COPY NO.

TECHNICAL REPORT 4980

INTERGRATED PROJECTILE1 SYSTEMS SYNTHESIS

MODEL (IPSSM)

L. F. NICHOLSD. LEWIS

AUGUST 1976

APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED.

PICATINNY ARSENALDOVER, NEW JERSEY

The findings in this report are not to be construedas an official Department of the Army position.

DISPOSITION

Destroy this report when no longer needed. Do notreturn to the originator.

, , 'g

UNCLASSIFIEDSECURITY CLASSIFICATION OF THIS PAGE ( hen DM. Entered)

REPORT DOCUMENTATION PAGE READ INSTRUC71ONSBEFORE COMt=LETMG FORMI- REPORT NUMBER 1. GOVT A= 3. RECIPIENT'S CATALOG NUMER

Technical Report_90q 54. TITLE (ndSube,/, ( S. TYPE OF REPORTa PERIOD COVERED

Integrated Projectile Systems (Synthesis Model (IPSSM), - .Interim

I -S. PlERFORMING OPU .FR-vef _ MBER

7. AUTHOR(*) S. CONTRACT OR GRANT NUMBER(.)

L.F. 'NicholsD,. Lewis/ ]-

5. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT. PROJECT TASK

Picatinny Arsenal A UNT-,/_/_

SARPA-ND-CDover, New Jersey

11. CONTROLLING OFFICE NAME AND ADDRESS 2AzOTDELAu~g 6.

:,,. 28414. MONITORING AGENCY NAME ADDRESS(If dlfferent free, Co-irotlhig Office) IS. SECURITY CLASS. (of thl report)

UNCLASSIFIED

ISO. DECL ASSIFICATION/OOBNGRAOINGSCHEOULE

14. OtSTB#IITIOM STATEMENT (ol gAl. Report)

Approved for public release; distribution unlimited.

17. DISTRIRUTIOM STATEMENT (of I . absert entered In Block 2", If EI lorn? frow. Report)

1I. SUPPLEMENTARY NOTES

It. KEY WORDS (Cnetluie an reverse side If necesary and Identify by block numeber)

Computer modeling Exterior ballistics Program modulesProjectile design Aerodynamic properties Interactive teletype modeIPSSM Lethal area effectiveness Batch modeI terior ballistics Trajectory calculations Weapon system modeling

""TRACT (Cenetsmae an revers elds It ecesuy and Idontll by block tumer)

A Computer model called IPSSM (Integrated Projectile Systems SynthesisModel) is being developed for use in the preliminary design of large caliberprojectiles. Complete capabilities of the interim version of this modelare detailed, and instructions are given for users of the program in both theinteractive teletype and batch modes. The use of this initial version of IPSSMill determine additional modules to be added as well as refinements in the

over-all operation of the system.

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ACKNOWLEDGEMENTS

The original idea and many innovative techniques for this projectwere conceived by Forrest McMains in a pilot version of the executiveprogram. A special note of thanks is also due to Frank Morehouse,Mike Siegal and Cindy Lou Fancy, each of whom devoted numerous hoursincorporating suggested programming improvements into IPSSM, attemptingto make IPSSM as uncomplicated as possible for future users of thesystem. Also to be acknowledged is the invaluable technical programmingexpertise provided by Ed Loniewski of PAD and the very helpful editorialassistance of Frank Morehouse and John Reformato in preparing thisdocument for publication.

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II I I II

TABLE OF CONTENTSPage No.

Objectives and Approach 1

Background 1

Present Status 3

User Instructions 7

A. Data Preparation 7

1. General 7

2. Data Base Generation Using IPSDATA 7

3. Multiple Value Option 8

4. Format and Use of P, L and N Numbers 9

5. Data Base Entry Using the Executive Program 10

B. Instructions for TTY Mode 10

1. General 10

2. Explanation of "INPUT/OUTPUT OPTION LIST" 11

a. Teletype Option 11

b. Data Base Transfer Option 11

c. Batch Terminal Option 20

d. Central Site Option 20

3. IPSSM Short TTY Inputs 20

C. Instructions for Batch Mode 21

1. General 21

2. Control Cards 21

3. Batch Instruction Cards 23

4. Storage Options 25

Application Programs and Description 26

A. Static Properties and Stability Calculations (WT) 26

B. Generation of Aerodynamic Coefficients (SP) 28

C. Interior Ballistics (IB) 29

D. Exterior Ballistics (AR) 29

E. Terminal Effectiveness Calculations (LA) 31

F. 6-D Trajectory (TR) 32

G. Recoil Mechanism Design (RM) 33

H. Sabot Design (SD) 33

I. Heppner Interior Ballistics (IH) 34

Sample Input for Initial Data Base Generation 35

Sample Test Cases and Setup 41

A. Introduction 41

B. TTY Examples 41

1. General Information 41

2. Representative TTY Examples 42

C. Batch Examples 58

1. General Input Information 58

2. Representative Batch Examples 58

References 61

Tables

I Specific TTY Instructions 12

t .5.

Figures

1 Executive Module Operation (IPSSM) 4

2 Input - Output Interface 5

3 IPSSM Flow Diagram (HE Version) 6

Appendixes

Al Static Properties Calculation Program (WT) 63Key Variable Input

A2 Static Properties Calculation Program (WT) 67Format of Shell Item Inputs

B Aeroballistic Coefficients Program (SP) 71Key Variable Input

C Interior Ballistics Program (IB) 75Key Variable Input

Dl Exterior Ballistics Program (AR) 79Key Variable Input

D2 Exterior Ballistics Program (AR) 89List of Tables

E Terminal Effectiveness Program (LA) 93Key Variable Input

F 6-D Trajectory Program (TR) 101Key Variable Input

G Recoil Mechanism Design Program (RM) 111Key Variable Input

H Sabot Design Program (SD) 117Key Variable Input

I Heppner-Interior Ballistics (IH) 121Key Input Variables

J IPSDATA Sample Output 125

K Sample TTY and Batch Results 137

L unabbreviated Output at the Teletype 275

Distribution List 279

OBJECTIVES AND APPROACH

The objective of this program is to develop a complete computermodel for use in the preliminary design of large caliber projectiles.This model, called IPSSM (Integrated Projectile Systems SynthesisModel), is a set of computer program modules and subroutines integratedin such a manner as to provide a realistic, interactive, computationaltool for engineers and designers engaged in the development of pre-liminary design information for projectiles. The model described inthis report includes the capability of performing extensive calcula-tions necessary to formulate projectile designs. Computations includeinterior and exterior ballistics, static shell property calculations,aerodynamic properties generation, lethal area effectiveness, 6-Dtrajectory calculations, recoil mechanism design, and sabot design.

The general approach in the complete development of the modelcalls for the selection and modification of existing computer programsto accomplish specific calculations as well as the identification ofprogramminq tasks required to complete the model. The essentialingredient of IPSSM is its common data base and a well coordinatedand integrated set of computer programs which are not only extractinginformation from previously run programs within the system but arealso generating specific data for subsequent use by other programs.These programs will either continue or modify the design process orbe used for optimization. They are modular in nature so as to facili-tate future improvements or replacements of the design programs.Over-all control of the model is accomplished by the user through theexecutive program.

The objective of this report is to provide an initial user'smanual for the IPSSM System currently available. Additional features,updates, and modifications will be accomplished as use is made ofthis initial version of IPSSM.

BACKGROUND

In May 1970, DARCOM (AMC) initiated a feasibility study directedtoward weapon system computer modeling which would provide preliminarydesign parameters for tactical missile weapon system concepts. AfterDARCOM (AMC) had presented the concept and preliminary comments ofsubordinate commands to the CAD-E Council in October 1970, the IWSSM(Integrated Weapon System Synthesis Model) Ad Hoc Working Group ofthe Council was established to study the concept in more detail.After a six-month effort, the working group concluded that such asystem was both feasible and desirable, but initially it should belimited to the construction of a number of computer models, each

1i| I

addressing a particular military commodity. It was considered toolarge an undertaking to develop one model that would handle allcommodity designs such as guns, projectiles, missiles, aircraft,vehicles, etc.

The recommendation of the IWSSM Working Group was that eachcommand submit a Program Data Sheet outlining a proposed activitydirected toward a specific commodity. The Integrated ProjectileSystem Synthesis Model (IPSSM) Program was established at PicatinnyArsenal to address the preliminary design of large caliber projectilessuch as artillery and mortar rounds.

The Picatinny IPSSM program was funded as a CAD-E task on 1 April1972. A substantial initial effort was directed toward a survey ofexisting computer programs in use at Picatinny and other governmentagencies which would be suitable for incorporation into the IPSSMSystem. Major areas of design interest were identified by systemengineers,and computer programs within each area were identified.The proqrams were examined for (1) adequate documentation and technicaladaptibility within the design area, and (2) adaptibility of input andoutput data formats that would be consistent with the over-all re-quirements of the executive program.

Existing computer programs to determine static and aerodynamicshell properties, perform interior and exterior ballistics calculations,compute lethal areas, do 6-D trajectory calculations, and design recoilmechanisms and sabots were selected. Source listings were obtainedand put into update format, and proper operation was verified withtest cases. Each of the nine codes (Weight, Spinner, Aerol, InteriorBallistics, Lethal Area, 6-D Trajectory, Recoil Mechanism, SabotDesign and Heppner-Interior Ballistics) has been made operationalunder both the interactive teletype (TTY) and batch mode to facilitateentry and exit from the executive program. Major effort was devotedto the design and checkout of the preliminary IPSSM executive program.The system has been used on a trial basis and is now ready for generaluse to determine its adequacy as a design tool.

Several user sessions have been conducted to acquaint engineersand scientists involved in projectile design and evaluation withthe operation of the current IPSSM system. These sessions willcontinue as more personnel become involved. As a result of theseinitial meetings, several important modifications were made to improvethe operational capabilities of the system. For example, an optionalabbreviated input format can now be utilized to quicken system responsein the TTY mode. Testing of user responses in the TTY interactivemode has also been incorporated to avoid program abort as a result of

2

trivial user typing errors. In addition, an independent computerprogram (IPSDATA) has been written to simplify the establishment ofinitial data base files. Output from this program provides the basisfor accurate checking of input data files.

PRESENT STATUS

The present IPSSM System can execute nine applications programsfrom either batch or teletype (TTY) mode. These programs performthe following computations: (1) Static Properties Calculations, (2)Generation of Aerodynamic Coefficients, (3) Interior Ballistics, (4)Exterior Ballistics, (5) Lethal Area Computations, (6) 6-D TrajectoryCalculations, (7) Recoil Mechanism Design, (8) Sabot Design, and (9)Heppner-Interior Ballistics.

In TTY mode, the executive program contains options for examiningand modifying common data base information. In both modes the programallows the user to modify the data base variables, to store the modi-fied data base in a new permanent file if desired, and to run linkedcases of selected variables to facilitate the execution of parametricanalyses. Special abbreviated output can be generated and storedautomatically for later examination at the TTY. Options also existfor directing entire input/output for each set of application runsto the user's batch terminal or to the central site. The system isalso capable of generating input data in the format required forrunning the graphics projectile measurement program (PROMS) (Refer-ence 2). Output from PROMS can then be entered into the common database for subsequent computations within the IPSSM System. Figure 1illustrates the executive module operation in the batch or TTY mode.Figure 2 shows the input-output interface scheme utilized withinIPSSM. Although this chart shows the technique for the exteriorballistic interface, the same system has been applied for all appli-cation programs. Figure 3 shows the latest flow diagram for IPSSM.The small boxes between the applications programs represent theinput-output interfaces controlled by the executive program. Dataanalysis and optimization will be incorporated to a much greaterextent as directed by future user requirements.

Options have also been installed to allow either the currentdata base to be automatically updated with the results of the currentprogram or to have a separate and distinct new data base created withthe same generated results.

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USER INSTRUCTIONS

A. Data Preparation

1. General

In order to execute the IPSSM Program, a data base containing thegeneric characteristics of the projectile to be analyzed must beavailable. This is established initially through the use of a programcalled IPSDATA (Cycle 5). Subsequent to this, data may be added,deleted, or changed either by rerunning IPSDATA with the modifieddata base cards or by using IPSSM's executive program, which is calledIPSM (Cycle 5). The latter option may be accomplished through eitherthe batch or the teletype (TTY) mode.

2. Data Base Generation Using IPSDATA

The program called IPSDATA was written for easy cataloging andchecking of an entire data base. Use of the following deck of cardswill result in your data base being entered on whichever permanentfile you specify:

(JOBCARD),CM75000.

(COMMENT CARD)

ATTACH,IPSM,IPSD,CY=5,ID=NICHOLS,MR=1

IPSM.

(7/8/9 CARD)

(DATA BASE CARDS)

(6/7/EY9 CARD)

The first data base card contains the title to be associated withyour data base. The second card contains the cycle number followedby a comma and the permanent file name (up to 10 alpha-numerics) inwhich you wish your data base to be stored. These two cards arefollowed by the key variable data cards. Each such card is identifiedby its three-letter symbol in the first three columns. The fourthcolumn is blank. The value of the variable is then entered in freefloating point format (cannot be integer) on the card anywhere in thenext ten columns. Following the last key variable data card is a

7

card with the word "END" punched in the first three columns (seeSample Input for Initial Data Base Generation).

The key variable data are followed by the table entries requiredto execute the AERO 1 (AR), WEIGHT (WT), and LETHAL AREA (LA) Programs.Format for entering these tables is described in the discussions ofprograms in " Application Programs and Descriptions".

"Sample Input for Initial Data Base Generation" contains an ex-ample of a set of data base cards for the M106 8-inch Projectilewhich permits execution of the first five programs listed on page 3.Other data sets were generated in a similar manner to execute theremaining programs currently in operation within IPSSM. Thesesample data can be used to test the operation of each applicationprogram within IPSSM. (See "Sample Test Cases and Setup" fortypical batch and TTY runs). These files will remain in thesystem as a permanent file for users to become familiar with theIPSSM System.

When establishing an initial data base, it should be noted thatIPSDATA will store the data base in the requested cycle under apermanent file name of the form PFNXX, where PFN is the particularpermanent file name you have selected, and XX is the symbol for theparticular application program being run (AR, WT, LA, etc.). IPSDATAattaches these last two letters automatically by determining whatdata are being catalogued in that particular run. For example, iffor an initial run of IPSDATA, the user includes data for the AR andLA programs and specifies that he wishes the data base stored inJOHN. cy=5, IPSDATA will automatically create two data bases: JOHNAR,cy=5 will contain the data needed to run the AR program and JOHNLA,cy=5 will contain the data needed to run the LA program. NOTE:This automatic appending of the two-letter program symbol i-onlydone when running through IPSDATA; any subsequent modification of databases using the executive program IPSH will recatalog the modified database exactly as specified at the time of modification.

