONTACT p. 103, p. 136, p. 255, p. 257, 7.5.26

p. 259, p. 288∗ TRANSVERSE SHEAR STIFFNESS

❏ p. 107, p. 108, p. 110, p. 113, 7.5.27p. 115, p. 119, p. 121, p. 232,p. 234, p. 235, p. 237, p. 238,p. 241, p. 244, p. 246

Material Definition ∗ MATERIAL ❏ p. 44 7.6.2∗ CAP HARDENING ❏ p. 69 7.6.4∗ COMBINED TEST DATA ❏ p. 69∗ CAP PLASTICITY ❏ p. 69 7.6.5∗ CONDUCTIVITY ❏ p. 77, p. 78, p. 79 7.6.8∗ CREEP ❏ p. 70, p. 71 7.6.9∗ DAMPING ❏ p. 49, p. 72 to p. 75 7.6.11∗ DEFORMATION PLASTICITY ❏ p. 64 7.6.12∗ DENSITY ❏ p. 49 to p. 59, p. 72 to p. 79 7.6.13

Material Definition(continued)

∗ DRUCKER-PRAGER ❏ p. 69 7.6.16∗ ELASTIC ❏ p. 49, p. 72, p. 73, p. 74, 7.6.17

❏ p. 75

Table 2-1 Supported ABAQUS Model Definition Options (continued)



Page No.



The following ABAQUS History Definition options are supported.

∗ EXPANSION ❏ p. 49 to p. 59, p. 72 to p. 79 7.6.18∗ HYPERELASTIC ❏ p. 51 to p. 56 7.6.22∗ HYPERFOAM ❏ p. 57, p. 59 7.6.23∗ LATENT HEAT ❏ p. 57, p. 59 7.6.27∗ NO COMPRESSION ❏ p. 57, p. 59 7.6.29∗ NO TENSION ❏ p. 57, p. 59 7.6.30∗ PLANAR TEST DATA ❏ p. 69∗ PLASTIC ❏ p. 65, p. 66, p. 67 7.6.34∗ POTENTIAL ❏ p. 65 to p. 67, p. 70, p. 71 7.6.37∗ RATE DEPENDENT ❏ p. 65 to p. 68∗ SHEAR TEST DATA ❏ p. 69∗ SIMPLE SHEAR TEST DATA ❏ p. 69∗ SPECIFIC HEAT ❏ p. 77, p. 78, p. 79 7.6.40∗ UNIAXIAL TEST DATA ❏ p. 69∗ VISCOELASTIC ❏ p. 60, p. 61, p. 62, p. 63 7.6.43∗ VOLUMETRIC TEST DATA ❏ p. 69*YIELD ❏ p. 68 7.6.44

Material Orientation ∗ ORIENTATION ❏ p. 80, p. 232, p. 234, p. 235, 7.7.1❏ p. 237, p. 238, p. 241, p. 244,❏ p. 246, p. 248, p. 251, p. 287,❏ p. 294, p. 295, p. 296, p. 298

Kinematic Constraints ∗ BOUNDARY ❏ p. 312, p. 316, p. 317 9.5.1∗ EQUATION ❏ p. 24 7.8.3∗ MPC ❏ p. 25 to p. 42 7.8.4

Initial Conditions ∗ INITIAL CONDITIONS ❏ p. 315, p. 325 7.9.1Restart Options ∗ RESTART ❏ p. 332 7.10.1Miscellaneous Model Options

∗ AMPLITUDE ❏ p. 346 7.11.1∗ PSD-DEFINITION ❏ p. 378 7.11.3∗ SPECTRUM ❏ p. 374 7.11.5∗ WAVEFRONT MINIMIZATION ❏ p. 334 7.11.9

Table 2-1 Supported ABAQUS Model Definition Options (continued)



Page No.


Table 2-2 Supported ABAQUS History Definition Options



Page No.

ABAQUS/ Standard

Section No.

Step Initialization/Termination

*STEP ❏ p. 336, p. 346, p. 382, p. 386, 9.2.1p. 390, p. 394, p. 402

∗ END STEP ❏ p. 336 9.2.2

Procedure Definition ∗ BUCKLE ❏ p. 349 9.3.2∗ DYNAMIC ❏ p. 352, p. 386 9.3.4∗ FREQUENCY ❏ p. 359, p. 366, p. 374, p. 377 9.3.5∗ HEAT TRANSFER ❏ p. 401, p. 402 9.3.7∗ MODAL DYNAMIC ❏ p. 359 9.3.8∗ RANDOM RESPONSE ❏ p. 377 9.3.9∗ RESPONSE SPECTRUM ❏ p. 374 9.3.10∗ STATIC ❏ p. 382 9.3.12∗ STEADY STATE DYNAMICS ❏ p. 366, p. 370 9.3.13∗ VISCO ❏ p. 390, p. 394 9.3.15

Loading Definition ∗ BASE MOTION ❏ p. 359, p. 365, p. 366 9.4.2∗ CFLUX ❏ p. 324 9.4.4∗ CLOAD ❏ p. 312 9.4.5∗ DFLUX ❏ p. 324 9.4.9∗ DLOAD ❏ p. 313, p. 315 9.4.10∗ FILM ❏ p. 323 9.4.12∗ TEMPERATURE ❏ p. 313 9.4.18

Prescribed Boundary Conditions

∗ BOUNDARY ❏ p. 317 9.5.1

Miscellaneous History Options

∗ CORRELATION ❏ p. 377 9.4.6∗ MODAL DAMPING ❏ p. 359 to p. 364 9.6.6

Print Definition ∗ EL PRINT ❏ p. 338 9.8.2∗ ENERGY PRINT ❏ p. 338 9.8.3∗ MODAL PRINT ❏ p. 338 9.8.4∗ NODE PRINT ❏ p. 338 9.8.6∗ PRINT ❏ p. 338 9.8.7

File Output Definition ∗ EL FILE ❏ p. 338 9.9.2∗ ELEMENT MATRIX OUTPUT ❏ p. 338∗ ENERGY FILE ❏ p. 338 9.9.3FILE FORMAT ❏ p. 338 9.9.4∗ MODAL FILE ❏ p. 338 9.9.5∗ NODE FILE ❏ p. 338 9.9.6∗ PREPRINT ❏ p. 338

Table 2-2 Supported ABAQUS History Definition Options (continued)



Page No.

ABAQUS/ Standard

Section No.


The following ABAQUS element types are supported.

Table 2-3 Supported ABAQUS Element Types

Element TypesMSC.Patran ABAQUS

Preference Guide Page No.

Str

ess-

Dis

pla

cem

ent

Ele

men

ts

Beam Elements

Two-dimensional B21B21HB22

B22HB23B23H

❏ p. 106, p. 108

Three-dimensional B31B31HB32B32H

B33B33HB34

❏ p. 113, p. 115, p. 119

Three-dimensional Open Section

B31OSB31OSH

B32OSB32OSH

❏ p. 121

One-dimensional C1D2C1D2H

C1D3C1D3H

❏ p. 123

Axisymmetric CAX3CAX3HCAX4CAX4HCAX4ICAX4IH

CAX4RCAX4RHCAX6CAX6H

CAX8CAX8HCAX8RCAX8RH

❏ p. 252

Axisymmetric with twist

CGAX3CGAX3HCGAX4CGAX4HCGAX4RCGAX4RH

CGAX6CGAX6HCGAX8CGAX8HCGAX8RCGAX8RH

❏ p. 253

Plane Strain CPE3CPE3HCPE4CPE4HCPE4ICPE4IH

CPE4RCPE4RHCPE6CPE6HCPE6MCPE6MH

CPE8CPE8HCPE8RCPE8RH

❏ p. 248

Generalized Plane Strain

CGPE5CGPE5HCGPE6CGPE6HCGPE6ICGPE6IHCGPE6R

CGPE6RHCGPE8CGPE8HCGPE10CGPE10HCGPE10RCGPE10RH

❏ p. 249

Plane Stress CPS3CPS4CPS4ICPS4R

CPS6CPS6MCPS8CPS8R

❏ p. 251

Three-dimensional C3D4C3D4HC3D6C3D6HC3D8C3D8HC3D8IC3D8IHC3D8RC3D8RH

C3D10C3D10HC3D10MC3D10MHC3D15C3D15HC3D20C3D20HC3D20RC3D20RH

C3D27C3D27HC3D27RC3D27RH

❏ p. 287

Str

ess-

Dis

pla

cem

ent

Ele

men

ts

Membrane Elements

Membrane Elements M3D3M3D4M3D4RM3D6

M3D8M3D8RM3D9M3D9R

❏ p. 254

Shell Elements

Shell S3RF S4RF ❏ p. 244, p. 246S4R STRI3 ❏ p. 235, p. 237, p. 241S4R5 S9R5 ❏ p. 232, p. 234, p. 238S8R ❏ p. 40, p. 41, p. 235,

p. 237, p. 241S8R5 ❏ p. 40, p. 41, p. 232,

p. 234, p. 238STRI35 ❏ p. 232, p. 234, p. 238STRI65 ❏ p. 232, p. 234, p. 235,

p. 237, p. 238, p. 241Axisymmetric SAX1 SAX2 ❏ p. 134, p. 135

Sp

ecia

l Ele

men

ts

Elbow Elements

Elbow Elements ELBOW31ELBOW31B

ELBOW31CELBOW32

❏ p. 117

Spring Elements

Spring Elements SPRING1 ❏ p. 98, p. 99SPRING2 ❏ p. 125, p. 127SPRINGA ❏ p. 124, p. 126

Dashpot Elements

Dashpot Elements DASHPOT1 ❏ p. 100DASHPOT2 ❏ p. 101, p. 129, p. 131DASHPOTA ❏ p. 128, p. 130

Mass Element

Mass Element MASS ❏ p. 96Rotary Inertia Element

Rotary Inertia Element ROTARY1 ❏ p. 97Gap Elements

Gap Elements GAPCYL ❏ p. 132GAPSPHER ❏ p. 133GAPUNI ❏ p. 132

Small Sliding Contact Elements

Interface INTER1 ❏ p. 136INTER2 INTER3 ❏ p. 255INTER4INTER8

INTER9 ❏ p. 288

Axisymmetric INTER2A INTER3A ❏ p. 257

Table 2-3 Supported ABAQUS Element Types (continued)




Sp

ecia

l Ele

men

ts

Rigid Surface Contact Elements

Rigid Surface IRS3IRS4

IRS9 ❏ p. 259

IRS12 ❏ p. 102IRS13 ❏ p. 104IRS21 IRS22 ❏ p. 148IRS31 IRS32 ❏ p. 152

Axisymmetric IRS21A IRS22A ❏ p. 150Slide Line Contact Elements

Two-dimensional ISL21 ISL22 ❏ p. 138, p. 147Three-dimensional ISL31 ISL32 ❏ p. 142, p. 147Axisymmetric ISL21A ISL22A ❏ p. 140, p. 147

ISL31A ISL32A ❏ p. 145, p. 147

Hea

t T

ran

sfer

Ele

men

ts

Heat Transfer Elements

Axisymmetric DCAX3DCAX4

DCAX6DCAX8

❏ p. 296

Axisymmetric Convection/Diffusion

DCCAX2 DCCAX2D

DCCAX4 DCCAX4D ❏ p. 296One-dimensional DC1D2 DC1D3 ❏ p. 290Two-dimensional DC2D3

DC2D4DC2D6DC2D8

❏ p. 296

Two-dimensional Convection/Diffusion

DCC2D4DCC2D4D

❏ p. 296

Three-dimensional DC3D4DC3D6DC3D8

DC3D10DC3D15DC3D20

❏ p. 298

Three-dimensional Convection/Diffusion

DCC3D8 DCC3D8D ❏ p. 298

Interface Elements DINTER1 ❏ p. 293DINTER2 DINTER3 ❏ p. 297DINTER4 DINTER8 ❏ p. 299

Interface Elements, Axisymmetric

DINTER2ADINTER3A

❏ p. 297

Shell Elements DS4DS8

❏ p. 294, p. 295

Shell Elements, Axisymmetric

DSAX1DSAX2

❏ p. 291, p. 292

Table 2-3 Supported ABAQUS Element Types (continued)



2.2 Coordinate FramesCoordinate frames will generate different ABAQUS input, depending on the use of the coordinate frame. Unreferenced coordinate frames will not be translated into ABAQUS.

If a node references a coordinate frame in the Analysis Coordinate Frame field, the nodal degrees-of-freedom will be rotated into that system through the use of the *TRANSFORM option. All vector type loads or boundary conditions must reference the same coordinate frame as the node.

If a coordinate frame is referenced for element property orientation, the appropriate *ORIENTATION option will be created.

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2.3 Finite ElementsFinite Elements in MSC.Patran allows the definition of basic finite element constructs, including the creation of nodes, element topology, and multi-point constraints.

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Nodes The nodes form will generate the ∗ NODE option (see Section 7.3.6 in the ABAQUS/Standard User’s Manual).

The name of the node set to which the nodes will be assigned will be based on the associated analysis coordinate frame number. For example, creating nodes in analysis coordinate frame “Coord 1" will generate the ABAQUS option ∗ NSET, NSET=CID1.

Finite Elements

CreateAction:

NodeObject:

EditMethod:

1

Node Id List

Coord 0

Analysis Coordinate Frame

Coord 0

Refer. Coordinate Frame

Associate with Geometry

Node Location List

Auto Execute

-Apply-

Defines a local coordinate frame for displacements and rotations at the node.

Not used by MSC.Patran ABAQUS.


ElementsFinite elements in MSC.Patran simply assigns element topology, such as Quad⁄ 4, for standard finite elements. The type of element to be created is not determined until the element properties are assigned. See Element Properties Form (p. 82) for details concerning the ABAQUS element types. Elements can be created either discretely using the Element object, or indirectly using the Mesh object.

An *ELEMENT option is created for each unique group of elements. The name of the element set to which the elements will be assigned will be defined by the region number. For example, elements in region 1 will be assigned by the ABAQUS option *ELEMENT, ELSET=PID1.The optional INPUT and OFFSET parameters are not used.

Finite Elements

CreateAction:

MeshObject:

SurfaceType:

1

Node Id List

1

Element Id List

Output Ids

0.1

Global Edge Length

Quad4Quad5Quad8

Element Topology

IsoMesh Paver

Mesher

IsoMesh Parameters...

Surface List

-Apply-

Node Coordinate Frames...

◆ ◆ ◆

Multi-Point ConstraintsMulti-point constraints (MPCs) can also be created from the Finite Elements menu. These are special element types which define a rigorous behavior between several specified nodes. The forms for creating MPCs are found by selecting MPC as the Object on the Finite Elements form. The full functionality of the MPC forms are defined in The Create Action (FEM Entities) (Ch. 3) in the MSC.Patran Reference Manual, Part 3: Finite Element Modeling.

MPC Types

Finite Elements

CreateAction:

MPCObject:

ExplicitType:

1

MPC ID

Constant Term

Specifies the ID to associate to the MPC when it is created.

This databox is not currently used.

Define Terms...

- Apply -


To create an MPC, you must first select the type of MPC you want to create from an option menu. The types that will appear in this option menu are dependent on the current Analysis Type preference setting. The following table describes the MPC types that are supported.Degrees-of-Freedom

MPC Type Analysis Type Description

Explicit Structural

Thermal

Creates an ∗ EQUATION option which defines an explicit MPC between a dependent degree-of-freedom and one or more independent degrees-of-freedom. The dependent term consists of a node ID and a degree-of-freedom, while an independent term consists of a coefficient, a node ID, and a degree-of-freedom. An unlimited number of independent terms and one dependent term can be specified.

Rigid (Fixed) Structural Creates a BEAM type MPC between one independent node and one or more dependent nodes in which all six structural degrees-of-freedom are rigidly attached to each other. An unlimited number of dependent terms and one independent term can be specified. Each term consists of a single node.

Rigid (Pinned) Structural Creates a LINK type MPC between one independent node and one or more dependent nodes in which only the three translational structural degrees-of-freedom are rigidly attached to each other. An unlimited number of dependent terms and one independent term can be specified. Each term consists of a single node.

Linear Surf-Surf Structural

Thermal

Creates a LINEAR type MPC between a dependent node on one linear 2D element and two independent nodes on another linear 2D element to model a continuum. One dependent and two independent terms can be specified. Each term consists of a single node.

Linear Surf-Vol Structural Creates an SS LINEAR type MPC between a dependent node on a linear 2D plate element and two independent nodes on a linear 3D solid element to connect the plate element to the solid element. One dependent and two independent terms can be specified. Each term consists of a single node.

Linear Vol-Vol Structural

Thermal

Creates a BILINEAR type MPC between a dependent node on one linear 3D solid element and four independent nodes on another linear 3D solid element to model a continuum. One dependent and four independent terms can be specified. Each term consists of a single node.

Quad. Surf-Surf Structural Creates a QUADRATIC type MPC between a dependent node on one quadratic 2D element and three independent nodes on another quadratic 2D element to model a continuum. One dependent and three independent terms can be specified. Each term consists of a single node.

Quad. Surf-Vol Structural Creates an SS BILINEAR type MPC between a dependent node on a quadratic 2D plate element and three independent nodes on a quadratic 3D solid element to connect the plate element to the solid element. One dependent and three independent terms can be specified. Each term consists of a single node.

Quad. Vol-Vol Structural Creates a C BIQUAD type MPC between a dependent node on one quadratic 3D solid and eight independent nodes on another quadratic 3D solid element to model a continuum. One dependent and eight independent terms can be specified. Each term consists of a single node.

Slider Structural Creates a SLIDER type MPC between one dependent node and two independent nodes which forces the dependent node to move along the vector defined by the two independent nodes. One dependent and two independent terms can be specified. Each term consists of a single node.

Elbow Structural Creates an ELBOW type MPC which constrains two nodes of ELBOW31 or ELBOW32 elements together. One dependent and one independent terms can be specified. Each term consists of a single node.

Tie Structural Creates a TIE type MPC which makes all active degrees-of-freedom equal at two nodes. One dependent and one independent terms can be specified. Each term consists of a single node.

Revolute Structural Creates a REVOLUTE type MPC which defines a revolute joint. One dependent and two independent terms can be specified. Each term consists of a single node.

V Local Structural Creates a V LOCAL type MPC which constrains the velocity components at the first node to be equal to the velocity components at the third node along local, rotating, directions. These local directions rotate according to the rotation at the second node. One dependent and two independent terms can be specified. Each term consists of a single node.



Whenever a list of degrees-of-freedom is expected for an MPC term, a listbox containing the valid degrees-of-freedom is displayed on the form. A degree-of-freedom is valid if:

1. It is valid for the current Analysis Type Preference.

2. It is valid for the selected MPC type.

In most cases, all degrees-of-freedom which are valid for the current Analysis Type preference are valid for the MPC type.

The following degrees-of-freedom are supported by the MSC.Patran ABAQUS MPCs for the various analysis types:

Universal Structural Creates a UNIVERSAL type MPC which defines a universal joint. One dependent and three independent terms can be specified. Each term consists of a single node.

SS Linear Structural Creates an SS LINEAR type MPC which constrains a shell node to a line of solid nodes for linear elements. One dependent and an unlimited number of independent terms can be specified. Each term consists of a single node.

SS Bilinear Structural Creates an SS BILINEAR type MPC which constrains a shell node to a line of solid nodes for quadratic elements. One dependent and an unlimited number of independent terms can be specified. Each term consists of a single node.

SSF Bilinear Structural Creates an SSF BILINEAR type MPC which constrains a mid-side shell node to a line of mid-face solid nodes for quadratic elements. One dependent and an unlimited number of independent terms can be specified. Each term consists of a single node.

Degrees-of-Freedom Analysis Type

UX Structural

UY Structural

UZ Structural

RX Structural

RY Structural

RZ Structural

Temperature Thermal


Explicit MPCs

Creates an *EQUATION option. (See Section 7.8.3 in the ABAQUS/Standard User’s Manual). No constant term is allowed for this type of equation. The A1 multiplier for the dependent term will be set to -1.0 to create the desired equation.

Note: Care must be taken to make sure that a degree-of-freedom selected for an MPC actually exists at the nodes. For example, a node that is attached only to solid structural elements will not have any rotational degrees-of-freedom. However, MSC.Patran will allow you to select rotational degrees-of-freedom at this node when defining an MPC.

Holds the dependent term information. Only one node and DOF combination may be defined for any given explicit MPC. The A1 field on the MPC entry is automatically set to -1.0.

Holds the independent term information. As many coefficient, node, DOF combinations as desired may be defined.

Define Terms

Dependent Terms (1)

Independent Terms (No Max)

Create Dependent

Create Independent

Modify

Delete

Node 12

Node List

Auto Execute

UY

DOFs

Apply Reset Cancel

Nodes (1) DOFs (1)

Coefficient Nodes (1) DOFs (1)

UX

-3.4Coefficient =

14 UX

1. 7 UY

-3.4000> 12 UZ

UZ

◆◆ ◆◆

◆◆◆


Rigid (Fixed) MPCs

Creates an *MPC option of type BEAM for each dependent node (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This provides a rigid beam between two nodes to constrain the displacement and rotation at the first node to the displacement and rotation at the second node, corresponding to the presence of a rigid beam between the two nodes.

Holds the dependent term information. As many nodes as desired may be selected as dependent terms.

Holds the independent term information. Only one node may be selected.

Define Terms

Dependent Terms (No Max)

Independent Terms (1)

Node 4

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

14

10

6

4

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆

Rigid (Pinned) MPCs

Creates an *MPC of type LINK for each dependent node (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This provides a pinned rigid link between two nodes in order to keep the distance between the two nodes constant. The displacements of the first node are modified to enforce this constraint. The rotations at the nodes, if any, are not involved in this constraint.

Holds the dependent term information. As many nodes as desired may be selected as dependent terms.

Holds the independent term information. Only one node may be selected.

Define Terms

Dependent Terms (No Max)


Node 4

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

14

10

6

4

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆


Linear Surf-Surf MPCs

Creates an *MPC option of type LINEAR (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This is the standard method for mesh refinement of first-order elements.

This MPC constrains each degree-of-freedom at the dependent node to be interpolated linearly from the corresponding degrees-of-freedom at the independent nodes.

Note: Linear Surf-Surf and Linear Surf-Vol MPCs both generate the ABAQUS ∗ MPC type LINEAR.

Holds the dependent term information. The “1” in parentheses next to the Dependent Terms label indicates that exactly one dependent term must be specified. A dependent term consists of a single node. Existing dependent terms can be selected for modification or deletion.

Holds the independent term information. The “2” in parentheses next to the Independent Terms label indicates that exactly two terms must be specified. An independent term consists of a single node. Existing independent terms can be selected for modification or deletion.

Define Terms

Dependent Terms (1)


Node 8

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

7

6

8

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆

Linear Surf-Vol MPCs

Creates an *MPC option of type SS LINEAR (see Section 7.8.4 in the ABAQUS/Standard User’s Manual).

This is the standard method for mesh refinement of first-order elements. This MPC constrains each degree-of-freedom at the dependent node to be interpolated linearly from the corresponding degrees-of-freedom at the independent nodes.

Note: Linear Surf-Surf and Linear Surf-Vol MPCs both generate the ABAQUS ∗ MPC type SS LINEAR.

Define Terms

Dependent Terms (1)


Node 8

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

7

6

8

Holds the dependent term information. The “1” in parentheses next to the Dependent Terms label indicates that exactly one dependent term must be specified. A dependent term consists of asingle node. Existing dependent terms canbe selected for modification or deletion.

Holds the independent term information. The “2” in parentheses next to the Independent Terms label indicates that exactly two terms must be specified. An independent term consists of a single node. Existing independent terms can beselected for modification or deletion.Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆


Linear Vol-Vol MPCs

Creates an *MPC option of type BILINEAR (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This is a standard method for mesh refinement of first-order solid elements in three dimensions.

This MPC constrains each degree-of-freedom at the dependent node to be interpolated bilinearly from the corresponding degrees-of-freedom at the independent nodes.


Holds the independent term information. The “4” in parentheses next to the Independent Terms label indicates that exactly four terms must be specified. An independent term consists of a single node. Existing independent terms can be selected for modification or deletion.

Define Terms

Dependent Terms (1)


Node 12

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

5

10

6

2

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆

Quad. Surf-Surf MPCs

Creates an *MPC option of type QUADRATIC (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This is a standard method for mesh refinement of second-order elements.

This MPC constrains each degree-of-freedom at the dependent node to be interpolated quadratically from the corresponding degrees-of-freedom at the independent nodes.

Note: Quad Surf-Surf and Quad Surf-Vol MPCs both generate the ABAQUS *MPC type QUADRATIC


Holds the independent term information. The “3” in parentheses next to the Independent Terms label indicates that exactly three terms must be specified. An independent term consists of a single node. Existing independent terms can be selected for modification or deletion.

Define Terms

Dependent Terms (1)


Node 7

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

10

15

11

7

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆


Quad. Surf-Vol MPCs

Creates an *MPC option of type SS BILINEAR (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This is a standard method for mesh refinement of second-order elements.

This MPC constrains each degree-of-freedom at the dependent node to be interpolated quadratically from the corresponding degrees-of-freedom at the independent nodes.

Note: Quad Surf-Surf and Quad Surf-Vol MPCs both generate the ABAQUS ∗ MPC type SS BILINEAR.


Holds the independent term information. The “3” in parentheses next to the Independent Terms label indicates that exactly three terms must be specified. An independent term consists of a single node. Existing independent terms can be selected for modification or deletion.

Define Terms

Dependent Terms (1)


Node 7

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

10

15

11

7

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆

Quad. Vol-Vol MPCs

Creates an *MPC option of type C BIQUAD (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This is a standard method for mesh refinement of second-order solid elements in three dimensions.

This MPC constrains each degree-of-freedom at the dependent node to be interpolated by a constrained biquadratic from the corresponding degrees-of-freedom at the eight independent nodes.

Holds the independent term information. The “8” in parentheses next to the Independent Terms label indicates that exactly eight terms must be specified. An independent term consists of a single node. Existing independent terms can be selected for modification or deletion.


Define Terms

Dependent Terms (1)


Node 16

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

13

12

15

16

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆


Slider MPCs

Creates an *MPC option of type SLIDER (see Section 7.8.4 in the ABAQUS/Standard User’s Manual).

This MPC will keep a node on a straight line defined by two other nodes, but allows the possibility of moving along the line, and the line to change length.

Define Terms

Dependent Terms (1)


Node 8

Node List

CancelResetApply

Nodes (1)

Nodes (1)

7

6

8



Auto Execute

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆

Elbow MPCs

Creates an *MPC option of type ELBOW (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This MPC constrains two ELBOW31 or ELBOW32 elements together, where the cross-sectional direction changes.


Holds the independent term information. The “1” in parentheses next to the Independent Terms label indicates that exactly one term must be specified. An independent term consists of a single node. Existing independent terms can be selected for modification or deletion.

Define Terms

Dependent Terms (1)


Node 10

Node List

Auto Execute

CancelResetApply

Nodes (1)

10

Nodes (1)

6

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆


Pin MPCs

Creates an *MPC option of type PIN (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This MPC provides a pinned joint between two nodes. This makes the displacements equal, but leaves the rotations, if they exist, independent of each other.



Define Terms

Dependent Terms (1)


Node 10

Node List

Auto Execute

CancelResetApply

Nodes (1)

10

Nodes (1)

6

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆

Tie MPCs

Creates an *MPC option of type TIE (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This MPC makes all active degrees-of-freedom equal at two nodes.

If there are different degrees-of-freedom active at the two nodes, only those in common will be constrained. It is usually used to join two parts of a mesh when corresponding nodes on the two parts are to be fully connected.

Define Terms

Dependent Terms (1)


Node 10

Node List

Auto Execute

CancelResetApply

Nodes (1)

10

Nodes (1)

6Holds the dependent term information. The “1” in parentheses next to the Dependent Terms label indicates that exactly one dependent term must be specified. A dependent term consists of a single node. Existing dependent terms can be selected for modification or deletion.


Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆


Revolute MPCs

Creates an *MPC option of type REVOLUTE (see Section 7.8.4 in the ABAQUS/Standard User’s Manual).

Define Terms

Dependent Terms (1)


Node 8

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

7

6

8


Holds the independent term information. The “2” in parentheses next to the Independent Terms label indicates that exactly two terms must be specified. An independent term consists of a single node. Existing independent terms can be selected for modification or deletion.Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆

V Local MPCs

Creates an *MPC option of type V LOCAL (see Section 7.8.4 in the ABAQUS/Standard User’s Manual).



Define Terms

Dependent Terms (1)


Node 8

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

7

6

8

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆


Universal MPCs

Creates an *MPC option of type UNIVERSAL (see Section 7.8.4 in the ABAQUS/Standard User’s Manual).


Holds the independent term information. The “4” in parentheses next to the Independent Terms label indicates that exactly four terms must be specified. An independent term consists of a single node. Existing independent terms can be selected for modification or deletion.

Define Terms

Dependent Terms (1)


Node 7

Node List

Auto Execute

CancelResetApply

Nodes (1)

Nodes (1)

10

15

11

7

Create Dependent

Create Independent

Modify

Delete◆◆

◆◆

◆◆

◆

SS Linear MPCs

Creates an *MPC option of type SS LINEAR (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This MPC is used to constrain a shell node to a solid node line for linear elements (S4R or S4R5; C3D8, C3D8R; SAX1; CAX4; etc.) or for midside lines on quadratic elements (S8R, S8R5; C3D20, C3D20R; etc.).

This MPC is only valid for small rotations.

Define Terms

Dependent Terms (1)

Independent Terms (Min=2, Max=7)

Node 1

Node List

Auto Execute

Nodes (1)

9

Nodes (1)

11

Apply Reset Cancel

5

1


Holds the independent term information. An independent term consists of a single node. Existing independent terms can be selected for modification or deletion.

Create Dependent

Create Independent

Modify

Delete

◆◆

◆◆◆

◆◆


SS Bilinear MPCs

Creates an *MPC option of type SS BILINEAR (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This MPC is used to constrain a corner node of a quadratic shell element (S8R, S8R5) to a line of edge nodes on 20-node bricks.


Define Terms

Dependent Terms (1)


Node 1

Node List

Auto Execute

Nodes (1)

9

Nodes (1)

11

Apply Reset Cancel

5

1



Create Dependent

Create Independent

Modify

Delete

◆◆

◆◆◆

◆◆

SSF Bilinear MPCs

Creates an *MPC option of type SSF BILINEAR (see Section 7.8.4 in the ABAQUS/Standard User’s Manual). This MPC is used to constrain a corner node of a quadratic shell element (S8R, S8R5) to a line of edge nodes on 20-node bricks.


Define Terms

Dependent Terms (1)


Node 1

Node List

Auto Execute

Nodes (1)

9

Nodes (1)

11

Apply Reset Cancel

5

1



Create Dependent

Create Independent

Modify

Delete

◆◆

◆◆◆

◆◆

4CHAPTER

2.4 Material LibrarySelecting Materials from this MSC.Patran window displays the main form for the creation of materials. The following sections provide an introduction to the Materials form, followed by the details of all the material property definitions supported by the MSC.Patran ABAQUS Application Interface.

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Materials FormThe Materials form shown below provides the following options for the purpose of creating ABAQUS materials.

Displays the Input Prop form used to define the material properties.

A description of the material up to 2500 characters in length.

Lists the created materials whose names pass the filter.

Materials

Create

Isotropic

Manual Input

Filter*

Existing Materials

Material Names

Date: 18-Jan-93

Description

Preference:

Type:

ABAQUS

Structural

Input Properties ...

Change Material Status ...

Apply Reset

Action:

Object:

Method:

Generates a form that is used to indicate the models for this particular material that will be active in the current analysis. For more information, see Change Material Status (p. 45).

Indicates the active analysis type. This selection is made on the form in Preferences>Analysis (p. 343) in the MSC.Patran Reference Manual, Part 1: Basic Functions.

Indicates the method used to enter the material properties.

Time: 13:35:41

Defines the basic material orthotropy. This can be set to Isotropic, 2D Orthotropic, 3D Orthotropic, 2D Anisotropic, 3D Anisotropic, or Composite.

A material name up to 32 characters in length. A unique material ID will be directly assigned to the NAME parameter on the ∗ MATERIAL option.

Input Properties:

• Structural (p. 45)• Thermal (p. 43)

☞ More Help:

4CHAPTER

Change Material Status. The approach to defining material properties in MSC.Patran is similar to that in ABAQUS; the complete material model is defined by individually defining the necessary constitutive models. For example, to define a material for a plasticity analysis, one would first define the elastic properties and select Apply. Then the plastic properties are defined by selecting Plastic as Option 1, the yield criteria as Option 2, the hardening law as Option 3, entering the appropriate data and pushing Apply.

Not all constitutive model options are valid for a particular material in a particular ABAQUS analysis. For example, it is not permissible to have both elastic and hyperelastic properties defined for the same ABAQUS material. MSC.Patran, however, allows these different constitutive models to be defined and then “deactivated” for a given ABAQUS analysis. This is done on the form displayed when the Change Material Status button is selected on the main Materials form. For example, if a user defines both Elastic and Hyperelastic properties for a given material, one of these constitutive options must be deactivated on the Change Material Status form before initiating the ABAQUS analysis.

Temperature Dependence. ABAQUS allows most material properties to be functions of temperature. The ABAQUS interface in MSC.Patran generally supports this as well. The first step in defining a temperature dependent material property is to define a temperature dependent material field in the Fields application. This field can then be selected from a listbox on the Materials, Input Options form. When the databox for a material property that may be temperature dependent is selected, the fields listbox appears.

The following table shows the allowable selections for all options when the Action is set to Create and the Analysis Type in the Analysis Preference form is set to Structural. The various options have different names, depending on previous selections.

Object Option 1 Option 2 Option 3Isotropic ❏ Elastic Material Failure Theory

Hyperelastic Incompressible Test Data❏ Ogden

❏ Polynomial

Coefficients❏ Ogden❏ Mooney Rivlin

❏ Neo Hookean

❏ PolynomialSlightly Compressible Test Data

❏ Ogden

❏ Polynomial

Coefficients❏ Ogden❏ Polynomial

Compressible Test Data❏ OgdenCoefficients❏ Ogden

Viscoelastic Frequency ❏ Formula

❏ Tabular

Time ❏ Prony❏ Creep Test Data

❏ Combined Creep Test Data

❏ Relaxation Test Data

❏ Combined Relax Test Data❏ Deformation

PlasticityPlastic Mises/Hill ❏ Perfect Plasticity

❏ Isotropic❏ Kinematic

❏ Drucker-Prager CompressionTensionShear

Modified D-Prager/Cap Cap HardeningCreep ❏ Time

❏ Strain❏ Hyperbolic

2D Orthotropic (Lamina)

❏ Elastic Material Failure Theory

Viscoelastic Frequency ❏ FormulaTabular


Combined Creep Test Data❏ Relaxation Test Data

Combined Relax Test DataPlastic Mises/Hill ❏ Perfect Plasticity





3D Orthotropic

❏ Elastic Engineering Constants❏ [D] Matrix

Material Failure Theory

Viscoelastic Frequency ❏ FormulaTabular

Object Option 1 Option 2 Option 3

4CHAPTER


Combined Creep Test Data❏ Relaxation Test Data

Combined Relax Test DataPlastic Mises/Hill ❏ Perfect Plasticity





3D Anisotropic

❏ Elastic [D] Matrix Material Failure TheoryViscoelastic Frequency ❏ Formula

TabularTime ❏ Prony

❏ Creep Test DataCombined Creep Test Data

❏ Relaxation Test DataCombined Relax Test Data

Plastic Mises/Hill ❏ Perfect Plasticity❏ Isotropic❏ Kinematic




Composite ❏ LaminateRule of MixturesHAL Cont. FiberHAL Disc. FiberHAL Cont. RibbonHAL Disc. RibbonHAL ParticulateShort Fiber 1DShort Fiber 2D


The following table shows the allowable selections for all options when the Action is set to Create and the Analysis Type is set to Thermal in the Analysis Preference form. The various options have different names, depending on previous selections.

Object Option 1Isotropic Thermal3D Orthotropic Thermal3D AnisotropicComposite Laminate

Rule of MixturesHAL Cont. FiberHAL Disc. FiberHAL Cont. RibbonHAL Disc. RibbonHAL ParticulateShort Fiber 1DShort Fiber 2D

4CHAPTER

Isotropic

Elastic

Object Option 1 Option 2

Isotropic Elastic Material Failure Theory

Input Options

ElasticConstitutive Model:

Material Failure Theory: None

Property Name Value

Poisson’s Ratio =

Elastic Modulus =

Density =

Current Constitutive Models:

-Apply- Clear Cancel

These input boxes define Young’s modulus and Poisson’s ratio for an isotropic, linearly elastic material.

Defines the material mass density.

More data input is available for defining the Elastic properties for the Isotropic materials. Listed below are the descriptions for the remaining material properties.

Property Name Description

Reference Temperature This is the reference value of temperature for the coefficient of thermal expansion. The thermal strain in the material is based on the difference between the current temperature and this reference value (default is 0.0).

Thermal Expansion Coeff Coefficient of thermal expansion for the isotropic material.

Fraction Critical Damping Set this parameter equal to the fraction of critical damping to be used with this material in calculating composite damping factors for the modes (for use in modal dynamics). The default is 0.0. The value is ignored in direct integration dynamics.

Mass Propornl Damping Factor for mass proportional damping in direct integration dynamics (default = 0.0). This value is ignored in modal dynamics.

Stiffness Propornl Damping Factor for stiffness proportional damping in direct integration dynamics (default = 0.0). This value is ignored in modal dynamics.

5CHAPTER

Hyperelastic


Isotropic Hyperelastic Incompressible Test Data -OgdenPolynomial

Input Options

Constitutive Model:

Test Data

Compressibility:

Data Type:

Property Name Value


Uniaxial Stress =

Strain Energy Potential: Ogden

Incompressible

Order of Polynomial: 1

Hyperelastic


Biaxial Stress =

Planar Stress =

Density =

Thermal Expansion Coeff =

Strain dependent material field defining uniaxial test data.

Strain dependent material field defining biaxial test data.

Strain dependent material field defining planar test data.

Coefficient of thermal expansion for the isotropic material.


Hyperelastic


Isotropic Hyperelastic Incompressible Coefficients - Ogden

Input Options

Constitutive Model:

Coefficients

Compressibility:

Data Type:

Property Name Value


Coefficient MU1 =


Incompressible


Hyperelastic


Coefficient ALPHA1 =

Density =


Polynomial exponents for the Ogden strain energy potential.



Polynomial coefficients for the Ogden strain energy potential.

5CHAPTER

Hyperelastic


Isotropic Hyperelastic Incompressible Coefficients - Moony RivlinNeo HookeanPolynomial

Input Options

Constitutive Model:

Coefficients

Compressibility:

Data Type:

Property Name Value


Coefficient C10 =

Strain Energy Potential: Polynomial

Incompressible


Hyperelastic


Coefficient C01 =

Density =




Coefficients for the polynomial form of the hyperelastic strain energy potential.

Hyperelastic


Isotropic Hyperelastic Slightly Compressible Test Data -OgdenPolynomial

Input Options

Constitutive Model:

Test Data

Compressibility:

Data Type:

Property Name Value


Uniaxial Stress =


Slightly Compressible


Hyperelastic


Biaxial Stress =

Planar Stress =

Volumetric Pressure =

Density =







Strain dependent material field defining volumetric test data. Defines the compressibility of the material.

5CHAPTER

Hyperelastic


Isotropic Hyperelastic Slightly Compressible Coefficients - Ogden

Input Options

Constitutive Model:

Coefficients

Compressibility:

Data Type:

Property Name Value


Coefficient MU1 =




Hyperelastic



Coefficient D1 =

Density =

Thermal Expansion Coeff =Defines the material mass density.




Coefficient defining compressibility in the Ogden Strain energy potential.

Hyperelastic


Isotropic Hyperelastic Slightly Compressible Coefficients - Polynomial

Input Options

Constitutive Model:

Coefficients

Compressibility:

Data Type:

Property Name Value


Coefficient C10 =

Strain Energy Potential: Polynomial



Hyperelastic


Coefficient C01 =

Coefficient D1 =

Density =

Thermal Expansion Coeff = Defines the material mass density.


Coefficients for the polynomial form of the hyperelastic strain energy potential.

Coefficient defining compressibility in the polynomial form of the strain energy potential.

