patran 2008 r1 interface to abaqus preference guide

Patran 2008 r1

Interface To ABAQUSPreference Guide

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Con t en t s

Patran Interface to ABAQUS Preference Guide

1 Overview

Purpose 2

ABAQUS Product Information 3

What is Included with this Product? 4

Patran ABAQUS Integration with Patran 5

Configuring the ABAQUS Submit File 7

2 Building A Model

Introduction to Building a Model 10

Coordinate Frames 22

Finite Elements 23

Nodes 23

Elements 25

Multi-Point Constraints 27

Material Library 51

Materials Form 52

Element Properties 90

Element Properties Form 90

Loads and Boundary Conditions 332

Loads & Boundary Conditions Form 332

Load Cases 351

Group 352

3 Running an Analysis

Review of the Analysis Form 354


ii

Analysis Form 355

Translation Parameters 357

Restart Parameters 358

Optional Controls 359

Direct Text Input 360

Step Creation 361

Select Load Cases 362

Output Requests 362

Direct Text Input 363

Solution Types 364

Step Selection 432

Read Input File 433

ABAQUS Input File Reader 435

Input Deck Formats 435

ABAQUS ELSET and NSET Entries 435

4 Read Results

Review of the Read Results Form 454

Upgrading ABAQUS ODB Results Files 454

Read Results Form 455

Flat File Results 456

Translation Parameters 457

Attach Method 457

Translate and Control File Methods 457

Select Results File 458

Results Created in Patran 458

Data Translated from the Analysis Code Results File 463

Key Differences between Attach and

Translate Methods 464

Result Type Naming Conventions 464

Vector vs. Scalar Moment and Rotational Results 464

Reaction Forces 465

Delete Result Attachment Form 466

iiiCONTENTS

5 Files

Files 468

6 Errors/Warnings

Errors/Warnings 470


iv

Chapter 1: Overview


1 Overview

� Purpose 2

� ABAQUS Product Information 3

� What is Included with this Product? 4

� Patran ABAQUS Integration with Patran 5

� Configuring the ABAQUS Submit File 7

Patran Interface to ABAQUS Preference GuidePurpose

2

Purpose

Patran comprises a suite of products written and maintained by MSC.Software Corporation. The core of

the product suite is a finite element analysis pre and postprocessor. The Patran system also includes

several optional products such as advanced postprocessing programs, tightly coupled solvers, and

interfaces to third party solvers. This document describes one of these interfaces. See the Patran User

Manual for more information.

The Patran ABAQUS Application Preference Guide provides a communication link between Patran and

ABAQUS. It also provides customization of certain features that can be activated simply by selecting

ABAQUS as the analysis code preference in Patran.

Patran ABAQUS is integrated into Patran. The casual user will never need to be aware that separate

programs are being used. For the expert user, there are three main components of Patran ABAQUS:

several PCL files to provide the customization of Patran for ABAQUS, PAT3ABA to convert model data

from the Patran database into the analysis code input file, and ABAPAT3 to translate results and⁄or

model data from the analysis code results file into the Patran database.

Selecting ABAQUS as the analysis code under the “Analysis Preference” menu customizes Patran in five

main areas:

1. MPCs

2. Material Library

3. Element Library

4. Loads and Boundary Conditions

5. Analysis forms

PAT3ABA translates model data directly from the .Patran database into the analysis code-specific input

file format. This translation must have direct access to the originating Patran database. The program

name indicates the direction of translation: from Patran to ABAQUS.

ABAPAT3 translates results and⁄or model data from the analysis code-specific results file into the Patran

database. This program can be run such that the data is loaded directly into the Patran database, or if

incompatible computer platforms are being used, an intermediate file can be created. The program name

indicates the direction of translation: from ABAQUS to Patran.

3Chapter 1: OverviewABAQUS Product Information

ABAQUS Product Information

ABAQUS is a general-purpose finite element computer program for structural and thermal analyses. It

is developed, supported, and maintained by Hibbitt, Karlsson, and Sorensen, Inc., 1080 Main Street,

Pawtucket, Rhode Island 02860, (401) 727-4200. See the ABAQUS User’s Manual for a general

description of ABAQUS’ capabilities.

Patran Interface to ABAQUS Preference GuideWhat is Included with this Product?

4

What is Included with this Product?

The Patran ABAQUS product includes all of the following items:

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

2. The executable programs pat3aba and abapat3 which perform the forward and results

translation of data. Although these programs are separate executables, they are run from within

Patran, and are transparent to the user.

3. Script files are also included to drive the programs in item 2. These script files are started by

Patran and control the running of the programs in Patran ABAQUS.

4. This Application Preference User’s Manual is included as part of the product. An on-line version

is also provided to allow you direct access to this information from within Patran.

5Chapter 1: OverviewPatran ABAQUS Integration with Patran

Patran ABAQUS Integration with Patran

Two diagrams are shown below to indicate how these files and programs fit into the Patran environment.

In some cases, site customization of some of these files is indicated. Please see the Patran Installation and

Operations Guide for more information on this topic.

Figure 1-1 shows the process of running an analysis. The abaqus.plb library defines the various

Translation Parameter, Solution Type, Solution Parameter, and Output Request forms called by the

Analysis form. When the Apply button is selected on the Analyze form, a.jba file is created, and the

script AbaqusSubmit is started. This script may need to be modified for your site installation. The

script, in turn, starts the PAT3ABA forward translation. Patran operation is suspended at this time.

PAT3ABA reads data from the database and creates the ABAQUS input deck. A message file is also

created to record any translation messages. If PAT3ABA finishes successfully, and you have requested

it, the script will then start ABAQUS.

Figure 1-1 Forward Translation

Figure 1-2 shows the process of reading information from an analysis results file. When the Apply button

is selected on the Read Results form, a .jbr file is created, depending on whether model or results

data is to be read. The ResultsSubmit script is also started. This script may need to be modified for

Patran Interface to ABAQUS Preference GuidePatran ABAQUS Integration with Patran

6

your site installation. The script, in turn, starts the ABAPAT3 results translation. The Patran database is

closed while this translation occurs. A message file is created to record any translation messages.

ABAPAT3 reads the data from the ABAQUS results file. If ABAPAT3 can find the desired database, the

results will be loaded directly into it. If, however, it cannot find the database (for example, if you are

running on several incompatible platforms), ABAPAT3 will write all the data into a flat file. This flat file

can be taken to wherever the database is and read in using the read file selections.

Figure 1-2 Results Translation

7Chapter 1: OverviewConfiguring the ABAQUS Submit File

Configuring the ABAQUS Submit File

The AbaqusSubmit script file controls the execution of the PAT3ABA translator and the ABAQUS

analysis code. It is located in the Patran directory called

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

The information that AbaqusSubmit uses to perform its operations can be categorized as specific to the

job and the site. The job specific information is automatically supplied by Patran as command line

arguments at run time. The site specific information is set within the script file at the time of installation.

Host=LOCALScratchdir=”Acommand=’abaqus’

The Host parameter defines the machine that is used to perform the ABAQUS analysis. When this

parameter is set to LOCAL, the analysis is performed on the same machine as the Patran session

(PAT3ABA translations are always performed on the same machine as the Patran session.)

The Scratchdir parameter defines the directory on the host machine that temporarily holds the

analysis files as they are created. The advantage of having a scratch directory is that the contents of the

analysis scratch files are never transferred across the network. This benefit is not achieved when the Host

parameter is set to LOCAL, so the Scratchdir parameter is ignored for this condition.

The Acommand is the ABAQUS analysis code executable. If the Host is not LOCAL then the executable

should include the complete pathname.

Patran Interface to ABAQUS Preference GuideConfiguring the ABAQUS Submit File

8

Chapter 2: Building A Model


2 Building A Model

� Introduction to Building a Model 10

� Coordinate Frames 22

� Finite Elements 23

� Material Library 51

� Element Properties 90

� Loads and Boundary Conditions 332

� Load Cases 351

� Group 352

Patran Interface to ABAQUS Preference GuideIntroduction to Building a Model

10

Introduction to Building a Model

There are many aspects to building a finite element analysis model. In several cases, the forms used to

create the finite element data are dependent on the selected analysis type. Other parts of the model are

created using standard forms.

Under Preferences on the Patran main form is a selection for Analysis Settings. Analysis Settings defines

the intended analysis code which is to be used for this mode.

The specified code may be changed at any time during model creation. As much data as possible will be

converted if the analysis code is changed after the modeling process has already begun. The setting of

this option defines what will be presented in several areas during the subsequent modeling steps.

These areas include the material and element libraries (including multi-point constraints), the applicable

loads and boundary conditions, and the analysis forms. The selected Analysis Type may also affect the

allowable selections in these same areas. For more details, see Analysis Codes (p. 426) in the Patran

Reference Manual.

11Chapter 2: Building A ModelIntroduction to Building a Model

Supported ABAQUS Commands

The following tables summarize all the ABAQUS commands supported by the Patran ABAQUS

Preference Guide. The tables indicate where in this guide you can find more information on how the

commands are supported

Table 2-1 Supported ABAQUS Model Definition Options

History Definition Options Command


Page No.

ABAQUS/ Standard Section #

Initial Options ∗HEADING • p. 334 7.2.1

Node Definition ∗NODE • p. 18 7.3.6

∗NSET • p. 18 7.3.8

∗TRANSFORM • p. 16 7.3.11

Element

Definition

∗ELEMENT • p. 19 7.4.2

∗ELSET • p. 328 7.4.2

∗RIGID SURFACE • p. 154, p. 155, p. 156 p. 261 7.4.7

∗SLIDE LINE • p. 147 7.4.8

Property

Definition

∗BEAM GENERAL

SECTION

• p. 106, p. 113, p. 121 7.5.2

∗BEAM SECTION • p. 108, p. 115 to p. 119, 7.5.3

*CENTROID • p. 114 7.5.2


12

∗DASHPOT • p. 100, p. 101, p. 128 to p. 131 7.5.5

∗FRICTION • p. 102 to p. 104, p. 132, p. 133, 7.5.7

• p. 136 to p. 145, p. 148 to p. 152

• p. 255 to p. 259, p. 289

Property

Definition

(continued)

∗GAP • p. 132, p. 133, p. 294, p. 298 7.5.8

• p. 300

*GAP

CONDUCTANCE

*GAP RADIATION

• p. 294, p. 298, p. 300

∗HOURGLASS

STIFFNESS

• p. 232, p. 235, p. 238, p. 241, 7.5.13

• p. 244, p. 246, p. 248, p. 251,

• p. 252, p. 254, p. 287

∗INTERFACE • p. 102, p. 104, p. 136, p. 138, 7.5.14

• p. 140, p. 142, p. 145, p. 148,

• p. 150, p. 152, p. 255, p. 257,

• p. 259, p. 289, p. 294, p. 298,

• p. 300

∗MASS • p. 96 7.5.17

∗ROTARY INERTIA • p. 97 7.5.18

∗SHELL GENERAL

SECTION

• p. 238, p. 241, p. 246 7.5.19

∗SHELL SECTION • p. 80, p. 134, p. 135, p. 232, 7.5.20

• p. 234, p. 235, p. 237, p. 244,

• p. 292, p. 293, p. 295, p. 296

∗SOLID SECTION • p. 123, p. 248, p. 251, p. 252, 7.5.21

• p. 254, p. 287, p. 291, p. 297,

• p. 299

∗SPRING • p. 98, p. 99, p. 124 to p. 127

∗SURFACE

CONTACT

• p. 103, p. 136, p. 255, p. 257, 7.5.26

• p. 259, p. 289

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



Page No.



∗TRANSVERSE

SHEAR STIFFNESS

• p. 107, p. 108, p. 110, p. 113, 7.5.27

• p. 115, p. 119, p. 121, p. 232,

• p. 234, p. 235, p. 237, p. 238,

• p. 241, p. 244, p. 246

Material

Definition

∗MATERIAL • p. 44 7.6.2

∗CAP HARDENING • p. 69 7.6.4

∗COMBINED TEST

DATA

• p. 69

∗CAP PLASTICITY • p. 69 7.6.5

∗CONDUCTIVITY • p. 77, p. 78, p. 79 7.6.8

∗CREEP • p. 70, p. 71 7.6.9

∗DAMPING • p. 49, p. 72 to p. 75 7.6.11

∗DEFORMATION

PLASTICITY

• p. 64 7.6.12

∗DENSITY p. 49 to p. 59, p. 72 to p. 79 7.6.13

Material

Definition

(continued)

∗DRUCKER-PRAGER • p. 69 7.6.16

∗ELASTIC • p. 49, p. 72, p. 73, p. 74, 7.6.17

• p. 75

∗EXPANSION p. 49 to p. 59, p. 72 to p. 79 7.6.18

∗HYPERELASTIC p. 51 to p. 56 7.6.22

∗HYPERFOAM • p. 57, p. 59 7.6.23

∗LATENT HEAT • p. 57, p. 59 7.6.27

∗NO COMPRESSION • p. 57, p. 59 7.6.29

∗NO TENSION • p. 57, p. 59 7.6.30

∗PLANAR TEST

DATA

• p. 69

∗PLASTIC • p. 65, p. 66, p. 67 7.6.34

∗POTENTIAL • p. 65 to p. 67, p. 70, p. 71 7.6.37

∗RATE DEPENDENT • p. 65 to p. 68

∗SHEAR TEST DATA • p. 69




Page No.



14

∗SIMPLE SHEAR

TEST DATA

• p. 69

∗SPECIFIC HEAT • p. 77, p. 78, p. 79 7.6.40

∗UNIAXIAL TEST

DATA

• p. 69

∗VISCOELASTIC • p. 60, p. 61, p. 62, p. 63 7.6.43

∗VOLUMETRIC TEST

DATA

• p. 69

*YIELD • p. 68 7.6.44

Material

Orientation

∗ORIENTATION • p. 80, p. 232, p. 234, p. 235, 7.7.1

p. 237, p. 238, p. 241, p. 244,

p. 246, p. 248, p. 251, p. 287,

p. 295, p. 296, p. 297, p. 299

Kinematic

Constraints

∗BOUNDARY • p. 313, p. 317, p. 318 9.5.1

∗EQUATION • p. 24 7.8.3

∗MPC • p. 25 to p. 42 7.8.4

Initial Conditions ∗INITIAL

CONDITIONS

• p. 316, p. 326 7.9.1

Restart Options ∗RESTART • p. 332 7.10.1

Miscellaneous

Model Options

∗AMPLITUDE • p. 346 7.11.1

∗PSD-DEFINITION • p. 378 7.11.3

∗SPECTRUM • p. 374 7.11.5

∗WAVEFRONT

MINIMIZATION

• p. 334 7.11.9




Page No.



The following ABAQUS History Definition options are supported.

Table 2-2 Supported ABAQUS History Definition Options



Page No.

ABAQUS/ Standard Section

No.

Step Initialization/

Termination

*STEP • p. 336, p. 346, p. 382, p. 386, 9.2.1

p. 390, p. 394, p. 402

∗END STEP • p. 336 9.2.2

Procedure

Definition

∗BUCKLE • p. 349 9.3.2

∗DYNAMIC • p. 352, p. 386 9.3.4

∗FREQUENCY • p. 359, p. 366, p. 374, p. 377 9.3.5

∗HEAT TRANSFER • p. 401, p. 402 9.3.7

∗MODAL DYNAMIC • p. 359 9.3.8

∗RANDOM RESPONSE • p. 377 9.3.9

∗RESPONSE

SPECTRUM

• p. 374 9.3.10

∗STATIC • p. 382 9.3.12

∗STEADY STATE

DYNAMICS

• p. 366, p. 370 9.3.13

∗VISCO • p. 390, p. 394 9.3.15

Loading Definition ∗BASE MOTION • p. 359, p. 365, p. 366 9.4.2

∗CFLUX • p. 325 9.4.4

∗CLOAD • p. 313 9.4.5

∗DFLUX • p. 325 9.4.9

∗DLOAD • p. 314, p. 316 9.4.10

∗FILM • p. 324 9.4.12

∗TEMPERATURE • p. 314 9.4.18

Prescribed

Boundary

Conditions

∗BOUNDARY • p. 318 9.5.1

Miscellaneous

History Options

∗CORRELATION • p. 377 9.4.6

∗MODAL DAMPING • p. 359 to p. 364 9.6.6


16

The following ABAQUS element types are supported.

Print Definition ∗EL PRINT • p. 338 9.8.2

∗ENERGY PRINT • p. 338 9.8.3

∗MODAL PRINT • p. 338 9.8.4

∗NODE PRINT • p. 338 9.8.6

∗PRINT • p. 338 9.8.7

File Output

Definition

∗EL FILE • p. 338 9.9.2

∗ELEMENT MATRIX

OUTPUT

• p. 338

∗ENERGY FILE • p. 338 9.9.3

FILE FORMAT • p. 338 9.9.4

∗MODAL FILE • p. 338 9.9.5

∗NODE FILE • p. 338 9.9.6

∗PREPRINT • p. 338

Table 2-3 Supported ABAQUS Element Types

Element Types

Patran ABAQUS Preference Guide Page

No.

Stress-Displacement Elements

Beam Elements

Two-dimensional B21

B21H

B22

B22H

B23

B23H

• p. 106, p. 108

Three-dimensional B31

B31H

B32

B32H

B33

B33H

B34

• p. 113, p. 115, p. 119

Three-dimensional

Open Section

B31OS

B31OSH

B32OS

B32OSH

• p. 121

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



Page No.

ABAQUS/ Standard Section

No.



Beam Elements

One-dimensional C1D2

C1D2H

C1D3

C1D3H

• p. 123

Axisymmetric CAX3

CAX3H

CAX4

CAX4H

CAX4I

CAX4IH

CAX4R

CAX4RH

CAX6

CAX6H

CAX8

CAX8H

CAX8R

CAX8RH

• p. 252

Axisymmetric with

twist

CGAX3

CGAX3H

CGAX4

CGAX4H

CGAX4R

CGAX4RH

CGAX6

CGAX6H

CGAX8

CGAX8H

CGAX8R

CGAX8RH

• p. 253

Plane Strain CPE3

CPE3H

CPE4

CPE4H

CPE4I

CPE4IH

CPE4R

CPE4RH

CPE6

CPE6H

CPE6M

CPE6MH

CPE8

CPE8H

CPE8R

CPE8RH

• p. 248

Generalized Plane

Strain

CGPE5

CGPE5H

CGPE6

CGPE6H

CGPE6I

CGPE6IH

CGPE6R

CGPE6RH

CGPE8

CGPE8H

CGPE10

CGPE10H

CGPE10R

CGPE10RH

• p. 249

Plane Stress CPS3

CPS4

CPS4I

CPS4R

CPS6

CPS6M

CPS8

CPS8R

• p. 251

Table 2-3 Supported ABAQUS Element Types (continued)

Element Types


No.


18


Beam Elements

Three-dimensional C3D4

C3D4H

C3D6

C3D6H

C3D8

C3D8H

C3D8I

C3D8IH

C3D8R

C3D8RH

C3D10

C3D10HC3

D10M

C3D10MH

C3D15

C3D15H

C3D20

C3D20H

C3D20R

C3D20RH

C3D27

C3D27H

C3D27R

C3D27RH

• p. 287

Membrane Elements

Membrane Elements M3D3

M3D4

M3D4R

M3D6

M3D8

M3D8R

M3D9

M3D9R

• p. 254


Element Types


No.



Shell Elements

Shell S3RF S4RF • p. 244, p. 246

S4R STRI3 • p. 235, p. 237, p. 241

S4R5 S9R5 • p. 232, p. 234, p. 238

S8R • p. 40, p. 41, p. 235,

p. 237, p. 241

S8R5 • p. 40, p. 41, p. 232,

p. 234, p. 238

STRI35 • p. 232, p. 234, p. 238

STRI65 • p. 232, p. 234, p. 235,

p. 237, p. 238, p. 241

Special Elements

Axisymmetric SAX1 SAX2 • p. 134, p. 135

Elbow Elements

Elbow Elements ELBOW31

ELBOW31B

ELBOW31C

ELBOW32

• p. 117

Spring Elements

Spring Elements SPRING1 • p. 98, p. 99

SPRING2 • p. 125, p. 127

SPRINGA • p. 124, p. 126

Dashpot Elements

Dashpot Elements DASHPOT1 • p. 100

DASHPOT2 • p. 101, p. 129, p. 131

DASHPOTA • p. 128, p. 130

Mass Element

Mass Element MASS • p. 96

Rotary Inertia Element

Rotary Inertia Element ROTARY1 • p. 97


Element Types


No.


20

Special Elements

Gap Elements

Gap Elements GAPCYL • p. 132

GAPSPHER • p. 133

GAPUNI • p. 132

Small Sliding Contact Elements

Interface INTER1 • p. 136

INTER2 INTER3 • p. 255

INTER4

INTER8

INTER9 • p. 289

Axisymmetric INTER2A INTER3A • p. 257

Rigid Surface Contact Elements

Rigid Surface IRS3

IRS4

IRS9 • p. 259

IRS12 • p. 102

IRS13 • p. 104

IRS21 IRS22 • p. 148

IRS31 IRS32 • p. 152

Axisymmetric IRS21A IRS22A • p. 150

Slide Line Contact Elements

Two-dimensional ISL21 ISL22 • p. 138, p. 147

Three-dimensional ISL31 ISL32 • p. 142, p. 147

Axisymmetric ISL21A ISL22A • p. 140, p. 147

ISL31A ISL32A • p. 145, p. 147

Heat Transfer Elements


Axisymmetric DCAX3

DCAX4

DCAX6

DCAX8

• p. 297

Axisymmetric

Convection/Diffusion

DCCAX2 DCCAX2D

DCCAX4 DCCAX4D • p. 297

One-dimensional DC1D2 DC1D3 • p. 291


Element Types


No.




Two-dimensional DC2D3

DC2D4

DC2D6

DC2D8

• p. 297

Two-dimensional


DCC2D4

DCC2D4D

• p. 297

Three-dimensional DC3D4

DC3D6

DC3D8

DC3D10

DC3D15

DC3D20

• p. 299

Three-dimensional


DCC3D8 DCC3D8D • p. 299

Interface Elements DINTER1 • p. 294

DINTER2 DINTER3 • p. 298

DINTER4 DINTER8 • p. 300

Interface Elements,

Axisymmetric

DINTER2A

DINTER3A

• p. 298

Shell Elements DS4

DS8

• p. 295, p. 296

Shell Elements,

Axisymmetric

DSAX1

DSAX2

• p. 292, p. 293


Element Types


No.

Patran Interface to ABAQUS Preference GuideCoordinate Frames

22

Coordinate Frames

Coordinate frames will generate different ABAQUS input, depending on the use of the coordinate frame.

Unreferenced coordinate frames will not be translated into ABAQUS.

If a node references a coordinate frame in the Analysis Coordinate Frame field, the nodal degrees-of-

freedom will be rotated into that system through the use of the *TRANSFORM option. All vector type

loads or boundary conditions must reference the same coordinate frame as the node.

