Livermore Software Technology Corporation LS-INGRID Mesh Generator User Manual

LS-INGRID: A Pre-Processor

And Three-Dimensional Mesh Generator

For The Programs LS-DYNA,

LS-NIKE3D

And TOPAZ3D

Version 3.5

Livermore Software Technology Corporation

2876 Waverley Way

Livermore, CA 94550

August 1998

Mailing Address:

Livermore Software Technology Coporation

2876 Waverley Way

Livermore, California 94550-1740

Support Address:

Livermore Software Technology Corporation

97 Rickenbacker Circle

Livermore, California 94550-7612

FAX: 510-449-2507

TEL: 510-449-2500

EMAIL: [email protected]

Copyright



1989-1998 by Livermore Software Technology Corporation

All Rights Reserved

LS-INGRID

T

ABLE OF

C

ONTENTS

TABLE OF CONTENTS

ABSTRACT .............................................................................................................................................. I.1

PREFACE.................................................................................................................................................. I.1

1. LS-INGRID BASICS ........................................................................................................................... 1.1

1.1 The Parser............................................................................................................................. 1.1

1.2 Command File Format.......................................................................................................... 1.2

1.3 The Calculator ...................................................................................................................... 1.2

1.4 Built in Variables ................................................................................................................. 1.3

1.5 Basic Arithmetic Options ..................................................................................................... 1.4

1.6 Logical Operations ............................................................................................................... 1.4

1.7 Functions .............................................................................................................................. 1.4

1.8 Options ................................................................................................................................. 1.5

1.9 Directives ............................................................................................................................. 1.6

2. Control Commands............................................................................................................................... 2.1

3. IDEAS Part ........................................................................................................................................... 3.1

3.1 Options and Functions.......................................................................................................... 3.1

4. PATRAN Part....................................................................................................................................... 4.1

4.1 Options and Functions.......................................................................................................... 4.1

5. NASTRAN Part ..................................................................................................................................... 5.1

5.1 Options and Functions.......................................................................................................... 5.1

6. Standard Part ........................................................................................................................................ 6.1

6.1 DEFINITIONS ..................................................................................................................... 6.1

6.2 Index Progression ................................................................................................................. 6.10

6.3 Part Commands and Functions............................................................................................. 6.11

7. Beam Part .............................................................................................................................................. 7.1

7.1 Options and Functions.......................................................................................................... 7.3

8. Old Data Part ........................................................................................................................................ 8.1

8.1 Options and Functions.......................................................................................................... 8.5

9. MAZE Part ........................................................................................................................................... 9.1

9.1 Required Part Data ............................................................................................................... 9.1

9.2 Options and Functions.......................................................................................................... 9.3

9.3 Functions .............................................................................................................................. 9.5

10. EDIT Part............................................................................................................................................ 10.1

10.1 Options and Functions........................................................................................................ 10.1

11. DYNA3D Part .................................................................................................................................... 11.1

11.1 Options and Functions......................................................................................................... 11.1

12. Loads and Boundary Conditions......................................................................................................... 12.1

iii

TABLE OF CONTENTS LS-INGRID

13. Interactive Commands ........................................................................................................................ 13.1

13.1 Exploded View Commands ................................................................................................ 13.10

13.2 TAURUS/Post-Processing Commands............................................................................... 13.11

14. Two-Dimensional Line Definitions .................................................................................................... 14.1

15. Three-Dimensional Line Definitions .................................................................................................. 15.1

16. Surface Definitions ............................................................................................................................. 16.1

17. Volume Definitions............................................................................................................................. 17.1

18. Coordinate Transformations ............................................................................................................... 18.1

19. LS-DYNA2D Commands and Materials ............................................................................................ 19.1

19.1 LS-DYNA2D Material Input .............................................................................................. 19.4

19.2 General Material Options ................................................................................................... 19.4

20. LS-DYNA3D Commands and Materials ............................................................................................ 20.1

20.1 LS-DYNA3D Material Input .............................................................................................. 20.13

20.2 General Material Options ................................................................................................... 20.13

21. Equations-of-State............................................................................................................................... 21.1

22. LS-NIKE2D Commands and Materials .............................................................................................. 22.1

22.1 LS-NIKE2D Material Input ................................................................................................ 22.4

23. LS-NIKE3D Commands and Materials .............................................................................................. 23.1

23.1 LS-NIKE3D Material Input ................................................................................................ 23.4

24. TOPAZ Commands and Materials....................................................................................................... 24.1

24.1 TOPAZ Material Input ....................................................................................................... 24.3

ACKNOWLEDGMENTS ......................................................................................................................... ACK.1

REFERENCES .......................................................................................................................................... REF.1

iv

LS-INGRID INTRODUCTION

LS-INGRID: A Pre-Processor and Three Dimensional Mesh Generator for the Programs LS-DYNA, LS-NIKE3D and TOPAZ3D.

ABSTRACT

LS-INGRID is a general purpose pre-processor for the programs, LS-NIKE2D[1],

LS-NIKE3D[2], LS-DYNA2D[3], LS-DYNA3D[4], TOPAZ2D[5] and TOPAZ3D[6]. It can be used as a simple translator to convert various databases to these programs. In addition, it is a general purpose three-dimensional mesh generator with considerable capability to deal with complex geometries and allows for parametric geometric modeling.

PREFACE

LS-INGRID is an alternative mesh generator for finite element modeling which is principally intended as "research" program or one that focuses on various capabilities and techniques which are not addressed by commercial mesh generators. As a general purpose mesh generator, the capabilities are fairly complete with a wide range of geometric capabilities. An extensive parametric modeling capability is also support. LS-INGRID is most effective in combination with NIKExx and DYNAxx. A considerable amount of effort has gone into making LS-INGRID support virtually every feature of these programs (an almost impossible task given the rate that LS-DYNA3D improves). Although the usage of

LS-INGRID can seem somewhat combersome relative to more traditional mesh generation schemes, the productivity of users performing parametric modeling tasks with LS-INGRID can much higher in some cases.

Unlike most general purpose mesh generators, LS-INGRID was developed by the

Author for the sole purpose of aiding them in their routine analysis tasks. The original code was developed to assist in the preparation of SAP5 models at the University of Tennessee beginning in 1978. The 1978 program was loosely based on index space ideas obtained from the INGEN[7] program which was developed at Los Alamost National Laboratory. In 1981, the author moved to Lawrence Livermore National Laboratory. INGRID developments continued at LLNL on the side because LLNL was committed to the development of

MAZE3D, but did not have any supported three-dimensional mesh generator. In 1985, the

MAZE3D effort was finally abandoned and INGRID became the principal mesh generator of

LLNL by default. At this time, the program was merged with the MAZE[8] program to produce a version similar to the current LS-INGRID.

After 1985, development work continued at SPARTA with a steady evolution and the

I.1

INTRODUCTION LS-INGRID

addition of the parametric modeling capabilities. LS-INGRID is the latest version supported by LSTC. Development on LS-INGRID is continuing in the directions which proved most popular in the past. The emphasis will continue to be providing a general purpose capability focused on NIKExx and DYNAxx with much work being done to support advanced modeling capabilities which are not found in any other program.

I.2

LS-INGRID

1. LS-INGRID BASICS

LS-INGRID BASICS

The LS-INGRID input file is an ASCII datafile which contains a complete description of the analysis. The commands are input using a parser which is simple and efficient, but also has a considerable amount of flexibility for dealing with complex situation.

1.1 T

HE

P

ARSER

The parser basically takes a stream of blank delimited character strings and number and decodes them for the program. The character strings are for commands or parameters and are arbitrary in length. Normally, only the first four characters are significant.

Deviations from this rule are described in the documentation. Numbers can be input in a variety of formats ranging from simple integers to floating point numbers specified with an

"E" format. If an error is detected in the decoding of a number, the user will be notified.

All character input for commands or numbers is automatically converted to lower case for processing. Thus case selection can be performed strictly for the purpose of enhancing readability. Any number of commands and numbers can be placed on a single line of input with the only constraint being the 80 character input line limit. In the commands description, upper case characters or characters enclosed within quotes are commands which are to be typed exactly as lower (ignoring case). Lower case items represent variables which require input.

Comments may be included by using a "c" anywhere in the input followed by a blank and the comment. If the comment does not begin in column 1, then the "c" must be preceded by a blank. Blocks of input lines can be commented by preceding the block with the character "{" and ending it with "}".

Although items are normally blank delimited, commas can also be used to separate items. Two commas which are separated by blanks are treated as having the number 0 between them. Lists of numbers or character strings are input and terminated normally by a

";". This ";" does not necessarily need a blank between it and the last item. If the list is a list of numbers, then the list can be terminated by simply beginning the next command and eliminating the semicolon.

A function calculator is also built into the parser to permit advanced programming techniques to be used. This calculator is invoked by placing the calculator command within two square brackets. If the parser is expecting a character string, then the function will be processed without any other effect on the command stream. If a number is expected, then the calculator will send whatever value it calculates to the program. See Section 1.3 for a detailed description of the calculator functions.

1.1

LS-INGRID BASICS LS-INGRID

1.2 C

OMMAND

F

ILE

F

ORMAT

The LS-INGRID input file "ingridi" has a relatively free flowing input format with few restrictions, some of which are:

Define an item before using it; e.g. a line definition must occur before applying it to a part.

Materials data and code execution options cannot be input until a code output option has been selected.

Some commands have order dependent effects, e.g. rotating local coordinate systems successively about different axes.

Many items which have names in LS-INGRID are assigned numbers for the analysis program. These numbers are assigned sequentially starting from one based on the order of first occurrence of names.

The form of ingridi is as follows:

Title line (format is 80al)

Control commands (Section 2)

Part definition

Control commands

(Section 3 - 8)

Part definition

.

.

.

END

1.3 The Calculator

The calculator is used to insert expressions into LS-INGRID input descriptions and is particularly useful for developing parametric models. When used in conjunction with the

"include" command, it is possible to write programs for individual parts which can then be assembled into larger models. The calculator capabilities are invoked by inserting an expression anywhere in the input between two square brackets (e.g. [5*sin(30)]). If at that point in the input, LS-INGRID is expecting an integer or a floating point number, then the expression is evaluated and the results passed to LS-INGRID as either the nearest integer or floating point number. If a character string is expected, then the expression is evaluated and skipped over as if it were just a comment.

1.2

LS-INGRID LS-INGRID BASICS

Within the calculator variables may be created and they will remain in effect until the program completes. Thus the expression [length=5*5] would store 25.0 into a variable named "length" and return 25.0 to LS-INGRID if a number is expected. This variable could be recalled later by [length].

Separate from the variable capability is a function capability. The function capability stores an expression which may consist of variables and other functions into a particular name for future evaluations. An example follows:

[a=1] [b=2] [c=1] Set some variables so this won't evaluate improperly.

[def root1(a,b,c)=(-b+sqrt(b*b-4*a*c))/2*a] Define the function.

[root1(2,1,0)] Evaluate the function.

The general form of the calculator's capabilities is as follows:

[option name = expression]

Following is a summary of the calculator capabilities:

1.4 B

UILT IN

V

ARIABLES

Variable Value pi e

# p e

Result of last operation nnode The current node number is set to nnode when outside of a part. Until the first part is complete, nnode is zero.

nbeam nbrick nshell

The current beam element number is set to nbeam outside of a part. Until the first part is complete, nbeam is zero.

The current brick element number is set to nbrick outside of a part. Until the first part is complete, nbrick is zero. nbrick includes both regular bricks and 8-node shell elements.

The current shell element number is set to nshell outside of a part. Until the first part is complete, nshell is zero.

npart This variable is set inside parts and is set to the current part number.

1.3

LS-INGRID BASICS LS-INGRID

1.5 B

ASIC

A

RITHMETIC

O

PTIONS

Operator Purpose Example

-

+ Addition

Subtraction

3+4

4-1

/

*

^

%

Multiplication

Division

Exponentiation

Modulo arithmetic

5.5*7.6

7.5/length

10^3

5%2

1.6 L

OGICAL

O

PERATIONS

The result of a logical operator is 1.0 if true and 0.0 if false. These may be used either as expressions or as part of "if-then-else-endif" constructs.

Function Purpose

==

!=

Equal to

Not equal to

<

<=

>

Less than

Less than or equal to

Greater than

!

||

>=

&&

Greater than or equal to

Logical and

Logical or

Negation

1.7 F

UNCTIONS

The angles in the following trigonometric functions are all in radians by default. This can be controlled by the "deg" and "rad" options listed in the "options" section below.

Function Purpose sin(angle) cos(angle)

Trigonometric sine.

Trigonometric cosine.

tan(angle) asin(x) acos(x)

Trigonometric tangent.

Inverse trigonometric sine.

Inverse of trigonometric cosine.

atan(x) atan2(y,x) sinh(x) cosh(x) tanh(x) exp(x)

Inverse of trigonometric tangent.

Two argument inverse tangent.

Hyperbolic sine.

Hyperbolic cosine.

Hyperbolic tangent.

Exponential.

1.4

LS-INGRID LS-INGRID BASICS

ln(x) ln2(x) log(x) min(x

1

,x

2

, . . .) max(x

1

,x

2

, . . .) gcd(x

1

,x

2

, . . .)

Natural logarithm.

Logarithm base 2.

Logarithm base 10.

Minimum of arbitrary number of parameters.

Maximum of arbitrary number of parameters.

Greatest common denominator.

lcm(x

1

,x

2

, . . .) Least common multiple.

asa(angle,side,angle) Evaluate the triangle and return largest angle.

ass(angle,side,side) Evaluate the triangle and return largest angle.

sas(side,angle,side) Evaluate the triangle and return largest angle.

sss(side,side,side) Evaluate the triangle and return largest angle.

rnd rnd2

Return a random number.

Return a random number but do not update the seed

.

1.8 O

PTIONS

Function Purpose help help subject def name=expression

Print the help message.

Print help for any of the calculator functions or options.

Define a function "name". Any time name is encountered in future expressions, it will be recursively save filename load filename quit rad evaluated.

Save all variables to file "filename".

Load variables from file "filename".

Exit calculator (this will shut down LS-INGRID).

All angles for trigonometric functions are assumed to be defined in radians (default).

deg list flist root(c

n

, . . .,c

1

,c

0

)

All angles for trigonometric functions are assumed to be defined in degrees.

List current active variables.

List current definitions of functions.

Determine the roots of the nth degree polynomial with factor(x) integral(e

1

,e

2

,f,v) coefficients c

0

through c

n

.

Factor x into prime coefficients.

Determine the integral of the function f with respect to the variable v. The limits are from e

1

to e

2

which may degree n be expressions. A Romberg integration rule is used.

The degree of Romberg integration for the "integral" command is n (default=4). Simpson's rule corresponds to n=1 and the trapezoidal rule is n=0.

solve (f

1

,f

2

, . . .,f

n

) for (x

1

=v

1

+d

1

, . . . x

n

=v

n

+d

n

)

Solve a system of nonlinear equations. The equations are previously defined functions, f

1

through f

n

.

Variables x

1

through x

n

must be listed and the calculator will attempt to determine them. Optional inputs include v

i and d

i

. The initial starting guess is v

i

and the initial increments for iterations are d

i

.

1.5

LS-INGRID BASICS LS-INGRID

maxits n tol t display

Set the maximum number of iterations for the "solve" command to n (default=30).

Set the convergence tolerance for the "solve" command to t (default=1e-6).

The display command is a brute force method for improving results of a divergent solve command.

Results are displayed after every iteration.

if expr1 then expr2 else expr3 endif

If expression 1 is true than evaluate expression 2.

Otherwise, evaluate expression 3.

1.6

LS-INGRID LS-INGRID BASICS

1.9 D

IRECTIVES

LS-INGRID provides directives to control the flow of logic in command file descriptions. Directives begin in the first column of a line and no other commands are allowed on the same line as the directive. This capability is patterned similar to the preprocessor used in the C-programming language.

D

IRECTIVE

F

UNCTION

This is for #IF - #ELSE - #ENDIF constructs.

#ELSE

#ELSEIF expression Perform conditional execution of the following input lines as part of an #IF - #ELSEIF -

#ENDIF construct.The results of expression should be either true (1) or false (0).

#ENDIF

#ENDMACRO

#IF expression

This signifies the end of an #IF - #ENDIF block.

End definition of macro initiated by #MACRO.

Conditionally execute the following lines of input. The results of expression should be either true (1) or false (0).

#INCLUDE name

#MACRO name

#RETURN

Begin execution of commands in file name.

When a #RETURN or an end-of-file is encountered, control is returned to the original file.

Begin definition of macro name. The definition ends when an #ENDMACRO is encountered.

Cease reading input from the current input file and return control back to the next higher level file. See also #INCLUDE.

1.7

LS-INGRID CONTROL COMMANDS

2. Control Commands

Control commands are optional and can be input in any order. They must not be placed inside a part. The following control commands are available:

ARRI lc Generate arrival times for pressure surfaces associated with load curve lc. Arrival times are generated by assuming that the loads are caused by a wave. This wave starts from a threedimensional point, line, or surface and travels with a velocity. The arrival time is the time required for the wave to travel from the source to an individual pressure segment.

Options:

CG p

CL p

COSINE

DECAY d type [a]

LINE p

x

p y

p z

v x

v y

v z

PLANE p

x

p y p z v x

v y

v z

POINT p

x

p y

p z

TOFF dt

;

VELO vel

Pressure cannot exceed p.

Pressure cannot be less than p. (This option is selected with p=0.0 when "COSI" is executed).

The pressure varies as a function of the angle between the pressure segments normal and the direction of the wave from the source.

The pressure wave decays as a function of the distance from the source. The distance at which the scale factor for the input pressure equals 1.0

is d. The type of decay is specified by type.

type = "R": relationship is 1.0/R

= "R2": relationship is 1.0/R

2

= "R3": relationship is 1.0/R

3

= "CONSTANT": no decay

= "EXP": relationship is 1.0/R

a

The source is a line. (p

x

p y

,p z

) is any point on the line and (v

x

,v y

,v z

) is any vector along the line.

The source is a plane. (p

x

,p y

,p z

) is any point on the plane and (v

x

,v

y

,v

z

) is any vector normal to the plane.

The source is a point located at (p

x

p y

,p z

).

Add dt to the arrival time.

The wave travels with velocity vel.

Terminate this command.

2.1

CONTROL COMMANDS LS-INGRID

BATCH

BELT

LS-INGRID is to operate in batch mode. The interactive commands are placed at the end of the LS-INGRID model description so that they can be read automatically. A graphics device will still be requested since one of the batch output devices may be desired. If no graphics are needed use the NOPL command.

This section defines the properties of seat belt systems, but possibly has other applications.

The seat belt capability is supported in LS-920 and later. A detailed description is included in the LS-920 manual.

SLIPRING name Define a slipring.

Slip rings provide for a contiuous feeding of material through a pully. One node for the slip ring is fixed to a support structure. The slip ring logic works with seatbelt elements.

Two seatbelt elements must also be identified which touch the slip ring. The friction coefficient, f, determines the resisting force to the belt being pulled through the slipring.

;

FRIC fFriction coefficient for material sliding through the slip ring.

End of slipring definition.

RETRACTOR name

Define a retractor.

Retractor elements simulate the normal function of retrator systems for seat belts within an automobile.

;

DELAY dt

FEDL feed_length

LCL lcl

LCU lcu

PULL pullout

SENSOR name

Time delay for retractor operation.

Load curve for loading.

Load curve for unloading.

Amount of pull-out between time delay ending and retractor locking.

Sensor for trigering retractor. At least one must be specified and no more than four.

End of retractor definition.

PRETENSIONER name Define pretensioner.

During an automobile accident, pretensioners are frequently employed to automatically increase the tension on a seatbelt. Both pyrotechnic and spring type systems are supported. Usually, a sensor triggers the event.

PYROTECHNIC

LCP lcp

RETR name

TIME t

Use a pyrotechnic pretensioner.

Load curve for pretensioner.

Retractor name effected.

Time between sensor triggering and pretensioner acting.

2.2

LS-INGRID

PRELOAD

LOCK

DELAY dt

SPRING ispd

DELAY dt

;

SPRING ispd

DISTANCE

SENSOR name

CONTROL COMMANDS

The pretensioner consists of a preloaded spring.

Time between sensor triggering and pretensioner acting.

Spring element number.

The pretensioner consists of a lock spring which is removed.

Time between sensor triggering and pretensioner acting.

Spring element number.

The distance between nodes is locked.

Pretensioner is activated by one to four sensors.

End of pretensioner definition.

SENSOR name Define sensor.

A variety of sensor systems are incorporated into automobiles to sense the onset of a crash. The accelerometers are simply used for saving output to an ASCII file. The other sensors are used to initiate the retractors and pretensioners.

ACCE a

X

Y

Z

TIME dt

CNV

n

;

Options:

;

RETR

TIME t

DIST

RETR name

RATE r

TIME t

DMAX d max

DMIN d min

The sensor is an accelerometer.

The acceleration is measured in the x-direction.

The acceleration is measured in the y-direction.

The acceleration is measured in the z-direction.

The sensor is triggered if a is exceeded for duration dt.

The sensor triggers based on the retractor pullout rate.

Retractor name.

Pullout rate.

Time over which rate of pull-out must be exceeded.

The sensor triggers after time t.

The sensor triggers based on the distance between two nodes.

Maximum distance.

Minimum distance.

End of Sensor definition.

End of BELT command.

Define control volume n. (MVMA/DYNA3D,

LS-910 and later.)

2.3

CONTROL COMMANDS

DAMP d

MATE m

1

. . . m

n

;

PSCA psca

REVERSE

TYPE m

VINI vini

VSCA vsca

LS-INGRID

Set airbag damping constant to d.

The airbag consists of material subset m

1

. . .

m n

.

Pressure scale factor used for converting pressures calculated by the thermodynamic control volume to pressures which will be applied to the finite element model.

(default=1.0)

Reverse normals.

Control volume is of type m. Input for type m control volume begins immediately.

Initial filled volume. (default = 0.0)

Scale factor for converting calculated volume to volume used for thermodynamic calculations.

(default = 1.0)

Type 1:

The pressure-volume relationship is of the form:

Pressure = p

0

* s/Relative volume

Type 3:

P0 p

0

;

SCAL s

Initial pressure.

Scale factor.

Terminate control volume input.

The pressure-volume relationship is of the form: m out

=

A

2 p

ρµ

γ

γ −

1







Q

2

γ

−

Q

( )

γ

 where

Q = \f(pe,p)

γ

= \f(cp,cv) p = \f((

γ

– 1)E,V)

Options:

CV c

v

CP c

p

TIN t

LCM lcm

MU m

Heat capacity at constant volume.

Heat capacity at constant pressure.

Input gas temperature.

Load curve defining input mass flow rate.

Shape factor for exit area. If m is negative, then

|m| is the number of a load curve which defines the shape factor as a function of pressure.

2.4

LS-INGRID

A a

;

PE p

e

RHO r

GRAV g

CONTROL COMMANDS

Exit Area. If a is less than zero, then |a| is the number of a load curve which defines the area as a function of pressure.

Ambient pressure.

Ambient density.

Gravitational constant. If the ambient density is defined in units of weight per volume, then the actual gravitational constant must be used.

Otherwise, g is set to 1.

Terminate control volume input.

Type 4:

Type 4 applies a constant internal pressure scaled by s until a point in time. A load curve is used to cause a change in behavior at some point in time. When the change occurs, the volume of the control volume is first calculated and used to initialize an adiabatic gas relationship.

PINT p int

LC lc

SCAL s

PE p

e

;

RHO r

GAMM g

Interior pressure.

Load curve.

Scale factor for pressure.

Ambient pressure.

Density of gas when initialized.

Ratio of specific heats.

Terminate control volume input.

Type 5:

Type 5 is an implementation of the Wang-Nefske airbag model.

CV c

v

CP c

p

TIN t

LCM lcm

C23 c23

A23 a23

CP23 c23¢

AP23 a23¢

PEXT p

e

RHO r

GRAV g

VOLT v

LCOUT lc

;

PINI p

0

PPOP ppop

COOR

nc data

Heat capacity at constant volume.

Heat capacity at constant pressure.

Input gas temperature.

Load curve defining input mass flow rate.

Shape factor for exit hole.

Exit hole area.

Shape factor for exit porisity.

Exit hole porosity.

Ambient pressure.

Ambient density.

Gravitational constant.

Optional tank volume.

Optional load curve specifying exit flow as a function of pressure.

Optional initial overpressure (gauge).

Optional pressure where a plug is assumed to pop and venting begins.

Terminate control volume input.

Input nc global coordinate systems. Global coordinate systems remain in effect until reset using this command. Coordinate system data is

2.5

CONTROL COMMANDS

CSCA

s

CSYM

Options:

AXIS p

x

p y

p z

;

DEFAULT

dir

DETP

mat

Options:

LNPT p

x

p y

p z

q x

q y

q z

n

;

POINT p

x

p y

p z

TIME t

DN2D

i j

DN3D

DS

n

LS-INGRID

described in detail in the section on Coordinate

Transformations.

Scale all nodal coordinates by s.

Define cyclic symmetry interface.

The vector which orients the axis for rotational cyclic symmetry is (p

x

,p y

,p z

).

Terminate the CSYM command.

The default directory for finding include files is dir. Currently, this is only supported on

CONVEX computers.

Define detonation point for material mat. If mat is zero then all materials are detonated.

Generate n equals spaced detonation points on the line from (p

x

,p y

,p z

) to (q

x

,q y

,q z

).

Detonate the point (p

x

,p y

,p z

).

Lighting time for detonation point.

Terminate this command.

Output generated is compatible with LS-

DYNA2D i and j flags specifying which 3-D coordinates correspond to the LS-DYNA2D r and z coordinates. i and j can have values "x",

"y", or "z". This activates additional commands which are described in LS-DYNA2D Options

and Materials.

Output is generated for LS-DYNA3D. This activates additional control commands which are described in LS-DYNA3D Options and

Materials.

Input digitized 3-D surface number n. Digitized surfaces consist of a surface defined by triangles. This is not smooth for coarse meshes; however, 10,000 and more triangles are common in defining surfaces to achieve

2.6

LS-INGRID

Option:

MOVE data

Type 1: GRID n

i

n j

Type 2: FEM m n

x

1

y

1

z

1

x

2

y

2

z

2

...

i

1

j

1

k

1

l

1

i

2

j

2

k

2

l

2

...

Type 3: CONT ncont

Options:

XLE x

YLE y

ZLE z

CHORD scal

FNU n

u

FNL n

1

XF x

f

YF y

f

ZF z

f

L3D l

L3E l n

;

Data: n x

1

y

1

z

1

... x

n

y n

z n

CONTROL COMMANDS

reasonably accurate definitions. This command consist of "DS n" optionally followed by a coordinate transformation and then one of the digitized surface types is input to complete the command.

Move the surface definition by data. data is described in the section on Coordinate

Transformations.

The surface is defined by a logically regular set of points in three dimensions. n

i

*n

j

points must be input in the following order. x

11

y

11

z

11

... x

il

y

i1

z

i1

... x

ij

y ij

z ij

.

The surface is a grid of finite element quadrilaterals. It has m nodes and n elements.

Input m nodal points.

Input n four node elements.

The surface is defined by ncont contours that each have an arbitrary number of points.

X-coordinate of leading edge.

Y-coordinate of leading edge.

Z-coordinate of leading edge.

Scale factor for the chord length.

The contour is defined by n

u

points on the upper surface followed by n

1

points on the lower surface.

Contour points are in the plane X=x

f

.

Contour points are in the plane Y=y

f

.

Contour points are in the plane Z=z

f

.

Use three-dimensional line definition l. The number of points on the contour is the number of points used to define the line definition.

Use three-dimensional line definition l with n equal spaced points.

Terminate option and read required data.

Skip this section if L3D or L3E is requested.

Number of points on contour. (Input only if

nu=n1=0).

Contour coordinates. If XF was used, do not input any X coordinates, and similarly for YF and ZF.

2.7

CONTROL COMMANDS

Type 4: FUNC n

s

n t

x y z

Type 5: PROJ m offset

LS-INGRID

Define a parametric surface using parameters s and t. The number of points for making a grid in the s direction is ns and the number of points in the t direction is nt. s and t are assumed to range from 0 to 1. x, y and z are input as functions of s and t.

The current digitized surface is formed by taking digitized surface m and projecting m a distance "offset" in the normal direction.

Options:

XSYM xsym xtol

YSYM ysym ytol

ZSYM zsym ztol

;

END

FDEF

n v

1

v

2

v

3

v

4

v

5

v

6

v

7

v

8

v

9

Digitized surface m is symmetric about X=xsym.

This forces normal components of points within xtol of the symmetry plane to be in the Y-Z plane only.

Digitized surface m is symmetric about Y=ysym.

This forces normal components of points within ytol of the symmetry plane to be in the X-Z plane only.

Digitized surface m is symmetric about Z=zsym.

This forces normal components of points within ztol of the symmetry plane to be in the X-Y plane only.

End digitized surface definition.

Terminate the model description.

Define fold plane number n. Fold planes are used later in the interactive phase to generate folded models of meshes such as airbags. The nine parameters have the following meanings:

v

1

= x or y position of fold relative to the unfolded mesh.

v

2

= x or y position of fold relative to the folded mesh.

v

3

= postive / negative fold flag. If v

3

=+1, then the folded portion lies along the positive coordinate. If v

3

=-1, then the folded portion lies along the negative coordinate.

v

4

= fold thickness desired.

2.8

LS-INGRID CONTROL COMMANDS

v

5

= Up / down flag. If v

5

=+1, then the material is folded onto the top of the mesh. If v

5

=-1, then the material is folded under the mesh.

v

6

= Direction. The fold plane is normal to the

X-axis if v

6

=0 and normal to the Y-axis if v

6

=1.

v

7

= Fold logic flag. The thin fold logic is used if v

7

= 0 and the thick fold logic is used if v

7

=1.

v

8

= Scale factor. This can be used to scale the normal thickness offsets at the fold point. This will increase the separation between layers, but possibly cause unacceptable mesh distortion.

v

9

= Fold radius. This will take precedence over the internally computed fold radius.

See also FOLD and PFOLD under Interactive Commands.

FIGN

f expr When performing fold definition f, ignore nodes with undeformed coordinates that result in expr being true. (e.g. fign 6 [y<=0]).

FLEX

name Begin definition of flexure-torsion or cardan joints (LS-920 and later.)

Options:

CARDAN

FLEXION

LC1 lc1

LC2 lc2

LC3 lc3

LC4 lc4

LC5 lc5

LC6 lc6

MATM m

MATS m

MSYS s

This joint is a cardan joint.

This joint is a flexion-torsion joint.

First torque-twist load curve.

Second torque-twist load curve.

Third torque-twist load curve.

Fourth torque-twist load curve.

Fifth torque-twist load curve.

Sixth torque-twist load curve.

Define master material.

Define slave material.

Define master side local system.

2.9

CONTROL COMMANDS

PHIF s

PHIS s

PSIF s

PSIS s

SSYS s

STOPA- s

STOPA+ s

STOPB- s

STOPB+ s

STOPC- s

STOPC+ s

THEF s

THES s

FMOV

f data

FOPT

f options

Options:

L3D

ANGLE

θ

SCALE scale

;

FSYM

m x y z n

x

n y

n z

s f

GEOC

igeo mat

LS-INGRID

First angle friction.

First angle stiffness.

Third angle friction.

Third angle stiffness.

Define slave side local system.

Negative stop for first angle.

Positive stop for first angle.

Negative stop for second angle.

Positive stop for second angle.

Negative stop for third angle.

Positive stop for third angle.

Second angle friction.

Second angle stiffness.

After performing fold definition f, affected nodes are moved by the transformation described in data (see Coordinate

Transformations).

Input additional parameters for airbag folding. .

Fold abour 3-D line denfinition ldnum.

Fold the material

θ degrees.

The folded section will become thicker by the factor scale.

End of FOPT command.

Define failing symmetry plane m. (x,y,z) is any point on the plane and (n

x

,n y

,n z

) is any normal vector. Solid element faces are slaved to the symmetry plane and failure occurs when the normal stress exceeds s

f

.

Geometric contact entity definition. A geometric contact entity is an analytical surface type which can be attached to a rigid body of

2.10

LS-INGRID

Options:

COUPLE type n

FRIC f

INSIDE

MATE m

1

. . . m

n

;

MOVE n

OUTSIDE

PNLT p

QUAD q

GMI

n

;

SD n

INCLUDE

fname

JD

j

Options:

SJ

RJ

CJ

PJ

UJ

TJ

PNLT p

NC icode

CONTROL COMMANDS

material mat. (MVMA/DYNA3D, LS-910 and later.)

The contact is between a CAL3D/MADYMO coupled rigid body and a deformable body. The rigid body type is either "ELLIPSE" or

"PLANE" and n is the number of the shape in either CAL3D or MADYMO.

Set friction coefficient to f.

The slaved mesh is the material subset m

1

. . .

m n

.

Move the entity using the global transformation number n.

Penalty p.

Quadrature rule.

q=0: Nodes only.

q=1: Element centers.

q=2: 2«2 quadrature on segments.

Use surface definition n. Valid surface types include planes, ellipsoids and spheres.

Terminate this command.

Increment the default material number by n for each global copy of a part. This number is initially set to zero.

Include the information in file fname in the command stream. The INCLUDE command can perform to 20 levels deep.

Begin joint definition for joint j. Diagrams of the types of joints are shown in Figure 2-1.

Nodes are assigned to joint definitions within parts.

Spherical joint.

Revolute joint.

Cylindrical joint.

Planar joint.

Universal joint.

Translational joint.

Joint penalty.

This joint is a simple nodal constraint. The common translational degrees of freedom are specified by icode:

=-1: Rigid Massless Beam (LS-902 and later)

2.11

CONTROL COMMANDS

;

RC icode

REPE n

LS-INGRID

= 0: Rigid Massless Truss (LS-902 and later)

=1: X

=2: Y

=3: Z

=4: X and Y

=5: Y and Z

=6: Z and X

=7: X, Y, and Z

This joint is a simple nodal constraint. The common rotational degrees of freedom are specified by icode:

=0: none

=1: X

=2: Y

=3: Z

=4: X and Y

=5: Y and Z

=6: Z and X

=7: X, Y, and Z

Repeat the current joint definition for a total of n joints.

Terminate this command.

2.12

LS-INGRID CONTROL COMMANDS

Spherical joint Revolute joint

Cylindrical joint Planar joint

Universal joint Translational joint

Figure 2-1. Joint definitions.

2.13

CONTROL COMMANDS

L3D

n data

LABELS

Options:

ELEMENT m

MAT m

NODE m

;

LCD

n m t

1

f

1

... t

m

f m

LCDF

n m f t

1

t

n

LD

n data

LEV

n

Options:

ADD m

COOR n data

LS-INGRID

Begin definition of three-dimensional line n. If line n has been previously defined, this command has the effect of destroying the old definition. See Three Dimensional Line

Definitions for a description of the data for this command.

Define offsets for node, element and other item numbering. This applies to meshes which are imported after this command.

Offset element labels by m.

Offset material labels by m.

Offset node labels by m.

End of LABELS command.

Define load curve n with m pairs of time function points.

Define load curve n with m pairs of time function points. f is input as an analytical function of variable t which ranges from t

1

to t

n

.

Thus to input one period of a sine wave with

100 points:

LCDF 1 100 [sin(t)] [0] [2*pi]

Begin definition of two-dimensional line n. If line n has been previously defined, this command has the effect of destroying the old definition. See Two Dimensional Line

Definitions for a description of the data for this command.

Define part transformation sequence n. This defines a series of operations which can be performed on groups of parts.

Add the list of transformations in sequence number m to the current sequence.

Add n coordinate transformations to the current sequence. The data for this command is described in the section, Coordinate

Transformations.

2.14

LS-INGRID

CYLI

PROD i j

LMI n

;

REPE l

1

l

2

...;

SPHE

LSYS name

Options:

PLANE p

x

p y

p z

r x

r y

r z

2 c

x

c y

c z

p x

p y

p z

r x

r y

r z

NODE n

1

n

2

n

3

;

MAT n data

MATE m

MAZT tol

MDBC m lc amp f

x

f y

f z

CONTROL COMMANDS

Perform a cylindrical coordinate transformation.

Form the product of sequence i with sequence j.

If sequence i has 1 transformations, and sequence j has m transformations,then this option produces 1*m transformations and adds them to the current sequence.

Copy parts in global coordinate systems l

1

, l

2

, ...

Perform a spherical coordinate transformation.

Terminate this command.

Increment the default material number by n for each local copy of a part. This number is initially set to zero.

Define local system name for single point constraints, etc.

The local X-axis is parallel to (p

x

,p y

,p z

) and

(r

x

,r y

,r

z

) is a vector in the XY-plane.

The center of the local system is (c

x

,c y

,c z

).

(p

x

,p y

,p z

) is a point along the local X-axis and

(r

x

,r y

,r z

) is a point in the XY-plane.

The center of the local system is node n

1

. Node

n

2

is a point along the local X-axis and node n

3 is a point in the XY-plane.

Terminate LSYS command.

Code-dependent material data can be input. See the chapter on the specific computer program for input related to the MAT command.

The default material name for the following parts is set to m. This name is initially set to 1.

Set the MAZE tolerance to tol. This is used for a variety of two-dimensional line definitions and the MAZE parts.

Material displacment boundary condition. This command is used only for rigid body materials in DYNA3D. The load curve number is lc, amp is the scale factor and (f

x

,f y

,f z

) is in the load direction.

2.15

LS-INGRID

NSMOOTH n

CONTROL COMMANDS

NOTE "Copyright 1985"

Perform n smoothing operations on surfaces when using the standard part. The default is zero since this can be costly and is usually necessary only for complex free form surfaces.

Input orientation vector n.

ORV n {options}

Options:

PLANE vx vy vz

VECTOR vx vy vz

The sping/damper distances are measured in the plane defined by normal vector (vx,vy,vz).

The spring/damper distances are measured along the vector defined by (vx,vy,vz).

End the ORV command.

Execute a FORTRAN pause statement.

PAUSE

;

PLANE nplane Input nplane plane definition. These planes are for applying boundary conditions only. Do not try to use this command more than once in the same input file.

Repeat the following information for each plane:

p x

p y

p z

Global coordinates of any point on the plane.

q x

q y

q z

Any vector normal to the plane.

Tolerance All nodes within a distance less than tolerance from the plane are included in the definition. If the tolerance is negative, no nodes will be found. The "SW" command in the standard part can also be used to include nodes in the definition.

Options:

CYLI radius len

FRIC m

LCD lc vx vy vz

The stonewall is a cylindrical surface. The radius is radius and the length is len. If len=0, then an infinite cylinder is assumed. (LS-910 and later).

Specify stonewall friction properties.

m=0: Frictionless sliding occurs.

0<m<1: m is colomb friction coefficient

(LS-910 and later).

m=1: No tangential motion allowed during contact.

Load curve lc specifies the displacement history of the stone wall in the direction (vx,vy,vz).

2.17

CONTROL COMMANDS

LCV lc vx vy vz

MASS mass

OVERRIDE i

PLANE a

x

a y

a z

alen blen

PRISM a

x

a y

a z

alen blen clen

SPHE radius

VELOCITY v

LS-INGRID

Load curve lc specifies the velocity history of the stone wall in the direction (vx,vy,vz).

The stonewall has mass mass. (LS-910 and later).

If a node is also on plane i, then this plane takes precedence.

The stonewall is a finite plane. (a

x

,a y

,a z

) is a vector which specifies an in-plane a-axis. The

b-axis is determined from the cross-product of the a-axis with the normal vector. alen is the extent of the plane along the a-axis and blen is the extent along the b-axis. (LS-910 and later).

The stonewall is a prism. (a

x

,a y

,a z

) is a vector which specifies an in-plane a-axis. The b-axis is determined from the cross-product of the a-axis with the normal vector. alen is the extent of the plane along the a-axis and blen is the extent along the b-axis. c-len is the extent along the normal axis. (LS-910 and later).

The stonewall is a spherical surface. The radius is radius. (LS-910 and later).

The stonewall has a initial velocity v normal to the surface. (LS-910 and later).

One of the following three options is required to terminate the plane definition:

PPLV

ASYM

STONE or SW

SYMM

PRINT v

PSCALE m1 m2

SECTION scale

Asymmetric boundary conditions are applied to the nodes.

The boundary condition is a stonewall.

Symmetric boundary conditions are applied to the nodes.

Eliminate the part transformation sequence at the top of the stack. See also "PPLV" and

"LEV" in this section.

Echo the value of v to the terminal. This is primarily used with the calculator functions to verify calculations.

Scale properties. Materials from m1 to m2 are treated by this command. If m1 and m2 are numbers, than standard numeric comparisons are used to determine if materials are within the range. Otherwise, string comparisons are used.

Scale all section properties by scale. This allows for a general unit conversion on section

2.18

LS-INGRID

PSLV n

QUAD

;

RBMG

m

1

m

2

READ

Options:

NDIV n

NURB name

SC03 name

ROTATION p

x

p y

p z

v x

v y v z

w

RVBC m lc idof amp f

x

f y

f z

CONTROL COMMANDS

properties.

Terminate PSCALE command.

Begin performing part transformation sequence

n on all following parts. This remains in effect until a PPLV command is given. A stack is used for performing transformation sequences.

PSLV adds a transformation sequence to the top of the stack and PPLV eliminates the top sequence on the stack.

Turn on generation of elements with quadratic shape functions in standard part. This causes 8node shells and 20-node bricks to be generated.

Merge rigid body m

1

to rigid body m

2

. m

1

is the master and m

2

is the slave. For a group of merged rigid bodies, there can be only one master. (DYNA3D only.)

Read external database.

Number of subdivisions for internal NURB surface processing. (Default=1) Setting this to

2 or 3 can improve the reliability of intersections calculated from NURB surfaces, however, costs and memory requirements will increase roughly proportional to the square of this number.

Read a NURB surface database in file name.

This ends the READ command.

Read a SC03 database in file name. This ends the READ command.

Assign an initial rigid body rotation to all parts defined after this command. (p

x

, p y

, p z

) is any point on the axis of rotation and (v

x

, v y

, v z

) defines the axis direction. The angular velocity is w.

Rigid body velocity boundary condition. This command is used only for rigid body materials in DYNA3D. The load curve number is lc, amp is the scale factor and (f

x

,f y

,f z

) is in the load direction. idof can be:

=1: X-translational degree-of-freedom

=2: Y-translational degree-of-freedom

=3: Z-translational degree-of-freedom

2.19

CONTROL COMMANDS

SD n data

SDMV s

1

s

2

data

SI islide

Options:

A3

A5

A13

BIRTH t

BOND t

BOXM x

m

x x

y m

y x

z m

z x

BOXS x

m

x x

y m

y x

z m

z x

COMP t

LS-INGRID

=.4: translational velocity in direction of vector (f

x

,f y

,f z

).

=5: X-rotational degree-of-freedom

=6: Y-rotational degree-of-freedom

=7: Z-rotational degree-of-freedom

=8: rotational velocity in direction of vector

(f

x

,f y

,f z

).

=9: Y and Z degrees-of-freedom for node rotating about the global X-axis

=10: Z and X degrees-of-freedom for node rotating about the global Y-axis

=11: X and Y degrees-of-freedom for node rotating about the global Z-axis

Begin definition of surface n. If surface n has been previously defined, this command has the effect of destroying the old definition. See

Surface Definitions for a description of the additional input for this command.

Move surface definitions s

1

through s

2

. data is described in the section on Coordinate

Transformations.

Define sliding interface islide. These options apply to both slide surfaces and slide lines.

Select contact interface type a3 (LS-920).

Contact type a3 is insensitive to orientation of the contact segments.

Select contact interface type a5 (LS-920).

Contact type a5 is insensitive to orientation of the contact segments.

Select contact interface type a13 (LS-920). This model is a single surface method which is principally used for inflating folded airbags.

Birth time for interface (LS-910).

GA slideline option: Bond shear modulus.

Define box for master side of sliding interfaces

(LS-910, VECDYNA).

Define box for slave side of sliding interfaces.

(LS-910, VECDYNA)

GA slideline option: compressive strength of concrete.

2.20

LS-INGRID

DAMP d

DEATH t

DNIS

DNTS

DUMMY

FAIL e

FD fd

FE d

FFN f

FFNE f

FFS f

FFSE f

FRIC f

FS fs

GA

HDMG t

LCV

LS

MATERIAL MAST m

1

m

2

... ;

MATERIAL SLAV m

MAXS t

MERGE

1

m

2

... ;

CONTROL COMMANDS

Damping coefficient (percent of critical) (LS-

910).