5CHAPTER

Hyperelastic


Isotropic Hyperelastic Compressible Test Data - Ogden

Input Options

Constitutive Model:

Test Data

Compressibility:

Data Type:

Property Name Value


Uniaxial Stress =


Compressible


Hyperelastic


Uniaxial Lateral Strain =

Biaxial Stress =

Biaxial Lateral Strain =

Planar Stress =

Planar Lateral Strain =

Shear Stress =

Shear Trans Stress =

Material field defining lateral strain as a function of axial strain. (The default is zero. Not needed if a value is entered for Poisson’s Ratio.)




Material field defining lateral strain as a function of axial strain. (The default is zero. Not

Strain dependent material field defining shear test data.

Material field defining transverse stress as a function of shear strain.

1

3

4

5

6

2

2

2

1

2

3

4

5

6

More data input is available for defining the Hyperelastic properties. Listed below are the descriptions for the remaining material properties.


Volumetric Pressure Material field defining volume ratio (current volume/original volume) as a function of pressure. This field appears on the *VOLUMETRIC TEST DATA sub option.

Poisson’s Ratio Effective Poisson’s ratio of the material which will be equal to all . This is the value of the POISSON parameter on the

*HYPERFOAM option. If no value is given, the lateral strains should be entered.

Density Defines the material mass density. This quantity appears on the *DENSITY option.

Thermal Expansion Coeff Coefficient of thermal expansion for the isotropic material. This parameter appears as a on the *EXPANSION option.

ν i

5CHAPTER

Hyperelastic


Isotropic Hyperelastic Compressible Coefficients - Ogden

Input Options

Constitutive Model:

Coefficients

Compressibility:

Data Type:

Property Name Value


Coefficient MU1 =


Compressible


Hyperelastic



Coefficient NU1 =

Density =




Polynomial coefficients defining compressibility effects.



Viscoelastic


Isotropic, 2D Orthotropic,3D Orthotropic or 3D Anisotropic

Viscoelastic Frequency TabularFormula

Input Options

ViscoelasticConstitutive Model:

Domain Type:

Definition Type:

Property Name Value


Imaginary Part of wg =

Real Part of wg =

Real Part of wk =

Frequency

Imaginary Part of wk =

Tabular


Material field defining the real part of ϖg as a function of frequency.

Material field defining the imaginary part of ϖg as a function of frequency.

Material field defining the real part of ϖk as a function of frequency.

Material field defining the imaginary part of ϖk as a function of frequency.

6CHAPTER

Viscoelastic



Viscoelastic Time Prony

Input Options


Domain Type:

Definition Type:

Property Name Value


Bulk Relax Modulus Ratio =

Shear Relax Modulus Ratio =

Time

Prony


Time dependent material field for shear relaxation modulus. Each entry in the field defines a term and its associated relaxation time τ i in the Prony series.

ρ–δI-----

Time dependent material field for bulk relaxation modulus. Each entry in the field defines a term and its associated relaxation time τi in the Prony series.

kip

Viscoelastic



Viscoelastic Time Creep Test DataCombined Creep Test Data

Input Options


Domain Type:

Definition Type:

Property Name Value


Maximum Number of Terms =

Average RMS Error =

SHRINF =

Time

Normalzd Shear Compliance =

Creep Test Data


VOLINF =

Allowable average root-mean-square error of the data points in the least squares fit. Default is 0.01.

Maximum number of terms N in the Prony series. ABAQUS will perform the least squares fit from N=1 to N=MAX until convergence is achieved for the lowest N with respect to ERRTOL. The default and maximum value is 13.

Material field with normalized shear compliance as a function of time.

Value of the long term, normalized volumetric compliance.

Material field with bulk compliance as a function of time.

Normalzd Bulk Compliance =

Value of the long term, normalized shear compliance.

6CHAPTER

Viscoelastic



Viscoelastic Time Relaxation Test DataCombined Relax Test Data

Input Options


Domain Type:

Definition Type:

Property Name Value


Maximum Number of Terms =

Average RMS Error =

SHRINF =

Time

Normalzd Shear Modulus =

Relaxation Test Data


VOLINF =

Normalzd Bulk Modulus =

Allowable average root-mean-square error of the data points in the least squares fit. Default is 0.01. This is the value of the ERRTOL parameter on the ∗ VISCOELASTIC option.

Maximum number of terms N in the Prony series. ABAQUS will perform the least squares fit from N=1 to N=MAX until convergence is achieved for the lowest N with respect to ERRTOL. The default and maximum value is 13.

Material field with normalized shear modulus as a function of time.

Value of the long term, normalized volumetric modulus.

Material field with normalized volumetric modulus as a function of time.

Value of the long term, normalized shear modulus.

Deformation Plasticity

Object Option 1

Isotropic Deformation Plasticity

Input Options

Constitutive Model:

Property Name Value


Elastic Modulus =

Deformation Plasticity

Poisson’s Ratio =

Yield Stress =

Exponent=

Yield Offset =


Young’s modulus (slope of the stress-strain curve at zero stress).

Coefficients in the Ramberg-Osgood model.

6CHAPTER

Plastic



Plastic Mises/Hill Perfect Plasticity

Input Options

Constitutive Model:

Perfect Plasticity

Yield Criteria:

Hardening Rule:

Property Name Value


Yield Stress =

Rate Dependency: Power Law

Mises/Hill

Anisotropic Yield: Add

Plastic

Rate Dependent Param D =

Rate Dependent Param p =


S11/So =

S22/So =

S33/So =

S12*SQRT(3)/SO =

S13*SQRT(3)/SO =

Stress where perfectly plastic behavior is assumed to begin.

Coefficients defining the change in yield stress as a function of strain rate.

Ratios of yield stress for the six stress components to the equivalent yield stress.

S23*SQRT(3)/SO =

Enables the definition of rate dependency values used by the ∗ RATE DEPENDENT option.

Enables the definition of anisotropic yield values used by the ∗ POTENTIAL option.

Plastic


Isotropic, 2DOrthotropic,3DOrthotropic or 3D Anisotropic

Plastic Mises/Hill Isotropic

Input Options

Constitutive Model:

Isotropic

Yield Criteria:

Hardening Rule:

Property Name Value


Stress Strain vs. Strain Rate =

Rate Dependency: Strain Rate

Mises/Hill

Anisotropic Yield: None

Plastic


A material field defining yield stress as a function of plastic strain.



6CHAPTER

Plastic


Isotropic, 2D Orthotropic,3DOrthotropic or 3D Anisotropic

Plastic Mises/Hill Kinematic

Input Options

Constitutive Model:

Kinematic

Yield Criteria:

Hardening Rule:

Property Name Value


Yield Stress =

Rate Dependency: Yield Ratio

Mises/Hill


Plastic

2nd. Yield Stress =

Plastic Strain =


Initial yield stress for the material.

Second yield point on the stress-strain curve for the material.



Yield Ratio vs Strain Rate=

Yield stress ratio verses strain rate defined in the field menu under Material Property using the strain rate option.

Plastic



Plastic Drucker-Prager CompressionTensionShear

Input Options

Constitutive Model:

Compression

Yield Criteria:

Hardening Rule:

Property Name Value


Material Friction Angle =

Rate Dependency: None

Drucker-Prager


Plastic

Ratio of Flow Stresses =

Dilation Angle =

Stress vs. Plastic Strain =


Material angle of friction, β, in the p-t plane. Give the value in degrees.

K, the ratio of the flow stress in triaxial tension to the flow stress in triaxial compression. 0.778 ≤ K ≤ 1.0. If this field is left blank or a value of 0.0 is entered, the default of 1.0 is used.

Dilation angle ψ in the p-t plane. Give the value in degrees.

Material field defining yield stress as a function of plastic strain on the yield option.

Not currently used.


6CHAPTER

Plastic



Plastic ModifiedD-Prager/Cap

Cap Hardening

Input Options

PlasticConstitutive Model:

Yield Criteria: Modified D-Prager/Cap

Property Name Value


Material Friction Angle =

Material Cohesion =

Eccentricity Parameter =

Yield Surface Transition =

SurfaceRadiusParameter=

Ratio of Flow Stresses =


Hardening Rule:

Rate Dependency:

Cap Hardening

None

Stress vs. Plastic Strain =

Anisotropic Yield: NoneMaterial cohesion d, in the p-t plane.

Material angle of friction, β, in the p-t plane. Give the value in degrees.

K, the ratio of the flow stress in triaxial tension to the flow stress in triaxial compression. 0.778 ≤ K ≤ 1.0. If this field is left blank or a value of 0.0 is entered, the default of 1.0 is used.

Material field defining yield stress as a function of plastic strain on the *CAP HARDENING option.

Cap eccentricity parameter, R. Its value must be greater than 0.0 and less than or equal to 1.0.

Not currently used.

Creep



Creep TimeStrain

Input Options

CreepConstitutive Model:

Law:

NoneAnisotropic Yield:

Property Name Value


Value of n =

Value of a =

Value of m =

Time


Coefficient in the time power law.

Exponents in the time power law.

Enables the definition of anisotropic creep values used by the ∗ POTENTIAL option.

7CHAPTER

Creep



Creep Hyperbolic

Input Options

Property Name Value


Value of b =

Value of a =

Value of n =

Value of delta_H =

Value of R =

CreepConstitutive Model:

Law:

NoneAnisotropic Yield:

Hyperbolic


Constants in the hyperbolic sine law. The value of delta_H may be left blank if temperature dependence is not needed.

Enables the definition of anisotropic creep values used by the ∗ POTENTIAL option.

2D Orthotropic (Lamina)

Elastic

Option 1 Option 2

Elastic Material Failure Theory

Input Options



Property Name Value


Elastic Modulus 22 =


Poisson’s Ratio 12 =

Shear Modulus 12 =

Shear Modulus 13 =

Shear Modulus 23 =


Elastic constants for a 2D orthotropic material.

Density Defines the material mass density.

Enables the introduction of material failure theory for compression or tension only.

7CHAPTER

3D Orthotropic

Elastic

Option 1 Option 2 Option 3

Elastic Engineering Constants Material Failure Theory

Input Options


Elastic Constants: Engineering Constants

Property Name Value










Shear Modulus 12 =

Shear Modulus 13 =

Elastic constants for a 3D orthotropic material (the generalized Young’s moduli, Poisson’s ratios and shear moduli in the principal directions).




Elastic


3D Orthotropic Elastic [D] Matrix Material Failure Theory

Input Options


Elastic Constants Input: None

Property Name Value


D1122 (C12) =

D1111 (C11) =

D2222 (C22) =

D1133 (C13) =

D2233 (C23) =

D3333 (C33) =


D1212 (C44) =

D1313 (C55) =

Coefficients in the 6x6 stress-strain matrix for the 3D orthotropic material.

D2323 (C66) = Defines the material mass density.

Density

Elastic Constants: [D] Matrix


7CHAPTER

3D Anisotropic

Elastic

Option 1 Option 2

Elastic [D] Matrix

Input Options



Property Name Value


D1122 (C12) =

D1111 (C11) =

D2222 (C22) =

D1133 (C13) =

D2233 (C23) =

D3333 (C33) =


D1112 (C14) =

D2212 (C24) =

Coefficients in the 6x6 stress-strain matrix for the 3D anisotropic material.

.Enables the introduction of material failure theory for compression or tension only.

More data input is available for defining the Elastic properties for the 3D Anisotropic materials. Listed below are the descriptions for the remaining material properties.

Property Name Desciption

D1212 (C34)

D1212 (C44)

D1113 (C15)

D2213 (C25)

D3313 (C35)

D1213 (C45)

D1313 (C55)

D1123 (C16)

D2223 (C26)

D3323 (C36)

D1223 (C46)

D1323 (C56)

D2323 (C66)

Coefficients in the 6 x 6 stress-strain matrix for the 3D anisotropic material.


7CHAPTER

Isotropic (Thermal)

Input Options

ThermalConstitutive Model:

Property Name Value


Conductivity =

Specific Heat =

Density =



Specific heat per unit mass for the material.

Thermal conductivity for the isotropic material.

Latent Heat vs Solidus

Latent Heat vs Liquidus

Defines temperature dependent field for latent heat vs solidus.

Defines temperature dependent field for latent heat vs liquidus.

3D Orthotropic (Thermal)

Input Options


Property Name Value


Conductivity 11 =

Conductivity 22 =

Conductivity 33 =


Specific Heat =

Density =



Thermal conductivity matrix for the 3D orthotropic material.

7CHAPTER

3D Anisotropic (Thermal)

Input Options


Property Name Value


Conductivity 11 =

Conductivity 22 =

Conductivity 33 =


Conductivity 12 =

Conductivity 13 =

Conductivity 33 =

Specific Heat =

Density =



Thermal conductivity matrix for the 3D anisotropic material.

Composite

The Composite forms allow existing materials to be combined to create new materials. All of the composite materials, with the exception of the laminated composites, can be assigned to elements like any homogeneous material through the element property forms. For the laminated composites, the section thickness is entered indirectly through the definition of the stack, and the Homogeneous option on the Element Properties Form (p. 82) for shells, plates and beam must be changed to Laminate to avoid reentry of this information.

For details on how to use these forms, refer to the Composite Materials Construction (p. 75) in the MSC.Patran Reference Manual, Part 5: Functional Assignments.

Laminate

Laminated Composite

TotalStacking Sequence Convention Offset

Insert Material Names

Load Text Into Spreadsheet

InsertText Entry Mode

Material NamesThicknessesOrientations

Delete Selected Rows

Stacking Sequence Definition: Select an Existing Material.

Show Laminate Properties... Clear Text and Data Boxes

Material Name Thickness Orientation

◆

◆◆

◆◆

8CHAPTER

2.5 Element PropertiesBy choosing the Element Properties item, located on the application switch for MSC.Patran, an element properties form will appear. When creating element properties, several option menus are available. The selections made in these option menus will determine which element property form is presented, and ultimately, which ABAQUS element will be created.

The following pages give an introduction to the Element Properties form, followed by the details of all the element property definitions supported by the MSC.Patran ABAQUS Application Preference.

MSC.Patran

hp, 2




Viewing

Element Properties FormWhen Element Properties is selected on the main menu, this is the form which will be displayed. Four option menus on this form are used to determine which ABAQUS element types are to be created, and which property forms are to be displayed. The individual property forms are documented later in this section. For more details, see the Element Properties Forms (p. 41) in the MSC.Patran Reference Manual, Part 5: Functional Assignments.

Element Properties

Create Action:

2D Dimension:

Shell Type:

Option(s):

Homogeneous

Existing Property Sets

Input Properties...

Select Members

Add Remove

Application Region

Application Region

-Apply-

Property Set Name

Thin

By choosing this toggle your options are:

0D (point elements)1D (bar elements)2D (tri and quad elements)3D (tet, wedge, and hex elements)

This menu depends on the selection made in the Dimension option menu. This defines the general type of element, such as:

Mass versus Grounded SpringShell versus 2D_Solid

These option menus may or may not be presented and their contents depend heavily on the selections made in Dimension and Type. These buttons will be referred to as Option 1 and Option 2.

Input Properties:• Structural (p. 83)• Thermal (p. 95)

☞ More Help:

8CHAPTER

The following table shows the allowable selections for all option menus when Analysis Type is set to Structural.

Dimension Type Option 1 Option 2 Name

0D ❏ Mass MASS

❏ Rotary Inertia ROTARYI

Grounded Spring ❏ Linear❏ Nonlinear

SPRING1SPRING2

Grounded Damper ❏ Linear❏ Nonlinear

DASHPOT1DASHPOT2

IRS (single node) ❏ Planar Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

IRS12

❏ Spatial Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

IRS13

1D Beam in XY Plane ❏ General Section Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

❏ Box Section Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

❏ Circular Beam (Solid) Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

❏ Hexagonal Beam Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

❏ I Section Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

❏ Pipe Section Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

❏ Rectangular Section Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

❏ Trapezoid Section Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

Beam in Space ❏ General Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

❏ Arbitrary Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

❏ Box Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

❏ Circular Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

❏ Curved w/Pipe Section Standard Formulation

Ovalization OnlyOvalization Only with Approximated Fourier

ELBOW31, ELBOW32

ELBOW31BELBOW31C


8CHAPTER

❏ Hexagonal Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

❏ I Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

❏ L Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

❏ Open Section Standard FormulationHybrid

B31OS, B32OSB31OSH, B32OSH

❏ Pipe Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

❏ Rectangular Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

❏ Trapezoidal Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

❏ Truss Standard FormulationHybrid

CID2, CID3CID2H, CID3H

Spring Linear ❏ Standard Formulation❏ Fixed Direction

SPRINGASPRING2

Nonlinear ❏ Standard Formulation❏ Fixed Direction

Damper Linear ❏ Standard Formulation❏ Fixed Direction

DASHPOTADASHPOT2

Nonlinear ❏ Standard Formulation❏ Fixed Direction


1D (continued)

Gap ❏ Cylindrical True DistanceElastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

GAPCYL

❏ Spherical True DistanceElastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

GAPSPHER

❏ Uniaxial True DistanceElastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

GAPUNI

Axisym Shell ❏ Homogeneous❏ Laminate

SAX1, SAX2


8CHAPTER

1D (continued)

❏ 1D Interface Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

INTER1

ISL (in plane) ❏ Planar Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

ISL21, ISL22

❏ Axisymmetric Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

ISL21A, ISL22A

ISL (in space) ❏ Parallel Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

ISL31, ISL32ISL31, ISL32


1D(continued)

ISL (in space) (continued)

❏ Radial Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

ISL31A, ISL32A

❏ Slide Line --

IRS (planar/axisym)

❏ Planar Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

IRS21, IRS22

❏ Axisymmetric Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation1D (cont.)

IRS21A, IRS22A

❏ IRS (beam/pipe) Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

IRS31, IRS32


8CHAPTER

1D(continued)

❏ Rigid Surf (Seg)❏ Rigid Surf (Cyl)❏ Rigid Surf (Axi)❏ Rigid Surf (Bz2D)❏ Rigid Line (Lbc)

--------R2D2, RAX2

❏ Rebar Axisymmetric SFMAX1, SFMAX2

General Axisymmetric SFMGAX1, SFMGAX2

❏ Mech Joint (2D Model)

ALIGN

AXIAL

BEAM

CARTESIAN

JOIN

JOINTC

LINK

ROTATION

SLOT

TRANSLATOR

WELD

❏ Mech Joint (3D Model)

ALIGN

AXIAL

BEAM

CARDAN

CARTESIAN

CONSTANT VELOCITY

CVJOINT

CYLINDRICAL

EULER

FLEXION-TORSION

HINGE

JOIN

JOINTC

LINK

PLANAR


RADIAL-THRUST

REVOLUTE

ROTATION

SLIDE-PLANE

SLOT

TRANSLATOR

UJOINT

UNIVERSAL

WELD

❏ 1D Gasket Axisymmetric Link Gasket Behavior Model GKAX2

Thickness Behavior Only GKAX2N

Built-in Material GKAX2

3D Link Gasket Behavior Model GK3D2

Thickness Behavior Only GK3D2N

Built-in Material GK3D2

2D Link Gasket Behavior Model GK2D2

Thickness Behavior Only GK2D2N

Built-in Material GK2D2


9CHAPTER

,

2D Shell Thin ❏ HomogeneousLaminate

STRI35, S4R5, STRI65, S8R5, S9R5

Thick HomogeneousLaminate

S3R, S4R, STRI65,S8R

❏ General Thin HomogeneousLaminate

STRI35, S4R5, STRI65, S8R5, S9R5

❏ General Thick HomogeneousLaminate

S3R, S4R, STRI65,S8R

❏ Large Strain

❏ General Large Strain S3R, S4R, S8R

2D Solid ❏ Plane Strain Standard Formulation CPE3, CPE4, CPE6, CPE8

Hybrid CPE3H, CPE4H, CPE6H, CPE8H

Hybrid / Reduced Integration

CPE4RH, CPE8RH

Reduced IntegrationIncompatible ModesHybrid/Incompatible ModesModifiedModified/Hybrid

CPE4R, CPE8RCPE4ICPE4IH

CPE6M, CPE6MH

❏ Plane Stress Standard Formulation

Reduced IntegrationIncompatible ModesModifiedModified/Hybrid

CPS3, CPS4, CPS6CPS8

CPS4R, CPS8RCPS4I

CPS6M, CPS6MH


2D(continued)

2D Solid (continued)

❏ Axisymmetric Standard Formulation CAX3, CAX4, CAX6, CAX8

Hybrid CAX3H, CAX4H,CAX6H, CAX8H

Hybrid/Reduced Integration

CAX4RH, CAX8RH

Reduced Integration CAX4R, CAX8R

Incompatible Modes CAX4I

Hybrid/Incompatible Modes

CAX4IH

Modified CAX6M

Modified/Hybrid CAX6MH

❏ Axisymmetric with Twist

Standard Formulation CGAX3, CGAX4, CGAX6, CGAX8

Hybrid CGAX3H, CGAX4H, CGAX6H, CGAX8H

Hybrid/Reduced Integration

CGAX4RH, CGAX8RH

Reduced Integration CGAX4R, CGAX8R

❏ Membrane Standard Formulation M3D3, M3D4, M3D6, M3D8, M3D9

Reduced Integration M3D4R, M3D8R, M3D9R

2D Interface ❏ Planar Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

INTER2, INTER3


9CHAPTER

2D(continued)

2D Solid (continued)

❏ Axisymmetric Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

INTER2A, INTER3A

IRS (shell/solid) Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

IRS3, IRS4, IRS9

❏ Rigid Surf (Bz3D) --

❏ Rigid Surface(Lbc)

R3D3, R3D4

❏ 2D Rebar Cylindrical SFMCL9

General Standard Formulation SFM3D3, SFM3D4, SFM3D6, SFM3D8

Reduced Integration SFM3D4R, SFM3D8R

❏ 2D Gasket Plane Strain Gasket Behavior Model GKPE4

Built-in Material GKPE4

Plane Stress Gasket Behavior Model GKPS4

Thickness Behavior Only GKPS4N

Built-in Material GKPS4

Axisymmetric Gasket Behavior Model GKAX4

Thickness Behavior Only GKAX4N

Built-in Material GKAX4

Line Gasket Behavior Mode GK3D4L

Thickness Behavior Only GK3D4LN

Built-in Material GK3D4L


3D ❏ Solid Standard FormulationLaminate

C3D4, C3D6, C3D8, C3D10, C3D15, C3D20

HybridLaminate

C3D4H, C3D6H, C3D8H, C3D10H,C3D15H, C3D20H

Hybrid/Red Integration Laminate

C3D8RH, C3D20RH

Reduced Integration Laminate

C3D8R, C3D20R

Incompatible Modes Laminate

C3D8I

Hybrid/Incomp ModesLaminateModifiedModified/Hybrid

C3D8IH

C3D10MC3D1OH

❏ 3D Interface Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

INTER4, INTER8,INTER9

❏ Gasket Gasket Behavior Model GK3D8, GK3D6

Thickness Behavior Only GK3D8N, GK3D6N

Built-in Material GK3D8, GK3D6


9CHAPTER

The following table shows the allowable selections for all option menus when Analysis Type is set to Thermal.


1D ❏ Link DCID2, DCID3

Axisymmetric Shell

❏ Homogeneous❏ Laminate

DSAX1, DSAX2

❏ 1D Interface DINTER1

2D Shell ❏ Homogeneous❏ Laminate

DS4, DS8

2D Solid ❏ Planar Standard Formulation

Convection/DiffusionConvection/Diffusion with Dispersion/Control

DC2D2, DC2D4,DC2D6, DC2D8

DCC2D4DCC2D4D

❏ Axisymmetric Standard Formulation

Convection/DiffusionConvection/Diffusion with Dispersion/Control

DCAX3, DCAX4,DCAS6, DCAX8

DCCAX4DCCAX4D

❏ 2D Interface Planar DINTER2, DINTER3

Axisymmetric DINTER2A, DINTER3A

3D ❏ Solid Standard Formulation DC3D4, DC3D6, DC3D8, DC3D10, DC3D15, DC3D20

Convection/Diffusion DCC3D8

Convection/Diffusion with Dispersion Control

DCC3D8D

❏ 3D Interface DINTER4, DINTER8

Point Mass

Options above create MASS elements with ∗ MASS properties.This creates a concentrated mass at a point. The mass is associated with the translational degrees-of-freedom at a node.

Analysis Type Dimension Type Option 1 Option 2 Topologies

Structural 0D Mass Point/1

Defines the mass of the element. This is the mass value on the ∗ MASS option. This can be either a real constant or a reference to an existing field definition. This property is required.

Defines the mass proportionality factor for the MASS element when used in direct integration dynamics. This value is ignored in modal dynamics. The default is 0.0. This is the value of the ALPHA parameter on the ∗ MASS option. This can be either a real constant or a reference to an existing field definition.

Defines the fraction of critical damping to be used when calculating composite damping factors for the modes when used in modal dynamics. This value is ignored in direct integration dynamics. The default is 0.0. This is the value of the COMPOSITE parameter on the ∗ MASS option. This can be either a real constant or a reference to an existing field definition.

Input Properties

Point Mass

Property Name Value Value Type

OK

Mass Magnitude

[Mass Damping Factor ]

[ Crit Damping Factor ]

Real Scalar

Real Scalar

Real Scalar

Field Definitions

9CHAPTER

Rotary Inertia

Options above createROTARI elements with ∗ ROT ARY INERTIA properties. This element allows the rotary inertia of a rigid body to be included at a node. An ∗ ORIENTATION option may also be created, as required.


Structural 0D Rotary Inertia Point/1

Defines the fraction of critical damping to be used when calculating composite damping factors for the modes when used in modal dynamics. This value is ignored in direct integration dynamics. The default is 0.0. This is the value of the COMPOSITE parameter on the ∗ ROTARY INERTIA option. This can be either a real constant or a reference to an existing field definition.

Defines the orientation of this rigid body in space. This defines the ORIENTATION parameter on the ∗ ROTARY INERTIA option. This is a reference to an existing coordinate system.

Define the I11, I22, and I33 rotary inertia value on the *ROTARY INERTIA option. These values can be either real constants or references to existing field definitions.

Input Properties

Rotary Inertia


OK

[ Rotary Inertia,XX ]

[ Rotary Inertia, YY ]

[ Rotary Inertia, ZZ ]

Real Scalar

Real Scalar

Real Scalar

[ Orientation System ]

[ Mass Damping Factor ]

[ Crit Damping Factor ]

Real Scalar

Real Scalar

CID

Field Definitions

Defines the mass proportionality factor for the MASS element when used in direct integration dynamics. This value is ignored in modal dynamics. The default is 0.0. This is the value of the ALPHA parameter on the ∗ ROTARY INERTIA option. This can be either a real constant or a reference to an existing field definition.

Linear Spring (Grounded)

Options above create SPRING1 elements with ∗ SPRING properties. This element defines a linear spring between a node and ground. An ∗ ORIENTATION option may also be created, as required.


Structural 0D Grounded Spring Linear Point/1

Defines the linear spring coefficient on the ∗ SPRING option. This can be either a real constant or a reference to an existing field definition. If a field definition is referenced, it will be evaluated at the element centroid to derive the linear coefficient for each spring element. This property is required.

Defines the degree-of-freedom with which the springs are associated at their first nodes. This is an integer value, indicating the degree-of-freedom ID to be used. This property is required.

Input Properties

Linear Spring (Grounded)


OK

Stiffness

Dof at Node 1


Integer

CID

Real Scalar

Field Definitions

Defines the orientation of this property data. This defines the ORIENTATION parameter on the ∗ SPRING option. This is a reference to an existing coordinate system.

9CHAPTER

Nonlinear Spring (Grounded)

Options above create SPRING1 elements with ∗ SPRING properties. This element defines a nonlinear spring between a node and ground. An ∗ ORIENTATION option may also be created, as required.


Structural 0D Grounded Spring Nonlinear Point/1

Defines the nonlinear spring coefficients on the ∗ SPRING option. These are lists of real constants. The two lists must have the same number of values. These properties are required.

Defines the orientation of this property data. This defines the ORIENTATION parameter on the ∗ SPRING option. This is a reference to an existing coordinate system.

Input Properties

Non-Linear Spring (Grounded)


OK

Force

Displacement


Real List

CID

Real List

Dof at Node 1 Integer

Defines the degree-of-freedom with which the springs are associated at their first nodes. This is an integer value, indicating the degree-of-freedom ID to be used. This property is required.

Linear Damper (Grounded)

Options above create DASHPOT1 elements with ∗ DASHPOT properties. This element defines a linear damper between a node and ground. An ∗ ORIENTATION option may also be created, as required.


Structural 0D Grounded Damper Linear Point/1

Defines the linear dashpot coefficient on the ∗ DASHPOT property option. This can be either a real constant or a reference to an existing field definition. If a field definition is referenced, it will be evaluated at the element centroid to derive the linear coefficient for each dashpot element. This property is required.

Defines the orientation of this property data. This defines the ORIENTATION parameter on the ∗ DASHPOT option. This is a reference to an existing coordinate system.

Input Properties

Linear Damper (Grounded)


OK

Damping Coefficient

Dof at Node 1


Integer

CID

Real Scalar

Field Definitions

Defines the degree-of-freedom with which the dashpots are associated at their first node. This is an integer value, indicating the degree-of-freedom ID to be used. This property is required.

1CHAPTER

Nonlinear Damper (Grounded)

Options above create DASHPOT1 elements with ∗ DASHPOT properties. This element defines a nonlinear dashpot between a node and ground. An ∗ ORIENTATION option may also be created, as required.


Structural 0D Grounded Damper Nonlinear Point/1

Defines the nonlinear dashpot coefficients on the ∗ DASHPOT option. These are lists of real constants. The two lists must have the same number of values. These properties are required.

Defines the orientation of this property data. This defines the ORIENTATION parameter on the ∗ DASHPOT option. This is a reference to an existing coordinate system.

Input Properties

Non-Linear Damper (Grounded)


OK

Force (Damping)

Velocity (Damping)


Real List

CID

Real List


Defines the degree-of-freedom with which the dashpots are associated at their first nodes. This is an integer value, indicating the degree-of- freedom ID to be used. This property is required.

IRS (Single Node, Planar)

Options above create IRS12 elements with ∗ INTERFACE and ∗ FRICTION properties. This element defines an interface between a node on a planar model and a rigid surface.


Structural 0D IRS (single node)

Planar Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Point/1

Name of the element set containing the rigid surface elements for which properties are being defined. This should be the same for the Rigid Surface and Interface property sets.

Reference common to the IRS elements and the Rigid Surface.

Defines the element cross-sectional area. This value is used only for deriving interface pressure values. The default is 1.0. This is the thickness value on the ∗ INTERFACE option.

Input Properties

IRS Elastic Slip (2_d)


OK

ELSET name (8 chars)

Reference Node

[Friction in Dir_1]

Node id

Real Scalar

X-Sectional area Real Scalar

[Elastic Slip]

[Slip Tolerance]

Real Scalar

Real Scalar

String

1CHAPTER

More data input is available for creating IRS (single node, planar) elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.


Friction in Dir_1 Defines the sliding friction in the element’s 1 direction. This is the friction coefficient on the second card of the *FRICTION option definition.

Elastic Slip Defines the absolute magnitude of the allowable maximum elastic slip to be used in the stiffness method for sticking friction. This is the value of the ELASTIC SLIP parameter on the ∗ FRICTION option.

Slip Tolerance Defines the value of , to redefine the ratio of allowable maximum elastic slip to characteristic element length dimension. The default is .005. This is the value of the SLIP TOLERANCE parameter on the ∗ FRICTION option.

Stiffness in Stick This is currently not used.

Maximum Friction Stress Defines the equivalent shear stress limit of the gap element. This is the value of the TAUMAX parameter on the ∗ FRICTION option.

Clearance Zero-Pressure Defines the clearance at which the contact pressure is 0. This is the c value on the *SURFACE CONTACT, SOFTENED option. This property is only used for the Soft Contact option. This is a real constant.

Pressure Zero Clearance Defines the pressure at zero clearance. This is the value on the *SURFACE CONTACT, SOFTENED option. This property is only used for the Soft Contact option. This is a real constant.

Maximum Overclosure Defines the maximum overclosure allowed in points not considered in contact. This is the c value on the *SURFACE CONTACT option. This property is only used for the Soft Contact option. This is a real constant.

Maximum NegativePressure

Defines the magnitude of the maximum negative pressure allowed to be carried across points in contact. This is the value on the *SURFACE CONTACT option. This property is only used for the Hard Contact option. This is a real constant.

No Sliding Contact Chooses the Lagrange multiplier formulation for sticking friction when completely rough (no slip) friction is desired.

Clearance Zero Damping Clearance at which the damping coefficient is zero.

Damping Zero Clearance Damping coefficient at zero clearance.

Frac Clearance Const Damping Fraction of the clearance interval over which the damping coefficient is constant.

Ff

p0

p0

IRS (Single Node, Spatial)

Options above create IRS13 elements with ∗ INTERFACE and ∗ FRICTION properties. This element defines an interface between a node on a spatial model and a rigid surface.


Structural 0D IRS (single node)

Spatial Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Point/1


Reference node common to the IRS elements and the rigid surface.

Defines the element cross-sectional area. This value is used only for deriving interface pressure values. The default is 1.0. This is the thickness value on the ∗ INTERFACE option.

Input Properties

IRS Soft Contact (3_d)


OK


Reference Node

[Friction in Dir_1]

Node id

Real Scalar


[Friction in Dir_2]

[Elastic Slip]

Vector

Real Scalar

String

1CHAPTER

More data input is available for creating IRS (single node, spatial) elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.


Friction in Dir_1Friction in Dir_2

Defines the sliding friction in the element’s 1- and 2-directions. These are the friction coefficients on the second card of the ∗ FRICTION option. If Friction in Dir_2 is specified, then the ANISOTROPIC parameter is included on the ∗ FRICTION option. These values can be either real constants or references to existing field definitions.




Maximum FrictionStress

Defines the equivalent shear stress limit of the gap element. This is the equivalent shear stress limit value on the second card of the *FRICTION option.

Clearance Zero-Pressure Defines the clearance at which the contact pressure is 0. This is the c value on the *SURFACE CONTACT, SOFTENED option. This property is only used for the Soft Contact option. This is a real constant.




Defines the magnitude of the maximum negative pressure allowed to be carried across points in contact. This is the value on the *SURFACE CONTACT option. This property is only used for the Hard Contact option. This is a real constant.

No Sliding Contact Chooses the Language multiplier formulation for sticking friction when completely rough (no slip) friction is desired.



Frac Clearance Const Damping

Fraction of the clearance interval over which the damping coefficient is constant.

Ff

p0

p0

General Beam in Plane

Options above create B21, B22, B23, B21H, B22H, or B23H elements, depending on the specified options and topology. ∗ BEAM GENERAL SECTION, SECTION=GENERAL properties are also created. This defines a general section beam which is restricted to remain in the XY plane.


Structural 1D Beam in XY Plane

General Section

Standard FormulationHybridCubic InterpolationCubic Hybrid

Bar/2, Bar/3Bar/2, Bar/3Bar/2Bar/2

Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse, or type the name in. This identifies the material where the Young’s modulus, torsional shear modulus and coefficient of thermal expansion data on the *BEAM GENERAL SECTION option are defined. This property is required.

Defines the uniform cross-sectional area of the beam. This value is the A property on the *BEAM GENERAL SECTION option. This value can be either a real constant or a reference to an existing field definition. If a field is referenced, it will be evaluated at the centroid of each element. This property is required.

These define the area moments for the general section beam. These are the I11 and I22 properties on the *BEAM GENERAL SECTION option. These can be either real constants or references to existing field definitions. These properties are required.

Input Properties

General Std in Plane


OK

Material Name

X-Sectional area

Area Moment l22

Real Scalar

Real Scalar

Area Moment l11 Real Scalar

[Poisson Parameter]

[Shear Factor]

Real Scalar

Real Scalar

Mat Prop Name

Material Property Sets

1CHAPTER

More data input is available for creating General Beam in Plane elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.


Poisson Parameter Permits an “overall” change of the cross section dimensions as a function of the axial strains. This is the value of the POISSON parameter on the *BEAM GENERAL SECTION option.

Shear Factor The product of this factor, the beam cross-sectional area, and the shear modulus for the material defines the transverse shear stiffness for the beam.

1

2

1

2

3

2-NODE ELEMENT 3-NODE ELEMENT

Node 1

Node 2

tn1

2nVector in( t n1, ) plane

ShearCenter

Centroid(n1SC, n2SC) (n1C, n2C) N

Q1

Q2

M1

M2 T

Resultant Forcesat Node 2

Box Beam in Plane/Space

Options above create B21, B22, B23, B21H, B22H, or B23H elements in a plane, or B31, B32, B33, B34, B31H, B32H or B33H elements in space, depending on the specified options and topology. ∗ BEAM SECTION, SECTION=BOX properties are also created. The planar box section beam is restricted to remain in the XY-plane. For the spatial beam, ∗ TRANSVERSE SHEAR STIFFNESS is also created, as required.


Structural 1D Beam in XY Plane

Box Section Standard FormulationHybridCubic InterpolationCubic Hybrid

Bar/2, Bar/3Bar/2, Bar/3Bar/2Bar/2

Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse, or type the name in. This identifies the material where the Young’s modulus, torsional shear modulus and coefficient of thermal expansion data on the *BEAM SECTION option are defined. This property is required.

Input Properties

Box Std in Plane


OK

Material Name

Section Width

Thickness _RHS

Real Scalar

Real Scalar

Section Height Real Scalar

Thickness_TOP

Thickness_LHS

Real Scalar

Real Scalar

Mat Prop Name


Defines the section width and height of the element cross section. These are two of the data values on the second card of the ∗ BEAM SECTION option. These are either real constants or references to existing field definitions. These properties are required.

1CHAPTER

More data input is available for creating Box Beam in Plane elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.

Beam Shape Display in Plane/Space

All of the beam shapes can be displayed in their proper orientation on the 3D model. To activate the display, go to Display/Load/BC/Elem. Props... and set the "Beam Display" option. These options are discribed in detail in Display>LBC/Element Property Attributes (p. 315) in the MSC.Patran Reference Manual, Part 1: Basic Functions. The beam display is shown on beam elements only, not geometry.


Thickness_RHSThickness_TOPThickness_LHSThickness_BOT

Defines the wall thickness of the element cross section. These are for the right-hand side, top, left-hand side, and bottom, respectively. These are four of the data values on the second card of the *BEAM SECTION option. These can be either real constants or references to existing field definitions. These properties are required.


Shear Factor The product of this factor, the beam cross-sectional area, and the shear modulus for the material defines the transverse shear stiffness for the beam.

Definition of XY Plane (for beams in space only)

Defines the orientation of the XY-plane of the element coordinate system. The required input is a vector in the beam’s 1-direction. This corresponds to the second line of data under the *BEAM SECTION option. All of the MSC.Patran tools are available via the select menu to define this vector.

5 4 3 2

5

4

3 2 1

1

2

1

9 10 11

12

5

4

3 2 1

1

2

13

6 7 8

14 15 16

t 2

t 4

t 1

t 33b

a

b

a

t 3

t 2

t 4

t 1

Default integration,Beam in a plane.

Default integration, Beam in space.

Additional Beam Shapes in Plane/Space

Additional commonly used beam cross-sectional shapes are defined by forms analogous to that for box beams. The planar option defines a beam which is restricted to remain in the XY plane. For the spatial beam, *ORIENTATION and *TRANSVERSE SHEAR STIFFNESS is also created, as required.

CIRCULAR BEAM (SOLID). This property will have the SECTION=CIRC parameter. All that is required for the definition of the cross section is the radius. The integration schemes for planar analysis (left) and spatial analysis(right) are shown below.

HEXAGONAL BEAM. This property will have the SECTION=HEX parameter. All that is required for the definition of the cross section is the circumscribing radius and the wall thickness. The integration schemes for planar analysis (left) and spatial analysis (right) are shown below.

1

2

1 6

8 9

7

10 11

13

12 14 15

17 16

2

3

5 4

1

2

4

3

2

1

5

3

2

1 3

4

5

4

2

1

2

2

1 7

6

4

2

12

10

8

5

9 11

1

3

t

d

t

d

1CHAPTER

I-SECTION. This property will have the SECTION=I parameter. The height of section, flange widths, and associated thicknesses are required. In addition, the height of the centroid, depicted as “l” is also required. This allows placement of the origin of the local cross-section axis anywhere on the symmetry line. Note also that judicious specification of the flange widths and thicknesses will allow modelling of a T-section. See p. 3.5.2-11 of the ABAQUS User’s Manual for details. The integration schemes for planar analysis (left) and spatial analysis (right) are shown below.

PIPE BEAM. This property will have the SECTION=PIPE parameter. The pipe thickness and outside radius define the cross section. The integration schemes for planar analysis (left) and spatial analysis (right) are shown below.