3. Multiple Value Option for Running Parametric Studies

As part of the general data base setup within IPSSM, a provisionexists for entering up to six values for each key variable. Such anoption can be useful in preparing combinations of runs where keyvariables take on different values and, in addition, may require thesimultaneous change of other key variables. The technique for enteringsuch data is described in subsequent paragraphs. The symbols, P, L,and N will aid in this description. These symbols can be associatedwith the words "permutation", "link", and "number", respectively.

8

77

This system is not unique to IPSSM. It has been used quite success-fully in several other programs written at Picatinny Arsenal.

To begin with, each key variable has a P, L and N number (allintegers) associated with it. N simply denotes the number of differentvalues currently available for the given key variable. The P and Lvalues are used to set up run combinations. The value of L determineswhether or not the given key variable is "linked" with any other keyvariable. That is, in a combination of runs, if the L value for twoor more key variables is the same, each of these variables will changetheir values simultaneously on each successive run. Finally, the Pvalue determines the variable to be changed on each run and thenumber of runs to be made. For those variables which are linkedthrough the L value, only one of these variables can have a nonzeroP value. This is evident since when one linked variable changes itsvalue, all other variables linked to it will also change. By assigningdifferent L values, it is clear that sets of linked variables can beidentified. Since L is currently restricted to the integers 1 through9, nine sets of linked variables can be defined, if necessary. Itshould be stressed that only one variable within each set can have anonzero P value.

As an example, suppose three key variables AXX, BXX, and CXX wereto be varied in a combination of runs. Let AXX have two values andbe independent of BXX and CXX. Let BXX and CXX have three valueseach and suppose they are linked. Then, to run all combinationsunder these assumptions AXX, BXX and CXX would have the followingP, L and N numbers:

P L N

AXX 2 0 2

BXX 3 1 3

CXX 0 1 3

NOTE: Variable BXX in this case is used as the "permuted"variab1.

4. Format and Use of P, L and N Numbers

At this point the meaning of the P, L and N numbers (abbreviatedPLN numbers) should be clear. This paragraph describes how data areentered and modified within the data base when PLN numbers are in-volved. In paragraph 2 preceding, the entering of only single valuesfor each key variable was described. In this case, the IPSDATA

9

program automatically associates a PLN of 101 to each entry. If aPLN number other than 101 is used, then a comma is entered in columnfour (rather than a blank) and the PLN number is entered in columns5, 6 and 7. The N values (up to 6) are then entered in the remainingcolumns of the card in free floating point format separated by commas.No blanks are permitted following the first data entry.

Modifications of an existing data base to include PLN valuesother than 101 are described in the instructions for running theexecutive program in Batch or TTY mode. (See parts B and C of thissection.)

5. Data Base Modification Using the Executive Program

In order to modify an existing data base using the executiveprogram (IPSH) (as opposed to creating an entirely new data base fileusing IPSDATA), the initial data base must first be available as apermanent file. The procedure using the teletype is explained inPart B of this Section titled "Instructions for Teletype Mode" underquestion 10. This question, namely, "MODIFY DATA BASE, YES OR NO ="is answered "YES". This invokes questions 11 and 12 which allow theuser to enter data for key variables, even if no values currentlyexist for that variable. In this way data can be entered for a numberof variables. Where limited data entries are required, for example,in executing the Interior Ballistics Program or the AerodynamicCoefficient Program, this method would be preferable. For enteringdata via the Batch mode, the user should refer to part C of thissection.

B. Instructions for TTY Mode

1. General

The following pages indicate the instructions used to executethe executive program (IPSH) in the TTY mode. This mode is conver-sational and requires limited response to perform many useful op-erations. It is required for users who do not have access to a BatchTerminal, and is particularly useful in conjunction with a portableteletype. The system allows the user to access any program withinthe IPSSM System. Where extensive production runs are required, itis recommended that the Batch Mode be used. However, certain optionsfor some programs are currently available only in the TTY mode.

The first instruction required to enter the INTERCOM System (seeReference 7, page 3-2) from the teletype is "LOGIN". The system

10

responds with "ENTER USER NAME" to which you type XXXXYYYZZZ where

XXXX is a four letter user code assigned by the MISD.

YYY = Cost Center Code (See Reference 8, page 4-8)

ZZZ = Charge Code (See Reference 8, page 4-54

The system responds with "ENTER PASSWORD" to which you respond withthe Picatinny Arsenal Code (Consult MISD).

The system then types some accounting information followed bythe word "COMMAND:. From this point on, see the following tablefor specific IPSSM TTY instructions.

2. Explanation of "INPUT/OUTPUT OPTION LISTU (see question 23,

page 18 ).

a. Teletype Options

The first two digitscoatrol the teletype function.

Put a "I" in the second place if you wish to come back tothe teletype for the results of your run when it has finished. Youwill be asked to supply a permanent file name on which the resultswill be stored for eventual teletype display. In most cases, theresults stored for teletype retrieval will be an abbreviated versionof the complete results.

If, in addition to these abbreviated results, you wouldlike the values of specific variables to be printed out, include a"" in the first place. You will then be asked to identify these

variables (up to 6).

b. Data Base Transfer Option

The third and fourth digits are used to replace particulardata base values with new values obtained during your currentexecution of an application program.

This option can currently be used in two modes: whenrunning the SP program, part of the SP output contains variables thatare required in the AR input. Likewise, portions of the WT output arevariables that are used as SP input. Thus, either an AR or SP database can be automatically updated with this option when running eitherthe SP or WT programs, respectively.

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(V J >1U~ 0E3 S=0 0 4-)I-S cc)L4- CL Ua 4a~) E

S-) to'4-) a) V() to Sa - o : )S - () V)

r_ 0 4-) + = =a) 0L4- a0.I+n - C 4- W M1C 0 C-

0.- - 0) fO 4J C 4J d).-La -. 4 - > CA 0 4J ) 4-

4-) m V oC~ 0- 0CL r--~ = 0v)l* cf4- + a -4- X: U' 4An (flA )( 0

u) (Uaa)S>4-L0' to LC-c0)7 E

C70 0ooc 0* (0- LAm

L 4-j C- w a (A. +3 .E :U- * -I.) to c m 0 .0 c

-0 4-Q0U4-)O (MI U- 4-'C j0). -34-

C0I I

* ~ C)

DI = C0

U L) C0

a- V - w. (AJ X0

U.; I. I-'-X

L ) >< V

18

LAJ

ILLJ

C,, (DO f

LU 0 0-

(0(L-

4-) (A

) 0 E

0 (A Ol

I.C 4-J' )

Q-)

U)0 (A

>~>1

4.- - Q)~4-) S.-

19

A "0" in the third position together with a "I" in thefourth position indicates an automatic replacement of old values withcurrent ones in the AR or SP data base specified. If a "1" is enteredin both the third and fourth positions, the system will take thecurrent output values and update the old data base specified into a newdata base defined by the user, and, in addition, will allow the userto enter a title for his new data base. In this instance, the old ARor SP data base will remain intact with its original values.

A "0" in both the third and fourth positions indicates thatno data transfers will be made.

c. Batch Terminal Option

The fifth and sixth digits control printing on remoteterminals.

A "1" in the sixth position will provide a complete set ofresults at the remote terminal.

A "1" in the fifth position will cause the input data sets(as modified for the present run) to be printed out at the remoteterminal site also. This will facilitate future identification of thecomputer run with the input data base that generated it.

d. Central Site Option

The seventh and eighth digits control the disposition ofoutput to the central site.

A "I" in the eighth position disposes the results at thecentral site.

A "1" in the seventh position also copies the input datasets to the central site.

3. IPSSM Short TTY Inputs

For users who have become familiar with the TTY mode,input can be entered more quickly as shown below:

a. If the run is going to be a new one, questions 1, 2, 3,4 of paragraph 2 may be answered at once in the following manner:

20

Question 1. THIS IS IPSSM

MODE: TTY OR BATCH =

TTY,AR5,5,XM58

If one of the answers is not acceptedby the program, an error message willbe printed and the program will askyou to correct the information.

b. Questions 22 and 23 may always be answered together inthe following manner:

Question 22. TTY, DB, TERM, CS =

11001100,177000,180

C. Instructions for Batch Mode Operation

1. General

If the user has access to a card reader at the central siteor at a batch terminal, he will probably find it more useful to runIPSSM via card input. Four options are currently available:

a. Modify and store new data base file.

b. Delete tables used in the exterior ballistics (AR)program.

c. Prepare data for the graphics (PROM) program.

d. Perform and store error computations for the exteriorballistics (AR) program.

2. Control Cards

In this mode, the executive program generates input data ona local file named TAPE9. The executable (LGO?) file of the programselected is copied to a local file named TAPE8. The control cardslisted on the following page provide the necessary cards to attachand run the executive program, which, in turn, executes the selectedapplication program. Cards enclosed In brackets are included only ifyou are making use of the error analysis option. The cycle number

21

which you specify here when cataloging the permanent file ERROR must

agree with the number you specify on the ERROR card (paragraph 3).

(JOBNAME) ,CM145000,T210.

(COIMMENTCARD)

ATTACH( IPSM,IPSH,CY=5,ID=NICHOLS,MR~1)

IPSM.

REQUEST,TEMP3,*PF.

LREWINDTAPE9.COPYSBF ,TAPE9.

REWIND ,TAPE9 ,TAPE6 ,TAPE1O.

RFL,145000.

MAP(OFF)

REWINO,TAPE12.

COPYBF(TAPE12,TEMP1)

IREWINDTEMPI.

RETURNJAPE12.

TAPE8( TAP E9).

REWINDTAPE6.

COPYBF(TAPE6 ,0UTPUT)

/ REWIND,TAPE12.

COPYBF(TAPE12,TEMP2)

REWINDTEMP2.

RE WIND JAPE 12.

22

COPYBF(TEMP1 ,TAPE12)

BKSP(TAPE12,1)

C0PYBF(TEMP2 ,TAPE 12)

REWINDTAPE12.

COPYBF( TAPEI2 ,TEMP3)

RETURNJAPE 12.

REWINDTEMP3.

CATALOG(TEMP3,ERROR,CY=N,ID=NICHOLS)

(7/8/9CARD)

(BATCH INSTRUCT IONCARDS)

(6/7/8/9CARD)

NOTE: The CM and T values specified on the job card mustboth agree with the values specified on card (b) ofthe batch instruction cards (see next paragraph).

3. Batch Instruction Cards

In order to explain the use of batch instruction cards, thefollowing example illustrates all available options:

a. BATCH,AR5,5,M1O6AR

b. 00011100,145000,210

c. DATA

VMX ,202

2500. ,2700.

THO

30.

END

23

d. TABLE,2,NEWMI06 NEW PROJECTILE RUN

11

12

END

e. GRAPHICS,4,PFNAMEI GRAPHIC DISPLAY TITLE

f. ERROR,I,NICHOLS

The explanation is given in terms of the card numbers designated onthe left.

CARD a:

The word "BATCH "is entered in the first five columnsfollowed by a comma in column 6. Columns 7 and 8 will have the two-letter symbol corresponding to the program in IPSSM's library thatis being run. Column 9 is the number specifying the current opera-tional cycle number of that program (usually 5). Column 10 containsa comma, followed by the cycle number, a comma, and the name of thepermanent file where data base is located.

CARD b:

In columns 1-8 are entered the input/output option listvalues (for explanation-see question 23 and paragraph 3 of Part B),followed by a comma in column 9. The computer core and timerequired to execute the applications program are entered next,separated by a comma. The core requirement is designated in octal.See note on page 23.

CARD c:

If changes in the data base are to be made, then a cardwith the word "DATA" entered in columns 1-4 is inserted next. Thenext card follows with the symbol of the key variable to be changedentered in columns 1-3. The PLN value of 101 will be assumed forthat variable unless it is followed by a comma in column 4, inwhich case the different PLN number is entered in columns 5-7. Thenext card provides the value(s) for that variable in free floatingpoint format (No blanks; start in column 1.) After all the datachanges have been entered, a card with the word "END" punched incolumns 1-3 is inserted to terminate this option.

24

CARD d:

If the AR program is being run and table deletion is desired,then a card with the word "TABLE" entered in columns 1-5 is insertednext. One of the table numbers to be deleted is entered in the firsttwo columns of the next card. Each table number is indicated on aseparate card. A card with the word "END" punched in columns 1-3 isinserted last to terminate this option. NOTE: A table card ispermissible only if you are running the AR-ogram. Otherwise anerror message will be printed and your job will resume execution.

4. Storage Options

If it is desired to store the new data as modified by anyrun, additional entries can be made on either the DATA or TABLEcards as follows:

A comma is placed after the word "DATA" or "TABLE",followed by the cycle number and the name of the permanent filewhere the modified data base is to be stored. These entries mustalso be separated by a comma. A new title card for the new database is also entered on the card in columns 25-80.

CARD e:

If the WT program is being run and it is desired to havethe output made available for later display on the graphics projectilemeasurement program (PROMS), then a graphics card is included. Theword "GRAPHICS" is entered in columns 1-8, followed by a comma. Thecycle number in column 10, a comma, and the permanent file name(starting in column 12) where you wish to store the graphics inputfollow. The title for the graphics display is also entered on thesame card in columns 25-80. NOTE: A graphics card is permissiblejoyj when running the WT program. Otherwise an error message will berTnted and your job will resume execution.

CARD f:

If the AR program is being run and it is desired that anerror analysis be performed on the data for future teletype retrieval,then an ERROR card is included. The word "ERROR" is punched incolumns 1-5, followed by a comma. Then the cycle number (correspondingto the one specified in the control cards) is punched in column 7,followed by a comma and the ID name, NICHOLS (starting in column 9).Example 11 on page 56 illustrates the method of retrieving on the

25

teletype the error analysis stored in this way. NOTE: An ERROR cardis permissible only when running the AR program. Otherwise an errormessage will be printed and your job will resume execution. NOTE:Only the first two cards and the ERROR card are order-dependent. TheDATA, TABLE, and GRAPHICS cards can be inserted in any order or anyone or all of them can be left out. If the ERROR card is included,it must directly precede the 6/7/8/9 card.

APPLICATION PROGRAMS AND DESCRIPTIONS

In order to have this manual somewhat self-contained withoutmaking it too cumbersome, a brief description of each applicationprogram is provided in this section. References to more completedocumentation are given, together with options available through theuse of the executive program (IPSH). References are also made tospecific appendices which describe key variable input and tablesrequired to each program.