Death time for interface (LS-910).

Discrete nodes impacting surface.

Discrete nodes tied to surface.

Dummy slide surface. This option can be used to allow distinct but coincident nodes.

Tied slide surface with failure when volume weighted strain exceeds e (LS-DYNA3D).

Dynamic friction coefficient.

Exponential decay coefficient.

Normal failure force.

Normal failure exponent.

Shear failure force.

Shear failure exponent.

Set static and dynamic friction to f. (default=0)

Static friction coefficient.

Select General Atomic's 1-D rebar slideline.

GA slideline option: Exponent in damage curve.

Load curve for force-penetration in types 19 and

20 contact. (LS-920 and later).

Turn on limited search flag. (Default is off).

The master side of the interface consists of material subset m

1

, m

2

, ... (VEC/DYNA3D, LS-

920 and later).

The slave side of the interface consists of material subset m

1

,

m

2

, ... (VEC/DYNA3D, LS-

920 and later).

GA slideline option: maximum shear displacement.

Coincident nodes are merged.

2.21

CONTROL COMMANDS

MSCA s

MTHI t

NFAIL fs

NOMERGE

NSWS

PNLM p

PNLS p

PNLT p

RADIUS t

SETS

SFAIL fs

SINGLE

SL

SSCA s

STHI t

SV

T10

T11

T12

T13

T14

T15

T16

LS-INGRID

Scale factor for master thicknesses. (LS-910 and later).

Master side thickness. (LS-910 and later).

Normal failure stress.

Coincident nodes are not merged.

Nodes spot welded to surface.

Change master side penalty to p.

Change slave side penalty to p.

Change penalty to p.

GA slideline option: Radius of rebar.

Shell edge tied to shell surface.

Shear failure stress.

Single sided slide surface.

Sliding only.

Scale factor for slave thicknesses. (LS-910 and later).

Slave side thickness. (LS-910 and later).

Sliding with voids (default).

Type 10 interface.

Type 11 interface. This is the box/material limited automatic contact for shells in LS-910 and later. It is the single surface airbag contact for MVMA/DYNA3D.

Type 12 interface. Automatic contact for shells.

(LS-910 and later).

Type 13 interface. (LS-920 and later. Converts to the similar type 11 in MVMA/DYNA3D).

Type 14 interface. Surface to surface eroding contact. (LS-920 and later).

Type 15 interface. Node to surface eroding contact. (LS-920 and later).

Type 16 interface. Single surface eroding

2.22

LS-INGRID

T17

T18

T19

T20

SPD n

TBI

TCRS r

TIED

;

VFRI v

CONTROL COMMANDS

contact. (LS-920 and later).

Type 17 interface. Surface to surface symmetric/asymetric constraint method. (LS-

920 and later).

Type 18 interface. Taylor and Flanagan contact force calculation technique from PRONTO3D.

(LS-920 and later).

Type 19 interface. Rigid body to rigid body with specified force deflection curve. (LS-920 and later.)

Type 20 interface. Node to rigid body with specified force deflection curve. (LS-920 and later.)

Tie-break interface.

Thermal contact resistance is r.

Tied slide surface

Viscous friction coefficient is v.

Terminate this slide surface definition.

Input definition for spring/damper.

Options:

ROTA

The spring/damper is rotary and not translational.

Options (the following options end the SPD command):

LE e Define a linear elastic spring with stiffness e.

(force/displacement).

LV d

IEP e t y

NE l

Define a linear damper with damping constant

d. (force/velocity).

Define an elastic-plastic spring with stiffness e

(force/displacement), tangent stiffness t

(force/displacement), and yield y (force).

Define a nonlinear spring using load curve l. l represents force versus displacement.

NV l

Define a nonlinear damper using load curve l. l represents force versus velocity.

2.23

CONTROL COMMANDS

GN l l

l

ul

b Y t

Y c

VE K

0

K i

b T c

F c

iopt

STOL t

TCO l K

SLVM m

STOP

SYNTAX

1

m

2

ul

flag

Options:

REGION

Options:

STANDARD

Options:

STANDARD

LS-INGRID

Define a general nonlinear spring. The spring loads along load curve l l

and unloads along l

ul with hardening parameter b. The initial yield in tension is Y

t

and Y

c

for compression. (LS-910 and later).

Three-parameter Maxwell viscoelastic spring.

K

0

is the short time stiffness, K

i

is the long time stiffness with decay parameter b. T

c

is a cutoff time and F

c

is the force after cutoff. iopt is zero for an incremental treatment and nonzero for a continuous treatment. (LS-910 and later).

Inelastic tension or compression only. The spring loads along load curve l. K

ul

is an optional unloading stiffness and flag is -1.0 for tension only and +1.0 for compression only.

(LS-910 and later).

This command applies to the DYNA3D coupling with CAL3D or MADYMO3D.

Deformable materials can be identified as being slaved to rigid bodies which are coupled to

CAL3D or MADYMO3D. During the

DYNA3D initialization, the deformable materials will be repositioned to reflect the shifting to global coordinates performed by

CAL3D or MADYMO3D. The master rigid body is material m

1

and the slaved deformable material is m

2

. (LS-920 and later.)

Set the tolerance for surface intersections to t.

(Default=1.0e-6.)

Execute a FORTRAN stop statement.

Command for redefining the syntax of various part options.

Set syntax for <Region> in part definitions.

Set syntax for <Region> in standard part.

Use the standard syntax for <Region> in the

2.24

LS-INGRID

;

MAZE

Options:

STANDARD

PD

;

OLD

Options:

STANDARD

1

2

;

SYSEND

SYSTEM name

CONTROL COMMANDS

standard part.

Terminate SYNTAX command.

Set syntax for <Region> in the MAZE part.

The syntax for the <MRegion> is according to this manual and the 1985 INGRID manual from

LLNL.

The syntax for the <MRegion> has 6 indices according to the modification to INGRID by

LLNL after 1986.

Terminate SYNTAX command.

Set syntax for <Region> in the OLD, BEAM and other low level input parts.

Use the standard definition of <Region>. This assumes <Region> = imin imax, unless the first item encountered is an expression in brackets.

For an expression, it will only read one parameter.

Use a one paramter definition of <Region>.

<Region> = imin=imax normally identifies single nodes and elements only, but can also identify a range with an expression.

Use a two parameter definition of <Region>.

This does not allow an expression to specify the range, but is necessary for the following:

B [nodebeg] [nodeend] 111000.

This is because the standard method would see

[nodebeg] and convert to a one parameter method.

Terminate SYNTAX command.

Terminate existing subsystem definition.

Begin definition of subsystem name. This remains in effect until a SYSEND or another

SYSTEM command is encountered or another

2.25

CONTROL COMMANDS

T12

T13

TEMP t

THIC t

TIND mat I

xx

I xy

I xz

I yy

I yz

I zz

TINE mat I

xx

I yy

I zz

I xy

I yz

I zx

TIVE mat v

x

v y

v x

w x

w y

w z

TMCG mat c

x

c y

c z

TMM n t

TMSM m s

1

s

2

... ;

TMVP mat (transformation)

TRACER

LS-INGRID

SYSTEM.

This command must be typed just prior to the use of the MAZE part. The third side, L

3

, of the next part will have exactly two times as many elements as side L

1

. The transition is accomplished with quadrilateral elements. This command does not apply to triangular parts.

This command must be typed just prior to the use of the MAZE part. The third side, L

3

, of the next part will have exactly three times as many elements as side L

1

. The transition is accomplished with quadrilateral elements. This command does not apply to triangular parts.

All parts defined after this command have initial temperature t. This remains in effect until reset with another "Temp" command. This can be overridden with an individual part. t can be a single number or it can be an expression of the form t(x,y,z). This allows nodes to be assigned temperatures based on an analytical expression of a temperature distribution based on the nodal coordinates.

The default thickness for shells is t.

Specify inertia tensor.

Specify inertia tensor.

Initial velocities (global), translational and rotational

Specify center of gravity.

The total mass of material n is t. The density of the material is determined by dividing the total mass of the material by the calculated volume.

The inertial properties which are input for material m include the masses of deformable materials s

1

, s

2

, .... The properties of m are computed such that the total mass properties of

m, s

1

, s

2

... is equal to the input values.

Move center of gravity and inertias.

Transformation refers to the section, Coordinate

Transformations.

Define tracer particles for material.

2.26

LS-INGRID

Options:

LNPT p

x

p y

p z

q x

q y

q z

n

MATERIAL t

POINT p

x

p y

p z

;

TRANS

SPACE t

TIME t

TZ2D i j

TZ3D

WRITE format v1 v2 . . ;

XOFF d

XSCA s

x

VD n data

CONTROL COMMANDS

Generate n equals spaced tracer particles on the line from (p

x

,p y

,p z

) to (q

x

,q y

,q z

).

The tracer particle is fixed to a material point.

Define a tracer particle starting at point

(p

x

,p y

,p z

).

The tracer particle is fixed in space.

Activation time for tracer particle.

Terminate this command.

This command must be typed just prior to a

MAZE part and changes the command such that

k+m elements are generated along sides L

1

and

L

2

and m elements are generated along sides L

3 and L

4

. This command does not apply to triangular parts or parts with variable zoning.

Output generated is compatible with TOPAZ2D.

i and j flags specifying which 3-D coordinates correspond to the TOPAZ2D r and z coordinates. i and j can have values "x", "y", or

"z". This command activates additional control commands which are described in TOPAZ

Options and Materials.

Output is generated for TOPAZ3D. A FACET input deck will also be created if necessary. This command activates additional control commands which are described in TOPAZ Options and

Materials.

Issue a Fortran write statement. variables v1, v2, ... are written to standard out and format is the Fortran format statement. Example:

WRITE "('I =',e13.5)" [i] ;

Global X-offset.

Scale all X-coordinates.

Begin definition of volume n. If volume n has been previously defined, this command has the effect of destroying the old definition. Volume

Definitions describes the data for this command.

2.27

CONTROL COMMANDS

YOFF d

y

YSCA s

VELOCITY v

x

v y

v z

ZOFF d

z

ZSCA s

LS-INGRID

Global Y-offset.

Scale all Y-coordinates.

Assign initial rigid body velocity (v

x

, v y

, v z

) to all parts defined after this command. v

x

, v y

and

v z

can be functions of (x,y,z) to allow initial velocity distributions.

Global Z-offset.

Scale all Z-coordinates.

2.28

LS-INGRID

3. IDEAS Part

IDEAS PART

The IDEAS part provides for importing SDRC/IDEAS neutral files into LS-INGRID.

The form of the part is as follows:

IDEA filename

<optional functions>

END

filename is the name of the IDEAS neutral file.

3.1 O

PTIONS AND

F

UNCTIONS

Functions require the ability to identify groups of nodes and elements in a part and assign various properties. These have the general form of:

Keyword <region> function data

Where <region> is a part specific description of where the function is to be applied. For the current part, the nodes or elements through either node or element numbers or through analytical expressions. As an example:

SI [mat==2] 1 M C Elements of material 2 are assigned to

C the master side of contact interface 1.

Variables available for function application are as follows: center.

Variable Description x y z Part local coordinates of node or element xg yg zg center.

Global coordinates of node or element node mat elem

Node number.

Material number.

Element number.

The following options are allowed in any order. Additional functions can be applied and are described in the section on Loads and Boundary Conditions.

COOR nc data Input nc local coordinate systems. Coordinate system data is described in detail in the section on Coordinate Transformations.

CYLI

Nodes are converted from cylindrical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

Y = R sin

θ

3.1

IDEAS PART

LREP l

1

l

2

... l

n

MATE matnum

REPE l

1

l

2

... l

n

ROTA p

x

p y

p z

v x

v y

v

z w

SPHE

TEMP t

THIC thic

VELO v

x

v y

v z

LS-INGRID

Repeat command. This command makes copies of the part in each of the local coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

The part has material number matnum.

Repeat command. This command makes copies of the part in each of the global coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

Assign an initial rigid body rotation to the part.

(p

x

, p y

, p z

) is any point on the axis of rotation and (v

x

, v y

, v z

) defines the axis direction. The angular velocity is w in radians per second.

Nodes are converted from spherical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

sin ϕ

Y = R sin

θ

sin ϕ

Z = R cos ϕ

The initial temperature of this part is t and it can be expressed as a function of x, y, z coordinates.

Plates have the thickness thic for this part.

Assign initial rigid body velocity to all nodes within this parts. (V

x

, V y

, V z

) is the global velocity vector. (V

x

, V y

, V z

) can be expressed as a function of x, y, z coordinates.

3.2

LS-INGRID

4. PATRAN Part

PATRAN PART

The PATRAN part provides for importing PATRAN neutral files into LS-INGRID.

The form of the part is as follows:

PATRAN filename

<optional functions>

END

filename is the name of the PATRAN neutral file.

4.1 O

PTIONS AND

F

UNCTIONS

Functions require the ability to identify groups of nodes and elements in a part and assign various properties. These have the general form of

Keyword <region> function data

Where <region> is a part specific description of where the function is to be applied. For the current part, the nodes or elements through either node or element numbers or through analytical expressions. As an example:

SI [mat==2] 1 M C Elements of material 2 are assigned to

C the master side of contact interface 1.

Variables available for function application are as follows: center.

Variable Description x y z Part local coordinates of node or element xg yg zg center.

Global coordinates of node or element node mat elem

Node number.

Material number.

Element number.

The following options are allowed in any order. Additional functions can be applied and are described in the section on Loads and Boundary Conditions.

COOR

nc data Input nc local coordinate systems. Coordinate system data is described in detail in the section on Coordinate Transformations.

CYLI

Nodes are converted from cylindrical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

Y = R sin

θ

4.1

PATRAN PART

LREP

l

1

l

2

... l

n

MATE

matnum

REPE

l

1

l

2

... l

n

ROTA

p

x

p y

p z

v x

v y

v

z w

SPHE

TEMP

t

THIC

thic

VELO

v

x

v y

v z

LS-INGRID

Repeat command. This command makes copies of the part in each of the local coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

The part has material number matnum.

Repeat command. This command makes copies of the part in each of the global coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

Assign an initial rigid body rotation to the part.

(p

x

, p y

, p z

) is any point on the axis of rotation and (v

x

, v y

, v z

) defines the axis direction. The angular velocity is w in radians per second.

Nodes are converted from spherical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

sin ϕ

Y = R sin

θ

sin ϕ

Z = R cos ϕ

The initial temperature of this part is t and it can be expressed as a function of x, y, z coordinates.

Plates have the thickness thic for this part.

Assign initial rigid body velocity to all nodes within this parts. (V

x

, V y

, V z

) is the global velocity vector. (V

x

, V y

, V z

) can be expressed as a function of x, y, z coordinates.

4.2

LS-INGRID

5. NASTRAN Part

NASTRAN PART

The NASTRAN part provides for importing NASTRAN input files into LS-INGRID.

The form of the part is as follows:

NASTRAN filename

<optional functions>

END

filename is the name of the NASTRAN input file.

5.1 O

PTIONS AND

F

UNCTIONS

Functions require the ability to identify groups of nodes and elements in a part and assign various properties. These have the general form of:

Keyword <region> function data

Where <region> is a part specific description of where the function is to be applied. For the current part, the nodes or elements through either node or element numbers or through analytical expressions. As an example:

SI [mat==2] 1 M C Elements of material 2 are assigned to

C the master side of contact interface 1.

Variables available for function application are as follows: center.

Variable Description

x y z

Part local coordinates of node or element

xg yg zg

center.

Global coordinates of node or element node mat elem

Node number.

Material number.

Element number.

The following options are allowed in any order. Additional functions can be applied and are described in the section on Loads and Boundary Conditions.

COOR

nc data Input nc local coordinate systems. Coordinate system data is described in detail in the section on Coordinate Transformations.

5.1

NASTRAN PART

CYLI

LREP

l

1

l

2

... l

n

MATE

matnum

REPE

l

1

l

2

... l

n

ROTA

p x

p

y

p

z

v

x

v

y

v

z

w

SPHE

TEMP

t

THIC

thic

VELO

v x

v y

v z

LS-INGRID

Nodes are converted from cylindrical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

Y = R sin

θ

Repeat command. This command makes copies of the part in each of the local coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

The part has material number matnum.

Repeat command. This command makes copies of the part in each of the global coordinate systems l

1

to l

n

If the coordinate system number is zero, the part is repeated with no transformation.

Assign an initial rigid body rotation to the part.

(p

x

, p

y

, p

z

) is any point on the axis of rotation and (v

x

, v

y

, v

z

) defines the axis direction. The angular velocity is w in radians per second.

Nodes are converted from spherical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

sin ϕ

Y = R sin

θ

sin ϕ

Z = R cos ϕ

The initial temperature of this part is t and it can be expressed as a function of x, y, z coordinates.

Plates have the thickness thic for this part.

Assign initial rigid body velocity to all nodes within this parts. (V

x

, V y

, V z

) is the global velocity vector. (V

x

, V y

, V z

) can be expressed as a function of x, y, z coordinates.

5.2

LS-INGRID NASTRAN PART

Notes:

1. The following NASTRAN keywords are supported:

CBAR

CELAS2

CONM2

CBEAM

CHEXA

CDAMP

CMASS2

CORD1C CORD1R

CORD1S CORD2C CORD2R

CORD2S CPENTA CQUAD4

CTETRA

GRAV

CTRIA3

GRID

FORCE

MAT1

MPC

PLOAD2

PSOLID

SPC1

PBAR

PLOAD4

RBE2

PBEAM

PSHELL

SPC

2. The following keywords from MSC/DYNA are also supported:

DYMAT24 MATRIG

3. To preserve the arbitrary node, element and material numbering of NASTRAN input files, use the ARBITRARY command. (See LS-DYNA3D Commands and Materials.)

4. The material properties from the NASTRAN input are generally not used for LS-

DYNAxx calculations. To assign properties from LS-INGRID, the materials may be defined either before or after the NASTRAN part. The LS-INGRID material ID's are input the same as those of the NASTRAN input. If the LS-INGRID materials are defined prior to the

NASTAN model input, but the sections are not input, then LS-INGRID will try to use the section property data from the NASTRAN input. Section properties may be scaled using the global command: PSCALE.

5. Node, element and material ID's can be shifted using the global command, LABELS.

5.3

LS-INGRID

6. Standard Part

STANDARD PART

6.1 DEFINITIONS

Index Space: An index space is a three-dimensional discrete coordinate system with integer values greater than or equal to 1 in each of the three directions. The three discrete coordinates are labeled, I, J, and K axes respectively. Each point in the index space (i, j, k), represents a nodal point. Elements are defined as groups of adjacent nodes in the index space.

Region: A region is any rectangular or cubic block of nodes. A region is usually defined by a block in an index space.

Part: A part is a collection of regions which can be grouped and generated conveniently in an index space. Beginning users will typically use one region per part while more experienced users will be able to group numerous regions together into complex parts.

Model: The final model is a collection of parts. Each part has its own index space and is independent of other parts. Parts are connected together either by global coincident node removal, slide surfaces, or other constraints.

The standard part in LS-INGRID is based on a three-dimensional index space which is commonly used for finite difference mesh generation. Although this can be somewhat awkward for finite element meshes, proper usage technique and some enhancements have made this quite effective for certain geometries including some that are difficult for standard finite element mesh generators. The principal enhancement to the three-dimensional index space is an additional type of index notion, the "Index Progression". Index progressions provide a concise and simple method for describing complex structures, and are used to input data to LS-INGRID. The following is a detailed description of the index space notion and the index progression. This information provides the user with the concepts necessary to use

LS-INGRID effectively.

Index Space

Node generation in LS-INGRID is done by a mapping from Index space onto the object of interest as is shown in Figure 6-1. Each region of the object is referenced by a set of six indices; (IMIN, JMIN, KMIN) specify the minimum indices for a region in the index space and (IMAX, JMAX, KMAX) specify the maximum indices. For a solid region, all eight corner nodes are defined by combinations of minimum and maximum indices. Table 6-

1 lists the indices of the vertices in the example of Figure 6-1. We assume that any set of three indices, (I, J, K), defines a region in space.

If KMIN is set equal to KMAX, the resulting region is a plane of constant K as shown

6.1

STANDARD PART LS-INGRID

in Figure 6-2a. Similarly, a plane of constant I is defined when IMIN is set equal to IMAX and a plane of constant J for JMIN equal to JMAX. A line in the index space is defined by holding two indices constant while the third index varies as shown in Figure 6-2b.

K

J

E

G

H

F

C

A

B

D

I

Z

G

Y

C

A

D

B

X

Figure 6-1. Mapping from index space to object space.

H

F

6.2

LS-INGRID

K

C

(1, 5, 2)

J

STANDARD PART

D

(5, 5, 2)

A

(1, 1, 2)

K

B

(5, 1, 2)

I

Figure 6-2a. Planes in index space.

J

(3, 5, 2)

(3, 1, 2)

Figure 6-2b. Lines in index space.

I

6.3

STANDARD PART

TABLE 6-1. Indices associated with the vertices of a region.

LS-INGRID

Node Indices Position

A (1, 1, 1) (IMIN, JMIN, KMIN)

B

KMAX)

(5, 1, 1) (IMAX, JMAX,

C

D

KMAX)

E

(1, 1, 2)

(5, 1, 2)

(1, 5, 1)

(5, 5, 1)

(IMIN, JMIN, KMIN)

(IMAX, JMAX,

(IMIN, JMIN, KMIN)

(IMAX, JMAX, F

KMAX)

G

H

KMAX)

(1, 5, 2)

(5, 5, 1)

(IMIN, JMIN, KMIN)

(IMAX, JMAX,

An index space is defined as the set of all possible indices < <IMAX, < <JMAX, 1

< <

KMAX. If an index is zero, then it varies over all possible indices. Thus, the indices (3,

0, 2) defines a line which extends across the index space, and (0, 0, 2) defines a plane which divides the index space into two regions. (0, 0, 0) defines the entire index space.

Index Progressions

Index progressions were developed to facilitate the defining of multiple regions in index space. Rather than specifying the minimum and maximum indices for a region, one simply specifies the progression in indices along the I, J, and K directions respectively. For example, the region (2, 7, 6, 8, 9, 10) is represented as the progression (2, 8); (7, 9); (6, 10).

If there is a region adjacent to (2, 7, 6, 8, 9, 20) such as (2, 7, 2, 8, 9, 6), the two regions are defined together by a new progression (2, 8); (7, 9); (2, 6, 10). To define the four solids regions shown in Figure 6-3a requires the progression (3, 5, 7); (2, 4, 6); (1, 4).

Index progressions for planes are defined in a similar manner. The index which remains constant throughout a plane is indicated by a negative sign so the plane (2, 5, 5, 2, 7,

8) is represented as (-2); (5, 7); (5, 8).

In Figure 6-3b there are eight planes which can be represented by the progression (3, 5,

7); (2, 4, 6); (-1, -4). The savings by this notation is apparent since specifying separately the eight regions in Figure 6-3b requires 49 number where as the index progression requires only 8 numbers.

6.4

LS-INGRID

(7, 6, 4)

STANDARD PART

(3, 2, 1)

(a) Index Space

(7, 6, 4)

(3, 2, 4)

(3, 2, 1)

(b) Object Space

Figure 6-3. Index progressions for planes and solids.

(7, 6, 1)

6.5

STANDARD PART LS-INGRID

Another addition to the index progression notation is the zero index. The two solids regions shown in Figure 6-4 could be represented as an index progression except that they are not connected. In this case, a zero index is used along the I direction to indicate that the structure is discontinuous. This gives the progression (2, 4, 0, 6, 8); (3, 7); ( 4, 5). Plane regions can be separated by the zero index in a manner similar to solid regions.

More complicated regions can be represented by combining index progressions. An example of this is in Figure 6-5. The open box could be represented by two index progressions (-2, -5); (1, 7); (3, 5); and (2, 5); (1, 7); (-3, -5), but they can also be combined to give (-2, -5); (1, 7); (-3, -5). Figure 6-6 shows several more structures and their index progression representation.

LS-INGRID uses the index progression notation to set up regions in the index space which are to be mapped onto the object of interest. This notation has the advantage that it requires little input data and with less than 20 indices can represent thousands of configurations in index space. In practice, not all configurations in index space can be defined by an index progression so a command is added to allow deletion of regions in the index space. The delete command along with the index progression is enough to produce almost any conceivable region in the index space and is used as the central part of LS-

INGRID's mesh generation.

6.6

LS-INGRID

Figure 6-4. Separated solid regions.

STANDARD PART

Figure 6-5. Open Box.

6.7

STANDARD PART LS-INGRID

(a) Intersecting Plates

((2, -4, 6); (2, -4, 6); (-3, -7))

(c) Cube in a Box

((-2, 4, 6, -8); (-2, 4, 6, -8); (3, 5))

(c) Examples of Region Deletion

((-2, -6, -10); (3, 7); (-2, -4))

Deleted Regions:

(2, 3, 2, 6, 7, 2) and (6, 3, 4, 10, 7, 4)

(d) Planes and Solids with Gaps

((2, 4, 0, 6, -8); (2, 4, 0, 6, 8); (-2, 4, 6, -8))

Figure 6-6. Examples of index progressions.

6.8

LS-INGRID STANDARD PART

Each part definition consists of the following data:

START

Index progression

Part control commands and functions

Loads and Boundary Conditions

END

"START" signifies the beginning of a part definition and is require as the first card in each part. Part control commands affect properties of the mesh. Following is a list of the default properties for a part.

4 node plate elements

8 node solid element rectangular coordinates material property = 1 plate thickness = 0.0

The dimension of the index space along with all plane and solid regions are defined by the index progression. Function cards manipulate the mesh defined by the index progression and an "END" signifies the end of a part. Following are some important definitions in addition to those previously given.

Index Space

The set of all indices defined by an index progression. For example, the progression

(2, 3, -5, 10), (4, 5), (2, 6) defines the index space 2

^

|I|

^

10, 4

^

|J|

^

5, 2

^

|K|

^

6.

Reduced Index Space

The reduced index space references positions in an index progression. The point, I, J,

K in the reduced index space refers to the point in the index progression defined by the Ith integer in the I-progression, the Jth integer in the J-progression and the Kth integer in the Kprogression. For the progression (2, 3, -5, 10), (4, 5), (2, 6) the relationship between the reduced index space and the index space is shown in Table 6-3.

Unless otherwise noted, all points and regions are defined in the reduced index space.

Since the reduced index space is independent of the actual values of the index progression, the mesh can be refined or contracted only by changing the index progression.

6.9

STANDARD PART

Table 6-3. Comparison of the Reduced Index Space and the

LS-INGRID

Index Space for the Index Progression (2, 3, -5, 10),

(4, 5), (2, 6)

Reduced Index Space Index Space

1, 1, 1 2, 4, 2

1, 1, 2

1, 2, 1

2, 4, 6

2, 5, 2

2, 2, 2

3, 1, 2

4, 1, 1

3, 5, 6

5, 4, 6

10, 4, 2

6.2 Index Progression

Each part must have an index progression. The following input is required.

i

1

i

2

... i

i j

1

j

2

... j

i

; k

1

k

2

... k

i x

1

x

2

... x

i y

1

y

2

... y

i

z1 z

2

... z

i

Progression in I direction

Progression in J direction

Progression in K direction

Initial X-coordinates

Initial Y-coordinates

Initial Z-coordinates

6.10

i

LS-INGRID STANDARD PART

6.3 Part Commands and Functions

All functions have the following form:

Keyword - index specification - parameters

Index specifications have three types which are abbreviated as <Point> , <Region>, or <Index Progression>. All index specifications are applied in the reduced index space.

The input is defined as follows:

<Point>

<Region>

<Index Progression>

1

i

2

i

3

... ; j

1

j

2

... ; k

1

k

2

... ;

Input for <point> consists only of the three indices (i,j,k). If any index is input as zero, then the index varies from the smallest to the largest possible value.

The function locates the region defined by

(i

m

,j m

,k m

,i x

,j x

,k x

). If i

m

, j m

, or k

m

is input as zero, the zero index is given the minimum possible value. If i

x

, j

x

, or k

x

is input as zero, the zero index is set to the maximum possible value.

This is used to define multiple regions according to the rules for index progression. If no indices are found for a list in a direction, then the function is assumed to go all the way through the index space in that direction.

Functions which use <Region> or <Index Progression> for index specification can be repeated and shifted to other parts of the index space. The general form of these commands is as follows:

Keyword - <Region> or <Index Progression> parameters - first offset - parameters - second offset - parameters.

The offset information is as follows:

+

-or-

+o

Either a "+" or a "+o" is required as the first information for the offset. If "+" is used then the offset occurs from the region defined by the last offset. If "+O" is used then the offset is relative to the region defined by <Region> or <Index

Progression>.

One and only one of the following commands must be input following "+" or "+o".

6.11

STANDARD PART

I di

J dj

K dk

IJ di dj

JK dj dk

KI dk di

IJK di dj dk

SIJ

SJK

SKI

A

<Region> ityp

Z-coordinate of point P1 or P2

Radius

LS-INGRID

Increment I indices by di.

Increment J indices by dj.

Increment K indices by dk.

Increment I and J indices by di and dj.

Increment J and K indices by dj and dk.

Increment K and I indices by dk and di.`

Increment I, J, and K indices by di, dj, and dk.

Switch I indices with J indices.

Switch J indices with K indices.

Switch K indices with I indices.

Form a curved edge between nodes A and B.

The region is a line in the reduced index space.

Flag specifying type of curve.

=1: A parabola through point P1 (See

Figure 6-7).

=2: A circular arc through point P1.

=3: A circular arc with center P2.

X-coordinate of point P1 or P2

Y-coordinate of point P1 or P2

z r x y

If the radius is non-zero for a circular arc with center P2, then nodes A and B (See

Figure 6-7) are moved radially from P2 until they are a distance equal to the radius from P2.

An arc is formed through the nodes at their final location.

6.12

LS-INGRID

P1

B

R

STANDARD PART

A R P2

Figure 6-7. Curved boundaries.

A

,

AE

<Region> idir

Arc keyword. The region is a plane or a solid in the reduced index space with an arbitrary length.

Flag specifying axis of rotation in the index space.

="I": I-axis is axis of rotation

="J": J-axis is axis of rotation

="K": K-axis is axis of rotation

Radius

r

For any plane normal to the axis of rotation such as ABCD in Figure 6-8, a point 0 on the axis of rotation is located in the center of the plane. If the radius of the cylinder is not zero, then the points A, B, C and D are moved radially from 0 until they are a distance, R, from point 0. Curved boundaries are then formed for the segments AB, BD, AC and CD using center.0. This is done for each plane normal to the axis of rotation in the reduced index space.

6.13

STANDARD PART

(IMAX, JMAX, KMAX)

R

LS-INGRID

A

B

R

0

C

D

(IMIN, JMIN, KMIN)

Figure 6-8. Cylindrical region.

AC

,

ACE

<Region> idir

p x

p y

p z r q x

q y

q z

<Region> is a surface in the index space.

Flag specifying axis of rotation in the index space.

="I": I-axis is axis of rotation

="J": J-axis is axis of rotation

="K": K-axis is axis of rotation

Any point on axis of cylinder (See Figure 6-9).

Radius of the cylinder.

Any vector parallel to the axis of the cylinder.

6.14

LS-INGRID

Z

Q

P r r u

′ v

′ u v

Y

STANDARD PART

X

Figure 6-9. Cylindrical surface.

AUTO

BG

Perform automatic smoothing of edges and surfaces which represent continuous surface definitions..

Beam generation command.

The BG command permits beam elements to be defined within parts defined using an index space. If only beam elements are desired for the part, then all of the shell and solid elements can be deleted.

Options:

MT m

SC n

NGEN n

N1 <Point>

P1 p

x

p y

p z

N2 <Point>

P2 p

x

p y

p z

B1 n

Beams have material number m.

Beams have section number n.

Generate n beams from point 1 to point 2.

Point 1 is located at <Point>

Point 1 is located at (p

x

, p y

, p z

)

Point 2 is located at <Point>

Point 2 is located at (p

x

, p y

, p z

).

Set boundary code for point 1. n is a six digit binary number which specifies degrees of freedom which are to be constrained.

Numbering the digits from left to right, they affect the following degree-of-freedom.

6.15

STANDARD PART

V2 v

x

v y

v z

B2 n

NO <Point>

PO p

x

p y

p z

VOv

x

v y

v z

CO p

x

, p y

, p z

SO p

x

, p y

, p z

;

BIAS

x

0

y

0

z

0

v

x

v y

v z

r

0

r

1

f

COOR

CPL

<Region>

CYLI

nc data dir

LS-INGRID

1st digit: x-displacement

=0: free

=1: fixed

2nd digit: y-displacement

3rd digit: z-displacement

4th digit: x-rotation

5th digit: y-rotation

6th digit: z-rotation

Point 2 is offset from point 1 by the vector (v

x

, v y

, v

z)

.

Set boundary code for point 2. n is has the same meaning as for the "B1" option in this command.

The point defining the orientation of the local 2axis is located at <Point>.

The point defining the orientation of the local 2axis is located at (p

x

p y

p z

).

The local 2-axis is defined by vector (v

x

, v y

, v z

).

Same as "PO" except the point is in cylindrical coordinates.

Same as "PO" except the point is in spherical coordinates.

Terminate this command.

Bias mesh. This command is experimental.

(x

0

,y

0

,z

0

,v

x

,v y

,v z

) represents a line towards which the elements are biased. A transition distance is defined beginning at r

0

and ending at

r

1

and f is a factor for adjacent element scaling.

Input nc local coordinate systems. Coordinate system data is described in detail in the section on Coordinate Transformations.

Center points along line. If <Region> is a line, then this command forces elements to be equally spaced from the beginning point to the ending point. If <Region> is a surface or a volume then the command is subdivided into lines in the direction specified by the direction flag.

Direction flag (do not input if <Region> is a line).

="I": Equal space along I-index

="J": Equal space along J-index

="K": Equal space along K-index

Nodes are converted from cylindrical to rectangular coordinates. The equations for this

6.16

LS-INGRID

transformation are:

X = R cos

θ

Y = R sin

θ

Region deletion keyword.

STANDARD PART

D

<Region> or

DI

<Index Progression>

EQSP

Equal space along arc. This applies to the "AC" and "A" functions.

FIND

<Point> exp1 exp2 exp3 exp4 The FIND command places the generated coordinates of <Point> into the variables [cenx]

[ceny] [cenz] and the node number into [node].

Four expressions must be input as part of this command.

Example:

FIND 1 2 1 [bp3x=cenx] [bp3y=ceny] [bp3z=cenz] [bp3n=node]

I

,

J

or

K

<Point> c

1

c

2

c

3

...

INT

<Region> s

1

s

2

LORI

dir2

v

x

v y

v z

Specify independent variable for the function.

="I": coordinates vary as a function of the

I-index.

=J": coordinates vary as a function of the

J-index.

="K": coordinates vary as a function of the

K-index.

Flag specifying which coordinate is modified.

="X": X-coordinate is modified.

="Y": Y-coordinate is modified.

="Z": Z-coordinate is modified.

New progression of coordinates along index

dir1.

Nodes within <Region> lie on the intersection of surface s

1

and s

2

. Surfaces are defined using the "SD" command in the control section.

These commands will be generated automatically if two "SF" commands result in an intersection surface in the index space.

Specify local axis for orthotropic shell elements.

The vector in the local part system is (v

x

,v

y

,v

z

).

The vector (v

x

,v

y

,v

z

) may be specified as a function of the local x,y,z coordinates. For example:

6.17

STANDARD PART

LREP

l

1

l

2

... l

n

MA

or

MB

<POINT>

<REGION>

n d x

d y

d z

MATE

m

MS

<Region> idir

LS-INGRID

LORI [-y] [x] 0

Repeat part command. This command makes copies of the part in each of the local coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

Point functions. These commands are used to modify 1, 2, or 3 coordinates of groups of nodes.

For "MA" only.

For "MB" only.

Flag indicating which coordinates to change.

="X": x coordinate is changed

="Y": y coordinate

="Z": z coordinate

="XY": x and y coordinates

="XZ": x and z coordinates

="YZ": y and z coordinates

="XYZ": x, y, and z coordinates

New coordinates. Only the coordinates required by flag n need to be input. The new coordinates are added to the old coordinates.

The part has material number m.

Apply multiple surface equations to <Region>.

This command permits the identification of parallel index planes for the purpose of applying surface equations. The function of this command is similar to the "SF" command; however, this command can result in considerable reduction in input for many common cases.

<Region> is divided into a series of parallel planes normal to the axis in index space specified by idir.

="I": I-axis

="J": J-axis

="K": K-axis

Next, one surface equation must be input for each of the index planes in <Region> normal to the specified axis. One of the following options may be used.

6.18

LS-INGRID

Option 1: sf

1

sf

2

.

.

.

Option 2:

PPX, PPY, or PPZ

u

1

u

2

u

3

...

Option 3:

CNSP

p x

p y

p z r

1

r

2

r

3

...

Option 4:

CNCY

p x

p y

p z v x

v y v z r

1

r

2

r

3

...

Option 5:

PON, POX, POY, POZ

p x

p y

p z q x

q y

q z o

1

o

2

o

3

...

MT

<Region> or

MTI

<Index Progression> mat

MTV

m n

STANDARD PART

Data for first surface equation (See Surface

Definitions).

Data for second surface equation.

Parallel planes normal to x, y, or z axes respectively.

The point along the specified axis where the planes intercept. One value must be input for each plane.

Center of the spheres.

Radii.

Any point on the axis of the cylinder.

Any vector parallel to the axis.

Radii.

Planes offset normal or in the x, y, or z direction, respectively.

Any point on the plane.

Any vector normal to the plane.

Offsets in the requested direction.

Signifies material command.

Material number.

All elements contained within volume definition

6.19

STANDARD PART LS-INGRID

m are assigned material number n.

OR

<Region>

l

1

l

2

ORDER

d1 d2 d3

Order of writing nodes in index space (d = "I",

"J", or "K").

PA.i.Commands:PA; or PB.i.Commands:PB; Point functions. These commands are used to modify 1, 2, or 3 coordinates of groups of nodes.

<POINT>

<REGION> n d x

d y

d z

For "PA" only.

For "PB" only.

Flag indicating which coordinates to change.

="X": x coordinate is changed

="Y": y coordinate

="Z": z coordinate

="XY": x and y coordinates

="XZ": x and z coordinates

="YZ": y and z coordinates

="XYZ": x, y, and z coordinates

New coordinates. Only the coordinates required by flag n need to be input. The old coordinates are replaced by the new coordinates.

REPE

l

1

l

2

...l

n

Specify orientation of local axes relative to the index space. This is necessary when orthotropic materials are used and/or if 8-node shells are requested.

Local r axis.

="I": I-axis

="J": J-axis

="K": K-axis

Local s axis.

="I": I-axis

="J": J-axis

="K": K-axis

Repeat command. This command makes copies of the part in each of the global coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

RES

<Region> idir

Use unequal element spacing.

Direction of sides to be operated on in

<Region>.

="I": I-direction

6.20

LS-INGRID

r

REST

name

ROTATION

p

x

p y

p z

v x

v y

v z

w

RR <Region> data

SAVE name

SF <Region> ityp -or-

SFI <Index Progression> ityp

STANDARD PART

="J": J-direction

="K": K-direction

The ratio of the length of one element side to the next element side as the I, J, or K index increases is r.

Restore the nodal coordinates of the existing standard part from file "name". For complicated parts, this can save considerable amounts of computing. See also the SAVE command.

Assign an initial rigid body rotation to all parts defined after this command. (p

x

, p

y

, p z

) is any point on the axis of rotation and (v

x

, v

y

, v z

) defines the axis direction. The angular velocity is w in radians per time unit.

Rotate region.

Data for this command is described in the section on Coordinate Transformations.

Save the nodal coordinates of the existing standard part to file "name". For complicated parts, this can save considerable amounts of computing by using the REST command.

Surface command. This command allows for the exact equation specification for 3-D surfaces.

The command operates by moving nodes from an initial location to the closest point on the surface. Intersections of surfaces in the index space are detected and calculated. Since intersections are rarely unique the user must define initial coordinates which are near the final configuration using the initial coordinates and/or point functions. This is often necessary for LS-INGRID to converge to the correct geometry.

If a part is generated in cylindrical coordinates the surfaces are still assumed to be in rectangular coordinates. This permits nonaxisymmetric surfaces to be generated on primarily axisymmetric parts.

ityp= "SD n". If itype = "SD" then the surface is defined using the command "SD" in the control section. The surface name must be input to complete this option.

6.21

STANDARD PART

SFE

<Region> dir ityp -or-

SFEI

<Index Progression> dir ityp

SFV <Region> -or-

SFVI <Index Progression>

SPHE

TEMP

THIC

t

t

LS-INGRID

ityp\o(=,/) "SD". ityp refers to an option in

Surface Definitions. See Surface Definitions for the remaining input.

Surface command. These commands are similar to the and SFI commands. The primary difference is that only edges of blocks oriented in direction dir (dir = "I", "J" or "K") are projected onto the surface rather than all nodes within the region.

ityp= "SD n". If itype = "SD" then the surface is defined using the command "SD" in the control section. The surface name must be input to complete this option.

ityp\o(=,/) "SD". ityp refers to an option in

Surface Definitions. See Surface Definitions for the remaining input.

Surface command. These commands are similar to the SF and SFI commands. The primary difference is that only vertices of blocks are projected to the nearest point on a surface rather than all nodes within a region.

ityp= "SD n". If itype = "SD" then the surface is defined using the command "SD" in the control section. The surface name must be input to complete this option.

ityp\o(=,/) "SD". ityp refers to an option in

Surface Definitions. See Surface Definitions for the remaining input.

Nodes are converted from spherical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

sin ϕ

Y = R sin

θ

sin ϕ

Z = R cos ϕ

The initial temperature of this part is t and it can be expressed as a function of x, y, z coordinates.

Plates have the thickness t for this part. The thickness, t, may be specified as a function of the part local coordinates to permit thickness distributions.

6.22

LS-INGRID

TRI2

t

TRIA

t

VELOCITY

v

x

v y

v z

VTSP

STANDARD PART

All quadrilateral shell elements in this part will be converted to triangular shells. The attached pressure segments, contact segments, etc. will remain as quadrilaterals.

All quadrilateral shell elements in this part will be converted to triangular shells. The attached pressure segments, contact segments, etc. will also be converted to triangles.

Assign initial rigid body velocity (V

x

, V y

, V z

) to all parts defined after this command. (V

x

, V y

, V z

) can be expressed as a function of x, y, z coordinates to allow for velocity distributions.

Equal space along chord. This applies to the

"AC" and "A" functions.

6.23

STANDARD PART LS-INGRID

6.24

LS-INGRID

7. Beam Part

BEAM PART

Beam generation in LS-INGRID is performed by a special part. The data in the part is as follows:

BEAM

Local nodal point input.

0 (zero)

Element generation commands

0 (zero)

Optional functions

END

Local Node Point Input

Important vertices are listed in this section. All points in this section are assigned node numbers in the global system and output even if there are no elements connected.

Nodes are input sequentially and assigned local node numbers starting from one. These numbers are used later for generating elements.

ctype

n x

1

y

1

z

1

Coordinate transformation to be performed on nodal coordinates.

="RT": rectangular coordinates (no transformation)

="CY": cylindrical coordinates

="SP": spherical coordinates

n is a six digit binary number which specifies degrees of freedom to be constrained.

Numbering the digits from left to right they affect the following degrees of freedom.

1st digit: x-displacement

=0 free

=1 fixed

2nd digit: y-displacement

3rd digit: z-displacement

4th digit: x-rotation

5th digit: y-rotation

6th digit: z-rotation

Nodal coordinates.

7.1

BEAM PART

Element Generation Commands

is if nel mat isect normal

LS-INGRID

First local node number in a beam sequence.

Last local node number in a beam sequence.

Number of elements to be generated from is to if.

Material number for the beams.

Section property number for the beams.

Third local node for defining the orientation of the beams. Note: this node can be moved by the "REPEAT" command and is not necessarily in global coordinates.

7.1 O

PTIONS AND

F

UNCTIONS

Functions require the ability to identify groups of nodes and elements in a part and assign various properties. These have the general form of

Keyword <region> function data

Where <region> is a part specific description of where the function is to be applied. For the current part, the nodes or elements through either node or element numbers or through analytical expressions. As an example:

SI [mat==2] 1 M C Elements of material 2 are assigned to

C the master side of contact interface 1.

Variables available for function application are as follows:

Variable Description x y z Part local coordinates of node or element center.

xg yg zg center.

Global coordinates of node or element node mat elem

Node number.

Material number.

Element number.