1

2

1

2

4

5

3

h

b 2

1

9

2

10 11 12 13

8

7

6

1 2 4 5 3

h

b 2

b

t 1

t 2

t 3 l l

b 1

t 1

t 2

t 3

2

1

1 2

3

4 5

4

3

2

2

1

1 2

3

4 5

6

7

8

r

t

r

t

RECTANGULAR BEAM (SOLID). This property will have the SECTION=RECT parameter. The section width and section height define the cross section. The integration schemes for planar analysis (left) and spatial analysis (right) are shown below.

TRAPEZOID BEAM (SOLID). This property will have the SECTION=TRAP parameter. The top and bottom width and section height define the cross section. The integration schemes for planar analysis (left) and spatial analysis (right) are shown below.

2

1

21

16

11 6 1

22

17

12 7 2

23

18

13 8 3

24

19

14 9 4

25

20

15 10

5

b

a

1

5 4

3 2 1

b

a

2

2 5

4

3

2

1

2

1

21 22 23 24 25

16 17 18 19 20

11 12 13 14 15

6 7 8 9 10

1 2 3 4 5

1 d

b

a

d

b

a

c c

1CHAPTER

General Beam in Space

Options above create B31, B32, B33, B34, B31H, B32H, or B33H elements depending on the specified options and topology. *BEAM GENERAL SECTION properties are also created. This property will have the SECTION=GENERAL parameter. *ORIENTATION and *TRANSVERSE SHEAR STIFFNESS options are also created, as required. This defines a general section beam.


Structural 1D Beam in Space

General Section

Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

Bar/2, Bar/3Bar/2, Bar/3Bar/2Bar/2Bar/2

Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material where the Young’s modulus, torsional shear modulus, and coefficient of thermal expansion data on the *BEAM GENERAL SECTION option are defined. This property is required.


These define the area moments for the general section beam. These are the I11, and I22 properties on the *BEAM GENERAL SECTION option. These can be either real constants or references to existing field definitions. These properties are required.

Input Properties

General Std in Plane


OK

Material Name

X-Sectional area

[Area Moment l12]

Real Scalar

Real Scalar


Mat Prop Name


[Torsional Constant] Real Scalar


More data input is available for creating General Beam in Space elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.


Area Moment I12 Defines the area moment of the element cross section. This is the I12 value on the second card of the *BEAM GENERAL SECTION option. This can be either a real constant or a reference to an existing field definition.

Torsional Constant Defines the torsional constant of the element cross section. This is the J value on the second card of the *BEAM GENERAL SECTION option. This can be either a real constant or a reference to an existing field definition.

Definition of XY Plane Defines the orientation of the XY plane of the element coordinate system. The required input is a vector in the beam’s 1-direction. This corresponds to the second line of data under the ∗ BEAM GENERAL SECTION option. All of the MSC.Patran tools are available via the select menu to define this vector.

Centroid Coord 1Centroid Coord 2

Defines the location of the centroid of the cross section with respect to the local cross section coordinate system. These values are either real constants or references to existing field definitions. These are the values on the ∗ CENTROID suboption of the ∗ BEAM GENERAL SECTION option.

Shear Centroid Coord 1Shear Centroid Coord 2

Defines the location of the shear centroid of the cross section with respect to the nodal locations. These values are measured in the local cross section coordinate system. These values are either real constants or references to existing field definitions. These are the values on the *SHEAR CENTER suboption on the *BEAM GENERAL SECTION option.


Shear Factor The product of this factor, the beam cross-sectional area, and the shear modulus for the material defines the transverse shear stiffness for the beam. This value appears on the ∗ TRANSVERSE SHEAR STIFFNESS option.

Section Point Coord 1Section Point Coord 2

Defines the coordinates of points in the beam cross section where output is requested. These are lists of real constants. These values are measured in the beam cross section coordinate system. The lists must have the same number of entries. These are the values on the *SECTION POINTS suboption of the *BEAM GENERAL SECTION option.

1CHAPTER

Arbitrary Beam in Space

Options above create B31, B32, B33, B34, B31H, B32H, or B33H elements depending on the specified options and topology. ∗ BEAM SECTION, SECTION=ARBITRARY properties are also created. ∗ ORIENTATION and ∗ TRANSVERSE SHEAR STIFFNESS options are created, as required. This defines an arbitrary section beam.



Arbitrary Section

Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight


Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material where the Young’s modulus, torsional shear modulus and coefficient of thermal expansion data on the *BEAM SECTION option are defined. This property is required.

Defines the cross-sectional locations of the points defining the element cross section. These define the X and Y coordinate data on the *BEAM SECTION option. These are lists of real constants. Both lists must have the same number of values. These properties are required.

Defines the thickness of each of the legs making up the arbitrary cross section. This is the thickness data on the *BEAM SECTION option. This is a list of real constants. There must be one fewer values in this list than there are in the preceding coordinate lists. This list of values is required.

Input Properties

Arbitrary Std in Space


OK

Material Name

Coordinate_1 (n)

Thickness (n-1)

Real List

Real List

Coordinate_2 (n) Real List

Definition of XY Plane

[Poisson Parameter]

Vector

Real Scalar

Mat Prop Name


More data input is available for creating Arbitrary Beam in Space elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.


Definition of XY Plane Defines the cross section axis N1 of the beam such that the tangent along the beam and the cross section axes N1 and N2 form a right-hand rule. This is the data on the second card of the ∗ BEAM SECTION option. This is a real vector. This property is required.



1

2

t AB

t BC

t CD

A

B

C

D

2

1

3

5

4

6

7

Example of arbitrary section

1CHAPTER

Curved Pipe in Space

Options above create ELBOW31, ELBOW32, ELBOW31B, or C elements depending on the specified options and topology. ∗ BEAM SECTION, SECTION=ELBOW properties are also created. ∗ ORIENTATION and ∗ TRANSVERSE SHEAR STIFFNESS options are created, as required. This defines an elbow element.



Curved w/Pipe Section

Standard FormulationOvalization OnlyOvaliz Only w/ Approx Fourier

Bar/2, Bar/3Bar/2Bar/2

Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material which will referenced on the *BEAM SECTION option are defined. This property is required.

Defines the outside radius of the cross section. This is one of the data values on the second card of the *BEAM SECTION option. This is either a real constant or a reference to an existing field definition. This property is required.

Defines the wall thickness of the cross section. This is one of the data values on the second card of the *BEAM SECTION option. This is either a real constant or a reference to an existing field definition. This property is required.

Input Properties

Beam ELBOW31/ELBOW32


OK

Material Name

Outside Radius

Torus Radius

Real Scalar

Real Scalar

Wall Thickness Real Scalar

Integ Points around Pi

Point Tangents Intense

Integer

Node Id

Mat Prop Name


For curved elements, find the intersection of the two tangents to the axis of the curved element at both ends (typically these are the axes of the adjacent straight pipe runs). You should have a node in that intersection and use its ID in this panel. For straight elements, the node in question is any node off the pipe axis.

More data input is available for creating Curved Pipe in Space elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.


Torus Radius Defines the radius of the elbow bend. This is one of the data values on the second card of the *BEAM SECTION option. This is either a real constant or a reference to an existing field definition. This property is required.

Integ Points around Pi Defines the number of integration points to be used around the pipe cross section. This is the second value on the fourth card of the *BEAM SECTION option. This is an integer value. This property is required.

Point Tangents Inters Defines the orientation of the XY plane of the element coordinate system. This is the data on the second card of the *BEAM SECTION option. This is a Node ID. This property is required.

Integ Points thru Thick Defines the number of integration points to be used through the pipe wall thickness. This is the first value on the fourth card of the *BEAM SECTION option. This is an integer value.

# Ovalization Modes Defines the number of ovalization modes to be included in the shape functions of this element. This is the third value of the fourth card of the *BEAM SECTION option. This is an integer value.

Poisson Parameter Permits an “overall” change of the cross section dimensions as a function of the axial strains. This is the value of the POISSON parameter on the ∗ BEAM SECTION option.


1CHAPTER

L-Section Beam in Space

Options above create B31, B32, B33, B34, B31H, B32H, or B33H elements depending on the specified options and topology. ∗ BEAM SECTION, SECTION=L properties are also created. ∗ ORIENTATION and ∗ TRANSVERSE SHEAR STIFFNESS options are created, as required. This defines an L-section beam.



L-Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight


Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material where the Young’s modulus, torsional shear modulus and coefficient of thermal expansion data on the *BEAM SECTION option are defined. This property is required.

Defines the horizontal and vertical leg lengths of the cross section. These are two of the data values on the second card of the *BEAM SECTION option. These are either real constants or references to existing field definitions. These properties are required. (“Vertical” is in the direction of the XY plane definition. “Horizontal” is normal to this direction.)

Defines the thicknesses of the horizontal and vertical legs of the cross section. These are two of the data values on the second card of the *BEAM SECTION option. These are either real constants or references to existing field definitions. These properties are required.

Input Properties

L-Sec Std in Space


OK

Material Name

Horizontal Width

Horizontal Thickness

Real Scalar

Real Scalar

Vertical Height Real Scalar

Vertical Thickness

Definition of XY Plane

Real Scalar

Vector

Mat Prop Name


More data input is available for creating L-Section Beam in Space elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.


Definition of XY Plane Defines the cross section axis N1 of the beam such that the tangent along the beam and the cross section axes N1 and N2 form a right-hand rule. This is the data on the second card of the *BEAM SECTION option. This is a real vector. This property is required.

Poisson Parameter Permits an “overall” change of the cross section dimensions as a function of the axial strains. This is the value of the POISSON parameter on the ∗ BEAM SECTION option.

Shear Factor The product of this factor, the beam cross sectional area, and the shear modulus for the material defines the transverse shear stiffness for the beam. This value appears on the ∗ TRANSVERSE SHEAR STIFFNESS option.

b

a

d

1

2 5

4

3

2

1

c

b

d

1

2 9

8

7

6

5

4 3 2 1

c

a

1CHAPTER

Open Beam in Space

Options above create B31OS, B32OS, B31OSH, or B32OSH elements depending on the specified options and topology. ∗ BEAM GENERAL SECTION, SECTION=GENERAL properties are also created. ∗ ORIENTATION and ∗ TRANSVERSE SHEAR STIFFNESS options are created, as required. This defines an open section beam.



Open Section

Standard FormulationHybrid

Bar/2, Bar/3Bar/2, Bar/3

Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material where the Young’s modulus, torsional shear modulus and coefficient of thermal expansion data on the *BEAM GENERAL SECTION option are defined. This property is required.


These define the area moments for the general section beam. These are the I11, and I22 properties on the *BEAM GENERAL SECTION option. These can be either real constants or references to existing field definitions. These properties are required.

Input Properties

Open Std in Space


OK

Material Name

X-Sectional area

[Area Moment l12]

Real Scalar

Real Scalar


Area Moment l22

[Torsional Constant]

Real Scalar

Real Scalar

Mat Prop Name


More data input is available for creating Open Beam in Space elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.


Area Moment I12 Defines the area moment of the element cross section. This is the I12 value on the second card of the *BEAM GENERAL SECTION option. This can be either a real constant or a reference to an existing field definition.

Torsional Constant Defines the torsional constant of the element cross section. This is the J value on the second card of the *BEAM GENERAL SECTION option. This can be either a real constant or a reference to an existing field definition.

Definition of XY Plane Defines the cross section axis N1 of the beam such that the tangent along the beam and the cross section axes N1 and N2 form a right-hand rule. This is the data on the second card of the *BEAM GENERAL SECTION option. This is a real vector. This property is required.

1st. Sectorial Moment This can be either a real constant or a reference to an existing field definition. This property is required for open section beams.

Warping Constant This can be either a real constant or a reference to an existing field definition. This property is required for open section beams.

Centroid Coord 1Centroid Coord 2

Defines the location of the centroid of the cross section with respect to the local cross section coordinate system. These values are either real constants or references to existing field definitions. These are the values on the ∗ CENTROID suboption of the ∗ BEAM GENERAL SECTION option.

Shear Center Coord 1Shear Center Coord 2

Defines the location of the shear centroid of the cross section with respect to the local cross section coordinate system. These values are either real constants or references to existing field definitions. These are the values on the ∗ SHEAR CENTER suboption of the ∗ BEAM GENERAL SECTION option.



Section Point Coord 1Section Point Coord 2

Defines the coordinates of points in the beam cross section where output is requested. These are lists of real constants. These values are measured in the beam cross section coordinate system. The lists must have the same number of entries. These are the values on the ∗ SECTION POINTS suboption of the ∗ BEAM GENERAL SECTION option.

1CHAPTER

Truss

Options above create T3D2, T3D2H, T3D3, or T3D3H elements depending on the specified options and topology. *SOLID SECTION properties are also created. The cross sectional area is included on the *SOLID SECTION option.


Structural 1D Truss Standard FormulationHybrid

Bar/2. Bar/3Bar/2. Bar/3

Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material which will be referenced on the *SOLID SECTION option. This property is required.

Defines the area of the cross section. This is the area value on the *SOLID SECTION option. This is either a real constant or a reference to an existing field definition. This property is required.

Input Properties

Truss


OK

Material Name Mat Prop Name



Linear Spring (Axial)

Options above create SPRINGA elements with *SPRING properties. This element defines a linear spring between two nodes whose line of action is the line joining the two nodes.


Structural 1D Spring Linear Standard Formulation Bar/2

Defines the linear spring coefficient on the ∗ SPRING option. This is a real constant. This property is required.

Input Properties

Linear Spring (Axial)


OK

Stiffness Real Scalar

Field Definitions

1CHAPTER

Linear Spring (Fixed Direction)

Options above create SPRING2 elements with *SPRING properties.This element defines a linear spring between specified degrees-of-freedoms at two nodes. An *ORIENTATION option may also be created, as required.


Structural 1D Spring Linear Fixed Direction Bar/2

Defines the linear spring coefficient on the ∗ SPRING option. This is a real constant. This property is required.

Defines the degree-of-freedom this value is to be attached to at each node. The is an integer value, indicating the degree-of-freedom ID to be used. This is the degree-of-freedom reference on the *SPRING option. This property is required.

Defines the orientation of this property data. This defines the ORIENTATION parameter on the *SPRING option. This is a reference to an existing coordinate system.

Input Properties

Linear Spring (Fixed Direction)Property Name Value Value Type

OK

Stiffness Real Scalar



[Orientation System ] CID

Field Definitions

Nonlinear Spring (Axial)

Options above create SPRINGA elements with *SPRING properties.This element defines a nonlinear spring between two nodes whose line of action is the line joining the two nodes.


Structural 1D Spring Nonlinear Standard Formulation

Bar/2

Defines the nonlinear spring coefficients on the *SPRING option. These are lists of real constants. The two lists must have the same number of values. These properties are required.

Input Properties

Non-Linear Spring (Axial)


OK

Force Real List

Displacement Real List

1CHAPTER

Nonlinear Spring (Fixed Direction)

Options above create SPRING2 elements with ∗ SPRING properties. This element type defines a nonlinear spring between two nodes, acting in a fixed direction. An ∗ ORIENTATION option may also be created, as required.


Structural 1D Spring Nonlinear Fixed Direction Bar/2

Defines the nonlinear spring coefficients on the *SPRING option. These are lists of real constants. The two lists must have the same number of values. These properties are required.

Defines the degree-of-freedom this value is to be attached to at each node. This is an integer value, indicating the degree-of-freedom ID to be used. This is the degree-of-freedom reference on the *SPRING option. This property is required.

Defines the orientation of this property data. This defines the ORIENTATION parameter on the *SPRING option. This is a reference to an existing coordinate system.

Input Properties

Non-Linear Spring (Fixed Direction)


OK

Force

Dof at Node 1

Real List

Integer

Displacement Real List


[Orientation System] CID

Linear Damper (Axial)

Options above create DASHPOTA elements with ∗ DASHPOT properties. This element type defines a linear damper between two nodes whose line of action is the line joining the two nodes.


Structural 1D Damper Linear Standard Formulation

Bar/2

Defines the linear dashpot coefficient on the ∗ DASHPOT option. This can be either a real constant or a reference to an existing field definition. If a field definition is referenced, it will be evaluated at the element centroid to derive the linear coefficient for each dashpot element. This property is required.

Input Properties

Linear Damper (Axial)


OK

Damping Coefficient Real Scalar

Field Definitions

1CHAPTER

Linear Damper (Fixed Direction)

Options above create DASHPOT2 elements with ∗ DASHPOT properties. This element type defines a linear damper between two nodes, acting in a fixed direction. An ∗ ORIENTATION option may also be created, as required.


Structural 1D Damper Linear Fixed Direction Bar/2

Defines the linear dashpot coefficient on the *DASHPOT property option. This can be either a real constant or a reference to an existing field definition. If a field definition is referenced, it will be evaluated at the element centroid to derive the linear coefficient for each dashpot element. This property is required.

Defines the degree-of-freedom this value is to be attached to at each node. This is an integer value, indicating the degree-of-freedom ID to be used. This is the degree-of-freedom reference on the *DASHPOT option. This property is required.

Defines the orientation of this property data. This defines the ORIENTATION parameter on the *DASHPOT option. This is a reference to an existing coordinate system.

Input Properties

Linear Damper (Fixed Direction)


OK

Damping Coefficient

Dof at Node 2

Real Scalar

Integer



Field Definitions

Nonlinear Damper (Axial)

Options above create DASHPOTA elements with ∗ DASHPOT properties. This element type defines a nonlinear damper between two nodes whose line of action is the line joining the two nodes.


Structural 1D Damper Nonlinear Standard Formulation

Bar/2

Defines the nonlinear dashpot coefficients on the *DASHPOT option. These are lists of real constants. The two lists must have the same number of values. These properties are required.

Input Properties

Non-Linear Damper (Axial)


OK

Force (Damping) Real List

Velocity (Damping) Real List

1CHAPTER

Nonlinear Damper (Fixed Direction)

Options above create DASHPOT2 elements with ∗ DASHPOT properties. This element type defines a nonlinear damper between two specified nodes, acting in a fixed direction. An ∗ ORIENTATION option may also be created, as required.


Structural 1D Damper Nonlinear Fixed Direction Bar/2

Defines the nonlinear dashpot coefficients on the *DASHPOT option. These are lists of real constants. The two lists must have the same number of values. These properties are required.

Defines the degree-of-freedom this value is to be attached to at each node. This is an integer value, indicating the degree-of-freedom ID to be used. This is the degree-of-freedom reference on the *DASHPOT option. This property is required.

Defines the orientation of this property data. This defines the ORIENTATION parameter on the *DASHPOT option. This is a reference to an existing coordinate system.

Input Properties

Non-Linear Damper (Fixed Direction)Property Name Value Value Type

OK

Force (Damping)

Dof at Node 1

Real List

Integer

Velocity (Damping) Real List



Gap (Uniaxial), Gap (Cylindrical)

Options above create GAPUNI or GAPCYL elements with *GAP properties. The ∗ FRICTION option is created, as required.


Structural 1D Gap CylindricalUniaxial

True DistanceElastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Bar/2

This button is currently not used.

Defines the closure direction (GAPUNI elements) or cylinder axis (GAPCYL elements). This value is a global vector. This property is required for GAPCYL elements.

Defines the equivalent shear stress limit of the gap element. This is the equivalent shear stress limit value on the second card of the ∗ FRICTION option. This can be either a real constant or a reference to an existing field definition. This property is required.

Input Properties

Gap (Cylindrical)Property Name Value Value Type

OK

[ Initial Clearance ]

[ Friction in Dir_1 ]

Real Scalar

Real Scalar

Vector Vector

[ Friction in Dir_2 ] Real Scalar

[ Stiffness in Stick ] Real Scalar

[ Max Friction Stress ] Real Scalar

Defines the initial opening of the gap. This is the d value on the second card of the ∗ GAP option. This can be either a real constant or a reference to an existing field definition. The default is 0.

Field Definitions

Defines the sliding friction in the element’s 1 and 2 directions. These are the friction coefficients on the second card of the ∗ FRICTION option. If Friction in Dir_2 is specified, then the ANISOTROPIC parameter is included on the ∗ FRICTION option.

1CHAPTER

Gap (Spherical)

Options above create GAPSPHER elements with *GAP properties. The *FRICTION option is created, as required.


Structural 1D Gap Spherical True DistanceElastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Bar/2

Defines the initial opening of the gap. This is the d value on the second card of the ∗ GAP option. This can be either a real constant or a reference to an existing field definition. The default is 0.

This button is currently not used.

Defines the equivalent shear stress limit of the gap element. This is the value of the TAUMAX parameter on the ∗ FRICTION option. This can be either a real constant or a reference to an existing field definition. This property is required.

Input Properties

Gap (Spherical)


OK

[ Initial Clearance ]

[ Fiction in Dir_1 ]

Real Scalar

Real Scalar




Defines the sliding friction in the element’s 1 and 2 directions. These are the friction coefficients on the second card of the *FRICTION option. If Friction in Dir_2 is specified, then the ANISOTROPIC parameter is included on the *FRICTION option.

Field Definitions

Axisymmetric Shell

Options above create SAX1 or SAX2 elements, depending on the specified topology, with *SHELL SECTION properties.


Structural 1D Axisymmetric Shell

Homogeneous Bar/2 Bar/3

Defines the uniform shell thickness for these elements. This can be either a real constant or a reference to an existing field definition. This property is required.

Defines the number of integration points through the shell section. This is an integer value and must be an odd number. The default is 5.

Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material which will be referenced on the ∗ SHELL SECTION option. This property is required.

Input Properties

Axisymmetric ShellProperty Name Value Value Type

OK

Material Name

Shell Thickness

Mat Prop Name

Real Scalar

[ # Integration Points ] Integer


1CHAPTER

Axisymmetric Shell (Laminate)

Options above create SAX1 or SAX2 elements, depending on the specified topology, with ∗ SHELL SECTION, COMPOSITE properties.


Structural 1D Axisymmetric Shell Laminate Bar/2

Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material which will be referenced on the ∗ SHELL SECTION option. This property is required. This must be a laminate composite material within MSC.Patran.

Input Properties

Axisymmetric Shell (Laminated)


OK



1D Interface

Options above create INTER1 elements with *INTERFACE, *FRICTION, and *SURFACE CONTACT properties. The SOFTENED parameter on the *SURFACE CONTACT option may be included, depending on the selected option. This element defines an interface region between two portions of an axisymmetric model. These elements must be created from one contact surface to the other.


Structural 1D 1D Interface

Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Bar/2

Defines the cross-sectional area of the interface. This value is used only for deriving interface pressure values. The default is 1.0. This is the thickness value on the *INTERFACE option.

Defines the sliding friction in the element’s 1 and 2 directions. These are the friction coefficients on the second card of the *FRICTION option. If Friction in Dir_2 is specified, then the ANISOTROPIC parameter is included on the *FRICTION option. These values can be either real constants or references to existing field definitions.

Defines the closure direction of the gap. This is the second card of the *INTERFACE option. This value is a global vector. This property is required.

Input Properties

Interface Elastic Slip (General)


OK

X-Sectional area


Real Scalar

Real Scalar


Vector Vector

[ Elastic Slip ] Real Scalar

[ Slip Tolerance ] Real Scalar

Field Definitions

1CHAPTER

More data input is available for creating 1D Interface elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.



Slip tolerance Defines the value of , to redefine the ratio of allowable maximum elastic slip to characteristic element length dimension. The default is .005. This is the value of the SLIP TOLERANCE parameter on the ∗ FRICTION option.



Clearance Zero-Pressure Defines the clearance at which the contact pressure is 0. This is the c value on the ∗ SURFACE CONTACT, SOFTENED option. This property is only used for the Soft Contact option. This is a real constant.


Maximum Overclosure Defines the maximum overclosure allowed in points not considered in contact. This is the c value on the ∗ SURFACE CONTACT option. This property is only used for the Soft Contact option. This is a real constant.

Maximum Negative Pressure Defines the magnitude of the maximum negative pressure allowed to be carried across points in contact. This is the value on the ∗ SURFACE CONTACT option. This property is only used for the Hard Contact option. This is a real constant.






Ff

p0

p0

Planar ISL (In Plane)

Options above create ISL21 or ISL22 elements (depending on the selected topology) with *INTERFACE and *FRICTION properties. This element defines an interface between the edge of an element on a planar model and another part of the model.


Structural 1D ISL (in plane)


Bar/2, Bar/3

Name of the element set containing the ISL elements. This should be the same for the Slide Line and the Interface property sets.

Defines the thickness of the interface. This value is used only for deriving interface pressure values. This is the thickness value on the *INTERFACE option.

Input Properties

ISL Elastic Slip (planar)Property Name Value Value Type

OK


Width

[ Elastic Slip ]

Real Scalar

Real Scalar


String



1CHAPTER

More data input is available for creating Planar ISL (in plane) elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.


Friction in Dir_1 Defines the sliding friction in the element’s 1 direction. This is the friction coefficient on the second card of the *FRICTION option.





Clearance Zero Pressure Defines the clearance at which the contact pressure is 0. This is the c value on the ∗ SURFACE CONTACT, SOFTENED option. This property is only used for the Soft Contact option. This is a real constant.

Press Zero Clearance Defines the pressure at zero clearance. This is the value on the ∗ SURFACE CONTACT, SOFTENED option. This property is only used for the Soft Contact option. This is a real constant.



Defines the magnitude of the maximum negative pressure allowed to be carried across points in contact. This is the value on the ∗ SURFACE CONTACT option. This property is only used for the Hard Contact option. This is a real constant.






Ff

p0

p0

Axisymmetric ISL (In Plane)

Options above create ISL21A or ISL22A elements (depending on the selected topology) with *INTERFACE and *FRICTION properties. This element defines an interface between the edge of an element on an axisymmetric model and another part of the model.


Structural 1D ISL (in plane)

Axisymmetric Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Bar/2, Bar/3

Name of the element set containing the ISL elements. This should be the same for the Slide Line and Interface property sets.

Input Properties

ISL Elastic Slip (axisymm)


OK



[ Slip Tolerance ]

Real Scalar

Real Scalar


String



1CHAPTER

More data input is available for creating Axisymmetric ISL (in plane) elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.







Clearance Zero Pressure Defines the clearance at which the contact pressure is 0. This is the c value on the *SURFACE CONTACT, SOFTENED option. This property is only used for the Soft Contact option. This is a real constant.



Maximum Negative Pressure Defines the magnitude of the maximum negative pressure allowed to be carried across points in contact. This is the value on the *SURFACE CONTACT option. This property is only used for the Hard Contact option. This is a real constant.





Ff

p0

p0

Parallel ISL (In Space)

Options above create ISL31 or ISL32 elements (depending on the selected topology) with *INTERFACE and *FRICTION properties. This element type defines an interface between the edge of an element and another part of the model.


Structural 1D ISL (in space)

Parallel Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Bar/2, Bar/3

Name of the element set containing the ISL elements. This should be the same for the Slide Line and Interface property sets.

Defines the thickness of the interface. This value is used only for deriving interface pressure values. The default is 1.0. This is the thickness value on the *INTERFACE option.

Input Properties

ISL Elastic Slip (parallel planProperty Name Value Value Type

OK


Width


Real Scalar

Real Scalar


String

Vector Vector


1CHAPTER

More data input is available for creating Parallel ISL (in space) elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.




Vector Defines the normal to the plane in which sliding contact occurs. This is the second card of the *INTERFACE option. This value is a global vector. This property is required.

Elastic Slip Defines the absolute magnitude of the allowable maximum elastic slip to be used in the stiffness method for sticking friction. This is the value of the ELASTIC SLIP parameter on the *FRICTION option.

Slip Tolerance Defines the value of , to redefine the ratio of allowable maximum elastic slip to characteristic element length dimension. The default is .005. This is the value of the SLIP TOLERANCE parameter on the *FRICTION option.


Maximum Friction Stress Defines the equivalent shear stress limit of the gap element. This is the value of the TAUMAX parameter on the *FRICTION option.




Maximum Negative Pressure Defines the magnitude of the maximum negative pressure allowed to be carried across points in contact. This is the p0 value on the *SURFACE CONTACT option. This property is only used for the Hard Contact option. This is a real constant.



Ff

p0





1CHAPTER

Radial ISL (In Space)

Options above create ISL31 or ISL32 elements (depending on the selected topology) with *INTERFACE and *FRICTION properties. This element defines an interface between the edge of an element and another part of the model.


Structural 1D ISL (in space)

Radial Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Bar/2, Bar/3

Name of the element set containing the ISL elements. This should be same for the Slide Line and Interface property sets.

This value is used only for deriving interface pressure values. This is the value on the ∗ INTERFACE option.

Input Properties

ISL Elastic Slip (radial planProperty Name Value Value Type

OK


Wedge Angle in degrees

Symmetry Axis (Pt. b)

Real Scalar

Node ID

Symmetry Axis (Pt. a) Node ID

String

[ Friction in Dir_1] Vector

[ Friction in Dir_2 ] Real ScalarTwo node IDs which define the symmetry axis for the radial plane in which sliding contact occurs.

More data input is available for creating Radial ISL (in space) elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.




Vector Defines the normal to the plane in which sliding contact occurs. This is the second card of the ∗ INTERFACE option. This value is a global vector. This property is required.






Pressure Zero Clearance Defines the pressure at zero clearance. This is the value on the ∗ SURFACE CONTACT, SOFTENED option. This property is only used for the Soft Contact option. This is a real constant.


Maximum Negative Pressure

Defines the magnitude of the maximum negative pressure allowed to be carried across points in contact. This is the value on the ∗ SURFACE CONTACT option. This property is only used for the Hard Contact option. This is a real constant.

Ff

p0

p0

1CHAPTER

Slide Line

Options above create Slide Lines for the ISL elements. These elements must be equivalenced and continuous.







Structural 1D Slide Line Bar/2, Bar/3


Name of the element set containing the ISL elements which interact with the slide line being defined. This name should be the same as the ISL element group name.

Defines a radius of curvature to smooth discontinuities between adjoining segments. This is the value of the SMOOTH parameter.

Input Properties

Slide LineProperty Name Value Value Type

OK


[ Smooth Param Value ] Real Scalar

String

Start Point (Node id) Node ID

Node ID to define the positive progression direction of the slide line.

IRS (Planar)

Options above create IRS21 or IRS22 elements (depending on the selected topology) with *INTERFACE and *FRICTION properties. This element type defines an interface between the edge of a linear element on a planar model and a rigid surface.


Structural 1D IRS (plane/axisym)


Bar/2, Bar/3

Name of the element set containing the IRS elements. This should be the same for the Rigid Surface and Interface property sets.

Reference node common to the IRS elements and the Rigid Surface.

Defines the thickness of the interface. This value is used only for deriving interface pressure values. The default is 1.0. This is the thickness value on the ∗ INTERFACE option.

Input Properties

IRS Elastic Slip ( planar)


OK


Reference Node


Node ID

Real Scalar

Width Real Scalar

String



1CHAPTER

More data input is available for creating IRS (planar) elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.









Maximum Overclosure Defines the maximum overclosure allowed in points considered not in contact. This is the c value on the *SURFACE CONTACT option. This property is only used for the Hard Contact option. This is a real constant.






Ff

p0

p0

IRS (Axisymmetric)

Options above create IRS21A or IRS22A elements (depending on the selected topology) with *INTERFACE and *FRICTION properties. This element type defines an interface between the edge of a linear element on an axisymmetric model and a rigid surface.


Structural 1D IRS (plane/axisym)

Axisymmetric Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Bar/2, Bar/3



Input Properties

IRS Elastic Slip (axisymm)


OK


Reference Node

[ Elastic Slip ]

Node ID

Real Scalar


String


[ Stiffness in Stick ]] Real Scalar

1CHAPTER

More data input is available for creating IRS (axisymmetric) elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.









Maximum Overclosure Defines the maximum overclosure allowed in points considered not in contact. This is the c value on the ∗ SURFACE CONTACT option. This property is only used for the Hard Contact option. This is a real constant.







Ff

p0

p0

IRS (Beam/Pipe)

Options above create IRS31 or IRS32 elements (depending on the selected topology) with *INTERFACE and *FRICTION properties. This element type defines an interface between a beam or pipe element on a spatial model and a rigid surface.


Structural 1D IRS (beam/pipe) Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Bar/2, Bar/3

Input Properties

IRS Elastic Slip (beam)Property Name Value Value Type

OK


Reference Node


Node ID

Real Scalar


String





1CHAPTER

More data input is available for creating IRS (beam/pipe) elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.












No Sliding Contact Defines the ROUGH parameter on the *FRICTION option. This property is only used for the Lagrange option.





Ff

p0

p0

Rigid Surface (Segments)

Options above create a ∗ RIGID SURFACE, TYPE=SEGMENTS option (see Section 7.4.7 of the ABAQUS/Standard User’s Manual).

The rigid surface is defined by creating Bar/2 elements. All the elements must be connected and should not have duplicate nodes. The start Point (Node ID) defines the positive progression direction along the surface. The right-handed rotation from this direction defines the outward normal.


Structural 1D Rigid Surf (Seg) Bar/2

Name of the element set containing the IRS elements that will be used in conjunction with the rigid surface being defined. This must be same as the IRS element group name.

Input PropertiesRigid Surface (Segments)


OK


Start Point (Node_ID) Node ID

String

[ Smooth Param Value ] Real Scalar Node ID to define the positive progression direction of the rigid surface.


1CHAPTER

Rigid Surface (Cylindrical)

Options above create a ∗ RIGID SURFACE, TYPE = CYLINDRICAL option (see Section 7.4.7 of the ABAQUS/Standard User’s Manual).

The rigid surface is first defined by creating Bar/2 elements. All the elements must be connected and should not have duplicate nodes.

The rigid surface’s +x direction is defined from the start point (node ID) along the line of the rigid surface. The +y direction is away from the object the rigid surface will be in contact with. The +z direction (the surface generation vector) is defined by using right-hand rule, crossing the rigid surface’s +x axis with the +y axis.


Structural 1D Rigid Surf (Cyl) Bar/2


Input Properties

Rigid Surface (Cylindrical)Property Name Value Value Type

OK


Surface Gen. Direction Vector

String

Start Point (Node_ID) Node ID



Node ID used to define the positive progression direction of the rigid surface.

Cylinder generator direction.

Start

-y+z

+x

n

n

Surface Gen.Vector

Positive normal of rigid surface

+y

Rigid Surface (Axisymmetric)

Options above create a ∗ RIGID SURFACE, TYPE=AXISYMMETRIC option (see Section 7.4.7 of the ABAQUS/Standard User’s Manual).

The rigid surface is defined by creating Bar/2 elements. All the elements must be connected and should not have duplicate nodes. The Start Point defines the positive progression direction along the surface. The right-handed rotation from this direction defines the outward normal.


Structural 1D Rigid Surf (Axi) Bar/2


Input Properties

Rigid Surface (Axisymmetric)


OK


[ Orientation System ] CID

String

Start Point (Node_id) Real Scalar

z (local y)

Start

nb

a

n r (local x)

Local y-axis

Local x-axisz

MSC.PatranCoordinate

Frame



Defines the orientation of the material within the element. This is a reference to an existing coordinate system. The referenced coordinate system defines the data used to Create the ∗ ORIENTATION option.


1CHAPTER

Rigid Surface (Bezier 2D)

Options above create a ∗ RIGID SURFACE, TYPE=BEZIER option for use in two-dimensional analysis (see Section 7.4.7 of the ABAQUS/Standard User’s Manual).

The rigid surface is defined by creating Bar/2 elements. All the elements must be connected and should not have duplicate nodes. The Start Point defines the positive progression direction along the surface. The right-handed rotation from this direction defines the outward normal.


Structural 1D Rigid Surf (Bz2D) Bar/2

Name of the element set containing the IRS elements that will be used in conjunction with the rigid surface being defined. This must be the same as the IRS element group name.

Input Properties

Rigid Surface (Bezier 2D)Property Name Value Value Type

OK


Start Point (Node_id) Node ID

String

[ Critical Distance ] Real Scalar


Vertices

Rigid surface patch

Smooth Bezier curve

n

V1 V2

y

x

Critical penetration distance which will cause ABAQUS to restart an increment. This is the value of the HCRIT parameter on the ∗ RIGID SURFACE option. The default value is the radius of a sphere that circumscribes a characteristic patch in the surface. It is rarely necessary to change this default.

Rigid Line (LBC)

This property set is created when the Rigid-Deform contact LBC is created in the Loads/BCs menu. The creation or deletion of this property set is not required by the user. The elements associated with this property set are translated as R2D2 and RAX2 elements.


Structural 1D Rigid Line(LBC) Bar/2

Name of the Rigid-Deform contact LBC for which this element property set was created.

Input Properties

Rigid Line (Lbc)Property Name Value Value Type

OK

Contact Lbc Name String

1CHAPTER

Rebar

The options above create SFMAX1, SFMAX2, SFMGAX1 and SFMGAX2 elements (depending on the selected options and topologies) with *SURFACE SECTION properties. The *EMBEDDED ELEMENT and *REBAR LAYER options are also created..


Structural 1D Rebar AxisymmetricGeneral Axisymmetric

Bar/2, Bar/3

Material Name Defines the material to be used. When entering data here, a list of all isotropic materials in the database is displayed. You can either pick one from the list with the mouse or type in the name. This identifies the material that will be referenced on the *REBAR LAYER option. This property is required.

X-Sectional Area Defines the area of the rebar cross-section. This is the cross-sectional area value on the *REBAR LAYER option. A real constant, a reference to an existing field definition, or a real list may be entered. A real list is used to specify the cross-sectional area for more than one rebar layer. This property is required.

Spacing Defines the spacing of the rebars within a layer. This is the spacing value on the *REBAR LAYER option. A real constant, a reference to an existing field definition, or a real list may be entered. A real list is used to specify the spacing for more than one rebar layer. This property is required.

Spacing Unit Type Defines the unit type for the spacing values. When “Angle” is specified, the ANGULAR SPACING parameter is used for the *REBAR LAYER option. “Distance” is the default value. This property is not required.

Rebar Orient. Angle Defines the angular orientation of the rebar from the meridional plane in degrees. This is the angular orientation value on the *REBAR LAYER option. A real constant, a reference to an existing field definition, or a real list may be entered. A real list is used to specify the angular orientation for more than one rebar layer. This property is required.

Host Property Set Defines the element property set of the elements that host the rebar elements. This is the “HOST ELSET” parameter on the *EMBEDDED ELEMENT option. A reference to an existing element property set may be specified. By default, the solver determines the host elements based on the position of the embedded elements within the model. This property is not required.

Roundoff Tolerance Defines the value below which the weigh factors of the host element’s nodes will be zeroed out. This is the ROUNDOFF TOLERANCE parameter on the *EMBEDDED ELEMENT option. A real scalar may be specified. The default value is 1E+6. This property is not required.

1CHAPTER

Mech Joint (2D Model) - ALIGN

This option creates CONN2D2 elements. The connection type is set to ALIGN on the *CONNECTOR SECTION option.


Structural 1D Mech Joint (2D Model)

ALIGN Bar/2

Node A Analysis CID This property defines the directions for the degrees of freedom at the first node of the connector element. It is translated to the ABAQUS input file with an *ORIENTATION option and is referenced from the *CONNECTOR SECTION option. Use an existing coordinate system to specify this property.

Node B Analysis CID This property defines the directions for the degrees of freedom at the second node of the connector element. It is translated to the ABAQUS input file with an *ORIENTATION option and is referenced from the *CONNECTOR SECTION option. Use an existing coordinate system to specify this property.

Mech Joint (2D Model) - AXIAL

This option creates CONN2D2 elements. The connection type is set to AXIAL on the *CONNECTOR SECTION option.



AXIAL Bar/2

Force/Disp, X Axis This stiffness property value defines the relationship between force and relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR ELASTICITY option. Use a real constant or a non-spatial field to specify this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is force, and displacement is a required independent variable.

Zero Force Ref Len This property value defines the reference length of the unloaded connector element. This value is translated to the ABAQUS input file with the *CONNECTOR CONSTITUTIVE REFERENCE option. Use a real constant to specify this property.

1CHAPTER

Damping, X Axis This damping property value defines the relationship between force and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR DAMPING option. A real constant or a non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is force, and velocity is a required independent variable.

Connector Min Stop This property value defines a lower limit for the connector's relative position. This value is translated to the ABAQUS input file with the *CONNECTOR STOP option. Use a real constant to specify this property.

Connector Max Stop This property value defines an upper limit for the connector's relative position. This value is translated to the ABAQUS input file with the *CONNECTOR STOP option. Use a real constant to specify this property.