If a coordinate frame is referenced for element property orientation, the appropriate *ORIENTATION

option will be created.

23Chapter 2: Building A ModelFinite Elements

Finite Elements

Finite Elements in Patran allows the definition of basic finite element constructs, including the creation

of nodes, element topology, and multi-point constraints.

Nodes

The nodes form will generate the ∗klab option (see Section 7.3.6 in the ABAQUS / Standard

User’s Manual).

The name of the node set to which the nodes will be assigned will be based on the associated analysis

coordinate frame number. For example, creating nodes in analysis coordinate frame “Coord 1" will

generate the ABAQUS option ∗NSET, NSET=CID1.

Patran Interface to ABAQUS Preference GuideFinite Elements

24


Elements

Finite elements in Patran simply assigns element topology, such as Quad⁄4, for standard finite elements.

The type of element to be created is not determined until the element properties are assigned. See Element

Properties Form for details concerning the ABAQUS element types. Elements can be created either

discretely using the Element object, or indirectly using the Mesh object.


26


Multi-Point Constraints

Multi-point constraints (MPCs) can also be created from the Finite Elements menu. These are special

element types which define a rigorous behavior between several specified nodes. The forms for creating

MPCs are found by selecting MPC as the Object on the Finite Elements form. The full functionality of

the MPC forms are defined in Create Action (FEM Entities) (Ch. 3) in the Reference Manual - Part III .


28

MPC Types

To create an MPC, you must first select the type of MPC you want to create from an option menu. The

types that will appear in this option menu are dependent on the current Analysis Type preference setting.

The following table describes the MPC types that are supported.

MPC Type Analysis Type Description

Explicit Structural

Thermal

Creates an ∗EQUATION option which defines an explicit

MPC between a dependent degree-of-freedom and one or

more independent degrees-of-freedom. The dependent term

consists of a node ID and a degree-of-freedom, while an

independent term consists of a coefficient, a node ID, and a

degree-of-freedom. An unlimited number of independent

terms and one dependent term can be specified.

Rigid (Fixed) Structural Creates a BEAM type MPC between one independent node

and one or more dependent nodes in which all six structural

degrees-of-freedom are rigidly attached to each other. An

unlimited number of dependent terms and one independent

term can be specified. Each term consists of a single node.

Rigid (Pinned) Structural Creates a LINK type MPC between one independent node

and one or more dependent nodes in which only the three

translational structural degrees-of-freedom are rigidly

attached to each other. An unlimited number of dependent

terms and one independent term can be specified. Each term

consists of a single node.

Linear Surf-Surf Structural

Thermal

Creates a LINEAR type MPC between a dependent node on

one linear 2D element and two independent nodes on

another linear 2D element to model a continuum. One

dependent and two independent terms can be specified.

Each term consists of a single node.

Linear Surf-Vol Structural Creates an SS LINEAR type MPC between a dependent

node on a linear 2D plate element and two independent

nodes on a linear 3D solid element to connect the plate

element to the solid element. One dependent and two

independent terms can be specified. Each term consists of a

single node.

Linear Vol-Vol Structural

Thermal

Creates a BILINEAR type MPC between a dependent node

on one linear 3D solid element and four independent nodes

on another linear 3D solid element to model a continuum.

One dependent and four independent terms can be

specified. Each term consists of a single node.


Quad. Surf-Surf Structural Creates a QUADRATIC type MPC between a dependent

node on one quadratic 2D element and three independent

nodes on another quadratic 2D element to model a

continuum. One dependent and three independent terms can

be specified. Each term consists of a single node.

Quad. Surf-Vol Structural Creates an SS BILINEAR type MPC between a dependent

node on a quadratic 2D plate element and three independent

nodes on a quadratic 3D solid element to connect the plate

element to the solid element. One dependent and three


single node.

Quad. Vol-Vol Structural Creates a C BIQUAD type MPC between a dependent node

on one quadratic 3D solid and eight independent nodes on

another quadratic 3D solid element to model a continuum.

One dependent and eight independent terms can be


Slider Structural Creates a SLIDER type MPC between one dependent node

and two independent nodes which forces the dependent

node to move along the vector defined by the two

independent nodes. One dependent and two independent

terms can be specified. Each term consists of a single node.

Elbow Structural Creates an ELBOW type MPC which constrains two nodes

of ELBOW31 or ELBOW32 elements together. One

dependent and one independent terms can be specified.

Each term consists of a single node.

Tie Structural Creates a TIE type MPC which makes all active degrees-of-

freedom equal at two nodes. One dependent and one


single node.

Revolute Structural Creates a REVOLUTE type MPC which defines a revolute

joint. One dependent and two independent terms can be


V Local Structural Creates a V LOCAL type MPC which constrains the

velocity components at the first node to be equal to the

velocity components at the third node along local, rotating,

directions. These local directions rotate according to the

rotation at the second node. One dependent and two


single node.



30

Degrees-of-Freedom

Whenever a list of degrees-of-freedom is expected for an MPC term, a listbox containing the valid

degrees-of-freedom is displayed on the form. A degree-of-freedom is valid if:

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

2. It is valid for the selected MPC type.

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

for the MPC type.

The following degrees-of-freedom are supported by the Patran ABAQUS MPCs for the various

analysis types:

Universal Structural Creates a UNIVERSAL type MPC which defines a

universal joint. One dependent and three independent


SS Linear Structural Creates an SS LINEAR type MPC which constrains a shell

node to a line of solid nodes for linear elements. One

dependent and an unlimited number of independent terms

can be specified. Each term consists of a single node.

SS Bilinear Structural Creates an SS BILINEAR type MPC which constrains a

shell node to a line of solid nodes for quadratic elements.

One dependent and an unlimited number of independent


SSF Bilinear Structural Creates an SSF BILINEAR type MPC which constrains a

mid-side shell node to a line of mid-face solid nodes for

quadratic elements. One dependent and an unlimited

number of independent terms can be specified. Each term

consists of a single node.

Degrees-of-Freedom Analysis Type

UX Structural

UY Structural

UZ Structural

RX Structural

RY Structural

RZ Structural

Temperature Thermal



Explicit MPCs

Creates an *EQUATION option. (See Section 7.8.3 in the ABAQUS/Standard User’s Manual). No

constant term is allowed for this type of equation. The A1 multiplier for the dependent term will be set

to -1.0 to create the desired equation.

Note: Care must be taken to make sure that a degree-of-freedom selected for an MPC actually exists

at the nodes. For example, a node that is attached only to solid structural elements will not have

any rotational degrees-of-freedom. However, Patran will allow you to select rotational degrees-

of-freedom at this node when defining an MPC.


32

Rigid (Fixed) MPCs

Creates an *MPC option of type BEAM for each dependent node (see Section 7.8.4 in the

ABAQUS/Standard User’s Manual). This provides a rigid beam between two nodes to constrain the

displacement and rotation at the first node to the displacement and rotation at the second node,

corresponding to the presence of a rigid beam between the two nodes.


Rigid (Pinned) MPCs

Creates an *MPC of type LINK for each dependent node (see Section 7.8.4 in the ABAQUS/Standard

User’s Manual). This provides a pinned rigid link between two nodes in order to keep the distance

between the two nodes constant. The displacements of the first node are modified to enforce this

constraint. The rotations at the nodes, if any, are not involved in this constraint.


34

Linear Surf-Surf MPCs

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

This is the standard method for mesh refinement of first-order elements.

This MPC constrains each degree-of-freedom at the dependent node to be interpolated linearly from the

corresponding degrees-of-freedom at the independent nodes

.

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


Linear Surf-Vol MPCs

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

Manual).

This is the standard method for mesh refinement of first-order elements. This MPC constrains each

degree-of-freedom at the dependent node to be interpolated linearly from the corresponding degrees-of-

freedom at the independent nodes.

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

LINEAR.


36

Linear Vol-Vol MPCs

Creates an *MPC option of type BILINEAR (see Section 7.8.4 in the ABAQUS/Standard User’s

Manual). This is a standard method for mesh refinement of first-order solid elements in three dimensions.

This MPC constrains each degree-of-freedom at the dependent node to be interpolated bilinearly from

the corresponding degrees-of-freedom at the independent nodes.


Quad. Surf-Surf MPCs

Creates an *MPC option of type QUADRATIC (see Section 7.8.4 in the ABAQUS/Standard User’s

Manual). This is a standard method for mesh refinement of second-order elements.

This MPC constrains each degree-of-freedom at the dependent node to be interpolated quadratically from


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

QUADRATIC


38

Quad. Surf-Vol MPCs

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

Manual). This is a standard method for mesh refinement of second-order elements.

This MPC constrains each degree-of-freedom at the dependent node to be interpolated quadratically from


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

BILINEAR.


Quad. Vol-Vol MPCs

Creates an *MPC option of type C BIQUAD (see Section 7.8.4 in the ABAQUS/Standard User’s

Manual). This is a standard method for mesh refinement of second-order solid elements in three

dimensions.

This MPC constrains each degree-of-freedom at the dependent node to be interpolated by a constrained

biquadratic from the corresponding degrees-of-freedom at the eight independent nodes.


40

Slider MPCs

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

This MPC will keep a node on a straight line defined by two other nodes, but allows the possibility of

moving along the line, and the line to change length.


42

Elbow MPCs

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

This MPC constrains two ELBOW31 or ELBOW32 elements together, where the cross-sectional

direction changes.


Pin MPCs

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

MPC provides a pinned joint between two nodes. This makes the displacements equal, but leaves the

rotations, if they exist, independent of each other.

Tie MPCs

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

MPC makes all active degrees-of-freedom equal at two nodes.

If there are different degrees-of-freedom active at the two nodes, only those in common will be

constrained. It is usually used to join two parts of a mesh when corresponding nodes on the two parts are

to be fully connected.


44

Revolute MPCs

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

Manual).


46

V Local MPCs

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


Universal MPCs

Creates an *MPC option of type UNIVERSAL (see Section 7.8.4 in the ABAQUS/Standard

User’s Manual).

SS Linear MPCs

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

Manual). This MPC is used to constrain a shell node to a solid node line for linear elements (S4R or

S4R5; C3D8, C3D8R; SAX1; CAX4; etc.) or for midside lines on quadratic elements (S8R, S8R5;

C3D20, C3D20R; etc.).

This MPC is only valid for small rotations.


48

SS Bilinear MPCs

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

Manual). This MPC is used to constrain a corner node of a quadratic shell element (S8R, S8R5) to a line

of edge nodes on 20-node bricks.



SSF Bilinear MPCs

Creates an *MPC option of type SSF BILINEAR (see Section 7.8.4 in the ABAQUS/Standard User’s

Manual). This MPC is used to constrain a corner node of a quadratic shell element (S8R, S8R5) to a line

of edge nodes on 20-node bricks.



50

51Chapter 2: Building A ModelMaterial Library


Material Library

Selecting Materials from this Patran window displays the main form for the creation of materials. The

following sections provide an introduction to the Materials form, followed by the details of all the

material property definitions supported by the Patran ABAQUS Application Interface.

Patran Interface to ABAQUS Preference GuideMaterials Form

52

Materials Form

The Materials form shown below provides the following options for the purpose of creating

ABAQUS materials.

Change Material Status

The approach to defining material properties in Patran is similar to that in ABAQUS; the complete

material model is defined by individually defining the necessary constitutive models. For example, to

define a material for a plasticity analysis, one would first define the elastic properties and select Apply.

Then the plastic properties are defined by selecting Plastic as Option 1, the yield criteria as Option 2, the

hardening law as Option 3, entering the appropriate data and pushing Apply.

53Chapter 2: Building A ModelMaterials Form

Not all constitutive model options are valid for a particular material in a particular ABAQUS analysis.

For example, it is not permissible to have both elastic and hyperelastic properties defined for the same

ABAQUS material. Patran, however, allows these different constitutive models to be defined and then

“deactivated” for a given ABAQUS analysis. This is done on the form displayed when the Change

Material Status button is selected on the main Materials form. For example, if a user defines both Elastic

and Hyperelastic properties for a given material, one of these constitutive options must be deactivated on

the Change Material Status form before initiating the ABAQUS analysis.

Temperature Dependence

ABAQUS allows most material properties to be functions of temperature. The ABAQUS interface in

Patran generally supports this as well. The first step in defining a temperature dependent material

property is to define a temperature dependent material field in the Fields application. This field can then

be selected from a listbox on the Materials, Input Options form. When the databox for a material property

that may be temperature dependent is selected, the fields listbox appears.

The following table shows the allowable selections for all options when the Action is set to Create and

the Analysis Type in the Analysis Preference form is set to Structural. The various options have different

names, depending on previous selections.

Object Option 1 Option 2 Option 3

Isotropic • Elastic Material Failure Theory

Hyperelastic Incompressible Test Data

• Ogden

• Polynomial

Coefficients

• Ogden

• Mooney Rivlin

• Neo Hookean

• Polynomial

Slightly Compressible Test Data

• Ogden

• Polynomial

Coefficients

• Ogden

• Polynomial


54

Compressible Test Data

• Ogden

Coefficients

• Ogden

Viscoelastic Frequency • Formula

• Tabular

Time • Prony

• Creep Test Data

• Combined Creep Test Data

• Relaxation Test Data

• Combined Relax Test Data

• Deformation

Plasticity

Plastic Mises/Hill • Perfect Plasticity

• Isotropic

• Kinematic

• Drucker-Prager Compression

Tension

Shear

Modified D-Prager/Cap Cap Hardening

Creep • Time

• Strain

• Hyperbolic

2D Orthotropic (Lamina)

• Elastic Material Failure Theory


Tabular

Time • Prony

• Creep Test Data

Combined Creep Test Data


Combined Relax Test Data




• Isotropic

• Kinematic


Tension

Shear


Creep • Time

• Strain

• Hyperbolic

3D Orthotropic

• Elastic Engineering Constants

• [D] Matrix

Material Failure Theory


Tabular

Time • Prony

• Creep Test Data





• Isotropic

• Kinematic


Tension

Shear


Creep • Time

• Strain

• Hyperbolic



56

3D Anisotropic

• Elastic [D] Matrix Material Failure Theory


Tabular

Time • Prony

• Creep Test Data





• Isotropic

• Kinematic


Tension

Shear


Creep • Time

• Strain

• Hyperbolic

Composite • Laminate

Rule of Mixtures

HAL Cont. Fiber

HAL Disc. Fiber

HAL Cont. Ribbon

HAL Disc. Ribbon

HAL Particulate

Short Fiber 1D

Short Fiber 2D



The following table shows the allowable selections for all options when the Action is set to Create and

the Analysis Type is set to Thermal in the Analysis Preference form. The various options have different

names, depending on previous selections.

Object Option 1

Isotropic Thermal

3D Orthotropic Thermal

3D Anisotropic

Composite Laminate

Rule of Mixtures

HAL Cont. Fiber

HAL Disc. Fiber

HAL Cont. Ribbon

HAL Disc. Ribbon

HAL Particulate

Short Fiber 1D

Short Fiber 2D


58

Isotropic

Elastic

Object Option 1 Option 2

Isotropic Elastic Material Failure Theory


More data input is available for defining the Elastic properties for the Isotropic materials. Listed below

are the descriptions for the remaining material properties.

Property Name Description

Reference Temperature This is the reference value of temperature for the coefficient of

thermal expansion. The thermal strain in the material is based on

the difference between the current temperature and this reference

value (default is 0.0).

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

Fraction Critical Damping Set this parameter equal to the fraction of critical damping to be

used with this material in calculating composite damping factors

for the modes (for use in modal dynamics). The default is 0.0. The

value is ignored in direct integration dynamics.

Mass Propornl Damping Factor for mass proportional damping in direct integration

dynamics (default = 0.0). This value is ignored in modal dynamics.

Stiffness Propornl Damping Factor for stiffness proportional damping in direct integration

dynamics (default = 0.0). This value is ignored in modal dynamics.


60

Hyperelastic


Isotropic Hyperelastic Incompressible Test Data -

Ogden

Polynomial


Hyperelastic


Isotropic Hyperelastic Incompressible Coefficients - Ogden


62

Hyperelastic


Isotropic Hyperelastic Incompressible Coefficients -

Moony Rivlin

Neo Hookean

Polynomial


Hyperelastic


Isotropic Hyperelastic Slightly Compressible Test Data -

Ogden

Polynomial


64

Hyperelastic


Isotropic Hyperelastic Slightly Compressible Coefficients - Ogden


Hyperelastic


Isotropic Hyperelastic Slightly Compressible Coefficients - Polynomial


66

Hyperelastic


Isotropic Hyperelastic Compressible Test Data - Ogden


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

for the remaining material properties.


Volumetric Pressure Material field defining volume ratio (current volume/original

volume) as a function of pressure. This field appears on the

*VOLUMETRIC TEST DATA sub option.

Poisson’s Ratio Effective Poisson’s ratio of the material which will be equal to all

. This is the value of the POISSON parameter on the

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

should be entered.

Density Defines the material mass density. This quantity appears on the

*DENSITY option.

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

parameter appears as a on the *EXPANSION option.

νi


68

Hyperelastic


Isotropic Hyperelastic Compressible Coefficients - Ogden


Viscoelastic


Isotropic, 2D Orthotropic,

3D Orthotropic or 3D Anisotropic

Viscoelastic Frequency Tabular

Formula


70

Viscoelastic




Viscoelastic Time Prony


Viscoelastic




Viscoelastic Time Creep Test Data



72

Viscoelastic




Viscoelastic Time Relaxation Test Data



Deformation Plasticity

Object Option 1

Isotropic Deformation Plasticity


74

Plastic




Plastic Mises/Hill Perfect Plasticity


Plastic


Isotropic, 2DOrthotropic,

3DOrthotropic or 3D Anisotropic

Plastic Mises/Hill Isotropic


76

Plastic



3DOrthotropic or 3D Anisotropic

Plastic Mises/Hill Kinematic


Plastic




Plastic Drucker-Prager Compression

Tension

Shear


78

Plastic




Plastic Modified

D-Prager/Cap

Cap Hardening


CrÉep




Creep Time

Strain


80

Creep




Creep Hyperbolic


2D Orthotropic (Lamina)

Elastic

Option 1 Option 2

Elastic Material Failure Theory


82

3D Orthotropic

Elastic

Option 1 Option 2 Option 3

Elastic Engineering Constants Material Failure Theory


Elastic


3D Orthotropic Elastic [D] Matrix Material Failure Theory


84

3D Anisotropic

Elastic

Option 1 Option 2

Elastic [D] Matrix


More data input is available for defining the Elastic properties for the 3D Anisotropic materials. Listed

below are the descriptions for the remaining material properties.

Property Name Desciption

D1212 (C34)

D1212 (C44)

D1113 (C15)

D2213 (C25)

D3313 (C35)

D1213 (C45)

D1313 (C55)

D1123 (C16)

D2223 (C26)

D3323 (C36)

D1223 (C46)

D1323 (C56)

D2323 (C66)

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

anisotropic material.

Density Defines the material mass density.


86

Isotropic (Thermal)


3D Orthotropic (Thermal)


88

3D Anisotropic (Thermal)

Composite

The Composite forms allow existing materials to be combined to create new materials. All of the

composite materials, with the exception of the laminated composites, can be assigned to elements like

any homogeneous material through the element property forms. For the laminated composites, the

section thickness is entered indirectly through the definition of the stack, and the Homogeneous option

on the Element Properties Form for shells, plates and beam must be changed to Laminate to avoid reentry

of this information.


For details on how to use these forms, refer to the Composite Materials Construction (p. 116) in the Patran

Reference Manual.

Laminate

Patran Interface to ABAQUS Preference GuideElement Properties

90

Patran I nterface to ABAQU S Preference Gu ide

Element Properties

By choosing the Element Properties item, located on the application switch for Patran, an element

properties form will appear. When creating element properties, several option menus are available. The

selections made in these option menus will determine which element property form is presented, and

ultimately, which ABAQUS element will be created.

The following pages give an introduction to the Element Properties form, followed by the details of all

the element property definitions supported by the Patran ABAQUS Application Preference.

Element Properties Form

When Element Properties is selected on the main menu, this is the form which will be displayed. Four

option menus on this form are used to determine which ABAQUS element types are to be created, and

which property forms are to be displayed. The individual property forms are documented later in this

section. For more details, see the Element Properties Forms (p. 67) in the Patran Reference Manual.

91Chapter 2: Building A ModelElement Properties


92

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

Structural.

Dimension Type Option 1 Option 2 Name

0D • Mass MASS

• Rotary Inertia ROTARYI

Grounded Spring • Linear

• Nonlinear

SPRING1

SPRING2

Grounded Damper • Linear

• Nonlinear

DASHPOT1

DASHPOT2

IRS (single node) • Planar Elastic Slip Soft Contact Elastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis DampingNo SeparationLagrange Vis DampingLagrange Vis Damping NoSeparation

IRS12

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

IRS13

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

B21, B22B21H, B22HB23B23H

• Box Section Standard Formulation

HybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

• Circular Beam

(Solid)

Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H


• Hexagonal Beam Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

• I Section Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

• Pipe Section Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

• Rectangular

Section

Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

• Trapezoid Section Standard FormulationHybridCubic InterpolationCubic Hybrid

B21, B22B21H, B22HB23B23H

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

B31, B32B31H, B32HB33B33HB34

• Arbitrary Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

• Box Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

• Circular Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

• Curved w/Pipe

Section

Standard FormulationOvalization OnlyOvalization Only with Approximated Fourier

ELBOW31,ELBOW32ELBOW31BELBOW31C

• Hexagonal Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34



94

• I Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

• L Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

• Open Section Standard FormulationHybrid

B31OS, B32OSB31OSH, B32OSH

• Pipe Section Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

• Rectangular

Section

Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

• Trapezoidal

Section

Standard FormulationHybridCubic InterpolationCubic HybridCubic Initially Straight

B31, B32B31H, B32HB33B33HB34

• Truss Standard FormulationHybrid

CID2, CID3CID2H, CID3H

Spring Linear • Standard Formulation

Fixed Direction

SPRINGASPRING2

Nonlinear • Standard Formulation

Fixed Direction

Damper Linear • Standard Formulation

Fixed Direction

DASHPOTADASHPOT2

Nonlinear • Standard Formulation

Fixed Direction



1D

(continued)

Gap • Cylindrical True DistanceElastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis DampingNo SeparationLagrange Vis DampingLagrange Vis Damping NoSeparation

GAPCYL

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

GAPSPHER

• Uniaxial True DistanceElastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis DampingNoSeparationLagrange Vis DampingLagrange Vis Damping NoSeparation

GAPUNI

Axisym Shell • Homogeneous

• Laminate

SAX1, SAX2



96

1D

(continued)

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

INTER1

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

ISL21, ISL22

• Axisymmetric Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping NoSeparationLagrange Vis DampingLagrange Vis Damping NoSeparation

ISL21A, ISL22A

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

Lagrange Vis Damping

Lagrange Vis Damping No Separation

ISL31, ISL32ISL31, ISL32



1D

(continued)

ISL (in space) (continued)

• Radial Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping NoSeparationLagrange Vis DampingLagrange Vis Damping NoSeparation

ISL31A, ISL32A

• Slide Line --

IRS (planar/axisym) • Planar Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping NoSeparationLagrange Vis DampingLagrange Vis Damping NoSeparation

IRS21, IRS22

• Axisymmetric Elastic Slip Soft ContactElastic Slip Hard ContactLagrange Soft ContactLagrange Hard ContactElastic Slip No SeparationLagrange No SeparationElastic Slip Vis DampingElastic Slip Vis Damping NoSeparationLagrange Vis DampingLagrange Vis Damping NoSeparation1D (cont.)