A. Static Properties and Stability Calculations (WT)

The program used in IPSSM for performing static property calcula-tions is a program currently known as WEIGHT. An earlier version ofthis program was called DAGMAR. Reference 1 contains the latestcomplete instructions and use of the weight program. The key variablesassociated with this program through IPSSM are given in Appendix Al.In addition to the key variable input, the description of each shellitem, i.e. body, fin, known and ogival is entered following a cardwith the name WGTTAB punched on it, starting in Column 1. The for-mat for entering this information is identical to that used in theWEIGHT program. For completeness, this format is given in AppendixA2; however, for a complete explanation of reference points,associated diagrams and the equations used, see Reference 1. Thevariables named NBI, NOF, NFP, NKI and NOI provide the number ofbody, fin, fin pieces, known and ogival items, respectively. Thenumber of cards following WGTTAB must agree and correspond with thevalues given for the key variables. Following the shell descriptioncards is the card with ENDWGT punched in columns 1 to 6.

The executive program (IPSH) is capable of changing the shellitems in a similar way to that done at the graphics terminal. Theprocedure is written in conversational mode that starts with thequestion: "CHG ITEMS, YES OR NO = ". (See question 18 -- TTYInstructions). If the answer is NO, the executive routine continuesby asking the question; "STORE MOD DATA YES OR NO = " (question 19).

26

Ada&~

However, if you answer YES, the program asks the following: "ITEMTYPE - BDY, FIN, KNO, OGV OR END -". You may then select the appro-priate type or end the process with END. Having selected an item type,the next question is; "DEL, ADD, OR CHG -". Typing DEL means youwish to delete one entire item (line) of the type you selected. Theprogram will then ask for the item number: "ITEM NO. =". The itemnumber corresponds to the particular location of t'ie item, i.e., linenumber within its group (body, fin, or ogive). T~is can most easilybe determined by looking at a previous WT run on ihich the items arenumbered within their group.

WARNING: DEL should be the lastoperation specified, afterall ADDs and CHGs areperformed, as the lineswill be automatically re-numbered after each deletionand any subsequent attemptsto add or change item numberswill most likely beinaccurate.

For the same reason all deletions should be specified in the order ofthe highest item number first to the lowest item number last. ADDrequires that you specify additional data for the item type selected.The data are then typed in free floating point format as it is askedfor and the new item is automatically entered into the data base forthe run being made. These changes are not permanent unless you storethe modified data base. The CHG option requires that you specify theitem you wish to change and then the field within that item that youwish to modify. Field one represents the first formatted entry on thatparticular body, fin, or ogive card; field two the second, and so on.

These options allow for limited modifications of the shell con-figuration via the teletype. Obviously, the graphics system calledPROMS (Reference 2) with a visual display is much easier to work with,particularly if you are working with new shell designs. However, fora limited number of straightforward design changes the user may findit more convenient to use the teletype located in his immediate area.The TTY procedure is not recommended for any extensive changes.

In addition to this option, the executive program can also preparedata for use with the PROMS system. After selecting the weight pro-gram (WT), the question "GRAPHICS YES OR NO=" will be asked. If youranswer is YES, you are then required to specify a cycle number andpermanent file name to store the data for a subsequent graphics run.

27

The graphics output (currently in the form of cards) can then be re-

entered into the data base for additional IPSSM runs.

B. Generation of Aerodynamic Coefficients (SP)

The program used in IPSSM for calculating aerodynamic coefficientsis a program known as SPINNER. The documentation for this programis given in Reference 3. The program was originally written inFortran IV for use of the IBM 360/65. Later it was converted to runon the CDC 6500. Computational techniques used to estimate the aero-dynamic coefficients of spin-stabilized projectilesare based upon theuse of empirical equations and apply for Mach numbers from 0.01 to3.0. The key variable data required to execute the program are givenin Appendix B. The following aerodynamic coefficients are predictedby SPINNER for projectiles of 3.6 to 9.0 calibers in length, withogival nose lengths of 1.8 to 4.0 calibers and boattail lengths between0.0 (square base) and 1.0 calibers:

Zero Yaw Drag Coefficient

Normal Force Coefficient Derivative

Pitching Moment Coefficient

Magnus Force Coefficient Derivative

Magnus Moment Coefficient Derivative

Damping in Pitch Coefficient Derivative

Spin Deceleration Coefficient

The formulas are based upon the use of "standard" projectilelength, and center of gravity from the standard.

The SPINNER Program does provide the engineer with a rapid,accurate technique for estimating the aerodynamic coefficients foruse in preliminary design studies. However, SPINNER results shouldbe checked against reliable aerodynamic data when available. (Theabove remarks are excerpts from Reference 3.)

28

C. Interior Ballistics Calculations (IB)

The program used in IPSSM for interior ballistic calculations isa short FORTRAN program called INTERIOR BALLISTICS, and is describedin Reference 4. The program uses a series of simple equations tocompute muzzle velocity given charge weight,chaniber volumemaximumpressure,and other variables shown in Appendix C. The program canalso be used to calculate charge weight if the muzzle velocity isknown. However, the process used in this case is an iterativescheme which usually converges. Maximum pressure can also be estimatedby another iterative process. The codes required for the key variablePKI are 1.0, 2.0, 5.0, 6.0, 8.0, 9.0, 10.0, 15.0, 17.0, 26.0, 30.0,31.0 which represent the propellants MI, M2, M5, M6, M8, M9, MIO, M15,M17, M26, M30, and M31, respectively.

D. Exterior Ballistics Calculations (AR)

The program used in IPSSM for exterior ballistic calculations isa two-stage, point-mass trajectory program called AEROI with dragcancelling and stability calculation options. One of the originalversions of the program was known as RKTCAN, which was written in1962. The most recent documentation for this program can be found inReference 5. It was written for the IBM 360/65 and did not containthe stability calculations. In 1966 a new version of RKTCAN waswritten to include stability, and is currently known as AEROI.Documentation for this program is contained in Reference 6. Basically,the program can be used for both one and two-stage missiles or Rocket-Assisted Projectiles (RAP). The trajectory calculations are dividedinto the following four phases:

Phase I Acceleration of Booster and Main Stage

a. Start from Launcher (VMX-O.)

b. Start without Launcher (VMX greater

than zero)

Phase II Coasting of Main Stage

Phase III Acceleration of Main Stage

Phase IV Free Flight of Main Stage

29

.-T I

For calculations involving Rocket-Assisted Projectiles, only PhasesIII and IV are required. Other combinations can be used, dependingon the functions of the missile or projectile. A purely ballistictrajectory may be simulated by either Phase 11 or Phase IV. A listingof the key variables used in this program is given in Appendix D1,together with an explanation of their meaning, values, and format.The program tables required for the program are given in Appendix D2.For consistency, all tables are described by the same format, whichrequires six cards. The first three denote values of the independentvariable (mach number, altitude, or time); the last three give thevalues of the dependent variable (drag coefficient, thrust, weight,density, temperature, etc.). Each card is in 1OF7.0 format.

All table cards are inserted in the initial IPSDATA data deckbehind two table control cards. The first card has tho name EXTTABpunched on it starting in column 1. The second card denotes thetables to follow. Each column of the card corresponds to the numberof the table to be inserted. A 1 in any given column indicates thatthe correspondingly numbered table will be included. For example,a 1 punched in column I of the card would indicate that six cardsfor Table I would appear next. A blank in any column indicates nocorresponding table will be inserted. Thus, the second card indicatesthe tables that follow (in order) corresponding to the column numbercontaining a 1. Depending on the value of certain key variableslisted in Appendix D1, certain tables must be inserted for properexecution of the AEROI Program. However, any table can be storedinitially in the data base as long as the appropriate ones aredeleted when setting up a run through the executive program (IPSH).The AERO I table cards must be followed by a card with ENDEXT punchedin columns I to 6. For the TTY mode, tables, by number, can bedeleted one at a time (see Instruction for TTY mode, page 10 ). Forthe batch mode, tables are deleted by a number following the cardlabelled "TABLE" (see Instruction for Batch Mode, page 21 ). Allaerodynamic coefficients are "C" coefficients. The conversion of"k" coefficients to "C" coefficients is given in Reference 6.

A fixed flat earth and the 1959 ARDC standard atmosphere areused when no other option is identified. Provision for insertingnonstandard atmospheres is provided by the use of the key variableNAT and Tables 19 and 20.

30

E. Terminal Effectiveness Calculations (LA)

The effectiveness program used in IPSSM computes the lethal areaof fragmentation ammunition. It has many options and computationalfeatures that are described in references. The essential input tothe program is the fragmentation data as a function of "zones"described with respect to the axis of symmetry of the shell. A zoneis the region between two conical surfaces whose axes are at thecenter of gravity of the round and whose half-angleis measured fromthe nose end of the round. Fragmentation data within each zoneconsist of the number of fragments within given weight groups and theinitial velocity of the fragments. Each fragment in a weight grouphas a weight equal to the average fragment weight. All fragments withina given zone are assumed to have the same initial velocity. However,their drag is dependent upon a shape factor, the size and weight ofthe fragments themselves, and the type of media (air, grass, leaves,etc.) through which the fragment will travel.

The shell is assumed to detonate at some point in space above thetarget area or at impact with the ground plane. The shell may havea terminal velocity at detonation. Its angle of fall with respect tothe ground plane is also required input. The targets for this programare personnel in various postures such as prone, standing, or in fox-holes and are also assumed to be in some stage of military readiness.These military situations are described further in the references.Those who use the program will recognize the required key variablesgiven in Appendix E.

The program is also capable of generating probability of kill(PK) matrices in the ground plane. In this case, the target areais divided into rectangular cells that can be specified by the useror generated internally, depending upon the option called for by theinput data. The PK is then calculated for each cell. The PKmatrices can then be used in other lethality programs to determinethe effectiveness of volley fire and multiple round firings. Pro-grams which evaluate multiple round effectiveness could be incorporatedinto IPSSM at some future date, if desired.

Another significant feature of the program is its ability toaccount for velocity decay of the fragments as they pass throughdifferent layers between planes parallel to the ground plane. Theregions between layers can represent various types of media repre-sentative of environments such as grass, jungle tangle, or highcanopy forests.

31

- - .... --, .: . . - V ... ' -M .m

It should be emphasized that for purposes of the IPSSM systemsome of these sophistications need not be used to obtain a preliminaryestimate of the shell's lethal potential. However, having thisprogram available does allow for parametric studies to be made in aneasy manner by varying the key variable data.

The format of the fragmentation data is identical to that usedwhen running the lethal area program independent of IPSSM. Preceedingthe fragmentation data is a card labelled FVMTAB in columns 1 to 6, andfollowing the list fragmentation data card is a card labelled ENDFVM.Data describing the fragment drag tables are separated in a similarmanner by cards labelled FDXTAB and ENDFDX in columns 1 to 6. Thistable is required and must contain at least two values for both thedependent and independent variables.

F. 6-D Trajectory Program (TR) (references 9, 13)

The six degree-of-freedom missile trajectory program may beutilized to compute trajectories for one and two-stage rockets and/orballistic projectiles (fin and spin-stabilized) and consists of thefollowing phases:

Phase I Acceleration of Booster and Main Stage

Phase II Coasting of Booster and Main Stage

Phase III Separation of Booster from Main Stage

Phase IV Coasting of Main Stage

Phase V Acceleration of Main Stage

Phase VI Free-flight of Main SLage

Any of these phases may be excluded in the computation. For ballis-tic trajectory computations, only Phase VI is required.

Thrust values for the acceleration phases (I and V) are obtainedin the computation by linear interpolation of a thrust versus timetable. Provisions in the program permit altering the table thrustvalues by using a constant thrust modifier term. Also, thecorrection of presented thrust data for changes of atmosphericpressure with altitude may be performed, if desired, by the user.

32

Thrust misalignments may be introduced by establishing the thrustmisalignment distances and angles as input data. Also, a constant jettorque may be introduced.

A linear change in mass during acceleration or a change in massas a function of the thrust and specific impulse of the rocketpropellant is another option for phases one and five. If a separationthrust is required in phase three, only a linear mass change iscomputed.

During all acceleration phases, center of gravity and moments ofinertia are varied linearly with time.

Range, crcss-range, and vertical winds may be introduced in theprogram in tables as functions of range and altitude for flat earthprofiles. At present, wind equations for a spherical earth have notbeen included in the computer program because data formats for thesewind profiles have not been made available. Constant flat earth windsmay also be introduced for the entire trajectory. Inclusion of windsin the computation is an option and not required for all trajectories.

Normal force, yaw damping, drag ballistic coefficients, andnormal force center of pressure axial positions are introduced in theprogram as table functions of mach number and angle of attack. Whenthey are available, magnus, roll moment, and roll damping (or spindeceleration) ballistic coefficients and the magnus force center ofpressure positions may also be included as table functions of machumbers ond angle of attack. For entry of tabular data, consultroballlstics Branch, FRL, 'icatinny Arsenal.

G. Recoil Mechanism Design (RM)

This program was written at Rodman Laboratories, Rock Island.Documentation is not available at this time. It is suggested thatMr. B. Moody at Rodman be contacted for further information.

H. Sabot Design Program (SD)

The program SABOT DESIGN is currently used in IPSSM for thedetermination of sabot design parameters. Before a weapon system canbe designed and tailored to achieve stated objectives, adequatedesign criteria must be established. In the case of weapon systemsemploying saboted flechettes, many interdependent variables arepresent that serve to confound the design process. Reference 10contains the latest complete instructions for the use of the SABOTDESIGN Program, which can accomplish the coordination of such

33

variables as sabot geometry, inbore pressure, intersegment spacing,bore friction, sabot density, and flechette weight. These and otherkey variables associated with this program through IPSSM are listedin Appendix H.

In addition to various numerical analyses, SABOT DESIGN is capableof producing Calcomp and printer plots of inbore loading through theuse of the NANCY plotting routine. Examples can be found in Reference9.

The SABOT DESIGN Program enables a sound engineering approach tosabot design that, in the past, largely relied upon numerous cut andtry methods. At Frankford Arsenal, where the program was written,it has already been used to design two functional flechette/sabotassemblies.

I. Heppner Interior Ballistics (IH) (referencL 11)

The use of multigranulation propellant charges requires improvedballistic theory for the prediction of interior ballistic phenomena.Accordingly, the Hitchock equations of interior ballistics weremodified and new procedures developed that are more applicable tothe high charge-to-projectile weight systems. These modifications,incorporated into the Heppner Interior Ballistics Program, givemore reliable predictions of the effects of changes in the weight ofthe charge, the weight of the projectile, web size, and type ofpropellant and granulation of ammunition. The program performs allnecessary computations for the high-velocity guns for any shape ofpropellant grain and multigrain charges.

Principal output is proportion of propellant burned, projectiletravel and velocity, chamber pressure, pressure on the base of theprojectile (all as a function of time), and "variable quickness"(as a function of projectile travel in the tube of the gun).Another feature of the IH program is that if experimental data(velocity and maximum pressure) are available for a particularsystem (gun, projectile, or propellant), the data can be used as a"basis" for calculations of additional pressure and velocity chargerelationships for new systems to be studied. The closer the newsystem is to the basis system, the more accurate the calculationswill be.