Friction Lim, X Axis This property value defines the force limit associated with the friction portion of the connector element. This value is translated to the ABAQUS input file with the *CONNECTOR FRICTION option. A real constant or a non-spatial field may be used to specify this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define a limit that varies with temperature and/or displacement. The dependent variable for these fields is force.

Friction Stick Stiff This property value defines the stiffness associated with the friction portion of the connector element. This value appears as the STICK STIFFNESS parameter in the *CONNECTOR FRICTION option. Use a real constant to specify this property.

Lock, Min Disp This property value defines the lower bound on the relative position that triggers a locked condition in the connector element. This value is translated to the ABAQUS input file with the *CONNECTOR LOCK option. Use a real constant to specify this property.

Mech Joint (2D Model) - BEAM

This option creates CONN2D2 elements. The connection type is set to BEAM on the *CONNECTOR SECTION option.



BEAM Bar/2



1CHAPTER

Mech Joint (2D Model) - CARTESIAN

This option creates CONN2D2 elements. The connection type is set to CARTESIAN on the *CONNECTOR SECTION option.



CARTESIAN Bar/2


Force/Disp, X Axis

Force/Disp, Y Axis

This stiffness property value defines the relationship between force and relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR ELASTICITY option. Use a real constant or a non-spatial field to specify this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is force, and displacement is a required independent variable.

Zero Force Ref Len These property values define the reference lengths for the components of the unloaded connector element. These values are translated to the ABAQUS input file with the *CONNECTOR CONSTITUTIVE REFERENCE option. Use a real vector to specify this property.

Damping, X Axis

Damping, Y Axis

This damping property value defines the relationship between force and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR DAMPING option. A real constant or a non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is force, and velocity is a required independent variable.

Connector Min Stop These property values define the lower limits for the components of the connector's relative position. These values are translated to the ABAQUS input file with the *CONNECTOR STOP option. Use a real vector to specify this property.

Connector Max Stop These property values define the upper limits for the components of the connector's relative position. These values are translated to the ABAQUS input file with the *CONNECTOR STOP option. Use a real vector to specify this property.

1CHAPTER

Mech Joint (2D Model) - JOIN

This option creates CONN2D2 elements. The connection type is set to JOIN on the *CONNECTOR SECTION option.



JOIN Bar/2


Mech Joint (2D Model) - JOINTC

This option creates JOINTC elements. The *JOINT, *SPRING and *DASHPOT options are used to define the properties.



JOINTC Bar/2

Node A Analysis CID This property defines the directions for the degrees of freedom at the first node of the connector element. It is translated to the ABAQUS input file with an *ORIENTATION option and is referenced from the *JOINT option. Use an existing coordinate system to specify this property.

Units for Angles This property determines the units for the angle values. It may be set to either "Degrees" or "Radians". The default value is "Radians".

1CHAPTER

Force/Disp, X Axis

Force/Disp, Y Axis

This stiffness property value defines the relationship between force and relative displacement in the connector element. It is translated to the ABAQUS input file with the *SPRING option. A real constant or a non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is force, and displacement is a required independent variable.

Mom/Rot about Z AxisThis stiffness property value defines the relationship between moment and relative displacement in the connector element. It is translated to the ABAQUS input file with the *SPRING option. A real constant or a non-spatial field may be used for this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is moment, and displacement is a required independent variable.

Damping, X Axis

Damping, Y Axis

This damping property value defines the relationship between force and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *DASHPOT option. A real constant or non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is force, and velocity is a required independent variable.

Rot Damping, Z Axis This damping property value defines the relationship between moment and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *DASHPOT option. A real constant or a non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is moment, and velocity is a required independent variable.

Mech Joint (2D Model) - LINK

This option creates CONN2D2 elements. The connection type is set to LINK on the *CONNECTOR SECTION option.



LINK Bar/2



1CHAPTER

Mech Joint (2D Model) - ROTATION

This option creates CONN2D2 elements. The connection type is set to ROTATION on the *CONNECTOR SECTION option.



ROTATION Bar/2




Mom/Rot about Z AxisThis stiffness property value defines the relationship between moment and relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR ELASTICITY option. A real constant or a non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is moment, and displacement is a required independent variable.

Zero Moment Ref AngThis property value defines the reference angle of the unloaded connector element. This value is translated to the ABAQUS input file with the *CONNECTOR CONSTITUTIVE REFERENCE option. Use a real constant to specify this property.

Rot Damping, Z Axis This damping property value defines the relationship between moment and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR DAMPING option. A real constant or non-spatial field may be used for this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is moment, and velocity is a required independent variable.



1CHAPTER

Mech Joint (2D Model) - SLOT

This option creates CONN2D2 elements. The connection type is set to SLOT on the *CONNECTOR SECTION option.



SLOT Bar/2




Damping, X Axis This damping property value defines the relationship between moment and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR DAMPING option. A real constant or non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is moment, and velocity is a required independent variable.





1CHAPTER

Mech Joint (2D Model) - TRANSLATOR

This option creates CONN2D2 elements. The connection type is set to TRANSLATOR on the *CONNECTOR SECTION option.



TRANSLATOR Bar/2



Mech Joint (2D Model) - WELD

This option creates CONN2D2 elements. The connection type is set to WELD on the *CONNECTOR SECTION option.



WELD Bar/2



1CHAPTER

Mech Joint (3D Model) - ALIGN

This option creates CONN3D2 elements. The connection type is set to ALIGN on the *CONNECTOR SECTION option.



ALIGN Bar/2



Mech Joint (3D Model) - AXIAL

This option creates CONN3D2 elements. The connection type is set to AXIAL on the *CONNECTOR SECTION option.



AXIAL Bar/2



1CHAPTER




Friction Lim, X Axis This property value defines the force limit associated with the friction portion of the connector element. This value is translated to the ABAQUS input file with the *CONNECTOR FRICTION option. A real constant or a non-spatial field may be used to specify this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define a limit that varies with temperature and/or displacement. The dependent variable for these fields is force.


Lock Min Disp This property value defines the upper bound on the relative position that triggers a locked condition in the connector element. This value is translated to the ABAQUS input file with the *CONNECTOR LOCK option. Use a real constant to specify this property.

Mech Joint (3D Model) - BEAM

This option creates CONN3D2 elements. The connection type is set to BEAM on the *CONNECTOR SECTION option.



BEAM Bar/2



1CHAPTER

Mech Joint (3D Model) - CARDAN

This option creates CONN3D2 elements. The connection type is set to CARDAN on the *CONNECTOR SECTION option.



CARDAN Bar/2




Mom/Rot about X Axis

Mom/Rot about Y Axis

Mom/Rot about Z Axis

This stiffness property value defines the relationship between moment and relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR ELASTICITY option. A real constant or a non-spatial field may be used for this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is moment, and displacement is a required independent variable.

Zero Moment Ref Ang These property values define the reference angles for the components of the unloaded connector element. These values are translated to the ABAQUS input file with the *CONNECTOR CONSTITUTIVE REFERENCE option. Use a real vector to specify this property.

Rot Damping, X Axis This damping property value defines the relationship between moment and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR DAMPING option. A real constant or non-spatial field may be used for this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is moment, and velocity is a required independent variable.

1CHAPTER

Mech Joint (3D Model) - CARTESIAN

This option creates CONN3D2 elements. The connection type is set to CARTESIAN on the *CONNECTOR SECTION option.



CARTESIAN Bar/2


Force/Disp, X Axis

Force/Disp, YAxis

Force/Disp, Z Axis


Zero Force Ref Len These property values define the reference angles for the components of the unloaded connector element. These values are translated to the ABAQUS input file with the *CONNECTOR CONSTITUTIVE REFERENCE option. Use a real vector to specify this property.

Damping, X Axis

Damping, Y Axis

Damping, Z Axis

This damping property value defines the relationship between force and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR DAMPING option. A real constant or a non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is force, and velocity is a required independent variable.

1CHAPTER

Mech Joint (3D Model) - CONSTANT VELOCITY

This option creates CONN3D2 elements. The connection type is set to CONSTANT VELOCITY on the *CONNECTOR SECTION option.



CONSTANT VELOCITY

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Mech Joint (3D Model) - CVJOINT

This option creates CONN3D2 elements. The connection type is set to CVJOINT on the *CONNECTOR SECTION option.



CVJOINT Bar/2



1CHAPTER

Mech Joint (3D Model) - CYLINDRICAL

This option creates CONN3D2 elements. The connection type is set to CYLINDRICAL on the *CONNECTOR SECTION option.



CYLINDRICAL Bar/2



Mech Joint (3D Model) - EULER

This option creates CONN3D2 elements. The connection type is set to EULER on the *CONNECTOR SECTION option.



EULER Bar/2



1CHAPTER





This stiffness property value defines the relationship between moment and relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR ELASTICITY option. A real constant or a non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is moment, and displacement is a required independent variable.



Mech Joint (3D Model) - FLEXION-TORSION

This option creates CONN3D2 elements. The connection type is set to FLEXION-TORSION on the *CONNECTOR SECTION option.



FLEXION-TORSION

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1CHAPTER








Mech Joint (3D Model) - HINGE

This option creates CONN3D2 elements. The connection type is set to HINGE on the *CONNECTOR SECTION option.



HINGE Bar/2



1CHAPTER

Mech Joint (3D Model) - JOIN

This option creates CONN3D2 elements. The connection type is set to JOIN on the *CONNECTOR SECTION option.



JOIN Bar/2


Mech Joint (3D Model) - JOINTC

This option creates JOINTC elements. The *JOINT, *SPRING and *DASHPOT options are used to define the properties.



JOINTC Bar/2

Node A Analysis CID This property defines the directions for the degrees of freedom at the first node of the connector element. It is translated to the ABAQUS input file with an *ORIENTATION option and is referenced from the *JOINT option. Use an existing coordinate system to specify this property.


1CHAPTER

Force/Disp, X Axis

Force/Disp, Y Axis

Force/Disp, Z Axis

This stiffness property value defines the relationship between force and relative displacement in the connector element. It is translated to the ABAQUS input file with the *SPRING option. A real constant or a non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is force, and displacement is a required independent variable.




This stiffness property value defines the relationship between moment and relative displacement in the connector element. It is translated to the ABAQUS input file with the *SPRING option. A real constant or a non-spatial field may be used for this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is moment, and displacement is a required independent variable.

Mech Joint (3D Model) - LINK

This option creates CONN3D2 elements. The connection type is set to LINK on the *CONNECTOR SECTION option.



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1CHAPTER

Mech Joint (3D Model) - PLANAR

This option creates CONN3D2 elements. The connection type is set to PLANAR on the *CONNECTOR SECTION option.



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Mech Joint (3D Model) - RADIAL-THRUST

This option creates CONN3D2 elements. The connection type is set to RADIAL-THRUST on the *CONNECTOR SECTION option.



RADIAL-THRUST

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Force/Disp, X Axis

Force/Disp, ZAxis

This stiffness property value defines the relationship between force and relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR ELASTICITY option. Use a real constant or a non-spatial field to specify this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is force, and displacement is a required independent variable.

1CHAPTER


Damping, X Axis

Damping, Z Axis

This damping property value defines the relationship between force and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR DAMPING option. A real constant or a non-spatial field may be used for this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is force, and velocity is a required independent variable.



Mech Joint (3D Model) - REVOLUTE

This option creates CONN3D2 elements. The connection type is set to REVOLUTE on the *CONNECTOR SECTION option.



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2CHAPTER


Mom/Rot about X Axis This stiffness property value defines the relationship between moment and relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR ELASTICITY option. A real constant or a non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is moment, and displacement is a required independent variable.

Zero Moment Ref Ang This property value defines the reference angle of the unloaded connector element. This value is translated to the ABAQUS input file with the *CONNECTOR CONSTITUTIVE REFERENCE option. Use a real constant to specify this property.




Mech Joint (3D Model) - ROTATION

This option creates CONN3D2 elements. The connection type is set to ROTATION on the *CONNECTOR SECTION option.



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2CHAPTER








Mech Joint (3D Model) - SLIDE-PLANE

This option creates CONN3D2 elements. The connection type is set to SLIDE-PLANE on the *CONNECTOR SECTION option.



SLIDE-PLANE Bar/2


Force/Disp, Y Axis

Force/Disp, Z Axis


2CHAPTER


Damping, Y Axis

Damping, Z Axis

This damping property value defines the relationship between force and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR DAMPING option. A real constant or a non-spatial field may be used for this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is force, and velocity is a required independent variable.



Mech Joint (3D Model) - SLOT

This option creates CONN3D2 elements. The connection type is set to SLOT on the *CONNECTOR SECTION option.



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2CHAPTER







Mech Joint (3D Model) - TRANSLATOR

This option creates CONN3D2 elements. The connection type is set to TRANSLATOR on the *CONNECTOR SECTION option.



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2CHAPTER

Mech Joint (3D Model) - UJOINT

This option creates CONN3D2 elements. The connection type is set to UJOINT on the *CONNECTOR SECTION option.



UJOINT Bar/2



Mech Joint (3D Model) - UNIVERSAL

This option creates CONN3D2 elements. The connection type is set to UNIVERSAL on the *CONNECTOR SECTION option.



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2CHAPTER




This stiffness property value defines the relationship between moment and relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR ELASTICITY option. A real constant or a non-spatial field may be used for this property. The n on-spatial fields that have been created with the “Tabular Input” method may be used to define stiffness that varies with displacement and temperature. The dependent variable for this field is moment, and displacement is a required independent variable.


Rot Damping, X Axis

Rot Damping, Z Axis

This damping property value defines the relationship between moment and the rate of change of relative displacement in the connector element. It is translated to the ABAQUS input file with the *CONNECTOR DAMPING option. A real constant or non-spatial field may be used for this property. The non-spatial fields that have been created with the “Tabular Input” method may be used to define damping that varies with velocity and temperature. The dependent variable for these fields is moment, and velocity is a required independent variable.

Mech Joint (3D Model) - WELD

This option creates CONN3D2 elements. The connection type is set to WELD on the *CONNECTOR SECTION option.



WELD Bar/2



2CHAPTER

Axisym Link Gasket

These options create GKAX2 elements. The *GASKET SECTION option is used to define the gasket thickness, width, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to define the membrane and transverse shear behaviors.


Structural 1D 1D Gasket Axisymmetric Link

Gasket Behavior Model

Bar2

Membrane Material This property defines the membrane material to be used. It is translated to the ABAQUS input file as the *GASKET ELASTICITY option with the COMPONENT parameter set to MEMBRANE. The Elastic Modulus and Poisson's Ratio may vary with temperature. This property is not required.

Behavior Type This property defines the type of behavior for the thickness direction. It may be set to either "Damage" or "Elastic-Plastic". This value is translated to the ABAQUS input file as the TYPE parameter on the *GASKET THICKNESS BEHAVIOR option. This property is required.

F/L vs. Closure (Loading)

This property defines the force per unit length versus gasket closure for loading in the thickness direction. It is translated to the ABAQUS input file as the *GASKET THICKNESS BEHAVIOR option with the DIRECTION parameter set to LOADING. A non-spatial field created with the "Tabular Input" method must be used to define this property. The field's independent variables must be either Displacement or Displacement and Temperature. This property is required.

F/L vs. Closure (Unloading)

This property defines the force per unit length versus gasket closure for unloading in the thickness direction. It is translated to the ABAQUS input file as the *GASKET THICKNESS BEHAVIOR option with the DIRECTION parameter set to UNLOADING. A non-spatial field created with the "Tabular Input" method must be used to define this property. The field's independent variables must be either displacement or displacement and temperature. This property is not required.

Shear Stiffness This property defines the shear stiffness of the gasket elements. It is translated to the ABAQUS input file as the *GASKET ELASTICITY option with the COMPONENT parameter set to TRANSVERSE SHEAR. A real constant or a non-spatial field may be used to define this property. The non-spatial fields that have been created with the "Tabular Input" method may be used to define shear stiffness that varies with temperature. This property is not required.

Gasket Thickness This property defines the thickness of the gasket elements. It is translated to the ABAQUS input file as an entry on the *GASKET SECTION option. A real constant or a spatially varying field may be used to define this property. This property is not required. When this property is not specified, the gasket elements' thicknesses are determined from their nodal coordinates.

Thickness Direction This property defines the thickness direction (local one direction) for the elements. It is translated to the ABAQUS input file on the *GASKET SECTION option. A real vector or a spatially varying vector field may be used to define this property. This property is not required.

Width This property defines the width of the gasket element. It is translated to the ABAQUS input file as an entry on the *GASKET SECTION option. A real constant or a spatially varying field may be used to define this property. This property is required.

Initial Gap This property defines the initial gap in the thickness direction of the gasket element. It is translated to the ABAQUS input file as an entry on the *GASKET SECTION option. A real constant or a spatially varying field may be used to define this property. This property is not required.

Initial Void This property defines the initial void in the thickness direction of the gasket element. It is translated to the ABAQUS input file as an entry on the *GASKET SECTION option. A real constant or a spatially varying field may be used to define this property. This property is not required.

2CHAPTER

Axisym Link Gasket (Thick only)

These options create GKAX2N elements. The *GASKET SECTION option is used to define the gasket thickness, width, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction.



Thickness Behavior Only

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2CHAPTER

Axisym Link Gasket (Material)

These options create GKAX2 elements. The *GASKET SECTION option is used to define the gasket thickness, width, initial gap and initial void values. The gasket material is specified using the MATERIAL parameter on the *GASKET SECTION option.



Built-in Material Bar2

Material Name This property defines the material to be used. It is translated to the ABAQUS input file as the MATERIAL parameter on the *GASKET SECTION option. This property is required.






2CHAPTER

3D Link Gasket

These options create GK3D2 elements. The *GASKET SECTION option is used to define the gasket thickness, x-sectional area, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to define the transverse shear behavior.


Structural 1D 1D Gasket 3D Link Gasket Behavior Model

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F vs. Closure (Loading)

This property defines the force versus gasket closure for loading in the thickness direction. It is translated to the ABAQUS input file as the *GASKET THICKNESS BEHAVIOR option with the DIRECTION parameter set to LOADING. A non-spatial field created with the "Tabular Input" method must be used to define this property. The field's independent variables must be either Displacement or Displacement and Temperature. This property is required.

F vs. Closure (Unloading)

This property defines the force versus gasket closure for unloading in the thickness direction. It is translated to the ABAQUS input file as the *GASKET THICKNESS BEHAVIOR option with the DIRECTION parameter set to UNLOADING. A non-spatial field created with the "Tabular Input" method must be used to define this property. The field's independent variables must be either displacement or displacement and temperature. This property is not required.




X-Sectional Area This property defines the x-sectional area of the gasket element. It is translated to the ABAQUS input file as an entry on the *GASKET SECTION option. A real constant or a spatially varying field may be used to define this property. This property is required.

Orientation System This property defines the coordinate system to use in defining the local two and three directions for the gasket elements. It is translated to the ABAQUS input file as an *ORIENTATION option that is referenced in the *GASKET SECTION option from the ORIENTATION parameter. An existing coordinate frame may be used to define this property. This property is not required.

2CHAPTER

Orientation Axis This property defines the axis of rotation of the Orientation System for the Orientation Angle. It is translated to the ABAQUS input file as an *ORIENTATION option that is referenced in the *GASKET SECTION option from the ORIENTATION parameter. An integer value of 1, 2 or 3 may be used to define this property. This property is not required. The default value is 1.

Orientation Angle This property defines the additional rotation about the Orientation Axis in degrees. It is translated to the ABAQUS input file as an *ORIENTATION option that is referenced in the *GASKET SECTION option from the ORIENTATION parameter. A real constant or a spatially varying field may be used to define this property. This property is not required.



3D Link Gasket (Thick only)

These options create GK3D2N elements. The *GASKET SECTION option is used to define the gasket thickness, x-sectional area, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction.


Structural 1D 1D Gasket 3D Link Thickness Behavior Only

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F vs. Closure (Loading)


2CHAPTER

F vs. Closure (Unloading)







3D Link Gasket (Material)

These options create GK3D2 elements. The *GASKET SECTION option is used to define the gasket thickness, x-sectional area, initial gap and initial void values. The gasket material is specified using the MATERIAL parameter on the *GASKET SECTION option.


Structural 1D 1D Gasket 3D Link Built-in Material Bar2



2CHAPTER








2D Link Gasket

These options create GK2D2 elements. The *GASKET SECTION option is used to define the gasket thickness, x-sectional area, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to define the transverse shear behavior.


Structural 1D 1D Gasket 2D Link Gasket Behavior Model

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F vs Closure (Loading)


2CHAPTER

F vs Closure (Unloading)








2D Link Gasket (Thick only)

These options create GK2D2N elements. The *GASKET SECTION option is used to define the gasket thickness, x-sectional area, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction.


Structural 1D 1D Gasket 2D Link Thickness Behavior Only

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F vs Closure (Loading)


2CHAPTER

F vs Closure (Unloading)







2D Link Gasket (Material)

These options create GK2D2 elements. The *GASKET SECTION option is used to define the gasket thickness, x-sectional area, initial gap and initial void values. The gasket material is specified using the MATERIAL parameter on the *GASKET SECTION option.


Structural 1D 1D Gasket 2D Link Built-in Material Bar2



2CHAPTER





Thin Shell

Options above create STRI35, STRI65, S4R5, S8R5, or S9R5 elements with *SHELL SECTION properties. *ORIENTATION, *TRANSVERSE SHEAR STIFFNESS, and *HOURGLASS STIFFNESS options may also be created, as required. This element defines a standard thin shell element.


Structural 2D Shell Thin Shell Homogeneous Tri/3, Quad/4, Tri/6, Quad/8, Quad/9

Defines the uniform shell thickness of the elements. This can be either a real constant or a reference to an existing field definition. This property is required.


Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse, or type the name in. This identifies the material which will be referenced on the *SHELL SECTION option. This property is required.

Defines the orientation of the material within the element. This is a reference to an existing coordinate system. The referenced coordinate system defines the data used to create the ∗ ORIENTATION option.

Defines the offset of the reference surface, which contains the nodes of the elements, as a fraction of the shell's thickness. The offset is measured from the mid-surface of the shell. For example, a value of 0.5 indicates that the reference surface is located at shell's top surface. A value of -0.5 indicates that the reference surface is located at the shell's bottom surface.

2CHAPTER

More data input is available for creating Thin Shell elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.


Orientation System Defines the orientation of the material within the shell element. This is a reference to an existing coordinate system. The referenced coordinate system defines the data used to create the *ORIENTATION option.

Ave Shear Stiffness Defines the transverse shear stiffness. This is the value on the *TRANSVERSE SHEAR STIFFNESS option. This is either a real constant or a reference to an existing field definition.

Membrane Hourglass StiffnessNormal Hourglass StiffnessBending Hourglass Stiffness

Define the artificial stiffness for hourglass control in membrane, normal, and bending modes. These define parameters on the *HOURGLASS STIFFNESS option. These can be either real constants or references to existing field definitions.

Thin Shell (Laminated)

Options above create STRI35, STRI65, S4R5, S8R5, or S9R5 elements with *SHELL SECTION properties. *ORIENTATION and ∗ TRANSVERSE SHEAR STIFFNESS options may also be created, as required. This defines a laminate thin shell element.


Structural 2D Shell Thin Shell Laminate Tri/3, Quad/4, Tri/6, Quad/8, Quad/9

Defines the orientation of the material within the shell element. This is a reference to an existing coordinate system. The referenced coordinate system defines the data used to create the *ORIENTATION option.

Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material which will be referenced on the ∗ SHELL SECTION option. This property is required. This material must be a laminate composite within MSC.Patran.

Defines the transverse shear stuffiness. These are the values on the ∗ TRANSVERSE SHEAR STIFFNESS option. These are either real constants or references to existing field definitions.


2CHAPTER

Thick Shell

Options above create S3R, STRI65, S4R, or S8R elements with *SHELL SECTION properties. *ORIENTATION, *TRANSVERSE SHEAR STIFFNESS and *HOURGLASS STIFFNESS options may also be created, as required. This defines a homogeneous thick shell element.


Structural 2D Shell Thick Shell Homogeneous Tri/3, Quad/4, Tri/6, Quad/8



Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material which will be referenced on the *SHELL SECTION option. This property is required.

Orientation axis.

Orientation angle.


More data input is available for creating Thick Shell elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.



Shear Stiffness K13Shear Stiffness K23

Defines the transverse shear stIffness. These are the values on the *TRANSVERSE SHEAR STIFFNESS option. These are either real constants or references to existing field definitions.


Define the artificial stIffness for hourglass control in membrane, normal, and bending modes. These define parameters on the *HOURGLASS STIFFNESS option. These can be either real constants or references to existing field definitions.

2CHAPTER

Thick Shell (Laminated)

Options above create S3R, STRI65, S4R, or S8R elements with *SHELL SECTION properties. *ORIENTATION and ∗ TRANSVERSE SHEAR STIFFNESS options may also be created, as required. This defines a laminate thick shell element.


Structural 2D Shell Thick Shell Laminate Tri/3, Quad/4, Tri/6, Quad/8



Defines the transverse shear stiffness. These are the values on the *TRANSVERSE SHEAR STIFFNESS option. These are either real constants or references to existing field definitions.


General Thin

Options above create STRI35, STRI65, S4R5, S8R5, or S9R5 elements with *SHELL GENERAL SECTION properties. *ORIENTATION, *TRANSVERSE SHEAR STIFFNESS, and *HOURGLASS STIFFNESS options may also be created, as required. This defines a general thin shell element.


Structural 2D Shell General Thin Shell

Homogenous Tri/3, Quad/4, Tri/6, Quad/8, Quad/9

Input Properties

General Thin Shell


OK

Section Stiffness D11


Real Scalar

Real Scalar



Real Scalar

Real Scalar



Real Scalar

Real Scalar

Field Definitions

Defines the symmetric half of the [D] section stiffness matrix on the ∗ SHELL GENERAL SECTION option. These properties are required. The remainder of the matrix entries are shown on the following page.

2CHAPTER

More data input is available for creating General Thin Shell elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.


Section Stiffness D14Section Stiffness D24Section Stiffness D34Section Stiffness D44Section Stiffness D15Section Stiffness D25Section Stiffness D35Section Stiffness D45Section Stiffness D55Section Stiffness D16Section Stiffness D26Section Stiffness D36Section Stiffness D46Section Stiffness D56Section Stiffness D66

Defines the symmetric half of the [D] section stiffness matrix on the *SHELL GENERAL SECTION option. These properties are required.

Force Vector {F1..F6} Defines the 6 values of the {F} vector on the *SHELL GENERAL SECTION option. This vector defines the generalized stresses caused by a fully constrained unit temperature rise. This is a list of 6 real constants. This property is required.

Temperature ScalingThermal Expansion ScalingTemperature Values

Define the temperature effects on the *SHELL GENERAL SECTION option. These are lists of real values. Each list must have the same number of values. These values are optional.


Reference Temperature Defines the reference temperature for all thermal effects on this element. This defines the ZERO parameter on the *SHELL GENERAL SECTION option.

Density, mass/area Defines the mass per unit area for the shell element. This is the DENSITY parameter on the *SHELL GENERAL SECTION option. This value can be either a real constant or a reference to an existing field definition.

Ave Shear Stiffness Defines the transverse shear stiffness. This is the value on the *TRANSVERSE SHEAR STIFFNESS option. This is either a real constant or a reference to an existing field definition.



General Thin Shell (Laminated)

Options above create STRI3, STRI65, S4R5, S8R5 or S9R5 elements with *SHELL GENERAL SECTION properties. *ORIENTATION and ∗ TRANSVERSE SHEAR STIFFNESS options may also be created, as required. This defines a laminate thin shell element.


Structural 2D Shell General Thin Shell Laminate Tri/3, Quad/4, Tri/6, Quad/8, Quad/9


Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material which will be referenced on the ∗ SHELL GENERAL SECTION option. This property is required. This material must be a laminate composite in MSC.Patran.


2CHAPTER

General Thick

Options above create S3R, STRI65, S4R, or S8R elements with *SHELL GENERAL SECTION properties. *ORIENTATION, *TRANSVERSE SHEAR STIFFNESS, and *HOURGLASS STIFFNESS options may also be created, as required. This defines a general thick shell element.


Structural 2D Shell General Thick Shell Tri/3, Quad/4, Tri/6, Quad/8

Input Properties

General Thick Shell


OK



Real Scalar

Real Scalar



Real Scalar

Real Scalar



Real Scalar

Real Scalar

Field Definitions


More data input is available for creating General Thick Shell elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.



Defines the symmetric half of the [D] section stiffness matrix on the *SHELL GENERAL SECTION option. These properties are required.

Force Vector {F1..F6} Defines the 6 values of the {F} vector on the *SHELL GENERAL SECTION option. This vector defines the generalized stresses caused by a fully constrained unit temperature rise. This is a list of 6 real constants. This property is required.

Temperature ScalingThermal Expansion ScalingTemperature Values

Define the temperature effects on the *SHELL GENERAL SECTION option. These are lists of real values. Each list must have the same number of values. These values are optional.


Reference Temperature Defines the reference temperature for all thermal effects on this element. This defines the ZERO parameter on the *SHELL GENERAL SECTION option.

Density, mass/area Defines the mass per unit area for the shell element. This is the DENSITY parameter on the *SHELL GENERAL SECTION option. This value can be either a real constant or a reference to an existing field definition.





2CHAPTER

General Thick Shell (Laminated)

Options above create S3R, STRI65, S4R, or S8R elements with *SHELL GENERAL SECTION properties. *ORIENTATION and ∗ TRANSVERSE SHEAR STIFFNESS options may also be created, as required. This defines a laminate thick shell element.


Structural 2D Shell General Thick Shell

Laminate Tri/3, Quad/4, Tri/6, Quad/8, Quad/9


Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material which will be referenced on the ∗ SHELL GENERAL SECTION option. This property is required. This material must be a laminate composite in MSC.Patran.



Large Strain

Options above create S3R, S4R, or S8R elements with ∗ SHELL SECTION properties. ∗ ORIENTATION, ∗ TRANSVERSE SHEAR STIFFNESS, and ∗ HOURGLASS STIFFNESS options may also be created, as required. This defines a large strain element.


Structural 2D Shell Large Strain Shell Tri/3, Quad/4, Tri/6, Quad/8

This is currently not supported.



Defines the orientation of the material within the shell element. This is a reference to an existing coordinate system. The referenced coordinate system defines the data used to create the ∗ ORIENTATION option.

2CHAPTER

More data input is available for creating Large Strain Shell elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.


Membrane Hourglass StiffNormal Hourglass StiffBending Hourglass Stiff

Define the artificial stiffness for hourglass control in membrane, normal, and bending modes. These define parameters on the ∗ HOURGLASS STIFFNESS option. These can be either real constants or references to existing field definitions.

General Large Strain

Options above create S3R, S4R, or S8R elements with ∗ SHELL GENERAL SECTION properties. ∗ ORIENTATION, ∗ TRANSVERSE SHEAR STIFFNESS, and ∗ HOURGLASS STIFFNESS options may also be created, as required. This defines a general large strain element.


Structural 2D Shell General Large Strain Shell

Tri/3, Quad/4

Input Properties

General Large Strain Shell


OK



Real Scalar

Real Scalar



Real Scalar

Real Scalar



Real Scalar

Real Scalar



2CHAPTER

More data input is available for creating General Large Strain Shell elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu.



Defines the symmetric half of the [D] section stiffness matrix on the ∗ SHELL GENERAL SECTION option. These properties are required.

Force Vector F1...F6 Defines the 6 values of the {F} vector on the ∗ SHELL GENERAL SECTION option. This vector defines the generalized stresses caused by a fully constrained unit temperature rise. This is a list of 6 real constants. This property is required.

Temperature Scaling DThermal Expansion ScalingTemperature Values

Define the temperature effects on the ∗ SHELL GENERAL SECTION option. These are lists of real values. Each list must have the same number of values. These values are optional.

Orientation System Defines the orientation of the material within the shell element. This is a reference to an existing coordinate system. The referenced coordinate system defines the data used to create the ∗ ORIENTATION option.

Reference Temperature Defines the reference temperature for all thermal effects on this element. This defines the ZERO parameter on the ∗ SHELL GENERAL SECTION option.

Density, mass/area Defines the mass per unit surface area for the shell element. This is the DENSITY parameter on the ∗ SHELL GENERAL SECTION option. This value can be either a real constant or a reference to an existing field definition.

Poisson Parameter Permits an “overall” change of the cross section dimensions as a function of the axial strains. This is the value of the POISSON parameter on the *SHELL GENERAL SECTION option.


Defines the transverse shear stiffness. These are the values on the ∗ TRANSVERSE SHEAR STIFFNESS option. These are either real constants or references to existing field definitions.


Define the artificial stiffness for hourglass control in membrane, normal, and bending modes. These define parameters on the ∗ HOURGLASS STIFFNESS option. These can be either real constants or references to existing field definitions.

Plane Strain

Options above create CPE3, CPE4, CPE4R, CPE6, CPE6M, CPE8, CPE8R, CPE3H, CPE4H, CPE4RH, CPE6H, CPE6MH, CPE8H, or CPE8RH (depending on the selected options and topologies) elements with *SOLID SECTION properties. The thickness value on the *SOLID SECTION option is included. *ORIENTATION and *HOURGLASS STIFFNESS options may also be included, as required. If triangular element are found where reduced integration is requested, standard integration elements will be used.


Structural 2D 2D Solid Plane Strain

Standard FormulationHybridHybrid/Reduced IntegrationReduced IntegrationIncompatible ModesHybrid/Incompatible ModesModified FormulationModified/Hybrid

Tri/3, Quad/4, Tri/6, Quad/8

Tri/6Tri/6


Defines the material to be used. When entering data here, a list of all materials in the database is displayed. You can either pick one from the list with the mouse or type the name in. This identifies the material which will be referenced on the ∗ SOLID SECTION option. This property is required.

Input PropertiesPlain Strain


OK

Material Name

[Thickness]

Mat Prop Name

Real Scalar

[Orientation System CID


Defines the thickness of the elements. The default is unit thickness.Integer[Orientation Axis ]]

Define the artificial stiffness for hourglass control. This defines a parameter on the ∗ HOURGLASS STIFFNESS option. This can be either a real constant or a reference to an existing field definition.

Real Scalar[ Hourglss Stiff Param ]

2CHAPTER

Generalized Plane Strain

These options create CGPE5, CGPE5H, CGPE6, CGPE6H, CGPE6I, CGPE6IH, CGPE6R, CGPE6RH, CGPE8, CGPE8H, CGPE10, CGPE10H, CGPE10R or CGPE10RH elements with *SOLID SECTION properties when writing an ABAQUS V5.X or V4.X input file. Otherwise, they create CPEG3, CPEG3H, CPEG4, CPEG4H, CPEG4I, CPEG4IH, CPEG4R, CPEG4RH, CPEG6, CPEG6H, CPEG8, CPEG8H, CPEG8R or CPEG8RH elements with *SOLID SECTION properties. The thickness value on the *SOLID SECTION option is included. *ORIENTATION and *HOURGLASS STIFFNESS options may also be included, as required. If triangular elements are found where reduced integration is requested, standard integration elements will be used.


Structural 2D 2D Solid General PlaneStrain

Standard FormulationHybridHybrid/Reduced IntegrationReduced IntegrationIncompatible ModesHybrid/Incompatible Modes

Tri/3, Quad/4Tri/6, Quad/8

Input PropertiesPlain Strain


OK

Material Name

[Thickness]

Mat Prop Name

Real Scalar

[Orientation System CID


Real Scalar[Orientation Angle ]Defines the orientation of the material within the element. This is a reference to an existing coordinate system. The referenced coordinate system defines the data used to create the ∗ ORIENTATION option.


Defines the thickness of the elements. The default is unit thickness.

Defines the extra degrees of freedom required for each CGPE type element. Used to define the last two nodes in the element connectivity list. (Note: nodes A and B are uniquely defined.)

Defines the original value of the two components of rotation about the x-and y- axes <RX,RY> in the bounding planes at Node B. These values appear as the second and third values on the *SOLID SECTION data card.

Node Id

Node Id

Node A: DOF <UZ>

Node B: DOF <RX,RY>

Real Scalar[Bounding Plane <RX]

[Bounding Plane.<RY] Real Scalar


[Reference Node] V6.X+ Defines the REF NODE parameter on the *SOLID SECTION option. The third degree of freedom of this node defines the change in length between the bounding planes. The fourth and fifth degrees of freedom of this node define the relative rotations of one bounding plane with respect to the other. This property is required when generating an ABAQUS version 6 or greater input file.

[Node A: DOF<UZ>] V5.X This property is required when generating an ABAQUS version 4 or 5 input file.

[Node B: DOF<RX,RY] V5.X This property is required when generating an ABAQUS version 4 or 5 input file.

2CHAPTER

Plane Stress

Options above create CPS3, CPS4, CPS4R, CPS6, CPS6M, CPS8, or CPS8R (depending on the selected options and topologies) elements with *SOLID SECTION properties. The thickness value on the *SOLID SECTION option will be included. *ORIENTATION and *HOURGLASS STIFFNESS options may also be created, as required. If triangular elements are found where reduced integration is requested, standard integration elements will be used.


Structural 2D 2D Solid Plane Stress

Standard FormulationReduced IntegrationIncompatible ModesModified Formulation


Tri/6




Defines the uniform thickness of the elements. The default is unit thickness. This can be either a real constant or a reference to an existing field definition. If a field is referenced, it will be evaluated at the centroid of each element.

Input Properties

Plane Stress


OK

Material Name

[ Thickness ]

Mat Prop Name

CID

[ Orientation System ] Real Scalar

[ Hourglss Stiff Param ] Real Scalar


Integer[Orientation Axis ]]

Axisymmetric Solid

Options above create CAX3, CAX4, CAX4R, CAX6, CAX6M, CAX8, CAX8R, CAX3H, CAX4H, CAX4RH, CAX6H, CAX6MH, CAX8H, or CAX8RH elements (depending on the selected options and topologies) with ∗ SOLID SECTION properties. *ORIENTATION and ∗ HOURGLASS STIFFNESS option may also be created, as required. If triangular elements are found where reduced integration is requested, standard integration elements will be used.


Structural 2D 2D Solid Axisymmetric Standard FormulationReduced IntegrationIncompatible ModesHybridModified FormulationModified/Hybrid


Tri/6Tri/6

Input Properties

Axismmetric Solid (Red_Int)


OK



[Orientation Axis ]] Integer


[Orientation Angle ] Real Scalar


m:compound_x

compound_x




2CHAPTER

Axisymmetric Solid with Twist (General)

Options above create CGAX3, CGAX4, CGAX4R, CGAX6, CGAX8, CGAX8R, CGAX3H, CGAX4H, CGAX4RH, CGAX6H, CGAX8H, or CGAX8RH elements (depending on the selected options and topologies) with ∗ SOLID SECTION properties. *ORIENTATION and ∗ HOURGLASS STIFFNESS options may also be created, as required. If triangular elements are found where reduced integration is requested, standard integration elements will be used.


Structural 2D 2D Solid General Axisymmetric

Standard FormulationHybridReduced IntegrationHybrid/Reduced Integration

Tri/3, Quad/4, Tri/6, Quad/8Quad/4, Quad/8

Input Properties

Gen Axi Solid (Red_Int)


OK







m:compound_x

compound_x




Membrane

Options above create M3D3, M3D4, M3D4R, M3D6, M3D8, M3D8R, M3D9 or M3D9R elements (depending on the selected options and topologies) with ∗ SOLID SECTION properties. The thickness value on the ∗ SOLID SECTION option is included. ∗ ORIENTATION and ∗ HOURGLASS STIFFNESS options may also be created, as required. If triangular elements are found where reduced integration is requested, standard integration elements will be used.


Structural 2D Membrane Standard FormulationReduced Integration




Define the artificial stiffness for hourglass control. This defines a parameter on the ∗ HOURGLASS STIFFNESS option. This can be either a real constant or a reference to an existing field definition. This is not used if reduced integration is selected.

Input Properties

MembraneProperty Name Value Value Type

OK

Material Name

Membrane Thickness

Mat Prop Name

CID

[ Orientation System ] Real Scalar



Defines the uniform thickness of the elements. This is the thickness value on the ∗ SOLID SECTION option. This can be either a real constant or a reference to an existing field definition. If a field is referenced, it will be evaluated at the centroid of each element.



2CHAPTER

Planar 2D Interface

Options above create INTER2 or INTER3 elements (depending on the selected topology) with ∗ INTERFACE, ∗ FRICTION, and ∗ SURFACE CONTACT properties. The SOFTENED parameter on the ∗ SURFACE CONTACT option may be included, depending on the selected option. This element defines an interface region between two portions of a planar model. These elements must be created from one contact surface to the other.