IRS21A, IRS22A

• IRS

(beam/pipe)

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

IRS31, IRS32



98

1D

(continued)

• Rigid Surf

(Seg)

• Rigid Surf (Cyl)

• Rigid Surf (Axi)

• Rigid Surf

(Bz2D)

• Rigid Line

(Lbc)

--

--

--

--

R2D2, RAX2

• Rebar Axisymmetric SFMAX1, SFMAX2

General Axisymmetric SFMGAX1, SFMGAX2

• Mech Joint (2D

Model)

ALIGN

AXIAL

BEAM

CARTESIAN

JOIN

JOINTC

LINK

ROTATION

SLOT

TRANSLATOR

WELD

• Mech Joint (3D

Model)

ALIGN

AXIAL

BEAM

CARDAN

CARTESIAN

CONSTANT VELOCITY

CVJOINT

CYLINDRICAL

EULER

FLEXION-TORSION



HINGE

JOIN

JOINTC

LINK

PLANAR

RADIAL-THRUST

REVOLUTE

ROTATION

SLIDE-PLANE

SLOT

TRANSLATOR

UJOINT

UNIVERSAL

WELD

• 1D Gasket Axisymmetric Link Gasket Behavior Model GKAX2

Thickness Behavior Only GKAX2N

Built-in Material GKAX2

3D Link Gasket Behavior Model GK3D2

Thickness Behavior Only GK3D2N

Built-in Material GK3D2

2D Link Gasket Behavior Model GK2D2

Thickness Behavior Only GK2D2N

Built-in Material GK2D2



100

2D Shell Thin • Homogeneous

Laminate

STRI35, S4R5, STRI65, S8R5, S9R5

Thick Homogeneous

Laminate

S3R, S4R, STRI65, S8R

• General Thin Homogeneous

Laminate

STRI35, S4R5, STRI65, S8R5, S9R5

• General Thick Homogeneous

Laminate

S3R, S4R, STRI65, S8R

• Large Strain

• General Large

Strain

S3R, S4R, S8R

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

Hybrid CPE3H, CPE4H, CPE6H, CPE8H

Hybrid / Reduced Integration

CPE4RH, CPE8RH

Reduced IntegrationIncompatible ModesHybrid/Incompatible ModesModifiedModified/Hybrid

CPE4R, CPE8RCPE4ICPE4IHCPE6M, CPE6MH

• Plane Stress Standard FormulationReduced IntegrationIncompatible ModesModifiedModified/Hybrid

CPS3, CPS4, CPS6, CPS8CPS4R, CPS8RCPS4ICPS6M, CPS6MH



2D

(continued)

2D Solid (continued)

• Axisymmetric Standard Formulation CAX3, CAX4, CAX6, CAX8

Hybrid CAX3H, CAX4H, CAX6H, CAX8H

Hybrid/Reduced Integration

CAX4RH, CAX8RH

Reduced Integration CAX4R, CAX8R

Incompatible Modes CAX4I

Hybrid/Incompatible Modes

CAX4IH

Modified CAX6M

Modified/Hybrid CAX6MH

• Axisymmetric with

Twist

Standard Formulation CGAX3, CGAX4, CGAX6, CGAX8

Hybrid CGAX3H, CGAX4H, CGAX6H, CGAX8H

Hybrid/Reduced Integration

CGAX4RH, CGAX8RH

Reduced Integration CGAX4R, CGAX8R

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

Reduced Integration M3D4R, M3D8R, M3D9R

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

INTER2, INTER3



102

2D

(continued)

2D Solid (continued)

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

INTER2A, INTER3A

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

IRS3, IRS4, IRS9

• Rigid Surf

(Bz3D)

--

• Rigid

Surface(Lbc)

R3D3, R3D4

• 2D Rebar Cylindrical SFMCL9

General Standard Formulation SFM3D3, SFM3D4, SFM3D6, SFM3D8

Reduced Integration SFM3D4R, SFM3D8R

• 2D Gasket Plane Strain Gasket Behavior Model GKPE4

Built-in Material GKPE4

Plane Stress Gasket Behavior Model GKPS4

Thickness Behavior Only GKPS4N

Built-in Material GKPS4

Axisymmetric Gasket Behavior Model GKAX4

Thickness Behavior Only GKAX4N

Built-in Material GKAX4



Line Gasket Behavior Mode GK3D4L

Thickness Behavior Only GK3D4LN

Built-in Material GK3D4L

3D • Solid Standard Formulation

Laminate

C3D4, C3D6, C3D8, C3D10, C3D15, C3D20

Hybrid

Laminate

C3D4H, C3D6H, C3D8H, C3D10H, C3D15H, C3D20H

Hybrid/Red Integration Laminate

C3D8RH, C3D20RH

Reduced Integration Laminate

C3D8R, C3D20R

Incompatible Modes Laminate

C3D8I

Hybrid/Incomp Modes

Laminate

Modified

Modified/Hybrid

C3D8IH

C3D10M

C3D1OH

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

INTER4, INTER8, INTER9

• Gasket Gasket Behavior Model GK3D8, GK3D6

Thickness Behavior Only

GK3D8N, GK3D6N

Built-in Material GK3D8, GK3D6



104

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

Thermal.


1D • Link DCID2, DCID3

Axisymmetric

Shell

• Homogeneous

• Laminate

DSAX1, DSAX2

• 1D Interface DINTER1

2D Shell • Homogeneous

• Laminate

DS4, DS8

2D Solid • Planar Standard Formulation



with

Dispersion/Control

DC2D2, DC2D4,

DC2D6, DC2D8

DCC2D4

DCC2D4D

• Axisymmetric Standard Formulation



with

Dispersion/Control

DCAX3,

DCAX4,

DCAS6, DCAX8

DCCAX4

DCCAX4D

• 2D Interface Planar DINTER2,

DINTER3

Axisymmetric DINTER2A,

DINTER3A


3D • Solid Standard Formulation DC3D4, DC3D6,

DC3D8,

DC3D10,

DC3D15,

DC3D20

Convection/Diffusion DCC3D8


with Dispersion

Control

DCC3D8D

• 3D Interface DINTER4,

DINTER8



106

Point Mass

Options above create MASS elements with ∗MASS properties.This creates a concentrated mass at a

point. The mass is associated with the translational degrees-of-freedom at a node.

Analysis Type Dimension Type Option 1 Option 2 Topologies

Structural 0D Mass Point/1


Rotary Inertia

Options above createROTARI elements with ∗ROT ARY INERTIA properties. This element allows the

rotary inertia of a rigid body to be included at a node. An ∗ORIENTATION option may also be created,

as required.


Structural 0D Rotary Inertia Point/1


108

Linear Spring (Grounded)

Options above create SPRING1 elements with ∗SPRING properties. This element defines a linear spring

between a node and ground. An ∗ORIENTATION option may also be created, as required.


Structural 0D Grounded Spring Linear Point/1


Nonlinear Spring (Grounded)

Options above create SPRING1 elements with ∗SPRING properties. This element defines a nonlinear

spring between a node and ground. An ∗ORIENTATION option may also be created, as required.

Linear Damper (Grounded)


Structural 0D Grounded Spring Nonlinear Point/1


Structural 0D Grounded Damper Linear Point/1


110

Options above create DASHPOT1 elements with ∗DASHPOT properties. This element defines a linear

damper between a node and ground. An ∗ORIENTATION option may also be created, as required.

Nonlinear Damper (Grounded)

Options above create DASHPOT1 elements with ∗DASHPOT properties. This element defines a

nonlinear dashpot between a node and ground. An ∗ORIENTATION option may also be created, as

required.


Structural 0D Grounded Damper Nonlinear Point/1


112

IRS (Single Node, Planar)

Options above create IRS12 elements with ∗INTERFACE and ∗FRICTION properties. This element

defines an interface between a node on a planar model and a rigid surface.


Structural 0D IRS

(single

node)

Planar Elastic Slip Soft Contact

Elastic Slip Hard Contact

Lagrange Soft Contact

Lagrange Hard Contact

Elastic Slip No Separation

Lagrange No Separation

Elastic Slip Vis Damping

Elastic Slip Vis Damping No

Separation


Lagrange Vis Damping No

Separation

Point/1


More=data input is available for creating IRS (single node, planar) elements by scrolling down the input

properties menu bar on the previous page. Listed below are the remaining options contained in this menu.

Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more

than one of these options, all but the first will be ignored.


Friction in Dir_1 Defines the sliding friction in the element’s 1 direction. This is the

friction coefficient on the second card of the *FRICTION option

definition.

Elastic Slip Defines the absolute magnitude of the allowable maximum elastic

slip to be used in the stiffness method for sticking friction. This is

the value of the ELASTIC SLIP parameter on the ∗FRICTION

option.

Slip Tolerance Defines the value of , to redefine the ratio of allowable

maximum elastic slip to characteristic element length dimension.

The default is .005. This is the value of the SLIP TOLERANCE

parameter on the ∗FRICTION option.

Stiffness in Stick This is currently not used.

Ff


114

Maximum Friction Stress Defines the equivalent shear stress limit of the gap element. This is

the value of the TAUMAX parameter on the ∗FRICTION option.

Clearance Zero-Pressure Defines the clearance at which the contact pressure is 0. This is the

c value on the *SURFACE CONTACT, SOFTENED option. This

property is only used for the Soft Contact option. This is a real

constant.

Pressure Zero Clearance Defines the pressure at zero clearance. This is the value on the

*SURFACE CONTACT, SOFTENED option. This property is only

used for the Soft Contact option. This is a real constant.

Maximum Overclosure Defines the maximum overclosure allowed in points not considered

in contact. This is the c value on the *SURFACE CONTACT

option. This property is only used for the Soft Contact option. This

is a real constant.

Maximum Negative

Pressure

Defines the magnitude of the maximum negative pressure allowed

to be carried across points in contact. This is the value on the

*SURFACE CONTACT option. This property is only used for the

Hard Contact option. This is a real constant.

No Sliding Contact Chooses the Lagrange multiplier formulation for sticking friction

when completely rough (no slip) friction is desired.

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

Damping Zero Clearance Damping coefficient at zero clearance.

Frac Clearance Const Damping

Fraction of the clearance interval over which the damping

coefficient is constant.


p0

p0


IRS (Single Node, Spatial)

Options above create IRS13 elements with ∗INTERFACE and ∗FRICTION properties. This element

defines an interface between a node on a spatial model and a rigid surface.


Structural 0D IRS

(single

node)

Spatial Elastic Slip Soft Contact








No Separation



No Separation

Point/1


116

More data input is available for creating IRS (single node, spatial) elements by scrolling down the input





Friction in Dir_1

Friction in Dir_2

Defines the sliding friction in the element’s 1- and 2-directions. These are

the friction coefficients on the second card of the ∗FRICTION option. If

Friction in Dir_2 is specified, then the ANISOTROPIC parameter is

included on the ∗FRICTION option. These values can be either real

constants or references to existing field definitions.

Elastic Slip Defines the absolute magnitude of the allowable maximum elastic slip to

be used in the stiffness method for sticking friction. This is the value of

the ELASTIC SLIP parameter on the ∗FRICTION option.

Slip Tolerance Defines the value of , to redefine the ratio of allowable maximum

elastic slip to characteristic element length dimension. The default is

.005. This is the value of the SLIP TOLERANCE parameter on the

∗FRICTION option.

Ff


General Beam in Plane

Options above create B21, B22, B23, B21H, B22H, or B23H elements, depending on the specified

options and topology. ∗BEAM GENERAL SECTION, SECTION=GENERAL properties are also

created. This defines a general section beam which is restricted to remain in the XY plane.


Maximum Friction

Stress

Defines the equivalent shear stress limit of the gap element. This is the

equivalent shear stress limit value on the second card of the *FRICTION

option.

Clearance Zero-Pressure Defines the clearance at which the contact pressure is 0. This is the

c value on the *SURFACE CONTACT, SOFTENED option. This

property is only used for the Soft Contact option. This is a real constant.


*SURFACE CONTACT, SOFTENED option. This property is only used

for the Soft Contact option. This is a real constant.

Maximum Overclosure Defines the maximum overclosure allowed in points not considered in

contact. This is the c value on the *SURFACE CONTACT option. This


Maximum Negative

Pressure

Defines the magnitude of the maximum negative pressure allowed to be

carried across points in contact. This is the value on the *SURFACE

CONTACT option. This property is only used for the Hard Contact

option. This is a real constant.

No Sliding Contact Chooses the Language multiplier formulation for sticking friction when

completely rough (no slip) friction is desired.

Clearance Zero Damping

Clearance at which the damping coefficient is zero.

Damping Zero Clearance

Damping coefficient at zero clearance.


Fraction of the clearance interval over which the damping coefficient is

constant.


Structural 1D Beam in XY

Plane

General

Section

Standard Formulation

Hybrid

Cubic Interpolation

Cubic Hybrid

Bar/2, Bar/3

Bar/2, Bar/3

Bar/2

Bar/2


p0

p0


118

More data input is available for creating General Beam in Plane elements by scrolling down the input



Poisson Parameter Permits an “overall” change of the cross section dimensions as a

function of the axial strains. This is the value of the POISSON

parameter on the *BEAM GENERAL SECTION option.

Shear Factor The product of this factor, the beam cross-sectional area, and the

shear modulus for the material defines the transverse shear stiffness

for the beam.


Box Beam in Plane/Space

Options above create B21, B22, B23, B21H, B22H, or B23H elements in a plane, or B31, B32, B33, B34,

B31H, B32H or B33H elements in space, depending on the specified options and topology. ∗BEAM

SECTION, SECTION=BOX properties are also created. The planar box section beam is restricted to

remain in the XY-plane. For the spatial beam, ∗TRANSVERSE SHEAR STIFFNESS is also created, as

required.


Structural 1D Beam in

XY Plane

Box Section Standard Formulation

Hybrid

Cubic Interpolation

Cubic Hybrid

Bar/2, Bar/3

Bar/2, Bar/3

Bar/2

Bar/2


120


More data input is available for creating Box Beam in Plane elements by scrolling down the input


Beam Shape Display in Plane/Space

All of the beam shapes can be displayed in their proper orientation on the 3D model. To activate the

display, go to Display/Load/BC/Elem. Props... and set the "Beam Display" option. These options are

discribed in detail in Display>LBC/Element Property Attributes (p. 385) in the Patran Reference Manual.

The beam display is shown on beam elements only, not geometry.


Thickness_RHS

Thickness_TOP

Thickness_LHS

Thickness_BOT

Defines the wall thickness of the element cross section. These are for

the right-hand side, top, left-hand side, and bottom, respectively.

These are four of the data values on the second card of the *BEAM

SECTION option. These can be either real constants or references to

existing field definitions. These properties are required.




Shear Factor The product of this factor, the beam cross-sectional area, and the shear

modulus for the material defines the transverse shear stiffness for the

beam.

Definition of XY Plane (for

beams in space only)

Defines the orientation of the XY-plane of the element coordinate

system. The required input is a vector in the beam’s 1-direction. This

corresponds to the second line of data under the *BEAM SECTION

option. All of the Patran tools are available via the select menu to

define this vector.


122

Additional Beam Shapes in Plane/Space

Additional commonly used beam cross-sectional shapes are defined by forms analogous to that for box

beams. The planar option defines a beam which is restricted to remain in the XY plane. For the spatial

beam, *ORIENTATION and *TRANSVERSE SHEAR STIFFNESS is also created, as required.

CIRCULAR BEAM (SOLID)

This property will have the SECTION=CIRC parameter. All that is required for the definition of the cross

section is the radius. The integration schemes for planar analysis (left) and spatial analysis(right) are

shown below.

HEXAGONAL BEAM

This property will have the SECTION=HEX parameter. All that is required for the definition of the cross

section is the circumscribing radius and the wall thickness. The integration schemes for planar analysis

(left) and spatial analysis (right) are shown below.


I-SECTION

This property will have the SECTION=I parameter. The height of section, flange widths, and associated

thicknesses are required. In addition, the height of the centroid, depicted as “l” is also required. This

allows placement of the origin of the local cross-section axis anywhere on the symmetry line. Note also

that judicious specification of the flange widths and thicknesses will allow modelling of a T-section. See

p. 3.5.2-11 of the ABAQUS User’s Manual for details. The integration schemes for planar analysis (left)

and spatial analysis (right) are shown below.

PIPE BEAM

This property will have the SECTION=PIPE parameter. The pipe thickness and outside radius define

the cross section. The integration schemes for planar analysis (left) and spatial analysis (right) are

shown below.


124

RECTANGULAR BEAM (SOLID)

This property will have the SECTION=RECT parameter. The section width and section height define the

cross section. The integration schemes for planar analysis (left) and spatial analysis (right) are

shown below.

TRAPEZOID BEAM (SOLID)

This property will have the SECTION=TRAP parameter. The top and bottom width and section height

define the cross section. The integration schemes for planar analysis (left) and spatial analysis (right) are

shown below.

General Beam in Space



Space

General

Section


Hybrid

Cubic Interpolation

Cubic Hybrid

Cubic Initially

Straight

Bar/2, Bar/3

Bar/2, Bar/3

Bar/2

Bar/2

Bar/2


Options above create B31, B32, B33, B34, B31H, B32H, or B33H elements depending on the specified

options and topology. *BEAM GENERAL SECTION properties are also created. This property will have

the SECTION=GENERAL parameter. *ORIENTATION and *TRANSVERSE SHEAR STIFFNESS

options are also created, as required. This defines a general section beam.

More data input is available for creating General Beam in Space elements by scrolling down the input



126


Area Moment I12 Defines the area moment of the element cross section. This is the I12

value on the second card of the *BEAM GENERAL SECTION

option. This can be either a real constant or a reference to an existing

field definition.

Torsional Constant Defines the torsional constant of the element cross section. This is the

J value on the second card of the *BEAM GENERAL SECTION

option. This can be either a real constant or a reference to an existing

field definition.

Definition of XY Plane Defines the orientation of the XY plane of the element coordinate

system. The required input is a vector in the beam’s 1-direction. This

corresponds to the second line of data under the ∗BEAM GENERAL

SECTION option. All of the Patran tools are available via the select

menu to define this vector.

Centroid Coord 1

Centroid Coord 2

Defines the location of the centroid of the cross section with respect

to the local cross section coordinate system. These values are either

real constants or references to existing field definitions. These are the

values on the ∗CENTROID suboption of the ∗BEAM GENERAL

SECTION option.

Shear Centroid Coord 1

Shear Centroid Coord 2

Defines the location of the shear centroid of the cross section with

respect to the nodal locations. These values are measured in the local

cross section coordinate system. These values are either real constants

or references to existing field definitions. These are the values on the

*SHEAR CENTER suboption on the *BEAM GENERAL SECTION

option.






beam. This value appears on the ∗TRANSVERSE SHEAR

STIFFNESS option.

Section Point Coord 1


Defines the coordinates of points in the beam cross section where

output is requested. These are lists of real constants. These values are

measured in the beam cross section coordinate system. The lists must

have the same number of entries. These are the values on the

*SECTION POINTS suboption of the *BEAM GENERAL

SECTION option.


Arbitrary Beam in Space


options and topology. ∗BEAM SECTION, SECTION=ARBITRARY properties are also created.

∗ORIENTATION and ∗TRANSVERSE SHEAR STIFFNESS options are created, as required. This

defines an arbitrary section beam.



Space

Arbitrary

Section

Standard

Formulation

Hybrid

Cubic Interpolation

Cubic Hybrid

Cubic Initially

Straight

Bar/2, Bar/3

Bar/2, Bar/3

Bar/2

Bar/2

Bar/2


128

More data input is available for creating Arbitrary Beam in Space elements by scrolling down the input

properties menu bar on the previous page. Listed below are the remaining options contained in this menu


Definition of XY Plane Defines the cross section axis N1 of the beam such that the tangent

along the beam and the cross section axes N1 and N2 form a right-

hand rule. This is the data on the second card of the ∗BEAM

SECTION option. This is a real vector. This property is required.







beam. This value appears on the ∗TRANSVERSE SHEAR

STIFFNESS option.



130

Curved Pipe in Space

Options above create ELBOW31, ELBOW32, ELBOW31B, or C elements depending on the specified

options and topology. ∗BEAM SECTION, SECTION=ELBOW properties are also created.


defines an elbow element.



Space

Curved

w/Pipe

Section


Ovalization Only

Ovaliz Only w/ Approx

Fourier

Bar/2, Bar/3

Bar/2

Bar/2


More data input is available for creating Curved Pipe in Space elements by scrolling down the input



Torus Radius Defines the radius of the elbow bend. This is one of the data values on the

second card of the *BEAM SECTION option. This is either a real

constant or a reference to an existing field definition. This property is

required.

Integ Points around Pi Defines the number of integration points to be used around the pipe cross

section. This is the second value on the fourth card of the *BEAM

SECTION option. This is an integer value. This property is required.


132

L-Section Beam in Space


options and topology. ∗BEAM SECTION, SECTION=L properties are also created.


defines an L-section beam.

Point Tangents Inters Defines the orientation of the XY plane of the element coordinate system.

This is the data on the second card of the *BEAM SECTION option. This

is a Node ID. This property is required.

Integ Points thru Thick Defines the number of integration points to be used through the pipe wall

thickness. This is the first value on the fourth card of the *BEAM

SECTION option. This is an integer value.

# Ovalization Modes Defines the number of ovalization modes to be included in the shape

functions of this element. This is the third value of the fourth card of the

*BEAM SECTION option. This is an integer value.

Poisson Parameter Permits an “overall” change of the cross section dimensions as a function

of the axial strains. This is the value of the POISSON parameter on the

∗BEAM SECTION option.



beam. This value appears on the ∗TRANSVERSE SHEAR STIFFNESS

option.



Space

L-Section Standard Formulation

Hybrid

Cubic Interpolation

Cubic Hybrid

Cubic Initially Straight

Bar/2, Bar/3

Bar/2, Bar/3

Bar/2

Bar/2

Bar/2



More data input is available for creating L-Section Beam in Space elements by scrolling down the input



Definition of XY Plane

Defines the cross section axis N1 of the beam such that the tangent along the

beam and the cross section axes N1 and N2 form a right-hand rule. This is

the data on the second card of the *BEAM SECTION option. This is a real

vector. This property is required.