The following options are allowed in any order. Additional functions can be applied and are described in the section on Loads and Boundary Conditions.

COOR

nc data Input nc global coordinate systems. Coordinate system data is described in detail in the section on Coordinate Transformations.

7.2

LS-INGRID

CYLI

LREP

l

1

l

2

... l

n

REPE

l

1

l

2

...l

n

ROTA

p

x

p y

p z

v x

v y

v z

w

SPHE

TEMP t

VELO v

x

v y

v z

BEAM PART

Nodes are converted from cylindrical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

Y = R sin

θ

Repeat command. This command makes copies of the part in each of the local coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

Repeat command. This command makes copies of the part in each of the global coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

Assign an initial rigid body rotation to the part.

(p

x

, p y

, p z

) is any point on the axis of rotation and (v

x

, v y

, v z

) defines the axis direction. The angular velocity is w in radians per time unit.

Nodes are converted from spherical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

sin ϕ

Y = R sin

θ

sin ϕ

Z = R cos ϕ

The initial temperature of this part is t and it can be expressed as a function of x, y, z coordinates.

Assign an initial rigid body velocity to all nodeswithin this part. V

x

, V y

, V z

is the global velocity vector and it can be expressed as a function of x, y, z coordinates.

7.3

BEAM PART LS-INGRID

7.4

LS-INGRID

8. Old Data Part

OLD DATA PART

This part permits the user to input and manipulate models which were generated by other mesh generators. It can also be used to take old finite element models and update them

The data in the part is as follows:

OLD

Commands

END

The "commands" include the input nodes and elements in the form of tables. These tables may be either in free format or formatted. Before a table is input, a list of keywords is input which tells what the columns correspond to. After the data is input, the part may then be moved or otherwise modified before inclusion with the rest of the LS-INGRID model.

NODES

n

Options:

BCND

n nodal points are input.

BCNR

BCSP

DUMMY

FORM f

INCLUDE

K

NUMBER

T

LS-NIKE3D displacement boundary codes are input.

LS-NIKE3D rotational boundary codes are input.

SAP boundary codes are input.

Read and ignore this item. (Must be a number).

Nodal points are read using format f. f is a character string up to 80 characters long which has the correct FORTRAN format. All items must be read in floating point format. No more than one node point can be specified on a card.

If this option is not used then nodal point data is input free format.

Nodes are read from file. This option terminates the NODES command and reads the nodes.

Node point increment k is input.

Node numbers are to be read. If this option is not used, then node numbers are assigned sequentially.

Temperature.

8.1

OLD DATA PART

X

;

Y

Z

BEAMS

n

Options:

FORM f

NUMBER

K

MATERIAL

SECTION

INCLUDE

NODES

N1

N2

N3

;

DUMMY

SHELLS

n

Options:

FORM f

LS-INGRID

X-coordinate.

Y-coordinate.

Z-coordinate.

Terminate options and read the nodal points.

This is done automatically if an include file is specified.

n beam elements are input.

Beam elements are read using format f. f is a character string up to 80 characters long which has the correct FORTRAN format. All items must be read in floating point format. No more than one element can be specified on a card. If this option is not used then nodal point data is input free format.

Element numbers are to be read. If this option is not used, then element numbers are assigned sequentially.

Element increment K is input.

Material numbers are input.

Section property numbers are input.

Beam elements are read from file. This option terminates the BEAMS command and reads the beam elements.

Three nodes are input (first node, second node, and node defining local two axis).

First node.

Second node.

Node defining local two axis.

Read and ignore this item. (Must be a number).

Terminate options and read the element data.

n shell elements are input.

Elements are read using format f. f is a

8.2

LS-INGRID

NUMBER

K

MATERIAL

THICKNESS

INCLUDE

NODES

N1

N2

N3

N4

;

DUMMY

BRICKS

n

Options:

FORM f

NUMBER

K

MATERIAL

OLD DATA PART

character string up to 80 characters long which has the correct FORTRAN format. All items must be read in floating point format. No more than one element can be specified on a card. If this option is not used then nodal point data is input free format.

Element numbers are to be read. If this option is not used, then element numbers are assigned sequentially.

Element increment K is input.

Material numbers are input.

Thickness of element.

Shell elements are read from file. This option terminates the SHELLS command and reads the shells.

Four nodes are input.

Node 1.

Node 2.

Node 3.

Node 4.

Read and ignore this item.

Terminate options and read the element data.

n brick elements are input.

Elements are read using format f. f is a character string up to 80 characters long which has the correct FORTRAN format. All items must be read in floating point format. No more than one element can be specified on a card. If this option is not used then nodal point data is input free format.

Element numbers are to be read. If this option is not used, then element numbers are assigned sequentially.

Element increment K is input.

Material numbers are input.

8.3

OLD DATA PART

INCLUDE

NODES

N1

N2

N3

N4

N5

N6

N7

;

N8

DUMMY

LS-INGRID

Brick elements are read from file. This option terminates the BRICKS command and reads the brick elements.

Input 8 node numbers.

Node 1.

Node 2.

Node 3.

Node 4.

Node 5.

Node 6.

Node 7.

Node 8.

Read and ignore this item.

Terminate option and read the element data.

8.4

LS-INGRID OLD DATA PART

8.1 O

PTIONS AND

F

UNCTIONS

Functions require the ability to identify groups of nodes and elements in a part and assign various properties. These have the general form of

Keyword <region> function data

Where <region> is a part specific description of where the function is to be applied. For the current part, the nodes or elements through either node or element numbers or through analytical expressions. As an example:

SI [mat==2] 1 M C Elements of material 2 are assigned to

C the master side of contact interface 1.

Variables available for function application are as follows:

Variable Description x y z xg yg zg node mat elem

Part local coordinates of node or element center.

Global coordinates of node or element center.

Node number.

Material number.

Element number.

The following options are allowed in any order. Additional functions can be applied and are described in the section on Loads and Boundary Conditions.

COOR nc data Input nc local coordinate systems. Coordinate system data is described in detail in the section on Coordinate Transformations.

CYLI

LREP l

1

l

MATE matnum

REDUCE

2

... l

n

;

Nodes are converted from cylindrical to rectangular coordinates. The equations are:

X = R cos

θ

Y = R sin

θ

Repeat command. This command makes copies of the part in each of the local coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

The part has material number matnum.

Eliminate unattached nodes which are input in this part.

8.5

OLD DATA PART

REPE l

1

l

2

... l

n

ROTA p

x

p y

p z

v x

v y

v

z w

SPHE

TEMP t

THIC thic

VELO v

x

v y

v z

LS-INGRID

Repeat command. This command makes copies of the part in each of the global coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

Assign an initial rigid body rotation to the part.

(p

x

, p y

, p z

) is any point on the axis of rotation and (v

x

, v y

, v z

) defines the axis direction. The angular velocity is w in radians per second.

Nodes are converted from spherical to rectangular coordinates. The equations are:

X = R cos

θ

sin ϕ

Y = R sin

θ

sin ϕ

Z = R cos ϕ

The initial temperature of this part is t and it can be expressed as a function of x, y, z coordinates.

Plates have the thickness thic for this part.

Assign initial rigid body velocity to all nodes withinthis parts. (V

x

,

V y

, V z

) is the global velocity vector. (V

x

, V y

, V z

) can be expressed as a function of x, y, z coordinates.

8.6

LS-INGRID

9. MAZE Part

MAZE PART

MAZE parts provide simple methods for generating two dimensional cross sections.

These sections can then be used as shell elements or as 3-D solids using drag mesh operations. The data in the part is as follows:

PART

Required part data (9.1)

Optional part control commands (9.2)

Optional functions (9.3)

END

9.1 Required Part Data

Each MAZE part requires a set of line definitions followed by a material number and mesh density information. There are many possible methods for describing MAZE parts as:

L

1

L

2

L

3

L

4

mt k m

L

L

1

1

L

L

2

2

L

L

3

3

L

3

mt k m

0 mt k m

Define four sided region edges consisting of the intersection lines L

1

, L

2

, L

3

,and L

4

. This region will have material name mt and will be subdivided in a k x m element mesh with k elements lying along edges L

1

and L

3

and m elements lying along edges L

2

and L

4

. Edges must be listed in a counterclockwise order. If k or

m are zero, the number of elements are assumed to be one less than the number of points in lines

L

1

or L

2

, respectively. Points defining the lines then become nodal coordinates.

Define three sided region having edges consisting of the intersecting lines L

1

, L

2

, and

L

3

. This region will have material name mt and will be subdivided into m x (2k+m) elements with k+m elements along edges L

1

and L

2

and

2m elements along edge L

3

. Edges must be listed in a counterclockwise order.

Define three sided region having edges consisting of the intersecting lines L

1

, L

2

, and

L

3

. This region will have material name mt and will be subdivided into m x (2k+m) elements with k+m elements along edges L

1

and L

2

and

2m elements along edge L

3

. Edges must be listed in a counterclockwise order.

9.1

MAZE PART

L

1

L

2

L

3

L

4

mt -k-m r

1

r

2

-or-

L

1

L

2

L

3

L

4

mt -k m r

1

L

1

L

2

L

3

L

4

mt k-m r

2

L

1

L

2

L

3

L

4

-mt k m r

1

r

2

r

3

r

4

-L

.

.

.

1

L

1

L

2

L etc.

L

2

L

3

L

4

mt k m

3

L

4

mt k m

LS-INGRID

Define four sided region as described above but with variable zoning. Parameters r

1

and r

2

are the ratios of the first segment length to the last segment length along edges 1,3, and 2,4 respectively.

Define four sided region as described above but with variable zoning. Parameters r

1

to r

4

are the ratios of the first segment length to the last segment length along edges 1 to 4, respectively.

Define four sided region as described above but with a specified number of elements between consecutive points defining the lines whose line numbers are proceeded by a minus sign. For this option to work properly, the first intersection point must lie either on the first and second point of the line being subdivided. The total number of points used to define the line is equal to p. If desired, not all subdivisions need to be defined.

For example, if it is desired to specify the number of subdivisions between the first three points of the first line type. The other segments are equally spaced over the balance of the line.

9.2

LS-INGRID

9.2 O

PTIONS AND

F

UNCTIONS

The following part control commands are allowed.

COOR nc data

DRAG

Options:

MOVE n data

MAZE PART

Input nc local coordinate systems. Coordinate system data is described in detail in the section on Coordinate Transformations.

Perform a drag mesh operation to make solid elements from plane elements.

;

RES r

LREP l1 l

2

... l

n

REPE l

ROTA n p

1

ROTA p

SPIN n

θ

l

x

2

p

... l

y

p z n

w x x

p

w y y

p

w z z

q

x

q

y

q

z

α

Form n layers of solid elements by moving the original plane elements to the new location specified by data. Data is described in detail in

Coordinate Transformations.

Form n layers of solid elements by rotating the original plane elements about an axis. (p

x

, p

y

,

p z

) is any point on the axis of rotation and (q

x

,

q y

, q

z

) is a vector parallel to the axis. The angle of rotation in degrees is

α

.

The ratio of one element length to the next is r.

This applies only to the previous drag operation.

Terminate this command.

Repeat command. This command makes copies of the part in each of the local coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

Repeat command. This command makes copies of the part in each of the global coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

Assign an initial rigid body rotation to the part.

(p

x

, p y

, p z

) is any point on the axis of rotation and (w

x

, w y

, w z

) is the rotation vector in radians per second.

Perform spin operation. The number of layers of nodes is n and the total angle of the part is q in degrees.

9.3

MAZE PART

STACK n q

TEMP t

THICK t

TRI2 t

TRIA t

VELO v

x

v y

v

z

LS-INGRID

Perform stack operation. The number of layers of nodes is n and the total length of the part is

θ

.

The initial temperature of this part is t and it can be expressed as a function of x, y, z coordinates.

Plates have the thickness t for this part.

All quadrilateral shell elements in this part will be converted to triangular shells. The attached pressure segments, contact segments, etc. will remain as quadrilaterals.

All quadrilateral shell elements in this part will be converted to triangular shells. The attached pressure segments, contact segments, etc. will also be converted to triangles.

Assign initial rigid body velocity to all nodes within this part. (V

x

, V y

, V z

) is the global velocity vector and it can be expressed as a function of x, y, z coordinates.

9.4

LS-INGRID MAZE PART

9.3 F

UNCTIONS

All MAZE part functions have the following form:

Keyword - index specification - parameters

MAZE parts have one type of index specification which is abbreviated as <Mregion>.

The input for this index specification is as follows:

c

1

c

2

p

1

p

2

Four indices can identify any vertex, edge, or surface in the MAZE part. Each MAZE part has either 3 or 4 corners. The first corner is the intersection of the first line and the last line that makes up the part. The second corner is the intersection of the first and second lines.

Further corners are defined similarly around the part. The part also has several planes including the original cross section and one more plane for each drag operation. The first corner node reference by <Mregion> is c

1

and the last corner is c

2

. The first plane is p

1

and the last plane is

p

2

. If c

1

or c

2

is zero, they take on the minimum and maximum corner numbers respectively. Similarly, if p

1

or p

2

is zero, they are assigned the minimum and maximum plane numbers, respectively.

9.5

MAZE PART LS-INGRID

9.6

LS-INGRID

10. EDIT Part

EDIT PART

The EDIT part allows loads and boundary conditions to be applied to previously defined parts. It also provides for the performing of system assembly operation from subsystems using system joint commands. The general for of this part is:

EDIT filename

<optional functions>

END

10.1 O

PTIONS AND

F

UNCTIONS

Functions require the ability to identify groups of nodes and elements in a part and assign various properties. These have the general form of

Keyword <region> function data

Where <region> is a part specific description of where the function is to be applied. For the current part, the nodes or elements through either node or element numbers or through analytical expressions. As an example:

SI [mat==2] 1 M C Elements of material 2 are assigned to

C the master side of contact interface 1.

Variables available for function application are as follows:

Variable Description x y z Part local coordinates of node or element center.

xg yg zg center.

Global coordinates of node or element node mat elem

Node number.

Material number.

Element number.

The following options are allowed in any order. Additional functions can be applied and are described in the section on Loads and Boundary Conditions.

COOR nc data Input nc local coordinate systems. Coordinate system data is described in detail in the section on Coordinate Transformations.

CYLI

Nodes are converted from cylindrical to

10.1

EDIT PART

LREP l

1

l

2

... l

n

MATE matnum

REPE l

1

l

2

... l

n

ROTA p

x

p y

p z

v x

v y

v

z w

SPHE

TEMP t

THIC thic

VELO v

x

v y

v z

LS-INGRID

rectangular coordinates. The equations for this transformation are:

X = R cos

θ

Y = R sin

θ

Repeat command. This command makes copies of the part in each of the local coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

The part has material number matnum.

Repeat command. This command makes copies of the part in each of the global coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

Assign an initial rigid body rotation to the part.

(p

x

, p y

, p z

) is any point on the axis of rotation and (v

x

, v y

, v z

) defines the axis direction. The angular velocity is w in radians per second.

Nodes are converted from be to rectangular coordinates. The equations for these transformation are:

X = R cos

θ

sin ϕ

Y = R sin

θ

sin ϕ

Z = R cos ϕ

The initial temperature of this part is t and it can be expressed as a function of x, y, z coordinates.

Plates have the thickness thic for this part.

Assign initial rigid body velocity to all nodes within this parts. (V

x

, V y

, V z

) is the global velocity vector. (V

x

, V y

, V z

) can be expressed as a function of x, y, z coordinates.

10.2

LS-INGRID

11. DYNA3D Part

DYNA3D PART

The DYNA3D part provides for importing existing DYNA3D input files into LS-

INGRID. The form of the part is as follows:

For DYNA3D or LS-DYNA3D input files, use:

DYNA3D filename

<optional functions>

END

For VEC-DYNA3D input files, use:

VECDYNA filename

<optional functions>

END

filename is the name of the DYNA3D input file.

11.1 O

PTIONS AND

F

UNCTIONS

Functions require the ability to identify groups of nodes and elements in a part and assign various properties. These have the general form of

Keyword <region> function data

Where <region> is a part specific description of where the function is to be applied. For the current part, the nodes or elements through either node or element numbers or through analytical expressions. As an example:

SI [mat==2] 1 M C Elements of material 2 are assigned to

C the master side of contact interface 1.

Variables available for function application are as follows:

Variable Description x y z Part local coordinates of node or element xg yg zg center.

Global coordinates of node or element center.

node mat elem

Node number.

Material number.

Element number.

The following options are allowed in any order. Additional functions can be applied and are described in the section on Loads and Boundary Conditions.

COOR nc data Input nc local coordinate systems. Coordinate

11.1

DYNA3D PART

CYLI

LREP l

1

l

2

... l

n

MATE matnum

REPE l

1

l

2

... l

n

ROTA p

x

p y

p z

v x

v y

v

z w

SPHE

TEMP t

THIC thic

VELO v

x

v y

v z

LS-INGRID

system data is described in detail in the section on Coordinate Transformations.

Nodes are converted from cylindrical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

Y = R sin

θ

Repeat command. This command makes copies of the part in each of the local coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

The part has material number matnum.

Repeat command. This command makes copies of the part in each of the global coordinate systems l

1

to l

n

. If the coordinate system number is zero, the part is repeated with no transformation.

Assign an initial rigid body rotation to the part.

(p

x

, p y

, p z

) is any point on the axis of rotation and (v

x

, v y

, v z

) defines the axis direction. The angular velocity is w in radians per second.

Nodes are converted from spherical to rectangular coordinates. The equations for this transformation are:

X = R cos

θ

sin ϕ

Y = R sin

θ

sin ϕ

Z = R cos ϕ

The initial temperature of this part is t and it can be expressed as a function of x, y, z coordinates.

Plates have the thickness thic for this part.

Assign initial rigid body velocity to all nodes within this parts. (V

x

, V y

, V z

) is the global velocity vector. (V

x

, V y

, V z

) can be expressed as a function of x, y, z coordinates.

11.2

LS-INGRID LOADS AND BOUNDARY CONDITIONS

12. Loads and Boundary Conditions

Loads and boundary can be applied as optional functions within any of the previously describe parts. The syntax of <Region> can be slightly different depending on which part it is applied in. Refer to the appropriate part for a description of the meaning of <Region>.

Alternately, <Region> may be an expression. The local part coordinates for a node are stored as internal variables, x, y and z. The current global coordinates of the same node are

xg, yg and zg. The node number is stored as variable node. Thus, to create slave nodes for sliding interface 6, the following command may be used:

SFC [(node<=55)$$(x>5.0)] 6

ACC <Region> lc amp f

x

f y

f z

-or- Acceleration boundary condition. The load curve

ACCI <Index Progression> lc amp f

x

f y

f z

number is lc. amp is a scale factor and (f

x

,f y

,f z

) indicates the load direction.

ACCE acc_name local_node Definition of accelerometer acc_name. The local node numbers are 1 through 3.

Options:

N <Point>

P p

x

p

y

p

z

m

The local node is defined by <Point>.

The local node is at point (p

x

,p y

,p z

) in the local coordinate system. m is the rigid body number which is attached to the node.

B n

;

B <Region> code

The local joint node has boundary constraint n. n is a six digit binary number which specifies degrees of freedom to be constrained. Numbering digits from left to right they affect the following degrees of freedom.

1st digit: x-displacement

=0 free

=1 fixed

2nd digit: y-displacement

3rd digit: z-displacement

4th digit: x-rotation

5th digit: y-rotation

6th digit: z-rotation

Terminate ACCE command.

Boundary condition keyword. Code is a six digit binary number which specifies degrees of freedom to be constrained. Numbering the digits from left to right they affect the following

12.1

LOADS AND BOUNDARY CONDITIONS

degrees of freedom

1st digit: x-displacement

=0: free

=1: fixed

2nd digit: y-displacement

3rd digit: z-displacement

4th digit: x-rotation

5th digit: y-rotation

6th digit: z-rotation

BELT type belt_name local_node

LS-INGRID

Seat belt definition. This command identifies local node number local_node for item

belt_name. Values for type are as follows:

=RETRACTOR: Retractor definition.

=SENSOR: Sensor definition.

=SLIPRING: Slipring definition.

Options:

N <Point>

P p

x

B n

p y

p z

m

;

CNV <Region> icv p

x

p y

p z

-or-

CNVI <Index Progression> icv p

x

p y

p z

CSE <Point> n

PO i j k

RA <Region>

The local node is defined by <Point>.

The local node is at point (p

x

,p y

,p z

) in the local coordinate system. m is the rigid body number which is attached to the node.

The local node has boundary constraint n. n is a six digit binary number which specifies degrees of freedom to be constrained. Numbering digits from left to right they affect the following degrees of freedom.

1st digit: x-displacement

=0: free

=1: fixed

2nd digit: y-displacement

3rd digit: z-displacement

4th digit: x-rotation

5th digit: y-rotation

6th digit: z-rotation

Terminate BELT command.

Control volume. This command defines segments for control volume number icv. The segments are facing towards point (p

x

,p y

,p z

).

(MVMA/DYNA3D, LS-910 and later).

Identify elements for LS-DYNA3D crosssection resultant force calculations on interface

n.

Use the element offset from <Point> by (i,j,k).

Ignore <Point> and grab the elements identified

12.2

LS-INGRID

;

RO im jm km ix jx kx

CSN <Region> n

CSY <Region> side -or-

CSYI <Index Progression> side

CV <Region> lc

1

h lc

2

Tinf a -or- Convection boundary condition for surface

CVI <Index Progression> lc

1

h lc

2

T

inf

a

segments. lc

1

is the load curve for the convection coefficient with scale factor h. lc

2

is the load curve for the ambient temperature with scale factor T

in

. a is the exponent in the equation q=h(T-T

inf

)a.

CVL <Region> lc

1

h lc

2

T

inf

a

EDR i j k n

Convection boundary condition for edge segments.

Identify elements for deletion during restart number n. (i,j,k) are the minimum indices of the region in which elements are to be deleted.

Options:

RO i

m

j m

k m

i x

j x

k x

;

The elements to be deleted are the absolute indices i

m

<i<i

x

,j m

<j<j

x

, k

m

<k<k

x

, but offset by

(i,j,k).

Terminates this function.

EPB <Point>

PO i j k

;

RO i

m

j m

k m

i x

j x

k x

FC <Region> lc amp fx f

y

f z

-or-

FCI <Index Progression> lc amp f

FD <Region> lc amp f

x

f y

f z

-or-

FDI <Index Progression> lc amp f

x x

f

f y y

f

f z z

LOADS AND BOUNDARY CONDITIONS

by <Region>.

Use the block of elements offset from <Point>.

Terminate this command.

Identify nodes for LS-DYNA3D cross-section resultant force calculations on interface n.

Cyclic symmetry interface nodes. side can be

MASTER or SLAVE. (VEC/DYNA3D, LS-

920 and later).

Element Print Blocks.

Use the element offset from <Point> by (i,j,k).

Use the block of elements offset from <Point>.

Terminate this command.

Point force. The load curve number is lc. amp is a scale factor and (f

x

,f y

,f z

) indicates the load direction.

Displacement boundary condition. The load curve number is lc. amp is a scale factor and (f

x

,f y

,f z

) indicates the load direction.

12.3

LOADS AND BOUNDARY CONDITIONS LS-INGRID

FIND <Point> expr1 expr2 expr3 expr4 The FIND command places the generated coordinates of <Point> into the variables [cenx]

[ceny] [cenz] and the node number into [node].

Example:

FIND 1 2 1 [bp3x=cenx] [bp3y=ceny]

[bp3z=cenz] [bp3n=node]

Flux boundary condition.

FL <Region> lc scal -or-

FLI <Index Progression> lc scal

FN <Region> e

fail

FRV <Region> lc amp vx vy vz

All nodes within <Region> are failure nodes and will fail at strain e

fail

. Additional nodes are created, shell elements, pressure surfaces, and slide surfaces are renumbered to permit independent motion of adjacent elements (LS-

DYNA3D).

Failure nodes are a simple method for allowing fracture. Each adjacent element has completely independent nodes. Groups of nodes are initially constrained to move together. When the average strain of adjacent elements reaches the failure strain, the constraint is eliminated and the elements separate.

Set rotational velocity boundary conditions.

FT <Region> lc T -or-

FTI <Index Progression> lc T

FTB <Region> lc T Tbase -or-

FTBI <Index Progression> lc T Tbase

FV <Region> lc amp f

x

FVI <Region> lc amp f

f x y

f

f y z

f

-or-

z

Set temperature boundary condition to T and scaleby load curve lc.

Set temperature boundary condition to T and scale by load curve lc. The scaling is:

(T-Tbase)*f(lc,time).

Velocity boundary condition. The load curve number is lc. amp is a scale factor and (f

x

,f y

,f z

) indicates the load direction.

GEOC <Region> igeo

IN <Region> name -or-

INI <Index Progression> name

IS <Region> name -or-

ISI <Index Progression> name

JOY <Region> -or-

Geometric contact slave nodes. All identified nodes are slaved to geometric contact entity

igeo. (LS-910 and later.)

Define nodes associated with component interface name. (LS-920 and later.)

Define segments associated with component interface name. (LS-920 and later.)

Identify JOY interface nodes. (JOY is an

12.4

LS-INGRID

JOYI <Index Progression>

JT

l jn

Options:

N <Point>

P p

INC i

B n

x

p y

p z

m

;

MKI, MKI+, MKI-

<Index Progression> m p

x

p y

p

z -or-

MK, MK+, MK- <Region> m p

x

p y

p z

MKL <Region> m

N+ <Region> p

x

p y

p z

-or-

NI+ <Region>

p x

p y

p z

N- <Region> p

x

p y

p z

-or-

NI- <Region>

p x

p y

p z

LOADS AND BOUNDARY CONDITIONS

Eulerian hydrocode which exists only at Lawrence

Livermore National Laboratory).

Joint command.

Joint definition number.

Local node number (See Figure 2-1).

The local joint node, l, is defined by <Point> in the index space.

The local joint node, l, is at point (p

x

,p y

,p z

) in the local coordinate system. m is the rigid body number which is attached to the node.

Increment jn by i for each copy of the part. (default =

1).

The local joint node has boundary constraint n.

n is a six digit binary number which specifies degrees of freedom to be constrained.

Numbering digits from left to right they affect the following degrees of freedom.

1st digit: x-displacement

=0: free

=1: fixed

2nd digit: y-displacement

3rd digit: z-displacement

4th digit: x-rotation

5th digit: y-rotation

6th digit: z-rotation

Terminate joint command.

Surfaces in <Region> or <Index Progression> are assigned marked surface number m.

For MK+ and MKI+ the surface points toward this point. For MK- and MKI- the surface points away from this point. Do not input (p

x

, p y

, p z

) for MK or MKI.

Identify marked line number m.

Shell normal orientation command. (p

x

,p y

,p z

) is a vector along the element normal vector.

Shell normal orientation command. (p

x

,p y

,p z

) is a vector reverse to the element normal vector.

12.5

LOADS AND BOUNDARY CONDITIONS

NPB <Point> Nodal Print Block.

Options:

PO i j k

LS-INGRID

Use the node offset from <Point> by (i,j,k).

RO i

m

j m

k m

i x

j x

k x

Use the block of nodes offset for <Point>.

;

NFG <Region> name -or-

NFGI <Index Progression> name

NRB <Region> -or-

NRBI <Index Progression>

ORV

Terminate this command.

Identify nodal force group name.

Identify non-reflecting boundaries.

l jn

Options:

N <Point>

Define orientation vectors. The orientation vectors are used to specify which axis is to be used for determining the effects of springs and dampers. This particular option is used when two nodes are required for specifying an axis slaved to a body.

Orientation vector number.

Local node number (either 1 or 2).

P p

x

p y

p z

m

The local orientation vector node, l, is defined by <Point> in the index space.

The local orientation vector node, l, is at point

(p

x

,p y

,p z

) in the local coordinate system. m is the rigid body number which is attached to the node.

;

INC i

B n

Increment jn by i for each copy of the part. (default =

1).

The local orientation vector node has boundary constraint n. n is a six digit binary number which specifies degree of freedom to be constrained. Numbering digits from left to right they affect the following degrees of freedom.

1st digit: x-displacement

=0: free

=1: fixed

2nd digit: y-displacement

3rd digit: z-displacement

4th digit: x-rotation

5th digit: y-rotation

6th digit: z-rotation

Terminate ORV command.

12.6

LS-INGRID

PM <Region> m

PR <Region> -or-

PRI <Index Progression>

lc p a

PRL <Region>

lc p a x x

a

a y y

a

a z z

LOADS AND BOUNDARY CONDITIONS

All nodes within <Region> have mass m attached to them.

Signifies pressure load command for surface segments.

Load curve or load curve number.

Pressure magnitude. Spatial variations may be obtained by inputting p as a function of global coordinates (x,y,z).

(a

x

,a y

,a z

) is a point in the local coordinate system toward which the pressure acts. By specifying (a

x

,a y

,a z

) LS-INGRID knows in which direction the pressure is acting and numbers the pressure card node accordingly.

Signifies pressure load command for edge segments.

Load curve or load curve number.

Pressure magnitude.

(a

x

,a y

,a z

) is a point in the local coordinate system toward which the pressure acts. By specifying (a

x

,a y

,a z

) LS-INGRID knows in which direction the pressure is acting and numbers the pressure card node accordingly.

RB <Region> lc1 f lc2 t

inf

-or-

RBI <Index Progression> lc1 f lc2 t

inf

RBN <Region> set_name

Radiation boundary condition.

Assign nodes to rigid body node set set_name.

RE <Region> lc1 T flag -or- Define a radiation enclosure. lc1 is a load curve for emissivity. The temperature of the segment is T if lc1=0. flag is "YES" if this surface is to be included in obstructing surface calculations and "NO" otherwise.

Note: If this option is used, segments are oriented so that they face outward from the adjacent conduction elements. An error occurs if radiation segments defined by this command are not adjacent to a conduction element because the outward normal would be indeterminate.

RE+ <Region> lc1 T flag p

x

p y

p z

-or-

RE- <Region> lc1 T flag p

x

p y

p z

Define a radiation enclosure. lc1 is a load curve for emissivity. The temperature of the segment is T if lc1=0. flag is "YES" if this surface is to be included in obstructing surface calculations

12.7

LOADS AND BOUNDARY CONDITIONS LS-INGRID

and "NO" otherwise. (p

x

,p y

,p z

) is a point in the local coordinate system toward which the radiation occurs (RE+), or facing the opposite direction

(RE-).

RXN <Region> mat -or-

RXNI <Index Progression> mat

SBI <Region> idir ioff1 ioff2

SC <Region> idir{options}

Extra nodes for rigid body of material mat.

Define a shell/brick interface. <Region> must be a point or a line in the index space.side

="b": We are identifying nodes on the brick side of the interface.

="s": We are identifying nodes on the shell side of the interface.

Nodes on an interface are in a line parallel to axis idir.

=I: I-axis

=J: J-axis

=K: K-axis

Increments for determining the nodes to be selected along direction dir.

ALE smoothing constraints. idir Smoothing constraints are generated along the line defined by axis idir.

=I: I-axis

=J: J-axis

=K: K-axis

Options:

1A i j k

;

1R i j k

2A i j k

2R i j k

PRE

The first point of the smoothing constraint is located at absolute indices (i,j,k).

The first point of the smoothing constraint is located at absolute indices (i,j,k).

The last point of the smoothing constraint is located at absolute indices (i,j,k).

The last point of the smoothing constraint is located at absolute indices (i,j,k).

Constraints are applied before ALE iterative smoothing is done. (The default requires that the constraints be performed after the smoothing is done.)

Terminate smoothing constraint command.

12.8

LS-INGRID

SFC <Region> n

LOADS AND BOUNDARY CONDITIONS

Identify slave nodes for sliding interface n. This is used for interfaces which involve nodes impacting surfaces or to make more precise distinctions between master and slave sides for the merging algorithms.

Identify sliding interfaces.

SI <Region> -or-

SII <Index Progression> islid mslid

Sliding interface number

Master/slave flag

="M": master surface

="S": slave surface

Identify sliding interface.

SI+ <Region> -or-

SII+ <Index Progression> islid1 mslid

p x

p y

p z

Sliding interface number

Master/slave flag.

="M": master surface.

="S": slave surface.

A point in the local coordinate system toward which the sliding interface faces.

Signifies sliding interface command.

SI- <Region> -or-

SII- <Index Progression> islid1 mslid

p x

p y

p z

SL <Region> n isid

Sliding interface number.

Master/slave flag.

="M": master surface.

="S": slave surface.

A point in the local coordinate system which the sliding interface faces away from.

Define nodes on slide line n. <Region> should be a line in the index space. isid is either

"master" or "slave". This command is sometimes useful in conjunction with SI to fix node tolerance problems.

SPC <Region> name xyzxyz -or- Single point constraints to plane name. xyzxyz is

SPCI <Index Progression> name xyzxyz a binary number which is zero for an unconstrained degree-of-freedom and 1 for a constrained degree-of-freedom. The left three digits are for the translational dof's and the right three are for the rotational.

SPDP <Region> {options} n1 isid Define springs or dampers on all nodes within

12.9

LOADS AND BOUNDARY CONDITIONS LS-INGRID

<Region>. They behave according to spring/damper definition n. isid is used to force nodes to be on opposite side of the definition.

isid="m" for the master side and "s" for the slave side. {options} are as follows:

ORV n This spring/damper acts along orientation vector

n.

POFF

PON

SCAL s

Turn element printing off (default).

Turn element printing on.

The spring/damper force is scaled by s.

SW <Region> n -or-

SWI <Index Progression> n

SYSJ

l jn

Slave nodes to stonewall number n.

Joint command.

Joint definition name.

Local node number. Nodes 1 through 3 define the local system for the master side of a joint.

Nodes 4 through 6 define the slave side of a joint.

Options:

INC i

B n

N <Point>

P p

x

p y

p z

m

Increment jn by i for each copy of the part. (default =

1).

The local joint node has boundary constraint n.

n is a six digit binary number which specifies degrees of freedom to be constrained.

Numbering digits from left to right they affect the following degrees of freedom.

1st digit: x-displacement

=0: free

=1: fixed

2nd digit: y-displacement

3rd digit: z-displacement

4th digit: x-rotation

5th digit: y-rotation

6th digit: z-rotation

The local joint node, l, is defined by <Point> in the index space.

The local joint node, l, is at point (p

x

,p y

,p z

) in the local coordinate system. m is the rigid body number which is attached to the node.

12.10

LS-INGRID

SYSTEM name

;

TH <Region> -or-

THI <Index Progression> thick

TM <Region> t -or-

TMI <Index Progression> t

TN <Region> n -or-

TNI <Index Progression> n

VE <Region>

LOADS AND BOUNDARY CONDITIONS

The local joint node, l, is defined for system name. (Default is the current active system.)

Terminate joint command.

Specify thickness command.

Thickness of plates within the region.

Set initial temperature (TOPAZ) or steady

State temperature (DYNA/NIKE) to t.

Set thickness number to n.

Set edge visibility on for outline and phantom edge plotting. <Region> must be a line in the reduced index space.

12.11

LOADS AND BOUNDARY CONDITIONS LS-INGRID

12.12

AJNP p

x

p y

p z

AM m

1

m

2

...,

AMN m

1

m

2

...,

AP p

1

p

2

...;

ARROW

ASCII

BPTOL p

1

p

2

t

CCEN

CCOL

i r g b

CENT

CHUE m h

CONT

CSAT

m s

D x

DI ACCE

DI BELT

LS-INGRID

13. Interactive Commands

INTERACTIVE COMMANDS

After the model is generated, LS-INGRID enters the interactive graphics phase of the program. The x-axis in screen coordinates is fixed relative to the screen and extends horizontally to the viewers right. The y-axis is positive up. The z-axis extends out of the screen towards the viewer.

The following commands are allowed in this phase.

Print the nodal point which is nearest to point

(p

x

,p y

,p z

).

Add materials m

1

, m

2

,... (by number) to the active list.

Add materials m

1

, m

2

,... (by name) to the active list.

Add parts p

1

, p

2

, ... to the active list.

Toggle arrow plotting on or off. This allows the direction of the tool path to be visualized.

Read ASCII tracer particle file.

The tolerance to be used when merging part p

1 to p

2

is t.

Select the center of the picture using the mouse.

Change the (red,green,blue) values of color number i to (r,g,b).

Moments and products of inertia are determined relative to the centroid and global axes (default).

Change hue of material m to h.

Finish model generation and format the output file.

Change saturation of material m to s.

Move down distance x relative to the structure.

Display accelerometers.

Display seat belts.

13.1

DI DX

DI DY

DI DZ

DI EDR n

DI EPB

DI F lc

DI FL

DI FLUX

DI FSYM

DI INTF name

DI JOY

DI JTS

DI L3D

INTERACTIVE COMMANDS

DI CNV n

DI CSEC n

DI CSYM n

DI CV

DI CVL

DI D lc

DI DETP

DI DS n

1

n

2

... ;

DI DSAD n

1

n

2

... ;

DI DSRM

n

1

n

2

... ;

LS-INGRID

Display DYNA3D control volume n.

Display DYNA3D force output cross section n.

Display cyclic symmetry boundary conditions.

Display convection boundary condition.

(surface segments).

Display convection boundary condition. (edge segments).

Display forced displacements associated with load case (or load curve) lc.

Display detonation points.

Display digitized surface definitions n

1

, n

2

...

Display digitized surfaces and add definitions

n

1

, n

2

... to the display list.

Display digitized surfaces and remove definitions n

1

, n

2

... from the display list.

Display X-translational boundary conditions.

Display Y-translational boundary conditions.

Display Z-translational boundary conditions..

Display elements to be deleted on restart n.

Display element print blocks.

Display point loads associated with load case

(or load curve) lc.

Display flux boundary conditions; (edge segments).

Display flux boundary condition; (surface segments).

Display failing symmetry planes.

Display component substructure name.

Display joy interface nodes.

Display joints.

Display three-dimensional line definitions.

13.2

LS-INGRID

DI LAX code

DI PL lc

DI PM

DI PR lc

DI PV n

DI RB

DI RBL

DI RBN

DI M m

1

m

2

... ;

DI MCG m

DI MK m

DI NCV

DI NFG

DI NRB

DI NPB

DI NSF

DI NV

DI ORV

DI OUTL

DI P p

1

p

2

... ;

INTERACTIVE COMMANDS

Display local axes.

code = "R": code = "S": code = "T": local R-axis local S-axis local T-axis code = "RS": local RS-axes code = "ST": local ST-axes code = "TR": local TR-axes code = "RST": local RST-axes code = "CORI": local composite angles

Materials m

1

, m

2

, ... are to be highlighted during plotting.

Display mass properties of individual materials.

Display marked surface m.

Display NURB curves.

Display nodal force groups.

Display non-reflecting boundaries.

Display nodal print blocks.

Display NURB surfaces.

Display shell element normal vectors.

Display orientation vectors.

Display free edges of shells.

Parts p

1

, p

2

, ... are to be highlighted during plotting.

Display pressure surfaces associated with load case (or load curve) lc; (edge segments).

Display point masses.

Display pressure surfaces associated with load case (or load curve) lc; (surface segments).

Display tool path n.

Display radiation boundary conditions. (surface segments).

Display radiation boundary conditions; (edge segments).

Display nodal rigid bodies. (LS-910 and later).

13.3

DI SPC

DI SPD

DI SW s

DI SY isym

DI SYSJ isym

DI TB

DI TI

DI TRACER

DI VB lc

DI VECT c

INTERACTIVE COMMANDS

DI RE

DI REL

DI RX

DI RXN m

DI RY

DI RZ

DI SBI

DI SFC

islid mslid

DI SI islid mslid

DI SL n isid

LS-INGRID

Display radiation enclosure; (surface segments).

Display radiation enclosure. (edge segments)

Display X-rotational boundary conditions.

Display extra nodes slaved to rigid body material m.

Display Y-rotational boundary conditions.

Display Z-rotational boundary conditions.

Display shell/brick interfaces.

Display nodes which are part of sliding interface definition islid.

mslid = "M": display master side.

mslid = "S": display slave side.

mslid = "B": display both sides.

Display slide surface islid; (surface segments).

mslid = "M": display master side mslid = "S": display slave side mslid = "B": display both sides

Display slide line n; (edge segments).

mslid = "M": display master side.

mslid = "S": display slave side.

mslid = "B": display both sides.

Display single point constraints.

Display springs and dampers.

Display stonewall s.

Display symmetry plane isym.

Display symmetry plane isym.

Display temperature boundary conditions.

Display temperature initial conditions.

Display tracer particles.

Display velocity boundary conditions associated with load curve lc.

Display vectors of component c.

c = IV: initial velocity

c = IR: initial rotational velocity

c = IDV: initial distortional velocity

13.4

LS-INGRID

DI WARP ang

DIAD

DICOL l

DIOFF

DM m

1

m

2

...,

DMN m

1

m

2

...,

DMEM

DRAW

DSV

DSVS d

1

, d

2

, ...d

n

;

DSAD d

1

, d

2

, ...d

n

;

DSRM d

1

, d

2

, ...d

n

;

ELPLT on/off

EXIT

FOLD n d

FRAME

INTERACTIVE COMMANDS

c = IRB: initial rigid body velocity

c = V: current velocity

c = DV: current distortional velocity

c = RB: current rigid body velocity

c = A: current acceleration

Display shells with warp angles that exceed ang.

This can be used in any of the above commands instead of DI. If this is used, then the display request is in addition to the previous ones rather than replacing them.

Following DI and DIAD options are to be performed using color number l. Valid numbers for l are 1 through 7.

Turn off display options.

Delete materials m

1

, m

2

, ... (by number) from active display list.

Delete materials m

1

, m

2

, ... (by name) from active display list.

Dump memory allocations statistics.

Draw the mesh. All mesh lines are plotted.

View three-dimensional digitized surfaces.

View digitized surfaces d

1

, d

2

...

Add digitized surfaces d

1

, d

2

... to the active display list.

Remove digitized surfaces d

1

, d

2

... from the active display list.

Turn element number plotting on or off. The default is off.

Exit LS-INGRID now.

Airbag folding. All nodes of the model are included in the fold operation. Fold definitions

1 through n are applied in ascending order. d is an optional thickness which can be used to increase the fold thicknesses. The maximum of

d and the fold definition specified thickness is used.

Reference frame with tick marks plotted

13.5

INTERACTIVE COMMANDS

GRID

INFO

L x

L3V

L3VS l

1

, l

2

, ...l

n

;

LCV n

LIGHT p

x

p y

p z

LMIN l

LSIZE

LV

LVI m n

LVS l

1

, l

2

, ... l

n

;

M m

1

m

2

...,

MCOL

MMASS

MN m

1

m

2

...,

MPLT

MSIZ

NCV

;

NCV d

1

, d

2

, ... d

n

;

NCAD d

1

, d

2

, ... d

n

;

LS-INGRID

(default).

Displays will be overlaid by a grid of orthogonal lines. (Two dimensional plots only).

Print information on the mesh size.

Move left a distance x relative to the structure.

View three dimensional digitized surfaces.

View all three-dimensional lines l

1

, l

2

, ...

View load curve n.

Locate the light source for continuous color plots at (p

x

,p y

,p z

).

Set minimum luminosity for continuous color plots to l.

On/off switch for printing extent of active threedimensional line definitions during plotting.

Display all two-dimensional line definitions.

Display lines m to n.

Display lines l

1

, l

2

, ...

Display materials m

1

, m

2

, ... (by number).

Color plots based on element materials. (See also PCOL).

This is the same as TMASS except that the calculation is only performed for the active materials.

Display materials m

1

, m

2

, ... (by name).

Plot mass properties on screen.

Print the extent of the current active material subset.

View all NURB curves.

View NURB curves d

1

, d

2

...

Add NURB curves d

1

, d

2

... to the active display list.

13.6

LS-INGRID

NCRM d

1

, d

2

, ... d

n

;

NDPLT on/off

NOFRAME

NOGRID

NSET n x y z

NSV

;

NSV d

1

, d

2

, ...d

n

;

NSAD d

1

, d

2

, ... d

n

;

NSRM d

1

, d

2

, ... d

n

;

OVERLAY n x y z

P p

1

p

2

... ;

PCHK

PCOL

PFOLD n d p

1

p

2

PINF

PMASS

POOR

INTERACTIVE COMMANDS

Remove NURB curves d

1

, d

2

... from the active display list.

Turn node number plotting on or off. The default is off.

No reference frame is plotted.

Displays will not be overlaid by a grid of orthogonal lines. (Default).

Set the coordinates of node n to (x,y,z).

View all NURB surfaces.

View NURB surfaces d

1

, d

2

...

Add NURB surfaces d

1

, d

2

... to the active display list.