Structural 2D 2D Interface Planar Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Quad/4, Quad/8

Defines the thickness normal to the model plane. This value is used only for deriving interface pressure values. The default is 1.0.


Input Properties

Interface Elastic Slip ( planar )Property Name Value Value Type

OK

[ Thickness ]


Real Scalar

Real Scalar

[ Elastic Slip ]

[ Slip Tolerance ]

Real Scalar

Real Scalar

[ Stiffness in Stick ]

[ Max Friction ]

Real Scalar

Real Scalar

Field Definitions

More data input is available for creating Planar 2D Interface elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.







Pressure Zero Press Defines the pressure at zero clearance. This is the value on the ∗ SURFACE CONTACT, SOFTENED option. This property is only used for the Soft Contact option. This is a real constant.








Ff

p0

p0

2CHAPTER

Axisymmetric 2D Interface

Options above create INTER2A or INTER3A elements (depending on the selected topology) with *INTERFACE, *FRICTION, and *SURFACE CONTACT properties. The SOFTENED parameter on the *SURFACE CONTACT option may be included, depending on the selected option. This element defines an interface region between two portions of an axisymmetric model. These elements must be created from one contact surface to the other.


Structural 2D 2D Interface Axisymmetric Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Quad/4, Quad/8

Defines the sliding friction in the element’s 1 and 2 directions. These are the friction coefficients on the second card of the *FRICTION option. If Friction in Dir_2 is specified, then the ANISOTROPIC parameter is included on the ∗ FRICTION option. These values can be either real constants or references to existing field definitions.

Input Properties

Interface Elastic Slip (Axisym)


OK


[ Elastic Slip ]

Real Scalar

Real Scalar

[ Slip Tolerance ]

[ Stiffness in Stick ]

Real Scalar

Real Scalar

[ Max Friction Stress ]

[ Clearance Zero-Press

Real Scalar

Real Scalar

Field Definitions

More data input is available for creating Axisymmetric 2D Interface elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.















Ff

p0

p0

2CHAPTER

IRS (Shell/Solid)

Options above create IRS3, IRS4, and IRS9 elements (depending on the selected topology) with ∗ INTERFACE, ∗ FRICTION and ∗ SURFACE CONTACT properties. The SOFTENED parameter on the ∗ SURFACE CONTACT option may be included, depending on the selected option. This defines a rigid surface element for use with solid or shell elements.


Structural 2D IRS (shell/solid)

Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Quad/4


Input Properties

IRS Elastic Slip (shell/solid)Property Name Value Value Type

OK


Reference Node Node Id



Real Scalar

Real Scalar

[ Elastic Slip ]

[ Slip Tolerance ]

Real Scalar

Real Scalar

String

More data input is available for creating IRS (shell/solid) elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.


Reference Node Reference node common to the IRS elements and the rigid surface.


Defines the sliding friction in the element’s 1 and 2 directions. These are the friction coefficients on the second card of the ∗ FRICTION option. If Friction in Dir_2 is specified, then the ANISOTROPIC parameter is included on the ∗ FRICTION option. These values can be either real constants or references to existing field definitions.














Ff

p0

p0

2CHAPTER


Options above create a ∗ RIGID SURFACE, TYPE=BEZIER option for use in three-dimensional analysis (see Section 7.4.7 of the ABAQUS/Standard User’s manual).

All trias forming up the rigid surface must have the normals pointing towards the contacting surface. Trias must all be connected.


Structural 2D Rigid Surf (Bz3D) Quad 4


Input Properties



OK


[ Critical Distance ] Real Scalar

String

Critical penetration distance which will cause ABAQUS to restart an increment. This is the value of the HCRIT parameter on the ∗ RIGID SURFACE option. The default value is the radius of a sphere that circumscribes a characteristic patch in the surface. It is rarely necessary to change this default.

Rigid surface

Vertices

Smooth Bezier surface

V1 V2

V3

n y

x

z

patch

Rigid Surface (LBC)

This property set is created when the Rigid-Deform contact lbc is created in the Loads/BCs menu. The creation or deletion of this property set is not required by the user. The elements associated with this property set are translated as R3D3 and R3D4 elements.


Structural 2D Rigid Surface(LBC) Quad4,Tria3

Name of the Rigid-Deform contact lbc for which this element property set was created.

Input Properties

Rigid Surface (Lbc)Property Name Value Value Type

OK

Contact Lbc Name String

2CHAPTER

2D Rebar

The options above create SFM3D3, SFM3D4, SFM3D4R, SFM3D6, SFM3D8, SFM3D8R and SFMCL9 elements (depending on the selected options and topologies) with *SURFACE SECTION properties. The *EMBEDDED ELEMENT and *REBAR LAYER options are also created..


Structural 2D Rebar CylindricalGeneral

Standard Formulation Reduced Integration

Quad/9Tri/3, Tri/6, Quad/4, Quad/8Quad/4, Quad/8

Material Name Defines the material to be used. When entering data here, a list of all isotropic materials in the database is displayed. You can either pick one from the list with the mouse or type in the name. This identifies the material that will be referenced on the *REBAR LAYER option. This property is required.

X-Sectional Area Defines the area of the rebar cross-section. This is the cross-sectional area value on the *REBAR LAYER option. A real constant, a reference to an existing field definition, or a real list may be entered. A real list is used to specify the cross-sectional area for more than one rebar layer. This property is required.

Spacing Defines the spacing of the rebars within a layer. This is the spacing value on the *REBAR LAYER option. A real constant, a reference to an existing field definition, or a real list may be entered. A real list is used to specify the spacing for more than one rebar layer. This property is required.

Spacing Unit Type Defines the unit type for the spacing values. When “Angle” is specified, the ANGULAR SPACING parameter is used for the *REBAR LAYER option. “Distance” is the default value. This property is not required.

Rebar Orient. Angle Defines the angular orientation of the rebar from the local 1-direction in degrees. This is the angular orientation value on the *REBAR LAYER option. A real constant, a reference to an existing field definition, or a real list may be entered. A real list is used to specify the angular orientation for more than one rebar layer. This property is required.

Host Property Set Defines the element property set of the elements that host the rebar elements. This is the “HOST ELSET” parameter on the *EMBEDDED ELEMENT option. A reference to an existing element property set may be specified. By default, the solver determines the host elements based on the position of the embedded elements within the model. This property is not required.

Roundoff Tolerance Defines the value below which the weigh factors of the host element’s nodes will be zeroed out. This is the ROUNDOFF TOLERANCE parameter on the *EMBEDDED ELEMENT option. A real scalar may be specified. The default value is 1E+6. This property is not required.

Orientation System Defines a local coordinate system for orienting the rebars. This is a reference to an existing coordinate system. The referenced coordinate system defines the data used to create an *ORIENTATION option. The orientation name is then used for the ORIENTATION parameter on the *REBAR LAYER option. This property is not required.

Orientation Axis Defines the axis of rotation on the “Orientation System” to use for the additional rotation specified by the “Orientation Angle”. The axis should have a nonzero component in the direction of the normal to the surface. An integer value between 1 and 3 may be specified. The local 1-direction is the default value. This property is not required.

Orientation Angle Defines the additional rotation in degrees about the “Orientation Axis” of the “Orientation System”. Either a real scalar or a reference to an existing field definition may be specified. The default value is zero. This property is not required.

2CHAPTER

Plane Strain Gasket

These options create GKPE4 elements. The *GASKET SECTION option is used to define the gasket thickness, out-of-plane thickness, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to define the transverse shear behavior.


Structural 2D 2D Gasket Plane Strain Gasket Behavior Model

Quad4



P vs Closure (Loading)

This property defines the pressure versus gasket closure for loading in the thickness direction. It is translated to the ABAQUS input file as the *GASKET THICKNESS BEHAVIOR option with the DIRECTION parameter set to LOADING. A non-spatial field created with the "Tabular Input" method must be used to define this property. The field's independent variables must be either Displacement or Displacement and Temperature. This property is required.

P vs Closure (Unloading)

This property defines the pressure versus gasket closure for unloading in the thickness direction. It is translated to the ABAQUS input file as the *GASKET THICKNESS BEHAVIOR option with the DIRECTION parameter set to UNLOADING. A non-spatial field created with the "Tabular Input" method must be used to define this property. The field's independent variables must be either displacement or displacement and temperature. This property is not required.


Thickness This property defines the out-of-plane thickness of the of the gasket element. It is translated to the ABAQUS input file as an entry on the *GASKET SECTION option. A real constant or a spatially varying field may be used to define this property. This property is not required.





2CHAPTER

Plane Strain Gasket (Material)

These options create GKPE4 elements. The *GASKET SECTION option is used to define the gasket thickness, out-of-plane thickness, initial gap and initial void values. The gasket material is specified using the MATERIAL parameter on the *GASKET SECTION option.


Structural 2D 2D Gasket Plane Strain Built-in Material Quad4







2CHAPTER

Plane Stress Gasket

These options create GKPS4 elements. The *GASKET SECTION option is used to define the gasket thickness, out-of-plane thickness, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to define the transverse shear behavior.


Structural 2D 2D Gasket Plane Stress Gasket Behavior Model

Quad4













2CHAPTER

Plane Stress Gasket (Thick only)

These options create GKPS4N elements. The *GASKET SECTION option is used to define the gasket thickness, out-of-plane thickness, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction.


Structural 2D 2D Gasket Plane Stress Thickness Behavior Only

Quad4











2CHAPTER

Plane Stress Gasket (Material)

These options create GKPS4 elements. The *GASKET SECTION option is used to define the gasket thickness, out-of-plane thickness, initial gap and initial void values. The gasket material is specified using the MATERIAL parameter on the *GASKET SECTION option.


Structural 2D 2D Gasket Plane Stress Built-in Material Quad4







2CHAPTER

Axisymmetric Gasket

These options create GKAX4 elements. The *GASKET SECTION option is used to define the gasket thickness, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to define the transverse shear behavior..


Structural 2D 2D Gasket Axisymmetric Gasket Behavior Model

Quad4












2CHAPTER

Axisymmetric Gasket (Thick only)

These options create GKAX4N elements. The *GASKET SECTION option is used to define the gasket thickness, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction.


Structural 2D 2D Gasket Axisymmetric Thickness Behavior Only

Quad4










2CHAPTER

Axisymmetric Gasket (Material)

These options create GKAX4 elements. The *GASKET SECTION option is used to define the gasket thickness, initial gap and initial void values. The gasket material is specified using the MATERIAL parameter on the *GASKET SECTION option.


Structural 2D 2D Gasket Axisymmetric Built-in Material Quad4






2CHAPTER

3D Line Gasket

These options create GK3D4L elements. The *GASKET SECTION option is used to define the gasket thickness, width, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to define the transverse shear behavior.


Structural 2D 2D Gasket Line Gasket Behavior Model

Quad4













2CHAPTER

3D Line Gasket (Thick only)

These options create GK3D4LN elements. The *GASKET SECTION option is used to define the gasket thickness, width, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction.


Structural 2D 2D Gasket Line Thickness Behavior Only

Quad4











2CHAPTER

3D Line Gasket (Material)

These options create GK3D4L elements. The *GASKET SECTION option is used to define the gasket thickness, width, initial gap and initial void values. The gasket material is specified using the MATERIAL parameter on the *GASKET SECTION option.


Structural 2D 2D Gasket Line Built-in Material Quad4







2CHAPTER

Solid

Options above create C3D4, C3D6, C3D8, C3D8R, C3D10, C3D10M, C3D15, C3D20, C3D20R, C3D4H, C3D6H, C3D8H, C3D8RH, C3D10H, C3D10MH, C3D15H, C3D20H, C3D20RH, C3D27, C3D27R, C3D27H, or C3D27RH elements (depending on the selected options and topologies) with ∗ SOLID SECTION properties. ∗ ORIENTATION and ∗ HOURGLASS STIFFNESS options may also be created, as required. If tetrahedral or wedge elements are found where reduced integration is requested, standard integration elements will be used.


Structural 3D Solid Standard FormulationHybridHybrid/Reduced IntegrationReduced IntegrationIncompatible ModesHybrid/Incompatible ModesModified FormulationModified/Hybrid

Laminate Tet/4, Tet/10, Wedge/6, Wedge/15, Hex/8, Hex/20, Hex/27

Tet/10Tet/10



Defines the artificial stiffness for hourglass control. This defines the parameter on the *HOURGLASS STIFFNESS option. This can be either a real constant or a reference to an existing field definition.

Input Properties

SolidProperty Name Value Value Type

OK

Material Name


[Orientation Axis ] Integer

Mat Prop Name


[Hourglass Stiff Param] Real Scalar


3D Interface

Options above create INTER4, INTER8 or INTER9 elements (depending on the selected topology) with *INTERFACE, *FRICTION, and *SURFACE CONTACT properties. The SOFTENED parameter on the *SURFACE CONTACT option may be included, depending on the selected option. This element defines an interface region between two portions of a spatial model. These elements must be created from one contact surface to the other.


Structural 3D 3D Interface Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping No SeparationLagrange Vis DampingLagrange Vis Damping No Separation

Hex/8, Hex/20, Hex/27

Defines the sliding friction in the element’s 1 and 2 directions. These are the friction coefficients on the second card of the ∗ FRICTION option. If Friction in Dir_2 is specified, then the ANISOTROPIC parameter is included on the ∗ FRICTION option. These values can be either real constants or references to existing field definitions.

Input Properties

Interface Elastic Slip (Solid)Property Name Value Value Type

OK



Real Scalar

Real Scalar

[ Elastic Slip ]

[ Slip Tolerance ]

Real Scalar

Real Scalar

[ Stiffness in Stick

[ Max Friction Stress ]

Real Scalar

Real Scalar

Field Definitions

2CHAPTER

More data input is available for creating 3D Interface elements by scrolling down the input properties menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than one of these options, all but the first will be ignored.



Slip Tolerance Defines the value of to redefine the ratio of allowable maximum elastic slip to characteristic element length dimension. The default is .005. This is the value of the SLIP TOLERANCE parameter on the ∗ FRICTION option.












Ff

p0

p0

Thermal Link

Options above create DC1D2 or DC1D3 elements, depending on the specified topology with *SOLID SECTION properties. The cross-sectional area value on the *SOLID SECTION option is included.


Thermal 1D Link Bar/2, Bar/3


Defines the cross-sectional area of the thermal link. This value is the area value on the ∗ SOLID SECTION option. This value can be either a real constant or a reference to an existing field definition. If a field is referenced, it will be evaluated at the centroid of each element. This property is required.

Input Properties

Thermal Link


OK

Material Name

X-Sectional area

Mat Prop Name

Real Scalar


2CHAPTER

Thermal Axisymmetric Shell

Options above create DSAX1 or DSAX2 elements (depending on the specified topology) with *SHELL SECTION properties.


Thermal 1D Axisymmetric Shell

Homogeneous Bar/2, Bar/3


Defines the thickness of the thermal shell. This value is the thickness value on the ∗ SHELL SECTION option. This value can be either a real constant or a reference to an existing field definition. If a field is referenced, it will be evaluated at the centroid of each element. This property is required.

Input Properties

Thermal Axisym Shell


OK

Material Name

Shell Thickness

Mat Prop Name

Real Scalar

[ # Integration Points ] Integer


Defines the number of integration points through the shell section.This value is an integer and must be an odd number. The default is 5 points. This is also the number of temperature degrees-of-freedom at a node of the element.

Thermal Axisymmetric Shell (Laminated)

Options above create DSAX1 or DSAX2 elements (depending on the specified topology) with ∗ SHELL SECTION, COMPOSITE properties.


Thermal 1D Axisymmetric Shell Laminate Bar/2, Bar/3


Input Properties

Thermal Axisym Shell (Laminated)


OK



2CHAPTER

Thermal 1D Interface

Options above create DINTER1 elements with ∗ INTERFACE properties. These elements must be created from one contact surface to the other. ∗ GAP CONDUCTANCE and ∗ GAP RADIATION options are also created, as required.


Thermal 1D 1D Interface Bar/2

Defines the uniform cross-sectional area of the interface. This value is the area property on the ∗ INTERFACE option. This value can be either a real constant or a reference to an existing field definition. If a field is referenced, it will be evaluated at the centroid of each element. This property is required.

Defines the heat conductance across the interface. These properties define the gap conductance as a function of gap clearance used on the ∗ GAP CONDUCTANCE option. These are lists of real constants. These lists must have the same number of values. These lists are optional.

Input Properties

Thermal Interface (General)Property Name Value Value Type

OK

X-Sectional area

[ Conductance vs Clea ]

Real Scalar

Real List

[ Gap Clearance ]

[ Conductance vs Pres ]

Real List

Real List

[ Gap Pressure ]

[ Average Mass Flow ]

Real List

Real List

Field Definitions

Defines the constants of the radiation behavior across the interface. These properties define the , , and

values used on the ∗ GAP RADIATION option. These can be either real constants or references to existing field definitions.

FA FBθ0

Vector Vector

[ Rad Constant Fa ] Real Scalar

[ Rad Constant Fb ] Real Scalar

Absolute Zero Temp Real Scalar

[ Average Temperature ] Real List

Thermal Shell

Options above create DS3, DS4, DS6 or DS8 elements (depending on the selected topology) with *SHELL SECTION properties. An *ORIENTATION option may also be created, as required.


Thermal 2D Shell Homogeneous Quad/4, Quad/8


Defines the number of integration points through the shell section. This value is an integer and must be an odd number. The default is 5 points. This is also the number of temperature degrees-of-freedom at a node of the element.


Input Properties

Thermal Shell


OK

Material Name

Shell Thickness

Mat Prop Name

Real Scalar

[ # Integration Points ]


Integer

CID

Defines the orientation of this property data. This is a reference to an existing coordinate system. This referenced coordinate system defines the data used to create the ∗ ORIENTATION option for orienting the element and material coordinate systems.




2CHAPTER

Thermal Shell (Laminated)

Options above create DS3, DS4, DS6 or DS8 elements (depending on the selected topology) with *SHELL SECTION, COMPOSITE properties. An *ORIENTATION option may also be created, as required.


Thermal 2D Shell Laminate Quad/4, Quad/8


Defines the orientation of this property data. This is a reference to an existing coordinate system. This referenced coordinate system defines the data used to create the ∗ ORIENTATION option for orienting the element and material coordinate systems.

Input Properties

Thermal Shell (Laminated)


OK




Integer[ Orientation Axis ]

Orientation Axis defines a supplemental rotation made to the referenced coordinate system. This defines the third card on the ∗ ORIENTATION option.

Real Scalar[ Orientation Angle ]

Thermal Planar Solid

Options above create DC2D3, DC2D4, DC2D6, DC2D8, DCC2D4, DCC2D4D, DCAX3, DCAX4, DCAX6, DCAX8,DCCAX4, or DCCAX4D elements (depending on the selected options and topologies) with ∗ SOLID SECTION properties. The thickness value on the ∗ SOLID SECTION option is included. An ∗ ORIENTATION option may also be created, as required.


Thermal 2D 2D Solid PlanarAxisymmetric

Standard FormulationConvection/DiffusionConvection/Diffusion w/Dispersion Control

Tri/3, Quad/4, Quad/8Quad/4Quad/4



Defines the uniform thickness of the elements. This is the thickness value on the ∗ SOLID SECTION option. This can be either a real constant or a reference to an existing field definition. If a field is referenced, it will be evaluated at the centroid of each element.

Input Properties

Thermal Planar SolidProperty Name Value Value Type

OK

Material Name

[ Thickness ]

Mat Prop Name

Real Scalar



Integer[ Orientation Axis ]

2CHAPTER

Thermal Preference (Planar)

Options above create DINTER2, DINTER3, DINTER2A, or DINTER3A elements (depending on the selected option and topology) with *INTERFACE properties. These elements must be created from one contact surface to the other. *GAP CONDUCTANCE and ∗ GAP RADIATION options are created, as required.


Thermal 2D 2D Interface PlanarAxisymmetric

Quad/4, Quad/8

Defines the uniform thickness of the interface. This value is the thickness property on the ∗ INTERFACE option. This value can be either a real constant or a reference to an existing field definition. If a field is referenced, it will be evaluated at the centroid of each element.


Defines the constants of the radiation behavior across the interface. These properties define the , , and values used on the ∗ GAP RADIATION option.

FA FB θ0

Input Properties

Thermal Interface (Planar)Property Name Value Value Type

OK

[ Thickness ]

[ Gap Clearance ]

Real Scalar

Real List


[ Gap Pressure ]

Real List

Real List

[ Average Temperature ]

[ Rad Constant Fa ]

Real List

Real Scalar

Field Definitions

[ Conductance vs Clear ] Real List



[ Average Mass Flow ] Real List

Thermal Solid

Options above create DC3D4, DC3D6, DC3D8, DC3D10, DC3D15, DC3D20, DCC3D8, or DCC3D8D (depending on the selected options and topologies) elements with *SOLID SECTION properties. An *ORIENTATION option may also be created, as required.

Analysis Type Dimension Type Option 1 Topologies

Thermal 3D Solid Standard FormulationConvection/DiffusionConvection/Diffusion w/ Dispersion Control

Tet/4, Tet/10, Wedge/6, Wedge/15, Hex/8, Hex/20Hex/8



Input Properties

Thermal Solid


OK






2CHAPTER

Thermal Preference (Solid)

Options above create DINTER4 or DINTER8 elements (depending on the selected) with *INTERFACE properties. These elements must be created from one contact surface to the other. *GAP CONDUCTANCE and ∗ GAP RADIATION options are also created, as required.


Thermal 3D 3D Interface Hex/8, Hex/20


Defines the constants of the radiation behavior across the interface. These properties define the , , and

values used on the ∗ GAP RADIATION option.

FA FBθ0

Input Properties

Thermal Interface (Solid)Property Name Value Value Type

OK

[ Gap Clearance ] Real List


[ Gap Pressure ]

Real List

Real List

[ Average Temperature ]

[ Rad Constant Fa ]

Real List

Real Scalar

Field Definitions

[ Conductance vs Clear ] Real List



[ Average Mass Flow ] Real List

Solid Gasket

These options create GK3D8 or GK3D6 elements depending on the element topology. The *GASKET SECTION option is used to define the gasket thickness, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to define the transverse shear behavior.


Structural 3D Gasket Gasket Behavior Model

Wedge6, Hex8



3CHAPTER













3CHAPTER

Solid Gasket (Thick only)

These options create GK3D8N or GK3D6N elements depending on the element topology. The *GASKET SECTION option is used to define the gasket thickness, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction.


Structural 3D Gasket Thickness Behavior Only

Wedge6, Hex8










3CHAPTER

Solid Gasket (Material)

These options create GK3D8 or GK3D6 elements depending on the element topology. The *GASKET SECTION option is used to define the gasket thickness, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to define the transverse shear behavior.


Structural 3D Gasket Built-in Material Wedge6, Hex8









3CHAPTER

2.6 Loads and Boundary ConditionsWhen choosing the Loads/BCs toggle, the Loads and Boundary Conditions form will appear. The selections made will determine which loads and boundary form is presented, and ultimately, which ABAQUS loads and boundaries will be created.

The following pages give an introduction to the Loads and Boundary Conditions form, followed by the details of all the loads and boundary conditions supported by the MSC.Patran ABAQUS Application Preference.

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Loads & Boundary Conditions FormThe Loads & Boundary Conditions form shown below provides the following options for the purpose of creating ABAQUS loads and boundaries. The full functionality of the form is defined in Loads and Boundary Conditions Form (p. 18) in the MSC.Patran Reference Manual, Part 5: Functional Assignments.

Select the general type of load to be applied. Applicable loads for MSC.Patran ABAQUS are described Structural (p. 309) and Thermal (p. 309).

Defines the target element type to which this load will be applied. This only appears if the type is Element Uniform or Element Varying. This can be 0D, 1D, 2D, or 3D.

Generates either a Static (p. 310) or Transient (p. 311) Input Data form, depending on the current Load Case Type.

Defines the general type of load to be applied. When the Analysis Type is set to Structural, the available selections are Displacement, Force, Pressure, Temperature, Inertial Load, Initial Displacement, Initial Velocity, Velocity or Acceleration. If the Analysis Type is Thermal, this can be set to Temp (Thermal), Convection, Heat Flux, Heat Source, or Initial Temperature.

Load & Boundary Conditions

CreateAction:

DisplacementObject:

Type:

Default

Type: Static

Current Load Case:

Existing Sets

New Set Name

Input Data...

Select Application Region...

-Apply-

Nodal

StructuralAnalysis Type

2DTarget Element Type:

Defines the geometric or finite element entities to which the loads/boundary condition will be applied.

Defines what type of region is to be loaded. The available options here depends on the selected Object. The general selections can be Nodal, Element Uniform, or Element Varying. Nodal is applied explicitly to nodes. Element Uniform defines a constant value to be applied over an entire element, element face, or element edge. Element Varying defines a value which varies across an entire element, element face, or element edge.

3CHAPTER

The following table shows the allowable selections for all options when the Analysis Type is set to Structural.

The following table shows the allowable selections for all options when the Analysis Code is set to Thermal.

Analysis Type Object Type

Structural ❏ Displacement Nodal

❏ Force Nodal

❏ Pressure Element Uniform

❏ Temperature NodalElement UniformElement Variable

❏ Inertial Load Element Uniform

❏ Initial Velocity Nodal

❏ Velocity Nodal

❏ Acceleration Nodal

❏ Contact (Deform-Deform) Element Uniform

❏ Contact (Rigid-Deform) Element Uniform

❏ Pre-Tension Element Uniform

Analysis Type Object Type

Thermal ❏ Temperature (Thermal) Nodal

❏ Convection Element Uniform

❏ Heat Flux Element Uniform

❏ Heat Source NodalElement Uniform

❏ Initial Temperature Nodal

Input Data

Clicking on the Input Data button generates either a Static or Transient Input Data form, depending on the current Load Case Type.

Static

This subordinate form appears whenever Load Case Type is set to Static and the Input Data button is clicked. The information contained on this form will vary according to the Object that has been selected. Information that remains standard to this form is defined below.

Defines a general scaling factor for all values defined on this form.The default value is 1.0. This is primarily intended for use when field definitions are used to define the load values.

Input Data in this section will vary. See Object Tables (p. 312) for more detailed information.

When specifying real values in the Input Data entries, spatial fields can be referenced. This area lists all defined spatial fields currently in the database. If the input focus is placed in the Input Data entry, and then a spatial field is selected by double clicking in this list, a reference to that field will be entered in the Input Data entry.

Defines the coordinate frame to be used to interpret the degree-of-freedom data defined on this form. This only appears on the form for Nodal type loads. This can be a reference to any existing coordinate frame definition.

Input Data

1

Load/BC Set Scale Factor

Spatial Fields

Coord 0


OK Reset

Translations (T1, T2, T3)

Rotations (R1, R2, R3)

FEM Dependent Data...

This button will display a Discrete FEM Fields input form to allow field creation and modification within the loads/bcs application. Visible only when focus is set in a databox which can have a DFEM field reference.

3CHAPTER

Transient

This subordinate form appears whenever Load Case Type is set to Transient and the Input Data button is clicked. The information contained on this form will vary according to the Object that has been selected. Information that remains standard to this form is defined below.

Input Data

1

Load/BC Set Scale Factor

Spatial Dependence * Time Dependence

Spatial Fields Time Dependent Fields

Coord 0


OK Reset

Trans Accel (A1,A2,A3)

Rot Velocity (w1,w2,w3)

Defines a general scaling factor for all values defined on this form.The default value is 1.0. This is primarily intended for use when field definitions are used to define the load values.

When specifying time dependent values in the Input Data entries, time dependent fields can be referenced. This area lists all defined time dependent fields currently in the database. If the input focus is placed in the Input Data entry, and then a time dependent field is selected by double clicking in this list, a reference to that field will be entered in the Input Data entry.

Defines the coordinate frame to be used to interpret the degree-of-freedom data defined on this form. This only appears on the form for Nodal type loads. This can be a reference to any existing coordinate frame definition.

Input Data in this section will vary. See Object Tables (p. 312) for more detailed information.

When specifying real values in the Input Data entries, spatial fields can be referenced. This area lists all defined spatial fields currently in the database. If the input focus is placed in the Input Data entry, and then a spatial field is selected by double clicking in this list, a reference to that field will be entered in the Input Data entry.

FEM Dependent Data...

This button will display a Discrete FEM Fields input form to allow field creation and modification within the loads/bcs application. Visible only when focus is set in a databox which can have a DFEM field reference.

Object Tables

On the static and transient input data forms are areas where the load data values are defined. The data fields presented depend on the selected load Object and Type. In some cases, the data fields also depend on the selected Target Element Type. These Object Tables list and define the various input data that pertains strictly to a specific selected object:

Displacement

Creates *BOUNDARY TYPE=DISPLACEMENT options.

Force

Creates *CLOAD options.

Object Type Type

Displacement Nodal Structural

Input Data Description

Translations (T1,T2,T3) Defines the enforced translational displacement values. These are in model length units.

Rotations (R1,R2,R3) Defines the enforced rotational displacement values. These are in radians.

Object Type Type

Force Nodal Structural


Force (F1,F2,F3) Defines the applied forces in the translation degrees-of-freedom.

Moment (M1,M2,M3) Defines the applied moments in the rotational degrees-of-freedom.

3CHAPTER

Pressure

Creates *DLOAD options.

Creates *DLOAD options.

Temperature

Creates *TEMPERATURE options.

Object Type Type Dimension

Pressure Element Uniform Structural 2D


Top Surf Pressure Defines the magnitude of the pressure in the direction of the negative normal to the shell.

Bot Surf Pressure Defines the magnitude of the pressure in the direction of the positive normal to the shell.

Edge Pressure Defines the edge pressure value on axisymmetric, plane strain,and plane stress elements.


Pressure Element Uniform Structural 3D


Pressure Defines the face pressure value on solid elements.

Object Type Type

Temperature Nodal Structural


Temperature Defines the nodal temperature value.




Temperature Element Uniform Structural 1D2D3D


Temperature Defines the temperature on elements.


Temperature Element Variable Structural 1D2D3D


Centroid Temp (1D) Defines the temperature at the centroid of the beam.

Axis-1 Gradient (1D) Defines the temperature gradient along the axis-1 of the beam section.

Axis-2 Gradient (1D)S Defines the temperature gradient along the axis-2 of the beam section.

Top Surf Temp (2D) Defines the temperature at the top of the shell element.

Bot Surf Temp (2D) Defines the temperature at the bottom of the shell element.

Temperature (3D) Defines the temperature in the solid element.

3CHAPTER

Inertial Load

Creates *DLOAD options with the load type set to GRAV, CENT, or CORIO as appropriate.

Initial Velocity

Creates *INITIAL CONDITIONS TYPE=VELOCITY options.

Object Type Type

Inertial Load Element Uniform Structural


Trans Accel (A1,A2,A3) Defines the magnitude and direction of the gravity vector. This must be assigned to all elements which are to have gravity loads.

Rot Velocity (w1,w2,w3) Defines the centrifugal and Coriolis forces to be applied to the elements.

Rot Accel (a1,a2,a3) These load terms are not currently supported by MSC.Patran ABAQUS.

Object Type Type

Initial Velocity Nodal Structural


Trans Veloc (v1,v2,v3) Defines the initial velocity values for the translational degrees-of-freedom.

Rot Veloc (w1,w2,w3) Defines the initial velocity values for the rotational degrees-of-freedom.

Velocity

Creates *Boundary, Type=Velocity options.

Acceleration

Creates *Boundary, Type=Acceleration options.

Object Type Type

Velocity Nodal Structural


Trans Veloc (v1,v2,v3) Defines the velocity values for the translational degrees-of-freedom.

Rot Veloc (w1, w2, w3) Defines the velocity values for the rotational degrees-of-freedom.

Object Type Type

Acceleration Nodal Structural


Trans Accel (A1, A2, A3) Defines the acceleration values for the translational degrees-of-freedom.

Rot Accel (a1, a2, a3) Defines the acceleration values for the rotational degrees-of-freedom.

3CHAPTER

Contact (Deform-Deform)

Defines the contact between two deformable structural bodies and creates the following ABAQUS input cards:

*Surface Definition: Master and Slave surface definitions.

*Contact Pair: Pairing of the Master and Slave Surfaces.

*Tie: Tying of the Master and Slave Surfaces (version 6 and greater).

*Surface Interaction: Contact Interaction properties between Master and Slave.

*Contact Controls: Set the Automatic Tolerances parameter

*Contact Inerference: Set the Shrink parameter

Defines the Master and Slave surface interaction properties.

Object Type Type

Contact Element Uniform Structural

Options are: General, Tied.

Options are: Large, Small.

Options are: Hard, Softened, Modified, Softened, No Separation.

Options are: Penalty, Lagrange, No Slip.

Options are: Off, On.

Options are: One Sided, Symmetric.

The contact interaction properties data depending on the options set above.

Options are: Off, On


Input Data

Contact Type: General

Sliding Type: Large

Friction Coefficient (MU)

OK Reset

Surface Behavior: Hard

Viscous Damping: Off

Friction Formulation: Penalty

Contact Control Off

Shrink Fit Off

Shear Stress Limit

0.1

1000.0

Penatration Type: One Sided

The contact type can be General (contacting surfaces move relative to each other) or Tied (contacting surfaces remain fixed with respect to each other usually used in mesh refinement). The sliding between the contacting surfaces can be Large or Small. For contact in 3D space the sliding is limited to Small sliding. Four types of contact surface behavior options are available, Hard, Softened, Modified Softened, and No Separation. The surfaces do not separate after contact in the case when No Separation option is used. Three types of friction formulations are available, Penalty, Lagrange, and No Slip. In the case of No Slip option there is no relative motion between the contacting surfaces after contact. The Penetration Type can be One Sided (Only the slave nodes are checked against the master surface) or Symmetric (Both the slave and master nodes are checked against each other by swapping the master and slave surfaces). The Contact Control can be turned On to activate the *Contact Control, Automatic Tolerances parameter. Use this parameter to have ABAQUS automatically compute an overclosure tolerance and a separation pressure tolerance to prevent chattering in contact. Shrink Fit can be turned On to activate the *Contact Interference, Shrink parameter. Use this parameter to invoke the automatic shrink fit capability. This capability can be used only in the first step of an analysis. When this parameter is invoked, no data are required other than the contact pairs to which the option is applied.

The application region form is used to pick the master and slave surfaces.

Application Region: Defines the Master and Slave contacting surfaces.

Application Region

Geometry FilterGeometryFEM

Master Surface:Shell Surface

Slave Surface: Solid Face

Active Region: Master

Select Surface Edges

Add Remove

Master Region

Surface 1

Slave Region

Solid 1.4

OK Clear

Reverse Normal

Filter for picking Geometric entities or FEM entities.

Options are: Solid Face, Shell Surface, 2D solid Edge.

Options are: Solid Face, Shell Surface, 2D Solid Edge, 2D beam, Node.

Options are: Master, Slave.

Reverses the normal of Shell Surface if not pointing towards the slave surface.

Entity select databox which is active for the active region being master of slave.

Master and slave application regions.

Clears the active region text widgets.

◆

◆◆

3CHAPTER

Contact (Rigid-Deform)

Defines the contact between the rigid surface and deformable structural body and creates the following ABAQUS input cards:

*Surface Definition: Master and Slave surface definitions.

*Contact Pair: Pairing of the Master and Slave Surfaces.

*Surface Interaction: Contact Interaction properties between Master and Slave.

*Contact Controls: Set the Automatic Tolerances parameter

*Contact Inerference: Set the Shrink parameter

Defines the Master and Slave surface interaction properties.

Object Type Type

Contact Element Uniform Structural

Options are: Large, Small.

Options are: Hard, Softened, Modified Softened, No Separation.

Options are: Penalty, Lagrange, No Slip.

Options are: Off, On.

The contact interaction properties data depending on the options set above.

Defines the contact direction from master to slave which is used to find the rigid bars order.

The reference node associated with the rigid elements to which the loads and BCs are applied.



Input Data

Contact Type: Rigid Elements

Sliding Type: Large

Friction Coefficient (MU)

OK Reset

Surface Behavior: Hard

Viscous Damping: Off

Friction Formulation: Penalty

Contact Control Off

Shrink Fit Off

Shear Stress Limit

Out of Plane Width

Vector Pointing from Master to Slave Surface

Reference Node

0.1

1000.0

1.0

<0., 0.050000001, 0.>

Node 7

The sliding between the contacting surfaces can be Large or Small. Four types of contact surface behavior options are available, Hard, Softened, Modified Softened, and No Separation. The surfaces do not separate after contact in the case when No Separation option is used. Three types of friction formulations are available, Penalty, Lagrange, and No Slip. In the case of No Slip option there is no relative motion between the contacting surfaces after contact. The Contact Control can be turned On to activate the *Contact Control, Automatic Tolerances parameter. Use this parameter to have ABAQUS automatically compute an overclosure tolerance and a separation pressure tolerance to prevent chattering in contact. Shrink Fit can be turned On to activate the *Contact Interference, Shrink parameter. Use this parameter to invoke the automatic shrink fit capability. This capability can be used only in the first step of an analysis. When this parameter is invoked, no data are required other than the contact pairs to which the option is applied. A vector pointing from the rigid line to the slave surface must be defined. This vector is used to calculate the order of rigid bar elements. The vector should be defined such that the most of the vector markers point away from the rigid line.

The application region form is used to pick the master and slave surfaces.

Application Region: Defines the Master and Slave contacting surfaces.

Application Region

Geometry FilterGeometryFEM

Master Surface:Rigid Surface

Slave Surface: Solid Face


Select Surface Edges

Add Remove

Master Region

Surface 1

Slave Region

Solid 1.4

OK Clear

Filter for picking Geometric entities or FEM entities.

Options are: Rigid Surface, Rigid Line.



Entity select databox which is active for the active region being master of slave.



◆

◆◆

Rigid Elem’sContact Type:

Reverse Contact Direction

Options are: Rigid Elem’s, Rigid Geom.Rigid Elem’s uses mesh or meshed geometry to define rigid contact master region. Rigid Geom. uses geometry directly, without using elements, to define rigid contact master region.

Toggle to change contact direction for 3D. For 2D use Vector on Input Data... form.

3CHAPTER

Application Region: Defines the Master and Slave contacting surfaces. This form appears when Contact Type: is Rigid Geom. and Master: is Rigid Surface .

Application Region

Contact Type: Rigid Geom.

Geometry Filter

Geometry

Master: Rigid Surface

Slave: Shell Surface


Reverse Contact Direction

Type: Revolution of Line

Axis of Revolution

Select Origin

[ 0.5 0.5 0.1 ]

Select Orientation

<0., 0., 0.5>

Select Generating Curves

Add Remove

Master Generating Curves

Curve 1 2

Slave Region

Surface 1

OK Clear

Only geometry may be used to define rigid geometry.

Options are: Rigid Surface, Rigid Line.



Options are Revolution of Line, Extrusion of Line.



Options are: Rigid Elem’s, Rigid Geom.Rigid Elem’s uses mesh or meshed geometry to define rigid contact master region. Rigid Geom. uses geometry directly, without using elements, to define rigid contact master region.

Toggle to change contact direction for 3D. For 2D use Vector on Input Data... form.

Entity select databox to select curves for revolution or extrusion.

Define the axis of revolution by a point on the axis (Origin) and it direction (Orientation), or define extrusion direction as a vector. Revolutions are always 360 degrees. Extrusion extend to infinity in both directions along the extrusion direction.

Pre-tension

Creates *BOUNDARY and *PRE-TENSION SECTION options.

Creates *BOUNDARY, *SURFACE and *PRE-TENSION SECTION options.

Creates *CLOAD and *PRE-TENSION SECTION options.

Creates *CLOAD, *SURFACE and *PRE-TENSION SECTION options.

Object Type Option Type Dimension

Pre-tension Element Uniform Displacement Structural 1D


Relative Displacement Defines the relative displacement to apply to the length of the elements.


Pre-tension Element Uniform Displacement Structural 2D, 3D


Relative Displacement Defines the relative displacement to apply to the underlying elements in the direction of the section's normal.


Pre-tension Element Uniform Force Structural 1D


Force Defines the pre-tension force to apply to the elements.


Pre-tension Element Uniform Force Structural 2D, 3D


Force Defines the pre-tension force to apply to the underlying elements in the direction of the section's normal.

3CHAPTER

Temperature (Thermal)

Creates *BOUNDARY options.

Convection

Creates *FILM options.

Creates *FILM options.

Object Type Type

Temp (Thermal) Nodal Thermal


Temperature Defines the nodal temperature value.