Poisson Parameter Permits an “overall” change of the cross section dimensions as a function of

the axial strains. This is the value of the POISSON parameter on the ∗BEAM

SECTION option.


134

Open Beam in Space

Options above create B31OS, B32OS, B31OSH, or B32OSH elements depending on the specified

options and topology. ∗BEAM GENERAL SECTION, SECTION=GENERAL properties are also

created. ∗ORIENTATION and ∗TRANSVERSE SHEAR STIFFNESS options are created, as required.

This defines an open section beam.

Shear Factor The product of this factor, the beam cross sectional area, and the shear

modulus for the material defines the transverse shear stiffness for the beam.

This value appears on the ∗TRANSVERSE SHEAR STIFFNESS option.



Space

Open

Section


Hybrid

Bar/2, Bar/3

Bar/2, Bar/3



More data input is available for creating Open Beam in Space elements by scrolling down the input



Area Moment I12 Defines the area moment of the element cross section. This is the I12 value on

the second card of the *BEAM GENERAL SECTION option. This can be

either a real constant or a reference to an existing field definition.

Torsional Constant Defines the torsional constant of the element cross section. This is the J value

on the second card of the *BEAM GENERAL SECTION option. This can be

either a real constant or a reference to an existing field definition.


136

Truss

Definition of XY Plane Defines the cross section axis N1 of the beam such that the tangent along the

beam and the cross section axes N1 and N2 form a right-hand rule. This is the

data on the second card of the *BEAM GENERAL SECTION option. This is

a real vector. This property is required.

1st. Sectorial Moment This can be either a real constant or a reference to an existing field definition.

This property is required for open section beams.

Warping Constant This can be either a real constant or a reference to an existing field definition.

This property is required for open section beams.

Centroid Coord 1

Centroid Coord 2

Defines the location of the centroid of the cross section with respect to the

local cross section coordinate system. These values are either real constants

or references to existing field definitions. These are the values on the

∗CENTROID suboption of the ∗BEAM GENERAL SECTION option.

Shear Center Coord 1

Shear Center Coord 2

Defines the location of the shear centroid of the cross section with respect to

the local cross section coordinate system. These values are either real

constants or references to existing field definitions. These are the values on

the ∗SHEAR CENTER suboption of the ∗BEAM GENERAL SECTION

option.

Poisson Parameter Permits an “overall” change of the cross section dimensions as a function of

the axial strains. This is the value of the POISSON parameter on the *BEAM

GENERAL SECTION option.


modulus for the material defines the transverse shear stiffness for the beam.

This value appears on the ∗TRANSVERSE SHEAR STIFFNESS option.



Defines the coordinates of points in the beam cross section where output is

requested. These are lists of real constants. These values are measured in the

beam cross section coordinate system. The lists must have the same number

of entries. These are the values on the ∗SECTION POINTS suboption of the

∗BEAM GENERAL SECTION option.


Structural 1D Truss Standard

Formulation

Hybrid

Bar/2. Bar/3

Bar/2. Bar/3



Options above create T3D2, T3D2H, T3D3, or T3D3H elements depending on the specified options and

topology. *SOLID SECTION properties are also created. The cross sectional area is included on the

*SOLID SECTION option.

Linear Spring (Axial)

Options above create SPRINGA elements with *SPRING properties. This element defines a linear spring

between two nodes whose line of action is the line joining the two nodes.


Structural 1D Spring Linear Standard Formulation Bar/2


138

Linear Spring (Fixed Direction)

Options above create SPRING2 elements with *SPRING properties.This element defines a linear spring

between specified degrees-of-freedoms at two nodes. An *ORIENTATION option may also be created,

as required.


Structural 1D Spring Linear Fixed Direction Bar/2


Nonlinear Spring (Axial)

Options above create SPRINGA elements with *SPRING properties.This element defines a nonlinear

spring between two nodes whose line of action is the line joining the two nodes.


Structural 1D Spring Nonlinear Standard

Formulation

Bar/2


140

Nonlinear Spring (Fixed Direction)

Options above create SPRING2 elements with ∗SPRING properties. This element type defines a

nonlinear spring between two nodes, acting in a fixed direction. An ∗ORIENTATION option may also

be created, as required.


Structural 1D Spring Nonlinear Fixed Direction Bar/2


Linear Damper (Axial)

Options above create DASHPOTA elements with ∗DASHPOT properties. This element type defines a

linear damper between two nodes whose line of action is the line joining the two nodes.


Structural 1D Damper Linear Standard

Formulation

Bar/2


142

Linear Damper (Fixed Direction)

Options above create DASHPOT2 elements with ∗DASHPOT properties. This element type defines a

linear damper between two nodes, acting in a fixed direction. An ∗lofbkq^qflk option may also be

created, as required.


Structural 1D Damper Linear Fixed Direction Bar/2


Nonlinear Damper (Axial)

Options above create DASHPOTA elements with ∗DASHPOT properties. This element type defines a

nonlinear damper between two nodes whose line of action is the line joining the two nodes.


Structural 1D Damper Nonlinear Standard

Formulation

Bar/2


144

Nonlinear Damper (Fixed Direction)

Options above create DASHPOT2 elements with ∗a^pemlq properties. This element type defines a

nonlinear damper between two specified nodes, acting in a fixed direction. An ∗lofbkq^qflk option

may also be created, as required.


Structural 1D Damper Nonlinear Fixed Direction Bar/2


Gap (Uniaxial), Gap (Cylindrical)


Structural 1D Gap Cylindrical

Uniaxial

True Distance

Elastic Slip Soft Contact








No Separation



Separation

Bar/2


146

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

created, as required.


Gap (Spherical)

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

as required.


Structural 1D Gap Spherical True Distance









No Separation



Separation

Bar/2


148

Axisymmetric Shell

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

SECTION properties.


Structural 1D Axisymmetric

Shell

Homogeneous Bar/2 Bar/3


Axisymmetric Shell (Laminate)

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

SECTION, COMPOSITE properties.


Structural 1D Axisymmetric Shell Laminate Bar/2


150


1D Interface

Options above create INTER1 elements with *INTERFACE, *FRICTION, and *SURFACE CONTACT

properties. The SOFTENED parameter on the *SURFACE CONTACT option may be included,

depending on the selected option. This element defines an interface region between two portions of an

axisymmetric model. These elements must be created from one contact surface to the other.


Structural 1D 1D

Interface


Elastic Slip Hard

Contact



Elastic Slip No

Separation


Elastic Slip Vis

Damping

Elastic Slip Vis

Damping No Separation



No Separation

Bar/2


152

More data input is available for creating 1D Interface elements by scrolling down the input properties

menu bar on the previous page. Listed below are the remaining options contained in this menu. Elastic

Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered for more than

one of these options, all but the first will be ignored.


Elastic Slip Defines the absolute magnitude of the allowable maximum elastic slip

to be used in the stiffness method for sticking friction. This is the value

of the ELASTIC SLIP parameter on the ∗FRICTION option.

Slip tolerance Defines the value of , to redefine the ratio of allowable maximum



∗FRICTION option.


Maximum Friction Stress Defines the equivalent shear stress limit of the gap element. This is the

value of the TAUMAX parameter on the ∗FRICTION option.

Ff


Planar ISL (In Plane)

Clearance Zero-Pressure Defines the clearance at which the contact pressure is 0. This is the c

value on the ∗SURFACE CONTACT, SOFTENED option. This






contact. This is the c value on the ∗SURFACE CONTACT option. This


Maximum Negative Pressure


carried across points in contact. This is the value on the ∗SURFACE








Fraction of the clearance interval over which the damping coefficient

is constant.

Analysis TypeDimensio

n Type Option 1 Option 2 Topologies

Structural 1D ISL (in

plane)





Elastic Slip No

Separation




No Separation



No Separation

Bar/2, Bar/3


p0

p0


154

Options above create ISL21 or ISL22 elements (depending on the selected topology) with *INTERFACE

and *FRICTION properties. This element defines an interface between the edge of an element on a planar

model and another part of the model.

More data input is available for creating Planar ISL (in plane) elements by scrolling down the input






friction coefficient on the second card of the *FRICTION option.








∗FRICTION option.




Clearance Zero Pressure Defines the clearance at which the contact pressure is 0. This is the

c value on the ∗SURFACE CONTACT, SOFTENED option. This


Press Zero Clearance Defines the pressure at zero clearance. This is the value on the

∗SURFACE CONTACT, SOFTENED option. This property is only used





Maximum Negative

Pressure











constant.


Ff

p0

p0


156

Axisymmetric ISL (In Plane)

Options above create ISL21A or ISL22A elements (depending on the selected topology) with

*INTERFACE and *FRICTION properties. This element defines an interface between the edge of an

element on an axisymmetric model and another part of the model.



plane)

Axisymmetric Elastic Slip Soft Contact








No Separation



Separation

Bar/2, Bar/3


More data input is available for creating Axisymmetric ISL (in plane) elements by scrolling down the

input properties menu bar on the previous page. Listed below are the remaining options contained in this

menu. Elastic Slip, Slip Tolerance, and No Sliding Contact are mutually exclusive. If values are entered

for more than one of these options, all but the first will be ignored.






of the ELASTIC SLIP parameter on the ∗FRICTION option.




∗FRICTION option.


Ff


158

Parallel ISL (In Space)



Clearance Zero Pressure Defines the clearance at which the contact pressure is 0. This is the c

value on the *SURFACE CONTACT, SOFTENED option. This


constant.


∗SURFACE CONTACT, SOFTENED option. This property is only





constant.


Defines the magnitude of the maximum negative pressure allowed to

be carried across points in contact. This is the value on the



No Sliding Contact Chooses the Language multiplier formulation for sticking friction






is constant.



space)

Parallel Elastic Slip Soft Contact








No Separation

Lagrange Vis Dampin


Separation

Bar/2, Bar/3


p0

p0



and *FRICTION properties. This element type defines an interface between the edge of an element and

another part of the model.

More data input is available for creating Parallel ISL (in space) elements by scrolling down the input





Friction in Dir_1

Friction in Dir_2

Defines the sliding friction in the element’s 1 and 2 directions. These are

the friction coefficients on the second card of the *FRICTION option. If


included on the *FRICTION option. These values can be either real


Vector Defines the normal to the plane in which sliding contact occurs. This is

the second card of the *INTERFACE option. This value is a global

vector. This property is required.


160



the ELASTIC SLIP parameter on the *FRICTION option.




*FRICTION option.



value of the TAUMAX parameter on the *FRICTION option.


value on the *SURFACE CONTACT, SOFTENED option. This property

is only used for the Soft Contact option. This is a real constant.









carried across points in contact. This is the p0 value on the *SURFACE









constant.


Ff

p0


Radial ISL (In Space)


and *FRICTION properties. This element defines an interface between the edge of an element and

another part of the model.


Structural 1D ISL (in space) Radial Elastic Slip Soft Contact








No Separation



No Separation

Bar/2, Bar/3


162

More data input is available for creating Radial ISL (in space) elements by scrolling down the input





Friction in Dir_1

Friction in Dir_2

Defines the sliding friction in the element’s 1- and 2-directions. These are





Vector Defines the normal to the plane in which sliding contact occurs. This is the

second card of the ∗INTERFACE option. This value is a global vector.

This property is required.





Slide Line

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

continuous.


elastic slip to characteristic element length dimension. The default is .005.

This is the value of the SLIP TOLERANCE parameter on the

∗FRICTION option.


Maximum Friction Stress

Defines the equivalent shear stress limit of the gap element. This is the


Clearance Zero Pressure

Defines the clearance at which the contact pressure is 0. This is the c value

on the ∗SURFACE CONTACT, SOFTENED option. This property is only


Pressure Zero Clearance

Defines the pressure at zero clearance. This is the value on the













Clearance Zero Damping

Clearance at which the damping coefficient is zero.

Damping Zero Clearance

Damping coefficient at zero clearance.



constant.



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


Ff

p0

p0


164

IRS (Planar)

Analysis Type Dimension Type

Option 1 Option 2 Topologies

Structural 1D IRS

(plane/axisym)









No Separation



Separation

Bar/2, Bar/3


Options above create IRS21 or IRS22 elements (depending on the selected topology) with *INTERFACE

and *FRICTION properties. This element type defines an interface between the edge of a linear element

on a planar model and a rigid surface.

More data input is available for creating IRS (planar) elements by scrolling down the input properties









of the ELASTIC SLIP parameter on the *FRICTION option.


166




*FRICTION option.





value on the *SURFACE CONTACT, SOFTENED option. This


constant.


*SURFACE CONTACT, SOFTENED option. This property is only


Maximum Overclosure Defines the maximum overclosure allowed in points considered not in

contact. This is the c value on the *SURFACE CONTACT option.

This property is only used for the Hard Contact option. This is a

real constant.


Defines the magnitude of the maximum negative pressure allowed to

be carried across points in contact. This is the value on the









is constant.


Ff

p0

p0


IRS (Axisymmetric)

Options above create IRS21A or IRS22A elements (depending on the selected topology) with

*INTERFACE and *FRICTION properties. This element type defines an interface between the edge of

a linear element on an axisymmetric model and a rigid surface.

Analysis Type

Dimension Type Option 1 Option 2 Topologies

Structural 1D IRS

(plane/axisym)

Axisymmetric Elastic Slip Soft Contact

Elastic Slip Hard

Contact



Elastic Slip No

Separation


Elastic Slip Vis

Damping

Elastic Slip Vis

Damping No Separation



No Separation

Bar/2, Bar/3


168

More data input is available for creating IRS (axisymmetric) elements by scrolling down the input













∗FRICTION option.


Ff


IRS (Beam/Pipe)




value on the ∗SURFACE CONTACT, SOFTENED option. This property







property is only used for the Hard Contact option. This is a real constant.












is constant.

Analysis Type Dimension Type Option 1

Option 2 Topologies

Structural 1D IRS

(beam/pipe)









No Separation



Separation

Bar/2, Bar/3


p0

p0


170

Options above create IRS31 or IRS32 elements (depending on the selected topology) with *INTERFACE

and *FRICTION properties. This element type defines an interface between a beam or pipe element on

a spatial model and a rigid surface.

More data input is available for creating IRS (beam/pipe) elements by scrolling down the input properties





Friction in Dir_1

Friction in Dir_2


the friction coefficients on the second card of the *FRICTION option. If


included on the *FRICTION option. These values can be either real




the ELASTIC SLIP parameter on the *FRICTION option.


Rigid Surface (Segments)

Options above create a ∗RIGID SURFACE, TYPE=SEGMENTS option (see Section 7.4.7 of the

ABAQUS/Standard User’s Manual).

The rigid surface is defined by creating Bar/2 elements. All the elements must be connected and should

not have duplicate nodes. The start Point (Node ID) defines the positive progression direction along the

surface. The right-handed rotation from this direction defines the outward normal.




*FRICTION option.















carried across points in contact. This is the value on the *SURFACE



No Sliding Contact Defines the ROUGH parameter on the *FRICTION option. This

property is only used for the Lagrange option.





constant.


Structural 1D Rigid Surf (Seg) Bar/2


Ff

p0

p0


172

Rigid Surface (Cylindrical)

Options above create a ∗RIGID SURFACE, TYPE = CYLINDRICAL option (see Section 7.4.7 of the


The rigid surface is first defined by creating Bar/2 elements. All the elements must be connected and

should not have duplicate nodes.

The rigid surface’s +x direction is defined from the start point (node ID) along the line of the rigid

surface. The +y direction is away from the object the rigid surface will be in contact with. The +z

direction (the surface generation vector) is defined by using right-hand rule, crossing the rigid surface’s

+x axis with the +y axis.


Structural 1D Rigid Surf (Cyl) Bar/2


Rigid Surface (Axisymmetric)

Options above create a ∗RIGID SURFACE, TYPE=AXISYMMETRIC option (see Section 7.4.7 of the



Structural 1D Rigid Surf (Axi) Bar/2


174


not have duplicate nodes. The Start Point defines the positive progression direction along the surface. The

right-handed rotation from this direction defines the outward normal.

Rigid Surface (Bezier 2D)


Structural 1D Rigid Surf (Bz2D) Bar/2


Options above create a ∗RIGID SURFACE, TYPE=BEZIER option for use in two-dimensional analysis

(see Section 7.4.7 of the ABAQUS/Standard User’s Manual).


not have duplicate nodes. The Start Point defines the positive progression direction along the surface. The

right-handed rotation from this direction defines the outward normal.

Rigid Line (LBC)


Structural 1D Rigid Line(LBC) Bar/2


176

This property set is created when the Rigid-Deform contact LBC is created in the Loads/BCs menu. The

creation or deletion of this property set is not required by the user. The elements associated with this

property set are translated as R2D2 and RAX2 elements.

Rebar

The options above create SFMAX1, SFMAX2, SFMGAX1 and SFMGAX2 elements (depending on the

selected options and topologies) with *SURFACE SECTION properties. The *EMBEDDED ELEMENT

and *REBAR LAYER options are also created.


Structural 1D Rebar Axisymmetric

General

Axisymmetric

Bar/2, Bar/3


Material Name Defines the material to be used. When entering data here, a list of all

isotropic materials in the database is displayed. You can either pick one from

the list with the mouse or type in the name. This identifies the material that

will be referenced on the *REBAR LAYER option. This property is

required.

X-Sectional Area Defines the area of the rebar cross-section. This is the cross-sectional area

value on the *REBAR LAYER option. A real constant, a reference to an

existing field definition, or a real list may be entered. A real list is used to

specify the cross-sectional area for more than one rebar layer. This property

is required.

Spacing Defines the spacing of the rebars within a layer. This is the spacing value on

the *REBAR LAYER option. A real constant, a reference to an existing field

definition, or a real list may be entered. A real list is used to specify the

spacing for more than one rebar layer. This property is required.

Spacing Unit Type Defines the unit type for the spacing values. When “Angle” is specified, the

ANGULAR SPACING parameter is used for the *REBAR LAYER option.

“Distance” is the default value. This property is not required.


178

Mech Joint (2D Model) - ALIGN

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

SECTION option.

Rebar Orient. Angle Defines the angular orientation of the rebar from the meridional plane in

degrees. This is the angular orientation value on the *REBAR LAYER

option. A real constant, a reference to an existing field definition, or a real

list may be entered. A real list is used to specify the angular orientation for

more than one rebar layer. This property is required.

Host Property Set Defines the element property set of the elements that host the rebar elements.

This is the “HOST ELSET” parameter on the *EMBEDDED ELEMENT

option. A reference to an existing element property set may be specified. By

default, the solver determines the host elements based on the position of the

embedded elements within the model. This property is not required.

Roundoff Tolerance Defines the value below which the weigh factors of the host element’s nodes

will be zeroed out. This is the ROUNDOFF TOLERANCE parameter on the

*EMBEDDED ELEMENT option. A real scalar may be specified. The

default value is 1E+6. This property is not required.


Structural 1D Mech Joint

(2D Model)

ALIGN Bar/2


Node A Analysis CID This property defines the directions for the degrees of freedom at the first

node of the connector element. It is translated to the ABAQUS input file

with an *ORIENTATION option and is referenced from the *CONNECTOR

SECTION option. Use an existing coordinate system to specify this

property.

Node B Analysis CID This property defines the directions for the degrees of freedom at the second




property.


180

Mech Joint (2D Model) - AXIAL

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

SECTION option.



(2D Model)

AXIAL Bar/2


Force/Disp, X Axis This stiffness property value defines the relationship between force and

relative displacement in the connector element. It is translated to the

ABAQUS input file with the *CONNECTOR ELASTICITY option. Use a

real constant or a non-spatial field to specify this property. The n on-spatial

fields that have been created with the “Tabular Input” method may be used

to define stiffness that varies with displacement and temperature. The

dependent variable for this field is force, and displacement is a required

independent variable.

Zero Force Ref Len This property value defines the reference length of the unloaded connector

element. This value is translated to the ABAQUS input file with the

*CONNECTOR CONSTITUTIVE REFERENCE option. Use a real

constant to specify this property.

Damping, X Axis This damping property value defines the relationship between force and the

rate of change of relative displacement in the connector element. It is

translated to the ABAQUS input file with the *CONNECTOR DAMPING

option. A real constant or a non-spatial field may be used for this property.

The non-spatial fields that have been created with the “Tabular Input”

method may be used to define damping that varies with velocity and

temperature. The dependent variable for these fields is force, and velocity is

a required independent variable.

Connector Min Stop This property value defines a lower limit for the connector's relative

position. This value is translated to the ABAQUS input file with the

*CONNECTOR STOP option. Use a real constant to specify this property.

Connector Max Stop This property value defines an upper limit for the connector's relative



Friction Lim, X Axis This property value defines the force limit associated with the friction

portion of the connector element. This value is translated to the ABAQUS

input file with the *CONNECTOR FRICTION option. A real constant or a

non-spatial field may be used to specify this property. The n on-spatial fields

that have been created with the “Tabular Input” method may be used to

define a limit that varies with temperature and/or displacement. The

dependent variable for these fields is force.

Friction Stick Stiff This property value defines the stiffness associated with the friction portion

of the connector element. This value appears as the STICK STIFFNESS

parameter in the *CONNECTOR FRICTION option. Use a real constant to

specify this property.

Lock, Min Disp This property value defines the lower bound on the relative position that

triggers a locked condition in the connector element. This value is translated

to the ABAQUS input file with the *CONNECTOR LOCK option. Use a

real constant to specify this property.


182

Mech Joint (2D Model) - BEAM

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

SECTION option.



(2D Model)

BEAM Bar/2



with an *ORIENTATION option and is referenced from the

*CONNECTOR SECTION option. Use an existing coordinate system to








Mech Joint (2D Model) - CARTESIAN

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

*CONNECTOR SECTION option.



(2D Model)

CARTESIAN Bar/2


node of the connector element. It is translated to the ABAQUS input file with

an *ORIENTATION option and is referenced from the *CONNECTOR


property.

Force/Disp, X Axis

Force/Disp, Y Axis

This stiffness property value defines the relationship between force and









184

Mech Joint (2D Model) - JOIN

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

SECTION option.

Zero Force Ref Len These property values define the reference lengths for the components of the

unloaded connector element. These values are translated to the ABAQUS

input file with the *CONNECTOR CONSTITUTIVE REFERENCE option.

Use a real vector to specify this property.

Damping, X Axis

Damping, Y Axis

This damping property value defines the relationship between force and the








Connector Min Stop These property values define the lower limits for the components of the

connector's relative position. These values are translated to the ABAQUS

input file with the *CONNECTOR STOP option. Use a real vector to specify

this property.

Connector Max Stop These property values define the upper limits for the components of the



this property.



(2D Model)

JOIN Bar/2


Mech Joint (2D Model) - JOINTC

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

define the properties.