Remove NURB surfaces d

1

, d

2

... from the active display list.

Stop screen erasing of previous picture so that the next picture is overlaid.

Display parts p

1

, p

2

, ... To display all parts simply type "P ;". The ";" is also optional so that the command "P 1 VIEW" would show part one on the screen.

Turn on checking of penetrations in the single surface contact algorithms. Currently, this is only designed to work with the airbag folding capability. Repeating this command will turn the option off. Penetrations are graphically displayed.

Color plots based on element parts. This is the default. (See also MCOL).

This is the same as the FOLD command except that only parts p

1

through p

2

are treated rather than the entire mesh.

Print information on each part.

This is the same as TMASS except that the calculation is only performed for the active parts.

Poor man's hidden line algorithm.

13.7

INTERACTIVE COMMANDS

PRINT v

PSRGB

PTOL n t

PV

PVS p

QUIT

R x

1

REFP r

p

REDUCE

x

2

r

... p

y

r z

n

;

LS-INGRID

Echo the value of v back to the terminal. This is most frequently used with the calculator program. (e.g. "PRINT [SQRT(27)*24.3]" )

Create a RGB Postscript file.

Set the tolerance for part n to t. See also "T" and "TP".

View tool paths.

View tool paths p

1

, p

2

, ...

Quit LS-INGRID now.

Move right a distance x relative to the structure.

Eliminate exterior faces which have become interior faces due to the tolerance command.

Moments and products of inertia are determined relative to the point (r

x

,r y

,r z

) and global axes.

RESO ires

RP p

RX

RY

θ

θ

1

p

2

... ;

Set the Z-buffer resolution to ires for the VIEW command. ires is limited to one of 256, 512,

1024, 2048, 4096, 8192. (The default is 1024).

Restore all rotations to their initial settings.

REST

Note: The local coordinates are fixed to the model and rotate as the model rotates.

RLX

θ

RLY

θ

RLZ

θ

Rotate the body

Rotate the body

Rotate the body

θ

θ

θ

degrees about the local x-axis.

degrees about the local y-axis.

degrees about the local z-axis.

RM m

1

m

2

... , Remove materials m

1

, m

2

, ... (by number) from the active list.

RMN m

1

m

2

... , Remove materials m

1

, m

2

, ... (by name) from the active list.

Remove parts p

1

, p

2

, ... from the active list.

Rotate body

θ

degrees about the x-axis in the screen coordinates. A positive rotation is counterclockwise.

Rotate body

θ

degrees about the y-axis in the screen coordinates. A positive rotation is counterclockwise.

13.8

LS-INGRID

RZ

θ

SCALE s

SCOL

SEAL name

SEAL CIRCLE

SEAL OFF

SEAL OUTLINE

SHRINK s

SIZE

STOP

T tol

TMASS

TP tol

TRIAD on/off

TRPT

TTIME

INTERACTIVE COMMANDS

Rotate body

θ

degrees about the z-axis in the screen coordinates. A positive rotation is counterclockwise.

Multiply the mesh size by s. Default is 1.0.

Color plots based on system name; (see also

MCOL and PCOL).

Seal airbag edges which are marked with name.

Seal the airbag periphery. The airbag mesh is assumed to be circular in the x-y plane and centered along the z-axis at z=0; (default).

Turn off airbag sealing options.

Seal the free edges of an airbag.

Shrink individual elements by s when plotting.

This is used to see if there are any holes in the mesh.

Print the range of coordinates in the current active part list.

Exit the program immediately.

Remove duplicate nodes within a distance tol.

This command will not eliminate coincident nodes on opposite sides of slide surfaces or joints.

Calculate the total mass of the model. Mass densities must be input using the MAT command. This command also calculates kinetic energy, linear momentum, volume, moments of inertia, and the centroid.

Remove duplicate nodes within a distance tol and print the number of nodes merged between any two parts.

Show the coordinate system triad on the screen when doing three-dimensional plots. The default is on.

On/off flag for printing timing statistics from plot commands.

Plot time histories of tracer particles. (See also

ASCII TRACER.) comp is one of the following components:

= SX -->

σ xx

13.9

13.10

LS-INGRID INTERACTIVE COMMANDS

13.1 Exploded View Commands

Exploded view commands permit collections of parts or materials to be moved from their generated locations. Exploding a model will affect the graphics and mass property calculations, but will not affect the output computational model. Exploding a model with respect to parts will only affect the TMASS and PMASS commands, while exploding with respect to materials will only affect the MMASS command.

MEXP

MLOC data

MMOV data

MSEL m

NEXP

PEXP

PSEL p

1

1

m

PLOC data

PMOV data

, p

2

2

... ;

, ... ;

Exploded views are performed with respect to materials. This command is automatically invoked by all other material explode commands.

Set position of material subset to the position specified in data. Data is described in the section on Coordinate Transformations.

Shift the position of material subset by the transformation specified in data. Data is described in the section on Coordinate

Transformations.

Select material subset m

1

, m

2

, ... ; for explode operations.

Turn off exploded view option.

Exploded views are performed with respect to parts. This command is automatically invoked by all other part explode commands.

Set position of part subset to the position specified in data. Data is described in the section on Coordinate Transformations.

Shift the position of part subset by the transformation specified in data. Data is described in the section on Coordinate

Transformations.

Select part subset p

1

, p

2

, ... ; for explode operations.

13.11

INTERACTIVE COMMANDS LS-INGRID

13.2 TAURUS/Post-Processing Commands

The post-processing phase of LS-INGRID allows for the generated models to be displayed in their deformed configurations with a variety of boundary conditions or other graphical information superimposed. Some time history facilities are also included.

TAURUS file

ALAB label

ALAB OFF

ASCL scale

ASET min max

DSF d

DTS s

1

s

2

GTIME comp ;

LS

LTS

NTIME comp n

1

n

2

... ;

NTIME comp ;

OLAB label

OLAB OFF

OSCL scale

OSET min max

REP s

1

S n

S 0

SI n

s

2

k

Read TAURUS database file.

Set abscissa label.

Use default abscissa label.

Set abscissa scale factor.

Set abscissa range.

Set displacement scale factor to d; (default=1.0).

Delete states s

1

through s

2

.

Plot global component comp. Components are defined in table 13.2.1.

Last state.

List time states.

Plot nodal component comp for nodes n

1

, n

2

, ...

Components are defined in table 13.2.2.

Plot nodal component comp for the previously used nodal list. Components are defined in table 13.2.2.

Set ordinate label.

Use default ordinate label.

Set ordinate scale factor.

Set ordinate range.

Execute the next plot command from states s

1

to

s

2

by increment state increment k.

Select state number n.

Plot the generated geometry.

Increment the state number by n.

13.12

LS-INGRID

UDEF n

INTERACTIVE COMMANDS

The undeformed state is number n; (default=1).

13.13

A

DV

IDV

IR

IRB

IV

RB

V

INTERACTIVE COMMANDS

T

ABLE

13.2.1

G

LOBAL

T

IME

H

ISTORY

C

OMPONENTS

ENERGY

MOMENTUM

XVEL

YVEL

ZVEL

INTERNAL

KINETIC

TOTAL

LS-INGRID

Plot the total, kinetic and internal enegy.

Plot the momentum vector.

X-momentum/total mass.

Y-momentum/total mass.

Z-momentum/total mass.

Internal enegy.

Kinetic enegy.

Total enegy.

T

ABLE

13.2.2

V

ECTOR

P

LOT

C

OMPONENTS

Current acceleration.

Current distortional velocity.

Initial distortional velocity.

Initial rotational velocity.

Initial rigid body velocity.

Initial velocity.

Current rigid body velocity.

Current velocity.

13.14

LS-INGRID

Rectangular coordinates:

X

Y

Z

AX

AY

AZ

DX

DY

DZ

VX

VY

VZ

Cylindrical coordinates:

CR

CT

CZ

CAR

CAT

CAZ

CDR

CDT

CDZ

CVR

CVT

CVZ

Spherical coordinates:

SR

ST

SP

SAR

SAT

SAP

SDR

SDT

SDP

SVR

SVT

SVP

Special components:

TEMP

TIME

TOTP

TOTA

TOTD

TOTV

INTERACTIVE COMMANDS

T

ABLE

13.2.3

N

ODAL

T

IME

H

ISTORY

C

OMPONENTS

X-position

Y-position

Z-position

X-acceleration

Y-acceleration

Z-acceleration

X-displacement

Y-displacement

Z-displacement

X-velocity

Y-velocity

Z-velocity

Radial-position

Circumfirential-position

Axial-position.

Radial-acceleration

Circumfirential-acceleration

Axial-acceleration

Radial-displacement

Circumfirential-displacement

Axial-displacement

Radial-velocity

Circumfirential-velocity

Axial-velocity

Radial-position

Theta-position

Phi-position

Radial-acceleration

Theta-acceleration

Phi-acceleration

Radial-displacement

Theta-displacement

Phi-displacement

Radial-velocity

Theta-velocity

Phi-velocity

Temperature

Time

Total position

Total acceleration

Total displacement

Total velocity

13.15

INTERACTIVE COMMANDS LS-INGRID

13.16

LS-INRID TWO-DIMENSIONAL LINE DEFINITIONS

14. Two-Dimensional Line Definitions

Two-dimensional line definitions are lists of r,z (x,y) points which form a piecewise linear curve. Each line definitions has a number.

LAD r

c

z c

t

LADD l

1

sl

2

t

LADV ldr dz

LAP r

1

z

1

r c

z c

LAR r

1

z

1

R

LAT r

1

z

1

r

2

z

2

R

LCC n r

c

z c

t

1

t

2

r

1

... r

n

LD n

Define a circular arc centered at point (r

c

,z c

), beginning at the last point defined and sweeping through t degrees. Positive t is assumed to be counterclockwise.

Define line definition l as a linear combination of line definitions l

1

and l

2

. l = s* l

1

+ t *l

2

.

Add vector (dr,dz) to line definition l.

Define a circular arc by specifying points. The arc is assumed to begin at the last point defined and to end at (r

1

,z

1

). Point (r

c

,z c

) lies at the center of the arc.

Define a circular arc by specifying radius. An arc of radius R is assumed to begin at the last point defined and to end at (r

1

,z

1

). If R is positive, the center of the arc lies to the left as one moves from the last point defined to (r

1

,z

1

).

If R is negative, the center of the arc will be to the right.

Define a circular arc of radius R tangent to the last line segment and a line segment joining point (r

1

,z

1

) to point (r

2

,z

2

). These line segments will be automatically extended or truncated at the tangency point.

Define n lines consisting of circular arcs centered at point ( r

c

,z

c

) that sweep from angle

t

1

to t

2

. r

1

r

2

, ... r

n

are the radii of the next n lines. Line numbers are assigned by LS-

INGRID beginning with the next available number.

Begin line definition n.

14.1

TWO-DIMENSIONAL LINE DEFINITIONS

LEP a b r

c

z c

t

1

t

2

p

LEXP r(s) z(s) n

LINT l

LO m r

1

LOD m d

LP n r

LPIL l

LPT r

1

1

1

LPTA r

1

z

z

c

l

z

l

1

1

2

2

z

1

c

s

r

R

2

... r

r

2

z

z

n

2

2

z

R

n

LS-INGRID

Define an elliptical arc by the semi-major and semi-minor axes, a and b respectively, the center point (r

c

,z c

), and a sweep from angle t

1

to angle t

2

as measured from the major axis.

Angle p is the angle between the major axis and the r-axis. A circular arc is generated by setting

a=b. Positive angles represent counterclockwise rotations.

Define a line definition using expression r(s) and z(s) where 0 <s< 1. The number of points to be used is n.

The current line definition is formed by interpolation between line definition l

1

and line definition l

2

. The equation is l = s*l

1

+ (1-s) *

l

2

.

Define a line segment for line n by offsetting a segment of line m such that the first point of the new segment begins at (r

1

,z

1

) and the last point terminates at (r

2

,z

2

).

Define a line segment for line n by offsetting the entire line m a distance d. Positive d offsets the line segments to the left as one moves along line

m in the direction that was originally defined.

Negative d offsets the segment to the right.

The line definition consist of n points.

Define point for line n at the intersection point of lines l

1

and l

2

.

Define a circular arc of radius R beginning at the last point defined and tangent to a line segment joining point (r

1

,z

1

) to point (r

2

,z

2

).

This line segment will be extended or truncated to begin at the tangency point.

Define a line segment beginning at the last point defined and terminating at the tangency point on an arc of radius R centered at (r

c

,z c

). The first tangency point encountered as the arc is generated by a counterclockwise rotation from the r-axis will become the end point. If R is given as a negative number, a clockwise rotation from the r-axis will determine the first tangency point.

14.2

LS-INRID

LRL n r

c

LROT l t

z

LT n d

r

d z c

L t

LSCA l s

LSCR l s

LSCZ l s

LSTL m d

r

d z

1

... t

n

LTAS r

1

z

1

rot r

2

z

2

R

LTBC m t dt s r

LTP r z R

LVC t l

1

r

2

... r

m

LTBO m

1

d

1

m

2

d

2

... m

m

d m

TWO-DIMENSIONAL LINE DEFINITIONS

Define n lines consisting of radial lines of length

L originating at point (r

c

,z c

) and oriented at angles t

1

... t

n

. Positive angles are measured counterclockwise from r-axis.

Rotate line definition l about the origin t degrees.

Scale line definition l by s.

Scale r-coordinates of line definition l by s.

Scale z-coordinates of line definition l by s.

Define a line segment for line n by translating line m an increment (d

r

,d

z

).

Translate line n by the increment (d

r

,d

z

).

Define a line segment tangent to a circular arc centered at point (r

1

,z

1

), beginning at the last point defined, and sweeping counterclockwise if rot=1 and clockwise if rot =-1. The line segment terminates at its tangency point on a second arc of radius R centered at (r

2

,z

2

). The first tangency point encountered as the second arc is generated by a counterclockwise rotation from the r-axis will become the end point. If R is given as a negative number; a clockwise rotation from the r-axis will determine the tangency point.

Define a line segment for line n with tab cell data. Tab cell data is often used in drafting programs, and consist of m radii each dt degrees apart starting at angle t. Each radius is scaled by s. Positive angles represent counterclockwise rotations.

Define a line segment for line n by offsetting last line defined with the "LTBC" or "LTBO" command. The radii of the first m

1

points are offset d

1

, the next m

2

by d

2

, and so on. Note that m=m

1

+ m

2

+ ... m

m

where m comes from the last "LTBC" command.

Define a circular arc of radius R tangent to the last line segment and terminating at point (r,z).

The last line segment will be automatically extended or truncated to the tangency point.

Define a line segment vector of length l,

14.3

TWO-DIMENSIONAL LINE DEFINITIONS

or

LVC r

LVC r

1

2

z z

1

2

t l

t -l

LS-INGRID

oriented at t degrees (positive counterclockwise from the

r-axis). If this is the first command in a new line, the origin (r,z) must be given

(second or third forms). A negative l indicates that the second point is defined, i.e., that the vector points towards the first point.

RLN

Read next line definition in operational input file and assign the next available line number.

RLNS

Read all line definitions in operational input file and assign the next available line numbers.

14.4

LS-INGRID THREE-DIMENSIONAL LINE DEFINITIONS

15. Three-Dimensional Line Definitions

Three-dimensional line definitions are lists of x,y,z points which form a piecewise linear curve. Each line definition has a name which is a character string with up to eight characters.

AVGN l

1

l

2

...l

n ;

BLEN s

1

s

2

s

3

s

4

s

5

p

COMP l

1

l

2

...l

n

;

COPY n data

L2D n data

L3D n

LAD x

c

y c

a

LADD l

1

s

1

l

2

s

2

LBCX l r f

LBCY l r f

LBCZ l r f

Average n line definitions.

Determine a line interpolated between surface definition s

1

and s

2

by a ratio p. s

3

and s

4 determine the end points of the line and the line lies on s

5

. Convergence can be improved by using the following: PO for (s

1

,s

3

,s

5

), P1 for

(s

1

,s

4

,s

5

), P2 for (s

2

,s

4

,s

5

), P3 for (s

2

,s

3

,s

5

).

Refer to Figure 14-1.

Form a single line definition by placing line definitions l

1

l

2

... l

n

end-to-end.

Move line definition n using the transformation defined by data. Input for data is described in the section on Coordinate Transformations.

Turn two-dimensional line definition n into a three dimensional line definition. The line definition is initially assumed to lie in the x-y plane and can be moved anywhere in space using data which is described in Coordinate

Transformations.

Begin line definition n.

Form an arc about a z-vector located at (x

c

,y c

) beginning at the last point defined and sweeping through a degrees.

Make a linear combination: l

new

=l

1

*s

1

+l

2

*s

2

.

Ball-correct line definition l with a cylinder parallel to the x-axis with radius r. If the correction is to the left then f is 'left', otherwise f is 'right'.

Ball-correct line definition l with a cylinder parallel to the y-axis with radius r. If the correction is to the left then f is 'left', otherwise f is 'right'.

Ball-correct line definition l with a cylinder

15.1

THREE-DIMENSIONAL LINE DEFINITIONS LS-INGRID

parallel to the z-axis with radius r. If the correction is to the left then f is 'left', otherwise f is 'right'.

LBCV l r v

x

v y

v z

Ball-correct line definition l with a cylinder parallel to the vector, (v

x

,v y

,v z

), with radius r. If the correction is to the left then f is 'left', otherwise

f is 'right'.

LCUT l opt dist

LEXP x(s) y(s) z(s) n

LFOR l opt vd sd dir

LINT

l

1

l

2

s

Cut line definition l with a plane normal to axis opt (opt = X, Y or Z) at a distance of dist from the origin. The results are stored into calculator variables (l3cenx, l3ceny, l3cenz). They may then be accessed and used as necessary.

Define a line definition using expression x(s),

y(s) and z(s) where 0 <s< 1. The number of points to be used is n.

Form line definition l. If a point on l is inside

(opt=IN) or outside (opt=OUT) of surface definition vd, then it is projected onto surface definition sd. The projection is constrained by dir: dir=0: project to nearest point.

dir=1: project along X-axis dir=2: project along Y-axis dir=3: project along Z-axis

Form a line by linear interpolation between l

1 and l

2

with parameter s.

LLCM l

1

s

1

... l

n

s n

; Form a linear combination of n lines where lnew(r)=l

1

(r)*s

1

+ ... +l

n

(r)*s

n

.

The line definition consists of n points.

LP n x

1

y

1

z

1

... x

n

y n

z n

LPN n p

x

p y

p z

LPRJ l s

LREV

LRNX l r

The next point on the line definition is at

(p

x

,p y

,p z

) but n equal spaced points in a straight line are added to make up this segment.

Project line definition l onto surface definition s.

Reverse the direction of the line. Additions to the line definition will occur at the beginning of the line rather than the end of the line.

Sharp corners on line definitions l are rounded by a cylinder parallel to the x-axis with radius r. The coordinates of the center of rotation of the last round are returned to calculator variables

(l3cenx,l3ceny,l3cenz) and the last angle of sweep

15.2

LS-INGRID

LRNY l r

LRNZ l r

LRNV l r v

x

v y

v z

LROT p

x

p y

p z

v

x

v y

v z

w

LVT d

LVTB d

P0 x

0

y

0

z

0

P1 x

1

y

1

z

1

P2 x

2

y

2

z

2

P3 x

3

y

3

z

3

PINT s

1

s

2

s

3

PPRJ p

x

p y

p z

surf

THREE-DIMENSIONAL LINE DEFINITIONS

is returned to l3angle.

Sharp corners on line definitions l are rounded by a cylinder parallel to the y-axis with radius r.

The coordinates of the center of rotation of the last round are returned to calculator variables

(l3cenx,l3ceny,l3cenz) and the last angle of sweep is returned to l3angle.

Sharp corners on line definitions l are rounded by a cylinder parallel to the z-axis with radius r.

The coordinates of the center of rotation of the last round are returned to calculator variables

(l3cenx,l3ceny,l3cenz) and the last angle of sweep is returned to l3angle.

Sharp corners on line definition l are rounded by a cylinder parallel to the vector, (v

x

,v y

,v z

), with radius r. The coordinates of the center of rotation of the last round are returned to calculator variables (l3cenx,l3ceny,l3cenz) and the last angle of sweep is returned to l3angle.

Form an arc by taking the last point and rotating it an angle w (in degrees) about the axis defined by point (p

x

,p y

,p z

) and orientation vector

(v

x

,v y

,v z

).

Add a vector tangent to the last line segment with length d.

Add a vector tangent to the first line segment with length d.

Set point P0 for intersection.

Set point P1 for intersection determination on the next command.

Set point P2 for intersection determination on the next command.

Set point P3 for intersection determination on the next command.

The next point on the line is at the intersection of s

1

, s

2

and s

3

. P0 can be used to improve convergence. The results of the projection are returned to the calculator variables

(l3cenx,l3ceny,l3cenz).

The next point on the line definition is formed

15.3

THREE-DIMENSIONAL LINE DEFINITIONS LS-INGRID

by projecting (p

x

,p y

,p z

) to the nearest point on surface surf.

SINT s

1

s

2

s

3

s

4

Determine the curve formed by the intersection of s

1

and s

2

beginning at s

3

and terminating at

s

4

. If this is not the first point on the line, then

s

3

is not input and LS-INGRID assumes that the last point defined lies on the intersection of

s

1

and s

2

. The convergence can be improved by using P0 for (s

1

,s

2

,s

3

) and P1 for (s

2

,s

3

,s

4

).

15.4

LS-INGRID

16. Surface Definitions

SURFACE DEFINITIONS

This section describes options for defining three-dimensional curved surfaces.

Analytical representations of the surfaces are stored, if possible, so that exact projections can be made.

BLND d

1

l

1

d

2

l

2

CN2P

p

CONE

CR

p

CRX, CRY, or CRZ

l

CYLI p

x

p y

p z

v x

v y

v z

r

ER

p p x

p y

p z

v x

v y

v

CP data l

z

r

1

z

1

r

2

z

2

x

p y

p z

v x

v y

v z

r

θ

x

p y

p z

v x

v y

v z

l

x

p y

p z

v x

v y

v z

r

1

r

2

The surface is blended between line definition l

1 and line definition l

2

. Initially the line definitions are in the x-z plane at y=0. Line definitions are moved by d

1

and d

2

which are described in

Coordinate Transformations.

Define a conical surface by specifying the axis and two points. (p

x

,p y

,p z

) is a point on the axis and (v

x

,v y

,v z

) is a vector which orients the axis.

radial and axial positions relative to the center point are (r

1

,z

1

) and (r

2

,z

2

).

Define a conical surface by specifying an axis, a radius and an angle. (p

x

,p y

,p z

) is a point on the axis where the cone has radius r and (v

x

,v y

,v z

) is a vector along the axis. The angle of the cone relative to the positive axis is

θ

.

Form an infinite surface from line definition l.

Initially the r-coordinate of the line definition is the x-coordinate of the part and the z-coordinate of the line definition is the y-coordinate of the part. The surface is the same curve in any x-y plane along the part's z-axis. Coordinate

Transformations describes data which can be used to move the surface anywhere in space.

Spin two-dimensional line definition, l, about an axis to form a line. (p

x

,p y

,p z

) is the center point on the axis and (v

x

,v y

,v z

) is a vector which orients the axis.

Spin two-dimensional line definition, l, about the X, Y, or Z axes, respectively.

Define a cylindrical surface with a point on the axis at (p

x

,p

y

,p

z

), an orientation vector (v

x

,v

y

,v

z

), and radius r.

Define an elliptical surface revolved about an

16.1

GS n

GS1 n

GS2 n

GSM data n

GSN offset n

L3 l

L3P l v

x

v y

v z

L3R l r

L3S p

x

p y

p z

v x

v y

v z

l

NCV data n

NSF data n

SURFACE DEFINITIONS

GELN a b c n data

GELS a b c data

LS-INGRID

axis. (p

x

,p y

,p z

) is the center point, (v

x

,v y

,v z

) is a vector which orients the ellipse. The radius in the plane normal to the axis of rotation is r

1

and the intercept along the axis of rotation is at +/-

r

2

.

Define a general ellipsoid with the equation:

(x/a)

n

+(y/b)

n

+(z/c)

n

=1

The ellipsoid can be positioned anywhere in space with data which is described in the section on Coordinate Transformations.

Define an ellipsoid with the equation:

(x/a)

2

+(y/b)

2

+(z/c)

2

=1

The ellipsoid can be positioned anywhere in space with data which is described in the section on Coordinate Transformations.

Use general 3-D digitized surface number n.

Use lower side of general 3-D surface.

Use upper side of general 3-D surface.

Digitized surface n is moved by data which is described in Coordinate Transformations.

Use digitized surface n but offset the surface by offset in the normal direction.

The surface is actually just three-dimensional line definition l.

Three-dimensional line definition l is projected along (v

x

,v y

,v z

) to form a surface.

The surface is a circular tube of radius r about three-dimensional line definition l.

Spin three-dimensional line definition l about the axis defined by point (p

x

,p y

,p z

) and orientation vector (v

x

,v y

,v z

).

NURB curve defined by entity number n in the

NURB geometry database is used. This curve is moved by data which is described in Coordinate

Transformations.

NURB surface defined by entity number n in the

NURB geometry database is used. This surface

16.2

LS-INGRID

NSFN data n

PL3 f1 p1x p1y p1z

PLAN

p x

p y

p z v x

v y

v z

POLY

p x

p y

pz v x

v y

v z n a

0

a

1

... a

n

PR p

x

p y

p z

v x

v y

v z

r

1

t

1

r

2

t

2

r

3

t

3

SP p

x

p

T1 l

1

l

2 f2 p2x p2y p2z f3 p3x p3y p3z offset

y

T2 n opt

p z

r

l

3

l

4

l

5

SURFACE DEFINITIONS

is moved by data which is described in

Coordinate Transformations.

NURB surface defined by entity name n in the

SC03 geometry database is used. This surface is moved by data which is described in

Coordinate Transformations.

Plane Defined by three points. f1, f2 and f3 specify the coordinate system which is

RT for rectangular, CY for cylindrical, or SP for spherical. P1, P2, and P3 must be three noncollinear points in the plane. f2 and f3 can also be V to indicate that the input points are vectors relative to P1. The surface definition is offset from the three points by the distance offset.

Define a plane. (p

x

,p y

,p z

) is any point on the plane and (v

x

,v y

,v z

) is a normal vector.

Define a surface as a planar polynomial which is then spun about an axis. (p

x

,p y

,p z

) is a point on the axis of rotation and (v

x

,v y

,v z

) is a vector which orients the axis of rotation. The polynomial is of degree n with coefficients a

0

,

a

1

, ... a

n

.

Parabolic surface of revolution. (p

x

,p y

,p z

) is a point on the axis of revolution and (v

x

,v y

,v z

) is a vector orienting the axis of revolution. (r

1

,t

1

),

(r

2

,t

2

) and (r

3

,t

3

) are radial and axial positions of three points which are fit with a parabola.

Define a sphere with center (p

x

,p y

,p z

) and radius

r.

This is a special purpose surface. l

1

, l

2

, l

3

, l

4 and l

5

refer to two-dimensional line definitions.

The surface is axisymmetric about the Z-axis and performs Z-projections only. The equation for the surface is as follows:

z = l

3

(r)+(l

2

(r)-l1(r))*(1+

l4

(q)*l

5

(r))+l

1

(r)

Project along an axis onto digitized surface definition n. Values for opt are as follows:

=MINX: project along the X-axis to the minimum X- intercept.

=MAXX: project along the X-axis to the maximum X- intercept.

=MINY: project along the Y-axis to the minimum Y- intercept.

16.3

SURFACE DEFINITIONS

TS

p x p y

p z

q x q y

q z

r

1

t

1

r

2

TS2P

p x p y

p z v x v y

v z r

1

z

1

r

2

z

2

r

3

LS-INGRID

=MAXY: project along the Y-axis to the maximum Y- intercept.

=MINZ: project along the Z-axis to the minimum Z- intercept.

=MAXZ: project along the Z-axis to the maximum Z- intercept.

Define a torus. (p

x

,p y

,p z

) is a point on the primary axis of rotation and (v

x

,v y

,v z

) is a vector which orients this axis. r

1

is the radius to the secondary axis, t

1

is an axial offset relative to

(p

x

,p y

,p z

) and r

2

is the radius from the secondary axis to the torus surface.

Define a torus with two points on the surface.

(p

x

,p y

,p z

) is a point on the primary axis of rotation and (v

x

,v y

,v z

) is a vector which orients this axis. r

3

is the radius of the surface from the secondary axis. If r

3

> 0 then the secondary axis lies to the left as one moves from (r

1

, z

1

) to

(r

2

, z

2

). Otherwise, the axis is to the right.

16.4

LS-INGRID

17. Volume Definitions

VOLUME DEFINITIONS

This section documents the available solid geometric objects. Solid objects are used by the "VD" command in the control section. The following types are available.

CR

p x p y p z v x

CYF

p x p y p z v

CYLI

DS n

SPHE

p p x x

p

p y y

p

p z v y v x v y

v

z r

x

v

z v z r t

min

t max

y l

v

z

r

RECT n x min

x max

y min

y max

z min

z max

SD n t

TRIA n x

1

y

1

x

2

y

2

x

3

y

3

z min

z max

Form a solid by spinning two-dimensional line definition l about the axis defined by point

(p

x

,p y

,p z

) and orientation vector (v

x

,v y

,v z

).

Define a cylinder of radius r and axis defined by point (p

x

,p y

,p z

) and orientation vector (v

x

,v y

,v z

).

The cylinder extends along the axis from t min

to

t

max

.

Define a cylinder of radius r and axis defined by point (p

x

,p y

,p z

) and orientation vector (v

x

,v y

,v z

).

The cylinder has infinite length.

Digitized surface n is a closed surface which defines a volume.

Define a rectangular solid with x min

<x<x max

,

y

min

<y<y max

and z min

<z<z max

. This can be positioned anywhere in space using global coordinate transformation number n.

The surface is defined by surface definition n and thickness t.

Define a sphere of radius r and centered at

(p

x

,p y

,p z

).

The solid is a triangular section in the X-Y plane which runs from z min

to z max

in the Z-direction.

(x

1

,y

1

), (x

2

,y

2

), and (x

3

,y

3

) are the three corner points. This can be moved anywhere in space using global coordinate transformation n.

17.1

VOLUME DEFINITIONS LS-INGRID

17.2

LS-INGRID

18. Coordinate Transformations

COORDINATE TRANSFORMATIONS

Option 1:

For Option 1, three nodal points must be input. Figure 18-1 shows the orientation of the local coordinate system defined by the three points.

f

1

Flag describing coordinate type for point 1

="RT": rectangular coordinates

="CY": cylindrical coordinates (R,

θ

, Z).

="SP": spherical coordinates (R,

θ

,

ψ

)

Coordinates for point 1.

p

1x

p

1y

p

1z

f

2

Flag describing coordinate type for point 2.

="RT": rectangular coordinates

="CY": cylindrical coordinates (R,

θ

, Z).

="SP": spherical coordinates (R,

θ

,

ψ

)

="V": point 2 is offset from point 1 by the vector.

p

2x

p

2y

p

2z

f

3

Coordinates or vector for point 2

p

3x

p

3y

p

3z

Flag describing coordinate type for point 3.

="RT": rectangular coordinates

="CY": cylindrical coordinates (R,

θ

, Z).

="SP": spherical coordinates (R,

θ

,

ψ

)

="V": point 3 is offset from point 1 by the vector.

Coordinates or vector for point 3.

18.1

COORDINATE TRANSFORMATIONS

Z

Z

′

P

1

P

2

P

3

X

′

Y

′

Local axes

LS-INGRID

Y

Global axes

Figure 18-1. Coordinate Transformations.

X

′

18.2

LS-INGRID COORDINATE TRANSFORMATIONS

Option 2:

Option 2 allows the following commands in any order.

;

CSCA s

D1

Scale coordinates by s.

Save the current offset position and perform rotations relative to this point.

D2

L

Restore the offset position.

Copy the previous transformation and begin defining the next system.

MATRIX a

11

a

21

a

31

a

12

a

22

a

23

a

31

a

32

a

33

MX

∆

x

MY

∆

y

MZ

∆

z

REPE n

RX

θ

RY

θ

RZ

θ

RXY

Set the transformation to the input 3«3 matrix.

Move

∆

x in the x-direction.

Move

∆

y in the y-direction.

Move

∆

z in the z-direction.

Repeat the current transformation n times.

Rotate

θ

degrees about the X-axis.

Rotate

θ

degrees about the Y-axis.

Rotate

θ

degrees about the Z-axis.

Reflect about the XY plane.

RYZ

RZX

SAVE n

SCALE s

V

∆

x

∆

y

XSCA s

YSCA s

ZSCA s

∆

z

Reflect about the YZ plane.

Reflect about the ZX plane.

The sequence of coordinate transformations is generated starting from coordinate system n when using the "REPE" command.

Scale coordinates by s.

Move

∆

x,

∆

y, and

∆

z.

Scale X-coordinates.

Scale Y-coordinates.

Scale Z-coordinates.

Terminate Option 2.

18.3

COORDINATE TRANSFORMATIONS LS-INGRID

18.4

LS-INGRID LS-DYNA2D COMMANDS AND MATERIALS

19. LS-DYNA2D Commands and Materials

Analysis options are code dependent. They can be set either in the control section of the LS-INGRID input file or in the graphics phase. These commands become active when

LS-DYNA2D output is selected with the DN2D command (see Control Commands).

BRODE

Options:

YLD

HEIGHT

XBO

yld

h x

Define Brode function parameters.

Yield (Ktons)

Height of burst

Coordinates of Brode origin (space, time) in

LS-INGRID units.

;

YBO

ZBO

TBO

CL

CT

CP

t y z cl ct cp

Conversion factor - ft. to DYNA length units

(default = meters).

Conversion factor - ms to DYNA time units

(default - seconds).

Conversion factor - psi to DYNA pressure units

(default = Pascals).

Terminate Brode function input.

Note: If "RANG" "COEF", and "GFUN" are specified, a "modified" Brode function will be used in DYNA; otherwise, straight Brode is used.

RANG

COEF

GFUN

r

1

... r

5

c

1

... c

8

g

1

... g

7

Range values for Brode function.

Coefficient values for Brode function.

GFUNC values for Brode Function.

The Brode function is applied to pressure surfaces with load curve number -1.

DBQT i Change default bulk viscosity type from 1 to i:

=1: standard LS-DYNA2D

=2: Richards-Wilkins

DHGQ Q

h

Change default hourglass viscosity from .10 to

Q h

.

DHQT i Change default hourglass viscosity type from 1 to

i:

20.1

LS-DYNA2D COMMANDS AND MATERIALS LS-INGRID

=1: standard LS-DYNA2D

=2: rotational

=3: Flanagan-Belytschko viscous form.

=4: Hancock

DQL Q

l

Change default linear bulk viscosity from .06 to

Q l

.

DQQ Q

GEOM

q

Change default quadratic bulk viscosity from 1.5 to

Q q

.

Select geometry type.

=AXIS: axisymmetric (default)

=PLAN: plane strain

Gravity acceleration vector.

GRAV

ITSS

PLTI

PRTI

RDMT m

RDSI s

t g x

g y

g z o

Dt

Dt

Initial time step size. This is optional input for

LS-DYNA3D. If t

o

is zero, LS-DYNA3D picks the initial time step size.

Node and element data dump interval for

TAURUS post-processing.

Node and element data dump interval for high speed printer.

Delete material m. This applies to the restart number selected by the RNUM command.

Delete sliding interface s. This applies to the restart number selected by the RNUM command.

REST name

REZO t

1

t

2

DtPeriodic rezones begin at time t

1

and end at time t

2

. Rezones are performed after every time interval of Dt.

RHVC h

Set the family name for restart input file generation to name.

The default hourglass viscosity for restart is set to h. This applies to the restart number selected by the RNUM command.

RLBV l

RNUM n

RPLT t

The default linear bulk viscosity for restart is set to l. This applies to the restart number selected by the RNUM command.

Restart commands apply to restart number n.

The plot interval for restart is set to t. This applies to the restart number selected by the RNUM command.

20.2

LS-INGRID

RPRT t

RQBV q

RTERM t

RTSF s

SBRF n

SFSI s

TEO i

TERM

TINV

TSSF

LS-DYNA2D COMMANDS AND MATERIALS

The print interval for restart is set to t. This applies to the restart number selected by the RNUM command.

The default quadratic bulk viscosity for restart is set to q. This applies to the restart number selected by the RNUM command.

The termination time for this restart is t. This applies to the restart number selected by the

RNUM command.

t n

The time step scale factor for restart is set to s.

This applies to the restart number selected by the RNUM command.

Number of time steps between restart dumps is n.

Sliding interface scale factor (default = 1.0).

s

Thermal effects option

=0: no thermal effects.

=N: nodal temperatures are defined in input and are scaled according to a time function.

N is the load curve number.

=-1: each time step a new temperature state is read from a disk file. The time word at the beginning of each temperature state is ignored.

=-2: each time step a temperature state is interpolated from the temperature state in a disk file. Therefore the time words at the beginning of each temperature state are used.

=-3: the disk file containing temperatures has only one state. The initial state is assumed to be zero.

Terminate dynamic time integration at time t.

Number of time steps between dumps of reaction history blocks.

Scale factor on time step size.

20.3

LS-DYNA2D COMMANDS AND MATERIALS LS-INGRID

19.1

LS-DYNA2D M

ATERIAL

I

NPUT

LS-DYNA2D material input is possible after the DN2D command is input (see Control

Commands). The form of this input is: MAT n TYPE m {options specific to material type m}

{general material options} ENDMAT. n is a material name which is assigned an input number. Therefore, the materials should be defined in order before any additional use of materials is made.

19.2 G

ENERAL

M

ATERIAL

O

PTIONS

BQL Q

l

BQQ Q

q

BQT i

EOS eost

HEAD

HGQ Q

HGQT

IMGL

MAT m

RO m

TYPE n

h

Change linear bulk viscosity for .06 to Q

l

.

Change quadratic bulk viscosity from 1.5 to Q

q

.

Change bulk viscosity type from 1 to i:

=1: standard LS-DYNA2D

=2: Richards-Wilkins

Begin defining equation-of-state type eost for the current material definition. Each equationof-state is terminated by the ENDEOS command.

Replace default heading (typed on the next line).

Change value of hourglass viscosity from .10 to

Q h

.

Change value of hourglass viscosity type from 1 to i:

=1: standard LS-DYNA2D

=2: rotational

=3: Flanagan-Belytschko viscous form

=4: Hancock

Initialize material for gravity loads.

Begin material definition m. Each material definition is terminated by the ENDMAT command.

Density (required - no default).

The current material is of type n.

20.4

LS-INGRID

Material Type 1 (Elastic)

LS-DYNA2D COMMANDS AND MATERIALS

Default heading: Material Type #1 (Elastic)

Input any two of the following.

BULK K

E E

G G

PR

ν

Bulk modulus

Young's modulus

Shear modulus

Poisson's ratio

20.5

LS-DYNA2D COMMANDS AND MATERIALS

Material Type 2 (Orthotropic Elastic)

LS-INGRID

EA E

a

EB E

b

EC E

c

PRBA

υ ba

PRCA

υ

χ a

PRCB

υ cb

GAB G

ab

AOPT aopt

See constitutive matrix below

Material axes option (Figure 19-1).

=0.0: locally orthotropic with materials axes by j value specified on each element card and element nodes n

1

and n

2

. (see Figure

19-1).

=1.0: locally orthotropic with materials axes by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by j

G

.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

RP r

p

ZP z

p

PSIG j

G

The material law that relates stresses to strains is defined as:

C

~

=

T

~

T

C

L

~

T

~

,

Where \o(T,

~

) is a transformation matrix and\o(C,

~

)L is the constitutive matrix defined in terms of the material constants of the orthogonal material axes, a, b, and c. The inverse of

\o(C,

~

)L is defined as

C

−

1

~ L

=





















1

−

E a v ab

−

E a v ac

E a

0

0

0

− v ba

E b

1

−

E v b bc

E b

0

0

− v ca

−

E c v cb

E c

1

E c

0

0

0

0

0

1

G ab

0

0 0 0

0

0

0

0

1

G bc

0

0

0

0

0

0

1

G ca





















20.6

LS-INGRID LS-DYNA2D COMMANDS AND MATERIALS

Note that v ab

E a

= v ba

,

E b v ca

=

E c v ac

,

E a v cb

=

E c v bc

.

E b

20.7

LS-DYNA2D COMMANDS AND MATERIALS LS-INGRID c

(a)

b

n

4 n

1 n

2

AOPT=0.0 default

a a d c

(c)

b

n

3

a

AOPT=2.0 define a and d

d d

(b)

b c

z

v

(d)

v x n

y

x p

, y

p

, z

p

x

AOPT=1.0 d is parallel to the z-axis

n

shell element

AOPT=3.0

Figure 19-1.

Options for determining principal materials axes: (a) AOPT = 0.0, (b) AOPT

= 1.0, and (c) AOPT = 2.0.

20.8

LS-INGRID LS-DYNA2D COMMANDS AND MATERIALS

Material Type 3 (Kinematic/Isotropic Elastic/Plastic)

Default heading: Material Type #3 (Elastic-Plastic)

Input any two of the following:

BULK K

E

E

G G

PR

ν

Bulk modulus

Young's modulus

Shear modulus

Poisson's ratio

Additional Options:

SIGY

σ

y

ETAN E

t

BETA

β

'

Yield stress

Hardening modulus

Hardening parameter, 0 <

β

' < 1

Isotropic, kinematic, or a combination of isotropic and kinematic hardening may be specified by varying

β

' between 0 and 1. For

β

' equal to 0 and 1, respectively kinematic and isotropic hardening are obtained as shown in Figure 19-2. Effective stress is defined in terms of the deviatoric stress tensor, sij as:

σ =





3

2

S ij

S ij





1

2 where,

S ij

= σ ij

−

1

3

σ kk

δ ij and effective plastic strain by:

ε p

∫ t

= d

ε

0 p where t denotes time and d

ε p

=





2

3 d

ε ij p d

ε ij p



1

2

20.9

LS-DYNA2D COMMANDS AND MATERIALS LS-INGRID

yield stress

E

E t

l n

( )

0

β=0 kinematic hardening

β=

1 isotropic hardening

Figure 19-2.

Elastic-plastic behavior with isotropic and kinematic hardening where l

0

and l are undeformed and deformed length of uniaxial tension specimen.

20.10

LS-INGRID

Material Type 4 (Thermo-Elastic-Plastic)

LS-DYNA2D COMMANDS AND MATERIALS

Default heading: Material Type 4 (Thermo-Elastic-Plastic)

NPTS n

TEMP T

1

T

2

...T

n

E E

1

E

2

...E

n

PR

υ

1

υ

2

...

υ

n

ALPHA

α

1

SIGY

σ

y1

σ

α

y2

2

...

α

n

...

σ

yn

ETAN E

t1

E

t2

...E

tn

Number of temperature values for which material constants are defined.

Temperatures

Young's moduli

Poisson's ratios

Coefficients of thermal expansion.

Yield stresses

Tangent moduli

Material Type 5 (Soil and Crushable Foam)

Default heading: Material Type 5 (Soil and Crushable Foam)

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

AO a

0

A1 a

1

A2 a

2

PC P

c

NPTS n

VS

ε

v1

ε

v2

...

ε

vn

P p

1

p

2

...p

n

Bulk modulus

Young's modulus

Shear modulus

Poisson's ratio

Yield function constant.

Yield function constant.

Yield function constant.

Pressure cutoff for tensile fracture.

Number of points in volumetric strain versus pressure curve (n£10).

Volumetric strain values.

Pressures corresponding to volumetric strain values.

The deviatoric yield function,

φ

, is described in terms of the second invariant J

2

.

J

2

=

1

2 s ij s ij

20.11

LS-DYNA2D COMMANDS AND MATERIALS LS-INGRID

Pressure,

p, and constants a

0

, a

1

, and a

2

as:

φ =

J

2

−

[ a

0

+ a

1 p

+ a

2 p

2

]

.

On the yield surface, J

2

=1/3(

σ y

)

1/2

, where

σ y

is the yield stress, i.e.,

σ y

=

[

(

0

+ a

1 p

+ a

2 p

2

)

]

1

2

For elastic-perfectly plastic behavior a

1

=a

2

=0, and (3a

0

)

1/2

defines the yield strength.