Convection Element Uniform Thermal 2D


Top Surf Convection Defines the convection coefficient for the top surface of a shell element.

Bot Surf Convection Defines the convection coefficient for the bottom surface of a shell element.

Edge Convection Defines the convection coefficient for the edges of axisymmetric, plane strain, and plane stress type elements.

Ambient Temp Defines the ambient temperature.


Convection Element Uniform Thermal 3D


Convection Defines the convection coefficient for the face of a solid element.

Ambient Temp Defines the ambient temperature.

Heat Flux

Creates *DFLUX options.


Heat Source

Creates *CFLUX options.


Heat Flux Element Uniform Thermal 2D


Top Surf Heat Flux Defines the heat flux for the top surface of a shell element.

Bot Surf Heat Flux Defines the heat flux for the bottom surface of a shell element.

Edge Heat Flux Defines the heat flux for the edges of axisymmetric, plane strain, and plane stress type elements.


Heat Flux Element Uniform Thermal 3D


Heat Flux Defines the heat flux for the face of a solid element.

Object Type Type

Heat Source Nodal Thermal


Heat Source Defines the reference magnitude for flux (units ).

Object Type Type

Heat Source Element Uniform Thermal

JT 1–

3CHAPTER


Initial Temperature

Creates *INITIAL CONDITIONS TYPE=TEMPERATURE options.


Heat Source Defines the reference magnitude for flux (units ).

Object Type Type

Initial Temperature Nodal Thermal


Temperature Defines the initial temperature for a specified node.

JT 1–

2.7 Load CasesLoad Cases in MSC.Patran ABAQUS are used to group a series of Load sets into one load environment for the model. A load case is selected when preparing an analysis, not load sets. The individual load sets are translated into the input options described in the Object Tables of the section on Loads and Boundary Conditions form.

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3CHAPTER

2.8 GroupGroups in MSC.Patran ABAQUS are used to create groups of nodes (*NSET) and groups of elements (*ELSET). All the groups created in MSC.Patran will be translated as *NSETs and *ELSETs except for the “default_group” which always exists in the database, and group names which do not begin with an alphabetic character (a-z, A-Z).d

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MSC.Patran ABAQUS Preference Guide^

CHAPTER

3 Running an Analysis

■ Review of the Analysis Form

■ Translation Parameters

■ Restart Parameters

■ Optional Controls

■ Direct Text Input

■ Step Creation

■ Step Selection

■ Read Input File

■ ABAQUS Input File Reader

3.1 Review of the Analysis FormThe Analysis toggle located on the main form for MSC.Patran brings up The Analysis Form (p. 8) in the MSC.Patran Reference Manual, Part 5: Analysis Application. This form is used to request an analysis of the model with the ABAQUS finite element program. It can also be used to incorporate the contents of an ABAQUS results file into the database. See Read Results (Ch. 4).

The following page gives an introduction to the Analysis form used to prepare an ABAQUS analysis. This is followed by detailed descriptions of the subordinate forms that can be displayed from the Analysis form.

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3CHAPTER 3Running an Analysis

Analysis FormSetting the Action option menu on the Analysis Form to Analyze indicates that an analysis run is being prepared.

The Object indicates which part of the model is to be analyzed. It can be set to either Entire Model or Current Group. If the whole model is to be analyzed, select Entire Model. If only a part of the model is to be analyzed, create a group of that part, set that as the current group, then select Current Group as the Object.

The Method indicates how far the translation is to be taken. Currently only Analysis Deck is supported. The method generates an ABAQUS input deck.

Analysis

AnalyzeAction:

Code:

Entire ModelObject:

Full RunMethod:

Jobname

Restart Parameters...

Optional Controls...

Step Creation...

Step Selection...

Apply

Defines the name to be used for all parameters and files associated with this analysis. This is also used to associate the analysis results to their corresponding load case.

Indicates the selected Analysis Code and Analysis Type, as defined in the Preferences>Analysis (p. 343) in the MSC.Patran Reference Manual, Part 1: Basic Functions.

Indicates how much of the model is to be included in the analysis. This can be set to Entire Model or Current Group.

ABAQUS

Type: Structural

Available Jobs

Job Description

Lists all previously created ABAQUS jobs. Selecting a jobname from this box causes the name to appear in the Jobname box and the parameters associated with this job to appear on the lower level forms.

Translation Parameters...

Analysis Manager...

Direct Text Input...

3.2 Translation ParametersThis subordinate form appears whenever the Translation Parameters button is selected. The parameters controlling the translation of the ABAQUS input deck are defined on this form.

Note: The spatially varying field property values are compared within the band of +half of field properties tolerance and -half of field properties tolerance to group the elements. The property values for this group of elements are added and divided by the number of elements in this group to get the average property value to be used.

Translation Parameters

0Model Translation Tol. =

0Field Properties Tol. =

Tolerances:

Apply Defaults Cancel

Defines the tolerance that is used to group elements with spatially varying field property values that fall within this tolerance. This tolerance is applied to all the field dependent properties.

Defines the zero tolerance to be used in setting the x,y,z coordinates of nodes to zero.


3.3 Restart ParametersThis subordinate form appears whenever the Restart Parameters button is selected. This form creates a *RESTART option (see Section 7.10.1 of the ABAQUS/Standard User’s Manual).

Set Restart Parameters

NoneRestart Type:

Restart Job Name =

Restart From Step =

Restart Parameters:

CancelDefaultsApply

Restart From Increment =

Increments between Writing Data =

Indicates the type of restart data to be defined. This can be set to “None”, “Read”, “Write”, or “Read and Write.” This indicates which of the WRITE and/or READ parameters should be included.

Indicates the step and then the increment of that step at which the restart is to be made. These are integer constants. These are only used when Reading restart data. On the *RESTART option, these define the STEP and INC parameters, respectively.

Defines the jobname of the run to be read in the restart. This is only used when Reading restart data.

Indicates that only the final increment of any step is to be written to the restart file. This is only used when writing restart data. This corresponds to the OVERLAY parameter on the ∗ RESTART option.

Defines how often restart data is written to the restart file. This is not used when the “Write Last Increment Only” button is selected. This is only used when writing restart data. This defines the FREQUENCY parameter on the *RESTART option.

End Current Step:

Write Last Increment:

On/Off

On/Off

Used to terminate the current step at the time of restart, regardless of the step end time definition. Thus, the current step is considered completed even though all of the loading may not have been applied. Continuation of the analysis will be defined by history data provided with the restart run.

3.4 Optional ControlsThis subordinate form appears whenever the Restart Parameters button is selected.

Used to specify the file format in which the ABAQUS results will be written. It can be set to either binary or ASCII.

Defines the equation solver to be used for the analysis. The SPARSE solver is the default. In general, it will reduce the computational time for sparse equation systems. Alternatively, the FRONTAL wavefront solver can be used and has no limitations.

Optional Controls

Optional Controls:

CancelDefaults

Abaqus Version:

Apply

Linear Equation Solver:

Nonsymm Stiff Matrix:

V5.X

FRONTAL

Not Included

Results File Format:

Model Printout:

Binary

ON

Wavefront Minimization: ON

Coord. Transformations (Results): OFF

Optional Controls

Optional Controls:

CancelDefaults

Abaqus Version:

Apply

Linear Equation Solver:

Nonsymm Stiff Matrix:

V5.X

SPARSE

Not Included

Results File Format:

Model Printout:

Binary

ON

Wavefront Minimization: ON

Coord. Transformations (Results): OFF

Defines the setting of the ∗ WAVEFRONT MINIMIZATION command. If OFF is selected, then the ∗ WAVEFRONT MINIMIZATION, SUPPRESS command will be included, to suppress the automatic optimization procedures used by ABAQUS. If this button is not selected, the default optimization settings will be used.

Enable postprocessing of sress/strain results in alternative coordinate systems when set to ON. (See Coordinate Systems (p. 305) in the MSC.Patran Reference Manual, Part 6: Results Postprocessing.)

Defines the UNSYMM parameter of the ∗ HEADING option. This button can be set to INCLUDED or NOT INCLUDED. Selecting INCLUDED forces ABAQUS to use its nonsymmetric matrix storage and solution scheme. The nonsymmetric capability is chosen automatically by some of the input options (e.g., ∗ STEADY STATE DYNAMIC). Other options (e.g., ∗ FRICTION) use the symmetric capability even though the theory includes some nonsymmetric terms; these terms will be included if this parameter is used. This may then reduce the number of iterations needed, but each iteration will be more expensive.

Absolute Zero Temperature:

Physical Constants

NONESpecify the absolute zero on the temperature scale chosen (Celsius, Kelvin, Fahrenheit, or Rankine). Used for analyses that require this physical constant to be defined.


3.5 Direct Text InputThis subordinate form appears whenever the Direct Text Input button is selected.

This widget is to facilitate the input of the ABAQUS input data that cannot be created using the functionality available in MSC.Patran. All data input here will be appended to the ABAQUS model data before the step history block.

Note: There is no checking available for invalid input.

Note: The font for the text input may vary from one system to another. A default font is specified in app_defaults/Patran file:

Patran*fixedFont: -misc-fixed-bold-r-normal--13-100-100-100-c-70-iso8859-1

For any problems with the text on a particular system, change the font specifications in the MSC.Patran file which should reside in your ~home directory. Use xfontsel, or xlxfonts commands to get the list of available fonts on a given system.

Additional Model Definition

Additional Model Section Input:

Apply Clear Cancel

3.6 Step CreationThis subordinate form appears whenever the Step Creation button is selected on the Analysis form. A step is defined by associating the load cases created and stored on the database, with the ABAQUS analysis procedure that best addresses that load case, and the relevant associated parameters that guide the solution path for the chosen analysis procedure. There is no importance to the order in which the Job Steps are created on this form--they will be ordered for the job in the Step Selection form.

Step Create

Available Job Steps:

Apply Defaults Cancel

Default Static Step

Job Step Description

Default Static Step

Job Step Name

Job Step Parameters

Solution Type:Linear Static

Solution Parameters...

Select Load Cases...

Output Requests...

Defines the Solution Type associated with the step.

Each ABAQUS job consists of one or more steps. These steps are listed here. ∗ STEP and ∗ END STEP options are generated for the selected job step.

To edit the Job Step Parameters, select the step name from the Available Job Steps listed at the top of this form or type its name in the Job Step Name databox. If the name does not exist, a new step will be created.

Brings up a subordinate form for definition of parameters associated with the step.

Brings up a subordinate form to associate a load case with the step.

Brings up a subordinate form to define the results to be written to the results file during the step.

Direct Text Input...

Brings up the text form for inputting the ABAQUS input data not supported by MSC.Patran menus.


Select Load CasesThis subordinate form appears whenever the Select Load Cases button is selected on the Step Creation form.

Select Load Cases

Available Load Cases:

CancelDefaultsApply

Displays the list of all load cases currently defined in the database. The desired load case may be selected from this area. This selected load case is then highlighted. When Apply is selected, the Selected Load Case will then be associated with the Job Step Parameters for the step currently being defined on the Step Create form.

Default

Output RequestsThis subordinate form appears whenever the Output Requests button is selected on the Step Create form. It is used for specifying the specific variables to be included in the output from ABAQUS options such as: ∗ EL PRINT, ∗ ENERGY PRINT, ∗ MODAL PRINT, ∗ NODE PRINT, ∗ PRINT, ∗ EL FILE, ∗ ENERGY FILE, ∗ FILE FORMAT, ∗ MODAL FILE, and ∗ NODE FILE *ELEMENT MATRIX OUTPUT. An explanation of the output variables that can be requested is included in the Output Requests description for each solution type.

Output Requests

OK Defaults Cancel

Static Output Requests:

Increments between Outputs =

1

Output Variable

Integ Point

Option

None

Integ Point

None

None

None

None

None

On

Off

Off

Off

Stress Components:

Stress Invariants:

Strain Components:

Elem Energy Densitites:

Elem Energy Magnitudes:

Internal Stress Forces:

Section Forces:

Section Strains:

Displacements:

Reaction Forces:

Point Forces:

Whole Model Energies:

Determines the output frequency in increments. The output will be written to the data and results files at the last increment of each step, regardless of this value.


Direct Text InputThis subordinate form appears whenever the Direct Text Input button is selected.

This widget is to facilitate the input of the ABAQUS input data that cannot be created using the functionality available in MSC.Patran menus. All data input here will be appended to the ABAQUS step history being created.

Note:There is no checking available for invalid data.

Note:The font for the text input may vary from one system to another. A default font is specified in app_defaults/Patran file:

Patran*fixedFont: -misc-fixed-bold-r-normal--13-100-100-100-c-70-iso8859-1

For any problems with the text on a particular system, change the font specifications in the MSC.Patran file which should reside in your ~home directory. Use xfontsel, or xlxfonts commands to get the list of available fonts on a given system.

Additional History Definition

Additional History Section Input:

Apply Clear Cancel

Solution TypesEach step has an associated Solution type, and the information that is requested on the Solution Parameters and Output Requests forms varies based on this selection. ABAQUS calls these analysis procedures, and the full explanations of these procedures can be found in Chapter 2 “Procedures Library” of the ABAQUS/Standard User’s Manual.

Parameter Type Description

Linear Static Static stress analysis is used when inertia effects can be neglected. During a linear static step, the model’s response is defined by the linear elastic stiffness at the base state, the state of deformation and stress at the beginning of the step. For ∗ HYPERELASTIC and ∗ HYPERFOAM materials, the tangent elastic moduli in the base state is used. Contact conditions cannot change during the step--they remain as they are defined in the base state.

Natural Frequency This solution type uses eigenvalue techniques to extract the frequencies of the current system. The stiffness determined at the end of the previous step is used as the basis for the extraction, so that small vibrations of a preloaded structure can be modeled.

Bifurcation Buckling Eigenvalue buckling estimates are obtained. Classical eigenvalue buckling analysis (e.g., “Euler” buckling) is often used to estimate the critical (buckling) load of “stiff” structures. “Stiff” structures are those that carry their design loads primarily by axial or membrane action, rather than by bending action. Their response usually involves very little deformation prior to buckling.

Direct Linear Transient This solution procedure integrates all of the equations of motion through time, and is significantly more expensive than modal methods for finding dynamic response for linear systems. For linear systems, the dynamic method, using the Hilber-Hughes-Taylor operator, is unconditionally stable, meaning there is no mathematical limit on the size of the time increment that can be used to integrate a linear system. Since the procedure uses a fixed time increment, the HAFTOL parameter on the *DYNAMIC card is not required.

Direct Steady State Dynamics

Calculates steady state response for the given range of frequencies. The damping may be created by dashpots, by “Rayleigh” damping associated with materials, and by viscoelasticity included in the material definitions.

Modal Linear Transient This solution type gives the response of the model as a function of time, based on a given time dependent loading. The procedure is based on using a subset of the eigenmodes of the system, which must first be extracted using the NATURAL FREQUENCY solution type.The number of modes extracted must be sufficient to model the dynamic response of the system adequately. This is a matter of judgment on the part of the user. The modal amplitudes are integrated through time and the response synthesized from these modal responses.


Modal Steady State Dynamics

This solution type provides the response of the system when it is excited by harmonic loading at a given frequency. This procedure is usually preceded by extraction of the natural modes using the NATURAL FREQUENCY solution type, although ABAQUS also allows the response to be calculated directly from the system matrices for use in those cases where the eigenvalues cannot be extracted, such as a nonsymmetric stiffness case, or models in which the behavior is itself a function of frequency, such as frequency dependent material damping.

Response Spectrum This solution type provides an estimate of the peak response of a structure to steady-state dynamic motion of its fixed points (“base motion”). The method is typically used when an approximate estimate of such peak response is required for design purposes. The procedure is based on using a subset of the eigenmodes of the system, which must first be extracted using the NATURAL FREQUENCY solution type.

Random Vibration This solution type predicts the response of a system which is subjected to a nondeterministic continuous excitation that is expressed in a statistical sense using a power spectral density function. The procedure is based on using a subset of the eigenmodes of the system, which must first be extracted using the NATURAL FREQUENCY solution type.

Nonlinear Static Nonlinear static analysis requires the solution of nonlinear equilibrium equations, for which ABAQUS uses Newton’s method. Many problems involve history dependent response, so that the solution is usually obtained as a series of increments, with iteration within each increment to obtain equilibrium. For most cases, the automatic incrementation provided by ABAQUS is preferred, although direct user control is also provided for those cases where the user has experience with a particular problem.


Nonlinear Transient Dynamic

This solution type is used when nonlinear dynamic response is being studied. Because all of the equations of motion of the system must be integrated through time, direct integration methods are generally significantly more expensive than modal methods. For most cases, the automatic incrementation provided by ABAQUS is preferred, although direct user control is also provided for those cases where the user has experience with a particular problem.

Creep This analysis procedure performs a transient, static, stress⁄ displacement analysis. It is especially provided for the analysis of materials which are described by the ∗ CREEP material form.

Viscoelastic (Time Domain)

This is especially provided for the time domain analysis of materials which are described by the ∗ VISCOELASTIC, TIME material option. The dissipative part of the material behavior is defined through a Prony series representation of the normalized shear and bulk relaxation moduli, either specified directly on the ∗ VISCOELASTIC, TIME material option, determined from user input creep test data, or determined from user input relaxation test data.

Viscoelastic (Frequency Domain)

This is especially provided for the frequency domain analysis of materials which are described by the ∗ VISCOELASTIC, FREQUENCY material option, which is activated by a ∗ STEADY STATE DYNAMICS, DIRECT procedure.The dissipative part of the material behavior is defined by the real and imaginary parts of the Fourier transforms of the nondimensional shear viscoelasticity parameter g and, for compressible materials, of the bulk viscoelasticity parameter k.

Steady State Heat Transfer

This solution type is for pure heat transfer problems for which the ∗ HEAT TRANSFER option is used and where the temperature field can be found without knowledge of stress and deformation of the bodies being studied.

Transient Heat Transfer This solution type is for pure transient heat transfer problems for which the ∗ HEAT TRANSFER option is used and where the temperature field can be found without knowledge of stress and deformation of the bodies being studied. For all transient heat transfer cases, the time increments may be specified directly, or will be selected automatically based on a user prescribed maximum nodal temperature change in a step. Automatic time incrementation is generally preferred.



Linear Static

Read Temperature File

This option is used to specify temperatures via the results file which has been generated from a previous heat transfer analysis. Only one temperature results file is allowed in an analysis but the same file can be referenced by many steps.

Solution Parameters


OK Defaults Cancel

Temperature Results File Input

1Start Step Number =

1Start Increment Number =

1End Step Number =

1End Increment Number =

Temperature Read Selection Options:

Filter/main/*.fil

/main/users/.Directories Available Files

Selected Results File/main/*.fil

[ ]

CancelFilterOK

Defines the step and increment number at which the reading of temperatures ends.

Defines the step and increment number at which the reading of temperatures begins.

Results File Format: Binary

Linear Static

If the selected solution type is Linear Static then the following parameters may be defined on the Output Requests form.

Parameter Name DescriptionOutput Variable

Identifier

Stress Components

The stress components output depend on the elements analyzed. For example, the truss element outputs the axial stress (S11) only, while a three-dimensional solid element outputs all six components (S11, S22, S33, S12, S13, S23). Note that ABAQUS always reports the Cauchy, or true stress, which is equal to the force per current area. For more information about element output, see Chapter 3 of the ABAQUS/Standard User’s Manual.

S11, S22, S33, S12, S13, S23

Stress Invariants The stress invariants output by ABAQUS are the Mises stress, Tresca stress, Hydrostatic pressure, first principal stress, second principal stress, third principal stress, and the third stress invariant. These quantities are scalar quantities which do not vary with a change of coordinate system. For elastic analyses, the von Mises and/or the Tresca stress invariants can be monitored to ensure that the analysis remains within the assumptions of linearity.

SINV

Strain ComponentsThis is the total strain value for each component output. The strain components output depend on the elements analyzed, analogous to the stress components. Note that, for linear elastic analyses, the total strain is equal to the elastic strain.

E

Elem Energy Densities

The strain energy per unit volume of each element. Plastic, creep, and viscous dissipative energy densities should not be affected by linear static analysis.

ENER

Elem Energy Magnitudes

The strain energy of each element. Plastic, creep, and viscous dissipative energy densities should not be affected by linear static analysis.

ELEN

Internal Stress Forces

The forces that are found at each node by summing the element stress contributions at the nodes.

NFORC

Section Forces Section forces are output for beam elements and include the axial force, and, as applicable, the shears, bending moments and bimoment about the local axes. These are discussed in Section 3.5.1 and Section 7.5.2 of the ABAQUS/Standard User’s Manual.

For shell elements, the section forces include the direct membrane, shear, and moment forces per unit width, as applicable. These are discussed in Section 3.6 of the ABAQUS/Standard User’s Manual.

SF

Section Strains Section strains are output for beam elements and, as applicable, these include the axial strain, transverse shear strains, curvature changes, and twist about the local axes.These are discussed in Section 3.5.1 and Section 7.5.2 of the ABAQUS/Standard User’s Manual.

For shell elements, the section strains include the direct membrane, shear, curvature changes, and twist, as applicable. These are discussed in Section 3.6 of the ABAQUS/Standard User’s Manual.

SE


Shell Thickness Changes in thickness for shell elements (S3RF, S4RF,SAX1, SAX2, SAXA1N, SAXA2N).

STH

Displacements Displacements are output at nodes and are referred to as follows:

1. x-displacement

2. y-displacement

3. z-displacement

4. Rotation about the x-axis

5. Rotation about the y-axis

6. Rotation about the z-axis

Except for axisymmetric elements, where the displacement and rotation degrees-of-freedom are:

1. r-displacement

2. z-displacement

3. Rotation in the r-z plane

Here x, y, z, and r are global directions unless a coordinate transformation is used at the node. Note that the warping degree-of-freedom, the seventh displacement component of an open section beam element, is not supported by MSC.Patran at this time.

U

Reaction Forces The forces at the nodes which are constrained and therefore, resist changes in the system. The direction convention is the same as that for nodal output.

RF

Point Forces The forces at the nodes resulting from the imposed loads (e.g., the force at a node resulting from pressure distributions on adjacent elements).

CF

Whole Model Energies

The summation of all the energy of the model. The kinetic, recoverable (elastic) strain, plastic dissipation, creep dissipation, and viscous dissipation are reported.

ALLEN

Element Mass Matrix

Mass matrices output.

Element Stiffness Matrix

Stiffness matrices output.


Identifier

Natural Frequency

This subordinate form appears whenever the Solution Parameters button is selected and the solution types is Natural Frequency. This generates ∗ FREQUENCY procedures (see Section 9.3.5 of the ABAQUS/Standard User’s Manual). The optional NLGEOM parameter on the ∗ STEP option may be included, as defined below. None of the other optional parameters on the ∗ STEP option (AMPLITUDE, INC, or MONOTONIC) are used.

Defines the maximum frequency of interest, in cycles per time. This is a real value.

Defines the shift point in cycles squared per time. Eigenvalues closest to this point will be extracted. This is a real value, either positive or negative.

Solution Parameters

0

Max Frequency of Interest =

0

Shift Point (squared cycles/time) =

1

Number of Modes =

30

Number of Iterations =

Natural Frequency Solution Parameters:

OK Defaults Cancel

Defines the number of eigenvalues to be calculated. This is an integer value. ABAQUS will extract frequencies until either this value or the Maximum frequency of interest is reached.

Defines the maximum number of iterations to be used. This is an integer value.


,

Natural Frequency

If the selected Solution Type is Natural Frequency, then the following parameters may be defined on the Output Requests form. A complete discussion of the ABAQUS results file can be found in Chapter 6 of the ABAQUS/Standard User’s Manual. Note that the Natural Frequency solution type extracts the frequency and corresponding mode shapes (eigenvalues and eigenmodes), usually for use in a later analysis (e.g., Response Spectrum). The stresses and strains corresponding to the mode shapes can be output, but are usually of limited direct value except as a possible means for guiding mode limitations for future analyses.


Identifier

Stress Components The stress components output depend on the elements analyzed. For example, the truss element outputs the axial stress (S11) only, while a three-dimensional solid element outputs all six components (S11, S22, S33, S12, S13, S23). Note that ABAQUS always reports the Cauchy, or true stress, which is equal to the force per current area. For more information about element output, see Chapter 3 of the ABAQUS/Standard User’s Manual.

S11, S22, S33, S12S13, S23

Stress Invariants The stress invariants output by ABAQUS are the Mises stress, Tresca stress, Hydrostatic pressure, First principal stress, second principal stress, third principal stress, and the third stress invariant. These quantities are scalar quantities which do not vary with a change of coordinate system.

SINV

Strain Components This is the total strain value for each component output. The strain components output depend on the elements analyzed, analogous to the stress components. Note that, for linear elastic analyses, the total strain is equal to the elastic strain.

E



SF



SE


STH


1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U


RF

Element Mass Matrix Mass matrices output.




Identifier


Bifurcation Buckling

This subordinate form appears whenever the Solution Parameters button is selected and the Solution Type is Bifurcation Buckling. This form defines the data required for a *BUCKLE command (see Section 9.3.2 of the ABAQUS/Standard User’s Manual). This step may be included either as the first step or when the structure has already been preloaded. If the structure has been preloaded, the buckle sensitivity around the preloaded state is calculated. The problem is a classical eigenvalue problem, with the eigenvalues defined as the load multipliers of the load pattern for which buckling sensitivity is being investigated.

Solution Parameters

0

Max Eigenvalue of Interest =

30

Number of Eigenvalues Expected =

1

Number of Iterations =

Buckling Solution Parameters:

OK Defaults Cancel

ABAQUS will extract eigenvalues until either of these limits is reached.

Maximum number of iterations used in the subspace iteration scheme. The default is 30.

Bifurcation Buckling

If the selected Solution Type is Bifurcation Buckling then the following parameters may be defined on the Output Requests form.


Identifier


S11, S22, S33, S12, S13, S23


SINV


E



SF



SE


STH



1. x-displacement

2. y-displacement

3. z-displacement




except for axisymmetric elements, where the displacement and rotation degrees-of-freedom are:

1. r-displacement

2. z-displacement



U


RF





Identifier

Direct Linear Transient

This subordinate form appears whenever the Solution Parameters button is selected and the solution type is Direct Linear Transient. This generates a *DYNAMIC procedure, with the optional DIRECT parameter included (see Section 9.3.4 of the ABAQUS/Standard User’s Manual). Note that modal methods are usually more economical for linear dynamic analysis. Many of the parameters described in the ABAQUS/Standard User’s Manual for the *DYNAMIC option are not used for this option.

Defines the suggested time increment. This is a real constant.

Defines the total time period of the step. This is a real constant.

Solution Parameters

Direct Linear Solution Parameters

OK Defaults Cancel

0.1

1

Delta-T =

Time Duration of Step=

Read Temperature File Temperature Results file access for thermal check. There can be only one file referenced in a job.


Direct Linear Transient

If the selected Solution Type is Direct Linear Transient then the following parameters may be defined on this form.


Identifier


S11, S22, S33, S12, S13, S23


SINV

Strain Components This is the total strain value for each component output. The strain components output depend on the elements analyzed, analogous to the stress components. Note that for linear elastic analyses, the total strain is equal to the elastic strain.

E

Elem Energy Densities The strain energy per unit volume of each element. ENER


The strain energy of each element. ELEN

Internal Stress Forces The forces that are found at each node by summing the element stress contributions at the nodes.

NFORC



SF



SE


STH


1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U

Velocities Nodal velocities, following the same convention as for displacements.

V

Accelerations Nodal accelerations, following the same convention as for displacements.

A


RF


CF

Whole Model Energies The summation of all the energy of the model. The kinetic, recoverable (elastic) strain, plastic dissipation, creep dissipation, and viscous dissipation are reported.

ALLEN





Identifier



This subordinate form appears whenever the Solution Parameters button is selected and the solution type is Direct Steady State Dynamics. This generates a ∗ STEADY STATE DYNAMIC procedure.

Defines which type of frequency scale is to be used. This can be set to either “Logarithmic” or “Linear.” This defines a value on the ∗ STEADY STATE DYNAMICS option.

Solution Parameters

Direct Steady State Dyn Solution Parameters:

OK Defaults Cancel

Frequency Scale Choice: Logarithmic

Define Frequencies...


If the selected solution type is Direct Steady State Dynamics, then the following parameters may be defined on the Output Requests form.


Identifier


S11, S22, S33, S12, S13, S23


SINV

Ph Angle Stress Components

The phase angle shift of the stress components. PHS


E

Ph Angle Strain Components

The phase angle shift of the strain components. PHE



SF




SE


STH


1. x-displacement

2. y-displacement

3. z-displacement




except for axisymmetric elements, where the displacement and rotation degrees-of-freedom are:

1. r-displacement

2. z-displacement



U


V


A

Phase Angle Rel. Displacements

The phase angle shift of the relative displacement components.

PU


RF

Phase Angle Reaction Forces

The phase angle shift of the reaction force components. PRF


Identifier


CF


Element Stiffness Matrix Stiffness matrices output.


Identifier


Modal Linear Transient

This subordinate form appears whenever the Solution Parameters button is selected and the solution type is Modal Linear Transient. This generates a *FREQUENCY procedure (see Section 9.3.5 of the ABAQUS/Standard User’s Manual) followed by a ∗ MODAL DYNAMIC procedure (see Section 9.3.8 of the ABAQUS/Standard User’s Manual). A ∗ MODAL DAMPING option will also be generated, as required. Only one load case may be selected.

Defines the suggested time increment This is a real constant.


Solution Parameters

0.1

Modal Linear Solution Parameters:

OK Defaults Cancel

Time Duration of Step =

DELTA-T =

1

NoneModal Damping:

Previous StepStart From:

Define Damping...

Define Base Motion...

Defines the type of modal damping to be used. There are four types of modal damping to choose from: None, Composite, Direct or Rayleight*

* The forms for specification of damping

for the Direct option is discussed in Define Damping Direct (p. 363) and the Rayleigh option in Define Damping Rayleigh (p. 364). Composite modal damping is defined by the material. For the input of material damping, see Materials Form (p. 44). The concept of composite damping in ABAQUS is explained in Section 2.2.10 of the ABAQUS/Standard User’s Manual.

Defines parameters used by the ∗ BASE MOTION option.

Modal Linear Transient

This subordinate form appears whenever the Output Request button is selected on the Step Create form, and the Solution Type is Modal Linear Transient.


Identifier


S11, S22, S33, S12, S13, S23

Stress Invariants The stress invariants output by ABAQUS are the Mises stress, Tresca stress, Hydrostatic pressure, first principal stress, second principal stress, third principal tress, and the third stress invariant. These quantities are scalar quantities which do not vary with a change of coordinate system. For elastic analyses, the von Mises and/or the Tresca stress invariants can be monitored to ensure that the analysis remains within the assumptions of linearity.

SINV


E



SF



SE

Shell Thickness Changes in thickness for shell elements (S3RF, S4RF,SAX1, SAX2, SAXA1N, SAXA2N)

STH



1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U


V

Acceleration Nodal accelerations, following the same convention as for displacements.

A

Total Displacements The summation of all individual modal components of displacement. The output follows the same convention as for the individual modal components.

TU

Total Velocities The summation of all individual modal components of velocity. The output follows the same convention as for the individual modal components.

TV

Total Accelerations The summation of all individual modal components of acceleration. The output follows the same convention as for the individual modal components.

TA


RF

Point Forces The forces at the nodes resulting from the imposed loads, (e.g., the force at a node resulting from pressure distributions on adjacent elements).

CF

Generalized Displacements

The displacements associated with the modes of vibrations, each of which have a shape (eigenmode) and associated frequency (eigenvalue).

GU

Generalized Velocities The velocities associated with the modes of vibration. GV


Identifier

Generalized Accelerations The accelerations associated with the modes of vibration. GA

Strain Energy per Mode Elastic strain energy for the entire model per each mode. SNE

Kinetic Energy per Mode Kinetic energy for the entire model per each mode. KE

External Work per Mode External work for the entire model per each mode. T

Base Motion The base motion (displacement, velocity, or acceleration). BM


ALLEN




Identifier


Define Damping Direct

When the type of Modal Damping selected is Direct, this subordinate form appears whenever Define Damping is selected. The data is used to define the *MODAL DAMPING option (see Section 9.6.6 of the ABAQUS/Standard User’s Manual) with the MODAL parameter set to DIRECT.

Damping Table

Input Data

OK Defaults Cancel

Mode Ranges

Lower

Delete RowAdd Row

Upper Coefficient

1

Defines a mode range by the lower mode number and the higher mode number of the range. The coefficient of this row applies to all modes in this mode range.

Defines the fraction of critical damping for all modes within this mode range. At critical damping, no vibration takes place.

Define Damping Rayleigh

When the type of Modal Damping selected is Rayleigh, this subordinate form appears whenever Define Damping is selected. This form defines the data required for the *MODAL DAMPING, RAYLEIGH option (see Section 9.6.6 of the ABAQUS/Standard User’s Manual).

Damping Table

Input Data

OK Defaults Cancel

Mode Ranges

Lower

Delete RowAdd Row

1

Upper Alpha Beta

Defines a mode range by giving the lowest mode number and the highest mode number of the range. The coefficients of this row apply to all modes in this mode range.

For Rayleigh damping, the Alpha and Beta factors define the damping contribution. The Alpha value defines the mass proportional damping, while the Beta factor defines the stiffness proportional damping.


Base Motion

This subordinate form appears whenever Define Base Motion is selected from the Modal Linear Transient, Steady State Dynamics, or Viscoelasticity Frequency Domain Solution Parameter forms. It defines the values on the ∗ BASE MOTION option (see Section 9.4.2 of the ABAQUS/Standard User’s Manual).

Base Motion

Amplitude Type:

OK Defaults Cancel

Acceleration

Base Motion Definition

DOF Number: 1

Allows the setting of the amplitude type to “Acceleration,” “Velocity,” or “Displacement.”

Defines the degree-of-freedom to which this base motion will be applied. This can be any integer from 1 through 6.

Steady State Dynamics

This subordinate form appears whenever the Solution Parameters button is selected and the Solution Type is Steady State Dynamics. This generates a *STEADY STATE DYNAMICS procedure (see Section 9.3.13 of the ABAQUS/Standard User’s Manual). A *FREQUENCY procedure may also be created prior to the *STEADY STATE DYNAMICS procedure, if required.

Defines which type of frequency scale is to be used. This can be set to either “Logarithmic” or “Linear.”

Solution Parameters

Steady State Dynamics Solution Parameters:

OK Defaults Cancel

NoneModal Damping:

LogarithmicFrequency Scale Choice:

Define Damping...


Define Base Motion...

Damping for four of the five choices available (None, Composite, Direct, and Rayleigh) is defined identically as for Modal Linear Transient.

In addition, Structural damping is allowed in which the damping is proportional to the internal forces but opposite in direction to the velocity. The value of the damping constant, s, that multiplies the internal forces is input on a form identical to that for Modal Damping Direct.

Defines parameters used by the ∗ BASE MOTION option.

The button brings up the Frequency Range Table form.


Steady State Dynamics

If the selected solution type is Steady State Dynamics, then the following parameters may be defined on the Output Requests form.


Identifier


S11, S22, S33, S12, S13, S23

Ph Angle Stress Component The phase angle shift of the stress components. PHS


SINV


E

Ph Angle Strain Component The phase angle shift of the strain components. PHE

Element Energy Magnitudes A scalar value for the energy content of the element. ELEN



SF



SE


STH


1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U


V


A

Total Displacements The summation of all individual modal components of displacement. The output follows the same convention as for the individual modal components.

TU

Total Velocities The summation of all individual modal components of velocity. The output follows the same convention as for the individual modal components.

TV


Identifier


Total Accelerations The summation of all individual modal components of acceleration. The output follows the same convention as for the individual modal components.

TA


All components of the phase angle of the displacements at the node.

PU

Phase Angle Total Displacements

All components of the phase angle of the total displacements at the node.

PTU

Reaction Forces The forces at the nodes which are constrained and so, therefore, resist changes in the system. The direction convention is the same as that for nodal output.

RF

Phase Angle Reaction Forces All components of the phase angle of the reaction forces at the node.

PRF

Point Forces The forces at the nodes resulting from the imposed loads, (e.g., the force at a node resulting from pressure distributions on adjacent elements).

CF

Generalized Displacements The displacements associated with the modes of vibrations, each of which have a shape (eigenmode) and associated frequency (eigenvalue).

GU



Phase Angle Generalized Displacements

The phase angle of displacements associated with the modes of vibrations, each of which have a shape (eigenmode) and associated frequency (eigenvalue).

PGU

Phase Angle Generalized Velocities

The phase angle of velocities associated with the modes of vibration.

PGV

Phase Angle Generalized Accelerations

The phase angle of accelerations associated with the modes of vibration.

PGA






ALLEN




Identifier

Define Frequencies

The data on this form is used to define the input for the *STEADY STATE DYNAMICS option (see Section 9.3.13 of the ABAQUS/Standard User’s Manual).

Frequency Range Table

Input Data

OK Defaults Cancel

Frequency Ranges

Lower

Delete RowAdd Row

1

Upper Points Bias

Indicates the lower and upper frequency range limits in cycles/time.

Defines the number of points in the frequency range at which results are to be given.

Defines the bias parameter, which is used to bias the results towards the ends of the intervals, so that better resolution is obtained there.


Response Spectrum

This subordinate form appears whenever the Solution Parameters button is selected and the Solution Type is Response Spectrum. This generates a *FREQUENCY procedure, and a *RESPONSE SPECTRUM procedure (see Sections 9.3.5 and 9.3.10, respectively, of the ABAQUS/Standard User’s Manual). A ∗ SPECTRUM option is also created (see Section 7.11.5 of the ABAQUS/Standard User’s Manual).

Solution Parameters

Response Spectrum Solution Parameters

OK Defaults Cancel

Excitation Components:

NoneModal Damping:

Define Response Spectra...

Define Damping...

Algebraic

Response Values Sum:

Spectrum Type:

ABS

Acceleration

Defines which method is to be used when combining the directional excitation components. This can be set to either “Algebraic” or “SRSS.” This is the COMP parameter on the RESPONSE SPECTRUM command.

Defines which method is to be used when combining the absolute values of the response in each natural mode. This defines the SUM parameter on the ∗ RESPONSE SPECTRUM option. The choices are ABS, SRSS, TENP, CQC, and RRL.Coord 0Spectrum Coord Frame =

Damping for the four choices available (None, Composite, Direct, and Rayleigh), as well as the Base Motion, is defined identically as for Modal Linear Transient.

Determines the value of the TYPE parameter on the ∗ SPECTRUM option. The available choices are Displacement, Velocity, Acceleration, and Gravity.

Define Response Spectra (Response Spectrum)

This subordinate form appears whenever the Define Response Spectra button is selected on the Response Spectrum Solution Parameter form.

Response Spectra

1ST Direction Response Spectrum

OK Defaults Cancel

1ST Multiplying Factor =

Define Spectrum...

1

2ND Direction Response Spectrum

2ND Multiplying Factor =

Define Spectrum...

1

3RD Direction Response Spectrum

3RD Multiplying Factor =

Define Spectrum...

1

This factor multiplies the magnitudes of the values defined in the response spectrum when the spectrum type is set to Gravity. Since acceleration spectra are often reported in units of “g” (gravity), this factor is used to define the acceleration of gravity. Note that spectra for up to three directions (X,Y,Z) can be defined with this form, and that the input for the second and third directions is the same as that for the first direction.


Define Spectrum (Response Spectrum)

This form appears whenever the Define Spectrum button is selected on the Response Spectra form, which is itself subordinate to the Response Spectrum Solution Parameter Form. Similar forms are used for the second and third directions.The data on this form will define the *SPECTRUM option (see Section 7.11.5 of the ABAQUS/Standard User’s Manual).

Spectrum Data Table

Input Data

OK Defaults Cancel

1ST Direction Data

Frequency

Delete RowAdd Row

Magnitude Damping

1

Defines (frequency, magnitude) pairs. The data must be entered in increasing frequency order. The magnitude values are either displacement, velocity, acceleration or g values, depending on the selected Spectrum type.

Defines the associated damping at the given frequency. This damping is expressed as the ratio of critical damping. At critical damping, no vibration takes place.

Response Spectrum

If the selected solution type is Response Spectrum, then the following parameters may be defined on the Output Requests form.


Identifier


S11, S22, S33, S12, S13, S23


SINV


E



SF



SE


STH



1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U


V


A


RF


CF


Identifier



GU








ALLEN




Identifier


Random Vibration

This subordinate form appears whenever the Solution Parameters button is selected and the Solution Type is Random Vibration. This generates a *FREQUENCY procedure and a *RANDOM RESPONSE procedure (see Sections 9.3.5 and 9.3.9 of the ABAQUS⁄ Standard User’s Manual).