SECTION option. Use an existing coordinate system to specify this property.



(2D Model)

JOINTC Bar/2


186



with an *ORIENTATION option and is referenced from the *JOINT option.

Use an existing coordinate system to specify this property.

Units for Angles This property determines the units for the angle values. It may be set to either

"Degrees" or "Radians". The default value is "Radians".

Force/Disp, X Axis

Force/Disp, Y Axis



ABAQUS input file with the *SPRING option. A real constant or a non-

spatial field may be used for this property. The non-spatial fields that have

been created with the “Tabular Input” method may be used to define stiffness

that varies with displacement and temperature. The dependent variable for

this field is force, and displacement is a required independent variable.


Mom/Rot about Z Axis

This stiffness property value defines the relationship between moment and



spatial field may be used for this property. The n on-spatial fields that have

been created with the “Tabular Input” method may be used to define stiffness

that varies with displacement and temperature. The dependent variable for

this field is moment, and displacement is a required independent variable.

Damping, X Axis

Damping, Y Axis



translated to the ABAQUS input file with the *DASHPOT option. A real

constant or non-spatial field may be used for this property. The non-spatial

fields that have been created with the “Tabular Input” method may be

used to define damping that varies with velocity and temperature. The

dependent variable for these fields is force, and velocity is a required


Rot Damping, Z Axis This damping property value defines the relationship between moment and

the rate of change of relative displacement in the connector element. It is

translated to the ABAQUS input file with the *DASHPOT option. A real

constant or a non-spatial field may be used for this property. The non-spatial

fields that have been created with the “Tabular Input” method may be

used to define damping that varies with velocity and temperature. The

dependent variable for these fields is moment, and velocity is a required



188

Mech Joint (2D Model) - LINK

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

SECTION option.


Structural 1D Mech Joint (2D

Model)

LINK Bar/2










Mech Joint (2D Model) - ROTATION

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




(2D Model)

ROTATION Bar/2






Node B Analysis CID This property defines the directions for the degrees of freedom at the

second node of the connector element. It is translated to the ABAQUS

input file with an *ORIENTATION option and is referenced from the




190

Units for Angles This property determines the units for the angle values. It may be set to

either "Degrees" or "Radians". The default value is "Radians".

Mom/Rot about Z Axis This stiffness property value defines the relationship between moment

and relative displacement in the connector element. It is translated to the

ABAQUS input file with the *CONNECTOR ELASTICITY option. A

real constant or a non-spatial field may be used for this property. The

non-spatial fields that have been created with the “Tabular Input”

method may be used to define stiffness that varies with displacement and

temperature. The dependent variable for this field is moment, and

displacement is a required independent variable.

Zero Moment Ref Ang This property value defines the reference angle of the unloaded

connector element. This value is translated to the ABAQUS input file

with the *CONNECTOR CONSTITUTIVE REFERENCE option. Use

a real constant to specify this property.

Rot Damping, Z Axis This damping property value defines the relationship between moment

and the rate of change of relative displacement in the connector element.

It is translated to the ABAQUS input file with the *CONNECTOR

DAMPING option. A real constant or non-spatial field may be used for

this property. The n on-spatial fields that have been created with the

“Tabular Input” method may be used to define damping that varies with

velocity and temperature. The dependent variable for these fields is

moment, and velocity is a required independent variable.


position. This value is translated to the ABAQUS input file with

the *CONNECTOR STOP option. Use a real constant to specify

this property.


position. This value is translated to the ABAQUS input file with

the *CONNECTOR STOP option. Use a real constant to specify

this property.


jÉÅÜ=gçáåí=EOa=jçÇÉäF=J=pilq

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

SECTION option.



Model)

SLOT Bar/2


192

















Damping, X Axis This damping property value defines the relationship between moment and



option. A real constant or non-spatial field may be used for this property. The

non-spatial fields that have been created with the “Tabular Input” method

may be used to define damping that varies with velocity and temperature.

The dependent variable for these fields is moment, and velocity is a required


Connector Min Stop This property value defines a lower limit for the connector's relative position.

This value is translated to the ABAQUS input file with the *CONNECTOR

STOP option. Use a real constant to specify this property.
















Mech Joint (2D Model) - TRANSLATOR

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




(2D Model)

TRANSLATOR Bar/2










194

Mech Joint (2D Model) - WELD

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

SECTION option.



(2D Model)

WELD Bar/2










Mech Joint (3D Model) - ALIGN

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

SECTION option.



(3D Model)

ALIGN Bar/2










196

Mech Joint (3D Model) - AXIAL

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

SECTION option.



(3D Model)

AXIAL Bar/2

















option. A real constant or non-spatial field may be used for this property.



temperature. The dependent variable for these fields is moment, and

velocity is a required independent variable.










non-spatial field may be used to specify this property. The non-spatial fields








Lock Min Disp This property value defines the upper bound on the relative position that

triggers a locked condition in the connector element. This value is translated

to the ABAQUS input file with the *CONNECTOR LOCK option. Use a

real constant to specify this property.


198

Mech Joint (3D Model) - BEAM

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

SECTION option.



(3D Model)

BEAM Bar/2












Mech Joint (3D Model) - CARDAN

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




(3D Model)

CARDAN Bar/2












200

jÉÅÜ=gçáåí=EPa=jçÇÉäF=J=`^oqbpf^k

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




Mom/Rot about X Axis

Mom/Rot about Y Axis





real constant or a non-spatial field may be used for this property. The n on-

spatial fields that have been created with the “Tabular Input” method may

be used to define stiffness that varies with displacement and temperature.

The dependent variable for this field is moment, and displacement is a

required independent variable.

Zero Moment Ref Ang These property values define the reference angles for the components of

the unloaded connector element. These values are translated to the

ABAQUS input file with the *CONNECTOR CONSTITUTIVE

REFERENCE option. Use a real vector to specify this property.

Rot Damping, X Axis This damping property value defines the relationship between moment and




The n on-spatial fields that have been created with the “Tabular Input”






(3D Model)

CARTESIAN Bar/2






property.

Force/Disp, X Axis

Force/Disp, YAxis

Force/Disp, Z Axis










202

Mech Joint (3D Model) - CONSTANT VELOCITY

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


Zero Force Ref Len These property values define the reference angles for the components of the




Damping, X Axis

Damping, Y Axis

Damping, Z Axis











(3D Model)

CONSTANT

VELOCITY

Bar/2


Mech Joint (3D Model) - CVJOINT

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





SECTION option. Use an existing coordinate system to specify

this property.





this property.



(3D Model)

CVJOINT Bar/2


204












Mech Joint (3D Model) - CYLINDRICAL

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




(3D Model)

CYLINDRICAL Bar/2





this property.





this property.


206

Mech Joint (3D Model) - EULER

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

SECTION option.



(3D Model)

EULER Bar/2


208

Mech Joint (3D Model) - FLEXION-TORSION

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








real constant or a non-spatial field may be used for this property. The non-









Rot Damping, X Axis This damping property value defines the relationship between moment










(3D Model)

FLEXION-TORSION Bar/2


210

Mech Joint (3D Model) - HINGE

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

SECTION option.
















Rot Damping, X Axis This damping property value defines the relationship between moment










(3D Model)

HINGE Bar/2


212

Mech Joint (3D Model) - JOIN

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

SECTION option.


Structural 1D Mech Joint (3D Model) JOIN Bar/2






Mech Joint (3D Model) - JOINTC

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

define the properties.


Structural 1D Mech Joint (3D Model) JOINTC Bar/2



with an *ORIENTATION option and is referenced from the *JOINT

option. Use an existing coordinate system to specify this property.




214

Force/Disp, X Axis

Force/Disp, Y Axis

Force/Disp, Z Axis




spatial field may be used for this property. The non-spatial fields that have

been created with the “Tabular Input” method may be used to define

stiffness that varies with displacement and temperature. The dependent

variable for this field is force, and displacement is a required








spatial field may be used for this property. The n on-spatial fields that have

been created with the “Tabular Input” method may be used to define

stiffness that varies with displacement and temperature. The dependent

variable for this field is moment, and displacement is a required



Mech Joint (3D Model) - LINK

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

SECTION option.


Structural 1D Mech Joint (3D Model) LINK Bar/2










216

Mech Joint (3D Model) - PLANAR

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

SECTION option.


Structural 1D Mech Joint (3D Model) PLANAR Bar/2


Mech Joint (3D Model) - RADIAL-THRUST

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






property.





property.



(3D Model)

RADIAL-THRUST Bar/2


218





property.

Force/Disp, X Axis

Force/Disp, ZAxis




real constant or a non-spatial field to specify this property. The non-spatial










Mech Joint (3D Model) - REVOLUTE

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


Damping, X Axis

Damping, Z Axis












this property.




this property.



(3D Model)

REVOLUTE Bar/2


220














Mech Joint (3D Model) - ROTATION

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


Mom/Rot about X Axis This stiffness property value defines the relationship between moment and








Zero Moment Ref Ang This property value defines the reference angle of the unloaded connector




















(3D Model)

ROTATION Bar/2


222














Mech Joint (3D Model) - SLIDE-PLANE

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



























(3D Model)

SLIDE-PLANE Bar/2


224





this property.

Force/Disp, Y Axis

Force/Disp, Z Axis














Mech Joint (3D Model) - SLOT

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

SECTION option.

Damping, Y Axis

Damping, Z Axis












this property.




this property.



(3D Model)

SLOT Bar/2


226


















Mech Joint (3D Model) - TRANSLATOR

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





option. A real constant or non-spatial field may be used for this property. The

non-spatial fields that have been created with the “Tabular Input” method

may be used to define damping that varies with velocity and temperature.

The dependent variable for these fields is moment, and velocity is a required


Connector Min Stop This property value defines a lower limit for the connector's relative position.

This value is translated to the ABAQUS input file with the *CONNECTOR

STOP option. Use a real constant to specify this property.

















(3D Model)

TRANSLATOR Bar/2


228

Mech Joint (3D Model) - UJOINT

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











(3D Model)

UJOINT Bar/2


SECTION option.










230

Mech Joint (3D Model) - UNIVERSAL

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




(3D Model)

UNIVERSAL Bar/2


Mech Joint (3D Model) - WELD

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


















real constant or a non-spatial field may be used for this property. The n on-









Rot Damping, X Axis

Rot Damping, Z Axis

This damping property value defines the relationship between moment and











Model)

WELD Bar/2


232

SECTION option.





property.





property.


Axisym Link Gasket

These options create GKAX2 elements. The *GASKET SECTION option is used to define the gasket

thickness, width, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is

used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to

define the membrane and transverse shear behaviors.


Structural 1D 1D Gasket Axisymmetric

Link

Gasket

Behavior Model

Bar2

Membrane Material This property defines the membrane material to be used. It is translated to the

ABAQUS input file as the *GASKET ELASTICITY option with the

COMPONENT parameter set to MEMBRANE. The Elastic Modulus and

Poisson's Ratio may vary with temperature. This property is not required.

Behavior Type This property defines the type of behavior for the thickness direction. It may

be set to either "Damage" or "Elastic-Plastic". This value is translated to the

ABAQUS input file as the TYPE parameter on the *GASKET THICKNESS

BEHAVIOR option. This property is required.


234

F/L vs. Closure (Loading)

This property defines the force per unit length versus gasket closure for

loading in the thickness direction. It is translated to the ABAQUS input file

as the *GASKET THICKNESS BEHAVIOR option with the DIRECTION

parameter set to LOADING. A non-spatial field created with the "Tabular

Input" method must be used to define this property. The field's independent

variables must be either Displacement or Displacement and Temperature.


F/L vs. Closure (Unloading)


unloading in the thickness direction. It is translated to the ABAQUS input

file as the *GASKET THICKNESS BEHAVIOR option with the

DIRECTION parameter set to UNLOADING. A non-spatial field created

with the "Tabular Input" method must be used to define this property. The

field's independent variables must be either displacement or displacement

and temperature. This property is not required.

Shear Stiffness This property defines the shear stiffness of the gasket elements. It is

translated to the ABAQUS input file as the *GASKET ELASTICITY option

with the COMPONENT parameter set to TRANSVERSE SHEAR. A real

constant or a non-spatial field may be used to define this property. The non-

spatial fields that have been created with the "Tabular Input" method may be

used to define shear stiffness that varies with temperature. This property is

not required.

Gasket Thickness This property defines the thickness of the gasket elements. It is translated to

the ABAQUS input file as an entry on the *GASKET SECTION option. A

real constant or a spatially varying field may be used to define this property.

This property is not required. When this property is not specified, the gasket

elements' thicknesses are determined from their nodal coordinates.

Thickness Direction This property defines the thickness direction (local one direction) for the

elements. It is translated to the ABAQUS input file on the *GASKET

SECTION option. A real vector or a spatially varying vector field may be

used to define this property. This property is not required.

Width This property defines the width of the gasket element. It is translated to the

ABAQUS input file as an entry on the *GASKET SECTION option. A real

constant or a spatially varying field may be used to define this property. This

property is required.

Initial Gap This property defines the initial gap in the thickness direction of the gasket

element. It is translated to the ABAQUS input file as an entry on the

*GASKET SECTION option. A real constant or a spatially varying field

may be used to define this property. This property is not required.

Initial Void This property defines the initial void in the thickness direction of the gasket





Axisym Link Gasket (Thick only)

These options create GKAX2N elements. The *GASKET SECTION option is used to define the gasket


used to define the behavior in the thickness direction.



Link

Thickness

Behavior Only

Bar2


236

Axisym Link Gasket (Material)





F/L vs. Closure (Loading)


loading in the thickness direction. It is translated to the ABAQUS input file

as the *GASKET THICKNESS BEHAVIOR option with the DIRECTION





F/L vs. Closure (Unloading)


unloading in the thickness direction. It is translated to the ABAQUS input


DIRECTION parameter set to UNLOADING. A non-spatial field created

with the "Tabular Input" method must be used to define this property. The

field's independent variables must be either displacement or displacement

and temperature. This property is not required.
























thickness, width, initial gap and initial void values. The gasket material is specified using the

MATERIAL parameter on the *GASKET SECTION option.



Link

Built-in Material Bar2

Material Name This property defines the material to be used. It is translated to the ABAQUS

input file as the MATERIAL parameter on the *GASKET SECTION option.








238

3D Link Gasket

These options create GK3D2 elements. The *GASKET SECTION option is used to define the gasket

thickness, x-sectional area, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR

option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is

used to define the transverse shear behavior.


















Structural 1D 1D Gasket 3D Link Gasket Behavior

Model

Bar2






F vs. Closure (Loading)

This property defines the force versus gasket closure for loading in the

thickness direction. It is translated to the ABAQUS input file as the

*GASKET THICKNESS BEHAVIOR option with the DIRECTION






240

F vs. Closure (Unloading)

This property defines the force versus gasket closure for unloading in the



parameter set to UNLOADING. A non-spatial field created with the "Tabular


variables must be either displacement or displacement and temperature. This

property is not required.







not required.










X-Sectional Area This property defines the x-sectional area of the gasket element. It is

translated to the ABAQUS input file as an entry on the *GASKET

SECTION option. A real constant or a spatially varying field may be used to

define this property. This property is required.

Orientation System This property defines the coordinate system to use in defining the local two

and three directions for the gasket elements. It is translated to the ABAQUS

input file as an *ORIENTATION option that is referenced in the *GASKET

SECTION option from the ORIENTATION parameter. An existing

coordinate frame may be used to define this property. This property is not

required.

Orientation Axis This property defines the axis of rotation of the Orientation System for the

Orientation Angle. It is translated to the ABAQUS input file as an

*ORIENTATION option that is referenced in the *GASKET SECTION

option from the ORIENTATION parameter. An integer value of 1, 2 or 3

may be used to define this property. This property is not required. The

default value is 1.


3D Link Gasket (Thick only)

These options create GK3D2N elements. The *GASKET SECTION option is used to define the gasket


option is used to define the behavior in the thickness direction.

Orientation Angle This property defines the additional rotation about the Orientation Axis in

degrees. It is translated to the ABAQUS input file as an *ORIENTATION

option that is referenced in the *GASKET SECTION option from the

ORIENTATION parameter. A real constant or a spatially varying field may

be used to define this property. This property is not required.










Structural 1D 1D Gasket 3D Link Thickness

Behavior Only

Bar2


242





F vs. Closure (Loading)









F vs. Closure (Unloading)


















translated to the ABAQUS input file as an entry on the *GASKET SECTION

option. A real constant or a spatially varying field may be used to define this

property. This property is required.



*GASKET SECTION option. A real constant or a spatially varying field may







244

3D Link Gasket (Material)


thickness, x-sectional area, initial gap and initial void values. The gasket material is specified using the



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






















coordinate frame may be used to define this property. This property is

not required.






default value is 1.















246

2D Link Gasket



option is used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is

used to define the transverse shear behavior.


Structural 1D 1D Gasket 2D Link Gasket Behavior

Model

Bar2






F vs Closure (Loading)








F vs Closure (Unloading)














not required.















248

2D Link Gasket (Thick only)

These options create GK2D2N elements. The *GASKET SECTION option is used to define the gasket


option is used to define the behavior in the thickness direction.










Structural 1D 1D Gasket 2D Link Thickness

Behavior Only

Bar2






F vs Closure (Loading)









250

F vs Closure (Unloading)






























2D Link Gasket (Material)


thickness, x-sectional area, initial gap and initial void values. The gasket material is specified using the



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


252

Thin Shell

Options above create STRI35, STRI65, S4R5, S8R5, or S9R5 elements with *SHELL SECTION

properties. *ORIENTATION, *TRANSVERSE SHEAR STIFFNESS, and *HOURGLASS STIFFNESS

options may also be created, as required. This element defines a standard thin shell element.


























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

Quad/8, Quad/9


More data input is available for creating Thin Shell elements by scrolling down the input properties menu

bar on the previous page. Listed below are the remaining options contained in this menu.


Orientation System Defines the orientation of the material within the shell

element. This is a reference to an existing coordinate system.

The referenced coordinate system defines the data used to

create the *ORIENTATION option.


254

Thin Shell (Laminated)

Options above create STRI35, STRI65, S4R5, S8R5, or S9R5 elements with *SHELL SECTION

properties. *ORIENTATION and ∗TRANSVERSE SHEAR STIFFNESS options may also be created,

as required. This defines a laminate thin shell element.

Ave Shear Stiffness Defines the transverse shear stiffness. This is the value on the

*TRANSVERSE SHEAR STIFFNESS option. This is either

a real constant or a reference to an existing field definition.

Membrane Hourglass Stiffness

Normal Hourglass Stiffness

Bending Hourglass Stiffness

Define the artificial stiffness for hourglass control in

membrane, normal, and bending modes. These define

parameters on the *HOURGLASS STIFFNESS option. These

can be either real constants or references to existing field

definitions.


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

Quad/8, Quad/9



Thick Shell

Options above create S3R, STRI65, S4R, or S8R elements with *SHELL SECTION properties.

*ORIENTATION, *TRANSVERSE SHEAR STIFFNESS and *HOURGLASS STIFFNESS options

may also be created, as required. This defines a homogeneous thick shell element.


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

Tri/6, Quad/8


256

More data input is available for creating Thick Shell elements by scrolling down the input properties

menu bar on the previous page. Listed below are the remaining options contained in this menu.


Orientation System Defines the orientation of the material within the shell element. This

is a reference to an existing coordinate system. The referenced

coordinate system defines the data used to create the

*ORIENTATION option.


Thick Shell (Laminated)

Options above create S3R, STRI65, S4R, or S8R elements with *SHELL SECTION properties.

*ORIENTATION and ∗TRANSVERSE SHEAR STIFFNESS options may also be created, as required.

This defines a laminate thick shell element.

Shear Stiffness K13

Shear Stiffness K23

Defines the transverse shear stIffness. These are the values on the

*TRANSVERSE SHEAR STIFFNESS option. These are either real


Membrane Hourglass StiffnessNormal Hourglass StiffnessBending Hourglass Stiffness

Define the artificial stIffness for hourglass control in membrane,

normal, and bending modes. These define parameters on the

*HOURGLASS STIFFNESS option. These can be either real



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

Tri/6, Quad/8



258

General Thin

Options above create STRI35, STRI65, S4R5, S8R5, or S9R5 elements with *SHELL GENERAL

SECTION properties. *ORIENTATION, *TRANSVERSE SHEAR STIFFNESS, and *HOURGLASS

STIFFNESS options may also be created, as required. This defines a general thin shell element.


Structural 2D Shell General Thin

Shell

Homogenous Tri/3, Quad/4,

Tri/6, Quad/8,

Quad/9


More data input is available for creating General Thin Shell elements by scrolling down the input



260


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

Defines the symmetric half of the [D] section stiffness matrix on the

*SHELL GENERAL SECTION option. These properties are required.

Force Vector {F1..F6} Defines the 6 values of the {F} vector on the *SHELL GENERAL

SECTION option. This vector defines the generalized stresses caused

by a fully constrained unit temperature rise. This is a list of 6 real

constants. This property is required.

Temperature ScalingThermal Expansion ScalingTemperature Values

Define the temperature effects on the *SHELL GENERAL SECTION

option. These are lists of real values. Each list must have the same

number of values. These values are optional.

Orientation System Defines the orientation of the material within the shell element. This is

a reference to an existing coordinate system. The referenced coordinate

system defines the data used to create the *ORIENTATION option.

Reference Temperature Defines the reference temperature for all thermal effects on this

element. This defines the ZERO parameter on the *SHELL


Density, mass/area Defines the mass per unit area for the shell element. This is the

DENSITY parameter on the *SHELL GENERAL SECTION option.

This value can be either a real constant or a reference to an existing

field definition.

Ave Shear Stiffness Defines the transverse shear stiffness. This is the value on the

*TRANSVERSE SHEAR STIFFNESS option. This is either a real

constant or a reference to an existing field definition.


Define the artificial stiffness for hourglass control in membrane,


*HOURGLASS STIFFNESS option. These can be either real



General Thin Shell (Laminated)

Options above create STRI3, STRI65, S4R5, S8R5 or S9R5 elements with *SHELL GENERAL

SECTION properties. *ORIENTATION and ∗TRANSVERSE SHEAR STIFFNESS options may also be

created, as required. This defines a laminate thin shell element.


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

Tri/6, Quad/8,

Quad/9


262

General Thick

Options above create S3R, STRI65, S4R, or S8R elements with *SHELL GENERAL SECTION

properties. *ORIENTATION, *TRANSVERSE SHEAR STIFFNESS, and *HOURGLASS STIFFNESS

options may also be created, as required. This defines a general thick shell element.

More data input is available for creating General Thick Shell elements by scrolling down the input



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

Tri/6, Quad/8





*SHELL GENERAL SECTION option. These properties are required.

Force Vector {F1..F6} Defines the 6 values of the {F} vector on the *SHELL GENERAL

SECTION option. This vector defines the generalized stresses caused by

a fully constrained unit temperature rise. This is a list of 6 real constants.