34

_ o '

SAMPLE INPUT FOR INITIAL DATA BASE GENERATION

Following is a list of the data base cards used to generate the

data base titled "PROJECTILE 8-INCH M106", using the IPSDATA

proqram. These cards would be inserted into the deck format shown

on page 7, and as a result of this run, five different

permanent files (M1O6AR, M1O6TR, M1O6SP, M1O6WT, and M1O6LA) are

created and catalogued (cy=5), as discussed on page 8 . Note

that these five different files are created as a result of both 5,

M106 being specified on the second data base card and the inclusion

of data used by each of the five application programs. Appendix J

shows the output of this run.

rr'yjr T 11 C ' Q I '. e

r- C I

T I

.,T r,

or T inn.

1TA 7 c

rA~'r. r' T O ,"T I-- 70,

-T - -'er

r'I ', .

.- r'r ,

r ,4 4A.

35

'"7.,+ .+

T 1-0 7)

'T r-

r !T C~c~n

cr r TrT 17,

r- T 4 7 q

'1 T C9 , *c e *

0 A.

T %/l I AP

36

* -- 7

Pr 7 17.

,r . ___________________

I rr

.113 *?AA . ; 1 -. ?? 2 ?f __"--_-

fl. "r 0.0nf Orn I~ .S *1f not I.fl 1.0 1 IIt

(7~ P7 -4-a" if-*~~ *1 I ICf n .'49 .47.4

r",, n F v 1 _ _.r- T T A w7 91 7.95 7 ?p 1P I9. ;2cPnflY I~7.q9' 7*QP I .Pl 24.? 45 pnfly?)7.qP F. *7c; 4~ .IA ?P' 3 1 . I POflY1 I7.c;( 7.99 .7p *?)P3 P.~a flPnfY4 I

7.QA 7.9P .4m .?Al IA 09~rrYq

7.49 1 .29l ?9.1.7 -Flp-0 nf -1

7'q7 pI s .;)P3 29;) pflfY7

4 . Af 4.~ r- 1 -. ??1 11 Tpnflyp

2.07 -.223;K ?6.r ~ T p'fY

Fort, 4.n6 ?.I) -. ?;)I ?Q. In TROnY7

T1.' --- , o. fltt ?C. In FR0CYP-

lA n. .1 A 4. 4C FpnrvT

.A .1 0. 4.~ Ic In

'.0~~ .1 A00047f 4 *

nr~o 4.~ .? .?P3 ?'.i P

- 1 .2P 27.'? ORnA I

P.R.?P3 ?P.A7 ('T 54T

Pop :1 .2PI 2A.07 CPOPFlC

7.q3 .1 70 ?R7v RPOTA

Q .t 7 . .(A~ )l 0A. ',3. Fflrd'6

__________ -1?'0. -9221 1 ;T161 VF

r v/ TAP -0.000 P I l. I' ?19, 0 f0 A ?'$. 67 ?1sn.nofl l-T-obn

37

0.000?.500 7 qoO 9.000 2166.667 2r7c9 .000 2000.000 1.0001.0000.0007.500 l?*rfl0 10.000 p2979;.00 ?3";.006 ?150.000 1.000

1P.500o 17.*0 1S.000 21?';.00 2Ar0.000 ?10n.000 1.000

0.000

1.000

",;.500 ?7.rf0 ;)r.000 3100.000 ?9#)0.000 ?AOfl.000 1.0001.0000.000

77.50 3?.CIo 10.000) 2q00.000o 3100.000 100A.000 1.000F

i37.500'- 17.r-e00 19.000 1100.000 327-.000 3?0n.000 1.000.176

17. 79aF17.500 4P.-,#0 40.000 3P79.600 4CO.000 115A.000 2.000

31 :3H ;!'Sp47.50A 47.--0 4.9.000 3450.000 35SO.000 IS5A.000 2.000

1400Q

47.501) 152. 9Ao -0. 000 11;56 * 00 4?00.000 1159n .004 4.000

c;'.Sof 57.9A0 rc9.000 4P00.000 4?no.000 4050.000 4.000.31? 1,441 2.PS3 50 O.O4016991 (;.4117 .407 9.4n7

S7.!300 6?.cZO% A0.000 4700.000 3379.060 39-36.000 1 .000*119 1.'40 2.194 7.4546 9.070 41.77A 973.973

161!1913 9..4AO Ip.Q02 Q*4.A 1A.9pp 11.g? 9.6

6;,.500 67.cEA0 49.000 1379.000n 33CO.0 0 0 120A.000 11.000.217 1.412 13.304 7.p97 I1A.90;1 14.161 ?.6

4t.8()7 9?.441 140.099 210.?IA111.791 9.4AA lp.902 9,460; q.466 2A.44A q.466

6750 7;:9," 75000 3149'6po 36PC.000 1"00.ooo 17.000.127 1.0;t4 2.1"51 I1.p?1 19.400 29.009 40 .2f7

AP.9ie. 92.772 118.4419 141.42Q 171.171 21A.Ap7 2 99.?C0390.39n 487.496 Sl9.9;4117q.971 18.94g 9.474 q.474 q.474 q.474 ?A.421

944 IR74 90948 10.940. 9,474 10.948 9.47490474 944" 94777.500 77.r,0O 79.000 16?9.000 3P~r,.000 375n.000 13.000

.097 1.rjo ?.ASA Co-c 9.041 17.01? 30.7134;,.7A3 oiO.Wo 1?2.171 23P.000 41A.4-48 571.00

100.030 37.0Ao 17.092 9*46' 9.4f7? Q.46P 37o.09?

9..41 412 9.462 20.4?9q 9.440; 07,773p "?.:q0 P 000 30e.00 *?0.0 3900;!000 JMOU.224 1.q4(0 1.154 7.799 0.771 11.900t 16.225

?3.342y 3A.79 43.042 9;7,770 7A.20;1 111.667 179.0043t;.2A2 020.flAO 1117.9;7f 2426476?L4.J09 37 At(, 47.158 Q.471 I0.943 2A.415 v.471T

9.4~~370o 947 Q471 10.941 2A.419; 20.415

Ap.500 87.9#o 05.*000 4.200.000 4500.000 4500n.000 14.000192 1.4c;3 IOQQ3 6016A 12.77A 31.PPS 9T7IgT2

i0m.108 179.174 206.?05 317,11A 4479447 O;10.166 1404.40535l.W772.1A- o49A 10.946 10.946 oZ

q.447 9.442 9.44? 9.442 9.442 56.$k3n 9.442

38

107.100 9;)1o q0.000 4COO* 0 0 0 447-*,flf 4-00.OnflO ,.01*11 l11P 7.141 1 P.411 17. n';3 ?9.5pfl

12113.213 1 ________________10._74 _0.4__ rv__ 9__4 1737 . 25*17 -4A6 I-97 --A'SA '7.

1. 17 17.Q4A 9.4P7 Q.4P7 Q.4A7 Q*4A7 C;6.92;1

92.500 97.r-O 9C.000 4479*0on 3P-O.nO0 435n.000 ??.non1! Ir-2 .4?0? 6'. 1,n7 11.141 IP.n3 - ?-.q9

1lr9 41.012 r,1 .17? 6c5.'72) 77*.67Q A4.161 91.33n1fl~.6s7 ?9.'9 17n.131 P41.17P 4?f.Pg 010 00 1937?

?3p64 g95 *73!0;QoH7 47.10~6 17.Q17 Q.47q 47.10396qs47,39!' 7r.913 9.479 lp*9 c0Q (947c) C.47q .7

'>. I 9.479 2P.41P 1A.9 qp IP.9c~q 50!'*P 9 4 7 . 4!'79*.41A

0 7 .5 t0 102.q%0 10l.nOC 390.OnPl 147-.Ono 113n00 on n.IQ? 1.91C 679~ 711 1;100 7.?

72';.t87 3r-;;7 4;!5-1; f6;!'57 74.421 713' 99P104.276 12P:.416 17P.111 2?5.056 2A7.146 l3's77A 446.2777qR.831 148C.7Q4 411=.714767.694 I1.177 117.77r 10.* I A A lo 37.993l 37.9ql

?a . J39 r f 57Q q 47. 19)1 17. 09 ;A91qc Q939 1. q9! 37991F317-9q3 ]P_996 QrC*34 37,9()3 '.7.3Q1 gr-384 jpq(qAIc 66.107 7r,*7R6

iop.500 1O?.,'A0 105.000 14P2;.Onn 32n0.000 ICOA.0on 14.00n.2?26-2 Po4' 7.12A' Q.911 11.711 19.706

?Q.447 3r9.6 40 C4 .;)5~ 77.rc59 102.19? 471.47) 50q.5 11?X6C.294 C-40 9.4 910 9.49fl 9.490O PO.41? 9.4rn

Q.450o 94rp 9'5p 9*0l 40117.500 112O p1.0 .?0.0 -72E.0S >qon90500 7

O095 I 1.1'0? 4.Q'A? 11. Ic4 17.41A 54 .95!'; 200.201171.117 9,.4A9 I P qg7 44. 4 f 9.4f( q.469 9.469

1.50 117.r-n0 l1q.DA0 ?72q.PO0 ?5qfl.06A P55fl*000 7.00nJ131 1.142 it.;7) ?0?07.9 41*24n 711.144

99.15 ,9-4r6 IP9Z2 q*456 9 9.45 9.5 1$3.QPAIt.50 120.000 ?r 9O.poo n60.0 ?5n 5N0 .

.216o ?.--42 r.077 Q.A10 11.201 2-.(-n7 127.3?7r,6.617 q,41o 9.410 9.43n 9).410n 0.41n 9.4?0

177.50n 127.r-MO 125.000 269A.000 ?7-0.C00 275n.000 7.000.T197 -1. 0 04 4 c;74 c;.124 0 . Ooc9 9;)!'94 210.21

19.61 1;.9:,? 9.45; 4c5'9 9.49*459 .91?7.5700 13.0 3.00 ?9.0 ?IP25.n40 790.000 1ir.-U00

.212 1.479 2.101 S.667 10.9ot) IO.,)4n 11.43215;.276 97 . 0;19 113.13? 1 p.I 7Sq ?9.2o-F42ic.4?e,---

6Qn.7s9 66.'10 9 .4 ?o ?A .190 7A .3 1=) .4?) 9.42n_9.420 4;.420 9.4?0 9.420 Q.420A 0.4?0

11500 ?P5.') 2"P2%0fl ?Q02.000 9.000

0.4110C"q a I6 61 20 32 2P1 . -12

9.113 q.113117.500 14P.C A0 140.000 2P25.000 ?(#2 . 000 279n0.000 100

-2774 ~ 1 , 2743 7,637 10,240 ?22.954 34.574AQ.B4 99.10 102.10?

9,41.737 39,t4P1 19.4?1 7.994 7.A94 Ir.76A 7.99P47.884 7.$3e4 7.994

14P.5410 147,4500 149.000 ?6?5.*00n P2579.00 790M.000 4.000.2708 1.600O ;).r47 4n.019

14.t0 15-Rl RU H sil 29go.000 P550.000 9.000,III 1,3C6 P.r7l 7.A79 19.299p

145,976 21,6?6 160??o S 54 (6 C;.4 0 4152.500f 157, r,0 1s;C.M00 2950,000 ?0"0.000 ?550.000 8.000

.243 104P5 1.191 6.706 12.219 3p,953 136.13t54R1.490

39

213.S75 26. 1ir4 24'j.164 4.15 it I A711 4 lei? 4.151

I1S7.500 16P,CMO 1(60.Oo0 20-00.000 P679;. of0 26'50.006 12.000.243 1*1Q2 3.441 A*P36 06971 17*p53 17.217

41.749 92.-112 121.12A 253.2sp -345.349

2A364 1,362 3*362 3.3

16?.500 167.c ̂ O 16r,.000 267S.000 2600.000 270M.000 16.000.24 ,322 2.P62 F,,r?p 9.396 1p.fl48 7.

?1.414 31.At.9 42.199 56.676 69.167 74.13A RO.532116.94? 14g*1CO'4t4475 !Z':;; 42:;;; 1;:,1; 4.889; 16.9 1.

4*~ 488 24g0 4:;;; 4,889

4.889 .AIA7.500 17?,c AO 170.000 2600.000 ?rETS.OOO 250n.000 ?3.000

.2qr5 1*5~s 1.476 6,447 Q.2n7 17.373 16.86-771.468 31.110 47.927 50.111 64,817 77.171 P5.7gg

16i6~2~7:t"' 179,912 23q.182 380.3P1 492.49? 529.529

107.916 1f-,777 13.684 16,727 4.55;4 A.i087 7,5973.041 (-,.'17 -3.041 10.-11 1.041 1.043 3.n4l1.511 4 .c54 3.043 l.043 10.511 1 .51 I1 105111.511 1 lI

47.50 17.~ 1 50 2575.000 311g:T667 26;53P 2,0.30 .'7 .4 A .387 917 1.3 17o64?

21i.680 2SX413 39.P26 54.297 61.013 71,357 80.00692.9A9 112.588 118o714 174.111 210.3q4 278.36i 330.334

401.798 61g.166 151q.471111.672 2 1 o702 ?9.F11 17.484 6.7QA Q.707 A.P166

.979 p?.;9 7.770c177.500 180.000 17P.750 1116.667 3190.000 3350.000 21.000T-

.238I 1.414 3.013 6k.757 Fk.267 11.980 17.923?Ao9314 ?9.QI2 41.r,71 59.96l 61.964 72.731 110.449q

117:.0 1724 13:jj 411:th Oq0:jj3 1517:1;; 2669.167

.669 1.119 2.008 .331 .6; 1.0"(2 .669*6f,9 .l11 .113 .331 1.339 ?.008 1.33q

~FlFvmrrX TAR0.0 670.0 P9. 160 1339.0 196P.fl 1786.0;)712.A 1148.0 ~P 04.

0.5 I 0.54 1%.56 0.67 A0.6F 0.70 0.700.68S 0.64 0 . f0 0 .5A

40

SAMPLE TEST CASES AND SETUP

A. Introduction

This section provides sample cases of both TTY and Batch runs

using IPSSM. They are given to illustrate the use of the system aswell as to show specific techniques. It is recommended that some or

all of these cases be run by new users. The permanent file namedM106 (Cycle 5) is available for this use and is used by all the

examples. However, other data base files may be generated by the use

of IPSDATA (Cycle 5). Care should be taken to specify differentpermanent file names than those catalogued in these examples to avoidconflict and possible job abort.

B. TTY Examples

1. General Information

The following lines show the initial login and attach

procedure that is common to all the teletype examples mentioned in

this manual. All subsequent examples will begin with the firststatement generated by IPSSM, namely, "THIS IS IPSSM,

D IJIgl IOf- .NION

Lmmmsma mm

Dflh own MU,

COPY AYAILABLE TO IC IBES 1OPERMIT FULLY LI BLE PROUUCTIO

41

MODE: TTY or BATCH=". All information shown underlined is user-supplied. Continuous reference to Table 1 should be made whilereviewing the following examples; the batch outputs generated bythese runs are shown in Appendix K.