Defines which type of frequency scale is to be used. This can be set to either “Logarithmic” or “Linear.”

Solution Parameters

Random Vibration Solution Parameters:

OK Defaults Cancel

Frequency Scale Choice:

Define Damping...

Logarithmic


NoneModal Damping:

Define Spectrum...

ForceSpectrum Type:

1Real Factor =

CorrelatedCorrelation Type:

0Imaginary Factor =

Damping for the four choices available (None, Composite, Direct, and Rayleigh), as well as the Base Motion, is defined identically as for Modal Linear Transient.

Defines the value of the TYPE parameter on the ∗ PSD-DEFINITION option (see Section 7.11.3 of the ABAQUS/Standard User’s Manual). The PSD may be defined for a force loading, a base acceleration, or an acoustic load in decibels.

Real and imaginary parts of the correlation factor for a single load case.

Defines the value of the TYPE parameter on the ∗ CORRELATION option (see Section 9.4.6 of the ABAQUS/Standard User’s Manual). The available types are Correlated, Uncorrelated, and Moving Noise.

Define Spectrum (Random Vibration)

The Spectrum Data Table form is used to define the power spectral density function data for the ∗ PSD-DEFINITION option (see Section 7.11.3 of the ABAQUS/Standard User’s Manual).

Spectrum Data Table

Input Data

OK Defaults Cancel

PSD Data

Frequency

Delete RowAdd Row

Real Part Imaginary

1

Defines the frequency in cycles/time.

Defines the real and imaginary parts of the power spectral density function in units2 per frequency.


Random Vibration

If the selected solution type is Random Vibration, then the following parameters may be defined on the Output Requests form.


Identifier


S11, S22, S33, S12, S13, S23

R.M.S. Stress Components

The root mean square value of the stress components. RA


SINV


E

R.M.S. Strain Components

The root mean square value of the strain components. RE



SF



SE


STH


1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U


V


A

R.M.S. Relative Displacement

The root mean square value of the displacement components relative to the base motion.

RU

R.M.S. Relative Velocities

The root mean square value of the velocity components relative to the base motion.

RV

R.M.S. Relative Acceleration

The root mean square value of the acceleration components relative to the base motion.

RA

Total Displacements The total displacement (including base motion) of the nodes. TU

Total Velocities The total velocity (including base motion) of the nodes. TV

Total Acceleration The total acceleration (including base motion) of the nodes. TA

R.M.S. Total Displacements

The root mean square value of the displacement components including the base motion.

RTU

R.M.S. Total Velocities The root mean square value of the velocity components including the base motion.

RTV

R.M.S. Total Accelerations

The root mean square value of the acceleration components including the base motion.

RTA


Identifier



RF

R.M.S. Reaction Forces The root mean square value of the modal component of the reaction forces.

RRF


CF



GU

Generalized Velocities The velocities associated with the modes of vibrations, each of which have a shape (eigenmode) and associated frequency (eigenvalue).

GV

Generalized Accelerations

The accelerations associated with the modes of vibrations, each of which have a shape (eigenmode) and associated frequency (eigenvalue).

GA


Whole Model Energies The summation of all the energy of the model. The kinetic, recoverable (elastic) strain, plastic dissipation, creep dissipation, and viscous dissipation is reported.

ALLEN




Identifier

Nonlinear Static

This subordinate form appears whenever the Solution Parameters button is selected and the Solution Type is Nonlinear Static. This generates a *STATIC procedure with the associated *STEP option. The NLGEOM parameter on the *STEP command is included. The NLGEOM parameter is included on the *STEP option.

Indicates whether automatic load incrementation is to be done. If this is selected, ABAQUS will choose the increments automatically (after trying the user’s initial time increment for the first attempt at the first increment) by defining the DIRECT parameter on the STATIC command.

Indicates whether large deflections are to be taken into account in the stiffness matrix. If this is selected, the optional NLGEOM parameter on the STEP option will be included.

Solution Parameters

10

Max No. of Increments Allowed =

Nonlinear Static Solution Parameters

OK Defaults Cancel

Large Deflections/Strains

Riks Method:

Initial DELTA-T = 0.1

Minimum DELTA-T =

Maximum DELTA-T =

Time Duration of Step = 1

The remainder of the parameters to be defined in this form are discussed on the following page.

Indicates that the RIKS parameter should be included on the ∗ STATIC option.

On/Off

On/Off


Automatic Load Increment: On/Off


More data input is available for defining the Nonlinear Static Solution Parameters shown on the previous page. Listed below are the remaining parameters contained in this menu if the Riks method is not selected .

Listed below are the remaining parameters contained in this menu if the Riks method is selected.

Parameter Name Description

Max No of Increments Defines the maximum number of increments that can be used within a single step. This is a positive integer value. This is the optional INC parameter on the ∗ STEP option.

Initial DELTA-T Defines the initial time increment to be used. This is a real constant. This will be modified as required if the automatic time stepping scheme is used. Otherwise, it will be used as a constant time increment.

Minimum DELTA-T Defines the minimum time increment to be used. This is a real constant. It is only used for automatic time incrementation. If ABAQUS finds it needs a smaller time increment than this value, the analysis is terminated.

Maximum DELTA-T Defines the maximum time increment to be used. This is a real constant. It is only used for automatic time incrementation. If this value is not specified, no upper limit is imposed.

Time Duration of Step Defines the total time period of the step. This is a real constant.


Initial Load Fraction Defines the initial load fraction to be applied to the model. This is a real constant. This is the initial time increment data value on the ∗ STATIC command.

Minimum Load Fraction Defines the minimum load fraction which will be added during any increment. These are real constants.

Maximum Load Fraction Defines the maximum load fraction which will be added during any increment. These are real constants.

Stopping Condition Indicates which stopping condition is to be used. This can be set to “Max. no. increments”, “Max. load multiplier”, or “Monitor a Node.” This indicates which stopping condition data values are to be defined on the ∗ STATIC option.

Max. Load Multiplier This defines the maximum load multiplier allowed before the iteration will be stopped. This is only used if “Max. load multiplier,” or “Monitor a Node” are selected.

Node Number Indicates the node ID to be monitored. This is only used if “Monitor a Node” is selected.

Limit Value Defines the limiting displacement at the node being monitored. This is only used if “Monitor a Node” is selected.

DOF Number Indicates which degree-of-freedom at this node is to be monitored. This is only used if “Monitor a Node” is selected.

Nonlinear Static

If the selected solution type is Nonlinear Static, then the following parameters may be defined on the Output Requests form.


Identifier


S11, S22, S33, S12, S13, S23


SINV


E

Plastic Strains The plastic strain component of the total strain. PE

Creep Strains The creep strain component of the total strain. CE

Elastic Strains The elastic strain component of the total strain. Note that the elastic strain component is the component from which the stress is computed.

EE

Inelastic Strains The total strain minus the elastic strain component. IE

Elem Energy Densities The energy per unit volume of each element. Strain, plastic, creep, and viscous dissipative energy densities are reported.

ENER


The energy of each element. Strain, kinetic, plastic, creep, and viscous dissipative energies are reported.

ELEN


NFORC



SF




SE


STH

Displacement Displacements are output at nodes and are referred to as follows:

1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U


RF


CF


ALLEN




Identifier


This subordinate form appears whenever the Solution Parameters button is selected and the Solution Type is Nonlinear Transient Dynamic. This generates a ∗ DYNAMIC procedure, with the associated ∗ STEP option. The DIRECT and HAFTOL parameters are available on the ∗ DYNAMIC option.

Indicates whether large deflections are to be taken into account in the stiffness matrix. If this is selected, the optional NLGEOM parameter on the ∗ STEP option will be included.

Defines the maximum number of increments that can be used within a single step. This is a positive integer value. This is the optional INC parameter on the ∗ STEP option.

Solution Parameters

10


Nonlinear Transient Dynamic Sol. Parameters

OK Defaults Cancel


Minimum DELTA-T =

Maximum DELTA-T =


Max Error in Mid Increment Residual =

Indicates whether automatic time step incrementation is to be done. If this is selected, ABAQUS will choose the increments automatically (after trying the user’s initial time increment for the first attempt at the first increment). This defines the DIRECT parameter on the ∗ DYNAMIC option.


Defines whether or not ABAQUS will calculate or recalculate accelerations at the beginning of the step. This is the INITIAL parameter on the ∗ DYNAMIC option.


Large Deflections/Strains: On/Off

Calculate Initial Acceleration: On/Off

Automatic Time Increment: On/Off


More data input is available for defining the Nonlinear Transient Dynamic Solution Parameters shown on the previous page. Listed below are the remaining parameters contained in this menu.


If the selected solution type is Nonlinear Transient Dynamics, then the following parameters may be defined on the Output Requests form.






Max Error in Mid Increment Residual

This is the HAFTOL parameter on the ∗ DYNAMIC option. See Section 9.3.4 of the ABAQUS/Standard User’s Manual and Section 5.2.1 of the ABAQUS/Standard Example Problems.


Identifier


S11, S22, S33, S12, S13, S23


SINV


E




EE


Elem Energy DensitiesThe energy per unit volume of each element. Strain, plastic, creep, and viscous dissipative energy densities are reported.

ENER


The energy of each element. Strain, kinetic, elastic, creep, and viscous dissipative energies are reported.

ELEM


NFORC



SF



SW


STH


Identifier



1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U


V


A


RF


CF


ALLEN





Identifier

Creep

This subordinate form appears whenever the Solution Parameters button is selected and the Solution Type is Creep. This generates a ∗ VISCO procedure, with the associated ∗ STEP option.

More data input is available for defining the Creep Solution Parameters shown on the previous page. Listed below are the remaining parameters contained in this menu.





Indicates whether large deflections are to be taken into account in the stiffness matrix. If this is selected, the optional NLGEOM parameter will be included on the ∗ STEP option.

Defines the maximum number of increments that can be used within a single step. This is a positive integer value. This is the optional INC parameter on the *STEP option.

Indicates which integration method is to be used. This can be set to either IMPLICIT or EXPLICIT. This indicates whether the EXPLICIT parameter is to be included on the ∗ VISCO option.

Solution Parameters

10


Creep Solution Parameters

OK Defaults Cancel


Minimum DELTA-T =

Maximum DELTA-T =


0

Admissable Error in Strain Increment =

Integration Method: IMPLICIT





Creep

The strain components output depend on the elements analyzed, analogous to the stress components. In addition, the total strain component can be separated into its contributory parts (e.g., elastic strain, plastic strains, etc.) and these are reported separately.


Admissable Error in Strain Increment

This is the CETOL parameter on the ∗ VISCO option. See Section 9.3.15 of the ABAQUS/Standard User’s Manual.


Identifier


S11, S22, S33, S12, S13, S23


SINV


E




EE


Elem Energy Densities

The energy per unit volume of each element. Strain, plastic, creep, and viscous dissipative energy densities are reported.

ENER



ELEM


Internal Stress ForcesThe forces that are found at each node by summing the element stress contributions at the nodes.

NFORC



SF



SE


STH


1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U


Identifier



RF


CF

Whole Model Energies

The summation of all the energy of the model. The kinetic, recoverable (elastic) strain, plastic dissipation, creep dissipation, and viscous dissipation are reported.

ALLEN





Identifier


This subordinate form appears whenever Solution Parameters is selected and the Solution Type is Viscoelastic (Time Domain). This generates a ∗ VISCO procedure, with the associated ∗ STEP command.

Indicates whether large deflections are to be taken into account in the stiffness matrix. If this is selected, the optional NLGEOM parameter on the ∗ STEP option will be included.

Defines the maximum number of increments that can be used within a single step. This is a positive integer value. This is the INC optional parameter on the ∗ STEP option.

Solution Parameters

10


Viscoelastic (Time) Sol. Parameters:

OK Defaults Cancel


Minimum DELTA-T =

Maximum DELTA-T =


0

Admissable Error in Strain Increment =





More data input is available for defining the Viscoelastic (Time Domain) Solution Parameters shown on the previous page. Listed below are the remaining parameters contained in this menu.


If the selected Solution Type is Viscoelastic (Time Domain), then the following parameters may be defined on the Output Requests form.







Identifier


S11, S22, S33, S12, S13, S23


SINV


E




EE


Elem Energy Densities The energy per unit volume of each element. Strain, plastic, creep, and viscous dissipative energy densities are reported.

ENER



ELEM


NFORC



SF



SE


STH


Identifier



1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U


RF


CF


ALLEN





Identifier


This subordinate form appears whenever the Solution Parameters button is selected and the solution type is Viscoelastic (Frequency Domain). This generates a *STEADY STATE DYNAMIC procedure.


If the selected solution type is Viscoelastic (Frequency Domain), then the following parameters may be defined on the Output Requests form.

Defines which type of frequency scale is to be used. This can be set to either “Logarithmic” or “Linear.” This defines a value on the ∗ STEADY STATE DYNAMICS option.

Solution Parameters

Viscoelastic Frequency Solution Parameters:

OK Defaults Cancel

Frequency Scale Choice: Logarithmic



Identifier


S11, S22, S33, S12, S13, S23


SINV

Ph Angle Stress Components

The phase angle shift of the stress components. PHS


E


Ph Angle Strain Components

The phase angle shift of the strain components. PHE



SF



SE


STH


1. x-displacement

2. y-displacement

3. z-displacement





1. r-displacement

2. z-displacement



U


V


Identifier


A


The phase angle shift of the relative displacement components. PU

Reaction Forces The forces at the nodes which are constrained and so, therefore, resist changes in the system. The direction convention is the same as that for nodal output.

RF

Phase Angle Reaction Forces

The phase angle shift of the reaction force components. PRF


CF




Identifier



This subordinate form appears whenever Solution Parameters is selected and the solution type is Steady State Heat Transfer. This generates a ∗ HEAT TRANSFER, STEADY STATE procedure.


If the selected solution type is Steady State Heat Transfer, then the following parameters may be defined on the Output Requests form.


Identifier

Element Temperature Temperature. TEMP

Heat Flux Current magnitude and components of the heat flux vector. The integration of points for these values are located at the Gauss points.

HFL

Nodal Temperatures All temperature values at a node. These will be the temperatures defined as degrees-of-freedom if heat transfer elements are connected to the node, or predefined temperatures if the node is only connected to stress elements without temperature degrees-of-freedom.

NT

Reaction Fluxes All reaction flux values (conjugate to temperature). RFL

Concentrated Fluxes All concentrated flux values. CFL


Defines the suggested time increment. This isa real constant.


Solution Parameters

Steady State Heat Transfer Sol. Parameters:

OK Defaults Cancel

0.1

1

Delta-T =

Time Duration of Step=

Transient Heat Transfer

This subordinate option is Transient Heat Transfer. This generates a ∗ HEAT TRANSFER procedure.

Solution Parameters

OK Defaults Cancel

Transient Heat Transfer Sol. Parameters:

Max No. of Increments Allowed = 10

Max Allowable Temperature Change =

0

0

Max Temp Change Rate (Temp/Time) =

0.1

0

1

Time PeriodStopping Condition:

Time Duration of Step =

Maximum Delta-T =

Minimum Delta-T =

Delta-T =

Defines the maximum number of increments in the step. This is the value of the INC parameter on the ∗ STEP option. This is a real constant.

Defines the maximum temperature change to be allowed in an increment. ABAQUS will restrict the time step to ensure that this value will not be exceeded at any node (except nodes with boundary conditions) during any increment of the analysis. This is the DELTMX parameter on the ∗ HEAT TRANSFER option. This is a real constant.

Defines the suggested time increment. This is a real constant.

Defines the minimum time increment allowed. This is a real constant.

Defines the maximum time increment allowed. This is a real constant.


Defines the stopping condition. Selecting Time Period generates END=PERIOD and selecting Steady State generates END=SS on the ∗ HEAT TRANSFER option.

Defines the temperature change rate (temperature per time) used to define steady-state. When all nodal temperatures are changing at less than this rate, the solution terminates. This is only used with the Steady State Stopping Condition. This is a real constant.


Transient Heat Transfer

If the selected solution type is Transient Heat Transfer, then the following parameters may be defined on the Output Requests form.


Identifier

Element Temperature Temperature. TEMP

Heat Flux Current magnitude and components of the heat flux vector. The integration of points for these values are located at the Gauss points.

HFL

Nodal Temperatures All temperature values at a node. These will be the temperatures defined as degrees-of-freedom if heat transfer elements are connected to the node, or predefined temperatures if the node is only connected to stress elements without temperature degrees-of-freedom.

NT

Reaction Fluxes All reaction flux values (conjugate to temperature). RFL

Concentrated Fluxes All concentrated flux values. CFL


3.7 Step SelectionThis subordinate form appears whenever the Step Selection button is selected on the main Analysis form. This form is used to select and order the Job Steps that will be analyzed for the ABAQUS Job.

Step Select

Existing Job Steps:

CancelDefaultsApply

Default Static Step

Default Static Step

Selected Job Steps

Lists the Job Steps that have been defined in the Step Create form. Select the job steps, in the order to be run, from this form and review your selections and their order in the bottom window. Remember, order is important in a nonlinear analysis since the state of the system is history dependent.

Lists the Job Steps that have been selected for the current ABAQUS job to be submitted. Each Job Step will be run in the order in which it appears. Each step involves nonlinear response, or is a linear perturbation analysis about the current base state (defined as the current state created by nonlinear response prior to this step). Each nonlinear step is thus a portion or period of the history.


3.8 Read Input FileIt is possible to read an existing ABAQUS input file (jobname.inp) into MSC.Patran. This is not a fully supported feature and must be invoked by setting a special parameter. This is done by editing the settings.pcl file and adding the following line:

pref_env_set_logical( "shareware_input_file", TRUE )

If this setting is set to TRUE, then an additional Action item will appear under the Analysis form called Read Input File. This file can exist in the installation, local or home directories.

Analysis

Read Input FileAction:

Code:

Model DataObject:

Jobname

Apply

Press this button to get a file browser to select the ABAQUS input file you wish to import.

Set this to Read Input File to read an existing ABAQUS input file into MSC.Patran. You must set the logical variable as described above.

ABAQUS

Type: Structural

Available Jobs

Job Description

Select Inpt File...

3.9 ABAQUS Input File ReaderThis section describes a software module that reads ABAQUS input files and writes the data to the MSC/PATRAN database in a form compatible with the MSC/PATRAN ABAQUS preference.

Input Deck FormatsBoth fixed format and free format entries are supported. Floating point formats with and without an “E” in the exponent are supported (e.g. 1.23E6 and 1.23+6 are both supported).

Message File

Informative, warning, and error messages are written to an external file with the name <input_file_basename>.msg.<version_number> where <input_file_basename> is the portion of the ABAQUS input file name before the suffix and <version_number> is a unique version number beginning with 01. After import, this file should be carefully examined to understand what was processed by the reader and what was not. Sometimes the error messages will indicate where minor editing of the input deck will convert an unsupported entity to one that can be handled by the reader.

ABAQUS ELSET and NSET EntriesA PATRAN group is created for each ABAQUS ELSET or NSET entry. The name of the group is taken from the NAME parameter of the ELSET or NSET.

Supported Element Types

When the reader encounters a *ELEMENT entry, the combination of the element type and the ABAQUS property set entry are used to map the ABAQUS element type to the appropriate PATRAN element type. In some cases this is not possible because not all ABAQUS element types are currently supported in PATRAN. In these cases, the reader attempts to find the PATRAN element type that “best” matches the ABAQUS type. Thus, the ABAQUS elements retain their association to their property set. This allows the finite element mesh to be edited in PATRAN and an ABAQUS input deck output that can be easily edited to correct the property entry.

Supported Keywords

The table below describes the ABAQUS keywords that are supported in the current version of the product.

ABAQUS Keyword Notes

Model Section

*AMPLITUDE A PATRAN time- or frequency-dependent field is created.

*BEAM GENERAL SECTION

A PATRAN property set is created.

*BEAM SECTION A PATRAN property set is created.


*BOUNDARY A PATRAN LBC set is created for each ABAQUS BOUNDARY and added to all load cases. Displacement, temperature, velocity, and acceleration boundary conditions are currently supported.

*CENTROID Location is added to the PATRAN property set.

*CONDUCTIVITY Value is added to the PATRAN material.

*CONTACT NODE SET When referenced in a *CONTACT PAIR, this data is added to a contact-type LBC set.

*CONTACT PAIR A PATRAN contact-type LBC set is created for each entry in *CONTACT PAIR.

*CORRELATION

*DAMPING Value is added to the PATRAN material or shell element property set.

*DASHPOT A PATRAN property set is created.

*DENSITY Value is added to the PATRAN material.

*ELASTIC Values are added to the PATRAN material.

*ELCOPY Element Generation Command

*ELEMENT PATRAN elements are created. Both a PATRAN group and a property set are created with the ELSET name.

*ELGEN PATRAN elements are created.

*ELSET A PATRAN group is created.

*EQUATION A PATRAN MPC is created. The use of node sets in *EQUATION entries is not currently supported.

*EXPANSION Values are added to the PATRAN material.

*FRICTION The *FRICTION keyword is supported within *GAP, *INTERFACE, and *SURFACE INTERACTION blocks. The friction properties are added to the appropriate property or LBC set.

*GAP A PATRAN property set is created.

*HEADING A PATRAN analysis job is created with this description.

*HOURGLASS STIFFNESS The values are added to the appropriate PATRAN property set.

*INCLUDE The referenced file is read. *INCLUDE entries may be nested to any reasonable depth.

*MASS A PATRAN property set is created.

*MATERIAL A PATRAN material is created.

*MEMBRANE SECTION A PATRAN property set is created.


*MPC A PATRAN MPC is created. The use of node sets in *MPC entries is not currently supported.

*MODAL DAMPING

*NCOPY Generates additional nodes using NID and X/Y/Z offsets.

*NFILL PATRAN nodes are created. The SINGULAR option is not currently supported.

*NGEN PATRAN nodes are created. Nodes may be generated along a line or a circular arc (LINE=C) but not along a parabola (LINE=P).

*NODAL THICKNESS A PATRAN nodal FEM field and property set are created.

*NODE PATRAN nodes are created. If an NSET parameter is specified, a PATRAN group is created with this name, otherwise the nodes are added to the default group.

*NSET A PATRAN group is created.

*ORIENTATION Is used to define orientation for homogeneous or laminate material properties.

*PLASTIC Only HARDENING=ISOTROPIC and HARDENING=KINEMATIC are currently supported. The RATE parameter is not currently supported; only the first set *PLASTIC entries for a material are imported.

*PSD

*RIGID BODY When referenced in a *CONTACT PAIR, this data is added to a contact-type LBC set.

*RIGID SURFACE The *RIGID SURFACE keyword is currently supported in two ways by the PATRAN, ABAQUS preference. For the older style of ABAQUS contact, which required the use of IRSx type elements, *RIGID SURFACE entries were written out for “rigid surface type” element properties. For the newer style of ABAQUS contact ,which uses *CONTACT PAIR, geometric curves are selected directly in a PATRAN contact-type LBC. Only this second usage of *RIGID SURFACE is supported by the reader. When referenced in a *CONTACT PAIR entry, curves are created and references to them added to the contact-type LBC set.

*ROTARY INERTIA A PATRAN property set is created.

*SECTION POINTS Points are added to the PATRAN property set.

*SHEAR CENTER Location is added to the PATRAN property set.

*SHELL GENERAL SECTION

A PATRAN property set is created.

*SHELL SECTION A PATRAN property set is created.



*SOLID SECTION A PATRAN property set is created.

*SPECTRUM

*SPECIFIC HEAT Value is added to the PATRAN material.

*SPRING A PATRAN property set is created.

*SURFACE DEFINITION When referenced in a *CONTACT PAIR, this data is added to a contact-type LBC set.

*SURFACE INTERACTION

The only keyword currently supported within this block is *FRICTION. The keyword parameters and friction data are added to the appropriate contact-type LBC set.

*SYSTEM PATRAN node locations are transformed to the coordinate system defined on this entry.

*TRANSFORM A PATRAN coordinate frame is created and used to define the analysis system for the node.

*TRANSVERSE SHEAR STIFFNESS

The values are added to the appropriate PATRAN property set.

History Section

*BOUNDARY A PATRAN LBC set is created for each ABAQUS BOUNDARY and added to the load case for this step. Displacement, temperature, velocity, and acceleration boundary conditions are currently supported.

*BUCKLE The parameters associated with this entry are added to the PATRAN analysis step.

*CFLUX A PATRAN LBC set is created for each ABAQUS CFLUX and added to the load case for this step.

*CLOAD A PATRAN LBC set is created for each ABAQUS CLOAD and added to the load case for this step.

*DFLUX A PATRAN LBC set is created for each ABAQUS DFLUX and added to the load case for this step.

*DLOAD A PATRAN LBC set is created for each ABAQUS DLOAD and added to the load case for this step. The pressure DLOAD types as well as GRAV, CENT, CENTRIF, and CORIO are currently supported.

*DYNAMIC The parameters associated with this entry are added to the PATRAN analysis step.

*FILM A PATRAN LBC set is created for each ABAQUS FILM and added to the load case for this step.

*FREQUENCY The parameters associated with this entry are added to the PATRAN analysis step.


Both fixed format and free format entries are supported.

*HEAT TRANSFER The parameters associated with this entry are added to the PATRAN analysis step.

*MODAL DYNAMIC The parameters associated with this entry are added to the PATRAN analysis step.

*STATIC The parameters associated with this entry are added to the PATRAN analysis step.

*STEADY STATE DYNAMICS

The parameters associated with this entry are added to the PATRAN analysis step.

*STEP A PATRAN load case and an analysis job step are created for each ABAQUS step. The parameters on the *STEP entry are added to the analysis step

*TEMPERATURE A PATRAN LBC set is created for each ABAQUS TEMPERATURE and added to the load case for this step.

*VISCO The parameters associated with this entry are added to the PATRAN analysis step.



The table below shows the PATRAN element property options that are created when a specific ABAQUS element type is imported.

Table 3-1 PATRAN Property Options for Each ABAQUS Element

ABAQUS Element Dim Name Option1 Option2

AC1D2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactAC1D3 1D ISL (in plane) Axisymmetric Lagrange Soft ContactAC2D4 2D Rigid Surface(LBC)AC2D8 2D 2D Interface Axisymmetric Lagrange Vis DampingAC3D20 3D Solid Homogeneous Standard FormulationAC3D8 3D Solid Homogeneous HybridACAX4 2D Rigid Surface(LBC)ACAX8 2D 2D Interface Axisymmetric Lagrange Vis DampingASI1 0D IRS (single node) Planar Elas Slip Vis DampingASI2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactASI2A 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactASI3 2D IRS (shell/solid) Elastic Slip Hard ContactASI3A 2D Shell General Large Strain HomogeneousASI4 2D IRS (shell/solid) Lagrange Hard ContactASI8 2D 2D Interface Axisymmetric Lagrange Vis DampingB21 1D Beam in XY Plane General Section Standard FormulationB21H 1D Beam in XY Plane General Section HybridB22 1D Beam in XY Plane General Section Standard FormulationB22H 1D Beam in XY Plane General Section HybridB23 1D Beam in XY Plane General Section Cubic InterpolationB23H 1D Beam in XY Plane General Section Cubic HybridB31 1D Beam in Space General Section Standard FormulationB31H 1D Beam in Space General Section HybridB31OS 1D Beam in Space Open Section Standard FormulationB31OSH 1D Beam in Space Open Section HybridB32 1D Beam in Space General Section Standard FormulationB32H 1D Beam in Space General Section HybridB32OS 1D Beam in Space Open Section Standard FormulationB32OSH 1D Beam in Space Open Section HybridB33 1D Beam in Space General Section Cubic InterpolationB33H 1D Beam in Space General Section Cubic HybridB34 1D Beam in Space General Section Cubic Initially StraightC1D2 1D Truss Standard FormulationC1D2H 1D Truss HybridC1D2T 1D Truss HybridC1D3 1D Truss Standard FormulationC1D3H 1D Truss HybridC1D3T 1D Truss Standard FormulationC3D10 3D Solid Homogeneous Standard FormulationC3D10E 3D Solid Homogeneous HomogeneousC3D10H 3D Solid Homogeneous HybridC3D10M 3D Solid Homogeneous Modified FormulationC3D10MH 3D Solid Homogeneous Modified/Hybrid

C3D15 3D Solid Homogeneous Standard FormulationC3D15E 3D Solid Homogeneous Standard FormulationC3D15H 3D Solid Homogeneous HybridC3D15V 3D Solid Homogeneous Standard FormulationC3D15VH 3D Solid Homogeneous HybridC3D20 3D Solid Homogeneous Standard FormulationC3D20E 3D Solid Homogeneous Standard FormulationC3D20H 3D Solid Homogeneous HybridC3D20HT 3D Solid Homogeneous Standard FormulationC3D20P 3D Solid Homogeneous Standard FormulationC3D20PH 3D Solid Homogeneous Standard FormulationC3D20R 3D Solid Homogeneous Reduced IntegrationC3D20RE 3D Solid Homogeneous Standard FormulationC3D20RH 3D Solid Homogeneous Hybrid/Reduced IntegrationC3D20RHT 3D Solid Homogeneous Standard FormulationC3D20RP 3D Solid Homogeneous Standard FormulationC3D20RPH 3D Solid Homogeneous Standard FormulationC3D20RT 3D Solid Homogeneous Standard FormulationC3D20T 3D Solid Homogeneous Standard FormulationC3D27 3D Solid Homogeneous Standard FormulationC3D27H 3D Solid Homogeneous HybridC3D27R 3D Solid Homogeneous Reduced IntegrationC3D27RH 3D Solid Homogeneous Hybrid/Reduced IntegrationC3D4 3D Solid Homogeneous Standard FormulationC3D4E 3D Solid Standard FormulationC3D4H 3D Solid Homogeneous HybridC3D6 3D Solid Homogeneous Standard FormulationC3D6E 3D Solid Homogeneous Standard FormulationC3D6H 3D Solid Homogeneous HybridC3D8 3D Solid Homogeneous Standard FormulationC3D8E 3D Solid Homogeneous HybridC3D8H 3D Solid Homogeneous HybridC3D8HT 3D Solid Homogeneous HybridC3D8I 3D Solid Homogeneous Incompatible ModesC3D8IH 3D Solid Homogeneous Hybrid/Incompatible ModesC3D8R 3D Solid Homogeneous Reduced IntegrationC3D8RH 3D Solid Homogeneous Hybrid/Reduced IntegrationC3D8T 3D Solid Homogeneous HybridCAX3 2D 2D Solid Axisymmetric Standard FormulationCAX3E 2D 2D Solid Axisymmetric Standard FormulationCAX3H 2D 2D Solid Axisymmetric HybridCAX4 2D 2D Solid Axisymmetric Standard FormulationCAX4E 2D 2D Solid Axisymmetric Standard FormulationCAX4H 2D 2D Solid Axisymmetric HybridCAX4HT 2D 2D Solid Axisymmetric Standard Formulation

Table 3-1 PATRAN Property Options for Each ABAQUS Element (continued)



CAX4I 2D 2D Solid Axisymmetric Incompatible ModesCAX4IH 2D 2D Solid Axisymmetric Hybrid/Incompatible ModesCAX4P 2D 2D Solid Axisymmetric Standard FormulationCAX4PH 2D 2D Solid Axisymmetric Standard FormulationCAX4R 2D 2D Solid Axisymmetric Reduced IntegrationCAX4RH 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCAX4T 2D 2D Solid Axisymmetric Standard FormulationCAX6 2D 2D Solid Axisymmetric Standard FormulationCAX6E 2D 2D Solid Axisymmetric AxisymmetricCAX6H 2D 2D Solid Axisymmetric HybridCAX6M 2D 2D Solid Axisymmetric Modified FormulationCAX6MH 2D 2D Solid Axisymmetric Modified/HybridCAX8 2D 2D Solid Axisymmetric Standard FormulationCAX8E 2D 2D Solid Axisymmetric HybridCAX8H 2D 2D Solid Axisymmetric HybridCAX8HT 2D 2D Solid Axisymmetric HybridCAX8P 2D 2D Solid Axisymmetric HybridCAX8PH 2D 2D Solid Axisymmetric HybridCAX8R 2D 2D Solid Axisymmetric Reduced IntegrationCAX8RE 2D 2D Solid Axisymmetric HybridCAX8RH 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCAX8RHT 2D 2D Solid Axisymmetric HybridCAX8RP 2D 2D Solid Axisymmetric HybridCAX8RPH 2D 2D Solid Axisymmetric HybridCAX8RT 2D 2D Solid Axisymmetric HybridCAX8T 2D 2D Solid Axisymmetric HybridCAXA41 2D 2D Solid Axisymmetric Standard FormulationCAXA42 2D 2D Solid Axisymmetric Standard FormulationCAXA43 2D 2D Solid Axisymmetric Standard FormulationCAXA44 2D 2D Solid Axisymmetric Standard FormulationCAXA4H1 2D 2D Solid Axisymmetric HybridCAXA4H2 2D 2D Solid Axisymmetric HybridCAXA4H3 2D 2D Solid Axisymmetric HybridCAXA4H4 2D 2D Solid Axisymmetric HybridCAXA4R1 2D 2D Solid Axisymmetric Reduced IntegrationCAXA4R2 2D 2D Solid Axisymmetric Reduced IntegrationCAXA4R3 2D 2D Solid Axisymmetric Reduced IntegrationCAXA4R4 2D 2D Solid Axisymmetric Reduced IntegrationCAXA4RH1 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCAXA4RH2 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCAXA4RH3 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCAXA4RH4 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCAXA81 2D 2D Solid Axisymmetric Standard FormulationCAXA82 2D 2D Solid Axisymmetric Standard FormulationCAXA83 2D 2D Solid Axisymmetric Standard Formulation



CAXA84 2D 2D Solid Axisymmetric Standard FormulationCAXA8H1 2D 2D Solid Axisymmetric HybridCAXA8H2 2D 2D Solid Axisymmetric HybridCAXA8H3 2D 2D Solid Axisymmetric HybridCAXA8H4 2D 2D Solid Axisymmetric HybridCAXA8P1 2D 2D Solid Axisymmetric HybridCAXA8P2 2D 2D Solid Axisymmetric HybridCAXA8P3 2D 2D Solid Axisymmetric HybridCAXA8P4 2D 2D Solid Axisymmetric HybridCAXA8R1 2D 2D Solid Axisymmetric Reduced IntegrationCAXA8R2 2D 2D Solid Axisymmetric Reduced IntegrationCAXA8R3 2D 2D Solid Axisymmetric Reduced IntegrationCAXA8R4 2D 2D Solid Axisymmetric Reduced IntegrationCAXA8RH1 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCAXA8RH2 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCAXA8RH3 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCAXA8RH4 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCAXA8RP1 2D 2D Solid Axisymmetric HybridCAXA8RP2 2D 2D Solid Axisymmetric HybridCAXA8RP3 2D 2D Solid Axisymmetric HybridCAXA8RP4 2D 2D Solid Axisymmetric HybridCGAX3 2D 2D Solid Axisymmetric Standard FormulationCGAX3H 2D 2D Solid Axisymmetric HybridCGAX4 2D 2D Solid Axisymmetric Standard FormulationCGAX4H 2D 2D Solid Axisymmetric HybridCGAX4I 2D 2D Solid Axisymmetric Incompatible ModesCGAX4IH 2D 2D Solid Axisymmetric Hybrid/Incompatible ModesCGAX4R 2D 2D Solid Axisymmetric Reduced IntegrationCGAX4RH 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCGAX6 2D 2D Solid Axisymmetric AxisymmetricCGAX6H 2D 2D Solid Axisymmetric HybridCGAX8 2D 2D Solid Axisymmetric Standard FormulationCGAX8H 2D 2D Solid Axisymmetric HybridCGAX8R 2D 2D Solid Axisymmetric Reduced IntegrationCGAX8RH 2D 2D Solid Axisymmetric Hybrid/Reduced IntegrationCGPE10 2D 2D Solid General Plane Strain Standard FormulationCGPE10H 2D 2D Solid General Plane Strain HybridCGPE10R 2D 2D Solid General Plane Strain Reduced IntegrationCGPE10RH 2D 2D Solid General Plane Strain Hybrid/Reduced IntegrationCGPE5 2D 2D Solid General Plane Strain Standard FormulationCGPE5H 2D 2D Solid General Plane Strain HybridCGPE6 2D 2D Solid General Plane Strain Standard FormulationCGPE6H 2D 2D Solid General Plane Strain HybridCGPE6I 2D 2D Solid General Plane Strain Incompatible ModesCGPE6IH 2D 2D Solid General Plane Strain Hybrid/Incompatible Modes




CGPE6R 2D 2D Solid General Plane Strain Reduced IntegrationCGPE6RH 2D 2D Solid General Plane Strain Hybrid/Reduced IntegrationCGPE8 2D 2D Solid General Plane Strain Standard FormulationCGPE8H 2D 2D Solid General Plane Strain HybridCONN2D2 1D Mech Joint (2D Model) ALIGN

AXIALBEAMCARTESIANJOINJOINTCLINKROTATIONSLOTTRANSLATORWELD

CONN3D2 1D Mech Joint (3D Model) ALIGNAXIALBEAMCARDANCARTESIANCONSTANT VELOCITYCVJOINTCYLINDRICALEULERFLEXION-TORSIONHINGEJOINJOINTCLINKPLANARRADIAL-THRUSTREVOLUTEROTATIONSLIDE-PLANESLOTTRANSLATORUJOINTUNIVERSALWELD

CPE3 2D 2D Solid Plane Strain Standard FormulationCPE3E 2D 2D Solid Plane Strain Plane StrainCPE3H 2D 2D Solid Plane Strain HybridCPE4 2D 2D Solid Plane Strain Standard FormulationCPE4E 2D 2D Solid Plane Strain Reduced IntegrationCPE4H 2D 2D Solid Plane Strain HybridCPE4HT 2D 2D Solid Plane Strain Reduced IntegrationCPE4I 2D 2D Solid Plane Strain Incompatible ModesCPE4IH 2D 2D Solid Plane Strain Hybrid/Incompatible Modes



CPE4R 2D 2D Solid Plane Strain Reduced IntegrationCPE4RH 2D 2D Solid Plane Strain Hybrid/Reduced IntegrationCPE4T 2D 2D Solid Plane Strain Reduced IntegrationCPE6 2D 2D Solid Plane Strain Standard FormulationCPE6E 2D 2D Solid Plane Strain Standard FormulationCPE6H 2D 2D Solid Plane Strain HybridCPE8 2D 2D Solid Plane Strain Standard FormulationCPE8E 2D 2D Solid Plane Strain Reduced IntegrationCPE8H 2D 2D Solid Plane Strain HybridCPE8HT 2D 2D Solid Plane Strain Reduced IntegrationCPE8P 2D 2D Solid Plane Strain Standard FormulationCPE8PH 2D 2D Solid Plane Strain HybridCPE8R 2D 2D Solid Plane Strain Reduced IntegrationCPE8RE 2D 2D Solid Plane Strain Reduced IntegrationCPE8RH 2D 2D Solid Plane Strain Hybrid/Reduced IntegrationCPE8RHT 2D 2D Solid Plane Strain Reduced IntegrationCPE8RP 2D 2D Solid Plane Strain Reduced IntegrationCPE8RPH 2D 2D Solid Plane Strain Hybrid/Reduced IntegrationCPE8RT 2D 2D Solid Plane Strain Reduced IntegrationCPE8T 2D 2D Solid Plane Strain Reduced IntegrationCPS3 2D 2D Solid Plane Stress Standard FormulationCPS3E 2D 2D Solid Plane Stress Plane StressCPS4 2D 2D Solid Plane Stress Standard FormulationCPS4E 2D 2D Solid Plane Stress Reduced IntegrationCPS4I 2D 2D Solid Plane Stress Incompatible ModesCPS4R 2D 2D Solid Plane Stress Reduced IntegrationCPS4T 2D 2D Solid Plane Stress Reduced IntegrationCPS6 2D 2D Solid Plane Stress Standard FormulationCPS6E 2D 2D Solid Plane Stress Standard FormulationCPS6M 2D 2D Solid Plane Stress Modified FormulationCPS8 2D 2D Solid Plane Stress Standard FormulationCPS8E 2D 2D Solid Plane Stress Standard FormulationCPS8R 2D 2D Solid Plane Stress Reduced IntegrationCPS8RE 2D 2D Solid Plane Stress Standard FormulationCPS8RT 2D 2D Solid Plane Stress Standard FormulationCPS8T 2D 2D Solid Plane Stress Standard FormulationDASHPOT1 0D Grounded Damper LinearDASHPOT2 1D Damper Linear Fixed DirectionDASHPOTA 1D Damper Linear Standard FormulationDC1D2 1D LinkDC1D2E 1D LinkDC1D3 1D LinkDC1D3E 1D LinkDC2D3 2D 2D Solid Planar Standard FormulationDC2D4 2D 2D Solid Planar Standard Formulation