Temperature ScalingThermal Expansion ScalingTemperature Values

Define the temperature effects on the *SHELL GENERAL SECTION

option. These are lists of real values. Each list must have the same

number of values. These values are optional.

Orientation System Defines the orientation of the material within the shell element. This is a

reference to an existing coordinate system. The referenced coordinate


Reference Temperature Defines the reference temperature for all thermal effects on this element.

This defines the ZERO parameter on the *SHELL GENERAL

SECTION option.

Density, mass/area Defines the mass per unit area for the shell element. This is the

DENSITY parameter on the *SHELL GENERAL SECTION option.

This value can be either a real constant or a reference to an existing field

definition.

Shear Stiffness K13

Shear Stiffness K23

Defines the transverse shear stiffness. These are the values on the

*TRANSVERSE SHEAR STIFFNESS option. These are either real



Define the artificial stiffness for hourglass control in membrane, normal,

and bending modes. These define parameters on the *HOURGLASS

STIFFNESS option. These can be either real constants or references to

existing field definitions.


264

General Thick Shell (Laminated)

Options above create S3R, STRI65, S4R, or S8R elements with *SHELL GENERAL SECTION

properties. *ORIENTATION and ∗TRANSVERSE SHEAR STIFFNESS options may also be created,

as required. This defines a laminate thick shell element.


Structural 2D Shell General Thick

Shell

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

Quad/8, Quad/9


Large Strain

Options above create S3R, S4R, or S8R elements with ∗SHELL SECTION properties. ∗ORIENTATION,

∗TRANSVERSE SHEAR STIFFNESS, and ∗HOURGLASS STIFFNESS options may also be created,

as required. This defines a large strain element.


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

Tri/6, Quad/8


266

More data input is available for creating Large Strain Shell elements by scrolling down the input

properties menu bar on the previous page. Listed below are the remaining options contained in this menu

.

General Large Strain

Options above create S3R, S4R, or S8R elements with ∗SHELL GENERAL SECTION properties.

∗ORIENTATION, ∗TRANSVERSE SHEAR STIFFNESS, and ∗HOURGLASS STIFFNESS options

may also be created, as required. This defines a general large strain element.


Membrane Hourglass Stiff

Normal Hourglass Stiff

Bending Hourglass Stiff

Define the artificial stiffness for hourglass control in

membrane, normal, and bending modes. These define

parameters on the ∗HOURGLASS STIFFNESS option.

These can be either real constants or references to existing

field definitions.


Structural 2D Shell General Large

Strain Shell

Tri/3, Quad/4


More data input is available for creating General Large Strain Shell elements by scrolling down the input



268




∗SHELL GENERAL SECTION option.

These properties are required.

Force Vector F1...F6 Defines the 6 values of the {F} vector on the ∗SHELL GENERAL

SECTION option. This vector defines the generalized stresses caused

by a fully constrained unit temperature rise. This is a list of 6 real

constants. This property is required.

Temperature Scaling DThermal Expansion ScalingTemperature Values

Define the temperature effects on the ∗SHELL GENERAL

SECTION option. These are lists of real values. Each list must have

the same number of values. These values are optional.

Orientation System Defines the orientation of the material within the shell element. This

is a reference to an existing coordinate system. The referenced

coordinate system defines the data used to create the

∗ORIENTATION option.

Reference Temperature Defines the reference temperature for all thermal effects on this

element. This defines the ZERO parameter on the ∗SHELL


Density, mass/area Defines the mass per unit surface area for the shell element. This is

the DENSITY parameter on the ∗SHELL GENERAL SECTION

option. This value can be either a real constant or a reference to an

existing field definition.



parameter on the *SHELL GENERAL SECTION option.


Plane Strain

Options above create CPE3, CPE4, CPE4R, CPE6, CPE6M, CPE8, CPE8R, CPE3H, CPE4H, CPE4RH,

CPE6H, CPE6MH, CPE8H, or CPE8RH (depending on the selected options and topologies) elements

with *SOLID SECTION properties. The thickness value on the *SOLID SECTION option is included.

*ORIENTATION and *HOURGLASS STIFFNESS options may also be included, as required. If

triangular element are found where reduced integration is requested, standard integration elements will

be used

Shear Stiffness K13

Shear Stiffness K23

Defines the transverse shear stiffness. These are the values on the

∗TRANSVERSE SHEAR STIFFNESS option. These are either real



Define the artificial stiffness for hourglass control in membrane,


∗HOURGLASS STIFFNESS option. These can be either real



Structural 2D 2D Solid Plane

Strain


Hybrid

Hybrid/Reduced

Integration

Reduced Integration

Incompatible Modes

Hybrid/Incompatible

Modes

Modified Formulation

Modified/Hybrid

Tri/3, Quad/4,

Tri/6, Quad/8

Tri/6

Tri/6



270

.

Generalized Plane Strain


Structural 2D 2D Solid General Plane

Strain


Hybrid

Hybrid/Reduced

Integration

Reduced Integration

Incompatible Modes

Hybrid/Incompatible

Modes

Tri/3, Quad/4

Tri/6, Quad/8


These options create CGPE5, CGPE5H, CGPE6, CGPE6H, CGPE6I, CGPE6IH, CGPE6R, CGPE6RH,

CGPE8, CGPE8H, CGPE10, CGPE10H, CGPE10R or CGPE10RH elements with *SOLID SECTION

properties when writing an ABAQUS V5.X or V4.X input file. Otherwise, they create CPEG3,

CPEG3H, CPEG4, CPEG4H, CPEG4I, CPEG4IH, CPEG4R, CPEG4RH, CPEG6, CPEG6H, CPEG8,

CPEG8H, CPEG8R or CPEG8RH elements with *SOLID SECTION properties. The thickness value on

the *SOLID SECTION option is included. *ORIENTATION and *HOURGLASS STIFFNESS options

may also be included, as required. If triangular elements are found where reduced integration is

requested, standard integration elements will be used.


272

Plane Stress

Options above create CPS3, CPS4, CPS4R, CPS6, CPS6M, CPS8, or CPS8R (depending on the selected

options and topologies) elements with *SOLID SECTION properties. The thickness value on the

*SOLID SECTION option will be included. *ORIENTATION and *HOURGLASS STIFFNESS options

may also be created, as required. If triangular elements are found where reduced integration is requested,

standard integration elements will be used.


[Reference Node] V6.X+ Defines the REF NODE parameter on the *SOLID

SECTION option. The third degree of freedom of this node

defines the change in length between the bounding planes.

The fourth and fifth degrees of freedom of this node define

the relative rotations of one bounding plane with respect to

the other. This property is required when generating an

ABAQUS version 6 or greater input file.

[Node A: DOF<UZ>] V5.X This property is required when generating an ABAQUS

version 4 or 5 input file.

[Node B: DOF<RX,RY] V5.X This property is required when generating an ABAQUS

version 4 or 5 input file.


Structural 2D 2D Solid Plane

Stress


Reduced Integration

Incompatible Modes


Tri/3, Quad/4,

Tri/6, Quad/8

Tri/6


Axisymmetric Solid


Structural 2D 2D Solid Axisymmetric Standard Formulation

Reduced Integration

Incompatible Modes

Hybrid

Modified

Formulation

Modified/Hybrid

Tri/3, Quad/4,

Tri/6, Quad/8

Tri/6

Tri/6


274

Options above create CAX3, CAX4, CAX4R, CAX6, CAX6M, CAX8, CAX8R, CAX3H, CAX4H,

CAX4RH, CAX6H, CAX6MH, CAX8H, or CAX8RH elements (depending on the selected options and

topologies) with ∗plifa=pb`qflk properties. *ORIENTATION and ∗HOURGLASS STIFFNESS

option may also be created, as required. If triangular elements are found where reduced integration is


Axisymmetric Solid with Twist (General)

Options above create CGAX3, CGAX4, CGAX4R, CGAX6, CGAX8, CGAX8R, CGAX3H, CGAX4H,

CGAX4RH, CGAX6H, CGAX8H, or CGAX8RH elements (depending on the selected options and

topologies) with ∗plifa=pb`qflk properties. *ORIENTATION and ∗HOURGLASS STIFFNESS


Structural 2D 2D Solid General

Axisymmetric


Hybrid

Reduced Integration

Hybrid/Reduced

Integration

Tri/3, Quad/4,

Tri/6, Quad/8

Quad/4, Quad/8


options may also be created, as required. If triangular elements are found where reduced integration is


Membrane

Options above create M3D3, M3D4, M3D4R, M3D6, M3D8, M3D8R, M3D9 or M3D9R elements

(depending on the selected options and topologies) with ∗plifa=pb`qflk properties. The thickness

value on the ∗plifa=pb`qflk option is included. ∗lofbkq^qflk and ∗elrodi^pp=

pqfcckbpp options may also be created, as required. If triangular elements are found where reduced

integration is requested, standard integration elements will be used.


Structural 2D Membrane Standard Formulation

Reduced Integration

Tri/3, Quad/4,

Tri/6, Quad/8


276


Planar 2D Interface

Options above create INTER2 or INTER3 elements (depending on the selected topology) with

∗fkqboc^`b, ∗cof`qflk, and ∗proc^`b=`lkq^`q properties. The SOFTENED parameter on

the ∗proc^`b=`lkq^`q option may be included, depending on the selected option. This element

defines an interface region between two portions of a planar model. These elements must be created from

one contact surface to the other.


Structural 2D 2D Interface Planar Elastic Slip Soft Contact







Elastic Slip Vis Damping No

Separation



Separation

Quad/4,

Quad/8


278

More data input is available for creating Planar 2D Interface elements by scrolling down the input











∗FRICTION option.





value on the ∗SURFACE CONTACT, SOFTENED option. This property


Pressure Zero Press Defines the pressure at zero clearance. This is the value on the

















constant.

Ff

p0

p0


Axisymmetric 2D Interface

Options above create INTER2A or INTER3A elements (depending on the selected topology) with

*INTERFACE, *FRICTION, and *SURFACE CONTACT properties. The SOFTENED parameter on

the *SURFACE CONTACT option may be included, depending on the selected option. This element


Structural 2D 2D Interface Axisymmetric Elastic Slip Soft Contact

Elastic Slip Hard

Contact



Elastic Slip No

Separation



Elastic Slip Vis

DampingNo

Separation



No Separation

Quad/4,

Quad/8


280

defines an interface region between two portions of an axisymmetric model. These elements must be

created from one contact surface to the other.

More data input is available for creating Axisymmetric 2D Interface elements by scrolling down the input











∗FRICTION option.







Ff


IRS (Shell/Solid)

Options above create IRS3, IRS4, and IRS9 elements (depending on the selected topology) with

∗INTERFACE, ∗FRICTION and ∗SURFACE CONTACT properties. The SOFTENED parameter on the

∗SURFACE CONTACT option may be included, depending on the selected option. This defines a rigid

surface element for use with solid or shell elements.


















is constant.

Analysis Type

Dimension Type Option 1 Option 2

Topologies

Structural 2D IRS

(shell/solid)









No

Separation



No Separation

Quad/4


p0

p0


282

More data input is available for creating IRS (shell/solid) elements by scrolling down the input properties





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

Friction in Dir_1

Friction in Dir_2












∗FRICTION option.


Ff


Rigid Surface (Bezier 3D)

Options above create a ∗RIGID SURFACE, TYPE=BEZIER option for use in three-dimensional analysis

(see Section 7.4.7 of the ABAQUS/Standard User’s manual).

All trias forming up the rigid surface must have the normals pointing towards the contacting surface.

Trias must all be connected.











property is only used for the Hard Contact option. This is a real constant.












is constant.


Structural 2D Rigid Surf (Bz3D) Quad 4


p0

p0


284

Rigid Surface (LBC)

This property set is created when the Rigid-Deform contact lbc is created in the Loads/BCs menu. The

creation or deletion of this property set is not required by the user. The elements associated with this

property set are translated as R3D3 and R3D4 elements.


Structural 2D Rigid Surface(LBC) Quad4,

Tria3


2D Rebar

The options above create SFM3D3, SFM3D4, SFM3D4R, SFM3D6, SFM3D8, SFM3D8R and

SFMCL9 elements (depending on the selected options and topologies) with *SURFACE SECTION

properties. The *EMBEDDED ELEMENT and *REBAR LAYER options are also created.


Structural 2D Rebar Cylindrical

General

Standard

Formulation

Reduced

Integration

Quad/9

Tri/3, Tri/6,

Quad/4, Quad/8

Quad/4, Quad/8


286

Material Name Defines the material to be used. When entering data here, a list of all

isotropic materials in the database is displayed. You can either pick one from

the list with the mouse or type in the name. This identifies the material that

will be referenced on the *REBAR LAYER option. This property is

required.

X-Sectional Area Defines the area of the rebar cross-section. This is the cross-sectional area

value on the *REBAR LAYER option. A real constant, a reference to an

existing field definition, or a real list may be entered. A real list is used to

specify the cross-sectional area for more than one rebar layer. This property

is required.

Spacing Defines the spacing of the rebars within a layer. This is the spacing value on

the *REBAR LAYER option. A real constant, a reference to an existing field

definition, or a real list may be entered. A real list is used to specify the

spacing for more than one rebar layer. This property is required.


Plane Strain Gasket

These options create GKPE4 elements. The *GASKET SECTION option is used to define the gasket

thickness, out-of-plane thickness, initial gap and initial void values. The *GASKET THICKNESS

BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET

ELASTICITY option is used to define the transverse shear behavior.

Spacing Unit Type Defines the unit type for the spacing values. When “Angle” is specified, the

ANGULAR SPACING parameter is used for the *REBAR LAYER option.

“Distance” is the default value. This property is not required.

Rebar Orient. Angle Defines the angular orientation of the rebar from the local 1-direction in

degrees. This is the angular orientation value on the *REBAR LAYER

option. A real constant, a reference to an existing field definition, or a real

list may be entered. A real list is used to specify the angular orientation for

more than one rebar layer. This property is required.

Host Property Set Defines the element property set of the elements that host the rebar elements.

This is the “HOST ELSET” parameter on the *EMBEDDED ELEMENT

option. A reference to an existing element property set may be specified. By

default, the solver determines the host elements based on the position of the

embedded elements within the model. This property is not required.

Roundoff Tolerance Defines the value below which the weigh factors of the host element’s nodes

will be zeroed out. This is the ROUNDOFF TOLERANCE parameter on the

*EMBEDDED ELEMENT option. A real scalar may be specified. The

default value is 1E+6. This property is not required.

Orientation System Defines a local coordinate system for orienting the rebars. This is a reference

to an existing coordinate system. The referenced coordinate system defines

the data used to create an *ORIENTATION option. The orientation name is

then used for the ORIENTATION parameter on the *REBAR LAYER

option. This property is not required.

Orientation Axis Defines the axis of rotation on the “Orientation System” to use for the

additional rotation specified by the “Orientation Angle”. The axis should

have a nonzero component in the direction of the normal to the surface. An

integer value between 1 and 3 may be specified. The local 1-direction is the

default value. This property is not required.

Orientation Angle Defines the additional rotation in degrees about the “Orientation Axis” of the

“Orientation System”. Either a real scalar or a reference to an existing field

definition may be specified. The default value is zero. This property is not

required.


Structural 2D 2D Gasket Plane Strain Gasket Behavior

Model

Quad4


288









P vs Closure (Loading)

This property defines the pressure versus gasket closure for loading in the








Plane Strain Gasket (Material)

P vs Closure (Unloading)

This property defines the pressure versus gasket closure for unloading in the













not required.

Thickness This property defines the out-of-plane thickness of the of the gasket element.

It is translated to the ABAQUS input file as an entry on the *GASKET


define this property. This property is not required.



















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


290

These options create GKPE4 elements. The *GASKET SECTION option is used to define the gasket

thickness, out-of-plane thickness, initial gap and initial void values. The gasket material is specified

using the MATERIAL parameter on the *GASKET SECTION option.














Plane Stress Gasket

These options create GKPS4 elements. The *GASKET SECTION option is used to define the gasket


BEHAVIOR option is used to define the behavior in the thickness direction. The *GASKET

ELASTICITY option is used to define the transverse shear behavior.














Structural 2D 2D Gasket Plane Stress Gasket Behavior

Model

Quad4


292


















Plane Stress Gasket (Thick only)















not required.























Structural 2D 2D Gasket Plane Stress Thickness

Behavior Only

Quad4


294

These options create GKPS4N elements. The *GASKET SECTION option is used to define the gasket


BEHAVIOR option is used to define the behavior in the thickness direction.



ABAQUS input file as the TYPE parameter on the *GASKET

THICKNESS BEHAVIOR option. This property is required.










Plane Stress Gasket (Material)

These options create GKPS4 elements. The *GASKET SECTION option is used to define the gasket

thickness, out-of-plane thickness, initial gap and initial void values. The gasket material is specified

using the MATERIAL parameter on the *GASKET SECTION option.





parameter set to UNLOADING. A non-spatial field created with the

"Tabular Input" method must be used to define this property. The field's

independent variables must be either displacement or displacement and

temperature. This property is not required.

Thickness This property defines the out-of-plane thickness of the of the gasket






















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


296














Axisymmetric Gasket


thickness, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used

to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to define

the transverse shear behavior.














Structural 2D 2D

Gasket

Axisymmetric Gasket Behavior

Model

Quad4


298

Membrane Material This property defines the membrane material to be used. It is translated to

the ABAQUS input file as the *GASKET ELASTICITY option with the




















parameter set to UNLOADING. A non-spatial field created with the

"Tabular Input" method must be used to define this property. The field's

independent variables must be either displacement or displacement and

temperature. This property is not required.







not required.



















300

Axisymmetric Gasket (Thick only)

These options create GKAX4N elements. The *GASKET SECTION option is used to define the gasket

thickness, initial gap and initial void values. The *GASKET THICKNESS BEHAVIOR option is used

to define the behavior in the thickness direction.


Structural 2D 2D Gasket Axisymmetric Thickness

Behavior Only

Quad4


302

Axisymmetric Gasket (Material)


thickness, initial gap and initial void values. The gasket material is specified using the MATERIAL

parameter on the *GASKET SECTION option.



Structural 2D 2D Gasket Axisymmetri

c

Built-in Material Quad4


3D Line Gasket

These options create GK3D4L elements. The *GASKET SECTION option is used to define the gasket


used to define the behavior in the thickness direction. The *GASKET ELASTICITY option is used to

define the transverse shear behavior.






















Structural 2D 2D Gasket Line Gasket Behavior

Model

Quad4


304

Membrane Material This property defines the membrane material to be used. It is translated

to the ABAQUS input file as the *GASKET ELASTICITY option with

the COMPONENT parameter set to MEMBRANE. The Elastic

Modulus and Poisson's Ratio may vary with temperature. This property

is not required.

Behavior Type This property defines the type of behavior for the thickness direction.

It may be set to either "Damage" or "Elastic-Plastic". This value is

translated to the ABAQUS input file as the TYPE parameter on the

*GASKET THICKNESS BEHAVIOR option. This property is

required.

F/L vs. Closure (Loading) This property defines the force per unit length versus gasket closure for

loading in the thickness direction. It is translated to the ABAQUS input


DIRECTION parameter set to LOADING. A non-spatial field created

with the "Tabular Input" method must be used to define this property.

The field's independent variables must be either Displacement or

Displacement and Temperature. This property is required.


F/L vs. Closure (Unloading) This property defines the force per unit length versus gasket closure for

unloading in the thickness direction. It is translated to the ABAQUS

input file as the *GASKET THICKNESS BEHAVIOR option with the

DIRECTION parameter set to UNLOADING. A non-spatial field

created with the "Tabular Input" method must be used to define this

property. The field's independent variables must be either displacement

or displacement and temperature. This property is not required.


translated to the ABAQUS input file as the *GASKET ELASTICITY

option with the COMPONENT parameter set to TRANSVERSE

SHEAR. A real constant or a non-spatial field may be used to define

this property. The non-spatial fields that have been created with the

"Tabular Input" method may be used to define shear stiffness that

varies with temperature. This property is not required.

Gasket Thickness This property defines the thickness of the gasket elements. It is


SECTION option. A real constant or a spatially varying field may be

used to define this property. This property is not required. When this

property is not specified, the gasket elements' thicknesses are

determined from their nodal coordinates.

Thickness Direction This property defines the thickness direction (local one direction) for

the elements. It is translated to the ABAQUS input file on the

*GASKET SECTION option. A real vector or a spatially varying

vector field may be used to define this property. This property is not

required.

Width This property defines the width of the gasket element. It is translated to

the ABAQUS input file as an entry on the *GASKET SECTION

option. A real constant or a spatially varying field may be used to


Initial Gap This property defines the initial gap in the thickness direction of the

gasket element. It is translated to the ABAQUS input file as an entry

on the *GASKET SECTION option. A real constant or a spatially

varying field may be used to define this property. This property is not

required.

Initial Void This property defines the initial void in the thickness direction of the

gasket element. It is translated to the ABAQUS input file as an entry

on the *GASKET SECTION option. A real constant or a spatially

varying field may be used to define this property. This property is not

required.


306

3D Line Gasket (Thick only)

These options create GK3D4LN elements. The *GASKET SECTION option is used to define the gasket


used to define the behavior in the thickness direction.


Structural 2D 2D Gasket Line Thickness

Behavior Only

Quad4


Behavior Type This property defines the type of behavior for the thickness direction. It

may be set to either "Damage" or "Elastic-Plastic". This value is

translated to the ABAQUS input file as the TYPE parameter on the

*GASKET THICKNESS BEHAVIOR option. This property is

required.

F/L vs. Closure (Loading) This property defines the force per unit length versus gasket closure for

loading in the thickness direction. It is translated to the ABAQUS input


DIRECTION parameter set to LOADING. A non-spatial field created

with the "Tabular Input" method must be used to define this property.

The field's independent variables must be either Displacement or

Displacement and Temperature. This property is required.

F/L vs. Closure (Unloading) This property defines the force per unit length versus gasket closure for

unloading in the thickness direction. It is translated to the ABAQUS

input file as the *GASKET THICKNESS BEHAVIOR option with the

DIRECTION parameter set to UNLOADING. A non-spatial field

created with the "Tabular Input" method must be used to define this

property. The field's independent variables must be either displacement

or displacement and temperature. This property is not required.

Gasket Thickness This property defines the thickness of the gasket elements. It is


SECTION option. A real constant or a spatially varying field may be

used to define this property. This property is not required. When this

property is not specified, the gasket elements' thicknesses are

determined from their nodal coordinates.

Thickness Direction This property defines the thickness direction (local one direction) for

the elements. It is translated to the ABAQUS input file on the

*GASKET SECTION option. A real vector or a spatially varying

vector field may be used to define this property. This property is not

required.

Width This property defines the width of the gasket element. It is translated to

the ABAQUS input file as an entry on the *GASKET SECTION

option. A real constant or a spatially varying field may be used to define

this property. This property is required.