2. Representative TTY Examples

a. Example 1 illustrates the running of the Static ShellProperties Program (WT) using the M106 data without modification.

Psfla(z g ) uem

001cS. .ose O me

mwvN Isam, Imil us.l g1 qnlot" IMal ves OR WO NO

call1SI SP am a

fW;:M "S) LI,°1IST B~~~

am a"- Cm,T -aaIsO,115

TrY IuM LIST- W4i * ._.1

COPY AVAILABLE TO DOC DOES NOTPERMIT FULLY LEGIBLE PRODUCTION

42

a m a" a a m w

Note that the short TTY input (page 21 ) is used to answer question1. Also, TTY results (a summary) are asked for and will be saved ona permanent file called SAVEWT (cycle 1), in addition to the morecomplete batch results that will be sent to the remote terminal site(see Appendix K-i for entire batch output). Also, the number of shellbody items (NBI) has been selected to be included in the TTY resultsfor the user's own reference.

The following TTY run was used to obtain the TTY resultsstored previously on the file SAVEWT (Cycle 1). Note that, forreference, the number of shell body items (NBI) is also provided.

THIS 5IPSs"qNOK- T Olt iDATCH TrY

WILL THIS RE A NEW RUN, YES on MO • NOWHERE UI[ ESULTS STORED,.PrM o.CY, ID. S UT. I ,NICHOLS

Niot 36.0"

PROJECTILE 8 INCH NIS0

PROPERIES OF ENTIRE SHELL

MEIGIHT M.SiU PNS

CG TO R.F U.7413 INCIES

POLPA INENTIA- 136.S16 PO.e6 INCH SQJA

TO UERSE INERTIA.1S66.7337 POUND INCH MW

OUTER t3OLIUE . t 6 CU@BIC INCHES

00 OF TTY RESULTS

STOP mc .13 CP KeWS EKUTIOP TIME

COPY AVAILABLE TO DOC DOES NOTPERMIT FULLY LEGIBLE PRODUCTIO

43

--'2--* 3 A .

b. Example 2 below also illustrates the running of theStatic Shell Properties Program (WT), but, in this case, thedensity of body item number 3 is changed to 0.300.Ogival item number 4 has also been deleted. The complete remoteoutput is given in Appendix K-2.

TWIS I PSN _SWODE " S l0ATCH * YYO.U1.IOMT

TITUeMPJCTILE I IN ImS

IWASJIT ( TAPE9.II ow )

ONIAPiCS. YES ON NO • NO

EXA INE DATA IMS. YES on NO * NONODIFy DATA, YES Ol NO. NO

CHS ITM ES SO • 0 .YESITON TVPE- IO.FIN.IIO.OWu DOID - IDY

KLo ADD OR CHO -CHO

ITEN NO. - 03FIELD NO.. VALUE a 4,0.3IT"M TIYM- BIY.FIN.Ke,OU OR EN - OOUDEL. AN OP CHO -KL

ITEM NO. 9 04

ITEN TVPE- 3UIFINKNO.00 Ol DODe DDSTOE NO DATA. YES OR NO -tNOIWWM~ OPTION LIST(Yo1 N") TTY.SD.MMN, CS • UWl..

)XX-)OOt a

61CP Igo

COPy AVAILABLE T3 DD t S NOtPERMIT F&Iy LEGIBLE "TION

44

c. Example 3 illustrates the running of the AeroballisticsCoefficients Program (SP). TTY input is shown below. Batch outputfor this run is given in Appendix K-3. In this case, the key variableCGS (distance in calibers of the center of gravity from the nose ofthe projectile) is changed from 3.315 to 3.50. Note also that thetwo values of WTS (shell weight in pounds) are changed by re-enteringonly one value. The option to automatically generate a new data basewith the permanent file name MOD (Cycle 1) and the title "MOD 8 INPROJECTILE" is also accomplished. This data base can then be usedby the Exterior Ballistics Program (AR) with the drag tablesgenerated and stored by the SP program in the MOD file (Example 4).

l -' 'ql~liwY • .WS.sfIeIp

TSt IS

S(flIqI. VIIr )

CWTHE INTO eIM. V" O No *U

9" V .re S#•

1Le Lm 1 S 3 e N:0P M.WI M.6I W n

* M AIA.S aV U IW

EUTRU NUSINSMB-flISan am.V .a .me _W

VW MI.T0-U

45

d. Example 4 shows the running of the Exterior BallisticsProgram (AR) using the MOD drag data generated by the SP program inExample 3. A recently added provision for conducting a partial erroranalysis in the AR program is utilized here. The data produced by theAR program are analyzed and stored in the permanent file ERRAN (Cycle 1).A second run is necessary to produce the analyzed results after theinitial execution is completed. Below is the TTY input yielding thefirst set of results shown in Appendix K-4.

N I IN PMI IIcI.i

Now W sm, VU 0 "ol No -

navy Tom, V"s aem s. no

uIII tlI-sas iI. IIsIe - U * u owl"

.NOTE: The permanent file, ERRAN,1,NICHOLS is available for recall.It does not have to be recreated by rerunning this example.

COPY AVAILABLE TO DOC DOES NOTPERMIT FULY LEGIBLE PHO[I90 0IN 41

ceemmum-c'. .sasw s-

The following run was used to analyze the TTY results

previously stored on the file ERRAN. The generated table gives the

errors in range contributed by the deviations caused by changing

drag data, angle of elevation (THD), and initial muzzle velocity

(VMX).

V -a, ""fle M-

ti3 Om0 am i.*. .440

m~.0 1mem.m wi

N%* TuV'a In=

asm unmam ssmu

COPY AVAII.ABLE O BOC DOES NOTPERMII FULLY LEGIBLE PRODUCIIOC

47

d . .• • • l • • m •

e. Example 5 shows the running of the Interior Ballistics

Program (18). Two new values of the propellant weight (PCI) are

entered via the TTY as a temporary change to examine differences in

muzzle velocity. Appendix K-5 shows the batch results. The TTY

input necessar'y to prnduce this run is snown oelow.

Nom •a, ,, U RNOM

3mit S M. m ___

VW L" We

*,. I..,_..

U ~ . |.S KU. 4

COPY AVAILABLE TO OC DOES NOTPERMIT FULLY LEGIBLE PRODUCTION

48

ow i " ,nunlin

f. Example 6 shows the running of the Lethal Area Program(LA), where two variables, burst height (PHB) and angle of fall (AOF),are linked by the L parameter discussed on page 9. Even though bothvariables have two values each, they are changed simultaneously (thepermuted variable is PHB). This run also used the option to storethe modified data in a permanent file called LAM0D2 (cycle 2) withthe new title, "LA M0D2 8 IN PROJECTILE". The batch output is shownin Appendix K-6. The TTY input is given below. Note that, in thisexample, the user initially typed the wrong symbol for the burstheight. The system allows corrections as shown without aborting.

TWIS Is IPSSNWSE- TTY O0 IATC4 4 TTIY.YLS.M1"LA

TITLE0

POJECTILE I INCH MIM

REQUEST (TIa 1 12P)!ESUST(TW U, SW)EXMIIE DATAWM, YES O'N0 No

WDIfV DATA, YES OE NO- YES

SYN.PL- P1Hle2

PiS S I ECom[t SYSOL

VMLES * Ms.,lS.SWI.PLN* AWr,Olg

UALUES * 47.,42.

SN, PLiI- END

STORE MD DATA, YES OR NO -YES

MEW TITLE - LA NOD IN PIOJICTILE_

uiiM DO YOU WISH TO o "MS DATA CY.PWA1 - R.LA

noD DATA STORED3s C a FLAIOW

r Vo KS Wt,0 IT,1[lfS•eeellCT CV- M SM478 MODS. I

OA.I TI LISTW.44

?TV TO.I$

49COOK, L

0I Io-w1 I

g. Example 7 illustrates the running of the InteriorBallistics Program (18). Here the option of examining al values ofthe data base is utilized by typing the word ALL in answer to thequestion "EXAMINE DATA, YES OR NO =". TTY input is shown below, andbatch output is given in Appendix K-7.

THIS is IPSS"

NOSE- TTV Olt BATCH * TTV.13.SNIS3

TITLE-

PROJECTILE I INGCH NI06

EXAMINE DATA SAM, yEs Olt No0 YESS"N ALL

Sy" PUG VALUES

DII 1o1 3.643XLI 101 166.000

Voll 101 310.10

PCI lo1 8. $atKI 101 17.00

WJI 101 .60NOCIFY DATA, YES OR Now No

INUTfOUTPJT OPTION LISTl~el Me$0) TTV.VB.TE0MCS a 001110

COME 4100- CN,T -16000,115

COST CENTE-0AE CODE,

202~ CoIR mIWO~~UT :01 TIME

FIlu Nm-PUNSOC DIUP-I#UT 19-Ag

COPY AVAILABLE TO DG DOES NOTPERMIT FULLY LEGIBLE PRODUCTION

50

h. Example 8 illustrates the running of the Recoil MechanismDesign Program (RM). In this case, the option to examine results ofthe run (in summary) on the TTY is selected. Note that the value ofthe rise-fall time of the rod pull curve (TIR) is selected forinitial printout when the results stored in RMD1 (cycle 2) are laterretrieved (page 52 ). The data base for this run is located inTESTRM (cycle 1). Also, the recoil tables in RMTAB (cycle 1) must bespecified. TTY input is shown below. Batch output is given inAppendix K-8.

THIS It ZPSSNNODE "yV on WATCH - TTY.RN6. 1.TtSTRM

TITLE-

RECOIL MECHWIS'M TESTK&AST(TAEIR. W)fews$ST(TAPE9S.SPV

EXAMINE DATA MS. YES OR No * NO

MODIFY DATA. YES OS NO- NO

INUT/OUTPUT OPTION LIST

(VaI N-) T.D2,7 ¢.CS • l____

CamE NES- CM.T *1asm.1@T INPUT LIST- SYIOLS - TIP

SPECIFY Pr1WwE FOR Try 11ESULTS-Wr"ARECY.I0u RaI.3.HICHOL

CATALOG CYCLE IUS aRECOIL TALES - PFPWNA CY,ID-

CT ID NICHOLS PFWo;Q1CT eV- on 00 UO12 .uN °lNNLS

COP CIE HMMc COME.

STOP s•3? CP ECONS MWctIGON TIMCemW.- wc. JoD. INUV.M

COPY AVAILA[FL TO PDC DOES NOTPERMIT FULLY i iODUCTION

51

* .*m ' ~.

The following run is necessary to retrieve the resultsstored in RMD1 (cycle 2) on the previous page. Note that the firstline printed out contains the value of TIR, as requested when RMD1 wasinitially created.

MON0 _ "V 00 SAYC. - M

WI~LL rHIS K1 A NEU ",DI AOS OR HO N

WWE RE RESOIULTS STONED. WM Cy. I D 01.0.M1,ICOLS

115k .010

.00 223" Ge000 00e00 .270

10.3"00 .24600 .4678W

as.00044 36.900W 76170 3"12.00~0

.00310 S .100.00 11.160"

.00300 .00100 .08144 .91060

2.0094,1 000W 3. Sea"

3.0400 0.000 INOSoW 000

00.90014 1.9000" 100

77.000

-,-z

see s. w0e. -O W1 3C 04"-ISt3

wIOS Iill 85 Se 2 gi

4"? 1.28433 am?366 S0M5

3.03006 4. MOSS 4 10 1104P 1740.09"00

1 4.0100 .0613 1010 071.4316n

r~o WO UP0 AIRV aM?

~'ooinc c31Iyr 0105

52

i. Example 9 illustrates the running of the 6-D TrajectoryProgram (TR). Here the data base is located in TRAJFLTR (cycle 3).Also, a file containing 6-D coefficients (TRDATA, cycle 1) must bespecified. Note that the short format for entering CM and T valueshas been utilized. TTY input is shown below. Batch output is givenin Appendix K-9.

THIS IS IPSSI

I1OKE- TTV OR BATCH - TTYoTRSo3TQAJFLTR

TITLE-XM 483 SPINNER ALL DALE BODY

KGU[ST( TWIEMS K )REQUEST (TM9 Xlq r

GO CoFurFICI'ws - PFIrEoCYo ID- TIDATA.INICHOLS

EXAMIE DATA &SE, YES OR NO • NONODIFY DATA, YES OR NOm NO

INPUT/OUTPUT OPTION LIST(Va1 N-) TTYVDB.TEMI.CS a 10 ItNISOWM

COST CENTER-CMAE CODE.XXX-XXX $ W76-60

STOP so.731 P SECONDS EXECUTION TIME

CONMD- DATCH, JOs, INPUT.aFILE 'Mf-IPSWOi. DISP-INUJT * ID-AD

53

j. Example 10 illustrates the running of the Sabot DesignProgram (SD), whose data base is located in SFRSD (cycle 1). Here theNPR parameter (Appendix 8) is set equal to 3.0, which is the option toobtain printer and Calcomp plots. The modified data are stored inPLOT (cycle 5) so that the graphs may be obtained again at a futuredate, if so desired (page 55 ). TTY input is shown below.Batch output, together with the Calcomp plot obtained, is given inAppendix K-10.

TNIS IPSSR

RODE- TTY O@ 3ATC4 - TTV.SDSD1oSFRD

TITLE.

5W430 DESION - SPOPlEGIJST TAPE $1 SP)*EST ( Ti~l9:PF)

EXAMINE DATA IASE, YES Ol NO • NO

MODImY DATA, YES Olt NO- YES

SYM."u9 Nn1SI

VJALUES - 3.0

SYM.PLN- END

STONE NOD DATA. YES 01 NO -YES

NEW TITLE - PRINTER I CALCOP PLOTTING

WER DO YOU UISH TO STORE NOD DATA- CYPF1 W •OT

ROD DATA STO0ED- Cy - S PF - PLOT

NE0IjST (TAPE9 ISPF)II)"1 HICI4OU InM-PILOYCT CV. U W 6 S VOID.'

INPUT'/OUTPUT OPTION LIST(V-1 No*) TrVo.N, 0 owIs"S

COE NEW- Col.T -150M.4"

COST dws"1 U COME,

Sm "'TNO N s

Fl s'""'" C"I AVAILABLE TV ValRMIT FULLY LEG. i IMOUC, 1

54

I:,t "

The following TTY run is necessary to obtain extra copiesof the plots stored previously (page 54 ) on PLQT (cycle 5).