The volumetric strain is given by the natural logarithm of the relative volume V. If the pressure drops below the cutoff value, PC, then it is reset to that value.

pressure

Loading and unloading follows the input curve if the volumetric crushing option is off (Card 3, col. 61-70) hysteretic behavior for option 2

The bulk unloading modulus is used if the volumetric crushing option is on

(Card 3, col. 61-70) tension cutoff

Volumetric strain

Figure 19-3. Volumetric strain versus pressure curve for soil and crushable foam model.

20.12

LS-INGRID

Material Type 6 (Viscoelastic)

G G

0

GI G

´

K K

BETA

β

LS-DYNA2D COMMANDS AND MATERIALS

Short term shear modulus.

Long term shear modulus.

Bulk modulus.

Decay constant.

The shear relaxation behavior is described by:

G(t) = G + (G

0

– G ) e

-

β t

A Jaumann rate formulation is used:

σ

∇

′ ij

=

2

∫ t

0

(

− τ

)

D ij

′

( ) dt where the prime denotes the deviatoric part of the stress rate,

σ

ij

,

and the strain rate D

IJ

.

Material Type 7 (Blatz-Ko Rubber)

Default heading: Material Type #7 (Rubber)

G m Shear modulus

The second Piola-Kirchhoff stress is computed as

S ij

= µ





1

V

C ij

−

V

−

1

1

−

2

υ

δ ij



 where

V is the relative volume, C

ij is the right Cauchy-Green strain tensor, and

ν

is the

Poisson's ratio which is set to .463 internally. This stress measure is transformed to the

Cauchy stress,

σ

ij

, according to the relationship

σ ij

= V

-1

F ik

F jl

S lk where

F ij

is the deformation gradient tensor.

Material Type 8 (High Explosive Burn)

20.13

LS-DYNA2D COMMANDS AND MATERIALS

Default heading: Material Type #8 (High Explosive Burn)

D D

PCJ P

CJ

Detonation velocity.

Chapman-Jouget pressure.

This material model requires an equation-of-state.

LS-INGRID

Material Type 9 (Null Material)

Default heading: Material Type #9 (Null Material)

PC pc

MU

µ

Pressure cutoff.

Viscosity.

The null material must be used with an equation-of-state. Pressure cutoff is negative in tension. A viscous stress of the form

σ ij

= µ ε

Ý

′ ij is computed for nonzero

µ

where

ε

Ý

′ ij is the deviatoric strain rate.

Material Type 10 (Isotropic-Elastic-Plastic-Hydrodynamic)

Default heading: Material Type #10 (Isotropic-Elastic-Plastic-Hydrodynamic)

G G

SIGY

σ

y

EH E

h

PC p

c

or -s

f

A1 a

1

A2 a

2

NPTS n

ES

σ

y1

σ

EPS

ε

p1

y2

ε

p2

...

σ

yn

...

ε

pn

P p

1

p

2

...p

n

FS s

Shear modulus

Yield strength

Plastic hardening modulus

Pressure cutoff

= 0: cutoff of -´ is assumed

Yield function constant

Yield function constant

Number of points in yield stress-effective plastic strain curve or yield stress-pressure curve.

Yield stress

Effective plastic strain

Pressure

Failure strain

20.14

LS-INGRID LS-DYNA2D COMMANDS AND MATERIALS

If the yield stress-plastic strain curve is not defined and if a1 = a2 = 0, the bilinear stress-strain curve shown in Figure 19-2 is obtained with b =1. The yield strength is calculated as

σ y

= σ

0

+

E h

ε p

The quantity Eh is the plastic hardening modulus defined in terms of Young’s modulus, E, and the tangent modulus, Et , as follows

E h

=

E t

E

E

−

E t

If Cards 5-8 are used, a curve like that shown in Figure 3.4 may be defined. Effective stress is defined in terms of the deviatoric stress tensor, sij, as:

σ =





3

2 s ij s ij

1

2

(1) and effective plastic strain by:

ε p

=

∫

0 t





2

3

D ij p

D ij p



1

2 dt,

(2) where t denotes time and

D ij p

is the plastic component of the rate of deformation tensor. In this case the plastic hardening modulus on Card 3 is ignored and the yield stress is given as

σ y

= f

( )

, where the value for f

( )

is found by interpolation from the data curve.

20.15

LS-DYNA2D COMMANDS AND MATERIALS

σ

y

LS-INGRID

Piecewise linear curve defining the yield stress versus effective plastic strain. A nonzero yield stress is defined when the plastic strain is zero.

0

e p

Figure 19-4. Effective stress versus effective plastic strain curve.

Material Type 11 (Temperature Dependent Elastic-Plastic Hydrodynamic)

Default heading: Material Type #11 (Temperature Dependent Elastic-Plastic Hydrodynamic)

G G

0

SIGO

σ

o

BETA

β

N n

GAMA g

i

SIGM

σ

m

B b

BP b'

H h

F f

A A

TO T

mo

GAMO

γ

0

SA a

Shear modulus.

See equations below.

20.16

LS-INGRID

PC pmin or -s

f

ECO EC

0

EC1 EC

1

EC2 EC

2

EC3 EC

3

EC4 EC

4

EC5 EC

5

EC6 EC

6

EC7 EC

7

EC8 EC

8

EC9 EC

9

LS-DYNA2D COMMANDS AND MATERIALS

Cold compression energy coefficients (optional)

If cold compression energy coefficients are not input, then LS-DYNA2D will calculate them based on the equation-of-state.

SPALL type Spall type

=0: default set to "2.0"

=1: p 3 p min

=2: if

σ max

>

σ

f

element spalls and tension

p < 0, is never allowed;

σ max

= maximum principal stress.

=3: if p < p min

element spalls and tension

p<0, is never allowed.

=4: failure strain

Users who have an interest in this mode are encouraged to study the paper by

Steinberg and Guinan [9] which provides the theoretical basis. Another useful reference is the KOVEC user's manual [10].

In terms of the foregoing input parameters, we define the shear modulus, G, before the material melts as:

G

=

G

0





1

+ bpV

1

3

− h



E i

−

E c

3

R

′

−

300







 e

− fE i

E m

−

E i where

p is the pressure, V is the relative volume, E

c

is the cold compression energy:

ε p

=

∫ t

0





2

3

D ij p

D ij p



1

2 dt,

x = 1 - V and E

m

is the melting energy:

E m

(x) = E c

(x) + 3R

′

T m

(x)

20.17

LS-DYNA2D COMMANDS AND MATERIALS

which is in terms of the melting temperature

T m

(x):

T m

( )

=

T

V mo

( )

2

(

γ o

− a

− 1

3

) and the melting temperature at

r = r

0

, T

mo

.

In the above equation, R' is defined by

R

′ =

R

ρ

A

LS-INGRID

where

R is the gas constant and A is the atomic weight. If R' is not defined, LS-DYNA2D computes it with R in the cm-gram-microsecond system of units.

The yield strength

σ

y

is given by:

σ y

σ

0





1

+ ′

1

3

− h



E i

−

3

R

′

E c

−

300







 e

− fEi

E m

−

Ei if

E m

exceeds E

i

. Here,

σ

0

' is given by:

σ y

σ

0

[

1

( i

+ ε

− p

)

] n where

ε

i

is the initial plastic strain. Whenever

σ

0

' exceeds

σ

m

,

σ

0

' is set equal to

σ

m

. After the material melts,

σ

y

and G are set to zero.

If the coefficients ECO,...EC9 are not defined above, LS-DYNA2D will fit the cold compression energy to the ten term polynomial expansion:

E c

=

9

∑ i

=

0

EC i

η i where

EC i

is the ith coefficient and

η

=

ρ

/

ρ

0

-1. The least square method is used to perform the fit.

Material Type 12 (Johnson/Cook Plasticity Model)

G G

A A

B B

N n

R r

Shear modulus.

See equation (1).

See equation (1).

See equation (1).

See equation (1).

20.18

LS-INGRID

M m

TM T

melt

TO To

EPSO Eo

HCP c

PC pc

D1 d

1

D2 d

2

D3 d

3

D4 d

4

D5 d

5

IT i

LS-DYNA2D COMMANDS AND MATERIALS

See equation (1).

Melt temperature

Room temperature.

Effective plastic strain rate.

Specific heat.

Pressure cutoff (pc < 0.0).

See equation (2).

See equation (2).

See equation (2).

See equation (2).

See equation (2).

Iteration options:

=0: no iterations.

=1: LS-DYNA2D iterates to determine a more accurate point on the stress-strain curve.

The Johnson/Cook model is described in reference [11]. This includes strain rate hardening, thermal softening, and a complex damage model. The equations describing the flow stress versus effective plastic strain and failure strain are as follows:

σ y

=





A

+

B

ε p n





(

1

+ c ln Ý

) (

1

−

T

∗ m

) where

A, B, C, n, and m are input constants,

ε p

effective plastic strain

Ý p

Ý

0

effective plastic strain rate for Ý

0

=

1 s

−

1

T*=T

r

/T m

=homologous temperature

Constants for a variety of materials are also provided in [11].

Due to the nonlinearity in the dependence of flow stress on plastic strain, an accurate value of the flow stress requires iteration for the increment in plastic strain. However, by using a Taylor series expansion with linearization about the current time, we can solve for

σ

y

with sufficient accuracy to avoid iteration.

The strain at fracture is given by

ε f

=

[

D

1

+

D

2 exp D

3

σ

∗

] [

1

+

D

4

ε

∗

] [

1

+

D

5

T

∗

] where

σ

* is the ratio of pressure divided by effective stress:

20.19

LS-DYNA2D COMMANDS AND MATERIALS

σ

∗

= p

σ eff

Fracture occurs when the damage parameter

D

=

∑ ∆ε p

ε f reaches the value of 1.

LS-INGRID

Material Type 13 (Power Law Plasticity)

Input any two of the following:

BULK K

E

E

G G

PR

ν

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Additional Options:

K k

M m

See equation below.

See equation below.

stress,

σ

Elastoplastic behavior with isotropic hardening is provided by this model. The yield y, is a function of plastic strain and obeys the equation:

σ y

= k

ε

( e

+ ε p

) n

ε e is the elastic strain to yield and where

ε p

is the effective plastic strain. ***missing***

.***missing***

Material Type 16 (Pseudo Tensor Geological Model)

Default heading: Material Type #16 (Pseudo Tensor Geological Model)

G G Shear modulus (constant Shear modulus model).

20.20

LS-INGRID

PR

ν

SIGF sigf

A0 a

0

A1 a

1

A2 a

2

A0F a

0f

A1F a

1f

B1 b

1

PER p

ER E

r

PR

ν

r

SIGY

σ

y

ETAN E

t

LCP lc

1

LCR lc

2

NPTS n

ES

σ

1

σ

2

...

σ

n

EPS

ε

p1

ε

p2

...

ε

p3

P p

1

p

2

... p

n

LS-DYNA2D COMMANDS AND MATERIALS

Poisson's ratio (constant Poisson's ratio model).

Tensile cutoff. (Maximum principal stress for failure.)

Cohesion.

Yield function constant.

Yield function constant.

Cohesion for failed material.

Pressure hardening coefficient for failed material.

Damage scaling factor.

Percent reinforcement.

Elastic modulus for reinforcement.

Poisson's ratio for reinforcement.

Initial yield strength.

Tangent modulus.

Load curve giving rate sensitivity for principal material.

Load curve giving rate sensitivity for reinforcement.

Number of points in yield stress-effective plastic strain curve or yield stress-pressure curve;

(n£16).

Yield stress.

Effective plastic strain.

Pressure.

See the LS-DYNA2D manual for a description of this model.

Material Type 25 (Inviscid Two Invariant Geologic Cap Model)

G G

K K

ALPHA

α

BETA

β

GAMMA

γ

THETA

θ

Shear Modulus.

Bulk Modulus.

γ

.

θ

.

α

.

β

.

20.21

LS-DYNA2D COMMANDS AND MATERIALS

R R

D D

X0 X

0

CC C

T T

NPLOT nplot

LTYPE ltype

LS-INGRID

R.

D.

X

0

.

C.

Tension cutoff.

Save the following variable for plotting in

ORION:

=1: k

=2: X

=3: e

v p

=4: J

1

=5: (J

2

)

1/2

=6: (J2|

L

)

1/2

=7: (J2|

tr

)

1/2

=8: MTYPE

=9: number of iterations

Variable ltype.

=1: soil/concrete (cap contracts)

=2: rock (cap doesn't contract)

Corner

S

S

=

F e

Failure

Singular corner region

S

=

F e

Cap

Cutoff

-T O

Elastic region

L(

κ

)

j l

X(

κ

)

Figure 19-5. The yield surface of the two-invariant cap model in pressure/J2-deviator space. f1 = 0, f2 = 0, and f3 = 0, denote the failure envelope, the hardening cap surface, and the tension cut-off surface, respectively.

The shaded area in Figure 19-5 is the “compressive corner regions”.

20.22

LS-INGRID LS-DYNA2D COMMANDS AND MATERIALS

f

1





σ

~





:

= s

~

−

F e

1 f

2





σ

~

,

κ





:

= s

~

−

F c

1,

κ f

3





σ

~





:

= −

T

−

J

1 where

J

1

:

= tr

σ

~

, s

~

:

= s

~

: s

~

, with s

~

:

= σ

~

−

1

3



 tr

σ

~





1

~

.

for

−

T

≤

J for

κ ≤

J

1 for

−

T

≤

J

1

1

< κ

<

X

( )

,

In addition, T > 0 is an material constant referred to as the tension cutoff. Note that the following standard conventions in soil mechanics, we have assumed compression and

compaction positive. Functional forms for Fe and Fc used are:

F e

( )

:

[ exp

( )

+ θ

J

1

]

F c

(

J

1

,

κ

)

:

=

F

2 e

( )

−

[

J

1

−κ

]

2

R

2

, where a > 0,

λ

> 0,

β

> 0,

θ

> 0, and R > 0 are material parameters. In addition, X(

κ

) is a function of the hardening parameter

κ defined as

X

:

= κ +

R F e

.



0





 max



 h

′

( )

 tr Ý p

; d s

F e dt

( )



 h

′

( ) tr Ý p if trÝ p

<

0 , J

1

= κ and Ý

= f

Ý

2

=

0 if J

1

= κ

, Ý

=

0, and Ý

<

0 otherwise h

( )

:

=

{

− exp

[

−

(

( )

−

X o

)

]

}

20.23

LS-DYNA2D COMMANDS AND MATERIALS LS-INGRID

20.24

LS-INGRID LS-DYNA3D COMMANDS AND MATERIALS

20. LS-DYNA3D Commands and Materials

Analysis options are code dependent. They can be set either in the control section of the LS-INGRID input file or in the graphics phase. These commands become active when

LS-DYNA3D output is selected with the DN3D command (see Control Commands).

ARBITRARY Node and element numbering is arbitrary. (LS-

902 and later).

Define Brode function parameters.

BRODE

Options:

;

YLD yld

HEIGHT h

XBO x

YBO y

ZBO z

TBO t

CL cl

CT ct

CP cp

Yield (Ktons)

Height of burst

Coordinates of Brode origin (space, time) in

LS-INGRID units.

Conversion factor - ft. to DYNA length units

(default = meters).

Conversion factor - ms to DYNA time units

(default - seconds).

Conversion factor - psi to DYNA pressure units

(default = Pascals).

Terminate Brode function input.

Note: If "RANG" "COEF", and "GFUN" are specified, a "modified" Brode function will be used in DYNA; otherwise, straight Brode is used.

RANG r

1

... r

5

COEF c

1

... c

8

GFUN g

1

... g

7

Range values for Brode function.

Coefficient values for Brode function.

GFUNC values for Brode Function.

The Brode function is applied to pressure surfaces with load curve number -1.

BRUL n Begin definition of user specified integration rule for beams number n.

20.1

LS-DYNA3D COMMANDS AND MATERIALS LS-INGRID

Options:

BUPD

opt

NPTS n s

1

t

1

w

1

<m

1

> ...

Input n integration points with the parametric

s

n

t n

w n

<m

n

> coordinate, (s,t) and the weight, w. This terminates the rule.

Flag for updating coordinates of reference node for beam elements. Values of opt are "on" or

"off". (LS-910 and later).

CUNI

length time force

D2R m

1

m

2

D3HSP

Unit conversion factors for coupling between

LS-DYNA3D and CAL3D or MADYMO3D.

(LS-910 and later).

Convert material m

1

from deformable to rigid.

If m

2

is 0, then this is an independent rigid body. Otherwise, m

2

is the master rigid body material. If a restart file definition has been initiated, then this command applies to the restart. Otherwise, it applies to the main

DYNA3D input. (LS-920 and later.)

Additional output options for the D3HSP and message files.

Options:

DEBUG opt

ECHO

opt

Option for producing debug output on calculation progress in the message file. Values for opt are either "on" or "off". (LS-910 and later).

Additional suppression options for printout.

(LS-910 and later).

=0: all data is printed.

=1: nodal printing is suppressed.

=2: element printing is suppressed.

=3: both node and element printing are suppressed.

IKEDIT n

;

SUPP opt

TSTEP opt

Number of time steps between writing global statistics data to D3HSP file. (Default = 1000.)

Performs suppression of output echo. Values for opt are either "on" or "off". (LS-910 and later).

Print flag for element time step sizes on first cycle. Values for opt are either "on" or "off".

(LS-910 and later).

Terminate the D3HSP command.

20.2

LS-INGRID

DBQT i

DELT

∆

t

DHGQ Qh

DHQT i

DQL Ql

DQQ Qq

DROPTS

Options:

DRFCTR d

DRTOL tol

NRCYCK n

TSSFDR tssfdr

DRTERM t

LS-DYNA3D COMMANDS AND MATERIALS

Change default bulk viscosity type from 1 to i:

=1: standard LS-DYNA3D

Set time step for mass scaled calculations to

∆

t.

Note that this is an advanced option. Normally

LS-DYNA3D sets the time step. Study the mass scaling option in LS-DYNA3D before using this option. (LS-910 and later).

Set default hourglass viscosity from .10 to Qh.

Set default hourglass viscosity type from 1 to i:

=1: standard LS-DYNA3D

=2: Flanagan-Belytschko viscous form

=3: Flanagan-Belytschko viscous form with exact volume integration.

=4: Flanagan-Belytschko stiffness form

=5: full Flanagan-Belytschko stiffness form with exact volume integration.

Set default linear bulk viscosity for .06 to Ql.

Set default quadratic bulk viscosity from 1.5 to

Qq.

Select dynamic relaxation options. There are three separate methods in LS-910 and later for performing dynamic relaxation. The first uses the

SYSD or LCDAMP commands and is designated

"Method A". This is the recommended method.

The second is designated "Method B" and requires the options below which must be set with care. The third is a method due to Papadrakakis and is designated "Method C". Only one method should be used at a time to avoid confusion.

Damping factor expressed as V

n+1

=d*V

n

. This should be set with care based on the formulas in the DYNA3D Course Notes. (Method B)

Tolerance on distortional kinetic energy for determining convergence. (Method B)

Number of time steps between convergence checks. (Method B)

Time step scale factor during dynamic relaxation.

(Method B)

Termination time for dynamic relaxation simulation should convergence not be obtained.

20.3

LS-DYNA3D COMMANDS AND MATERIALS LS-INGRID

(default = infinity). (LS-910 and later). (Method

B)

;

FLUID

End of dynamic relaxation options.

Set ALE and Eulerian options. (VECALE, LS-

930 and later.)

Options:

ADVECTION opt Set the advection formulation.

opt = 1: first order. (SALE Method)

opt = 2: second order. (Benson HIS)

opt = 3: second order. (Van-Leer)

ALE

;

EULERIAN

LAGRANGIAN

MAT m

NCYCLES n

RELAX1 r

RELAX2 r

RELAX3 r

RELAX4 r

START t

STOP t

FRES m

1

m

2

e s

... ;

1

2

3

4

The element formulation is Arbitrary Lagrangian-

Eulerian.

The element formulation is Eulerian.

The element formulation is Lagrangian (default).

These options apply to material m. (The default is that the specified fluid options apply globally to the model.)

The number of cycles between smoothing and advection (ALE) or smoothing (Eulerian) is n.

Weight for simple average relaxation method.

Weight for Kikuchi relaxation method.

Weight for isoparametric relaxation method.

Weight for equipotential relaxation method.

Start time for ALE.

Stop time for ALE.

End of dynamic relaxation options.

Perform a full restart. Materials m

1

, m

2

, ... are to be remapped. If "FRES ;" is input, then all materials will be remapped.

20.4

LS-INGRID

GMPRT

Options:

ABSTAT t

AVSFLT t

BCOUT t

BELT t

DEFGEO t

DEFORC t

ELOUT t

GEFORC t

GLSTAT t

JOINTS t

MATSUM t

MOVIE t

MPGS t

NCFORCE t

NFG t

NODOUT t

RBOUT t

RCFORC t

RWFORC t

SECFORCE t

SIDB t

SPCFORC t

SWFORC t

TRACER

VARIABLE typ icomp

;

GRAV g

x

g y

g z

HGENERGY on/off

IARB on/off

IRDMS on/off

ITSS t

o

LS-DYNA3D COMMANDS AND MATERIALS

Input general printing option intervals. (LS-910 and later).

Airbag statistics.

AVS filter.

Boundary condition forces.

Seat belt output file.

Smug animator file.

Discrete element.

Element data.

Geometric entity resultants.

Global data.

Joint file.

Material energies.

Movie-BYU output file.

MPGS output.

Nodal interface forces.

Nodel force groups.

Nodal point data.

Rigid body acceleration output.

Resultant interface forces.

Rigid wall forces.

Section forces.

Sliding interface database.

SPC reaction forces.

Nodal constant resultants.

Components for ASCII state output. typ can be

AVS, MOVIE or MPGS. The component number is icomp.

Terminate this command.

Gravity acceleration vector.

Option for computing hourglass energy dissipation. (Default=Off.) (LS-910 and later).

Selection for material input method. If on, then the material input is broken into separate constitutive model, equation-of-state and section property sections. LS-INGRID can convert from one method to another during generation.

The last method selected applies to the output file. (Default=Off.) (LS-910 and later).

Turn on deformable to rigid switching. (LS-920 and later.)

Initial time step size. This is optional input for

LS-DYNA3D. If t

o

is zero, LS-DYNA3D picks the initial time step size.

20.5

LS-DYNA3D COMMANDS AND MATERIALS

LCDAMP lc

LS-INGRID

System damping is specified by load curve lc.

(LS-902 and later).

LCGX lcgx

LCGY lcgy

Load curve number for X-body load.

(default=1).

Load curve number for Y-body load.

(default=1).

LCGZ lcgz

LCRX lcrx

LCRY lcry

LCRZ lcrz

LCMAX lc

MVMA

Load curve number for Z-body load.

(default=1).

Load curve number for X-centrifugal load.

(default=1).

Load curve number for Y-centrifugal load.

(default=1).

Load curve number for Z-centrifugal load.

(default=1).

lc is a load curve which specifies the maximum time step as a function of time.

Output is generated which is compatible with

MVMA-DYNA3D.

NCPU n

NEWC

NSTEP n

OPIFS n

PASS opt

PERCENT n

Use n CPU's for parallel processing. (LS-920 and later.)

Use new contact formulations. (LS-902,

VEC/DYNA3D). This turns on the eroding contact in VEC/DYNA3D.

The number of time steps for mass scaled calculations is n. Note that this is an advanced option and normally LS-DYNA3D sets the time step. Study the mass scaling option in LS-

DYNA3D before using this option. (LS-910 and later).

Output interval for interface file.

Option for sorting parallel assembly of the right hand side. Values for opt are "on" or "off".

(LS-920 and later).

Maximum allowable change in total energy in percent.

PLTI

∆

t

Node and element data dump interval for

TAURUS post-processing.

PRTI

∆

t

Node and element data dump interval for high

20.6

LS-INGRID

PSPO iopt

R2D m

1

m

2

RDENERGY on/off

RDMT m

RDSI s

REIN i

REST name

RHVC h

RIRDMS on/off

RLBV l

RNUM n

RPLT t

RPRT t

LS-DYNA3D COMMANDS AND MATERIALS

speed printer.

Plane stress iteration flag.

=1: iterative plasticity with 3 secant iterations (default).

=2: full iterative plasticity.

=3: radial return non-iterative plasticity.

(quick and very dirty.)

Convert material m

1

from rigid to deformable. If a restart file definition has been initiated, then this command applies to the restart. Otherwise, it applies to the main DYNA3D input. (LS-920 and later.)

Option for computing stone wall energy dissipation. (Default=Off.) (LS-910 and later).

Delete material m. This applies to the restart number selected by the RNUM command.

Delete sliding interface s. This applies to the restart number selected by the RNUM command.

Hughes-Liu shell normal initialization count.

i = -2: unique nodal fibers per Hughes-Liu

=-1: compute normals each cycle (default).

=1: compute on restart.

=n: compute on restart and every nth cycle.

Set the family name for restart input file generation to name.

The default hourglass viscosity for restart is set to h. This applies to the restart number selected by the RNUM command.

Turn on rigid to deformable switching. (LS-920 and later.)

The default linear bulk viscosity for restart is set to l. This applies to the restart number selected by the RNUM command.

Restart commands apply to restart number n.

The plot interval for restart is set to t. This applies to the restart number selected by the

RNUM command.

The print interval for restart is set to t. This applies to the restart number selected by the

RNUM command.

20.7

LS-DYNA3D COMMANDS AND MATERIALS

RQBV q

LS-INGRID

The default quadratic bulk viscosity for restart is set to q. This applies to the restart number selected by the RNUM command.

RTERM t

RTSF s

The termination time for this restart is t. This applies to the restart number selected by the

RNUM command.

The time step scale factor for restart is set to s.

This applies to the restart number selected by the RNUM command.

RWPNAL p

SBRF n

SEQUENTIAL

SFSI s

SIOPT

Scale factor for rigid body nodes impacting rigid walls. If p=0.0, then this capability is ignored.

Number of time steps between restart dumps is

n.

Use sequential node, element and material numbering. (Default)

Sliding interface scale factor (default = 0.1).

Additional sliding interface options. (LS-910 and later).

Options:

ENER opt

CHECK opt

OFFSET n

ORIE opt

PSOPT n

Option for determining sliding interface energy dissipation. Values for opt are "on" and "off".

Option for performing initial penetration checks on contact interfaces. Values for opt are "on" and "off".

Set shell thickness offset option to n:

=0: thickness is not considered in two surface contacts.

=1: thickness is considered but rigid bodies are excluded.

=2: thickness is considered including rigid bodies.

Option for automatically reorienting normals of shell contact segments during initialization.

Values for opt are "on" and "off".

Penalty stiffness option:

=1: use minimum of master segment and slave node (default).

=2: use master segment stiffness (old way).

=3: use slave node value.

=4: use slave node value area or mass

20.8

LS-INGRID

THIN opt

;

SRUL n

Options:

MATE

NPTS n t

1

w

1

<m

1

> ...

t n

w n

<m

n

>

STYP s

SWENERGY on/off

SYSD d

TAURUS

Options:

AVER opt

CMSO opt

DRDB opt

IFDT Dt

LS-DYNA3D COMMANDS AND MATERIALS

weighted.

=5: same as 4 but inversly proportional to the shell thickness.

Option for including thinning of shells in thickness offsets. Values for opt are "on" and

"off".

Terminate SIOPT command.

Begin definition of user specified integration rule for shell number n.

Include optional material selection.

(default=off)

Input n integration points with the parametric coordinate, t, the weight, w and the optional material number, m. This terminates the rule.

Default shell formulation type

s

= HUGHES: use Hughes-Liu shell formulation (default).

= BELYTSCHKO: use Belytschko-Lin-

Tsay shell theory.

Option for computing stone wall energy dissipation. (Default=Off.) (LS-910 and later).

System damping constant d.

(MVMA/DYNA3D, VEC/DYNA3D, LS-902 and later.)

Additional ouput options for the D3PLOT,

D3IFF and D3THDT files.

Output averaged accelerations from velocities in file "nodout" and the time history database file,

"d3thdt". (LS-910 and later).

Composite material stress output option. Values for opt are "global" and "local". (LS-910 and later).

Produce a separate TAURUS database for the dynamic relaxation option. Values for opt are

"on" or "off". (LS-910 and later).

Output interval for interface force database. If zero, the default is the same as for complete state dumps.

20.9

LS-DYNA3D COMMANDS AND MATERIALS

INT4 n

LS-INGRID

Number of additional integration point history variables written to the TAURUS database for shell elements.

INT8 n

SEPARATE opt

TINT n

Number of additional integration point history variables written to the TAURUS database for solid elements.

Option for separating D3PLOT file into one state per family output member. Values for opt are "on" or "off". (LS-910 and later).

Number of through thickness integration points written to TAURUS database. (default=3).

;

TCYCLE n

TEO i

TERM t

TINV n

Terminate TAURUS command options.

The termination cycle is n. (LS-910 and later).

Thermal effects option

=0: no thermal effects.

=N: nodal temperatures are defined in input and are scaled according to a time function.

N is the load curve number.

=-1: each time step a new temperature state is read from a disk file. The time word at the beginning of each temperature state is ignored.

= -2: at each time step a temperature state is interpolated from the temperature state in a disk file. Therefore the time words at the beginning of each temperature state is used.

=-3: the disk file containing temperatures has only one state. The initial state is assumed to be zero.

Terminate dynamic time integration at time t.

Number of time steps between dumps of reaction history blocks.

TSLIMIT

∆

t

TSORT opt

The minimum time step for shell elements of type 3, 18, 19 and 24 cannot go below

∆

t. To enforce this condition, the element stiffness is artificially softened. This is useful when pretty pictures are more important than good results.

Sort triangular elements to treat degenerate quadrilateral elements with the C

0

triangular shell formulation. Values for opt are "on" or

"off". (LS910 and later).

20.10

LS-INGRID

TSSF s

TUPD

V90

V91

V92

V93

VEC

VEC92

WARP ang

WEDGE

LS-DYNA3D COMMANDS AND MATERIALS

Scale factor on time step size.

Modify shell thickness based on membrane strains (default doe not modify shell thickness).

Output is compatible with LS-DYNA3D version

902.

Output is compatible with LS-DYNA3D version

910.

Output is compatible with LS-DYNA3D version

920.

Output is compatible with LS-DYNA3D version

930. This produces the LS-DYNA3D keyword based input.

Output is compatible with VEC-DYNA3D.

Output is compatible with VECALE.

Shell element warpage angle in degrees. If a warpage greater than this angle is found, a warning message is printed. (default=20.0)

(LS-902 and later).

Normally, LS-INGRID does not allow the generation of wedge elements. This command turns on the support for 6-node and 4-node solid elements.

20.1 LS-DYNA3D M

ATERIAL

I

NPUT

LS-DYNA3D material input is possible after the DN3D command is input (see

Control Commands). The form of this input is: MAT n TYPE m {options specific to material type m} {general material options} ENDMAT. n is a material name which is assigned a number as input. Therefore, the materials should be defined in order before any additional use of materials is made.

20.2 G

ENERAL

M

ATERIAL

O

PTIONS

ANGLES

β

1

β

2

...

β

n

Input angles for laminated materials. n is the number of integration points; thus, this command cannot be used until after the QUAD command has been used to specify the number of integration points for the current material.

20.11

LS-DYNA3D COMMANDS AND MATERIALS

BEAM

LS-INGRID

This material is defined for two node beam elements only.

BFORM s Beam formulation type s = "HUGH": Hughes-Liu s = "BELY": Belytschko-Schwer s = "TRUS": Truss

BQL Q

l

BQQ Q

q

BRFORM s

BQT i

CAREH a

Change linear bulk viscosity for .06 to Q

l

.

Change quadratic bulk viscosity from 1.5 to Q

Brick element formulation type (LS-920 and later): s = 1: standard single point brick s = 2: fully integrated brick element

Change bulk viscosity type from 1 to i:

=1: standard LS-DYNA3D (not much choice)

Cross sectional area for Belytscko-Schwer beam.

q

.

EOS eost

HEAD

HGQ Q

HGQT i

IMGL

IRR Irr

h

Begin defining equation-of-state type eost for the current material definition. Each equationof-state is terminated by the ENDEOS command.

Replace default heading (typed on the next line).

Change hourglass viscosity from .10 to Q

h

.

Change type of hourglass viscosity from 1 to i:

=1: standard LS-DYNA3D

=2: Flanagan-Belytschko viscous form

=3: Flanagan-Belytschko viscous form with exact volume integration.

=4: Flanagan-Belytschko stiffness form

=5: full Flanagan-Belytschko stiffness form with exact volume integration.

Initialize material for gravity loads.

Moment of area along r-axis for Belytschko-

Schwer beam.

IRULE GAUSS

IRULE TRAPEZOIDAL

IRULE USER n

ISS Iss

Use gauss quadrature (default).

Use trapezoidal integration.

Use user defined integration rule n.

Area moment of inertia along s-axis for

20.12

LS-INGRID

ITT Itt

LTMN

LTMX

MAT m

MDMP lc scale

QUADRATURE i

RAYD b

REPOSITION

Options:

ELLIPSE n

LS-DYNA3D COMMANDS AND MATERIALS

Belytschko-Schwer beam.

Area moment of inertia along t-axis for

Belytschko-Schwer beam.

The local t-axis for thick shell elements of this material is the shortest direction through the brick.

The local t-axis for thick shell elements of this material is the longest direction through the brick.

Begin material definition m. Each material definition is terminated by the ENDMAT command.

Apply mass weighted damping to material mat.

The magnitude is scale which is multiplied by load curve lc. (LS-920 and later.)

Select quadrature rule i.

For beams the rules are:

i = 1: truss element

i = 2: 2 X 2 Gauss (default)

i = 3: 3 X 3 Gauss

i = 4: 3 X 3 Lobatto

i = 5: 4 X 4 Gauss

For four node shells the rules are:

i = 1: membrane element

i = 2: 2 point Gauss (default)

i = 3: 3 point Gauss

i = 4: 4 point Gauss

i = 5: 5 point Gauss

For eight node thick shells the rules are:

i = 1: membrane element

i = 2: 2 point Gauss (default)

i = 3: 3 point Gauss

i = 4: 4 point Gauss

i = 5: 5 point Gauss

Rayleigh (stiffness proportional) damping coefficient. (LS-920 and later.)

Reposition deformable materials which are positioned relative to CAL3D/MADYMO3D bodies at initialization time. (LS-920 and later)

Slave to MADYMO3D ellipse n.

20.13

LS-DYNA3D COMMANDS AND MATERIALS

PLANE n Slave to MADYMO3D plane n.

SEGMENT n

SYSTEM n

Slave to CAL3D segment n.

Slave to MADYMO3D system n.

LS-INGRID

RO m

SAREA a

SFORM s

Density (required - no default).

Shear area for Belytschko-Schwer beam.

Shell formulation type

s = "HUGH": Hughes-Liu.

s = "BELY": Belytschko-Lin-Tsay

s = "BCZ": BCIZ triangular shell

s = "C0T": C

0

triangular shell.

s = "MEMB": B-L-T membrane.

s = "SRHL": S/R Hughes-Liu

s = "CRHL": Corotational Hughes-Liu.

s = "YASE": Engelmann-Whirley's

"YASE" shell. (Not recommended.)

SHELL

SLOC s

STHICK thick

TLOC t

TSHELL

TTHICK thick

TYPE n

This material is defined for four node shell elements only.

Factor specifying offset of the local s axis.

=-1: reference surface is at bottom plane of shell.

=0: reference surface is at center plane of shell

=1: reference surface is at upper plane of shell

The default thickness along the element local s axis is thick (beams and shell).

Factor specifying offset of the local t axis.

=-1: reference surface is at bottom plane of shell

=0: reference surface is at center plane of shell.

=1: reference surface is at upper plane of shell.

This material is defined for thick (8-node solid) shell elements only.

The default thickness along the element local t axis is thick (beams only).

The current material is of type n.

20.14

LS-INGRID

Material Type 1 (Elastic)

LS-DYNA3D COMMANDS AND MATERIALS

Default heading: Material Type #1 (Elastic)

Input any two of the following.

BULK K

E E

G G

PR

ν

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Material Type 2 (Orthotropic Elastic)

EA E

a

EB E

b

EC E

c

PRBA

υ

ba

PRCA

υ

ca

PRCB

υ

cb

GAB G

ab

GBC G

bc

GCA G

ca

AOPT aopt

XP x

YP y

p p

See constitutive matrix below.

Material axes option (Figure 20-1).

=0.0: locally orthotropic with materials axes by element nodes n

1

, n

2

, and n

4

, (see Figure 20-1).

=1.0: locally orthotropic with materials axes by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

=3.0: SHELL ELEMENTS ONLY: The material axis is locally orthotropic with material axes determined by a vector in the plane of the shell and the shell normal.

Define for AOPT = 1.

Define for AOPT = 1.

20.15

LS-DYNA3D COMMANDS AND MATERIALS

ZP z

p

A1 a

1

A2 a

2

A3 a

3

D1 d

1

D2 d

2

D3 d

3

V1 v

1

V2 v

2

V3 v

3

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 3.

Define for AOPT = 3.

Define for AOPT = 3.

LS-INGRID

The material law that relates stresses to strains is defined as:

C

~

=

T

~

T

C

L

~

T

~

, where \o(T,

~

) is a transformation matrix, and \o(C,

~

)L is the constitutive matrix defined in terms of the material constants of the orthogonal material axes, a, b, and c. The inverse of \o(C,

~

)L is defined as

C

−

1

~ L

=





















1

−

E a v ab

−

E a v ac

E a

0

0

0

− v ba

E b

1

−

E v b bc

E b

0

0

− v ca

−

E c v cb

E c

1

E c

0

0

0

0

0

1

G ab

0

0 0 0

0

0

0

0

1

G bc

0

0

0

0

0

0

1

G ca



















 v ab

Note that

E a

= v ba

,

E b v ca

=

E c v ac

,

E a v cb

=

E c v bc

.

E b

20.16

LS-INGRID c

(a)

b

n

4 n

1 n

2

AOPT=0.0 default

a

LS-DYNA3D COMMANDS AND MATERIALS

n

3

d c

(c)

b a

AOPT=2.0 define a and d

d a d

(b)

b c

z

v

(d)

v x n

y

x p

, y

p

, z

p

x

AOPT=1.0 d is parallel to the z-axis

n

shell element

AOPT=3.0

Figure 20-1. Options for determining principal materials axes: (a) AOPT = 0.0, (b) AOPT =

1.0, and (c) AOPT = 2.0, (d) AOPT = 3.0.

20.17

LS-DYNA3D COMMANDS AND MATERIALS

Material Type 3 (Kinematic/Isotropic Elastic/Plastic)

Default heading: Material Type #3 (Elastic-Plastic)

LS-INGRID

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

SIGY

σ

y

ETAN E

t

BETA

β

'

SC c

SP p

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Yield stress

Hardening modulus

Hardening parameter, 0 <

β

' < 1

Strain rate parameter, C

Strain rate parameter, p

Strain rate is accounted for using the Cowper and Symonds model which scales the yield stress with the factor

1

+





ε

Ý

C





1 p where Ý is the strain rate.

Isotropic, kinematic, or a combination of isotropic and kinematic hardening may be specified by varying

β

' between 0 and 1. For

β

' equal to 0 and 1, respectively kinematic and isotropic hardening are obtained as shown in Figure 20-2. Effective stress is defined in terms of the deviatoric stress tensor, S ij

as:

σ =





3

2

S ij

S ij





1

2 where,

S ij

= σ ij

−

1

3

σ kk

δ ij and effective plastic strain by:

ε p

∫ t

= d

ε

0 p where t denotes time and

20.18

LS-INGRID LS-DYNA3D COMMANDS AND MATERIALS

d

ε p

=





2

3 d

ε p ij d

ε ij p





1

2

For isotropic hardening (

β

' = 1) material model 12 requires less storage and is more efficient.

yield stress

E

E t

l n

l

β=0 kinematic hardening

β=

1 isotropic hardening

Figure 20-2.

Elastic-plastic behavior with isotropic and kinematic hardening where l

0

and l are undeformed and deformed length of uniaxial tension specimen.

20.19

LS-DYNA3D COMMANDS AND MATERIALS

Material Type 4 (Thermo-Elastic-Plastic)

LS-INGRID

Default heading: Material Type 4 (Thermo-Elastic-Plastic)

NPTS n

TEMP T

1

T

2

...T

n

E E

1

E

2

...E

n

PR

υ

1

υ

2

...

υ

n

ALPHA

α

1

SIGY

σ

y1

σ

α

y2

2

...

α

n

...

σ

yn

ETAN E

t1

E

t2

...E

tn

Number of temperature values for which material constants are defined.

Temperatures.

Young's moduli.

Poisson's ratios.

Coefficients of thermal expansion.

Yield stresses.

Tangent moduli.

Material Type 5 (Soil and Crushable Foam)

Default heading: Material Type 5 (Soil and Crushable Foam)

Input any two of the following:

BULK K

E E

G G

PR

ν

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Additional Options:

AO a

A1 a

A2 a

PC P

1

2

0 c

UL uopt

ULD d

NPTS n

VS

ε

v1

ε

v2

P p

1

p

2

...p

n

...

ε

vn

Yield function constant

Yield function constant

Yield function constant

Pressure cutoff for tensile fracture

Unloading option

=0: volumetric crushing

=1: loading and unloading are the same.

=2: hysteretic behavior.

Unloading distance for option 2 above.

Number of points in volumetric strain versus pressure curve (n£10).

Volumetric strain values

Pressures corresponding to volumetric strain values

The deviatoric, perfectly yield function,

φ

, is described in terms of the second invariant J

2

.

20.20

LS-INGRID LS-DYNA3D COMMANDS AND MATERIALS

J

2

=

1

2 s ij s ij

Pressure,

p, and constants a

0

, a

1

, and a

2

as:

φ =

J

2

−

[ a

0

+ a

1 p

+ a

2 p

2

]

.

On the yield surface,

J

2

=

1

3

σ

2 y

, where s

y

is the yield stress, i.e.,

σ y

=

[

(

0

+ a

1 p

+ a

2 p

2

)

]

1

2

For elastic-perfectly plastic behavior a

1

=a

2

=0, and (3a

0

)

1/2

defines the yield strength.

The volumetric strain is given by the natural logarithm of the relative volume V. If the pressure drops below the cutoff value, PC, then it is reset to that value.

pressure

Loading and unloading follows the input curve if the volumetric crushing option is off (Card 3, col. 61-70) hysteretic behavior for option 2

The bulk unloading modulus is used if the volumetric crushing option is on

(Card 3, col. 61-70) tension cutoff

Volumetric strain

Figure 20-3. Volumetric strain versus pressure curve for soil and crushable foam model.

20.21

LS-DYNA3D COMMANDS AND MATERIALS

Material Type 6 (Viscoelastic)

G G

0

GI G

´

K K

BETA

β

Short term shear modulus.

Long term shear modulus.

Bulk modulus.

Decay constant.

The shear relaxation behavior is described by:

G(t) = G + (G

0

– G ) e

-

β t

LS-INGRID

A Jaumann rate formulation is used:

σ

∇

′ ij

=

2

∫ t

0

(

− τ

)

D ij

′

( ) dt where the prime denotes the deviatoric part of the stress rate,

σ

ij

, and the strain rate D

IJ

.

Material Type 7 (Blatz-Ko Rubber)

Default heading: Material Type #7 (Rubber)

G G Shear modulus.

The second Piola-Kirchhoff stress is computed as

S ij

= µ





1

V

C ij

−

V

−

1

1

−

2

υ

δ ij where

V is the relative volume, C

ij is the right Cauchy-Green strain tensor, and n is the

Poisson's ratio which is set to .463 internally. This stress measure is transformed to the

Cauchy stress, s

ij

, according to the relationship

σ ij

= V

-1

F ik

F jl

S lk where

F ij

is the deformation gradient tensor.

20.22

LS-INGRID

Material Type 8 (High Explosive Burn)

LS-DYNA3D COMMANDS AND MATERIALS

Default heading: Material Type #8 (High Explosive Burn)

D D

PCJ P

CJ

Detonation velocity.

Chapman-Jouget pressure.

This material model requires an equation-of-state.

Material Type 9 (Null Material)

Default heading: Material Type #9 (Null Material)

PC pc

MU

µ

Pressure cutoff.

µ

.

The null material must be used with an equation-of-state. Pressure cutoff is negative in tension. A viscous stress of the form

σ ij

= µ ε

Ý

′ ij is computed for nonzero m where

ε

Ý

′ ij is the deviatoric strain rate.

Material Type 10 (Isotropic-Elastic-Plastic-Hydrodynamic)

Default heading: Material Type #10 (Isotropic-Elastic-Plastic-Hydrodynamic)

G G

SIGY

σ

y

EH E

h

PC p

c

or -

σ

f

A1 a

1

A2 a

2

NPTS n

ES

σ

y1

σ

y2

...