308

3D Line Gasket (Material)

These options create GK3D4L elements. The *GASKET SECTION option is used to define the gasket

thickness, width, initial gap and initial void values. The gasket material is specified using the


Initial Gap This property defines the initial gap in the thickness direction of the

gasket element. It is translated to the ABAQUS input file as an entry on

the *GASKET SECTION option. A real constant or a spatially varying

field may be used to define this property. This property is not required.

Initial Void This property defines the initial void in the thickness direction of the

gasket element. It is translated to the ABAQUS input file as an entry on

the *GASKET SECTION option. A real constant or a spatially varying

field may be used to define this property. This property is not required.


Structural 2D 2D Gasket Line Built-in Material Quad4





Gasket Thickness This property defines the thickness of the gasket elements. It is translated to the



property is not required. When this property is not specified, the gasket




SECTION option. A real vector or a spatially varying vector field may be used

to define this property. This property is not required.


310

Solid

Options above create C3D4, C3D6, C3D8, C3D8R, C3D10, C3D10M, C3D15, C3D20, C3D20R,

C3D4H, C3D6H, C3D8H, C3D8RH, C3D10H, C3D10MH, C3D15H, C3D20H, C3D20RH, C3D27,

C3D27R, C3D27H, or C3D27RH elements (depending on the selected options and topologies) with

∗SOLID SECTION properties. ∗ORIENTATION and ∗HOURGLASS STIFFNESS options may also be

created, as required. If tetrahedral or wedge elements are found where reduced integration is requested,

standard integration elements will be used.














Structural 3D Solid Standard Formulation

Hybrid

Hybrid/Reduced

Integration

Reduced Integration

Incompatible Modes

Hybrid/Incompatible

Modes


Modified/Hybrid

Laminate Tet/4, Tet/10,

Wedge/6, Wedge/15,

Hex/8, Hex/20,

Hex/27

Tet/10

Tet/10


Material Name Defines the material to be used. When entering data, a list of all materials in the

database is displayed. You can either pick one from the list with the mouse or type

the name in. This identifies the material which will be referenced on the *SOLID

SECTION option. This property is required.

Orientation Axis This property defines the the orientation of the material within the shell element.

This is a reference to an existing coordinate system. The referenced coordinate


Stack Direction This property defines the direction in which the material layers are stacked. This is

the STACK DIRECTION parameter on the *SOLID SECTION option. An integer

value of 1, 2 or 3 may be entered. Please see the section on defining composite

solid elements in the ABAQUS Standard User’s Manual to determine the correct

stack direction. This property is not required. The default value is 3.


312

3D Interface

Options above create INTER4, INTER8 or INTER9 elements (depending on the selected topology) with

*INTERFACE, *FRICTION, and *SURFACE CONTACT properties. The SOFTENED parameter on

the *SURFACE CONTACT option may be included, depending on the selected option. This element

defines an interface region between two portions of a spatial model. These elements must be created from

one contact surface to the other.


Structural 3D 3D Interface Elastic Slip Soft Contact




Elastic Slip No

Separation




No Separation



No Separation

Hex/8,

Hex/20,

Hex/27


More data input is available for creating 3D Interface elements by scrolling down the input properties





314

Thermal Link


Elastic Slip Defines the absolute magnitude of the allowable maximum elastic

slip to be used in the stiffness method for sticking friction. This is

the value of the ELASTIC SLIP parameter on the ∗FRICTION

option.

Slip Tolerance Defines the value of to redefine the ratio of allowable

maximum elastic slip to characteristic element length dimension.

The default is .005. This is the value of the SLIP TOLERANCE

parameter on the ∗FRICTION option.


Maximum Friction Stress Defines the equivalent shear stress limit of the gap element. This

is the value of the TAUMAX parameter on the ∗FRICTION

option.




constant.


∗SURFACE CONTACT, SOFTENED option. This property is

only used for the Soft Contact option. This is a real constant.

Maximum Overclosure Defines the maximum overclosure allowed in points considered

not in contact. This is the c value on the ∗SURFACE CONTACT

option. This property is only used for the Hard Contact option.

This is a real constant.

Maximum Negative Pressure Defines the magnitude of the maximum negative pressure allowed

to be carried across points in contact. This is the value on the

∗SURFACE CONTACT option. This property is only used for the






Frac Clearance Const Damping Fraction of the clearance interval over which the damping

coefficient is constant.


Thermal 1D Link Bar/2, Bar/3

Ff

p0

p0


Options above create DC1D2 or DC1D3 elements, depending on the specified topology with *SOLID

SECTION properties. The cross-sectional area value on the *SOLID SECTION option is included.

Thermal Axisymmetric Shell

Options above create DSAX1 or DSAX2 elements (depending on the specified topology) with *SHELL

SECTION properties.


Thermal 1D Axisymmetric

Shell

Homogeneous Bar/2, Bar/3


316

Thermal Axisymmetric Shell (Laminated)

Options above create DSAX1 or DSAX2 elements (depending on the specified topology) with ∗pebii=

pb`qflk, COMPOSITE properties.


Thermal 1D Axisymmetric Shell Laminate Bar/2, Bar/3


Thermal 1D Interface

Options above create DINTER1 elements with ∗fkqboc^`b properties. These elements must be

created from one contact surface to the other. ∗GAP CONDUCTANCE and ∗GAP RADIATION options

are also created, as required.


Thermal 1D 1D Interface Bar/2


318

Thermal Shell

Options above create DS3, DS4, DS6 or DS8 elements (depending on the selected topology) with

*SHELL SECTION properties. An *ORIENTATION option may also be created, as required.


Thermal 2D Shell Homogeneous Quad/4, Quad/8


Thermal Shell (Laminated)

Options above create DS3, DS4, DS6 or DS8 elements (depending on the selected topology) with

*SHELL SECTION, COMPOSITE properties. An *ORIENTATION option may also be created, as

required.


Thermal 2D Shell Laminate Quad/4, Quad/8


320

Thermal Planar Solid

Options above create DC2D3, DC2D4, DC2D6, DC2D8, DCC2D4, DCC2D4D, DCAX3, DCAX4,

DCAX6, DCAX8,DCCAX4, or DCCAX4D elements (depending on the selected options and topologies)

with ∗plifa=pb`qflk properties. The thickness value on the ∗plifa=pb`qflk option is included.

An ∗lofbkq^qflk option may also be created, as required.


Thermal 2D 2D Solid Planar

Axisymmetric




w/Dispersion Control

Tri/3,

Quad/4,

Quad/8

Quad/4

Quad/4


Thermal Preference (Planar)

Options above create DINTER2, DINTER3, DINTER2A, or DINTER3A elements (depending on the

selected option and topology) with *INTERFACE properties. These elements must be created from one


Thermal 2D 2D Interface Planar

Axisymmetric

Quad/4, Quad/8


322

contact surface to the other. *GAP CONDUCTANCE and ∗GAP RADIATION options are created, as

required.


Thermal Solid

Options above create DC3D4, DC3D6, DC3D8, DC3D10, DC3D15, DC3D20, DCC3D8, or DCC3D8D

(depending on the selected options and topologies) elements with *SOLID SECTION properties. An

*ORIENTATION option may also be created, as required.

Analysis Type Dimension Type Option 1 Topologies

Thermal 3D Solid Standard Formulation


Convection/Diffusion w/

Dispersion Control

Tet/4, Tet/10, Wedge/6,

Wedge/15, Hex/8, Hex/20

Hex/8


324

Thermal Preference (Solid)

Options above create DINTER4 or DINTER8 elements (depending on the selected) with *INTERFACE

properties. These elements must be created from one contact surface to the other. *GAP

CONDUCTANCE and ∗GAP RADIATION options are also created, as required.


Thermal 3D 3D Interface Hex/8, Hex/20


Solid Gasket

These options create GK3D8 or GK3D6 elements depending on the element topology. The *GASKET

SECTION option is used to define the gasket thickness, initial gap and initial void values. The

*GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction.

The *GASKET ELASTICITY option is used to define the transverse shear behavior.


Structural 3D Gasket Gasket Behavior

Model

Wedge6, Hex8


326































not required.











Solid Gasket (Thick only)

These options create GK3D8N or GK3D6N elements depending on the element topology. The

*GASKET SECTION option is used to define the gasket thickness, initial gap and initial void values.

The *GASKET THICKNESS BEHAVIOR option is used to define the behavior in the

thickness direction.






required.






default value is 1.















Structural 3D Gasket Thickness Behavior

Only

Wedge6, Hex8


328














Solid Gasket (Material)

These options create GK3D8 or GK3D6 elements depending on the element topology. The *GASKET

SECTION option is used to define the gasket thickness, initial gap and initial void values. The

*GASKET THICKNESS BEHAVIOR option is used to define the behavior in the thickness direction.

The *GASKET ELASTICITY option is used to define the transverse shear behavior.



























Structural 3D Gasket Built-in Material Wedge6, Hex8


330



















required.






default value is 1.














Patran Interface to ABAQUS Preference GuideLoads and Boundary Conditions

332

Patran I nterface to ABAQU S Preference Gu ide

Loads and Boundary Conditions

When choosing the Loads/BCs toggle, the Loads and Boundary Conditions form will appear. The

selections made will determine which loads and boundary form is presented, and ultimately, which

ABAQUS loads and boundaries will be created.

The following pages give an introduction to the Loads and Boundary Conditions form, followed by the

details of all the loads and boundary conditions supported by the Patran ABAQUS

Application Preference.

Loads & Boundary Conditions Form

The Loads & Boundary Conditions form shown below provides the following options for the purpose of

creating ABAQUS loads and boundaries. The full functionality of the form is defined in Loads and

Boundary Conditions Form (p. 27) in the Patran Reference Manual.

333Chapter 2: Building A ModelLoads and Boundary Conditions

The following table shows the allowable selections for all options when the Analysis Type is set to

Structural.


334

The following table shows the allowable selections for all options when the Analysis Code is set to

Thermal.

Input Data

Clicking on the Input Data button generates either a Static or Transient Input Data form, depending on

the current Load Case Type.

Static

This subordinate form appears whenever Load Case Type is set to Static and the Input Data button is

clicked. The information contained on this form will vary according to the Object that has been selected.

Information that remains standard to this form is defined below.

Analysis Type Object Type

Structural • Displacement Nodal

• Force Nodal

• Pressure Element Uniform

• Temperature Nodal

Element Uniform

Element Variable

• Inertial Load Element Uniform

• Initial Velocity Nodal

• Velocity Nodal

• Acceleration Nodal

• Contact (Deform-Deform) Element Uniform

• Contact (Rigid-Deform) Element Uniform

• Pre-Tension Element Uniform

Analysis Type Object Type

Thermal • Temperature (Thermal) Nodal

• Convection Element Uniform

• Heat Flux Element Uniform

• Heat Source Nodal

Element Uniform

• Initial Temperature Nodal


Transient

This subordinate form appears whenever Load Case Type is set to Transient and the Input Data button is

clicked. The information contained on this form will vary according to the Object that has been selected.

Information that remains standard to this form is defined below.


336

Object Tables

On the static and transient input data forms are areas where the load data values are defined. The data

fields presented depend on the selected load Object and Type. In some cases, the data fields also depend

on the selected Target Element Type. These Object Tables list and define the various input data that

pertains strictly to a specific selected object:


Displacement

Creates *BOUNDARY TYPE=DISPLACEMENT options.

Force

Creates *CLOAD options.

Pressure

Creates *DLOAD options.

Object Type Type

Displacement Nodal Structural

Input Data Description

Translations (T1,T2,T3) Defines the enforced translational displacement values. These are in model

length units.

Rotations (R1,R2,R3) Defines the enforced rotational displacement values. These are in radians.

Object Type Type

Force Nodal Structural


Force (F1,F2,F3) Defines the applied forces in the translation degrees-of-freedom.

Moment (M1,M2,M3) Defines the applied moments in the rotational degrees-of-freedom.

Object Type Type Dimension

Pressure Element Uniform Structural 2D


Top Surf Pressure Defines the magnitude of the pressure in the direction of the negative

normal to the shell.


338

Creates *DLOAD options.

Temperature

Creates *TEMPERATURE options.


Bot Surf Pressure Defines the magnitude of the pressure in the direction of the positive

normal to the shell.

Edge Pressure Defines the edge pressure value on axisymmetric, plane strain,and

plane stress elements.


Pressure Element Uniform Structural 3D


Pressure Defines the face pressure value on solid elements.

Object Type Type

Temperature Nodal Structural


Temperature Defines the nodal temperature value.


Temperature Element Uniform Structural 1D

2D

3D


Temperature Defines the temperature on elements.




Inertial Load

Creates *DLOAD options with the load type set to GRAV, CENT, or CORIO as appropriate.

Initial Velocity


Temperature Element Variable Structural 1D

2D

3D


Centroid Temp (1D) Defines the temperature at the centroid of the beam.

Axis-1 Gradient (1D) Defines the temperature gradient along the axis-1 of the beam section.

Axis-2 Gradient (1D)S Defines the temperature gradient along the axis-2 of the beam section.

Top Surf Temp (2D) Defines the temperature at the top of the shell element.

Bot Surf Temp (2D) Defines the temperature at the bottom of the shell element.

Temperature (3D) Defines the temperature in the solid element.

Object Type Type

Inertial Load Element Uniform Structural


Trans Accel (A1,A2,A3) Defines the magnitude and direction of the gravity vector. This must

be assigned to all elements which are to have gravity loads.

Rot Velocity (w1,w2,w3) Defines the centrifugal and Coriolis forces to be applied to the

elements.

Rot Accel (a1,a2,a3) These load terms are not currently supported by Patran ABAQUS.

Object Type Type

Initial Velocity Nodal Structural


340

Creates *INITIAL CONDITIONS TYPE=VELOCITY options.

Velocity

Creates *Boundary, Type=Velocity options.

Acceleration

Creates *Boundary, Type=Acceleration options.


Trans Veloc (v1,v2,v3) Defines the initial velocity values for the translational degrees-of-

freedom.

Rot Veloc (w1,w2,w3) Defines the initial velocity values for the rotational degrees-of-

freedom.

Object Type Type

Velocity Nodal Structural


Trans Veloc (v1,v2,v3) Defines the velocity values for the translational degrees-of-freedom.

Rot Veloc (w1, w2, w3) Defines the velocity values for the rotational degrees-of-freedom.

Object Type Type

Acceleration Nodal Structural


Trans Accel (A1, A2, A3) Defines the acceleration values for the translational

degrees-of-freedom.

Rot Accel (a1, a2, a3) Defines the acceleration values for the rotational degrees-of-freedom.


Contact (Deform-Deform)

Defines the contact between two deformable structural bodies and creates the following ABAQUS

input cards:

*Surface Definition: Master and Slave surface definitions.

*Contact Pair: Pairing of the Master and Slave Surfaces.

*Tie: Tying of the Master and Slave Surfaces (version 6 and greater).

*Surface Interaction: Contact Interaction properties between Master and Slave.

*Contact Controls: Set the Automatic Tolerances parameter

*Contact Inerference: Set the Shrink parameter

Object Type Type

Contact Element Uniform Structural


342

Defines the Master and Slave surface interaction properties.

The contact type can be General (contacting surfaces move relative to each other) or Tied (contacting

surfaces remain fixed with respect to each other usually used in mesh refinement). The sliding between

the contacting surfaces can be Large or Small. For contact in 3D space the sliding is limited to Small

sliding. Four types of contact surface behavior options are available, Hard, Softened, Modified

Softened, and No Separation. The surfaces do not separate after contact in the case when No Separation

option is used. Three types of friction formulations are available, Penalty, Lagrange, and No Slip. In the

case of No Slip option there is no relative motion between the contacting surfaces after contact. The

Penetration Type can be One Sided (Only the slave nodes are checked against the master surface) or

Symmetric (Both the slave and master nodes are checked against each other by swapping the master and

slave surfaces). The Contact Control can be turned On to activate the *Contact Control, Automatic

Tolerances parameter. Use this parameter to have ABAQUS automatically compute an overclosure

tolerance and a separation pressure tolerance to prevent chattering in contact. Shrink Fit can be turned

On to activate the *Contact Interference, Shrink parameter. Use this parameter to invoke the automatic

shrink fit capability. This capability can be used only in the first step of an analysis. When this parameter

is invoked, no data are required other than the contact pairs to which the option is applied.

The application region form is used to pick the master and slave surfaces.


Application Region:

Defines the Master and Slave contacting surfaces.

Contact (Rigid-Deform)

Defines the contact between the rigid surface and deformable structural body and creates the following

ABAQUS input cards:

*Surface Definition: Master and Slave surface definitions.

*Contact Pair: Pairing of the Master and Slave Surfaces.

Object Type Type

Contact Element Uniform Structural


344

*Surface Interaction: Contact Interaction properties between Master and Slave.

*Contact Controls: Set the Automatic Tolerances parameter

*Contact Inerference: Set the Shrink parameter

Defines the Master and Slave surface interaction properties.

The sliding between the contacting surfaces can be Large or Small. Four types of contact surface

behavior options are available, Hard, Softened, Modified Softened, and No Separation. The surfaces

do not separate after contact in the case when No Separation option is used. Three types of friction

formulations are available, Penalty, Lagrange, and No Slip. In the case of No Slip option there is no

relative motion between the contacting surfaces after contact. The Contact Control can be turned On to

activate the *Contact Control, Automatic Tolerances parameter. Use this parameter to have ABAQUS

automatically compute an overclosure tolerance and a separation pressure tolerance to prevent chattering


in contact. Shrink Fit can be turned On to activate the *Contact Interference, Shrink parameter. Use

this parameter to invoke the automatic shrink fit capability. This capability can be used only in the first

step of an analysis. When this parameter is invoked, no data are required other than the contact pairs to

which the option is applied. A vector pointing from the rigid line to the slave surface must be defined.

This vector is used to calculate the order of rigid bar elements. The vector should be defined such that

the most of the vector markers point away from the rigid line.

The application region form is used to pick the master and slave surfaces.

Application Region:

Defines the Master and Slave contacting surfaces.


346

Application Region:

Defines the Master and Slave contacting surfaces. This form appears when Contact Type: is Rigid Geom.

and Master: is Rigid Surface.


Pre-tension

Creates *BOUNDARY and *PRE-TENSION SECTION options.

Creates *BOUNDARY, *SURFACE and *PRE-TENSION SECTION options.

Creates *CLOAD and *PRE-TENSION SECTION options.

Object Type Option Type Dimension

Pre-tension Element Uniform Displacement Structural 1D


Relative Displacement Defines the relative displacement to apply to the length of the elements.


Pre-tension Element Uniform Displacement Structural 2D, 3D


Relative Displacement Defines the relative displacement to apply to the underlying elements in the

direction of the section's normal.


Pre-tension Element Uniform Force Structural 1D


Force Defines the pre-tension force to apply to the elements.


Pre-tension Element Uniform Force Structural 2D, 3D


348

Creates *CLOAD, *SURFACE and *PRE-TENSION SECTION options.

Temperature (Thermal)

Creates *BOUNDARY options.

Convection

Creates *FILM options.


Force Defines the pre-tension force to apply to the underlying elements in the direction of

the section's normal.

Object Type Type

Temp (Thermal) Nodal Thermal


Temperature Defines the nodal temperature value.


Convection Element Uniform Thermal 2D


Top Surf Convection Defines the convection coefficient for the top surface of a shell element.

Bot Surf Convection Defines the convection coefficient for the bottom surface of a shell element.

Edge Convection Defines the convection coefficient for the edges of axisymmetric, plane

strain, and plane stress type elements.

Ambient Temp Defines the ambient temperature.


Convection Element Uniform Thermal 3D


Creates *FILM options.

Heat Flux

Creates *DFLUX options.


Heat Source


Convection Defines the convection coefficient for the face of a solid element.

Ambient Temp Defines the ambient temperature.


Heat Flux Element Uniform Thermal 2D


Top Surf Heat Flux Defines the heat flux for the top surface of a shell element.

Bot Surf Heat Flux Defines the heat flux for the bottom surface of a shell element.

Edge Heat Flux Defines the heat flux for the edges of axisymmetric, plane strain, and plane

stress type elements.


Heat Flux Element Uniform Thermal 3D


Heat Flux Defines the heat flux for the face of a solid element.

Object Type Type

Heat Source Nodal Thermal


350

Creates *CFLUX options.


Initial Temperature

Creates *INITIAL CONDITIONS TYPE=TEMPERATURE options


Heat Source Defines the reference magnitude for flux (units ).

Object Type Type

Heat Source Element Uniform Thermal


Heat Source Defines the reference magnitude for flux (units ).

Object Type Type

Initial Temperature Nodal Thermal


Temperature Defines the initial temperature for a specified node.

JT 1Ó

JT 1Ó

351Chapter 2: Building A ModelLoad Cases

Load Cases

Load Cases in Patran ABAQUS are used to group a series of Load sets into one load environment for the

model. A load case is selected when preparing an analysis, not load sets. The individual load sets are

translated into the input options described in the Object Tables of the section on Loads and Boundary

Conditions form.

Patran Interface to ABAQUS Preference GuideGroup

352

Group

Groups in Patran ABAQUS are used to create groups of nodes (*NSET) and groups of elements

(*ELSET). All the groups created in Patran will be translated as *NSETs and *ELSETs except for the

“default_group” which always exists in the database, and group names which do not begin with an

alphabetic character (a-z, A-Z).d

Chapter 3 : Running Analysis


3 Running an Analysis

� Review of the Analysis Form 354

� Translation Parameters 357

� Restart Parameters 358

� Optional Controls 359

� Direct Text Input 360

� Step Creation 361

� Step Selection 432

� Read Input File 433

� ABAQUS Input File Reader 435

Patran Interface to ABAQUS Preference GuideReview of the Analysis Form

354

Review of the Analysis Form

The Analysis toggle located on the main form for Patran brings up The Analysis Form (p. 8) in the

MSC.Patran Reference Manual. This form is used to request an analysis of the model with the ABAQUS

finite element program. It can also be used to incorporate the contents of an ABAQUS results file into

the database. See Read Results.

The following page gives an introduction to the Analysis form used to prepare an ABAQUS analysis.

This is followed by detailed descriptions of the subordinate forms that can be displayed from the

Analysis form.

355Chapter 3 : Running AnalysisReview of the Analysis Form

Analysis Form

Setting the Action option menu on the Analysis Form to Analyze indicates that an analysis run is

being prepared.

The Object indicates which part of the model is to be analyzed. It can be set to either Entire Model or

Current Group. If the whole model is to be analyzed, select Entire Model. If only a part of the model is

Patran Interface to ABAQUS Preference GuideReview of the Analysis Form

356

to be analyzed, create a group of that part, set that as the current group, then select Current Group as

the Object.

The Method indicates how far the translation is to be taken. Currently only Analysis Deck is supported.

The method generates an ABAQUS input deck.