THIS IS IPSSMMOD- TM, OP DATCH • TT.SDSSPLOT

TITLE-PWINTEW & CALCOMP PLOTTING

0E1W[ST(TAPE12,3PV)PIUEST ( TWIE39, S1 )EXAMINE DATABAK.I ES Onu pO. YES

P. 1 L- S N-UtAES • 3.0"

SY. END

NOPI'Y DATA. YES On NOW NO

IWWT'OTPUT OPTION LIST(Val N-O) TTY,08.TEMCS a emII

OWE 105 CNT e.IUU.UW

CUT Cal 63A CM,XXX-XXX ° @W-7"

974P so• A.lSC . ON16 j tIo" TI1S

55

k. Example 11 shows the run necessary to retrieve theerror analysis stored in the batch mode in ERRR (page 60

U MLO N AulMe hs 8 WOWo W

TO, .OM &AMN II 1.1"SI) 36.M @.N sA -SU.U

NW OPT go"",V'

COPY AVAIABLE -t

56

I. Example 12 illustrates the running of the Heppner Interior

Ballistics Program (IH). In this case, the values of peak pressure

(PEP) and muzzle velocity (VO) are examined and subsequently modified.

The option to store this modified data with a new title is selected

here. TTY input is given below. Batch output is shown in Appendix K-11.

TITLE*NDPPIE-IWVUR BAI.LISIIPS

O"19 DATA IMU. V"S ai NO * "ESYK. P u

UALME A6 -ehe NoS".

NOIP" DATA. VES OR NO. -s

9"'SPU*0 PW

$",Put 1A. 191 4

MW TITLE * EJIIM I

300 YO V I TO iW &% C Y.1I W

M " Mgo*- Cy. 0 £ o

TIM[-t pol' stop[-IHE I *-

57

AkdA

C. Batch Examples

1. General Input Information

Section C, page 21 provides general instructions for running IPSSMin the batch mode. The examples below will show only the batchinstruction cards necessary to run certain options. The complete setof control cards is given in pages 22,23.

2. Representative Batch Examples

a. Example I is the same run illustrated in Example 3 ofthe TTY runs. Note that the DATA card is used to change the keyvariable CGS from 3.315 (value in data base) to 3.50 and also todelete one value of WTS. Batch output shown in Appendix K-12 isidentical with Appendix K-3. 6atch instruction cards are shown below:

BATCH,SPS,5,MlO6SP

00001100,120000,115

DATA

WTS

200.

CGS

3.5

END

b. Example 2 shows the use of the TABLE card. This cardis used to delete exterior ballistic tables before running the ARprogram. In the case below, Table 12 is deleted, since only phase 2of the trajectory is to be run. Table 12 is used only if phase 1 isto be run. AppendixK-13 shows the output for this run.

NOTE: When rerunning examples 2c and 2d care should be taken

to specify different permanent file names than 1,M1O6GRAPHand 2,TESTL and ERROR,3 to avoid conflict and possiblejob abort.

58

BATCH,AR5,5,M1O6AR

00001100,120000,115

TABLE

12

END

c. Example 3 illustrates the use of setting up a data setcompatible with the PROMS graphics program. The WT program is calledfor with the M106 data. The graphics data set is cataloged asM106GRAPH (cycle 1).Appendix K-14 shows the output for this run.

BATCH,WT5,5,M1O6WT

00001100,120000,115

GRAPHICS,1,M1O6GRAPH

d. Example 4 illustrates the use of the DATA, TABLE, andERRI R cards in the AR program. Modified data are stored in TESTI(cycle 2). Table 12 is also deleted. The ERROR card stores erroranalysis results in ERROR (cycle 3) for future teletype retrieval(page 56 ).Appendix K-15 shows the batch output for thisrun.

BATCH,AR5,5,MIO6AR

01001100,145000,210

DATA,2,TESTI

VMX,202

2500., 2700.

THD

30.

END

TABLE

59

- -low

12

END

ERROR,3,NICHOLS

REFERENCES

1. J. Klappholz, "A Computer Program to Calculate the Weight andStability Factor of a Shell", Technical Report 3537, PicatinnyArsenal, February 1967.

2. W.H. Bolte, "PROMS - PROjectile Measurement System Program",PROMS Report, Picatinny Arsenal, December 1973.

3. R.H. Whyte, "SPINNER - A Computer Program for EmpiricallyPredicting the Aerodynamic Coefficients of Spin StabilizedProjectiles", Engineering Sciences Laboratory Report, PicatinnyArsenal, September 1968.

4. F. McMains, "Interior Ballistics - A Short Computer Program",Technical Report 3365, Picatinny Arsenal, April 1966.

5. R. Beck, "RKTCAN - A Two-Dimensional Trajectory Computer Programwith Drag - Cancelling Option for One or Two - Stage MissilesUsing a Flat Earth Model", Technical Memorandum 1851, PicatinnyArsenal, September 1968.

6. E.M. Friedman, "Description of the Revised AEROI Program, PANo. 010417", Technical Memorandum 2151, Picatinny Arsenal,June 1974.

7. Control Data Corporation, Intercom Reference Manual, 6000Version 3, 1971 (or newer versions as they become available).

8. Management Information Systems Directorate, "Digital SystemsHandbook for Scientists and Engineers", Information ReportNumber 71-21, Picatinny Arsenal, (Updated through April 1973or any later version).

9. John Nielsen, "Computer Program for Six-Degree-of-FreedomMissile Trajectories", Technical Memorandum 1292, PicatinnyArsenal, November 1963.

10. Andrew Semeister and John Zavada, "Studies in Flechette andSabot Technology - Part 1: Slip Model for Single FlechetteSabot Assemblies, Part II: Axial Stress Model for Single FlechetteSabot Assemblies, ARMCOM-FA Report R-3006, 3007, April 1974.

61

11. L.D. Heppner, "Final Report of Special Study of an Electronic

Computer Program for Interior Ballistics", Technical Report

DPS-1711, Ballistic Research Laboratories, July 1965.

12. Management Information Systems Directorate, "Plotting Routines",

Information Report 73-6, Picatinny Arsenal, (Updated through

February 1973 or any later version).

13. Bruce Barnett, "Trajectory Equations for a Six-Degree-of-Freedom

Missile Using a Fixed-Pl-ane Coordinate System", Technical Report

3391, Picatinny Arsenal, June 1966.

62

APPENDIX Al

STATIC PROPERTIES CALCULATION PROGRAM (WT)

KEY VARIABLE INPUT

63

I. Number of Each Shell Item:

SYMBOL VALUES OR FORMAT MEANING

NBI FI0.4 Number of body items*

NOF F10.4 Number of fins

NFP F10.4 Number of fin pieces*

NKI F10.4 Number of known items*

NOI F10.4 Number of ogival items*

II. Control for Program Options:

SYMBOL VALUES OR FORMAT MEANING

WTC 0.0 Do weight calculation

1.0 Do not do weight calculation

DRS 0.0 Provide shell drawing

1.0 Do not provide shelldrawing

STC 0.0 Do not do stabilitycalculation

1.0 Do stability calculation

2.0 Supply volume of entire

shell (VOW)

3.0 Supply PIW, CGW, TIW

NAR F1O.4 Number of additionalruns

DDC 1.0 Drawing of each change

COO F10.4 Number of copies ofoutput

*The total number of these itemsshould correspond to the number ofcards following the WGTTAB card referred to on page 26.

65

-- DIN PAU BLAGZ L-i T I I ..

III. Additional Cards Required for Stability Calculation:

SYMBOL VALUES OR FORMAT MEANING

PIW FIO.4 Polar moment of inertia

CGW F10.4 Center of gravity

TIW F10.4 Transverse monient of

inertia

vow F10.4 Volume

BOW F10.4 Bore diameter

BAD F10.4 Base diameter

TEW F10.4 Temperature (degrees F)

TWW F10.4 Twist

PVM F10.4 Projectile velocity

COS F10.4 Copies of stabilityoutput

66

APPENDIX A2

STATIC PROPERTIES CALCULATION PROGRAM (WT)

FORMAT OF SHELL ITEM INPUTS

67

Body Item Card:

Columns 1-10 D1, diameter on left

Columns 11-20 D2, diameter on right

Columns 21-30 H, length

Columns 31-40 R, density

Columns 41-50 BARX, distance from D1 surface toreference. If D1 is to the right ofthe reference, BARX is positive.

Columns 61-71 Ideptification

Column 72 If blank, then this element is not apart of the outer surface of the shell.If "1", then this element is a part ofthe outer surface of the shell.Column 72 must contain either a blankor a 1.

Fin Item Card:

Columns 1-10 FD1, radius on left

Columns 11-20 FD2, radius on right

Columns 21-30 FH, length

Columns 31-40 FR, density

Columns 41-50 FBARX, distance from FD1 surface toreference

Columns 51-60 FD, thickness of fin

Columns 61-71 Identification

Column 72 If blank, this element is not a part ofouter volume. If "1", this element ispart of the outer volume.

69

DI II DII ?A P3 M M

Known Item Card:

Columns 1-10 Weight

Columns 11-20 Polar inertia

Columns 21-30 Transverse inertia

Columns 31-40 Distance of CG to reference

Columns 41-50 Volume, if needed for column 72

Columns 61-71 Identification

Column 72 If 0, not outer volume. If "1', outervolume

Ogival Item Card:

Columns 1-10 GA, see Reference 1

Columns 11-20 GB, see Reference 1

Columns 21-30 GS, length of ogive

Columns 31-40 GRH, density

Columns 41-50 GREP, distance to reference

Columns 51-60 GRAD, radius of ogive

Columns 61-71 Identification

Column 72 If blank, no outer volume. If "L"outer volume

The dimension cards are included only for a weight calculationor a plot. If a stability calculation orly is 'equired, there willbe no dimension cards.

70

-i,

APPENDIX B

AEROBALLISTIC COEFFICIENTS PROGRAM (SP)

KEY VARIABLE INPUT

71

I. Program Constants and Parameters

SYMBOL VALUE OR FORMAT MEANING

PLS F10.4 Projectile length(calibers)

NLS F10.4 Nose length (calibers)

BLS FIO.4 Boattail length(calibers)

CGS F10.4 Distance of CG fromnose (calibers)

DIS F10.4 Diameter of shell(calibers)

AMS F10.4 Axial Toment of inertia(lb-in)

TMS F10.4 Traverse momenj ofinertia (lb-ins)

WTS F10.4 Weight (lb)

TST F10.4 Twist (caliber/turn)

BOS F10.4 Boom length (calibers)

II. Program Options

SYMBOL VALUE OR FORMAT MEANING

STS 1.0 Calculate stability

0.0 Do not calculatestability

ARS 1.0 Punch AERO I tables

0.0 Do not punch AERO Itables

73

* &NOT ,rU*t

.~ _______?A=____

SYMBOL VALUE OR FORMAT MEANING

SLS 1.0 Punch SAUL 7 tables

0.0 Do not punch SAUL 7tables

N6S 1.0 Punch NOL6D tables

0.0 Do not punch NOL6Dtables

NGS 1.0 Punch graph output

0.0 Do not punch graphoutput

74

,.4 . ..

APPENDIX C

INTERIOR BALLISTICS PROGRAM (IB)

KEY VARIABLE INPUT

75

SYMBOL VALUES OR FORMAT MEANING

DII F10.4 Diameter of gun (inches)

XLI F10.4 Length of projectiletraveled (inches)

VOl F10.4 Chamber volume (cubicinches)

MPI F10.4 Maximum pressure (psi)

PMI F10.4 Projectile weight (Ib)

PCI F10.4 Propellant weight (Ib)

PKI FIO.4 Propellant type (code)

MVI FO.4 Muzzle velocity (fps)

NOTE:

One of the above values must remain zero in order forthe interior ballistics to execute properly. The parameterthat is set initially to zero is variable to be calculated.Thus, seven of the above eight variables require data input.

77 - -

FCEDIIG P*iI R 4IT YI D

• l I

APPENDIX Dl

EXTERIOR BALLISTICS PROGRAM (AR)

KEY VARIABLE INPUT

79

- '- ., • , i u m InG B1 * ,i W u II

I. Phase Options:

SYMBOL VALUES OR FORMAT MEANING

NX1 1.0 Compute Phase I

0.0 Do not compute Phase I

NX2 1.0 Compute Phase II

0.0 Do not compute Phase II

NX3 1.0 Compute Phase III

0.0 Do not computePhase III

NX4 1.0 Compute Phase IV

0.0 Do not compute Phase IV

II. Initial Conditions and Constants:

SYMBOL VALUES OR FORMAT MEANING

THD F1O.4 Quadrant elevation(Q.E.) (degrees)

VMX FI0,4 Initial velocity(ft/sec)

WGT FIO,4 Missile weight (Ib)

DIJ, FIO,4 Diameter (inches) ofprojectile

XIN F1O.4 Initial range (ft)

YIN FIO.4 Initial altitude (ft)

TIN F10.4 Initial time (sec)

TWS F10.4 Effective gun twist(1/25 use 25.0, etc.)

81

r

•~~~~~PtCDN =AG B- WT.. III III II - -|H I

SYMBOL VALUES OR FORMAT MEANING

YLA F10.4 Launcher length (ft)

DEL F10.4 Integration increment(sec)

SDT FIO.4 Initial spin rate(rad/sec)

YFA F10.4 Terminal altitude (ft)on descent of trajec-tory

FFA F10.4 Factor used for temper-ature variations

CKD F10.4 Constant drag coef-

ficient(Only necessary

when KDC=2.0)

FCT F10.4 Form factor for alldrag tables. Thisvalue may be leftblank when form factoris unity.

BIA F10.4 Sustaining thrust (lb)in addition to thatwhich is necessary toovercome drag. (Useonly when CAN=1.0).

TKI FIO.4 Constant rollingmoment (lb-ft) duringPhase I.

TK2 F10.4 Constant rollingmoment (lb-ft) duringPhase II.

TK3 F10.4 Constant rollingmoment (lb-ft) duringPhase III.

82

SYMBOL VALUES OR FORMAT MEANING

TK4 F1O.4 Constant rollingmoment (lb-ft) duringPhase IV

11. Phase I and III Options:

SYMBOL VALUES OR FORMAT MEANING

NTH 1.0 Use variable thrust

2.0 Use constant thrust

MXX 1.0 Use variable burningrate

2.0 Use constant burningrate

IV. Phase I Options:

SYMBOL VALUES OR FORMAT MEANING

THR FIO.4 Constant thrust value(b) for Phase I(NTH = 2.0)

DTM F1O.4 Constant burning rate(lb-sec) during Phase I(MXX = 2.0)

BWT F1O.4 Booster weight (lb):

weight of metal parts

that are dropped offimmediately followingburnout in Phase I.

83

V. Phase III Options:

SYMBOL VALUES OR FORMAT MEANING

TH2 FIO.4 Constant thrust value(ib) for Phase III(NTH = 2.0)

DT2 F10.4 Constant burning rate(ib/sec) durin PhaseIII (MXX = 2.0

VI. Time Constants for Each Phase:

SYMBOL VALUES OR FORMAT MEANING

TM1 F10.4 Time in seconds atend of completion ofPhase I.