σ

yn

Shear modulus

Yield strength

Plastic hardening modulus

Pressure cutoff

= 0: cutoff of -´ is assumed

Yield function constant

Yield function constant

Number of points in yield stress-effective plastic strain curve or yield stress-pressure curve.

Yield stress

20.23

LS-DYNA3D COMMANDS AND MATERIALS

EPS

ε

p1

ε

p2

...

ε

pn

P p

1

p

2

... p

n

FS

ε

f

Effective plastic strain

Pressure

Failure strain

LS-INGRID

If the yield stress-plastic strain curve is not defined and if a

1

= a

2

= 0, the bilinear stress-strain curve shown in Figure 20-2 is obtained with b =1. The yield strength is calculated as

σ y

= σ

0

+

E h

ε p where

p is the pressure. The quantity E

h

is the plastic hardening modulus defined in terms of

Young's modulus, E, and the tangent modulus, E

t

, as follows

E h

=

E t

E

E

−

E t

If the yield stress-plastic strain (pressure) curve is defined, a curve like that shown in Figure 20-4 may be defined. In this latter case, the yield stress and plastic hardening modulus,

a

1

and a

2

are ignored.

Effective stress is defined in terms of the deviatoric stress tensor, s

ij

, as:

σ =





3

2 s ij s ij





1

2

(1) and effective plastic strain by:

ε p

=

∫

0 t





2

3

D ij p

D ij p





1

2 dt,

(2) where

t denotes time and

D ij p

is the plastic component of the rate of deformation tensor. Yield stress may be defined as a function of plastic strain or pressure but not both.

20.24

LS-INGRID

σ

y

LS-DYNA3D COMMANDS AND MATERIALS

Piecewise linear curve defining the yield stress versus effective plastic strain. A nonzero yield stress is defined when the plastic strain is zero.

0

e p

Figure 20-4. Effective stress versus effective plastic strain curve.

Material Type 11 (Temperature Dependent Elastic-Plastic Hydrodynamic)

Default heading: Material Type #11 (Temperature Dependent Elastic-Plastic Hydrodynamic)

G G

0

SIGO

σ

o

BETA

β

N n

GAMA

γ

i

SIGM

σ

m

B b

BP b'

H h

F f

A a

TO T

mo

GAMO g

0

SA a

Shear modulus.

See equations below.

20.25

LS-DYNA3D COMMANDS AND MATERIALS

PC pmin or -s

f

ECO EC

0

EC1 EC

1

EC2 EC

2

EC3 EC

3

EC4 EC

4

EC5 EC

5

EC6 EC

6

EC7 EC

7

EC8 EC

8

EC9 EC

9

LS-INGRID

Cold compression energy coefficients (optional)

If cold compression energy coefficients are not input, then LS-DYNA3D will calculate them based on the equation-of-state.

SPALL type Spall type

=0: default set to "2.0"

=1: p 3 p min

=2: if s max

> s

f

element spalls and tension p

< 0, is never allowed; s max

= maximum principal stress.

=3: if p < p min

element spalls and tension

p<0, is never allowed.

=4: failure strain

Users who have an interest in this mode are encouraged to study the paper by

Steinberg and Guinan [9] which provides the theoretical basis. Another useful reference is the KOVEC user's manual [10].

In terms of the foregoing input parameters, we define the shear modulus, G, before the material melts as:

G

=

G

0





1

+ bpV

1

3

− h



E i

−

3 R

′

E c

−

300







 e

− fE i

E m

−

E i where

p is the pressure, V is the relative volume, E

c

is the cold compression energy:

ε p

=

∫ t

0





2

3

D ij p

D ij p





1

2 dt,

x = 1 - V and E

m

is the melting energy:

E m

(x) = E c

(x) + 3R

′

T m

(x)

20.26

LS-INGRID LS-DYNA3D COMMANDS AND MATERIALS

which is in terms of the melting temperature

T m

(x):

T m

( )

=

T

V mo

( )

2

(

γ o

− a

− 1

3

) and the melting temperature at

r = r

0

, T

mo

.

In the above equation, R' is defined by

R

′ =

R

ρ

A where

R is the gas constant and A is the atomic weight. If R' is not defined, LS-DYNA3D computes it with R in the cm-gram-microsecond system of units.

The yield strength

σ

y

is given by:

σ y

σ

0





1

+ ′

1

3

− h



E i

−

3

R

′

E c

−

300







 e

− fEi

E m

−

Ei if

E m

exceeds E

i

. Here,

σ

0

' is given by:

σ y

σ

0

[

1

( i

+ ε

− p

)

] n where

ε

i

is the initial plastic strain. Whenever

σ

0

' exceeds

σ

m

,

σ

0

' is set equal to

σ

m

. After the material melts,

σ

y

and G are set to zero.

If the coefficients ECO,...EC9 are not defined above, LS-DYNA3D will fit the cold compression energy to the ten term polynomial expansion:

E c

=

9

∑ i

=

0

EC i

η i where

EC i

is the ith coefficient and h=r/r

0

-1. A least square method is used to perform the fit.

Material Type 12 (Isotropic-Elastic-Plastic)

Default heading: Material Type #12 (Isotropic-Elastic-Plastic)

Input any two of the following:

BULK K

E E

G G

Bulk modulus.

Young's modulus.

Shear modulus.

20.27

LS-DYNA3D COMMANDS AND MATERIALS

PR

ν

Poisson's ratio.

Additional Options:

SIGY

σ

y

EH Eh

Yield strength.

Hardening modulus.

LS-INGRID

Pressure is integrated in time

Ý

= −

K

V where V is the relative volume.

This model is recommended for brick elements but not for shell elements since it is not too accurate.

Material Type 13 (Elastic-Plastic with Failure Model)

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

SIGY

σ

y

EH E

h

FS

ε

f

FP p

f

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Yield strength.

Hardening modulus.

Failure strain.

Failure pressure (£0.0).

When the effective plastic strain reaches the failure strain or when the pressure reaches the failure pressure, the material loses its ability to carry tension and the deviatoric stresses are set to zero, i.e., the material behaves like a fluid.

20.28

LS-INGRID LS-DYNA3D COMMANDS AND MATERIALS

Material Type 14 (Soil and Crushable Foam with Failure Model)

The input for this model is the same as for material type 5; however, when the pressure reaches the failure pressure, the element loses its ability to carry tension.

Material Type 15 (Johnson/Cook Plasticity Model)

G G

A A

B B

N n

R r

M m

TM T

melt

TO To

EPSO Eo

HCP c

PC pc

D1 d

1

D2 d

2

D3 d

3

D4 d

4

D5 d

5

IT i

Shear modulus.

See equation (1).

See equation (1).

See equation (1).

See equation (1).

See equation (1).

Melt temperature

Room temperature.

Effective plastic strain rate.

Specific heat.

Pressure cutoff (pc < 0.0).

See equation (2).

See equation (2).

See equation (2).

See equation (2).

See equation (2).

Iteration options:

=0: no iterations.

=1: LS-DYNA3D iterates to determine a more accurate point on the stress-strain curve.

The Johnson/Cook model is described in reference [11]. This model includes strain rate hardening, thermal softening, and has a complex damage model. The equations describing the flow stress vs. effective plastic strain and failure strain are as follows:

σ y

=





A

+

B

ε p n





(

1

+ c ln Ý

) (

1

−

T

∗ m

) where

A, B, C, n, and m are input constants,

ε p

effective plastic strain

20.29

LS-DYNA3D COMMANDS AND MATERIALS

Ý p

Ý

0

effective plastic strain rate for Ý

0

=

1 s

−

1

LS-INGRID

T*=T

r

/T m

=homologous temperature

Constants for a variety of materials are also provided in [11].

Due to the nonlinearity in the dependence of flow stress on plastic strain, an accurate value of the flow stress requires iteration for the increment in plastic strain. However, by using a Taylor series expansion with linearization about the current time, we can solve for s

y

with sufficient accuracy to avoid iteration.

The strain at fracture is given by

ε f

=

[

D

1

+

D

2 exp D

3

σ

∗

] [

1

+

D

4

ε

∗

] [

1

+

D

5

T

∗

] where s* is the ratio of pressure divided by effective stress:

σ

∗

= p

σ eff

Fracture occurs when the damage parameter

D

=

∑ ∆ε p

ε f reaches the value of 1.

Material Type 16 (Pseudo Tensor Geological Model)

Default heading: Material Type #16 (Pseudo Tensor Geological Model)

G G

PR

ν

SIGF sigf

A0 a

0

A1 a

1

A2 a

2

A0F a

0f

Shear modulus (constant Shear modulus model).

Poisson's ratio (constant Poisson's ratio model).

Tensile cutoff. (Maximum principal stress for failure.)

Cohesion.

Yield function constant.

Yield function constant.

Cohesion for failed material.

20.30

LS-INGRID

A1F a

B1 b

1

PER p

1f

ER E

r

PR

ν

r

SIGY

σ

y

ETAN E

t

LCP lc

LCR lc

1

NPTS n

2

ES

σ

1

σ

2

...

σ

n

EPS

ε

p1

ε

p2

...

ε

p3

P p

1

p

2

... p

n

LS-DYNA3D COMMANDS AND MATERIALS

Pressure hardening coefficient for failed material.

Damage scaling factor.

Percent reinforcement.

Elastic modulus for reinforcement.

Poisson's ratio for reinforcement.

Initial yield strength.

Tangent modulus.

Load curve giving rate sensitivity for principal material.

Load curve giving rate sensitivity for reinforcement.

Number of points in yield stress-effective plastic strain curve or yield stress-pressure curve;

(n£16).

Yield stress.

Effective plastic strain.

Pressure.

See the LS-DYNA3D manual for a description of this model.

Material Type 17 (Elastic Plastic with Failure Model)

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

SIGY

σ

y

EH E

h

FS

ε

f

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Yield strength.

Plastic hardening modulus.

Failure stress.

Model 17 can fail in two ways. In hydrostatic tension, the element will fail when the failure stress is exceeded. The element will then allow hydrostatic compressive loads only.

20.31

LS-DYNA3D COMMANDS AND MATERIALS LS-INGRID

If the effective stress exceeds the failure stress, the element will form a fracture plane and retain part of its strength.

Material Type 18 (Power Law Plasticity)

Input any two of the following:

BULK K

E

E

G G

PR

ν

Additional Options:

K k

M m

SC c

SP p

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

See equation below

See equation below.

Strain rate parameter, C.

Strain rate parameter, p.

***missing***

Elastoplastic behavior with isotropic hardening is provided by this model. The yield stress,

σ y, is a function of plastic strain and obeys the equation:

σ y

= k

ε

( e

+ ε p

) n

ε e is the elastic strain to yield and where

ε parameters are defined in material type 3.

p

is the effective plastic strain. The strain-rate

Material Type 19 (Strain Rate Sensitive Plasticity)

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

20.32

LS-INGRID

ECRV lc

ETAN e

tan

FCRV lc

SIGY lc

TCRV lc

TDEL Dt

LS-DYNA3D COMMANDS AND MATERIALS

Load curve describing Young's modulus as a function of strain rate.

Tangent hardening modulus.

Load curve describing failure stress as a function of strain rate.

Load curve describing yield as a function of strain rate.

Load curve describing tangent modulus as a function of strain rate.

Minimum time step. (This is for element deletion).

In this model, a load curve is used to describe the yield strength, s

0

, as a function of effective strain rate,

Ý





2

3

ε

Ý

′ ij

ε

Ý

′ ij





1

2 and the prime denotes the deviatoric component. The yield stress is defined as

σ y

= σ

0

( )

+

E h

ε p where

ε p is the effective plastic strain and E

h

is given by

E h

=

E E

E

−

E t t

.

Material Type 20 (Rigid Body)

All elements with the same material number become a single rigid body if the material is type 20 whether the elements are connected or not. Density and two independent material strength constants are required to establish penalties for contact surfaces and joints.

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

DEFG

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

The rigid body is defined in the global system used by CAL3D/MADYMO3D. (LS-920)

20.33

LS-DYNA3D COMMANDS AND MATERIALS

DEFL

LS-INGRID

The rigid body is defined in the local system used by CAL3D/MADYMO3D. (LS-920)

ELLIPSE m

MESH

The rigid body is slaved to MADYMO3D ellipsoid m. (LS-920)

Generate a mesh for the CAL3D/MADYMO3D coupled rigid body. (LS-920)

MSLAV m

PLANE m

SYSTEM n

VDA

The rigid body is slaved to CAL3D rigid body number m. (LS-920)

The rigid body is slaved to MADYMO3D plane

m. (LS-920)

The rigid body is slaved to MADYMO3D system n. (LS-920)

The rigid body is characterized by a VDA surface geometry. (LS-920)

AVEC a

x

a y

a z

VVEC v

x

v y

v z

Define the vector a for the rigid body local system.

Define the vector v for the rigid body local system.

Material Type 21 (Thermal Orthotropic)

EA E

a

EB E

b

EC E

c

PRBA

υ

ba

PRCA

υ

ca

PRCB

υ

cb

GAB G

ab

GBC G

bc

GCA G

ca

AA

α

a

AB

α

b

AC

α

c

AOPT aopt

See constitutive matrix for material 2.

α

a

.

α

b

.

α

c

.

Material axes option (Figure 20-1).

=0.0: locally orthotropic with materials axes determined by element nodes n

1

, n

2

, and n

4

,

(see Figure 20-1).

=1.0: locally orthotropic with materials axes

20.34

LS-INGRID

XP x

p

YP y

p

ZP z

p

A1 a

1

A2 a

2

A3 a

3

D1 d

1

D2 d

2

D3 d

3

V1 v

1

V2 v

2

V3 v

3

LS-DYNA3D COMMANDS AND MATERIALS

determined by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

=3.0: SHELL ELEMENTS ONLY: The material axis is locally orthotropic with material axes determined by a vector in the plane of the shell and the shell normal.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 3.

Define for AOPT = 3.

Define for AOPT = 3.

Material Type 22 (Orthotropic Damage Model)

See constitutive matrix below.

EA E

a

EB E

b

EC E

c

PRBA

υ

ba

PRCA

υ

ca

PRCB

υ

cb

GAB G

ab

GBC G

bc

GCA G

ca

K K

f

SC S

c

XT x

t

YT y

t

YC y

c

ALPH

α

Bulk modulus of failed material.

Shear strength, ab plane.

Longitudinal tensile strength, a-axis.

Transverse tensile strength, b-axis.

Transverse compressive strength.

Non-linear shear stress parameter.

20.35

LS-DYNA3D COMMANDS AND MATERIALS

AOPT aopt terial axes option (Figure 20-1).

XP x

YP y

ZP z

A1 a

A2 a

A3 a

D1 d

D2 d

D3 d

V1 v

V2 v

V3 v

p p p

1

2

3

1

2

3

1

2

3

LS-INGRID

Ma

=0.0: locally orthotropic with materials axes determined by element nodes n

1

, n

2

, and n

4

,

(see Figure 20-1).

=1.0: locally orthotropic with materials axes determined by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

=3.0: SHELL ELEMENTS ONLY: The material axis is locally orthotropic with material axes determined by a vector in the plane of the shell and the shell normal.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 3.

Define for AOPT = 3.

Define for AOPT = 3.

Material Type 23 (Thermal Orthotropic with Curves)

Number of points. (1<NPTS<50).

NPTS npts

EA (E

a

)

1

... (E

a

)

n

EB (E

b

)

1

... (E

b

)

n

EC (E

c

)

1

... (E

c

)

n

PRBA (

ν

ba

)

1

... (

ν

ba

)

n

PRCA (

ν

ca

)

1

... (

ν

ca

)

n

PRCB (

ν

cb

)

1

... (

ν

cb

)

n

AA (

α

a

)

1

... (

α

a

)

n

AB (

α

b

)

1

... (

α

b

)

n

AC (

α

c

)

1

... (

α

c

)

n

20.36

LS-INGRID

GAB (G

ab

)

1

... (G

ab

)

n

GBC (G

bc)1

... (G

bc)n

GCA (G

ca

)

1

... (G

ca

)

n

AOPT aopt

LS-DYNA3D COMMANDS AND MATERIALS

XP x

p

YP y

p

ZP z

p

A1 a

1

A2 a

2

A3 a

3

D1 d

1

D2 d

2

D3 d

3

V1 v

1

V2 v

2

V3 v

3

Material Type 24 (Elastic Plastic with Failure)

Input any two of the following:

BULK K

E E

G G

PR

ν

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Material axes option (Figure 20-1).

=0.0: locally orthotropic with materials axes determined by element nodes n

1

, n

2

, and n

4

,

(see Figure 20-1).

=1.0: locally orthotropic with materials axes determined by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

=3.0: SHELL ELEMENTS ONLY: The material axis is locally orthotropic with material axes determined by a vector in the plane of the shell and the shell normal.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 3.

Define for AOPT = 3.

Define for AOPT = 3.

20.37

LS-DYNA3D COMMANDS AND MATERIALS

Additional Options:

LS-INGRID

SIGY s

ETAN E

t

NPTS n

ES

σ

1

EPS

ε

FAIL

y

σ

2

1

TDEL

ε

CSR lc

ε

2

f

∆

t

...

σ

n

...

ε

n

Yield strength.

Hardening modulus

Number of points in effective stress-effective plastic strain curve. Note that the first point on this curve must be e

1

= 0.0 and s

1

= yield stress.

Effective stress.

Effective plastic strain.

Minimum time step. (This is for automatic element deletion).

Failure strain

Load curve which describes strain-rate effects.

Strain rate is accounted for using the Cowper and Symonds model which scales the yield stress with the factor

1

+





ε

Ý

C





1 p where Ý is the strain rate. For complete generality a load curve may be input instead. This latter option is quite expensive.

A curve similar to that shown in Figure 3.4 is expected. A load curve may be used with an arbitrary number of points if eight is not sufficient. The cost is roughly the same for either approach.

Material Type 25 (Inviscid Two Invariant Geologic Cap Model)

G G

K K

ALPHA

α

BETA

β

GAMMA

γ

THETA

θ

R R

D D

X0 X

0

CC C

T T

NPLOT nplot

Shear Modulus.

Bulk Modulus.

γ

.

θ

.

α

.

β

.

R.

D.

X

0

.

C.

Tension cutoff.

Save the following variable for plotting in

TAURUS:

=1: k

=2: X

20.38

LS-INGRID

LTYPE ltype

LS-DYNA3D COMMANDS AND MATERIALS

=3: e

v p

=.4: J

1

=5: (J

2

)

1/2

=6: (J2|

L

)

1/2

=7: (J2|

tr

)

1/2

=8: MTYPE

=9: number of iterations

Variable ltype.

=1: soil/concrete (cap contracts)

=2: rock (cap doesn't contract)

For details of this model, please refer to the LS-DYNA3D User's Manual.

Material Type 26 (Metallic Honeycomb)

Model 26 provides a method for modeling the crushing of an anisotropic material which eventually compresses to a solid, isotropic mass. This model is valid for brick elements only. For more details, see the LS-DYNA3D manual.

E E

PR

ν

SIGY

σ

y

VF V

f

LCA lca

LCB lcb

LCC lcc

LCS lcs

EAAU E

aau

EBBU E

bbu

ECCU E

ccu

GABU G

abu

GBCU G

bcu

GCAU G

cau

LCAB lcab

Young's modulus for fully compressed state.

Poisson's ratio for fully compressed state.

Yield stress for fully compressed state.

Relative volume at which the material is fully compacted.

Load curve for sigma-aa versus either relative volume or volumetric strain.

Load curve for sigma-bb versus either relative volume or volumetric strain.

Load curve for sigma-cc versus either relative volume or volumetric strain.

Load curve for shear stress versus either relative volume or volumetric strain.

Elastic modulus E

aau

in uncompressed configuration.

Elastic modulus E

bbu

in uncompressed configuration.

Elastic modulus E

ccu

in uncompressed configuration.

Elastic shear modulus G

abu

in uncompressed configuration.

Elastic shear modulus G

bcu

in uncompressed configuration.

Elastic shear modulus G

cau

in uncompressed configuration.

Load curve number for s

ab

versus either relative

20.39

LS-DYNA3D COMMANDS AND MATERIALS

LCBC lcbc

LCCA lcca

LS-INGRID

volume or volumetric strain. (default: lcab=lcs)

Load curve number for s

bc

versus either relative volume or volumetric strain. (default: lcbc=lcs)

Load curve number for s

ca

versus either relative volume or volumetric strain. (default: lcca=lcs)

AOPT aopt

XP x

YP y

ZP z

p

A1 a

1

A2 a

2

A3 a

3

D1 d

1

D2 d

2

D3 d

3

p p

Material axes option (Figure 20-1).

=0.0: locally orthotropic with materials axes by determined element nodes n

1

, n

2

, and n

4

,

(see Figure 20-1).

=1.0: locally orthotropic with materials axes determined by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Material Type 27 (Compressible Mooney-Rivlin Rubber)

This material model provides an alternative to the Blatz-Ko rubber model. The implementation is due to Maker [12].

A A

B B

PR

ν

Constant A.

Constant B.

Poisson's ratio.

The strain energy density function is defined as:

W=A(I-3)+B(II-3)+C(III

-2

-1)+D(III-1)

2 where

20.40

LS-INGRID LS-DYNA3D COMMANDS AND MATERIALS

C=0.5A+B.

D

=

(

υ −

2

(

)

+

−

2

(

υ −

υ

)

5

)

ν

=Poisson's ratio.

2(A+B)=G=shear modulus of linear elasticity.

I, II, III are invariants of the right Cauchy-Green Tensor

C

~

.

Material Type 28 (Resultant Plasticity)

Default heading: Material Type #28 (Resultant Plasticity)

This model is available for the Belytschko-Schwer beam and the Belytschko-Tsay shell and is still under development. For beams the treatment is elastic-perfectly plastic, but for shell elements isotropic hardening is approximately modeled.

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

SIGY

σ

y

ET E

t

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Yield strength.

Hardening modulus (shells only).

Material Type 29 (Force Limited Resultant Formulation)

This model is valid for the Belytschko beam element only. Experimentally obtained force-deflection curves may be used to model buckling and plastic behavior. See the LS-

DYNA3D manual for more details.

Input any two of the following:

20.41

LS-DYNA3D COMMANDS AND MATERIALS

BULK K

E E

G G

PR

ν

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Additional Options:

R R

1

lc

1

... R

n

lc

n

;

LPS1 lps1

SFS1 sfs1

LPS2 lps2

SFS2 sfs2

LPT1 lpt1

SFT1 sft1

LPT2 lpt2

SFT2 sft2

LS-INGRID

Applied moments for force deflection curves.

n£8.

Load curve for plastic moment versus rotation at node 1 in s-direction.

Scale factor for plastic moment versus rotation curve at node 1 in s-direction.

Load curve for plastic moment versus rotation at node 2 in s-direction.

Scale factor for plastic moment versus rotation curve at node 2 in s-direction.

Load curve for plastic moment versus rotation at node 1 in t-direction.

Scale factor for plastic moment versus rotation curve at node 1 in t-direction.

Load curve for plastic moment versus rotation at node 2 in t-direction.

Scale factor for plastic moment versus rotation curve at node 2 in t-direction.

Material Type 30 (Closed-Form Update Shell Plasticity)

Default heading: Material Type #30 (Closed-Form Update Shell Plasticity)

Input any two of the following:

BULK K

E E

G G

PR

ν

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

20.42

LS-INGRID

Additional Options:

SIGY

σ

y

ET E

t

LS-DYNA3D COMMANDS AND MATERIALS

Yield strength.

Hardening modulus.

This model is available for the Belytschko-Schwer beam and the Belytschko-Tsay shell and is still under development. For beams, the treatment is elastic-perfectly plastic, but for shell elements, isotropic harening is approximately modeled.

Material Type 31 (Frazer-Nash Rubber Model)

This model implements a hyperelastic constitutive law described in [13].

C001 C001

C010 C010

C020 C020

C100 C100

C101 C101

C110 C110

C200 C200

C210 C210

C300 C300

C400 C400

LIMIT l

EMAX

ε max

EMIN

ε min

Limit option

=0.0: stop if strain limits are exceeded.

10.0: continue if strain limits are exceeded.

Maximum strain limit.

Minimum strain limit.

The strain energy function, U, is defined in terms of the input constants as:

U

=

C

100

I

1

+

C

200

I

2

1

+

C

300

I

1

3

+

C

400

I

4

1

+

C

010

I

2

+

C

020

I

2

2

+

C

110

I

1

I

2

+

C

210

I

1

2

I

2

+

C

001

I

3

+

C

101

I

1

I

3

The derivative of U with respect to a component of strain gives the corresponding component of stress:

20.43

LS-DYNA3D COMMANDS AND MATERIALS

S ij

∂

U

E ij

=

2

∂

U

∂

C ij

LS-INGRID

where

S ij

, E

ij

, and C

ij

are the second Piola-Kirchhoff stress tensor, the Green-St. Venant strain tensor, and the right Cauchy-Green deformation tensor, respectively.

Material Type 32 (Laminated Glass Model)

EG E

g

PRG

ν

FSG (

ε

f

EP E

p

PRP

ν

p g

SYG (

σ

y

ETG (E

t

SYP (

σ

y

ETP (E

t

IOPT f

1

)

g

)

g

)

g

)

p

)

p

... f

n

;

Young's modulus for glass.

Poisson's ratio for glass.

Yield stress for glass.

Hardening modulus for glass.

Failure strain.

Young's modulus for polymer.

Poisson's ratio for polymer.

Yield stress for polymer.

Hardening modulus for polymer.

Integration point options.

f i

=0: glass.

f i

=1: polymer.

Isotropic hardening is assumed. The material to which the glass is bonded is assumed to stretch plastically without failure. A user defined integration rule is required which specifies the thickness of the layers making up the glass. There must be the same number of parameters for the IOPT command as integration points.

Material Type 34 (Fabric)

The fabric material is similar to the orthotropic composite model (22). It is designed to allow a fabric to be modeled as layers of orthotropic material. The principal characteristic of a fabric material is that it does not support compressive stresses. This is because it is usually modeled with elements that are at least an order-of-magnitude wider than the thickness of the material. This model is still somewhat experimental and model 22 is frequently substituted.

EA E

a

EB E

b

See constitutive matrix below.

20.44

LS-INGRID

EC E

c

PRBA

υ

ba

PRCA

υ

ca

PRCB

υ

cb

GAB G

ab

GBC G

bc

GCA G

ca

CSF csf

TSF tsf

EXP exp

CSEF f

LS-DYNA3D COMMANDS AND MATERIALS

Compressive modulus scale factor.

Tensile modulus scale factor.

Exponent.

Compressive stress elimination flag.

=0: use the variable modulus method.

=1: truncate stresses (recommended).

The material law that relates stresses to strains is defined as:

C

~

=

T

~

T

C

L

~

T

~

, where \o(T,

~

) is a transformation matrix, and \o(C,

~

)L is the constitutive matrix defined in terms of the material constants of the orthogonal material axes, a, b, and c. The inverse of \o(C,

~

)L is defined as

C

−

1

~ L

=





















1

−

E a v ab

−

E a v ac

E a

0

0

0 0

Note that v ab

E a

= v ba

,

E b v ca

=

E c v ac

,

E a v cb

=

E c v bc

.

E b

− v ba

E b

1

−

E v b bc

E b

0

0

− v ca

−

E c v cb

E c

1

E c

0

0

0

0

0

1

G ab

0

0 0

0

0

0

0

1

G bc

0

0

0

0

0

0

1

G ca





















20.45

LS-DYNA3D COMMANDS AND MATERIALS

AOPT aopt

XP x

YP y

ZP z

A1 a

A2 a

A3 a

D1 d

D2 d

D3 d

V1 v

V2 v

V3 v

p p p

1

2

3

1

2

3

1

2

3

LS-INGRID

Material axes option (Figure 20-1).

=0.0: locally orthotropic with materials axes determined by element nodes n

1

, n

2

, and n

4

,

(see Figure 20-1).

=1.0: locally orthotropic with materials axes determined by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

=3.0: SHELL ELEMENTS ONLY: The material axis is locally orthotropic with material axes determined by a vector in the plane of the shell and the shell normal.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 3.

Define for AOPT = 3.

Define for AOPT = 3.

Material Type 35 (Kinematic/Isotropic Elastic-Plastic Green-Naghdi Rate)

Default heading: Material Type #35 (Green-Naghdi Rate Plasticity)

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

SIGY

σ

y

ET E

t

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Yield strength

Hardening modulus

20.46

LS-INGRID

BETA

β

'

SC c

SP p

LS-DYNA3D COMMANDS AND MATERIALS

Hardening parameter, 0 <

β

' < 1

Strain rate parameter, C

Strain rate parameter, p

This model is available only for brick elements and is similar to model 3 but uses the

Green-Naghdi Rate formulation rather than the Jaumann rate.

Material Type #37 (Transversely Anisotropic Elastic-Plastic)

Default heading: Material Type #37 (Transversely Anisotropic Elastic-Plastic)

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

ET E

t

LCSS lc

R R

SIGY

σ

y

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Hardening modulus

Load curve number for stress-strain curve.

Anisotropic hardening parameter, R.

Yield strength

This model is only available for shell elements and is intended for modeling sheet metal forming processes. This is a degenerate form of Hill's model which assumes similar in-plane flow characteristics in all directions but different through-thickness effects. See the

LS-DYNA3D manual for more details.

Material Type 41-50 (User Defined Material Models)

NPTS npts Number of material parameters.

PARAM parameter 1 ... parameter Material parameters.

AOPT aopt Material axes option (Figure 20-1).

20.47

LS-DYNA3D COMMANDS AND MATERIALS LS-INGRID

=0.0: locally orthotropic with materials axes determined by element nodes n

1

, n

2

, and n

4

,

(see Figure 20-1).

XP x

YP y

ZP z

A1 a

A2 a

A3 a

D1 d

D2 d

D3 d

V1 v

V2 v

V3 v

p p p

1

2

3

1

2

3

1

2

3

=1.0: locally orthotropic with materials axes determined by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

=3.0: SHELL ELEMENTS ONLY: The material axis is locally orthotropic with material axes determined by a vector in the plane of the shell and the shell normal.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 3.

Define for AOPT = 3.

Define for AOPT = 3.

Material Type 51 (Temperature and Rate Dependent Plasticity)

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

T T

HC HC

COEF C

1

... C

18

ALPHA

α

1

α

2

α

4

α

5

α

6

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Initial Temperature.

Heat generation coefficient.

Model Coefficients.

Initial value of internal state variables.

20.48

LS-INGRID

KAPPA

κ

LS-DYNA3D COMMANDS AND MATERIALS

κ

.

See the LS-DYNA3D manual for a description of this model.

Material Type 52 (Sandia's Damage Model)

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

T T

HC HC

COEF C

1

... C

18

ALPHA

α

1

α

2

α

4

α

5

α

6

NEXP n

D0 D0

Initial Temperature.

Heat generation coefficient.

Model Coefficients.

Initial value of internal state variables.

Exponent in damage evolution

Initial damage (porosity).

See the LS-DYNA3D manual for a description of this model.

Material Type 53 (Low Density Closed Cell Polyurethane Foam)

Options:

E E

GAM0

γ

0

P0 p

0

PA a

PB b

PC c

PHI

φ

Young's modulus.

Initial volumetric strain.

Initial foam pressure.

a.

b.

c.

Ratio of foam to polymer density.

20.49

LS-DYNA3D COMMANDS AND MATERIALS

See the LS-DYNA3D manual for a description of this model.

LS-INGRID

Material Type 54 and 55 (Composite Damage Model)

Material 54 uses the Chang matrix failure criterion (the same as model 22). Material

55 uses the Tsay-Wu criterion. These models are for LS-920 and later.

See constitutive matrix below.

EA E

a

EB E

b

EC E

c

PRBA

υ

ba

PRCA

υ

ca

PRCB

υ

cb

GAB G

ab

GBC G

bc

GCA G

ca

FBRT fbrt

SOFT soft

K K

f

SC S

c

XT x

t

YT y

t

YC y

c

ALPH

α

TFAIL t

f

AOPT aopt

Softening for fiber tensile strength

=0.0: fiber rupture with tension cutoff.

>0.0: stress=fbrt, X

c

after failure.

Softening reduction factor for material strength in crashfront elements (default=1.0)

Bulk modulus of failed material.

Shear strength, ab plane.

Longitudinal tensile strength, a-axis.

Transverse tensile strength, b-axis.

Transverse compressive strength.

Non-linear shear stress parameter.

Time step for automatic element deletion.

Material axes option (Figure 20-1).

=0.0: locally orthotropic with materials axes determined by element nodes n

1

, n

2

, and n

4

,

(see Figure 20-1).

=1.0: locally orthotropic with materials axes determined by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

20.50

=3.0: SHELL ELEMENTS ONLY: The material axis is locally orthotropic with material axes determined by a vector in the plane of the shell and the shell normal.

LS-INGRID

XP x

p

YP y

p

ZP z

p

A1 a

1

A2 a

2

A3 a

3

D1 d

1

D2 d

2

D3 d

3

V1 v

1

V2 v

2

V3 v

3

LS-DYNA3D COMMANDS AND MATERIALS

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 3.

Define for AOPT = 3.

Define for AOPT = 3.

Material Type 57 (Low Density Urethane Foam)

This model is for LS-920 and later.

Options:

BETA

β

E E

LC l

TENSION t

UNLOAD d

Decay constant.

Young's modulus.

Load curve number of nominal stress versus strain.

Tension cut-off stress.

Hysteretic unloading factor between 0 and 1

(Default=1, i.e. no energy dissipation).

See the LS-DYNA3D manual for a description of this model.

Material Type 59 (Composite Failure Model - Plasticity Based)

This model is for LS-920 and later.

EA E

a

EB E

b

EC E

c

PRBA

υ

ba

PRCA

υ

ca

PRCB

υ

cb

GAB G

ab

See constitutive matrix below.

20.51

LS-DYNA3D COMMANDS AND MATERIALS

GBC G

bc

GCA G

ca

FBRT fbrt

SOFT soft

SF sf

SR sr

K Kf

SC S

XT x

YT y

c t

YC y

c t

ALPH

α

TFAIL t

f

LS-INGRID

Softening for fiber tensile strength

=0.0: fiber rupture with tension cutoff.

>0.0: stress=fbrt, X

c

after failure.

Softening reduction factor for material strength in crashfront elements (default=1.0)

Softening factor. (default=0.0).

Reduction factor. (default=0.447).

Bulk modulus of failed material.

Shear strength, ab plane.

Longitudinal tensile strength, a-axis.

Transverse tensile strength, b-axis.

Transverse compressive strength.

Non-linear shear stress parameter.

Time step for automatic element deletion.

AOPT aopt

XP x

p

YP y

p

ZP z

p

A1 a

1

A2 a

2

A3 a

3

D1 d

1

D2 d

2

D3 d

V1 v

V2 v

V3 v

3

1

2

3

Material axes option (Figure 20-1).

=0.0: locally orthotropic with materials axes determined by element nodes n

1

, n

2

, and n

4

,

(see Figure 20-1).

=1.0: locally orthotropic with materials axes determined by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

=3.0: SHELL ELEMENTS ONLY: The material axis is locally orthotropic with material axes determined by a vector in the plane of the shell and the shell normal.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 3.

Define for AOPT = 3.

Define for AOPT = 3.

20.52

LS-INGRID

Material Type 60 (Elastic with Viscosity)

LS-DYNA3D COMMANDS AND MATERIALS

This model is for LS-910 and later.

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

NPTS npts

T T

1

VC

ν

1

... T

n

...

ν

n

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Number of points. (npts£8). (Default=1).

Temperatures. (input only if npts>1.)

Viscosity coefficients (at least one is input.)

Material Type 64 (Simple Creep Model)

This model is for LS-930 and later.

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

EI ei

K k

LCK lck

LCM lcm

M m

N n

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Value for ei.

Value for k.

Load curve for k.

Load curve for m.

Value for m.

Value for n.

20.53

LS-DYNA3D COMMANDS AND MATERIALS

Material Type Belt

LS-INGRID

This is a special material which applies to beam elements only. When material type belt is specified, beams are converted to the special seat belt element in LS-920 and later.

Dummy beam elements are output to LS-DYNA3D also for viewing as null materials.

LCL lcl

LCU lcu

RO r

MINIMUM l

Load curve for loading.

Load curve for unloading.

Mass per unit length.

Minimum allowable length. (This is used to determine the minimum element size before an element is passed through a slip ring.)

Example:

MAT 56 TYPE BELT LCL 24 LCU 24 RO [0.100/386.4]

MINIMUM 0.2 BEAM ENDMAT

20.54

LS-INGRID LS-DYNA3D COMMANDS AND MATERIALS

20.55

LS-INGRID

21. Equations-of-State

EQUATIONS-OF-STATE

Equations-of-state are required by certain LS-DYNA2D and LS-DYNA3D material models. They provide a relationship between pressure, relative volume, and temperature (or internal energy) which is used in place of a bulk modulus. Equations-of-state are needed when significant volume changes occur during a deformation process. They are attached to a material model and the general form of the input is:

MAT i TYPE j {material options} ENDMAT

EOS k {equation-of-state options} ENDEOS

This will define material i as being of type j and having equation-of-state characteristics of type

k.

Equation-of-State Form 1 (Linear Polynomial)

Default heading: Equation-of-State Form 1 (Linear Polynomial)

CO C

0

C1 C

1

C2 C

2

C3 C

3

C4 C

4

C5 C

5

C6 C

6

E0 E

0

V0 V

0

ENDEOS

See equation below

Initial internal energy

Initial relative volume

End equation-of-state definition.

The linear polynomial equation-of-state is linear in internal energy. The pressure is given by:

P

=

C

0

+

C

1

µ +

C

2

µ

2

+

C

3

µ

3

+

(

C

4

+

C

5

µ +

C

6

µ

2

)

E .

where terms

C

2

µ

2

and C

6

µ

2

are set to zero if

µ

<0,

µ

=

ρ

/

ρ

0

-1 and

ρ

/

ρ

0

, is the ratio of current density to the initial density.

21.1

EQUATIONS-OF-STATE

Equation-of-State Form 2 (JWL)

Default heading: Equation-of-State Form 2 (JWL High Explosive)

A A

B B

R1 R

1

R2 R

2

OMEGA

ω

E0 E

0

V0 V

0

ENDEOS

See equation below.

Initial internal energy

Initial relative volume

End equation-of-state definition.

The JWL equation-of-state defines the pressure as

p

=



−

R

ω

V

1

e

−

R

1

V

+



−

R

ω

2

V e

−

R

2

V

and is usually used for detonation products of high explosives.

V

E

,

LS-INGRID

Equation-of-State Form 3 (Sack)

Default heading: Equation-of-State Form 3 (Sack Tuesday High Explosive)

A1 A

1

A2 A

2

A3 A

3

B1 B

1

B2 B

2

E0 E

0

V0 V

0

ENDEOS

See equation below

Initial internal energy

Initial relative volume

End equation-of-state definition.

The Sack equation-of-state defines the pressure as

p

=

V

A

A

3

1

e

−

A

2

V

1

−

B

1

V

B

2

V

E

21.2

LS-INGRID

and is used for detonation products of high explosives.

EQUATIONS-OF-STATE

Equation-of-State Form 4 (Gruneisen)

Default heading: Equation-of-State Form 4 (Gruneisen)

SP C

S1 S

1

S2 S

2

S3 S

3

GAMMA g

0

SA a

E0 E

0

V0 V

0

ENDEOS

See equation below.

Initial internal energy.

Initial relative volume.

End equation-of-state definition.

The Gruneisen equation-of-state with cubic shock velocity-particle velocity defines pressure for compressed materials as

p

=

ρ

0

C

2

µ

1

+



1

−

γ

2

0



1

−

(

S

1

−

1

)

µ −

S

2

µ

2

µ +

1

a

2

µ

2

S

3

(

µ

3

µ +

1

)

2

+

(

γ

0

+

a

µ

)

E .

and for expanded materials as

p

= ρ

0

C

2

0

+

a

µ

)

E .

where

C is the intercept of the u

s

-u p

curve, S

1

, S

2

, and S

3

are the coefficients of the slope of the u

s

-u p

curve,

γ

0 and

µ =

ρ

ρ

0

−

1.

is the Gruneisen gamma; and a is the first order volume correction to

γ

0

21.3

EQUATIONS-OF-STATE

Equation-of-State Form 5 (Ratio of Polynomials)

LS-INGRID

Default heading: Equation-of-State Form 5 (Ratio of Polynomials)

A10 A

10

A11 A

11

A12 A

12

A13 A

13

A20 A

20

A21 A

21

A22 A

22

A23 A

23

A30 A

30

A31 A

31

A32 A

32

A33 A

33

A40 A

40

A41 A

41

A42 A

42

A43 A

43

A50 A

50

A51 A

51

A52 A

52

A53 A

53

A60 A

60

A61 A

61

A62 A

62

A63 A

63

A70 A

70

A71 A

71

A72 A

72

A73 A

73

ALPHA a

BETA b

A14 A

14

A24 A

24

COEF A10..A24

E0 E

0

V0 V

0

ENDEOS

List the 32 above coefficients in the same order as they appear.

Initial internal energy

Initial relative volume

End equation-of-state definition.

21.4

LS-INGRID EQUATIONS-OF-STATE

The ratio of polynomials equation-of-state defines the pressure as

p

=

F

1

+

F

F

5

2

E

+

F

+

F

3

E

2

6

E

+

F

7

+

F

4

E

3

2

E

(

1

+ α µ

) where

F i

=

n

∑

A j

=

0

ij

µ

j

µ =

ρ

ρ

0

−

1 n

=

4 if i

<

3 n

=

3 if i • 3

In expanded zones

F1 is replaced by F

′

1 = F1 +

β µ

2. By setting coefficient A10 = 1.0, the delta-phase pressure modeling for this material will be initiated. The code will reset it to 0.0

after setting flags.

Equation-of-State Form 6 (Linear Polynomial With Energy Leak)

Default heading: Equation-of-State Form 6 (Linear Polynomial with Energy Leak)

C1 C

1

C2 C

2

C3 C

3

C4 C

4

C5 C

5

C6 C

6

E0 E

0

V0 V

0

CN cn

ENDEOS

See Equation-of-State Form 1.

Initial internal energy.

Initial relative volume.

Curve number of time history that gives energy deposition rate.

End equation-of-state definition.

21.5

EQUATIONS-OF-STATE

Equation-of-State Form 7 (Ignition and Growth of Reaction in HE)

LS-INGRID

Default heading: Equation-of-State Form 7 (Ignition and Growth of Reaction in High

Explosive)

AP A

p

BP B

p

R1P R

1p

R2P R

2p

G G

WPCP w

p

C p

AE A

e

BE B

e

WECE w

e

C e

R1E R

1e

R2E R

2e

FCRIT FCRIT

I I

H H

Z z

X x

Y Y

CP C

p

CE C

e

M m

T0 T

0

E0 E

0

ENDEOS

See equations below

See equations below

See equations below

See equations below

Second ignition coefficient

See equations below

See equations below

See equations below

See equations below

See equations below

See equations below

Critical fraction reached

First ignition coefficient

Growth coefficient

Pressure exponent

See equations below

See equations below

Heat capacity of reaction products

Heat capacity of unreacted HE

(generally = 0)

Initial temperature ( o

K)

Initial internal energy

End equation-of-state definition.

A JWL equation-of-state defines the pressure in the unreacted HE as

P e

=

A e



1

−

ω e

R1 e

V e

 e

−

R1 e

V e

+

B e



1

−

ω e

R2 e

V e

 e

−

R2 e

V e

+

ω

E e

V e where

V e

is the relative volume, E

e

is the internal energy, and the constants A

e

, B e

, w

e

, R

1e

, and R

2e

are input constants. Similarly the pressure in the reaction products is defined by another JWL form

P p

=

A p



1

−

ω

R1 p p

V p

 e



−

R1 p

V p

+

B e







1

−

R2

ω p p

V p

 e



−

R2 p

V p

+

ω

E p

V p

The mixture of unreacted explosive and reaction products is defined by the fraction reacted F (F=0)

¨ no reaction, (F=1) ¨ complete conversion from explosive to products. The pressures and temperatures are assumed to be in equilibrium and the volumes are assumed to be additive.

21.6

LS-INGRID EQUATIONS-OF-STATE

V = (1-F)V

e

+ FV

p

The rate of reaction is

∂

F

∂ t

=

(

−

F

) y

(

V

−

1 e

−

1

)

3

[

1

+

(

−

1 e

−

1

)

]

+

(

−

F

) y

F x

P z

(

V

−

1 p

−

1

) m where

I, G, H, x, y, z, and m (generally m=0) are input constants.