DC2D6 2D 2D Solid Planar Standard FormulationDC2D8 2D 2D Solid Planar Standard FormulationDC3D10 3D Solid Standard FormulationDC3D15 3D Solid Standard FormulationDC3D20 3D Solid Standard FormulationDC3D4 3D Solid Standard FormulationDC3D6 3D Solid Standard FormulationDC3D8 3D Solid Standard FormulationDCAX3 2D 2D Solid Axisymmetric Standard FormulationDCAX4 2D 2D Solid Axisymmetric Standard FormulationDCAX6 2D 2D Solid Axisymmetric Standard FormulationDCAX8 2D 2D Solid Axisymmetric Standard FormulationDCC1D2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactDCC1D2D 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactDCC2D4 2D 2D Solid Planar Convection/DiffusionDCC2D4D 2D 2D Solid Planar Convection/Diffusion with

Dispersion ControlDCC3D8 3D Solid Convection/DiffusionDCC3D8D 3D Solid Convection/Diffusion

with Dispersion ControlDCCAX2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactDCCAX2D 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactDCCAX4 2D 2D Solid Axisymmetric Convection/DiffusionDCCAX4D 2D 2D Solid Axisymmetric Convection/Diffusion with

Dispersion ControlDINTER1 1D 1D InterfaceDINTER2 2D 2D Interface PlanarDINTER2A 2D 2D Interface AxisymmetricDINTER3 2D 2D Interface PlanarDINTER3A 2D 2D Interface Axisymmetric Lagrange Vis DampingDINTER4 3D 3D InterfaceDINTER8 3D 3D InterfaceDS4 2D Shell HomogeneousDS8 2D Shell HomogeneousDSAX1 1D Axisym Shell HomogeneousDSAX2 1D Axisym Shell HomogeneousELBOW31 1D Beam in Space Curved with Pipe Section Standard FormulationELBOW31B 1D Beam in Space Curved with Pipe Section Ovalization OnlyELBOW31C 1D Beam in Space Curved with Pipe Section Ovaliz Only with

Approximated FourierELBOW32 1D Beam in Space Curved with Pipe Section Standard FormulationF2D2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactF3D3 2D Shell General Large Strain HomogeneousF3D4 2D Rigid Surface(LBC)FAX2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactFLINK 1D Link



GAPCYL 1D Gap Cylindrical True DistanceGAPSPHER 1D Gap Spherical Elas Slip Vis DampingGAPUNI 1D Gap Uniaxial Lagrange Vis Damping No SepINTER1 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactINTER1P 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactINTER1T 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactINTER2 2D IRS (shell/solid) Lagrange Hard ContactINTER2A 2D 2D Interface Axisymmetric Lagrange Hard ContactINTER2AT 2D 2D Interface Axisymmetric Lagrange Hard ContactINTER2T 2D IRS (shell/solid) Lagrange Hard ContactINTER3 2D 2D Interface Axisymmetric Lagrange Vis DampingINTER3A 2D 2D Interface Axisymmetric Lagrange Vis DampingINTER3AP 2D 2D Interface Axisymmetric Lagrange Vis DampingINTER3AT 2D 2D Interface Axisymmetric Lagrange Vis DampingINTER3P 2D 2D Interface Axisymmetric Lagrange Vis DampingINTER3T 2D 2D Interface Axisymmetric Lagrange Vis DampingINTER4 3D 3D Interface Lagrange Vis DampingINTER4T 3D 3D Interface Lagrange Vis DampingINTER8 3D 3D Interface Elas Slip Vis DampingINTER8T 3D 3D Interface Elas Slip Vis DampingINTER9 3D 3D Interface Lagrange Vis DampingIRS12 0D IRS (single node) Planar Elas Slip Vis DampingIRS13 0D IRS (single node) Planar Elas Slip Vis DampingIRS21 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactIRS21A 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactIRS22 1D ISL (in plane) Axisymmetric Lagrange Soft ContactIRS22A 1D ISL (in plane) Axisymmetric Lagrange Soft ContactIRS3 2D IRS (shell/solid) Elastic Slip Hard ContactIRS31 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactIRS32 1D ISL (in plane) Axisymmetric Lagrange Soft ContactIRS4 2D IRS (shell/solid) Lagrange Hard ContactIRS9 2D IRS (shell/solid) Lagrange Hard ContactISL21 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactISL21A 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactISL21AT 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactISL21T 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactISL22 1D ISL (in plane) Axisymmetric Lagrange Soft ContactISL22A 1D ISL (in plane) Axisymmetric Lagrange Soft ContactISL22AT 1D ISL (in plane) Axisymmetric Lagrange Soft ContactISL31 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactISL31A 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactISL32 1D ISL (in plane) Axisymmetric Lagrange Soft ContactISL32A 1D ISL (in plane) Axisymmetric Lagrange Soft ContactISP1 0D IRS (single node) Planar Elas Slip Vis DampingISP1T 0D IRS (single node) Planar Elas Slip Vis Damping




ISP3 2D Shell Thick HomogeneousISP4 2D Shell General Large Strain HomogeneousISP4T 2D Shell General Large Strain HomogeneousJOINTC 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactLS6 2D Shell Thin HomogeneousM3D3 2D Membrane Standard FormulationM3D4 2D Membrane Standard FormulationM3D4R 2D Membrane Reduced IntegrationM3D6 2D Membrane Standard FormulationM3D8 2D Membrane Standard FormulationM3D8R 2D Membrane Reduced IntegrationM3D9 2D Membrane Standard FormulationM3D9R 2D Membrane Reduced IntegrationMASS 0D MassMAX1 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactMAX2 1D ISL (in plane) Axisymmetric Lagrange Soft ContactMGAX1 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactMGAX2 1D ISL (in plane) Axisymmetric Lagrange Soft ContactPIPE21 1D Beam in XY Plane Pipe Section Standard FormulationPIPE21H 1D Beam in XY Plane Pipe Section HybridPIPE22 1D Beam in XY Plane Pipe Section Standard FormulationPIPE22H 1D Beam in XY Plane Pipe Section HybridPIPE31 1D Beam in XY Plane Pipe Section Standard FormulationPIPE31H 1D Beam in XY Plane Pipe Section Standard FormulationPIPE32 1D Beam in Space Pipe Section Standard FormulationPIPE32H 1D Beam in Space Pipe Section Standard FormulationR2D2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactR3D3 2D Rigid Surface(LBC)R3D4 2D Rigid Surface(LBC)RAX2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard ContactRB2D2 1D Rigid Line(LBC)RB3D2 1D Rigid Line(LBC)ROTARYI 0D Rotary InertiaS3 2D Shell Thick HomogeneousS3R 2D Shell General Large Strain HomogeneousS4 2D Shell General Large Strain HomogeneousS4R 2D Shell Thick HomogeneousS4R5 2D Shell Thin HomogeneousS8R 2D Shell Thick HomogeneousS8R5 2D Shell Thin HomogeneousS8RT 2D Shell Thick HomogeneousS9R5 2D Shell Thin HomogeneousSAX1 1D Axisym Shell HomogeneousSAX2 1D Axisym Shell HomogeneousSAX2T 1D Axisym Shell Homogeneous



Under some circumstances, the values of the option menus in MSC.Patran (Option 1 and Option 2) may be different than shown in the table. This is often the case when the ABAQUS element is one that is not directly supported by the MSC.Patran interface and the translator is making a “best guess” at which MSC.Patran element to choose. For many beam elements in the table, Option 1 is shown as “General Section”. Depending on the beam cross section type defined on the *BEAM SECTION or *BEAM GENERAL SECTION entry, Option 1 may be General Section, Box Section, Circular Section, Hexagonal Section, I Section, Pipe Section, Rectangular Section, or Trapezoid Section. For the 3D solid elements and shell elements in the table, Option 1 is shown as Homogeneous. Depending on the *SHELL SECTION or *SHELL GENERAL SECTION entry, Option 1 may be either Homogeneous or Laminate.

SAXA11 1D Axisym Shell HomogeneousSAXA12 1D Axisym Shell HomogeneousSAXA13 1D Axisym Shell HomogeneousSAXA14 1D Axisym Shell HomogeneousSAXA21 1D Axisym Shell HomogeneousSAXA22 1D Axisym Shell HomogeneousSAXA23 1D Axisym Shell HomogeneousSAXA24 1D Axisym Shell HomogeneousSPRING1 0D Grounded Spring LinearSPRING2 1D Spring Linear Fixed DirectionSPRINGA 1D Spring Linear Standard FormulationSTRI3 2D Shell Thick HomogeneousSTRI35 2D Shell Thin HomogeneousSTRI65 2D Shell Thick HomogeneousT2D2 1D Truss HybridT2D2E 1D Truss HybridT2D2H 1D Truss HybridT2D2T 1D Truss HybridT2D3 1D Truss Standard FormulationT2D3E 1D Truss Standard FormulationT2D3H 1D Truss Standard FormulationT2D3T 1D Truss Standard FormulationT3D2 1D Truss Standard FormulationT3D2E 1D Truss HybridT3D2H 1D Truss HybridT3D2T 1D Truss HybridT3D3 1D Truss Standard FormulationT3D3E 1D Truss Standard FormulationT3D3H 1D Truss HybridT3D3T 1D Truss Standard Formulation



MSC.Patran ABAQUS Preference Guided

CHAPTER

4 Read Results

■ Review of the Read Results Form

■ Translation Parameters

■ Select Results File

■ Data Translated from the Analysis Code Results File

■ Key Differences between Attach and Translate Methods

■ Delete Result Attachment Form

4.1 Review of the Read Results FormBy choosing the Analysis toggle located on the MSC.Patran main form, an Analysis form will appear.

Selecting Read Results as the Action on the Analysis form allows you to read results data into the MSC.Patran database from a text (“jobname”.fin) or binary (“jobname”.fil) ABAQUS results file, or to access ABAQUS results directly from an ABAQUS results output database (“jobname”.odb). Other forms that are accessible from here are used to define translation parameters and select the ABAQUS results file. These forms are described on the following pages.

MSC.Patran

hp, 2




Viewing

Note: Since the Abaqus DRA in the v2003 release will be integrated with Abaqus 6.3-1 libraries, users must make sure their ODB databases have been upgraded to 6.3 before attempting to attach to them from within MSC.Patran.

The procedure for upgrading them is part of Abaqus:

abaqus upgrade job=job-name odb=old-odb-file-name

4CHAPTER 4Read Results

Read Results FormRead Results defines the type of data to be read from the analysis code results file into MSC.Patran. The Object box may only be set to Results Entities.

When the Object selected is Result Entities, the model data must already exist in the database. No results can be read into MSC.Patran if the associated node or element does not already exist. Model Data only reads the model data that exists in the results file. Both will first read the model data, then the results entities. If Model Data or Both are selected, it is up to you to assure that there will not be any ID conflicts with existing model entities.

Defines the Jobname to be used for this job. The same jobname as was used for the Analyze menu should be used for the Read Results menu. This will allow MSC.Patran to load the results directly into the load cases that were used for the analysis. If this is not done, new load cases containing just these results will be created.

Defines the method of retrieving the results data. If Attach is selected, then only model data (if specified) is imported into the database, while results data is accessed directly from the Abaqus output database (ODB file). A job file is not generated if the Attach method is used.

If Translate is selected, then model and/or results data is imported into the database from the Abaqus results file (FIL file). For this method, a job file containing information for the results translation control is created, then submitted for translation. If Control File is selected, the procedure will stop as soon as the control file is generated. This is used primarily if the results translator is not located on a computer platform which MSC.Patran can talk with.

Also see section Key Differences between Attach and Translate Methods (p. 432).

Analysis

Read ResultsAction:

Current Analysis Code:ABAQUS

Result EntitiesObject:

AttachMethod:

Available Jobnames

smith

Jobname

Translation Parameters...

Select Results File...

Apply

Defines the results file to be read. This brings up a form which lists all files recognized as being analysis code results files.

Brings up the Translation Parameters form. This form defines any parameters used to control the results translation from the analysis code results file.

Flat File ResultsIn some cases, the translation will not be able to write the data directly into the MSC.Patran database. In those cases, a text file will be created containing all the instructions as to how this data is to be loaded into the database. This file can be transferred between computers if necessary, then read into the proper database using the File Import functionality. The full functionality of this form is described in Working with Files (p. 39) in the MSC.Patran Reference Manual, Part 1: Basic Functions.

/smith/../smith/.fminit2.0/smith/Exercises/smith/Mail/smith/Part_2_basic_functions/smith/Part_4_FEM

/smith/. [ ]Directories MSC.Patran Files

/okinawa/users/smith/*.flat*

Filter

Import File

- OK - Filter Cancel

Model Results

Import Analysis Type

MSC.Patran Results Flat FileP/FEA 2.5 .res FileMSC.Patran 2.5 .els File...MSC.Patran 2.5 .nod File...MSC.Patran 2.5 .dis File...

Import Results Type

ABAQUS

Current Analysis Code

1e-06

Zero Tolerance

Import

◆

◆

◆◆

◆◆

◆◆

◆◆

◆◆


4.2 Translation ParametersThe Translation Parameters form is used to define filters for the data being accessed.

Attach MethodThere is only one filter control for the Attach method, which indicates whether or not to allow access to the results invariants, as calculated by Abaqus.

Translate and Control File MethodsTranslation parameters for the Translate and Control File methods include the results filtering options based on the step number and the increment number. If none of the options are specified, then all the results will be translated. If only step is specified, then all the increments in that step will be translated. If only increment is specified, then that increment for the first step will be translated. If both step and increment are specified, then only the increment for that step will be translated.


Results Filtering Options:

OK Defaults Cancel

Include Results Invariants Specifies whether or not to include access to results invariants for vector and tensor results (e.g. Von Mises for tensor results or Magnitude for vector results). Default is off.


Step Number =

Increment Number =

Results Filtering Options:

OK Defaults Cancel

Step number and increment number for which the results will be filtered.

Superelement ID=

Superelement ID used to translate results for a particular superelement from the results file. A’’ or ’0’ means the results will be translated for all the nodes and elements in the results file. A ’-1’ means the results for the residual structure will be translated only.

4.3 Select Results FileThe Select file form allows you to select a file to be read. There are several features available. This form is brought up when you select the Select Results File button on the Read Results form. The default file filters will change depending on the Current analysis code in the Preferences menu.

/dallas/users/gamel/pf/forms/.

Select File

Filter is used when you have changed the definition in the Filter field and want the Directories and Available Files boxes to be updated.

Directories

OK Filter Cancel

Available Files

/dallas/users/gamel/pf/forms/./dallas/users/gamel/pf/forms/..

[ ]

Filter/dallas/users/gamel/pf/forms/*.odb

Selected Results File

Defines a filter to be used in selecting files to be displayed in the Available Files window. You may change the directory or default file extension by changing the data in this field.

The default extension is .odb for the attach Method and .fil for the Translate and Control File methods.

Lists all current directories. By double clicking on an entry in this box, or if you click on an entry, then on the Filter button at the bottom of the form, the directory in the Filter field and the Available Files are updated to show the files that fit the new filter.

Shows the list of files that fit the current filter. You may select any of these files by double clicking on any entry in this box.


Results Created in MSC.PatranFor direct ODB access (Attach method), no results are created in Patran, and all result types represented within the field output data in the ODB file are available for postprocessing.

The following table indicates all the possible results quantities which can be loaded into the MSC.Patran database during results translation (Translate method) from ABAQUS. The Primary and Secondary Labels are the items you select from the postprocessing menus. The Type indicates whether the results are Scalar, Vector, or Tensor. This determines which postprocessing techniques will be available to view this results quantity. Post Codes indicates which ABAQUS element post codes the data comes from. The Description gives a brief discussion about the results quantity. The Output Requests (p. 338) forms use the actual primary and secondary labels that will appear in the results. For example, if “Strain, Elastic” is selected on the Element Output Requests form, the “Strain, Elastic” is created for postprocessing.

Table 4-1 Results Quantities Loaded into MSC.Patran During Translation

Primary Label Secondary Label Type Results KeyAcceleration Generalized Rotational Vector 303

Generalized Translational Vector 303Rotational Vector 103Translational Vector 103

Base Motion Rotational Vector 304Translational Vector 304

Change in Length Components Tensor 21Concentrated Flux (Nodal) Layer or Section Points Scalar 206Concentrated Load Vector 106

Moment Vector 106Deformation Displacements Vector 101

Rotations Vector 101Displacements Generalized Displacements Vector 301

Generalized Rotations Vector 301Elastic Strain Components Tensor 25Energy Density Artificial Strain Energy Scalar 14

Creep Dissipation Scalar 14Plastic Dissipation Scalar 14Strain Energy Scalar 14Viscous Dissipation Scalar 14

Energy in Element Artificial Strain Energy Scalar 19Creep Dissipation Scalar 19Kinetic Energy Scalar 19Plastic Dissipation Scalar 19Strain Energy Scalar 19Viscous Dissipation Scalar 19

Total Energy Total Artificial Strain Energy Scalar 1999Total Creep Dissipation Scalar 1999Total Energy Loss at Impact Scalar 1999Total External Work Scalar 1999Total Kinetic Scalar 1999Total Plastic Dissipation Scalar 1999Total Strain Scalar 1999Total Viscous Dissipation Scalar 1999

Force and Shear Force Components Tensor 11Force Components Tensor 11Frequency Steady State Dynamics Scalar 2000Heat Flux (Nodal) Components Vector 10Heat Flux Components Vector 28

Magnitude Scalar 28Inelastic Strain Components Tensor 24Internal Flux (Nodal) Layer or Section Points Scalar 214Internal Forces Components at Element Node Vector 15Mass Flux Components Vector 39

Magnitude Scalar 39Modal Composite Damping Scalar 1980

Effective Mass Scalar 1980Eigen Values Scalar 1980Generalized Mass Scalar 1980Participation Factor Scalar 1980

Mag-Phase Strain Components Tensor 65Mag-Phase Stress Components Tensor 62Phase Angle Generalized Displacements Vector 305

Generalized Rotational Acceleration Vector 307Generalized Rotational Velocities Vector 306Generalized Rotations Vector 305Generalized Translational Accelerations Vector 307Generalized Translational Velocities Vector 306

Mag-Phase Reaction Force Vector 135Mag-Phase Reaction Moment Vector 135Mag-Phase Displacements Displacements Vector 111Mag-Phase Acceleration Rotational Vector 137Mag-Phase Velocity Rotational Vector 136Mag-Phase Displacements Rotations Vector 111Mag-Phase Velocity Translational Vector 136Mag-Phase Total Displacement

Translational Vector 112

Mag-Phase Total Acceleration

Rotational Vector 140

Mag-Phase Total Velocity Rotational Vector 139Mag-Phase Total Displacement

Rotational Vector 112

Mag-Phase Total Acceleration


Table 4-1 Results Quantities Loaded into MSC.Patran During Translation (continued)

Primary Label Secondary Label Type Results Key


Mag-Phase Total Velocity Translational Vector 139Mag-Phase Acceleration Translational Vector 137Plastic Strain Components Tensor 22

Equivalent Scalar 22Magnitude Scalar 22Yield Flag Scalar 22

Pressure and Shear Stresses

Components Tensor 11

RMS Strain Components Tensor 66RMS Stress Components Tensor 63Reaction Force Vector 104

Moment Vector 104Relative Displacements and Shear Slips


Rel. Normal & Tangential Displacements


Residual Flux (Nodal) Layer and Section Points Scalar 204Root Mean Square Reaction Forces Vector 134

Reaction Moments Vector 134Relative Displacements Vector 123Relative Rotational Accelerations Vector 131Relative Rotational Velocities Vector 127Relative Rotations Vector 123Relative Translational Velocities Vector 127Total Displacements Vector 124Total Rotational Accelerations Vector 132Total Rotational Velocities Vector 128Total Rotations Vector 124Total Translational Accelerations Vector 132Total Translational Velocities Vector 128Relative Translational Accelerations Vector 131

Strain Components Tensor 21Stress 1st Principal Scalar 12

2nd Principal Scalar 123rd Principal Scalar 123rd Stress Invariant Scalar 12Components Tensor 11Hydrostatic Pressure Scalar 12Maximum Stress in Section Scalar 16Mises Scalar 12Tresca Scalar 12

Temperature (Nodal) Layer or Section Points Scalar 201Temperature Element Centroidal Temperature Scalar 2Total Acceleration Rotational Vector 115

Translational Vector 115Total Displacement Rotational Vector 113




Total Velocity Rotational Vector 114Translational Vector 114

Total Creep Time Scalar 2000Dynamic Time Scalar 2000Heat Transfer Time Scalar 2000Soils Time Scalar 2000Time Scalar 2000

Velocity Generalized Rotational Vector 302Generalized Translational Vector 302Rotational Vector 102Translational Vector 102

Creep Strain Components Tensor 23Equivalent Scalar 23Magnitude Scalar 23Yield Flag Scalar 23




4.4 Data Translated from the Analysis Code Results FileWhen reading model data from an ABAQUS results file, the following table defines all the data which will be created. No other model data is extracted from the results file. This data should be sufficient for evaluating any results values.

Item Results Key Description

Nodes 1901 Node IDNodal Coordinates

Elements 1900 Element IDNodal Connectivity

Groups n/a, ODB access only

Group nameNode and Element referencesGroups are generated for each part instance, as well as for each node and element set.

4.5 Key Differences between Attach and Translate MethodsThe most obvious difference between direct ODB access (Attach method) and results translation (Translate method) is that the results are not imported into the Patran database in the case of the former, while they are for the latter. Direct access avoids redundancy and saves disk space, while Translation uses more disk space, but takes less time to retrieve results for postprocessing.

The following sections describe other differences that users should be aware of, before deciding which method to use.

Result Type Naming ConventionsThe names used for the result types within an ODB attachment come directly from the field output description fields of the ODB database. Using the “direct access” philosophy of bringing the data in as-is, there is no attempt to map those names to the same names used by the Translate method (listed in Table 4-1 Results Quantities Loaded into MSC.Patran During Translation).

Therefore, direct ODB access will use Abaqus terminology exclusively in generating the result type names. The primary name is equal to the field output description field, while the secondary name is the field output key. For example, the stress tensor result type is “Stress components, S”, where “Stress components” is the field output description, and “S” is the field output key.

Vector vs. Scalar Moment and Rotational ResultsFor results such as reaction moments or rotational displacements, the ODB database saves space by only storing results for the non-zero component, whenever possible. So, if non-zero values for moments only occur in the Z component, then the ODB database stores it as a scalar result (e.g. key RM3). However, the Translate method will import the results as vector results, with the X and Y values always being zero.

This difference may cause confusion when comparing translated results against direct ODB access via the quick or fringe plot operations, where reaction moments and rotational displacements are concerned. The default “invariant” for fringe plots of vector data is “Magnitude”, which is always a positive value. If the magnitude of the translated vector data is compared against the ODB scalar data, then they will not always match (all negative data from the ODB access will be flipped positive in the translated plot). To compare “apples with apples”, one must display the appropriate component (Z from our example) from the translated case, and compare that against the scalar (key RM3) from the direct ODB access case.

Reaction ForcesDuring translation, only non-zero reaction force data is imported. Direct ODB access, on the other hand, returns zero vectors for any nodes that do not have any reaction forces. This makes no difference for the display of reaction force vectors; however, if one displays a fringe plot distribution of the reaction forces, the fringe plots vary between translation and direct ODB access dramatically. The translation plot is all black, with only the min/max values displayed on a hidden line plot; while the ODB fringe plot shows a color distribution from the zero values (white over most of the model) to the non-zero values. For the latter, the contours only vary over elements with nodes having non-zero reaction forces.


4.6 Delete Result Attachment FormThe following form may be used to remove a results attachment, created via the Attach method, from the database.

Use the Delete action and Result Attachment method to remove a direct ODB access attachment from the Patran database. Any model data that was imported during the original attachment remains intact, while the results from the attachment will no longer be available, after the file is detached.

Select the ODB output database(s) to be detached.

Analysis

DeleteAction:

Current Analysis Code:ABAQUS

Result AttachmentObject:

Existing Files:

Apply

A1:/tmp/data/mymodel.odb


CHAPTER

5 Files

■ Files

5.1 FilesThere are several files associated which are either used or created by the MSC.Patran ABAQUS Application Preference. The following table describes each file and how it is used. In the definition of the file names, any occurrence of “jobname” would be replaced with the jobname the user assigns.

File Name Description

jobname.db This is the MSC.Patran database from which the model data is read during an analyze pass, and into which model and⁄ or results data is written during a Read Results pass.

jobname.jbmjobname.jbr

These are small files used to pass certain information between MSC.Patran and the Application Preference during translation. You should never have need to do anything directly with these files.

jobname.inp This is the ABAQUS input file created by the interface.

jobname.fil This is the ABAQUS results file which is read by the Read Results pass.

jobname.flat This file may be generated during a Read Results pass. If the results translation cannot, for any reason, write data directly into the jobname.db MSC.Patran database, it will create this jobname.flat file.

jobname.msg These message files contain any diagnostic output from the translation, either forward or reverse.

AbaqusExecute This is a UNIX script file which is called on to submit both the forward PAT3ABA translation program, as well as to submit ABAQUS after translation is complete. This file should be customized for your particular site installation.

ResultsSubmit This is another UNIX script which is called on to submit the reverse, ABAPAT3 translation program. This file should also be customized for your particular site.

load_abaqus.ses This file is only used when creating a new MSC.Patran template database. This file loads in all the element, material, MPCs and loads and boundary condition tables for the MSC.Patran ABAQUS product.


CHAPTER

6 Errors/Warnings

■ Errors/Warnings

6.1 Errors/WarningsThere are several error or warning messages which may be generated by the MSC.Patran ABAQUS Application Preference.

Message Description

Fatal This error stops the translation and exits the Preference.

Warning Some expected action did not execute. Translation continues. Check the .msg file.

Information General Messages about the translation.

4

I N D E XMSC.Patran ABAQUS Preference Guide

I N D E XMSC.Patran ABAQUS Preference

Guide
Numerics
1D interface, 87, 95, 1362D interface, 92, 952D orthotropic, 722D orthotropic lamina, 462D solid, 91, 953D anisotropic, 47, 753D anisotropic thermal, 793D interface, 94, 95, 2883D orthotropic, 46, 733D orthotropic thermal, 78

Aabapat3, 3ABAQUS, 3abaqus.plb, 3, 4AbaqusExecute, 436AbaqusSubmit, 4, 6acceleration, 309, 316Acommand, 6alpha, 52amplitude, 11analysis, 330anisotropic, 257arbitrary beam, 115area moment I12, 114average shear stiffness, 233axisymmetric 2D interface, 257axisymmetric ISL, 140axisymmetric shell, 86, 95, 134

laminate, 135axisymmetric solid, 252

Bbase motion, 12, 365

beam, 21, 25circular, 110cross-sectional shape, 110elements, 13general section, 9, 106, 113hexagonal, 110in space, 84in XY plane, 83section, 9

bias parameter, 370bifurcation buckling, 340, 349, 350bilinear, 21, 29boundary, 11, 12box beam, 108buckle, 12

CC biquad, 22, 32cap

hardening, 10, 69plasticity, 10

centrifugal force, 315centroid, 9centroid coordinate, 114CETOL, 391CFLUX, 12change material status, 45circular beam, 110

solid, 110clearance zero damping, 103, 105, 137clearance zero-pressure, 103, 105, 137CLOAD, 12combined creep test data, 62combined test data, 10COMP, 371composite, 47, 80, 295conductivity, 10, 77, 79constitutive models, 45control, 95convection, 95, 309, 323convection/diffusion, 296, 298

INDEX

coordinate frames, 16Coriolis force, 315correlation, 12, 377creep, 10, 46, 47, 70, 71, 342, 390, 391creep test data, 62cubic hybrid, 83, 84cubic initially straight, 84cubic interpolation, 83, 84curved pipe, 117

Ddamper, 85damping, 10, 373, 377

direct, 363Rayleigh, 364zero clearance, 103, 105, 137

dashpot, 9elements, 14

DASHPOT1, 100, 101DASHPOT2, 129, 131DASHPOTA, 128, 130deformation plasticity, 10, 46, 64degree-of-freedom, 23DELTMX, 402density, 10, 49, 58, 77, 78, 79DFLUX, 12diffusion, 95DIRECT, 382, 386direct linear transient, 340, 352, 353direct steady state dynamics, 340, 355, 356direct text input, 335, 339dispersion, 95displacement, 309, 312DLOAD, 12Drucker-Prager, 10, 68dynamic, 12

Eeigenvalue, 340eigenvalue buckling, 340EL

file, 12, 338print, 12, 338

elastic, 10, 45, 46, 47, 49, 72, 73, 74elastic slip, 103, 105, 137, 139, 141, 143, 146,

149, 151, 153, 256, 258, 260, 289hard contact, 83no separation, 83soft contact, 83vis damping, 83vis damping no separation, 83

elbow, 22, 34elements, 14MPC, 34

ELBOW31, 34, 117ELBOW31B, 117ELBOW32, 34, 117element, 9, 19

definition, 9matrix output, 12, 338properties, 81

elementsbeam, 13dashpot, 14elbow, 14gap, 14heat transfer, 15mass, 14membrane, 14rigid surface contact, 15rotary inertia, 14shell, 14slide line contact, 15small sliding contact, 14spring, 14

ELSET, 9, 327end step, 11energy

file, 12, 338print, 12, 338

engineering constants, 73equation, 11, 21, 24ERRTOL, 62, 63expansion, 11, 58explicit, 21

Ffatal, 438field properties tolerance, 332

4INDEX

fileEL, 12, 338energy, 12, 338format, 12, 338modal, 12, 338node, 12, 338output definition, 12

film, 12finite elements, 17flat file results, 424force, 309, 312Frac Clearance Const Damping, 103, 105, 137fraction of critical damping, 50, 96, 97, 363frequency, 12, 370frequency scale, 355, 377, 398friction, 9, 102Friction in Dir_1, 103, 105Friction in Dir_2, 105

Ggap, 10, 86

conductance, 10, 293, 299cylindrical, 132elements, 14radiation, 10, 293, 299spherical, 133uniaxial, 132

GAPCYL, 132GAPSPHER, 133GAPUNI, 132general beam, 106, 113general large strain, 246general thick, 241general thick shell

laminated, 243general thin, 238general thin shell

laminated, 240gravity loads, 315grounded damper, 83grounded spring, 83group, 327

HHAFTOL, 386, 387hard contact, 103, 105, 137, 139, 141, 143, 146,

149, 151, 153, 256, 258, 260, 289harmonic loading, 341HCRIT, 157, 261

heat conductance, 293, 297, 299heat flux, 309, 324heat source, 309, 324heat transfer, 12

elements, 15hexagonal beam, 110Hilber-Hughes-Taylor operator, 340host, 6hourglass stiffness, 10, 235

bending, 233, 236, 239, 242, 245, 247membrane, 233, 236, 239, 242, 245, 247normal, 233, 236, 239, 242, 245, 247

hybrid, 83, 84, 91, 248, 287integration, 91modes, 91

hyperbolic, 71sine law, 71

hyperelastic, 11, 45, 51, 52, 53, 54, 55, 56, 57, 59

hyperfoam, 11, 58

Iimport input file, 405INC, 386, 394incompatible modes, 91, 248, 249, 251, 252,

253, 287increment, 333inertia

rotary, 10inertial load, 309, 315information, 438initial conditions, 11initial temperature, 309, 325initial velocity, 309, 315input data, 310interface, 10, 102IRS, 88, 93, 102, 104

axisymmetric, 150beam/pipe, 152planar, 148shell/solid, 259single node, 83

IRS12, 102IRS13, 104I-section, 111ISL, 87, 88isotropic, 45, 49, 66

thermal, 77

INDEX

Jjobname.db, 436

Kkinematic, 67

constraints, 11

LLagrange

hard contact, 83no separation, 83soft contact, 83vis damping, 83vis damping no separation, 83

Lamina, 72laminate, 47, 80large strain, 244latent heat, 11, 77linear, 21, 27linear damper, 100, 128, 129

grounded, 100linear dashpot coefficient, 100, 128, 129linear spring, 98, 124, 125

grounded, 98linear spring coefficient, 98, 124, 125linear static, 340, 343, 344linear surf-surf, 21linear surf-surf MPC, 27linear surf-vol, 21linear surf-vol MPC, 27, 28linear vol-vol, 21linear vol-vol MPC, 29link, 21, 26, 95load cases, 326, 337loading definition, 12loads and boundary conditions, 307L-section beam, 119

Mmass, 10, 83, 96

elements, 14mass proportional damping, 50mass proportionality factor, 96, 97

material, 10change status, 45definition, 10orientation, 11temperature dependent, 45

materials, 43form, 44

maximum friction stress, 103, 105, 137maximum negative pressure, 103, 105, 137maximum overclosure, 103, 105, 137membrane, 92, 254

elements, 14Mises/Hill, 65, 66, 67modal

damping, 12dynamic, 12file, 12, 338print, 12, 338steady state dynamics, 341

modal linear transient, 340, 359, 360model translation tolerance, 332modified Drucker-Prager/Cap, 69Moony Rivlin, 53MPC, 11

elbow, 34explicit, 24linear surf-surf, 27linear surf-vol, 27, 28linear vol-vol, 29pin, 35quad surf-surf, 30quad surf-vol, 30, 31quad vol-vol, 32revolute, 37rigid fixed, 25rigid pinned, 26slider, 33SS bilinear, 41SS linear, 40SSF bilinear, 42tie, 36universal, 39V Local, 38

multi-point constraints, 20

Nnatural frequency, 340, 346, 347Neo Hookean, 53Newton’s method, 341NLGEOM, 394

4INDEX

no compression, 11no sliding contact, 103, 105, 137no tension, 11node, 9, 18

definition, 9file, 12, 338print, 12, 338

nondeterministic continuous excitation, 341nonlinear damper, 101, 130, 131

grounded, 101nonlinear dashpot coefficients, 101, 130, 131nonlinear spring, 99, 126, 127

grounded, 99nonlinear spring coefficient, 99, 126, 127nonlinear static, 341, 382, 384nonlinear transient dynamic, 342, 386, 387NSET, 9, 18, 327

Oobject tables, 312Ogden, 51, 52, 54, 55, 57, 59Ogden strain energy potential, 55open beam, 121optional controls, 334orientation, 11, 16, 80

system, 233output requests, 338overlay, 333

Pparallel ISL, 142pat3aba, 3peak response, 341perfect plasticity, 65pin, 35pin MPC, 35pipe beam, 111planar

2D interface, 255ISL, 138test data, 11

plane strain, 248, 249plane stress, 251plastic, 11, 46, 47, 65, 66, 67, 68, 69point mass, 96Poisson parameter, 107, 109, 114, 116, 120,

122Poisson’s ratio, 49, 58polynomial, 51, 53, 54, 56

potential, 11power spectral density, 378preferences, 8

analysis, 8preprint, 12prescribed boundary conditions, 12pressure, 309, 313pressure zero clearance, 103, 105, 137pre-tension, 322print, 12, 338

definition, 12EL, 12, 338energy, 12, 338modal, 12, 338node, 12, 338

procedure definition, 12Prony, 61, 342property definition, 9PSD-Definition, 11

Qquad surf-surf, 22quad surf-surf MPC, 30quad surf-vol, 22quad surf-vol MPC, 30, 31quad vol-vol, 22quad vol-vol MPC, 32quadratic, 22, 30

Rradial ISL, 145radiation, 293, 297, 299Ramberg-Osgood model, 64random response, 12random vibration, 341, 377, 378, 379rate dependent, 11Rayleigh damping, 364read, 333read input file, 405read results, 422, 423read temperature file, 343rebar 2D, 263rectangular beam, 112reduced integration, 91, 248, 249, 251, 252,

253, 254, 287reference temperature, 50relaxation test data, 63response spectrum, 12, 341, 371, 372, 373, 374restart, 11

INDEX

restart parameters, 333results file

select, 426ResultsSubmit, 5, 436revolute, 22, 37revolute MPC, 37rigid

fixed, 21pinned, 21

rigid fixed MPC, 25rigid line, 89

LBC, 158rigid pinned MPC, 26rigid surf, 89, 93rigid surface, 9, 102, 104, 148, 150, 152, 154,

155, 156, 157, 259, 261axisymmetric, 156Bezier 2D, 157Bezier 3D, 261cylindrical, 155LBC, 262segments, 154

rigid surface contactelements, 15

RIKS, 382ROTARI, 97rotary inertia, 10, 83, 97

elements, 14rough (no slip) friction, 103, 105, 137, 139,

141, 143, 147, 149, 151, 256, 258, 260, 289rough parameter, 153

SScratchdir, 6section point coordinate, 114shear centroid coordinate, 114shear factor, 107, 109, 114, 116, 120, 122shear test data, 11shell, 91, 95

elements, 14general section, 10, 241section, 10, 235

simple shear test data, 11slide line, 9, 88, 147slide line contact

elements, 15slider, 22, 33slider MPC, 33sliding friction, 103, 132, 133, 136, 139, 141,

143, 146, 149, 151, 153, 255, 260, 288

slip tolerance, 103, 105, 137small sliding contact

elements, 14smooth parameter, 147, 154, 155, 156soft contact, 103, 105, 137, 139, 141, 143, 146,

149, 151, 153, 256, 258, 260, 289solid, 94, 95, 287solid section, 10, 248, 249solution types, 340specific heat, 11, 77, 78, 79spectrum, 11spring, 10, 85

elements, 14SPRING1, 98, 99SPRING2, 125, 127SPRINGA, 124, 126SS bilinear, 22, 23, 31, 41SS bilinear MPC, 41SS linear, 21, 23, 28, 40SS linear MPC, 40SSF bilinear, 23, 42SSF bilinear MPC, 42standard formulation, 83, 84, 91, 95static, 12, 310steady state dynamics, 12, 366, 367steady state heat transfer, 342, 401steady state response, 340step, 11, 333

creation, 336initialization, 11selection, 404termination, 11

stiffnesshourglass, 10transverse shear, 10

stiffness in stick, 103, 105, 137stiffness proportional damping, 50strain, 70strain dependent material, 54strain energy potential, 52SUM, 371superelement ID, 425surface contact, 10, 257

Ttabular formula, 60tangent elastic moduli, 340TAUMAX, 133, 137, 139, 141, 143, 146, 149,

151, 153, 256, 258, 260, 289

4INDEX

temperature, 12, 309, 313thermal, 309, 323

temperature dependent material, 45test data

combined, 10creep, 62creep combined, 62Ogden, 57planar, 11relaxation, 63shear, 11simple shear, 11uniaxial, 11volumetric, 11

thermal 1D interface, 293thermal axisymmetric shell, 291

laminated, 292thermal expansion coefficient, 50, 58thermal interface

planar, 297solid, 299

thermal link, 290thermal planar solid, 296thermal shell, 294

laminated, 295thermal solid, 298thermal strain, 50thick shell, 235

laminated, 237thin shell, 232

laminated, 234tie, 22, 36tie MPC, 36time, 70time dependent loading, 340time power law, 70torsional constant, 114, 122transform, 9, 16transient, 311transient heat transfer, 342, 402, 403translation parameters, 332, 425transverse shear stiffness, 10, 110, 113, 115trapezoid beam, 112true distance, 86truss, 85, 123TYPE, 371, 377

Uuniaxial test data, 11universal, 23, 39

universal MPC, 39UNSYMM, 334

VV Local, 22, 38V Local MPC, 38velocity, 309, 316VISCO, 12, 390viscoelastic, 11, 45, 46, 47, 60, 61, 62, 63

frequency domain, 342, 398time domain, 342, 394, 395

volumetric pressure, 58volumetric test data, 11, 58

Wwarning, 438warping constant, 122wavefront minimization, 11write, 333

XXY plane

definition, 114, 116

Yyield, 11Young’s modulus, 49

INDEX

Documents

CONTENTSgc.nuaa.edu.cn/hangkong/doc/ziliao/MSC_PATRAN/MSC... · CONTENTS MSC.Patran ABAQUS Preference Guide ... - Beam Shape Display in Plane/Space, 109 ... The core of the product