TM2 FIO.4 Time in seconds atend of completion ofPhase II.

TM3 F10.4 Time in seconds atend of completion ofPhase Ill.

TM4 F1O.4 Time in seconds atend of completion ofPhase IV.

DL FIO.4 Integration increment(sec) for Phase I.

DL2 F10.4 Integration increment(sec) for Phase II.

DL3 FIO.4 Integration increment(sec) for Phase Ill.

DL4 FIO.4 Integration increment(sec) for Phase IV.

84

SYMBOL VALUES OR FORMAT MEANING

DWI F10.4 Printout interval (sec)for Phase I

DW2 F10.4 Printout interval (sec)for Phase II

DW3 F10.4 Printout interval (sec)for Phase III

DW4 F10.4 Printout interval (sec)for Phase IV

VII. Program Options:

SYMBOL VALUES'OR FORMAT MEANING

KOC 1.0 Use variable dragcoefficients

2.0 Use constant dragcoefficients

KTH 1.0 Input magnus forceand magnus center ofpressure coefficients

2.0 Input magnus moment

coefficients

NUN 1.0 Output given in feet

2.0 Output given in meters

JZN F5.1 Number of trajectoriesto be computed

NJR F5.1 Number identifyingfirst trajectory runin the set specifiedby JZN

85

m -..

SYMBOL VALUES OR FORMAT MEANING

ISP 0.0 Compute spin andstability calculation

1.0 Perform only spincalculations

2.0 Omit spin and stabilityinputs (Tables I thruII)

IAX F5.1 Frequency of stabilitycalculations in termsof printout (Example -if it is desired to have

stability calculationsevery third printout,set IAX equal to 3.0)

NOR XX.X Number of time pointsentered in the "G-Norm" Table

NAT F5.1 Number of nonstandardaltitudes, temperaturesand densities to beentered (NAT is setequal 0.0 if 1959 ARDCstandard atmosphereis to be used)

CAN 1.0 Cancel drag

2.0 Do not cancel drag

VIII. Constant Factors for Table Changes:

SYMBOL VALUES OR FORMAT MEANING

T12 0.0 or 1.0 No change to Table 12F10.4 Multiply all dependent

variable values by thegiven constant

86

hJOC3DIN3 PA HSAWC-4OT 1ID

SYMBOL VALUES OR FORMAT MEANING

T13 0.0 or 1.0 No change to Table 13F10.4 Multiply all dependent

variable values by thegiven constant

NOTE: Symbols T14 through T18 perform the same function forTables 14 through 18, respectively, as T12 and T13described above.

IX. Factors Used in Error Analysis (See Example 4):

SYMBOL VALUES OR FORMAT MEANING

13P X.XXX Nominal variation factorfor Drag Table 13

THP XX.XXX Nominal variation factorfor the Thrust (THD)

VMP XXX.XX Nominal variation factorfor the Initial Velocity(VMX)

13D X.XXX Standard deviationfactor for Drag Table13

TSD XX.XXX Standard deviationfactor for the Thrust(THD)

VSD XXX.XX Standard deviationfactor for the InitialVelocity (VMX)

87

X. Constants Used to Plot Trajectory Output:

SYMBOL VALUES OR FORMAT MEANING

NSY 33.0 = Code numbers definingsymbol to be plotted

54.0 = at data points. Fora complete listing,

12.0 = see Reference 6.

16.0 =

14.0 =

NPL 1.0 Plot trajectory

0.0 Do not plot trajectory

DXG XX.X Number of Range Units(feet or meters) perinch on the X-axis ofthe graph

DYG XX.X Number of AltitudeUnits on the Y-axisof the graph

88

APPENDIX D2

EXTERIOR BALLISTICS PROGRAM (AR)

LIST OF TABLES

89

TABLE NUMBER MEANING

I Roll damping coefficients vs. mach no.

2 Roll moment coefficients vs. mach no.

3 Normal force coefficients vs. mach no.(Omit when ISP = 1. or 2.)

4 Ncrmal centers of pressure (calibersfrom nose) vs. mach no. (Omit when ISP= 1. or 2.)

5 Magnus moment coefficients vs. mach no.(Omit when either ISP = 1. or whenKTH 1 1.)

6 Magnus force coefficient vs. mach no.(Omit when either ISP = 1. or whenKTH = 2.)

7 Magnus centers of pressure (calibers

from nose) vs. mach no. (Omit wheneither ISP = 1. or when KTH = 2.)

8 YAW damping moment coefficients vs.mach no. (Omit when ISP = 1.)

9 Centers of gravity (calibers from nose)vs. time. (Omit when ISP = 1.)

10 Transverse moment of inertia (lb-ft2)

vs. time. (Omit when ISP = 1.)

11 Axial moment of inertia (lb-ft2) vs.time.

12 Drag coefficients vs. mach. no. forPhase I. (Omit when either NX1 = 0.or when KDC = 2.)

13 Drag coefficients vs. mach no. forPhases II and IV. (Omit when eitherNX2 = 0. and NX4 0. or when KDC :2.)

91

.. CD..... PAU ... OT 1LX D

TABLE NUMBER MEANING

14 Drag coefficients vs. mach no. forPhase III. (Omit when either NX3 =0. or KDC = 2.)

15 Thrust (Ib) vs. time for Phase I.(Omit when either NXI = 0. or NTH = 2.)

16 Missile weight (Ib) vs. time forPhase I. (Omit when either NX1 =

0. or MXX = 2.)

17 Thrust (Ib) vs. time for Phase III.(Omit when either NX3 = 0. or NTH = 2.)

18 Missile weight (ib) vs. time forPhase III. (Omit when either NX30. or MXX = 2.)

19 Altitude (ft) vs. temperature indegrees Rankine (Omit when NAT = 0.)

20 Altitude (ft) vs. density (lb-sec 2/ft4).

21 Normal acceleration in "g's" vs.time (Omit if NOR = 0.)

NOTE: The same increments in altitude must be used in Tables 19 and 20.

92

APPENDIX E

TERMINAL EFFECTIVENESS PROGRAM (LA)

KEY VARIABLE INPUT

93

I. Terminal Conditions and Constants:

SYMBOL VALUES OR FORMAT MEANING

PHB FIO.4 Burst height (feet)

AOF FIO.4 Angle of fall (degrees)

TVM F1O.4 Terminal velocity (ft/sec)

COR F1O.4 Scale factor to correct fortotal fragment weight (set to0.0 if no factor is to be used.)

NOZ FI0.4 Number of fragmentation zones

I. Lethal Area Computation Options:

SYMBOL VAL;'EI OR FORMAT MEANING

TRP O.J Use Simpson's Rule Integration.

1.0 Use trapezoidal Rule

NQA 3.0 Compute lethal areas for fox-hole and prone targets only.

2.0 Compute lethal areas for stand-ing, foxhole, and prone targetsonly

1.0 Compute lethal areas for stand-ing, foxhole, prone and the six-point standing target

SKP 1.0 Lethal areas re computed asdefined by NQA stated above

2.0 If NQA = 1.0, compute standingtarget lethal area only; if NQA= 2.0, compute six-point standingtarget lethal area only

95

III I I 1 1 IC I I Ij . ..

III. Lethal Area Cut-Off Options:

SYMBOL VALUES OR FORMAT MEANING

BET F1O.4 Cutoff angle (degrees)

COP 1.0 Use constant cutoff velocity(CVL)

2.0 Compute cutoff velocity foreach weight group using con-stant shape factor (CKQ)

3.0 Compute cutoff velocity foreach weight group using constant A/M value (AQM)

CVL F1O.4 Constant cutoff veloci~y

0.0 No cutoff mass used

RMC F1O.4 Constant mass cutoff (usedif nonzero value is entered)

IV. Fragment Blast Option:

SYMBOL VALUES OR FORMAT MEANING

BLT 0.0 Blast effects are not included

i.0 Use blast radii

RB1 FIO.4 First blast radius

RB2 FIO.4 Second blast radius (RB2must be greater than RBI)

V. FramentDrag Options:

SYMBOL VALUES OR FORMAT MEANING

CCK 0.0 Compute shape factor givenC12 and AMB

1.0 Use shape factor (CKQ)

96

CKQ F10.4 Shape factor

C12 F1O.4 Constant to determine shape

factor

AMB F10.4 Average value of A/M

NCD F10.4 Number of values in drag vs.velocity table (must be equalto or greater than two)

VI. Casualty Criteria Options:

SYMBOL VALUES OR FORMAT MEANING

ABC 0.0 Use casualty index value

1.0 Enter AXC, BXC, CXC values

NCC XX.X Casualty criteria index

AXC F10.4 Casualty criteria constant

BXC F10.4 Casualty criteria constant

CXC F10.4 Casualty criteria constant

VII. Print and Punch Options:

SYMBOL VALUES OR FORMAT MEANING

IOU 0.0 Do not print zone data output

1.0 Print zone data output

NDL 1.0 Print PK arcs vs. range (Ifmatrix is to be generated CLSmust also be equal to 1.0)

2.0 Do not print

CLS 0.0 Do not print

1.0 Print PK arcs vs. range ifmatrix is to be generated

97

NT7 1.0 Print and Punch avg PK vs.

range

2.0 Do not print or punch

3.0 Print avg PK vs. range

VIII. Matrix Options:

SYMBOL VALUES OR FORMAT MEANING

MAT 0.0 Do not compute matrix

1.0 Compute matrix

NDG F10.4 Number of cells in deflection

NRG FIO.4 Number of cells in range

RAD 1.0 Use cell size in range anddeflection and matrix center(RAM, DAM and CNT)

2.0 Compute cell size based onmaximum effective range

3.0 Use cell size in range anddeflection directions. RAX,DAY, DAX number of cells basedupon maximum range.

DAM F10.4 Cell size in deflectionUsed with RAD = 1.0

RAM F1O.4 Cell size in rangeUsed when RAD = 1.0

CNT F1O.4 Center of matrixUsed when RAD = 1.0

DAY F1O.4 Cell size in deflectionUsed when RAD = 3.0

RAX FIO.4 Cell size in rangeUsed when RAD = 3.0

98

- - ,m m m m m • ,- • ,.

MCT 0.0 Insures at least two arcscutting each cell of prob-ability of kill matrix

F10.4 Specifies given number of cuts

in each cell of matrix

OSK 0.0 Do not punch matrix cards

1.0 Punch matrix cards

IX. Target Posture for Matrix:

SYMBOL VALUES OR FORMAT MEANING

IN2 0.0 Do not compute matrix forORO foxhole

1.0 Compute matrix for ORO foxhole

IN4 0.0 Do not compute matrix forBRL prone

1.0 Compute matrix for BRL prone

IN7 0.0 Do not compute matrix forone-point standing target

1.0 Compute matrix for one-pointstanding target

IN8 0.0 Do not compute matrix forsix-point standing target

1.0 Compute matrix for six-pointstanding target

NOTE: Only one of the above postures may be selected for any givencomputer run.

99

.. .. . .. :. . . . .. . . '. .. . .. .. . . . . . ..7 -,

APPENDIX F

6-D TRAJECTORY PROGRAM (TR)

KEY VARIABLE INPUT

101

. . ...... ...... . .. , . " " , J-

I. Control Parameters:

SYMBOL VALUES OR FORMAT MEANING

NER 1.0 Flat earth.

2.0 Spherical earth.

ROT 1.0 Rotating earth.

2.0 No earth rotation.

NWD 1.0 Include wind tables.

2.0 Do not include wind tables.

NKC 1.0 Use "k" coefficients.

2.0 Use "c" coefficients.

NIR 1.0 Include atmosphere table.

2.0 Use standard atmosphere.

MAL 1.0 Use cutoff at max. alt.

2.0 Use no cutoff at max. alt.

NKS 1.0 Print coefficient tables.

2.0 Do not print coefficient tables.

KFC 1.0 Include magnus (force) co-efficients as input.

2.0 Do not include magnus co-efficients as input.

KPC 1.0 Include roll moment coefficients.

2.0 Do not include roll momentcoefficients.

KZC 1.0 Include (yaw) roll dampingcoefficients.

103

2.0 Do not include (yaw) rolldamping coefficients.

KCM 1.0 Include magnus force C.P.

2.0 Do not include magnus force C.P.

NTV 0.0 Use table of thrust vs. time

1.0 Use table of thrust vs. altitude.

KTP 1.0 Punch card output for PMTASS input.

0.0 Do not punch card output.

KON 0.0 Assume KFC input to be basedon 71/16

1.0 Assume KFC input to be based

on 1/8.

KMR 0.0 Print output in feet.

1.0 Print output in meters.

KSP 1.0 For three-way table lookup ofKFC and CPF. KFC and CPF willnow be a function of mach no.,angle of attack, and spin.

0.0 For two-way table lookup ofKFC and CPF.

NTA 24.0 Number of entries in atmospheretable. Default value is 24.0.

NIW 40.0 Number of entries in wind table.Default value is 40.0.

NAX F10.4 Max. number of angle of attackarguments in coefficients.

NMX F10.4 Max. number of mach numberarguments.

104

NUR F1O.4 Number of trajectories to becomputed using same controlparameters, atmosphere, thrust,wind, and ballistic coefficients.

NRU F10.4 Starting number of trajectoriesindicated by NUR above.

NNW FO.4 Number of range values in windtables (max. 40). NOTE: 40altitudes must be given foreach range value.

NSP F1O.4 Max. number of spin variables

to be supplied when KSP=1.0.

DMA FO.4 Max. time interval (DLT max.).

0.0 Set OLT min. = 0.00005.

DMI F10.4 Min. time interval (DLT min.).

0.0 Set DLT min. = 0.5.

I. Phase Options:

SYMBOL VALUES OR FORMAT MEANING

NIX 0.0 Do not compute Phase I.

1.0 Compute Phase I.

N2X 0.0 Do not compute Phase II.

1.0 Compute Phase II.

N3X 0.0 Do not compute Phase Il1.

1.0 Compute Phase III.

N4X 0.0 Do not compute Phase IV.

1.0 Compute Phase IV.

N5X 0.0 Do not compute Phase V.

1.0 Compute Phase V.

105

p .. . . . . . . . . . . .. . . , . . . .

N6X 0.0 Do not compute Phase VI.

1.0 Compute Phase VI.

N7X 0.0 Do not compute Phase VII.

1.0 Compute Phase VII.

III. Initial Conditions:

SYMBOL VALUES OR FORMAT MEANING

ANA F10.4 Longitude (degrees).

ANB F10.4 Latitude (degrees).

AZI F10.4 Azimuthal heading (degrees).

QEL F10.4 Angle of elevation (degrees).

XOT F10.4 Initial displacement (feetor meters).

YOT F10.4 Initial altitude (feet or

meters).

TAS F10.4 Time at start (seconds).