The JWL equations of state and the reaction rates have been fitted to one- and twodimensional shock initiation and detonation data for four explosives: PBX-9404, RX-03-BB,

PETN, and cast TNT. The details of the calculational method are described by Cochran and

Chan [14]. The detailed one-dimensional calculations and parameters for the four explosives are given by Lee and Tarver [15].

Equation-of-State Form 8 ( Tabulated-Compaction)

Default heading: Equation-of-State Form 8(Tabulated-Compaction)

NPTS n

LNV e

V1

e

V2

e

Vn

PC C

1

C

2

...C

n

PT T

1

T

2

...T

n

KU K

1

K

2

...K

n

GAMMA

γ

E0 E

0

V0 V

0

ENDEOS

Number of points in tabulated curves.

Volumetric strain points, e

Vi

= ln(V

i)

.

Points on the curve for C(e

V

).

Points on the curve for T(e

V

).

Points on the curve for the unloading bulk modulus.

See equation below.

Initial internal energy.

Initial relative volume.

End equation-of-state definition.

The tabulated compaction model is linear in internal energy. Pressure is defined by

p

=

C(

ε

V

)

+

γ

T(

ε

V

)E in the loading phase. The volumetric strain e

V

, is given by the natural logarithm of the relative volume. Unloading occurs along the unloading bulk modulus to the pressure cutoff.

Reloading always follows the unloading path to the point where unloading began, and continues on the loading path. See Figure 21-1. Up to 10 points and as few as 2 may be used when defining the tabulated function, LS-DYNA2D/3D will extrapolate to find the pressure

21.7

EQUATIONS-OF-STATE

if necessary.

pressure

LS-INGRID

The bulk unloading modulus is a function of volumetic strain

Volumetric strain tension cutoff

Figure 21-1.

Pressure versues volumetric strain curve for equation-of-state form 8 with compaction. In the compacted states the bulk unloading modulus depend on the peak volumetric strain.

Equation-of-State Form 9 (Tabulated)

Default heading: Equation-of-State Form 9 (Tabulated)

NPTS n

LNV e

V1

e

V2

e

Vn

PC C

1

C

2

...C

n

PT T

1

T

2

...T

n

GAMMA g

Number of points in tabulated curves.

Volumetric strain points, e

Vi

= ln(V

i)

.

Points on the curve for C(e

V

).

Points on the curve for T(e

See equation below.

21.8

V

).

LS-INGRID

E0 E

0

V0 V

0

ENDEOS

EQUATIONS-OF-STATE

Initial internal energy.

Initial relative volume.

End equation-of-state definition.

The tabulated compaction model is linear in internal energy. Pressure is defined by

P = C (

ε

V

) +

γ

T (

ε

V

)E in the loading phase. The volumetric strain eV

, is given by the natural logarithm of the relative volume. Unloading occurs along the unloading bulk modulus to the pressure cutoff.

Reloading always follows the unloading path to the point where unloading began, and continues on the loading path. See Figure 21-1. Up to 10 points and as few as 2 may be used when defining the tabulated function, LS-DYNA2D/3D will extrapolate to find the pressure if necessary.

21.9

EQUATIONS-OF-STATE LS-INGRID

21.10

LS-INGRID LS-NIKE2D COMMANDS AND MATERIALS

22. LS-NIKE2D Commands and Materials

Analysis options are code dependent. They can be set either in the control section of the LS-INGRID input file or in the graphics phase. These commands become active when

LS-NIKE2D output is selected with the NK2D command.

ANAL

BWMO

n

GRAV

GSTIF

n

DCTOL tol

DELT

DTMAX

Dt

D

DTMN

d

ECTOL

GEOM

tol

sn g x

g y

g z

on/off

Analysis type

="STAT": static analysis (default).

="DYN": direct time integration.

="DYNS": direct time integration with static initialization.

="EIGE": eigenvalue extraction.

Bandwidth minimization option.

="ON": perform minimization in analysis code (default).

="OFF": don't minimize bandwidth.

Convergence tolerance on displacements. LS-

NIKE2D defaults to 0.001.

Time step size for LS-NIKE2D.

Maximum step size permitted. If SSO =

"AUTO" the default is set by LS-NIKE2D.

Minimum step size permitted. If SSO =

"AUTO" the default is set by LS-NIKE2D.

Convergence tolerance on energy. LS-NIKE2D defaults to 0.01.

Node and element data dump interval for high speed printer.

"STRE" Plane stress

"AXIS" Axisymmetric

Gravity acceleration vector. The gravitational field is scaled in time by load curve one.

Geometric stiffness option. The default is off and generally gives the best results.

IPLT

LST

n

tol

Node and element data dump interval for

TAURUS post-processing.

Line search tolerance.

22.1

LS-NIKE2D COMMANDS AND MATERIALS

MSRF

n

LS-INGRID

Maximum number of stiffness reformations per time step. LS-NIKE2D defaults to the recommended value of 15.

NBEI

n

NBSR

n

The number of time steps between equilibrium iterations.

The number of time steps between stiffness matrix reformation.

NEIG

n

NIBSR

n

Number of eigenvectors. This option turns on the subspace iteration eigenvalue/eigenvector solution method and overrides all other solution options. Eigenvectors are mass normalized and written into the graphics database. The time word corresponds to the frequency in radians/units of time.

Maximum number of equilibrium iterations permitted between stiffness matrix reformations.

LS-NIKE2D defaults to the recommended value of 10.

First Newmark integration parameter.

NIP1

NIP2

NSMD

s s n

Second Newmark integration parameter.

Nonlinear solution method.

="BFGS": BFGS (default)

="BROY": Broyden's

="MODN": modified Newton

To obtain a linear elastic solution, NBSR and

NBEI should be larger than the number of time steps in the problem.

The default parameters for nonlinear solution methods are near optimal. If a problem is having trouble converging the fixes include decreasing the time step, adding dynamic effects, or trying to eliminate some of the nonlinearities.

NSTEP

RFTS

n r

SBRF

SHIFT

n

w

Number of desired time steps.

Reduction factor for tangential stiffness. This is used for modeling the stick condition due to friction in the penalty formulation of contact.

Number of time steps between restart file generations. If zero, LS-NIKE2D writes a restart file as it terminates.

Shift frequency in hertz. This option works with

22.2

LS-INGRID

SSIT

SSO

SSOO

TEO i

n s u

TERM

t

LS-NIKE2D COMMANDS AND MATERIALS

the eigenvalue/eigenvector solution method.

Using this option, LS-NIKE2D will find the

NEIG eigenvalues nearest to w. If the model has rigid body modes, a negative value for w should be used to make the run stable. If w is exactly the same value as an eigenvalue the system becomes singular.

Slide surface insertion tolerance.

Step size option.

"AUTO"

"MANUAL"

Optimal number of iterations per step.

Thermal effects option

=0: no thermal effects.

=N: nodal temperatures are defined in input and are scaled according to a time function.

N is the load curve number.

=-1: each time step a new temperature state is read from a disk file. The time word at the beginning of each temperature state is ignored.

=-2: each time step a temperature state is interpolated from the temperature state in a disk file. Therefore the time words at the beginning of each temperature state are used.

=-3: the disk file containing temperatures has only one state. The initial state is assumed to be zero.

Terminate dynamic time integration at time t.

The dynamic time step size will be computed if this command is used instead of the "DELT" command.

22.3

LS-NIKE2D COMMANDS AND MATERIALS LS-INGRID

22.1 LS-NIKE2D M

ATERIAL

I

NPUT

LS-NIKE2D material input is possible after the NK2D command has been input (see

Control Commands). The form of this input is: MAT n TYPE m {options specific to material type m} {general material options} ENDMAT. n is a material name which is assigned a number in the order that they occur in the input. Therefore, the materials should be defined in order before any additional use of materials is made.

Material Type 1 (Elastic)

Default heading: Material Type #1 (Elastic)

Input any two of the following.

BULK K

E E

G G

PR n

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Material Type 2 (Orthotropic Elastic)

EA E

a

EB E

b

EC E

c

PRBA u

ba

PRCA u

ca

PRCB u

cb

GAB G

ab

AOPT aopt

RP r

ZP z

p p

PSIG y

G

See constitutive matrix below.

Material axes option (Figure 22-1).

=0.0: locally orthotropic with materials axes by y value specified on each element card and element nodes n

1

and n

2

, (see Figure 22-1).

=1.0: locally orthotropic with materials axes by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by y

G

.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

22.4

LS-INGRID LS-NIKE2D COMMANDS AND MATERIALS

The material law that relates stresses to strains is defined as:

C

~

=

T

~

T

C

L

~

T

~

,

Where

\o(T,

~

) is a transformation matrix, and

\o(C,

~

)L is the constitutive matrix defined in terms of the material constants of the orthogonal material axes, a, b, and c. The inverse of

\o(C,

~

)L is defined as v ab

Note that

E a

C

−

1

~ L

= v ba

,

E b v ca

=

E c

=





















1

−

E a v ab

−

E a v ac

E a

0

0

0 v ac

E a

, v cb

=

E c

−

−

E v

E

1 v

E

0

0

0 ba b b bc b v bc

.

E b

− v ca

−

E

E c v cb

E c

1

0

0

0 c

G

0

0

0

1

0

0 ab

0

0

0

0

1

G

0 bc

0

0

0

0

0

1

G ca





















22.5

LS-NIKE2D COMMANDS AND MATERIALS LS-INGRID c

(a)

b

n

4 n

1 n

2

AOPT=0.0 default

a a d c

(c)

b

n

3

a

AOPT=2.0 define a and d

d d

(b)

b

z y

x p

, y

p

, z

p

x

AOPT=1.0 d is parallel to the z-axis

c v

(d) shell element

AOPT=3.0

v x n n

Figure 22-1.

Options for determining principal materials axes: (a) AOPT = 0.0, (b) AOPT

= 1.0, and (c) AOPT = 2.0.

22.6

LS-INGRID LS-NIKE2D COMMANDS AND MATERIALS

Material Type 3 (Kinematic/Isotropic Elastic/Plastic)

Default heading: Material Type #3 (Elastic-Plastic)

Input any two of the following:

BULK K

E E

G G

PR n

Additional Options

SIGY s

y

ETAN E

t

BETA b'

NPTS n

ES s

y1

s

EPS e

p1

y2

e

... s

yn

p2

... e

pn

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Yield strength.

Hardening modulus.

Hardening parameter, 0 < b' < 1

Number of points on stress-effective plastic strain curve.

Effective stress.

Effective plastic strain.

Isotropic, kinematic, or a combination of isotropic and kinematic hardening may be specified by varying b' between 0 and 1. For b' equal to 0 and 1, respectively, kinematic and isotropic hardening are obtained as shown in Figure 22-2. Effective stress is defined in terms of the deviatoric stress tensor, s

ij

as:

σ

=

(

3

2

S ij

S ij

)

1

2 where,

S ij

=

σ

ij

−

1

3

σ

kk

δ

ij

and effective plastic strain by:

ε p

∫ t

= d

ε

0 p where t denotes time and

d

ε

p

=

(

2

3

d

ε

p ij d

ε

p ij

)

1

2

22.7

LS-NIKE2D COMMANDS AND MATERIALS LS-INGRID

yield stress

E

E t

l n

( )

0

β=0 kinematic hardening

β=

1 isotropic hardening

Figure 22-2.

Elastic-plastic behavior with isotropic and kinematic hardening where l

0

and l are undeformed and deformed length of uniaxial tensions specimen.

22.8

LS-INGRID

Material Type 4 (Thermo-Elastic-Plastic)

LS-NIKE2D COMMANDS AND MATERIALS

Default heading: Material Type 4 (Thermo-Elastic-Plastic)

NPTS n

TEMP T

1

T

2

...T

n

E E

1

E

2

...E

n

PR u

1

u

2

...u

n

ALPHA a

1

a

2

...a

n

SIGY

σ

y1

σ

y2

...

σ

yn

ETAN E

t1

E

t2

...E

tn

Number of temperature values for which material constants are defined.

Temperatures.

Young's moduli.

Poisson's ratios.

Coefficients of thermal expansion.

Yield stresses.

Tangent moduli.

Material Type 5 (Soil and Crushable Foam)

Default heading: Material Type 5 (Soil and Crushable Foam)

Input any two of the following:

BULK K

E E

G G

PR

ν

Additional Options:

AO n

A1 a

1

A2 a

2

PC P

c

UL uopt

NPTS n

VS e

v1

e

v2

... e

vn

P p

1

p

2

... p

n

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Yield function constant

Yield function constant

Yield function constant

Pressure cutoff for tensile fracture

Unloading option

=0: volumetric crushing

=1: no volumetric crushing

Number of points in volumetric strain versus pressure curve (n£10).

Volumetric strain values

Pressures corresponding to volumetric strain values

The deviatoric yield function,

φ

, is described in terms of the second invariant J

2

.

J

2

=

1

2 s ij s ij

22.9

LS-NIKE2D COMMANDS AND MATERIALS LS-INGRID

Pressure,

p, and constants a

0

, a

1

, and a

2

as:

φ =

J

2

−

[ a

0

+ a

1 p

+ a

2 p

2

]

.

On the yield surface,

J

2

=1/3(s

y

)

1/2

, where

σ

y

is the yield stress, i.e.,

σ y

=

[

(

0

+ a

1 p

+ a

2 p

2

)

]

1

2

For elastic-perfectly plastic behavior

a

1

=a

2

=0, and (3a

0

)

1/2

defines the yield strength. The volumetric strain is given by the natural logarithm of the relative volume V. If the pressure drops below the cutoff value, PC, then it is reset to that value.

pressure

Loading and unloading follows the input curve if the volumetric crushing option is off (Card 3, col. 61-70) hysteretic behavior for option 2

The bulk unloading modulus is used if the volumetric crushing option is on

(Card 3, col. 61-70) tension cutoff

Volumetric strain

Figure 22-3. Volumetric strain versus pressure curve for soil and crushable foam model.

22.10

LS-INGRID

Material Type 6 (Viscoelastic)

G G

K K

0

GI G

´

BETA b

LS-NIKE2D COMMANDS AND MATERIALS

Short term shear modulus.

Long term shear modulus.

Bulk modulus.

Decay constant.

The shear relaxation behavior is described by:

G(t) = G + (G

0

– G ) e

-

β t

A Jaumann rate formulation is used:

σ

∇

′ ij

=

2

∫ t

0

(

− τ

)

D ij

′

( ) dt where the prime denotes the deviatoric part of the stress rate,

σ

ij

,

and the strain rate D

IJ

.

Material Type 7 (Thermal Orthotropic Elastic)

Default heading: Material Type #7 (Thermal Orthotropic Elastic)

See constitutive matrix below.

EA E

a

EB E

b

EC E

c

PRBA u

ba

PRCA u

ca

PRCB u

cb

ALPA a

a

ALPB a

b

ALPC a

c

GAB G

ab

AOPT aopt

Thermal expansion coefficient along axis a.

Thermal expansion coefficient along axis b.

Thermal expansion coefficient along axis c.

Material axes option (Figure 22-1).

=0.0: locally orthotropic with materials axes determined by element nodes n

1

, n

2

, and n

4

,

(see Figure 22-1).

=1.0: locally orthotropic with materials axes determined by a point in space and global location of element center.

22.11

LS-NIKE2D COMMANDS AND MATERIALS

RP r

ZP z

p p

PSIG y

G

LS-INGRID

=2.0: globally orthotropic with materials axes determined by y

G

.

Define for AOPT = 1.

Define for AOPT = 1.

In radians, define for AOPT = 2.

Material Type 8 (Thermo-Elastic-Creep)

Default heading: Material Type #8 (Thermo-Elastic-Creep)

NPTS n

TEMP T

1

T

2

...T

n

G G

1

G

2

...G

n

K K

1

K

2

...K

n

ALPHA a

1

a

2

...a

n

A a

1

a

2

...a

n

B b

1

b

2

...b

n

Number of temperature values for which material constants are defined.

Temperatures

Shear moduli.

Bulk moduli.

Coefficients of thermal expansion.

Creep parameters.

Creep parameters.

In this model, G, is the shear modulus and the instantaneous creep is given by a power law of the form where a and b are functions of temperature. This model was developed and provided for LS-

NIKE2D by R. D. Krieg of Sandia National Laboratories.

Material Type 9 (Blatz-Ko Rubber)

Default heading: Material Type #9 (Rubber)

G m Shear modulus

The second Piola-Kirchhoff stress is computed as

S ij

= µ





1

V

C ij

−

V

−

1

1

−

2

υ

δ ij where

V is the relative volume, C

ij is the right Cauchy-Green strain tensor, and n is the

22.12

LS-INGRID LS-NIKE2D COMMANDS AND MATERIALS

Poisson's ratio which is set to .463 internally. This stress measure is transformed to the

Cauchy stress, s

ij

, according to the relationship

σ ij

= V

-1

F ik

F jl

S lk where

F ij

is the deformation gradient tensor.

Material Type 10 (Power Law Plasticity)

Input any two of the following:

BULK K

E E

G G

PR n

Additional Options:

K k

M m

FC f

Bulk modulus

Young's modulus

Shear modulus

Poisson's ratio

MPS s max

MSS t max

LC lc

See equation below

See equation below

Failure criteria.

=1: Mohr-Coulomb.

=2: Drucker-Prager

=3: check both

Maximum pricipal stress (optional).

Maximum shear stress (optional).

Optional failure curve number.

The stress-strain curve for this model is based on the following equation:

σ

y

=

k(

ε

e

+

ε

p

)

n

22.13

LS-NIKE2D COMMANDS AND MATERIALS

Material Type 12 (Power Law Thermo Plasticity)

NPTS n

T T

1

T

2

...T

n

E E

1

E

2

...E

n

PR u

1

u

2

...u

n

K k

1

...k

n

M m

1

...m

n

Number of temperature points (£8).

Temperatures

Young's moduli

Poisson's ratios

See equation below

See equation below

The stress-strain curve for this model is based on the following equation:

σ

y

=

k(

ε

e

+

ε

p

)

n

LS-INGRID

Material Type 22 (Frazer-Nash Rubber Model)

This model implements a hyperelastic constitutive law described in [13].

C001 C001

C010 C010

C020 C020

C100 C100

C101 C101

C110 C110

C200 C200

C210 C210

C300 C300

C400 C400

The strain energy function, U, is defined in terms of the input constants as:

U

=

C

100

I

1

+

C

200

I

1

2

+

C

300

I

1

3

+

C

400

I

1

4

+

C

010

I

2

+

C

020

I

2

2

+

C

110

I

1

I

2

+

C

210

I

1

2

I

2

+

C

001

I

3

+

C

101

I

1

I

3

The derivative of

U with respect to a component of strain gives the corresponding component of stress:

S ij

∂

U

E ij

=

2

∂

U

∂

C ij

22.14

LS-INGRID LS-NIKE2D COMMANDS AND MATERIALS

where,

S ij

, E

ij

and C

ij

are the second Piola-Kirchhoff stress tensor, the Green-St. Venant strain tensor, and the right Cauchy-Green deformation tensor, respectively.

22.15

LS-NIKE2D COMMANDS AND MATERIALS LS-INGRID

22.16

LS-INGRID LS-NIKE3D COMMANDS AND MATERIALS

23. LS-NIKE3D Commands and Materials

Analysis options are code dependent. They can be set either in the control section of the LS-INGRID input file or in the graphics phase. These commands become active when

LS-NIKE3D output is selected with the NK3D command.

ANAL

BWMO

n

DCTOL tol

DELT

DTMAX

Dt

D

DTMN

d

ECTOL

GRAV

GSTIF

IPLT

LST

MSRF

tol

g x

g y

g z

on/off

n

tol

n

NBEI

n n

Analysis type

="STAT": static analysis (default)

="DYN": direct time integration

="DYNS": direct time integration with tatic initialization.

="EIGE": eigenvalue extraction.

Bandwidth minimization option.

="ON": perform minimization in analysis code (default).

="OFF": don't minimize bandwidth.

Convergence tolerance on displacements. LS-

NIKE3D defaults to 0.001.

Time step size for LS-NIKE3D.

Maximum step size permitted. If SSO =

"AUTO" the default is set by LS-NIKE3D.

Minimum step size permitted. If SSO =

"AUTO" the default is set by LS-NIKE3D.

Convergence tolerance on energy. LS-NIKE3D defaults to 0.01.

Gravity acceleration vector. The gravitational field is scaled in time by load curve one.

Geometric stiffness option. The default is off and generally gives the best results.

Node and element data dump interval for

TAURUS post-processing.

Line search tolerance.

Maximum number of stiffness reformations per time step. LS-NIKE3D defaults to the recommended value of 15.

The number of time steps between equilibrium iterations.

23.1

LS-NIKE3D COMMANDS AND MATERIALS

NBSR

n

LS-INGRID

The number of time steps between stiffness matrix reformation.

NEIG

n

NIBSR

n

Number of eigenvectors. This option turns on the subspace iteration eigenvalue/eigenvector solution method and overrides all other solution options. Eigenvectors are mass normalized and written into the graphics database. The time word corresponds to the frequency in radians/units of time.

Maximum number of equilibrium iterations permitted between stiffness matrix reformation.

LS-NIKE3D defaults to the recommended value of 10.

NIP1

NIP2

NSMD

s s n

First Newmark integration parameter.

Second Newmark integration parameter.

Nonlinear solution method.

= "BFGS": BFGS (default)

="BROY": Broyden's

="MODN": modified Newton

To obtain a linear elastic solution, NBSR and

NBEI should be larger than the number of time steps in the problem.

The default parameters for nonlinear solution methods are near optimal. If a problem is having trouble converging the fixes include decreasing the time step, adding dynamic effects, or trying to eliminate some of the nonlinearities.

NSTEP

RFTS

SBRF

SHIFT

n r n

w

Number of desired time steps.

Reduction factor for tangential stiffness. This is used for modeling the stick condition due to friction in the penalty formulation of contact.

Number of time steps between restart file generation. If zero, LS-NIKE3D writes a restart file as it terminates.

Shift frequency in hertz. This option works with the eigenvalue/eigenvector solution method.

Using this option, NIKE will find the NEIG eigenvalues nearest to w. If the model has rigid body modes, a negative value for w should be used to make the run stable. If w is exactly the same value as an eigenvalue the system becomes singular.

23.2

LS-INGRID

SSIT

SSO

SSOO

TEO

TERM

i t s u n

LS-NIKE3D COMMANDS AND MATERIALS

Slide surface insertion tolerance

Step size option.

"AUTO"

"MANUAL"

Optimal number of iterations per step.

Thermal effects option

= 0: no thermal effects.

=N: nodal temperatures are defined in input and are scaled according to a time function.

N is the load curve number.

=-1: at each time step a new temperature state is read from a disk file. The time word at the beginning of each temperature state is ignored.

=-2: at each time step a temperature state is interpolated from the temperature state in a disk file. Therefore the time words at the beginning of each temperature state is used.

= -3: the disk file containing temperatures has only one state. The initial state is assumed to be zero.

Terminate dynamic time integration at time t.

The dynamic time step size will be computed if this command is used instead of the "DELT" command.

23.1 LS-NIKE3D M

ATERIAL

I

NPUT

LS-NIKE3D material input is possible after the NK3D command has been input (see

Control Commands). The form of this input is: MAT n TYPE m {options specific to material type m} {general material options} ENDMAT. n is a material name which is assigned a number in the order that they occur in the input. Therefore, the materials should be defined in order before any additional use of materials is made.

23.3

LS-NIKE3D COMMANDS AND MATERIALS

Material Type 1 (Elastic)

Default heading: Material Type #1 (Elastic)

Input any two of the following.

BULK K

E E

G G

PR n

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

LS-INGRID

Material Type 2 (Orthotropic Elastic)

EA E

a

EB E

b

EC E

c

PRBA u ba

PRCA u ca

PRCB u cb

GAB G

ab

GBC G

bc

GCA G

ca

AOPT aopt

XP x

YP y

ZP z

A1 a

A2 a

A3 a

D1 d

p p p

1

2

3

1

See constitutive matrix below.

Material axes option (Figure 23-1).

=0.0: locally orthotropic with materials axes by element nodes n

1

, n

2

, and n

4

, (see Figure 23-1).

=1.0: locally orthotropic with materials axes by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

=3.0: SHELL ELEMENTS ONLY: The material axis is locally orthotropic with material axes determined by a vector in the plane of the shell and the shell normal.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

23.4

LS-INGRID

D2 d

2

D3 d

3

V1 v

1

V2 v

2

V3 v

3

LS-NIKE3D COMMANDS AND MATERIALS

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 3.

Define for AOPT = 3.

Define for AOPT = 3.

The material law that relates stresses to strains is defined as:

C

~

=

T

~

T

C

~

L

T

~

,

Where

\o(T,

~

) is a transformation matrix, and

\o(C,

~

)L is the constitutive matrix defined in terms of the material constants of the orthogonal material axes, a, b, and c. The inverse of

\o(C,

~

)L is defined as

C

−

1

~ L

=





















1

−

E a v ab

−

E a v ac

E a

0

0

0

0

0 v ab

Note that

E a

= v ba

,

E b v ca

=

E c v ac

,

E a v cb

=

E c v bc

.

E b

− v ba

E b

1

−

E v b bc

E b

0

− v ca

−

E c v cb

E c

1

E c

0

0

0

0

0

0

1

G ab

0

0

0

0

0

0

1

G bc

0

0

0

0

0

0

1

G ca





















23.5

LS-NIKE3D COMMANDS AND MATERIALS LS-INGRID c

(a)

b

n

4 n

1 n

2

AOPT=0.0 default

a d c

(c)

b

n

3

a

AOPT=2.0 define a and d

d a d

(b)

b c

z

v

(d)

v x n

y

x p

, y

p

, z

p

x

AOPT=1.0 d is parallel to the z-axis

n

shell element

AOPT=3.0

Figure 23-1.

Options for determining principal materials axes: (a) AOPT = 0.0, (b) AOPT

= 1.0, and (c) AOPT = 2.0.

23.6

LS-INGRID LS-NIKE3D COMMANDS AND MATERIALS

Material Type 3 (Kinematic/Isotropic Elastic/Plastic)

Default heading: Material Type #3 (Elastic-Plastic)

Input any two of the following:

BULK K

E

E

G G

PR n

Bulk modulus

Young's modulus

Shear modulus

Poisson's ratio

Additional Options:

SIGY s

y

ETAN E

t

BETA b'

NPTS n

Yield stress

Hardening modulus

Hardening parameter, 0 < b' < 1

Number of points on stress-effective plastic strain curve.

Effective stress.

Effective plastic strain.

ES s

y1

s

y2

... s

yn

EPS e

p1

e

p2

... e

pn

Isotropic, kinematic, or a combination of isotropic and kinematic hardening may be specified by varying b' between 0 and 1. For b' equal to 0 and 1, respectively kinematic and isotropic hardening are obtained as shown in Figure 23-2. Effective stress is defined in terms of the deviatoric stress tensor, S ij

as:

σ

=

(

3

2

S ij

S ij

)

1

2 where,

S ij

=

σ

ij

−

1

3

σ

kk

δ

ij

and effective plastic strain by:

ε p

∫ t

= d

ε

0 p where t denotes time and

d

ε

p

=

(

2

3

d

ε

p ij d

ε

p ij

)

1

2

23.7

LS-NIKE3D COMMANDS AND MATERIALS LS-INGRID

yield stress

E

E t

l n

( )

0

β=0 kinematic hardening

β=

1 isotropic hardening

Figure 23-2.

Elastic-plastic behavior with isotropic and kinematic hardening where l

0

and l are undeformed and deformed length of uniaxial tension specimen.

23.8

LS-INGRID

Material Type 4 (Thermo-Elastic-Plastic)

LS-NIKE3D COMMANDS AND MATERIALS

Default heading: Material Type 4 (Thermo-Elastic-Plastic)

NPTS n

TEMP T

1

T

2

...T

n

E E

1

E

2

...E

n

PR u

1

u

2

...u

n

ALPHA a

1

a

2

...a

n

SIGY s

y1

s

y2

...s

yn

ETAN E

t1

E

t2

...E

tn

Number of temperature values for which material constants are defined.

Temperatures

Young's moduli

Poisson's ratios

Coefficients of thermal expansion.

Yield stresses

Tangent moduli

Material Type 5 (Soil and Crushable Foam)

Default heading: Material Type 5 (Soil and Crushable Foam)

Input any two of the following:

BULK K

E E

G G

PR n

Additional Options:

AO a

0

A1 a

1

A2 a

2

PC P

c

UL uopt

NPTS n

VS e

v1

e

v2

... e

vn

P p

1

p

2

...p

n

Bulk modulus

Young's modulus

Shear modulus

Poisson's ratio

Yield function constant.

Yield function constant

Yield function constant

Pressure cutoff for tensile fracture

Unloading option

=0: volumetric crushing

=1: loading and unloading are the same.

Number of points in volumetric strain versus pressure curve (n£10).

Volumetric strain values

Pressures corresponding to volumetric strain values

The deviatoric yield function,

φ

, is described in terms of the second invariant J

2

.

23.9

LS-NIKE3D COMMANDS AND MATERIALS

J

2

=

1

2 s ij s ij

Pressure,

p, and constants a

0

, a

1

, and a

2

as:

φ =

J

2

−

[ a

0

+ a

1 p

+ a

2 p

2

]

.

On the yield surface,

J

2

=1/3(s y

)

1/2

, where s y

is the yield stress, i.e.,

σ y

=

[

(

0

+ a

1 p

+ a

2 p

2

)

]

1

2

LS-INGRID

For elastic-perfectly plastic behavior

a

1

=a

2

=0, and (3a

0

)

1/2

defines the yield strength. The volumetric strain is given by the natural logarithm of the relative volume V. If the pressure drops below the cutoff value, PC, then it is reset to that value.

pressure

Loading and unloading follows the input curve if the volumetric crushing option is off (Card 3, col. 61-70) hysteretic behavior for option 2

The bulk unloading modulus is used if the volumetric crushing option is on

(Card 3, col. 61-70) tension cutoff

Volumetric strain

Figure 23-3. Volumetric strain versus pressure curve for soil and crushable foam model.

23.10

LS-INGRID

Material Type 6 (Viscoelastic)

G G

0

GI G

´

K K

BETA b

LS-NIKE3D COMMANDS AND MATERIALS

Short term shear modulus.

Long term shear modulus.

Bulk modulus.

Decay constant.

The shear relaxation behavior is described by:

G(t) = G + (G

0

– G ) e

-

β t

A Jaumann rate formulation is used:

σ

∇

′ ij

=

2

∫ t

0

(

− τ

)

D ij

′

( ) dt where the prime denotes the deviatoric part of the stress rate,

σ

ij

, and the strain rate D

IJ

.

Material Type 7 (Thermal Orthotropic Elastic)

Default heading: Material Type #7 (Thermal Orthotropic Elastic)

See constitutive matrix below.

EA E

a

EB E

b

EC E

c

PRBA

υ

ba

PRCA

υ

ca

PRCB

υ

cb

ALPA

α

a

ALPB

α

b

ALPC

α

c

Thermal expansion coefficient along material axis a.

Thermal expansion coefficient along material axis b.

Thermal expansion coefficient along material axis c.

GAB G

ab

AOPT aopt Material axes option (Figure 22-1).

=0.0: locally orthotropic with materials axes determined by element nodes n

1

, n

2

, and n

4

,

(see Figure 22-1).

23.11

LS-NIKE3D COMMANDS AND MATERIALS LS-INGRID

=1.0: locally orthotropic with materials axes determined by a point in space and global location of element center.

RP r

ZP z

p p

PSIG

ψ

G

=2.0: globally orthotropic with materials axes determined by

ψ

G

.

Define for AOPT = 1.

Define for AOPT = 1.

In radians, define for AOPT = 2.

Material Type 8 (Thermo-Elastic-Creep)

Default heading: Material Type #8 (Thermo-Elastic-Creep)

NPTS n

TEMP T

1

T

2

...T

n

G G

1

G

2

...G

n

K K

1

K

2

...K

n

ALPHA a

1

a

2

...a

n

A a

1

a

2

...a

n

B b

1

b

2

...b

n

Number of temperature values for which material constants are defined.

Temperatures

Shear moduli

Bulk moduli

Coefficients of thermal expansion

Creep parameters

Creep parameters

In this model, G, is the shear modulus and the instantaneous creep is given by a power law of the form where a and b are functions of temperature. This model was developed and provided for LS-

NIKE3D by R. D. Krieg of Sandia National Laboratories.

Material Type 9 (Blatz-Ko Rubber)

Default heading: Material Type #9 (Rubber)

G

µ

Shear modulus

23.12

LS-INGRID LS-NIKE3D COMMANDS AND MATERIALS

The second Piola-Kirchhoff stress is computed as where V is the relative volume, C

ij is the right Cauchy-Green strain tensor, and n is the

Poisson's ratio which is set to .463 internally. This stress measure is transformed to the

Cauchy stress, s

ij

, according to the relationship

σ

ij

=

V

−

1

F ik

F jl

S kl

where F

ij

is the deformation gradient tensor.

Material Type 10 (Power Law Thermo Plasticity)

NPTS n

T T

1

T

2

...T

n

E E

1

E

2

...E

n

PR u

1

u

2

...u

n

K k

1

...k

n

M m

1

...m

n

Number of temperature points (£8).

Temperatures

Young's moduli

Poisson's ratios

See equation below

See equation below

The stress-strain curve for this model is based on the following equation:

σ

y

=

k(

ε

e

+

ε

p

)

n

Material Type 11 (Compressible Mooney-Rivlin Rubber)

This material model provides an alternative to the Blatz-Ko rubber model. The implementation is due to Maker [12].

A A

B B

PR n

Constant A.

Constant B.

Poisson's ratio.

The strain energy density function is defined as:

W=A(I-3)+B(II-3)+C(III

-2

-1)+D(III-1)

2

23.13

LS-NIKE3D COMMANDS AND MATERIALS

where

C=0.5A+B.

D

=

A(5

ν

−

2)

+

B(11

ν

−

5)

2(1

−

2

ν

) n=Poisson's ratio.

2(A+B)=G=shear modulus of linear elasticity.

I, II, III are invariants of the right Cauchy-Green Tensor.

LS-INGRID

Material Type 20 (Rigid Body)

All elements with the same material number become a single rigid body if the material is type 20 whether the elements are connected or not. Density and two independent material strength constants are required to establish penalties for contact surfaces and joints.

Input any two of the following:

BULK K

E E

G G

PR n

Additional Options:

LC lc

SCALE scale

VVEC v

x

v y

v z

Bulk modulus.

Young's modulus.

Shear modulus.

Poisson's ratio.

Load curve number for displacement control.

Scale factor.

Define the vector v for the direction cosines.

Material Type 23 (Thermal Orthotropic with Curves)

Number of points (1<NPTS<50).

NPTS npts

EA (E

a

)

1

... (E

a

) n

EB (E

b

)

1

... (E

b

) n

EC (E

c

)

1

... (E

c

) n

PRBA (n ba

)

1

... (n

ba

)

n

PRCA (n ca

)

1

... (n

ca

)

n

23.14

LS-INGRID

PRCB (n cb

)

1

... (n

cb

)

n

AA (a

a

)

1

... (a

a

)

n

AB (a

b

)

1

... (a

b

)

n

AC (a

c

)

1

... (a

c

)

n

GAB (G

ab

)

1

... (G

ab

)

n

GBC (G

bc

)

1

... (G

bc

)

n

GCA (G

ca

)

1

... (G

ca

)

n

AOPT aopt

LS-NIKE3D COMMANDS AND MATERIALS

XP x

YP y

ZP z

A1 a

A2 a

A3 a

V3 v

p p p

1

2

3

D1 d

1

D2 d

2

D3 d

3

V1 v

1

V2 v

2

3

Material axes option (Figure 23-1).

=0.0: locally orthotropic with materials axes determined by element nodes n

1

, n

2

, and n

4

,

(see Figure 23-1).

=1.0: locally orthotropic with materials axes determined by a point in space and global location of element center.

=2.0: globally orthotropic with materials axes determined by vectors defined below.

=3.0: SHELL ELEMENTS ONLY: The material axis is locally orthotropic with material axes determined by a vector in the plane of the shell and the shell normal.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 1.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 2.

Define for AOPT = 3.

Define for AOPT = 3.

Define for AOPT = 3.

23.15

LS-NIKE3D COMMANDS AND MATERIALS LS-INGRID

23.16

LS-INGRID TOPAZ COMMANDS AND MATERIALS

24. TOPAZ Commands and Materials

Analysis options are code dependent. They can be set either in the control section of the LS-INGRID input file or in the interactive phase. These commands become active when

TOPAZ2D or TOPAZ3D output is selected with the TZ2D or TZ3D commands respectively.

BWMO

n

DCMX

dt

DCTOL

DELT

tol

Dt

DTMAX

DTMIN

FLUX

Dt max

Dt min

n

IPLT

IPRT

IUNIT

LINEAR

MFTS

t

MRDI

MSRF

m n n n n

Bandwidth minimization option.

="ON": minimize bandwidth (default).

="OFF": don't minimize bandwidth.

Desired maximum temperature change in each time step above which the time step will decrease.

Convergence tolerance for equilibrium iterations

(default = 0.0001).

Time step size for fixed time step and initial time step for variable time step.

Maximum time step size.

Minimum time step size.

Nodal heat flux calculations

="ON": perform calculations

="OFF": don't perform calculations

(default).

Number of time steps between output of graphics database.

Number of time steps between output printouts.

Temperature units

="DIME": dimensionless

="CENT": centigrade

="FAHR": fahrenheit

="KELV": Kelvin

=."RANK": Rankine

Problem is linear.

Modification factor for increasing/decreasing time step.

Maximum number of radiosity iterations.

Maximum number of conductance matrix reformations per time step (default = 10).

24.1

TOPAZ COMMANDS AND MATERIALS

NBEI

n

LS-INGRID

The number of time steps between equilibrium iterations (default =1).

NBSR

n

NIBSR

n

The number of time steps between conductance matrix reformation (default = 1).

Maximum number of equilibrium iterations permitted per conductance matrix reformation.

NIP1

x

NONLINEAR

NSSD

n

First Newmark integration parameter.

(default = 0.5).

=1.0: fully implicit

Problem is non-linear.

Number of surface subdivision for radiation view factor calculation (default = 5).

PHASE

RADI

RBAND

n n m n

Phase charge flag

= "ON": perform phase change calculation

= "OFF": no phase change calculation

(default).

Radiation calculation type

= "VIEW": view factors

= "EXCH": exchange factors

Radiation bands. The number of wavelength break points is m and the number of curves is n.

Wavelength breakpoints

RCTOL

RELAX

SBC

r s

l

1

l

2

...l

m

(E

1

) l

(E

2

) l

...(E

m

) l

(E

1

) n

(E

2

)

n

...(E

m

)

n s

SBRF

n

SOLUTION STEADY

SOLUTION TRANSIENT

STEP

n

TERM

t

Emissivities for curve l

Emissivities for curve n

Radiosity convergence tolerance.

Relaxation parameter (default =1).

Stefan-Boltzmann constant.

Number of time steps between restart dumps.

Analysis is steady state.

Analysis is transient.

Time step code

="FIXE": fixed time step

="VARI": variable time step.

Final problem time.

24.2

LS-INGRID

TIMIN

t

TOPAZ COMMANDS AND MATERIALS

Initial problem time.

24.1 TOPAZ M

ATERIAL

I

NPUT

TOPAZ material input is possible after the TZ2D or TZ3D command has been input

(see Control Commands). The form of this input is: MAT n TYPE m {options specific to material type m} {general material options} ENDMAT. n is a material name which is assigned a number in the order that they occur in the input. Therefore, the materials should be defined in order before any additional use of materials is made.

Material Type #1 (Isotropic)

RO r

TLHA t

LH h

TGC lc

TGM r

HCP c

K k

ENDMAT

Material Type 2 (Orthotropic)

RO r

TLHA t

LH h

TGC lc

TGM r

HCP c

K1 k

1

K2 k

2

K3 k

3

ENDMAT

Density

Temperature at which latent heat is absorbed or released.

Latent heat.

Thermal generation rate curve number.

Thermal generation rate multiplier.

Heat capacity.

Thermal conductivity

End this material model.

Density

Temperature at which latent heat is absorbed or released.

Latent heat.

Thermal generation rate curve number.

Thermal generation rate multiplier.

Heat capacity.

Thermal conductivity in local 1 direction.

Thermal conductivity in local 2 direction.

Thermal conductivity in local 3 direction.

End this material model.

24.3

TOPAZ COMMANDS AND MATERIALS LS-INGRID

Material Type 3 (Isotropic Temperature Dependent)

RO r

TLHA t

LH h

TGC lc

TGM r

NPTS n

TEMP T

1

T

2

...T

n

CP C

1

C

2

...C

n

K K

1

K

2

...K

n

ENDMAT

Density

Temperature at which latent heat is absorbed or released.

Latent heat.

Thermal generation rate curve number.

Thermal generation rate multiplier.

Number of temperature points.

Temperatures.

Heat capacities

Thermal conductivities.

End this material model.

Material Type 4 (Orthotropic Temperature Dependent)

RO r

TLHA t

LH h

TGC lc

TGM r

NPTS n

TEMP T

1

T

2

...T

n

CP C

1

C

2

...C

n

K1 (K

1

)

1

(K

1

)

2

...(K

1

)

n

K2 (K

2

)

1

(K

2

)

2

...(K

2

)

n

K3 (K

3

)

1

(K

3

)

2

...(K

3

)

n

ENDMAT

Density

Temperature at which latent heat is absorbed or released.

Latent heat.

Thermal generation rate curve number.

Thermal generation rate multiplier.

Number of temperature points.

Temperatures.

Heat capacities

Thermal conductivities in local 1 direction.

Thermal conductivities in local 2 direction

Thermal conductivities in local 3 direction.

End this material model.

24.4

LS-INGRID ACKNOWLEDGMENTS

ACKNOWLEDGMENTS

Any work of this magnitude obviously was influenced by a large number of people who cannot possibly be given proper credit. The authors very much appreciate the all of the inputs whether positive or hostile which have aided in this work. The original work of Bill Cook on INGEN influenced LS-INGRID considerably. Special thanks must be given to Russ Rosinsky for his patience in finding bugs, recommending new capabilities and proof reading this manual. Steve

Sackett, Greg Kay, and Tracy Glover also helped in providing sample problems, new ideas, and uncovering bugs.

Developments at SPARTA benefited from David Lichtblau's and Brian

Wainscott's work on the calculator program. Sophie Tsui and Dawn Greayer made contributions to the materials processing portion and Bill Campbell provided some useful ideas for surface intersection algorithms. Sharon Kiefer made some important contributions in debugging and improving the manufacturing capabilities. The

NURB curve and surface algorithms were developed by Alan Winslow.

Eunice Hinkle, Nikki Falco, Valli A. James and Debbie Aiken all suffered through the preparation of various versions of this manual. The University of

Tennessee, Lawrence Livermore National Laboratory and SPARTA, Inc. all generously provided computer resources to allow LS-INGRID to be developed.

ACK.1

ACKNOWLEDGMENTS LS-INGRID

ACK.2

LS-INGRID REFERENCES

REFERENCES

[1] Hallquist, John O., "LS-NIKE2D User's Manual", LSTC Report 1006, 1990

[2] Hallquist, John O., "NIKE3D: An implicit, finite-deformation, finite element code for analyzing the static and dynamic response of three-dimensional solids", University of

California, Lawrence Livermore National Laboratory, UCID-18822, 1984.

[3] Hallquist, John O., "LS-DYNA2D User's Manual", LSTC Report 1004, 1990

[4] Hallquist, John O., "LS-DYNA3D User's Manual", LSTC Report 1007, 1990

[5] Shapiro, Arthur B., "TOPAZ2D - A three-dimensional finite element heat transfer code", University of California, Lawrence Livermore National Laboratory, Rept. UCID-

20484 (1985).

[6] Shapiro, Arthur B., "TOPAZ3D - A three-dimensional finite element heat transfer code", University of California, Lawrence Livermore National Laboratory, Rept. UCID-

20484 (1985).

[7] Cook, William A., "INGEN: A General Purpose Mesh Generator for Finite Element

Codes," Los Alamos Scientific Laboratory, Rept. LA-7135-MS (1978).

[8] Hallquist, John O., "LS-MAZE: An Input Generator for NIKE2D, DYNA2D, and

TOPAZ2D", LSTC Report 1005, 1990.

[9] Steinberg, D.J. and M.W. Guinan, "A High-Strain-Rate Constitutive Model for

Metals," University of California, Lawrence Livermore National Laboratory, Rept.