AKN F10.4 Multiplies air densities bythis factor (0.0 is read as 1.0).

DTR F10.4 Diameter (inches).

WTR F10.4 Weight (pounds).

VXP F10.4 VX feet per second.

VYP FIO.4 Vy feet per second.

VZP F10.4 Vz feet per second.

SPT F10.4 Missile spin rate (rad/sec).

WYP F1O.4 Pitch rite (rad/sec).

WZP F10.4 Yaw rate (rad/sec).

106

-I

CIX F10.4 Booster initial IX (axialmoment, lb-sq in).

CIY FIO.4 Booster initial ly (transversemoment, lb-sq in).

XCG F10.4 Booster initial center ofgravity from nose (inches).

PUB F10.4 Booster specific impulse(lb-sec/lb fuel).

WDT F10.4 Booster burning rate (lb-fuel/sec).

CX2 F10.4 Booster final IX (axial momentlb-sq in).

CY2 F10.4 Booster final ly (transversemoment, lb-sq in).

CG2 F10.4 Booster final center of gravity(inches).

ANO F10.4 Booster nozzle diameter (inches).

AMA F10.4 Booster mal. angle, A (degrees).

TMA FI0.4 Booster mal. angle, T (degrees).

RXT FIO.4 Booster mal. distance, RX (inches).

RYT FIO.4 Booster mal. distance, Ry (inches).

RZT FIO.4 Booster mal. distance, RZ (inches).

TKA F1O.4 Booster jet torque moment (inches).

TMD F10.4 Booster thrust modifier.

CXS F10.4 Main stage initial IX (lb-sq in)./CYS FIO.4 Main stage initial Iy (lb-sq in).

CGM F1O.4 Main stage initial center ofgravity (inches).

107

r-I III.lI I I n *

. m

PUS F10.4 Main stage specific impulse

(Ib-sec/Ib).

WRS F10.4 Main stage burning rate (Ib/sec).

CX6 FIO.4 Main stage final IX (lb-sq in).

CY6 F10.4 Main stage final ly (lb-sq in).

CG6 F10.4 Main stage final center ofgravity (inches).

D05 F10.4 Main stage nozzle diameter(inches).

AL5 F10.4 Main stage mal. angle, A (degrees).

TL5 F10.4 Main stage mal. angle, T (degrees).

RX5 F10.4 Main stage mal. distance, RX(degrees).

RY5 F10.4 Main stage mal. distance, Ry(inches).

RZ5 F10.4 Main stage mal. distance, RZ(inches).

TK5 F10.4 Main stage jet torque arm (inches).

TM5 F10.4 Main stage thrust modifier.

TII F10.4 Time at end of Phase I (seconds).

T12 F10.4 Time at end of Phase II (seconds).

T13 FIO.4 Time at end of Phase III (seconds).

T14 F10.4 Time at end of Phase IV (seconds).

T15 F10.4 Time at end of Phase V (seconds).

T16 F10.4 Time at end of Phase VI (seconds).

WT5 FIO.4 Initial main stage weight (pounds).

108

L - I

BRB F10.4 Burning rate at separation

(Ib/sec).

FF1 F10.4 Phase I form factor drag.

FF2 F10.4 Phase II form factor drag.

FF3 F10.4 Phase III form factor drag.

FF4 F10.4 Phase IV form factor drag.

FF5 F10.4 Phase V form factor drag.

FF6 FIO.4 Phase VI form factor drag.

FF7 F10.4 Phase VII form factor drag.

ST5 FIO.4 Separation thrust (pounds).

IV. Integration and Print Options:

SYMBOL VALUES OR FORMAT MEANING

DII F10.4 Phase I integration step size(seconds).

012 F10.4 Phase II integration step size(seconds).

D13 F10.4 Phase III integration step size(seconds).

D14 FIO.4 Phase IV integration step size(seconds).

D15 F10.4 Phase V integration step size(seconds).

016 F10.4 Phase VI integration step size(seconds).

D17 F10.4 Phase VII integration step size(seconds).

109

DAZ F1O.4 Diameter (in.) of second stage.If left blank will be assumed=DTR

0SI FIO.4 Phase I output spacing (seconds).

DS2 F10.4 Phase II output spacing (seconds).

DS3 F1O.4 Phase III output spacing (seconds).

DS4 FIO.4 Phase IV output spacing (seconds).

DS5 FIO.4 Phase V output spacing (seconds).

DS6 F10.4 Phase VI output spacing (seconds).

DS7 F10.4 Phase VII output spacing (seconds).

SPZ F10.4 Spin rate of second stage. Ifleft blank, SPT will be assumedto be that which existed at endof last phase.

V. Constants and Parameters:

SYMBOL VALUES OR FORMAT MEANING

PRS F10.4 Static test atmospheric pressure(lb/sq in).

VWX F10.4 Constant range wind (feet/sec).

VWY F10.4 Constant cross-range wind (feet/sec).

VWZ F10.4 Constant vertical wind (feet/sec).

IYO FIO.4 Initial deflection (feet).

TZF F10.4 Terminal altitude (feet).

COD F10.4 CODE (three numeric characters toidentify job - are printed out).

110

APPENDIX G

RECOIL MECHANISM DESIGN PROGRAM (RM)

KEY VARIABLE INPUT

' 111

I. Program Options:

SYMBOL VALUES OR FORMAT MEANING

XND 0.0 Run next set of input data

1.0 Do not run next set of inputdata

PRT 0.0 Print auxiliary output data

1.0 Do not print auxiliary outputdata

ISW 0.0 Switch to bypass namelist

II. Constants and Parameters

SYMBOL VALUES OR FORMAT MEANING

TIR F10.4 Rise-fall time of rod pullcurve (sec)

RHI F10.4 Density of primary material-steel (lb/in.

2)

SIG F10.4 Allowable stress in primarymaterial (lb/in. 2)

RH2 F10.4 Density of secondary material-bronze (lb/in.

3)

XMR F10.4 Mass of recoiling parts-initially the mass of guntube and components (in-slug).

XMP F10.4 Mass of projectile (in-slug).

XMC F10.4 Mass of propelling charge(in-slug)

RSR FIO.4 Design recoil length-short (in.)

RLR F10.4 Design recoil length-long (in.)

XIR F10.4 Net impulse imparted (lb-sec)

113

1WJ

SYMBOL VALUES OR FORMAT MEANING

VOR F10.4 Projectile muzzle velocity(in./sec)

ALP F10.4 Time to centroid of breechforce (sec)

PMX F10.4 Design fluid pressure-recoil(lb/in.

2)

DGT F10.4 Diameter of gun tube at breech(in.)

DR1 F10.4 Allowable expansion (recoil)

DR2 F10.4 Allowable expansion (C <recoil inner)

DR3 F10.4 Allowable expansion (Crecoil outer)

DLM F10.4 Allowable deflection (breech

ring)

XNR F10.4 Number of recoil cylinders

CDR F10.4 Discharge coefficient for recoil

SO F10.4 Stress concentration forthreaded members

SC2 F10.4 Stress concentration forgrooves and thread reliefs

OVS F10.4 Allowable difference in sizebetween recoil and C I recoil

DLP FIO.4 Increment of design fluidpressure (lb/in.2)

CLR FIO.4 Clearance between gun tubesand cylinders (in.)

TRU F1O.4 Height from floor to trunnions(in.)

114

SYMBOL VALUES OR FORMAT MEANING

BAL F10.4 Thickness of rotor for ballisticprotection (in.)

CMT F10.4 Distance from front (muzzleend) of breech to gun tubecenter of gravity (in.)

ROF F10.4 Distance from floor to roofin cab (in.)

PGS FIO.4 Starting value of maximumgas pressure (lb/in.2 )

115

t - - : ... . . . .

APPENDIX H

SABOT DESIGN PROGRAM (SD)

KEY VARIABLE TNPUT

117

! via

F .. ... ....

I. Program Options:

SYMBOL VALUES OR FORMAT MEANING

SOC 0.0 Segments of sabot are open

1.0 Segments of sabot are closed

GFC 0.0 Rear geometry is cylinder

1.0 Rear geometry is frustrum

NPR 1.0 Printer plotting

2.0 CALCOMP plotting

3.0 Printer and CALCOMP plotting

II. Constants and Parameters

SYMBOL VALUES OR FORMAT MEANING

PKP F10.4 Peak pressure (PSI)

PPW F10.4 Projectile-flechette weight(ib)

KK1 F10.4 Percentage head friction

CCF F10.4 Percentage rear strut friction

NNS F10.4 Number of sabot segments

WOB F10.4 Weight of obturator (ib)

FRB F10.4 Major frustrum radius (in.)

FRL F10.4 Minor frustrum radius (in.)

LFR F10.4 Length of frustrum (in.)

RVB F10.4 Volume of rear section -0.0 is meaningless (in.

3)

FVH FIO.4 Volume of sabot head (in.3 )

119

.. POW%

SPS FIO.4 Sabot material density (lb/in?)

THK F10.4 Thickness of rear strut (in.)

PFD F10.4 Diameter of projectile (in.)

MBD F10.4 Mean diameter between lands

and grooves of bore (in.)

120

APPENDIX I

HEPPNER-INTERIQR BALLISTICS (IH)

KEY INPUT VARIABLES

121

I. Program Options:

SYMBOL VALUES OR FORMAT MEANING

ICK F10.4 Plotting parameter for sub-routine SYMBOL (angle at whichtext is to be printed - seeReference 11).

IPL 1.0 Printout only

2.0 Plot only

3.0 Printout and plot

RNS F10.4 Number of runs

ZLI F10.4 Number of lines between typeout.

II. Constants and Parameters:

SYMBOL VALUES OR FORMAT MEANING

PEP F10.1 Peak pressure (PSI)

VOM F10.1 Muzzle velocity (ft/in 2)

CHV F8.3 Chamber volume (in3)

CSA F8.3 Cross-section of bore (in2 )

WTG F8.2 Weight of gun and recoilingparts (lb)

DST F8.3 Distance travelled along tube (in.)

PWT F8.3 Projectile weight (lb)

SER F8.4 Specific energy ratio

INP F8.3 Initial pressure (PSI)

AFQ F8.6 Adjustment factor for Q

AFR FB.6 Adjustment factor for R

123

I .A .

PRF F8.3 Pressure factor

TP1 F10.4 Type of propellant

CW1 F10.4 Weight (Ib)

WB1 F10.4 Web (in.)

TP2 F10.4 Type of propellant

CW2 F10.4 Weight (ib)

WB2 F1O.4 Web (in.)

TP3 F10.4 Type of propellant

CW3 F10.4 Weight (Ib)

WB3 F10.4 Web (in.)

TP4 F10.4 Type of propellant

CW4 FIO.4 Web (in.)

WB4 FIO.4 Web (in.)

124

APPENDIX J

IPSDATA SAMPLE OUTPUT

125

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136

APPENDIX K

SAMPLE TTY & BATCH RESULTS

137

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147

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155

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161

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183

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APPENDIX L

UNABBREVIATED OUTPUT AT THE TELETYPE

275

. it •4,-4_.

Unabbreviated Output at the Teletype

Normal usage of IPSSM at the teletype involves batching the job toa central computer site, where the full output can later be retrieved,and/or asking for an abbreviated set of results to be recallable atthe same teletype terminal. At Picatinny Arsenal a routine DISPLAYOUTPUTis available to allow the full unabbreviated output of an IPSSM runto be examined at the teletype. Specific instructions follow.

Before typing IPSM at the start of the teletype run, enter:

ATTACH,DISPLAYDISPLAYOUTPUT,CY=1,ID=MISDSEAD.

Then proceed normally, but when ready to batch your program, enter:

BATCH_,JOB,INPUT,HERE.

A name will then be assigned to your job; wait until the job hasexecuted and is in the output queue, then enter:

BATCH,(JOBNAME),LOCAL

DISPLAY,(JOBNAME)

The system response will be

PAGE NUMBER = 1 TOTAL PAGES OF OUTPUT = N

PAGE NUMBER = --- (RIGHT JUSTIFIED)

The page number to be examined is now entered in right-justifiedformat (i.e., the third page would be designated as 003).

Upon completion of examination at the teletype terminal, PAGE 999is entered to terminate this routine. You may then logout or use theDISPOSE facility to send a permanent record of the unabbreviatedrFesuT-ts to batch terminal. To dispose your output to a specificterminal, enter the following statement:

DISPOSE,OUTPUT, (TEPI.IINAL CODE)

277

Imen, a

DISTRIBUTION LIST

Copy No.

CommanderFrankford ArsenalATTN: Mr Sylvan Eisman 1Philadelphia, PA 19137

CommanderRock Island ArsenalATTN: SARRI-LR Mr W. McGarvey 2

Mr Burnett Moody 3

Rock Island, IL 61201

CommanderRedstone ArsenalATTN: Mr Richard Eppes 4

Redstone, AL 35809

HeadquartersDepartment of the Amy 5Washington, DC 20310

CommanderUS Army Armament CommandATTN: DRSAR-RDM, Dr. N. Coleman 6Rock Island, IL 61201

CommanderPicatinny ArsenalATTN: SARPA-CO, Mr. H.W. Painter 7

Mr. R.C. Lundquist 8

SARPA-FR-S, Mr. J.W. Gregorits 9Mr. A.A. Loeb 10Mr. G. Demitrack 11Mr. G. Friedman 12

SARPA-AD, Mr. V. Lindner 13

SARPA-AD-C, Mr. S. Einbinder 14Mr. E. Leibowitz 15

SARPA-AD-D, Mr. E.H. Buchanan 16Mr. R. Reisman 17Mr. T. Stevens 18

SARPA-AD-E, Mr. D. Katz 19Mr. S. Bernstein 20

SARPA-AD-F, Mr. F. Saxe 21

SARPA-ND, Mr. A.M. Moss 22

279

SARPA-ND-C, Mr. C,.I. Jackman 23

Mr. P. Angelotti 24

Mr. 0. Miller 25

Dr. L.F. Nichols 26 - 55

Mr. F. Scerbo 56

SARPA-ND-D, Mr. H. Grundler 57

Mr. M. Rosenberg 58

SARPA-MI, Mr. D. Grobstein 59

SARPA-MI-E, Mr. R.I. Isakower 60

SARPA-MI-M, Mr. B.D. Barnett 61

SARPA-MI-T, Mr. I.E. Rucker 62

Mr. F. McMains 63

Mr. J. Bevelock 64

SARPA-TS-X, Mr. L. Glass 65

Mr. R. Drake 66

SARPA-QA-X, Mr. E. Loniewski 67

Dover, NJ 07801

CommanderUS Army MICOMATTN: AMSMI-RHS-AHELD/Bldg 8971 Mr Arthur Werkheiser 68

Redstone Arsenal, AL 35809

Defense Documentation Center 69 - 80

Cameron StationAlexandria, VA 22314

280

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