UCRL-80465 (1978).

[10] Woodruff, J.P. "KOVEC User's Manual," University of California, Lawrence

Livermore National Laboratory, Rept. UCRL-51079 (1973).

[11] Johnson, G.R. and W.H. Cook, "A Constitutive Model and Data for Metals Subjected to Large Strains, High Strain Rates and High Temperatures." Presented at the Seventh

International Symposium on Ballistics, The Hague, Netherlands, April 1983.

[12] Maker, B.N., Private communication, Lawrence Livermore National Laboratory.

[13] Kenchington, G.J.,"A Non-Linear Elastic Material Model for DYNA3D,

"Proceedings of the DYNA3D User's Group Conference, September 1988, published by Boeing Computer Services (Europe) Limited.

[14] Cochran, S.G., and J. Chan, "Shock Initiation and Detonation Models in One and

Two Dimensions," University of California, Lawrence Livermore National Laboratory,

[15] Lee, E.L., and C.M. Tarver, "A Phenomenological Model of Shock Initiation in

Heterogenous Explosives," University of California, Lawrence Livermore National

Laboratory, Rept. UCRL-83618 (1979).

REF.1

REFERENCES LS-INGRID

REF.2

LS-INGRID

Index

Acceleration Boundary

Condition

Applying 95

Accelerometer 13

Defining 95

Displaying 107

Advection Formulation

DYNA3D 169

Airbag

DYNA3D Ouput 170

Folding 18, 20, 111, 113

Inflator Model 13

Pentration Check 113

Sealing 114

Single Surface Contact

Algorithm 31

ALE Formulation

DYNA3D 170

ALE Smoothing

Applying 101

Analytical Contact 20

Angular Velocity

Initial 29, 68

Anisotropic Plasticity 226

Arbitrary Numbering

DYNA3D 167

Arrival Time

Pressure Load 11

Automatic Time Step

NIKE2D 255

AVS

TOPAZ 295

DYNA3D 170

Axisymmetry

NIKE2D 253

Bandwidth Minimization

NIKE2D 253

NIKE3D 273

TOPAZ 294

Batch Operation 12, 26

BCIZ Shell

DYNA3D 179

Beam

Area 177

Element Generation 63

Formulation 177

Moment of Area 178

Quadrature 178

Thickness 179

Belytschko-Lin-Tsay Shell

DYNA3D 179

Belytschko-Schwer Beam

DYNA3D 177, 179

Blatz-Ko Rubber

DYNA3D 191

NIKE2D 267

Boltzmann Constant

TOPAZ 295

Boundary Condition

Constraining 95

Displaying 109

Brick Formulation

DYNA3D 177

Brode Function

DYNA3D 167

Bulk Viscosity

DYNA3D 177

C0 Triangle

DYNA3D 179

CAL3D 20, 179

Repositioning Materials

35

Unit Conversions In

Coupling 168

Cap Model 214

Cardan Joint

Defining 19

Circular Arc

Standard Part 60, 61, 62

Coincident Node Removal 107

Commands

1 36

1A 101

1R 101

2 24, 36

2A 101

2R 102

A 14, 61, 157, 159, 196,

201, 217, 242, 266, 287,

290

A0 162, 203

A0F 162, 203

A1 149, 155, 162, 182,

188, 194, 203, 208, 210,

212, 216, 224, 227, 232,

235, 243, 262, 278, 284,

293

A10 245

A11 245

A12 245

A13 31, 245

A14 245

A1F 162, 203

A2 149, 155, 162, 182,

188, 194, 203, 208, 210,

212, 216, 224, 227, 232,

235, 243, 262, 278, 284,

293

A20 245

A21 245

A22 245

A23 15, 245

A24 245

A3 31, 182, 208, 210, 212,

216, 224, 227, 232, 235,

243, 278, 293

A30 245

A31 245

A32 245

A33 245

A40 245

A41 245

A42 245

A43 245

IND.1

INDEX

A5 31

A50 245

A51 245

A52 245

A53 245

A60 245

A61 245

A62 245

A63 245

A70 245

A71 245

A72 245

A73 245

AA 208, 211, 292

AB 208, 211, 292

ABSTAT 170

AC 62, 208, 211, 292

ACC 95

ACCE 13, 95

ACCI 95

ACE 62 acos 8

ADD 24

ADVECTION 169

AE 61, 248

AJNP 107

ALAB 117

ALE 170

ALPA 265

ALPB 265

ALPC 265

ALPH 209, 231, 234

ALPHA 148, 163, 187,

214, 228, 229, 245, 261,

266, 283, 287

AM 107

AMN 107

ANAL 253, 273

ANGL 20

ANGLES 177

AO 149, 188, 262, 284

AOPT 144, 182, 208, 210,

212, 216, 224, 227, 232,

235, 257, 265, 278, 293

AP 107, 248

AP23 15

ARBITRARY 167

ARRI 11

ARROW 107 asa 8

ASCII 107

ASCL 117

ASET 117 asin 8 ass 8

ASYM 28 atan 8 atan2 8

AUTO 63

AVEC 207

AVER 174

AVGN 125

AVSFLT 170

AXIS 16

INDEX

B 95, 96, 98, 100, 103,

157, 159, 196, 201, 217,

242, 266, 287, 290

B1 63, 162, 203, 243

B2 64, 243

BATCH 12

BCND 78

BCNR 78

BCOUT 170

BCSP 78

BE 248

BEAM 73, 177

BEAMS 79

BELT 12, 96, 170

BETA 146, 151, 157, 163,

185, 190, 196, 214, 225,

233, 245, 259, 264, 281,

286

BFORM 177

BG 63

BIAS 64

BIRTH 31

BLEN 125

BLND 129

BOND 31

BOXM 31

BOXS 31

BP 157, 196, 248

BPTOL 107

BQL 142, 177

BQQ 142, 177

BQT 142, 177

BRFORM 177

BRICKS 81

BRODE 139, 167

BRUL 167

BULK 143, 146, 149, 161,

181, 185, 188, 198, 199,

204, 205, 206, 207, 213,

218, 219, 220, 225, 226,

228, 229, 236, 237, 256,

259, 262, 268, 277, 281,

284, 288, 291

BUPD 168

BWMO 253, 273, 294

C001 221, 270

C010 221, 270

C020 221, 270

C1 241, 247

C100 221, 270

C101 221, 270

C110 221, 270

C2 241, 247

C200 221, 270

C210 221, 270

C23 15

C3 241, 247

C300 221, 270

C4 241, 247

C400 221, 270

C5 241, 247

C6 241, 247

CARDAN 19

CAREH 177

CC 163, 214

CCEN 107

CCOL 107

CE 248

CENT 107

CG 11

CHECK 173

CHORD 17

CHUE 107

CJ 21

CL 11, 139, 167

CMSO 174

CN 247

CN2P 129

CNV 13, 96

CNVI 96

CO 64, 241

COEF 139, 167, 228, 229,

245

COMP 31, 125

CONE 129

CONT 17, 107

COOR 16, 24, 41, 43, 45,

64, 75, 82, 87, 91, 93

COPY 125 cos 8 cosh 8

COSINE 11

COUPLE 20

CP 14, 15, 129, 139, 167,

248, 299, 300

CP23 15

CPL 64

CR 129, 133

CRX 129

CRY 129

CRZ 129

CSAT 107

CSCA 16, 137

CSE 96

CSEF 223

CSF 223

CSN 96

CSR 213

CSY 96

CSYI 96

CSYM 16

CT 139, 167

CUNI 168

CV 14, 15, 97

CVI 97

CVL 97

CYF 133

CYLI 24, 27, 41, 43, 45,

64, 75, 82, 91, 94, 129,

133

D 65, 107, 153, 163, 192,

214

D0 229

D1 137, 159, 182, 201,

208, 210, 212, 216, 224,

227, 232, 235, 278, 293

D2 137, 159, 182, 201,

208, 210, 212, 216, 224,

IND.2

LS-INGRID

DI DX 108

DI DY 108

DI DZ 108

DI EDR 108

DI EPB 108

DI F 108

DI FL 108

DI FLUX 108

DI FSYM 108

DI INTF 108

DI JOY 108

DI JTS 108

DI L3D 108

DI LAX 108

DI M 108

DI MCG 109

DI MK 109

DI NCV 109

DI NFG 109

DI NPB 109

DI NRB 109

DI NSF 109

DI NV 109

DI ORV 109

DI OUTL 109

DI P 109

DI PL 109

DI PM 109

227, 232, 235, 278, 293

D2R 168

D3 159, 182, 201, 208,

278, 293

D3HSP 168

D4 159, 201

D5 159, 201

DAMP 13, 31

DBQT 139, 168

DCMX 294

DCTOL 253, 273, 294

DEATH 31

DEBUG 168

DECAY 11

DEFAULT 16

DEFG 207

DEFGEO 170

DEFL 207

DEFORO 170

DELAY 12, 13

DELT 168, 253, 273, 294

DETP 16

DHGQ 139, 169

DHQT 139, 169

DI 65

DI ACCE 107

DI BELT 107

DI CNV 107

DI CSEC 107

DI CSYM 107

DI CV 108

DI CVL 108

DI D 108

DI DETP 108

DI DS 108

DI DSRM 108

LS-INGRID

DI PR 109

DI PV 109

DI RB 109

DI RBL 109

DI RBN 109

DI RE 109

DI REL 109

DI RX 109

DI RXN 109

DI RY 109

DI RZ 109

DI SBI 109

DI SFC 109

DI SI 110

DI SL 110

DI SPC 110

DI SPD 110

DI SW 110

DI SY 110

DI SYSJ 110

DI TB 110

DI TI 110

DI TRACER 110

DI VB 110

DI VECT 110

DI WARP 110

DIAD 110

DICOL 110

DIOFF 110

DIST 13

DISTANCE 13

DM 110

DMAX 13

DMEM 111

DMIN 13

DMN 111

DN2D 16

DN3D 16

DNIS 31

DNTS 31

DQL 140, 169

DQQ 140, 169

DRAG 87

DRAW 111

DRDB 174

DRFCTR 169

DROPTS 169

DRTERM 169

DRTOL 169

DS 16, 133

DSAD 111

DSF 117

DSRM 111

DSV 111

DSVS 111

DTMAX 253, 273, 294

DTMIN 294

DTMN 253, 273

DTS 117

DUMMY 31, 78, 79, 80,

81

DYNA3D 93

E 143, 146, 148, 149, 161,

181, 185, 187, 188, 198,

199, 204, 205, 206, 207,

213, 215, 218, 219, 220,

222, 225, 226, 228, 229,

230, 233, 236, 237, 256,

259, 261, 262, 268, 269,

277, 281, 283, 284, 288,

289, 291

E0 241, 242, 243, 244,

245, 247, 248, 250, 252

EA 144, 182, 208, 209,

211, 223, 231, 234, 257,

265, 278, 292

EAAU 215

EB 144, 182, 208, 209,

211, 223, 231, 234, 257,

265, 278, 292

EBBU 215

EC 144, 182, 208, 209,

211, 223, 231, 234, 257,

265, 278, 292

EC1 157, 196

EC2 157, 196

EC3 157, 196

EC4 157, 196

EC5 157, 196

EC6 157, 196

EC7 157, 196

EC8 157, 196

EC9 157, 196

ECCU 215

ECHO 168

ECO 157, 196

ECRV 206

ECTOL 253, 273

EDR 97

EH 155, 194, 198, 199,

204

EI 237

ELEMENT 23

ELLIPSE 179, 207

ELOUT 170

ELPLT 111

EMAX 221

EMIN 221

END 18, 41, 43, 45

ENDEOS 241, 242, 243,

244, 245, 247, 248, 250,

252

ENDMAT 297, 298, 299,

300

ENER 173

ENERGY 118

EOS 142, 177

EPB 97

EPS 155, 162, 194, 203,

213, 259, 281

EPSO 159, 201

EQSP 65

ER 129, 162, 203

ES 155, 162, 194, 203,

213, 259, 281

ET 218, 220, 225, 226

ETAN 146, 148, 162, 185,

187, 203, 206, 213, 259,

IND.3

INDEX

FFN 31

FFNE 31

FFS 31

FFSE 31

FIGN 19

FIND 65, 97

FL 97

FLEX 19

FLEXION 19

FLI 97

FLUID 169

FLUX 294

FMOV 20

FN 97

FNL 17

FNU 17

FOLD 111

FOPT 20

261, 281, 283

ETG 222

EULERIAN 170

EXIT 111 exp 8, 223

F 157, 196

FAIL 31, 213

FBRT 231, 234

FC 97, 268

FCI 97

FCRIT 248

FCRV 206

FD 31, 97

FDEF 18

FDI 97

FE 31

FEDL 12

FEM 17

FORM 78, 79, 80, 81

FP 199

FRAME 111

FRES 170

FRIC 12, 20, 27, 31

FRV 98

FS 32, 155, 194, 199, 204

FSG 222

FSYM 20

FT 98

FTB 98

FTBI 98

FTI 98

FUNC 17

FV 98

FVI 98

G 115, 143, 146, 149, 151,

152, 155, 157, 159, 161,

162, 163, 181, 185, 188,

190, 191, 194, 196, 198,

199, 201, 203, 204, 205,

206, 207, 213, 214, 218,

219, 220, 225, 226, 228,

229, 236, 237, 248, 256,

259, 262, 264, 266, 267,

268, 277, 281, 284, 286,

287, 288, 291

GA 32

INDEX

GAB 144, 182, 208, 209,

211, 223, 231, 234, 257,

265, 278, 292

GABU 215

GAM0 230

GAMA 157, 196

GAMM 15

GAMMA 163, 214, 244,

250, 252

GAMO 157, 196

GBC 182, 208, 209, 211,

223, 231, 234, 278, 292

GBCU 215

GCA 182, 208, 209, 211,

223, 231, 234, 278, 292

GCAU 215 gcd 8

GEFORO 170

GELN 129

GELS 130

GEOC 20, 98

GEOM 140, 253

GFUN 139, 167

GI 151, 190, 264, 286

GLSTAT 170

GMI 21

GMPRT 170

GN 34

GRAV 14, 15, 140, 171,

253, 273

GRID 17, 111

GS 130

GS1 130

GS2 130

GSM 130

GSN 130

GSTIF 253, 273

GTIME 117

H 157, 196, 248

HC 228, 229

HCP 159, 201, 297, 298

HDMG 32

HEAD 142, 177

HEIGHT 139, 167

HGENERGY 171

HGQ 142, 177

HGQT 142, 177

I 59, 65, 248

IARB 171

IDEA 41

IEP 34

IFDT 174

IJ 60

IJK 60

IKEDIT 168

IMGL 142, 178

IN 98

INC 98, 100, 103

INCLUDE 21, 78, 79, 80,

81

INFO 111

INI 98

INSIDE 20

INT 65

KINETIC 118

KU 250

L 111, 137

L2D 125

L3 130

L3D 17, 20, 23, 125

L3E 17

L3P 130

L3R 130

L3S 130

L3V 111

L3VS 111

LABELS 23

LAD 121, 125

LADD 121, 125

LADV 121

LAGRANGIAN 170

LAP 121

LAR 121

LAT 121

LBCV 125

LBCX 125

LBCY 125

LBCZ 125

LC 15, 233, 268, 291

LC1 19, 20

LC2 19

LC3 19

INT4 175

INT8 175

INTERNAL 118

IOPT 222

IPLT 253, 273, 294

IPRT 294

IRDMS 171

IRR 178

IRULE-TRAPEZOIDAL

178

IRULE-USER 178

IRULE.GAUSS 178

IS 98

ISI 98

ISS 178

IT 159, 201

ITSS 140, 171

ITT 178

IUNIT 294

J 59, 65

JD 21

JK 60

JOINTS 170

JOY 98

JOYI 98

JT 98

K 60, 65, 78, 79, 80, 81,

151, 161, 163, 190, 205,

209, 214, 231, 234, 237,

264, 266, 268, 269, 286,

287, 288, 289, 297, 299

K1 298, 300

K2 298, 300

K3 298, 300

KAPPA 228

KI 60

IND.4

LS-INGRID

LC4 19

LC5 19

LC6 19

LCA 215

LCAB 215

LCB 215

LCBC 215

LCC 121, 215

LCCA 215

LCD 23, 27

LCDAMP 171

LCDF 23

LCGX 171

LCGY 171

LCGZ 171

LCK 237

LCL 12, 238 lcm 8, 14, 15, 237

LCMAX 171

LCOUTF 15

LCP 12, 162, 203

LCR 162, 203

LCRX 171

LCRY 171

LCRZ 171

LCSS 226

LCU 12, 238

LCUT 126

LCV 27, 32, 111

LD 23, 121

LE 34

LEP 122

LEV 24

LEXP 122, 126

LFOR 126

LH 297, 298, 299, 300

LIGHT 111

LIMIT 221

LINE 11

LINEAR 294

LINT 122, 126

LLCM 126

LMI 24

LMIN 111 ln 8 ln10 8 ln2 8

LNPT 16, 38

LNV 250, 252

LO 122

LOCK 13

LOD 122

LORI 65

LP 122, 126

LPIL 122

LPN 126

LPRJ 126

LPS1 219

LPS2 219

LPT 122

LPT1 219

LPT2 219

LPTA 122

LREP 41, 43, 46, 65, 75,

LS-INGRID

82, 87, 92, 94

LREV 126

LRL 122

LRNV 127

LRNX 126

LRNY 126

LRNZ 126

LROT 122, 127

LS 32, 117

LSCA 122

LSCR 123

LSCZ 123

LSIZE 111

LST 253, 273

LSTL 123

LSYS 24, 25

LT 123

LTAS 123

LTBC 123

LTBO 123

LTMN 178

LTMX 178

LTP 123

LTS 117

LTYPE 163, 214

LV 34, 111

LVC 123

LVI 111

LVS 111

LVT 127

LVTB 127

M 112, 159, 161, 201,

205, 237, 248, 268, 269,

288, 289

MA 66

MASS 27

MAT 23, 25, 142, 170,

178

MATE 13, 20, 25, 42, 44,

46, 66, 82, 92, 94, 174

MATERIAL 38, 79, 80,

81

MATERIAL MAST 32

MATERIAL SLAV 32

MATM 19

MATRIX 137

MATS 19

MATSUM 170 max 8

MAXS 32

MAZE 36

MAZT 25

MB 66

MCOL 112

MDBC 25

MDMP 178

MERGE 32

MESH 207

MEXP 116

MFBC 25

MFTS 294 min 8

MINIMUM 238

MK 99

159, 196, 201, 237

N+ 99

N- 99

N1 63, 79, 80, 81

N2 63, 79, 80, 81

N3 79, 80, 81

N4 80, 81

N5 81

N6 81

N7 81

N8 81

NASTRAN 45

NBEI 254, 273, 294

NBSR 254, 273, 295

NC 21

NCAD 112

NCFORCE 170

NCPU 171

NCRM 112

NCV 112, 130

NCYCLES 170

NDIV 29

NDPLT 112

NE 34

NEIG 254, 274

NEWC 171

NEXP 116, 229

NFAIL 32

MK+ 99

MK- 99

MKDS 25

MKI 99

MKI+ 99

MKL 99

MLOC 116

MMASS 112

MMOV 116

MN 112

MOMENTUM 118

MOVE 17, 20, 87

MOVIE 170

MPGS 170

MPLT 112

MPS 268

MRDI 294

MS 66

MSCA 32

MSEL 116

MSIZ 112

MSLAV 207

MSRF 253, 273, 294

MSS 268

MSYS 19

MT 63, 67

MTHI 32

MTI 67

MTV 67

MU 14, 154, 193

MVBC 25

MVMA 171

MX 137

MY 137

MZ 137

N 95, 96, 98, 99, 103, 157,

IND.5

INDEX

NFG 25, 99, 170

NFGI 99

NGEN 63

NI+ 99

NI- 99

NIBSR 254, 274, 295

NIP 25

NIP1 254, 274, 295

NIP2 254, 274

NK2D 25

NK3D 26

NO 64

NODE 23, 24

NODES 78, 79, 80, 81

NODOUT 170

NOFRAME 112

NOGRID 112

NOMERGE 32

NONLINEAR 295

NOPL 26

NOTE 26

NPB 99

NPLOT 163, 214

NPTS 148, 149, 155, 162,

168, 174, 187, 188, 194,

203, 211, 213, 227, 236,

250, 252, 259, 261, 262,

266, 269, 281, 283, 284,

287, 289, 292, 299, 300

NRB 99

NRBI 99

NRCYCK 169

NSAD 112

NSET 112

NSF 130

NSFN 130

NSMD 254, 274

NSMO 26

NSRM 112

NSSD 295

NSTEP 172, 254, 274

NSV 112

NSWS 32

NTIME 117

NUMBER 78, 79, 80, 81

NURB 29

NV 34

OFFSET 173

OLAB 117

OLD 36, 77

OMEGA 242

OPIFS 172

OR 67

ORDER 67

ORIE 173

ORV 26, 99, 103

OSCL 117

OSET 117

OUTSIDE 20

OVERLAY 112

OVERRIDE 27

P 95, 96, 98, 100, 103,

112, 149, 155, 162, 188,

194, 203, 284

INDEX

P0 14, 230

P1 63, 127

P2 63, 127

P3 127

PA 68, 230

PARAM 227

PART 85

PASS 172

PATRAN 43

PAUSE 26

PB 68, 230

PC 149, 154, 155, 157,

159, 188, 193, 194, 196,

201, 230, 250, 252, 262,

284

PCHK 112

PCJ 153, 192

PCOL 113

PD 36

PE 14, 15

PER 162, 203

PERCENT 172

PEXP 116

PEXT 15

PFOLD 113

PHASE 295

PHI 230

PHIF 19

PHIS 19

PINF 113

PINI 15

PINT 15, 127

PJ 21

PL3 130

PLAN 131

PLANE 11, 24, 26, 27,

179, 207

PLOC 116

PLTI 140, 172

PM 100

PMASS 113

PMOV 116

PNLM 32

PNLS 32

PNLT 20, 21, 32

PO 64, 96, 97, 99, 127

POFF 103

POINT 16, 38

POLY 131

PON 103

POOR 113

PPLV 28

PPOP 16

PPRJ 127

PR 100, 131, 143, 146,

148, 149, 161, 162, 181,

185, 187, 188, 198, 199,

203, 204, 205, 206, 207,

213, 215, 217, 218, 219,

220, 222, 225, 226, 228,

229, 236, 237, 256, 259,

261, 262, 268, 269, 277,

281, 283, 284, 288, 289,

290, 291

PRBA 144, 182, 208, 209,

211, 223, 231, 234, 257,

265, 278, 292

PRCA 144, 182, 208, 209,

211, 223, 231, 234, 257,

265, 278, 292

PRCB 144, 182, 208, 209,

211, 223, 231, 234, 257,

265, 278, 292

PRE 102

PRELOAD 12

PRETENSIONER 12

PRI 100

PRINT 28, 113

PRISM 27

PRL 100

PROD 24

PROJ 18

PRTI 140, 172

PSCA 13

PSCALE 28

PSEL 116

PSIF 19

PSIG 144, 257, 265

PSIS 19

PSLV 28

PSOPT 174

PSPO 172

PSRGB 113

PT 250, 252

PTOL 113

PULL 12

PV 113

PVS 113

PYROTECHNIC 12

QUAD 20, 28

QUADRATURE 178

QUIT 113

R 113, 159, 163, 201, 214,

219, 226

R1 242

R1E 248

R1P 248

R2 242

R2D 172

R2E 248

R2P 248

RA 96

RADI 295

RADIUS 32

RANG 139, 167

RATE 13

RAYD 178

RB 100

RBAND 295

RBI 100

RBMG 28

RBN 101

RBOUT 170

RC 21

RCFORC 170

RCTOL 295

RDENERGY 172

RDMT 140, 172

IND.6

LS-INGRID

RDSI 140, 172

RE 101

RE+ 101

RE- 101

READ 29

RECT 133

REDUCE 82, 113

REFP 113

REGION 36

REIN 172

RELAX 295

RELAX1 170

RELAX2 170

RELAX3 170

RELAX4 170

REP 117

REPE 21, 24, 42, 44, 46,

68, 75, 82, 87, 92, 94, 137

REPO 179

RES 68, 87

RESO 113

REST 68, 113, 140, 172

RETR 12, 13

RETRACTOR 12

REVERSE 13

REZO 140

RFTS 254, 274

RHO 14, 15

RHVC 140, 172

RIRDMS 172

RJ 21

RLBV 140, 173

RLN 123

RLNS 123

RLX 113

RLY 113

RLZ 113

RM 113

RMN 113 rnd 8 rnd2 8

RNUM 140, 173

RO 96, 97, 99, 142, 179,

238, 297, 298, 299, 300

ROTA 34, 42, 44, 46, 75,

82, 87, 92, 94

ROTATION 29, 68

RP 114, 144, 257, 265

RPLT 140, 173

RPRT 140, 173

RQBV 140, 173

RR 68

RTERM 141, 173

RTSF 141, 173

RVBC 29

RWFORC 170

RWPNAL 173

RX 114, 137

RXN 101

RXNI 101

RXY 137

RY 114, 137

RYZ 137

RZ 114, 137

LS-INGRID

RZX 137

S 117

S1 244

S2 244

S3 244

SA 157, 196, 244

SAREA 179 sas 8

SAVE 68, 137

SBC 295

SBI 101

SBRF 141, 173, 254, 274,

295

SC 63, 101, 185, 205, 209,

225, 231, 234

SC03 29

SCAL 14, 15, 103

SCALE 114, 137, 291

SCOL 114

SD 20, 30, 133

SDMV 30

SEAL 114

SEAL CIRCLE 114

SEAL OFF 114

SEAL OUTLINE 114

SECFORCE 170

SECTION 28, 79

SEGMENT 179

SENSOR 12, 13

SEPARATE 175

SEQUENTIAL 173

SETS 32

SF 69, 234

SFAIL 32

SFC 102

SFE 69

SFEI 69

SFI 69

SFORM 179

SFS1 219

SFS2 219

SFSI 141, 173

SFT1 219

SFT2 219

SFV 69

SFVI 69

SHELL 179

SHELLS 80

SHIFT 254, 274

SHRINK 114

SI 31, 102, 117

SI+ 102

SI- 102

SIDB 170

SIGF 162, 203

SIGM 157, 196

SIGO 157, 196

SIGY 146, 148, 155, 162,

185, 187, 194, 198, 199,

203, 204, 206, 213, 215,

218, 220, 225, 226, 259,

261, 281, 283

SII 102

SII+ 102

SSCA 32

SSIT 254, 274

SSO 255, 274

SSOO 255, 274 sss 8

SSYS 19

STACK 87

STANDARD 36

START 56, 170

STEP 295

STHI 32

STHICK 179

STOL 35

STONE 28

STOP 35, 114, 170

STOPA+ 19

STOPA- 19

STOPB+ 19

STOPB- 19

STOPC+ 20

STOPC- 20

STYP 174

SUPP 168

SV 32

SW 103

SWENERGY 174

SWFORC 171

SWI 103

SII- 102

SIJ 60 sin 8

SINGLE 32 sinh 8

SINT 127

SIOPT 173

SIZE 114

SJ 21

SJK 60

SKI 60

SL 32, 102

SLIPRING 12

SLOC 179

SLVM 35

SO 64

SOFT 231, 234

SOLUTION STEADY

295

SOLUTION

TRANSIENT 295

SP 131, 185, 205, 225,

244

SPACE 38

SPALL 157, 196

SPC 102

SPCFORC 170

SPCI 102

SPD 34

SPDP 103

SPHE 24, 27, 42, 44, 46,

70, 75, 83, 92, 94, 133

SPIN 87

SPRING 12, 13

SR 234

SRUL 174

IND.7

INDEX

SYG 222

SYMM 28

SYNTAX 36

SYSD 174

SYSEND 37

SYSJ 103

SYSTEM 37, 104, 179,

207

T 78, 114, 163, 214, 228,

229, 269, 289

T0 248

T1 131

T10 32

T11 33

T12 33, 37

T13 33, 37

T14 33

T15 33

T16 33

T17 33

T18 33

T19 33

T2 131

T20 33 tan 8 tanh 8

TAURUS 117, 174

TBI 33

TBO 139, 167

TCO 34

TCRS 33

TCRV 206

TCYCLE 175

TDEL 206, 213

TEMP 37, 42, 44, 46, 70,

76, 83, 87, 92, 94, 148,

187, 261, 266, 283, 287,

299, 300

TENSION 233

TEO 141, 175, 255

TERM 141, 175, 255, 275,

295

TFAIL 231, 234

TGC 297, 298, 299, 300

TGM 297, 298, 299, 300

TH 104

THEF 20

THES 20

THETA 163, 214

THI 104

THIC 37, 42, 44, 46, 70,

83, 92, 94

THICK 87

THICKNESS 80

THIN 174

TIED 33

TIME 12, 13, 16, 38

TIMIN 295

TIN 14, 15

TIND 37

TINE 37

TINT 175

TINV 141, 175

TIVE 37

INDEX

TJ 21

TLHA 297, 298, 299, 300

TLOC 179

TM 104, 159, 201

TMASS 114

TMCG 37

TMI 104

TMM 37

TMSM 37

TMVP 38

TN 104

TNI 104

TO 157, 159, 196, 201

TOFF 11

TOTAL 118

TP 114

TRACER 38

TRACER t Tracer particle file..i.Tracer

Particles 171

TRANS 38

TRI2 70, 87

TRIA 70, 88, 133

TRIAD 114

TRPT 114

TS 131

TS2P 131

TSF 223

TSHELL 179

TSLIMIT 175

TSORT 175

TSSF 175

TSSFDR 169

TSTEP 168

TTHICK 179

TTIME 115

TUPD 175

TV 115

TYPE 13, 142, 180

TZ2D 38

TZ3D 38

U 115

UDEF 117

UJ 21

UL 188, 262, 284

ULD 188

UNLOAD 233

UPDATE 115

V 137

V0 241, 242, 243, 244,

245, 247, 250, 252

V1 182, 208, 210, 212,

224, 227, 232, 235, 278,

293

V2 64, 182, 208, 210, 212,

224, 227, 232, 235, 278,

293

V3 182, 208, 210, 212,

224, 227, 232, 235, 278,

293

V90 176

V91 176

V92 176

V93 176

VARIABLE 171

VC 236

VD 38

VDA 207

VE 34, 104

VEC 176

VEC92 176

VECDYNA 93

VECTOR 26

VELO 11, 42, 44, 46, 76,

83, 88, 92, 94

VELOCITY 27, 39, 70

VEOS 115

VF 215

VFRI 33

VIEW 115

VINI 14

VO 64

VOLT 15

VS 149, 188, 262, 284

VSCA 14

VTSP 70

VVEC 207, 291

WARP 176

WBGR 115

WBIF 115

WECE 248

WEDGE 176

WPCP 248

WRDB 115

WRITE 38

WTDB 115

X 13, 78, 248

X0 163, 214

XBO 139, 167

XF 17

XLE 17

XOFF 38

XP 182, 208, 210, 212,

216, 224, 227, 232, 235,

278, 293

XSCA 38, 137

XSYM 18

XT 209, 231, 234

XVEL 118

Y 13, 78, 248

YBO 139, 167

YC 209, 231, 234

YF 17

YLD 139, 167

YLE 17

YOFF 39

YP 182, 208, 210, 212,

216, 224, 227, 232, 235,

278, 293

YSCA 39, 137

YSYM 18

YT 209, 231, 234

YVEL 118

Z 13, 78, 248

ZBO 139, 167

ZF 17

ZIN 115

ZLE 17

IND.8

LS-INGRID

ZOFF 39

ZOUT 115

ZP 144, 182, 208, 210,

212, 216, 224, 227, 232,

235, 257, 265, 278, 293

ZSCA 39, 137

ZSYM 18

ZVEL 118

Component Interface

Defining 98

Composite

Angles 177

Damage Model 231

Plasticity Based Damage

234

Contact Interface

Defining 31

Displaying 110

DYNA3D Options 173

Eroding 33, 171

Geometric 20

Rigid Wall 27

Segment Selection 102

Slave Nodes 102

Control Volume

Defining 96

Definition 13

Displaying 107

Convection Boundary

Condition

Applying 97

Displaying 108

Convergence Tolerance

TOPAZ 294

Coordinate transformations 16

Copying Part 24

Creep

DYNA3D 237

NIKE2D 266

NIKE3D 287

Cross Section

Displaying 107

Crushable Foam

DYNA3D 188, 200

NIKE2D 262

NIKE3D 284

Cyclic Symmetry

Defining 16, 96

Displaying 107

Cylindrical Joint 21

Damper 34

Defining 103

Displaying 110

Damping

Material 178

Density

DYNA3D 179

Detonation Point 16

Displaying 108

Digitized Surface

Defining 17

Displaying 111

Saving 25

Directives 9

LS-INGRID

Discrete Mass

Defining 100

Displacement Boundary

Condition

Applying 97

Displaying 108

Rigid Body 25

Displacement Convergence

Tolerance

NIKE2D 253

NIKE3D 273

Display Options

Color Selection 110

Overlaying 110

Removal 110

Duplicate Node Removal 113,

114

DYNA3D

Airbag Statistics 170

ASCII Output Files 170

Beam Integration Rule

167

Brode Function 167

Bulk Viscosity 168, 169

CAL3D Coupling 168

Centrifugal Load 171

Comments 26

Contact Penalty 173

D3HSP 168

Damping 174

Dynamic Relaxation 169

Full Restart 170

Gravity Load 171

Hourglass Control 169

Hourglass Energy 171

Importing Files 93

Initial Time Step 171

MADYMO Coupling 168

Mass Scaling 169, 172

Maximum Time Step 171

Minimum Time Step 175

Output Control 168

Parallel Processing 172

Plane Stress Plasticity

Option 172

Rayleigh Damping 179

Rayleigh Damping Energy

Dissipation 172

Restart 173

Rigid Wall Penalty 173

Shell Formulation 174

Shell Integration Rule 174

Shell Thickness Updates

175

Stone Wall Energy

Dissipation 174

System Damping 171

TAURUS Database Save

Interval 172

Termination Cycle 175

Termination Time 175

Time Step 169

Time Step Scale Factor

175

Eigenvalue Extraction

NIKE2D 254

NIKE3D 274

Elastic Material

DYNA3D 181

Elasticity

NIKE2D 256

Element Delete on Restart

Displaying 108

Element Number

Displaying 111

Shifting 23

Element Print Block

Defining 97

Displaying 108

Element Shrink Plots 114

Emmisivity Curves

TOPAZ 295

Energy Convergence

Tolerance

NIKE2D 253

NIKE3D 273

Equation-of-State

Gruneisen 244

Ignition and Growth of

Reaction 248

JWL 242

Linear Polynomial 241

Linear Polynomial with

Energy Leak 247

Ratio of Polynomials 245

Sack Tuesday High

Explosive 243

Tabulated 252

Tabulated Compaction

250

Equipotential Relaxation 170

Eulerian Formulation

DYNA3D 170

Explosive

JWL Burn Model 242

Material 192

Reactive Burn Model 249

Sack Burn Model 243

Failing Symmetry Plane

Defining 20

Displaying 108

Failure

Tied Nodal Group 97

Fixed Nodes

Displaying 108

Flexion-Torsion Joint

Defining 19

Fluid

DYNA3D 169

Flux Boundary Condition

Applying 97

Displaying 108

Foam 233

Folding 20

Force Load

Applying 97

Displaying 108

Frazer-Nash Rubber

IND.9

INDEX

NIKE2D 270

Free-Form Surface 17

Friction Reduction Factor

NIKE2D 254

Geological Cap Model 214

Geological Material

DYNA3D 203

Geometric Contact 20

Identifying Slave Nodes

98

Geometric Stiffness

NIKE2D 253

NIKE3D 273

Graphics

Device Selection 115

Gravity Load

DYNA2D 140

DYNA3D 171, 178

NIKE2D 253

NIKE3D 273

Heat Conduction

TOPAZ 297, 299

Heat Flux

TOPAZ 294

Hourglass

Energy 171

Hourglass Control

DYNA3D 177

Hughes-Liu Beam

DYNA3D 177

Hughes-Liu Shell

DYNA3D 179

Importing

DYNA3D Files 93

NASTRAN Files 45

PATRAN Files 43

SDRC Files 41

Include File 21

Directory 16

Initial Time Step

TOPAZ 295

Interactive Model Updates 115

Intrinsic functions 8

Isoparametric Relaxation 170

Johnson/Cook Material

Joint

DYNA3D 201

Defining 21, 98

Displaying 108

Joints 170

JOY Interface Node

Defining 98

Displaying 108

Kikuchi Relaxation 170

Line Definition

Displaying 111

Three-dimensional 23

Two-dimensional 23

Line Search Tolerance

NIKE2D 253

NIKE3D 273

LLNL-INGRID Compatibility

36

Load Curve 23

INDEX

Displaying 111

Local Axes

Displaying 108

Specifying 67

Local System

Defining 24

LS-DYNA2D 16

LS-DYNA3D 16

LS-DYNA3D Version 902 176

LS-DYNA3D Version 910 176

LS-DYNA3D Version 920 176

LS-DYNA3D Version 930 176

LS-NIKE3D 26

MADYMO3D 20, 179

Repositioning Materials

35

Unit Conversions In

Coupling 168

Marked Surface

Defining 99

Displaying 109

Mass Property

Displaying 109, 112

Input 37

Material Subset 112

Part Subset 113

Total 114

Mass Scaling

DYNA3D 172

Masses 109

Material

Data Input 25

Display 107

Displaying 110, 112, 113

Heading 177

Highlighting 109

Increments 21

Label Increment 24

Maximum Time Step

NIKE2D 253

TOPAZ 294

Maze Part

Tolerance 25

Membrane

DYNA3D 179

Metallic Honeycomb 215

Minimum Time Step

NIKE2D 253

TOPAZ 294

Mooney-Rivlin Rubber

NIKE3D 290

MOVIE.BYU

DYNA3D 170

MPGS

DYNA3D 170

MVMA-DYNA3D 171

NASTRAN

Importing Files 45

Newmark Integration

Parameters

NIKE2D 254

NIKE3D 274

TOPAZ 295

NIKE2D 25

NIKE3D 273

Nodal Constraint 21

Defining 98

Nodal Force Group

Defining 25

Displaying 109

Specifying 99

Nodal Print Block

Defining 99

Displaying 109

Nodal Rigid Body

Defining 101

Displaying 109

Node Number

Displaying 112

Shifting 23

Nodes Slave To Rigid Body

Displaying 109

Non-Reflecting Boundary

Condition

Displaying 109

Specifying 99

Null Material

DYNA3D 193

Number of Time Steps

NIKE2D 254

NURB Curve

Displaying 109, 112

NURB Surface 29

Displaying 109, 112

Orientation

Arrow Display 107

Orientation Vector

Displaying 109

Specifying 99

Orientation Vectors 26

Orthotropic Elastic

NIKE2D 257, 265

NIKE3D 278

Orthotropic Elastic Material

DYNA3D 182

Orthotropic Heat Conduction

TOPAZ 298, 300

Orthotropic Shell

Local Axes 65

Parallel Processing

DYNA3D 171, 172

Parametric surface 18

Part

Copying 24

Displaying 114

Highlighting 109

PATRAN

Importing Files 43

Pause Operation 26

Phase Change

TOPAZ 295

Planar Joint 21

Plane Strain

NIKE2D 253

Plane Stress

NIKE2D 253

Plastic Hydrodynamic Material

194

IND.10

LS-INGRID

Plastic Material

DYNA3D 185, 198, 199,

204, 205

Plasticity

NIKE2D 259

NIKE3D 281

Plot Interval

NIKE2D 253

NIKE3D 273

TOPAZ 294

Power Law Plasticity

NIKE2D 268

NIKE3D 288

Pressure Load

Applying 100

Arrival Time 11

Displaying 109

Pretensioner 12

Print Interval

TOPAZ 294

Printing

Calculator Result 28

Quadratic Element 28

Radiation

TOPAZ 295

Radiation Boundary Condition

Applying 100

Displaying 109

Radiation Enclosure

Defining 101

Displaying 109

Radiosity Convergence

Tolerance

TOPAZ 295

Rayleigh Damping

DYNA3D 179

Energy Dissipation 172

Reaction Force

DYNA3D 170

Reinforced Concrete 32

Restart

DYNA3D 170, 172, 173

Element Deletion 97

NIKE2D 254

TOPAZ 295

Resultant Force Cross Section

Defining 96

Retractor 12

Defining 96

Revolute Joint 21

Rigid Body

Center Of Gravity 37

Displacement Boundary

Condition 25

Extra Node 101

Inertia 37

Initial Velocity 37

Merging 28

Moving Properties 38

NIKE3D 291

Total Mass 37

Velocity Boundary

Condition 25, 29

Rigid Material

LS-INGRID

DYNA3D 207

Rigid Wall 27

Rotational Velocity

Initial 75, 83, 87

Rubber

DYNA3D 191

SALE Advection 169

Scaling coordinates 16

Screen Movement

Left 107, 111

Restoring Original View

113

Right 113

Rotation 113, 114

Scaling 114

SDRC Ideas 41

Seat Belt 12

Defining 96

Displaying 107

Seat Belts 170

Section Property

Scaling 28

Sensor 12

Defining 96

Shell

Displaying Free Edge 109

Displaying Normal

Vectors 109

Displaying Warpage 110

Formulation 179

Integration Rule 178

Orientation 99

Property Numbers 104

Quadrature 178

Reference Fiber 179

Thicknesses 70, 104

Triangular 70, 88

User Integration Rule 178

Shell/Brick Interface

Displaying 109

Shift Frequency

NIKE2D 254

Single Point Constraint

Applying 95, 103

Displaying 110

Slide Line

Applying 102

Displaying 110

Sliding Interface

Applying 102

Defining 31

Displaying 110

DYNA3D Options 173

Insertion Tolerance 254,

274

Slipring 12

Defining 96

SMUG 170

Soil

NIKE2D 262

NIKE3D 284

Solution Method

NIKE2D 253

Spherical Joint 21

Spotweld 21

Spring 34

Defining 103

Displaying 110

Standard Part

Mesh Smoothing 63

Steady State Solution

TOPAZ 295

Steinberg Material

DYNA3D 196

Stone Wall 27

Displaying 110

Energy Dissipation 174

Identifying Slave Nodes

103

Substructure Interface

Displaying 108

Surface

Applying To Mesh 69

Definition 30

Digitized 17

NURB 29

Smoothing 26

Symmetry Plane 27

Displaying 110

Failing 20

System Assembly

Joint Definition 103

System Name 37

Viewing Assembly Points

110

Viewing Systems 114

System Damping

Control volume 13

DYNA3D 171, 174

TAURUS

Creating Database From

INGRID 115

Temperature Boundary

Condition

Applying 98

Displaying 110

Temperature Initial Condition

37, 42, 44, 46, 70, 76, 83, 87,

92, 94

Displaying 110

Termination Time

NIKE2D 255

TOPAZ 295

Thermal Effect

DYNA2D 141

DYNA3D 175

NIKE2D 255

NIKE3D 275

Thermo-Plastic Material

DYNA3D 187

Thermo-Plasticity

NIKE2D 261, 269

NIKE3D 283, 289

Thick Shell

DYNA3D 179

Local-t 178

IND.11

INDEX

Thickness

Shell 37

Three-Dimensional Line

Definition

Displaying 108

Time Step

NIKE2D 253

NIKE3D 273

TOPAZ 294

Tolerance

MAZE Part 25

Surface Intersections 35

Tool Path

Displaying 109

TOPAZ Materials

Isotropic 297

Isotropic Temperature

Dependent 299

Orthotropic 298

Orthotropic Temperature

Dependent 300

TOPAZ2D 38, 294

TOPAZ3D 38, 294

Tracer Particles 38, 107

Tracer ParticlesDisplaying 110

Transient Solution

TOPAZ 295

Translational Joint 21

Triad

Plotting 114

Truss Element

DYNA3D 177

Unit Systems

TOPAZ 294

Universal Joint 21

Van Leer Advection 169

VEC-DYNA3D 176

Vector

Displaying 110

Velocity

Initial 39, 42, 44, 46, 70,

76, 88, 92, 94

Velocity Boundary Condition

Applying 98

Displaying 110

Rigid Body 25, 29

View Factor

Non-interacting Materials

25

Visco-Plastic Material

DYNA3D 206

Viscoelasticity

DYNA3D 190, 236

NIKE3D 286

Volume Definition 39

Wang-Nefske Inflator Model

14

Warpage of Shell

Displaying 110

YASE Shell

DYNA3D 179