357Chapter 3 : Running AnalysisTranslation Parameters

Translation Parameters

This subordinate form appears whenever the Translation Parameters button is selected. The parameters

controlling the translation of the ABAQUS input deck are defined on this form.

Note: The spatially varying field property values are compared within the band of +half of

field properties tolerance and -half of field properties tolerance to group the

elements. The property values for this group of elements are added and divided by the number

of elements in this group to get the average property value to be used.

Patran Interface to ABAQUS Preference GuideRestart Parameters

358

Restart Parameters

This subordinate form appears whenever the Restart Parameters button is selected. This form creates a

*RESTART option (see Section 7.10.1 of the ABAQUS/Standard User’s Manual).

359Chapter 3 : Running AnalysisOptional Controls

Optional Controls

This subordinate form appears whenever the Restart Parameters button is selected.

Patran Interface to ABAQUS Preference GuideDirect Text Input

360

Direct Text Input

This subordinate form appears whenever the Direct Text Input button is selectedK

This widget is to facilitate the input of the ABAQUS input data that cannot be created using the

functionality available in Patran. All data input here will be appended to the ABAQUS model data before

the step history block.

Note: There is no checking available for invalid input.

Note: The font for the text input may vary from one system to another. A default font is specified in

app_defaults/Patran file:

Patran*fixedFont: -misc-fixed-bold-r-normal--13-100-100-100-c-70-iso8859-1

For any problems with the text on a particular system, change the font specifications in the

Patran file which should reside in your ~home directory. Use xfontsel, or xlxfonts commands to

get the list of available fonts on a given system.

361Chapter 3 : Running AnalysisStep Creation

Step Creation

This subordinate form appears whenever the Step Creation button is selected on the Analysis form. A

step is defined by associating the load cases created and stored on the database, with the ABAQUS

analysis procedure that best addresses that load case, and the relevant associated parameters that guide

the solution path for the chosen analysis procedure. There is no importance to the order in which the Job

Steps are created on this form--they will be ordered for the job in the Step Selection form.

Patran Interface to ABAQUS Preference GuideStep Creation

362

Select Load Cases

This subordinate form appears whenever the Select Load Cases button is selected on the

Step Creation form.

Output Requests

This subordinate form appears whenever the Output Requests button is selected on the Step Create form.

It is used for specifying the specific variables to be included in the output from ABAQUS options such

as: ∗EL PRINT, ∗ENERGY PRINT, ∗MODAL PRINT, ∗NODE PRINT, ∗PRINT, ∗EL FILE,

∗ENERGY FILE, ∗FILE FORMAT, ∗MODAL FILE, and ∗NODE FILE *ELEMENT MATRIX

OUTPUT. An explanation of the output variables that can be requested is included in the Output Requests

description for each solution type.


Direct Text Input

This subordinate form appears whenever the Direct Text Input button is selectedK

This widget is to facilitate the input of the ABAQUS input data that cannot be created using the

functionality available in Patran menus. All data input here will be appended to the ABAQUS step

history being created.

Note: There is no checking available for invalid data.

The font for the text input may vary from one system to another. A default font is specified

in app_defaults/Patran file:


364

Patran*fixedFont: -misc-fixed-bold-r-normal--13-100-100-100-c-70-iso8859-1

For any problems with the text on a particular system, change the font specifications in the Patran file

which should reside in your ~home directory. Use xfontsel, or xlxfonts commands to get the list of

available fonts on a given system.

Solution Types

Each step has an associated Solution type, and the information that is requested on the Solution

Parameters and Output Requests forms varies based on this selection. ABAQUS calls these analysis

procedures, and the full explanations of these procedures can be found in Chapter 2 “Procedures Library”

of the ABAQUS/Standard User’s Manual.

Parameter Type Description

Linear Static Static stress analysis is used when inertia effects can be neglected.

During a linear static step, the model’s response is defined by the

linear elastic stiffness at the base state, the state of deformation and

stress at the beginning of the step. For ∗HYPERELASTIC and

∗HYPERFOAM materials, the tangent elastic moduli in the base

state is used. Contact conditions cannot change during the step--they

remain as they are defined in the base state.

Natural Frequency This solution type uses eigenvalue techniques to extract the

frequencies of the current system. The stiffness determined at the

end of the previous step is used as the basis for the extraction, so that

small vibrations of a preloaded structure can be modeled.


Bifurcation Buckling Eigenvalue buckling estimates are obtained. Classical eigenvalue

buckling analysis (e.g., “Euler” buckling) is often used to estimate

the critical (buckling) load of “stiff” structures. “Stiff” structures are

those that carry their design loads primarily by axial or membrane

action, rather than by bending action. Their response usually

involves very little deformation prior to buckling.

Direct Linear Transient This solution procedure integrates all of the equations of motion

through time, and is significantly more expensive than modal

methods for finding dynamic response for linear systems. For linear

systems, the dynamic method, using the Hilber-Hughes-Taylor

operator, is unconditionally stable, meaning there is no mathematical

limit on the size of the time increment that can be used to integrate a

linear system. Since the procedure uses a fixed time increment, the

HAFTOL parameter on the *DYNAMIC card is not required.

Direct Steady State Dynamics Calculates steady state response for the given range of frequencies.

The damping may be created by dashpots, by “Rayleigh” damping

associated with materials, and by viscoelasticity included in the

material definitions.

Modal Linear Transient This solution type gives the response of the model as a function of

time, based on a given time dependent loading. The procedure is

based on using a subset of the eigenmodes of the system, which must

first be extracted using the NATURAL FREQUENCY solution

type.The number of modes extracted must be sufficient to model the

dynamic response of the system adequately. This is a matter of

judgment on the part of the user. The modal amplitudes are

integrated through time and the response synthesized from these

modal responses.

Modal Steady State Dynamics This solution type provides the response of the system when it is

excited by harmonic loading at a given frequency. This procedure is

usually preceded by extraction of the natural modes using the

NATURAL FREQUENCY solution type, although ABAQUS also

allows the response to be calculated directly from the system

matrices for use in those cases where the eigenvalues cannot be

extracted, such as a nonsymmetric stiffness case, or models in which

the behavior is itself a function of frequency, such as frequency

dependent material damping.



366

Response Spectrum This solution type provides an estimate of the peak response of a

structure to steady-state dynamic motion of its fixed points (“base

motion”). The method is typically used when an approximate

estimate of such peak response is required for design purposes. The

procedure is based on using a subset of the eigenmodes of the

system, which must first be extracted using the NATURAL

FREQUENCY solution type.

Random Vibration This solution type predicts the response of a system which is

subjected to a nondeterministic continuous excitation that is

expressed in a statistical sense using a power spectral density

function. The procedure is based on using a subset of the eigenmodes

of the system, which must first be extracted using the NATURAL

FREQUENCY solution type.

Nonlinear Static Nonlinear static analysis requires the solution of nonlinear

equilibrium equations, for which ABAQUS uses Newton’s method.

Many problems involve history dependent response, so that the

solution is usually obtained as a series of increments, with iteration

within each increment to obtain equilibrium. For most cases, the

automatic incrementation provided by ABAQUS is preferred,

although direct user control is also provided for those cases where

the user has experience with a particular problem.



Nonlinear Transient Dynamic

This solution type is used when nonlinear dynamic response is being

studied. Because all of the equations of motion of the system must be

integrated through time, direct integration methods are generally

significantly more expensive than modal methods. For most cases,

the automatic incrementation provided by ABAQUS is preferred,

although direct user control is also provided for those cases where

the user has experience with a particular problem.

Creep This analysis procedure performs a transient, static,

stress⁄displacement analysis. It is especially provided for the analysis

of materials which are described by the ∗CREEP material form.

Viscoelastic (Time Domain) This is especially provided for the time domain analysis of materials

which are described by the ∗VISCOELASTIC, TIME material

option. The dissipative part of the material behavior is defined

through a Prony series representation of the normalized shear and

bulk relaxation moduli, either specified directly on the

∗VISCOELASTIC, TIME material option, determined from user

input creep test data, or determined from user input relaxation test

data.

Viscoelastic (Frequency Domain)

This is especially provided for the frequency domain analysis of

materials which are described by the ∗VISCOELASTIC,

FREQUENCY material option, which is activated by a ∗STEADY

STATE DYNAMICS, DIRECT procedure.The dissipative part of the

material behavior is defined by the real and imaginary parts of the

Fourier transforms of the nondimensional shear viscoelasticity

parameter g and, for compressible materials, of the bulk

viscoelasticity parameter k.

Steady State Heat Transfer This solution type is for pure heat transfer problems for which the

∗HEAT TRANSFER option is used and where the temperature field

can be found without knowledge of stress and deformation of the

bodies being studied.

Transient Heat Transfer This solution type is for pure transient heat transfer problems for

which the ∗HEAT TRANSFER option is used and where the

temperature field can be found without knowledge of stress and

deformation of the bodies being studied. For all transient heat

transfer cases, the time increments may be specified directly, or will

be selected automatically based on a user prescribed maximum nodal

temperature change in a step. Automatic time incrementation is

generally preferred.



368

Linear Static

Read Temperature File=

This option is used to specify temperatures via the results file which has been generated from a previous

heat transfer analysis. Only one temperature results file is allowed in an analysis but the same file can be

referenced by many steps.


Linear Static

If the selected solution type is Linear Static then the following parameters may be defined on the Output

Requests form.

Parameter Name Description

Output Variable Identifier

Stress Components

The stress components output depend on the elements analyzed.

For example, the truss element outputs the axial stress (S11) only,

while a three-dimensional solid element outputs all six

components (S11, S22, S33, S12, S13, S23). Note that ABAQUS

always reports the Cauchy, or true stress, which is equal to the

force per current area. For more information about element output,

see Chapter 3 of the ABAQUS/Standard User’s Manual.

S11, S22, S33,

S12, S13, S23

Stress Invariants

The stress invariants output by ABAQUS are the Mises stress,

Tresca stress, Hydrostatic pressure, first principal stress, second

principal stress, third principal stress, and the third stress invariant.

These quantities are scalar quantities which do not vary with a

change of coordinate system. For elastic analyses, the von Mises

and/or the Tresca stress invariants can be monitored to ensure that

the analysis remains within the assumptions of linearity.

SINV

Strain Components

This is the total strain value for each component output. The strain

components output depend on the elements analyzed, analogous to

the stress components. Note that, for linear elastic analyses, the

total strain is equal to the elastic strain.

E

Elem Energy Densities

The strain energy per unit volume of each element. Plastic, creep,

and viscous dissipative energy densities should not be affected by

linear static analysis.

ENER

Elem Energy Magnitudes

The strain energy of each element. Plastic, creep, and viscous

dissipative energy densities should not be affected by linear static

analysis.

ELEN

Internal Stress Forces

The forces that are found at each node by summing the element

stress contributions at the nodes.

NFORC

Section Forces Section forces are output for beam elements and include the axial

force, and, as applicable, the shears, bending moments and

bimoment about the local axes. These are discussed in Section

3.5.1 and Section 7.5.2 of the ABAQUS/Standard User’s Manual.

For shell elements, the section forces include the direct membrane,

shear, and moment forces per unit width, as applicable. These are

discussed in Section 3.6 of the ABAQUS/Standard User’s Manual.

SF


370

Section Strains Section strains are output for beam elements and, as applicable,

these include the axial strain, transverse shear strains, curvature

changes, and twist about the local axes.These are discussed in

Section 3.5.1 and Section 7.5.2 of the ABAQUS/Standard

User’s Manual.

For shell elements, the section strains include the direct

membrane, shear, curvature changes, and twist, as applicable.

These are discussed in Section 3.6 of the ABAQUS/Standard

User’s Manual.

SE

Shell Thickness Changes in thickness for shell elements (S3RF, S4RF,SAX1,

SAX2, SAXA1N, SAXA2N).

STH

Displacements Displacements are output at nodes and are referred to as follows:

1. x-displacement

2. y-displacement

3. z-displacement

4. Rotation about the x-axis

5. Rotation about the y-axis

6. Rotation about the z-axis

Except for axisymmetric elements, where the displacement and

rotation degrees-of-freedom are:

1. r-displacement

2. z-displacement

3. Rotation in the r-z plane

Here x, y, z, and r are global directions unless a coordinate

transformation is used at the node. Note that the warping degree-

of-freedom, the seventh displacement component of an open

section beam element, is not supported by Patran at this time.

U

Reaction Forces

The forces at the nodes which are constrained and therefore, resist

changes in the system. The direction convention is the same as that

for nodal output.

RF

Point Forces The forces at the nodes resulting from the imposed loads

(e.g., the force at a node resulting from pressure distributions on

adjacent elements).

CF




Natural Frequency

This subordinate form appears whenever the Solution Parameters button is selected and the solution types

is Natural Frequency. This generates ∗FREQUENCY procedures (see Section 9.3.5 of the

ABAQUS/Standard User’s Manual). The optional NLGEOM parameter on the ∗STEP option may be

included, as defined below. None of the other optional parameters on the ∗pqbm option (AMPLITUDE,

INC, or MONOTONIC) are used.

Natural Frequency

If the selected Solution Type is Natural Frequency, then the following parameters may be defined on the

Output Requests form. A complete discussion of the ABAQUS results file can be found in Chapter 6 of

the ABAQUS/Standard User’s Manual. Note that the Natural Frequency solution type extracts the

frequency and corresponding mode shapes (eigenvalues and eigenmodes), usually for use in a later

analysis (e.g., Response Spectrum). The stresses and strains corresponding to the mode shapes can be

Whole Model Energies

The summation of all the energy of the model. The kinetic,

recoverable (elastic) strain, plastic dissipation, creep dissipation,

and viscous dissipation are reported.

ALLEN

Element Mass Matrix

Mass matrices output.

Element Stiffness Matrix

Stiffness matrices output.




372

output, but are usually of limited direct value except as a possible means for guiding mode limitations for

future analyses.



Stress Components

The stress components output depend on the elements

analyzed. For example, the truss element outputs the axial

stress (S11) only, while a three-dimensional solid element

outputs all six components (S11, S22, S33, S12, S13, S23).

Note that ABAQUS always reports the Cauchy, or true stress,

which is equal to the force per current area. For more

information about element output, see Chapter 3 of the

ABAQUS/Standard User’s Manual.

S11, S22, S33,

S12, S13, S23

Stress Invariants The stress invariants output by ABAQUS are the Mises stress,

Tresca stress, Hydrostatic pressure, First principal stress,

second principal stress, third principal stress, and the third

stress invariant. These quantities are scalar quantities which

do not vary with a change of coordinate system.

SINV

Strain Components

This is the total strain value for each component output. The

strain components output depend on the elements analyzed,

analogous to the stress components. Note that, for linear

elastic analyses, the total strain is equal to the elastic strain.

E

Section Forces Section forces are output for beam elements and include the

axial force, and, as applicable, the shears, bending moments

and bimoment about the local axes. These are discussed in


User’s Manual.

For shell elements, the section forces include the direct

membrane, shear, and moment forces per unit width, as

applicable. These are discussed in Section 3.6 of the


SF

Section Strains Section strains are output for beam elements and, as

applicable, these include the axial strain, transverse shear

strains, curvature changes, and twist about the local

axes.These are discussed in Section 3.5.1 and Section 7.5.2 of

the ABAQUS/Standard User’s Manual.




User’s Manual.

SE


Bifurcation Buckling

This subordinate form appears whenever the Solution Parameters button is selected and the Solution

Type is Bifurcation Buckling. This form defines the data required for a *BUCKLE command (see Section

9.3.2 of the ABAQUS/Standard User’s Manual). This step may be included either as the first step or when

the structure has already been preloaded. If the structure has been preloaded, the buckle sensitivity

around the preloaded state is calculated. The problem is a classical eigenvalue problem, with the



STH

Displacements Displacements are output at nodes and are referred to

as follows:

1. x-displacement

2. y-displacement

3. z-displacement




Except for axisymmetric elements, where the displacement

and rotation degrees-of-freedom are:

1. r-displacement

2. z-displacement



transformation is used at the node. Note that the warping

degree-of-freedom, the seventh displacement component of

an open section beam element, is not supported by Patran at

this time.

U

Reaction Forces The forces at the nodes which are constrained and therefore,

resist changes in the system. The direction convention is the

same as that for nodal output.

RF

Element Mass Matrix







374

eigenvalues defined as the load multipliers of the load pattern for which buckling sensitivity is being

investigated.

Bifurcation Buckling

If the selected Solution Type is Bifurcation Buckling then the following parameters may be defined on

the Output Requests form.



Stress Components

The stress components output depend on the elements analyzed.

For example, the truss element outputs the axial stress (S11)

only, while a three-dimensional solid element outputs all six

components (S11, S22, S33, S12, S13, S23). Note that

ABAQUS always reports the Cauchy, or true stress, which is

equal to the force per current area. For more information about

element output, see Chapter 3 of the ABAQUS/Standard User’s

Manual.

S11, S22,

S33, S12,

S13, S23


Tresca stress, Hydrostatic pressure, first principal stress, second

principal stress, third principal stress, and the third stress

invariant. These quantities are scalar quantities which do not

vary with a change of coordinate system. For elastic analyses,

the von Mises and/or the Tresca stress invariants can be

monitored to ensure that the analysis remains within the

assumptions of linearity.

SINV


Strain Components

This is the total strain value for each component output. The


analogous to the stress components. Note that, for linear elastic

analyses, the total strain is equal to the elastic strain.

E


axial force, and, as applicable, the shears, bending moments and

bimoment about the local axes.

These are discussed in Section 3.5.1 and Section 7.5.2 of the






SF




Section 3.5.1 and Sectiono 7.5.2 of the ABAQUS/Standard

User’s Manual.




User’s Manual.

SE



STH




376

Direct Linear Transient

This subordinate form appears whenever the Solution Parameters button is selected and the solution type

is Direct Linear Transient. This generates a *DYNAMIC procedure, with the optional DIRECT

parameter included (see Section 9.3.4 of the ABAQUS/Standard User’s Manual). Note that modal

methods are usually more economical for linear dynamic analysis. Many of the parameters described in

the ABAQUS/Standard User’s Manual for the *DYNAMIC option are not used for this option.

Displacements Displacements are output at nodes and are referred to as

follows:

1. x-displacement

2. y-displacement

3. z-displacement




except for axisymmetric elements, where the displacement and


1. r-displacement

2. z-displacement




degree-of-freedom, the seventh displacement component of an

open section beam element, is not supported by Patran at

this time.

U




RF

Element Mass Matrix







Direct Linear Transient

If the selected Solution Type is Direct Linear Transient then the following parameters may be defined

on this form.



Stress Components The stress components output depend on the elements








S11, S22, S33,

S12, S13, S23


Tresca stress, Hydrostatic pressure, first principal stress,


stress invariant. These quantities are scalar quantities which do

not vary with a change of coordinate system. For elastic

analyses, the von Mises and/or the Tresca stress invariants can

be monitored to ensure that the analysis remains within the


SINV

Strain Components This is the total strain value for each component output. The


analogous to the stress components. Note that for linear elastic


E


378


The strain energy per unit volume of each element. ENER


The strain energy of each element. ELEN




NFORC





User’s Manual.





SF





User’s Manual.




User’s Manual.

SE



STH





as follows:

1. x-displacement

2. y-displacement

3. z-displacement




Except for axisymmetric elements, where the displacement and


1. r-displacement

2. z-displacement






this time.

U

Velocities Nodal velocities, following the same convention as

for displacements.

V

Accelerations Nodal accelerations, following the same convention as

for displacements.

A




RF

Point Forces The forces at the nodes resulting from the imposed loads (e.g.,

the force at a node resulting from pressure distributions on

adjacent elements).

CF



recoverable (elastic) strain, plastic dissipation, creep

dissipation, and viscous dissipation are reported.

ALLEN

Element Mass Matrix







380

Direct Steady State Dynamics


is Direct Steady State Dynamics. This generates a ∗STEADY STATE DYNAMIC procedure.

Direct Steady State Dynamics

If the selected solution type is Direct Steady State Dynamics, then the following parameters may be

defined on the Output Requests form.







Note that ABAQUS always reports the Cauchy, or true

stress, which is equal to the force per current area. For more



S11, S22, S33,

S12, S13, S23

Stress Invariants The stress invariants output by ABAQUS are the Mises

stress, Tresca stress, Hydrostatic pressure, first principal

stress, second principal stress, third principal stress, and

the third stress invariant. These quantities are scalar

quantities which do not vary with a change of coordinate

system. For elastic analyses, the von Mises and/or the

Tresca stress invariants can be monitored to ensure that the

analysis remains within the assumptions of linearity.

SINV

Ph Angle Stress Components

The phase angle shift of the stress components. PHS


Strain Components This is the total strain value for each component output.

The strain components output depend on the elements

analyzed, analogous to the stress components. Note that,

for linear elastic analyses, the total strain is equal to the

elastic strain.

E

Ph Angle Strain Components

The phase angle shift of the strain components. PHE

Section Forces Section forces are output for beam elements and include

the axial force, and, as applicable, the shears, bending

moments and bimoment about the local axes. These are

discussed in Section 3.5.1 and Section 7.5.2 of the






SF




axes.These are discussed in Section 3.5.1 and Section 7.5.2



membrane, shear, curvature changes, and twist, as



SE

Shell Thickness Changes in thickness for shell elements (S3RF,

S4RF,SAX1, SAX2, SAXA1N, SAXA2N).

STH




382


follows:

1. x-displacement

2. y-displacement

3. z-displacement




except for axisymmetric elements, where the displacement


1. r-displacement

2. z-displacement




degree-of-freedom, the seventh displacement component

of an open section beam element, is not supported by

Patran at this time.

U

Velocities Nodal velocities, following the same convention as for

displacements.

V

Accelerations Nodal accelerations, following the same convention as for

displacements.

A

Phase Angle Rel. Displacements

The phase angle shift of the relative displacement

components.

PU

Reaction Forces The forces at the nodes which are constrained and

therefore, resist changes in the system. The direction

convention is the same as that for nodal output.

RF

Phase Angle Reaction Forces

The phase angle shift of the reaction force components. PRF


(e.g., the force at a node resulting from pressure

distributions on adjacent elements).

CF

Element Mass Matrix Mass matrices output.






Modal Linear Transient


is Modal Linear Transient. This generates a *FREQUENCY procedure (see Section 9.3.5 of the

ABAQUS/Standard User’s Manual) followed by a ∗MODAL DYNAMIC procedure (see Section 9.3.8

of the ABAQUS/Standard User’s Manual). A ∗MODAL DAMPING option will also be generated, as

required. Only one load case may be selected.


384

Modal Linear Transient

This subordinate form appears whenever the Output Request button is selected on the Step Create form,

and the Solution Type is Modal Linear Transient.











S11, S22,

S33, S12,

S13, S23



stress, second principal stress, third principal tress, and the

third stress invariant. These quantities are scalar quantities

which do not vary with a change of coordinate system. For

elastic analyses, the von Mises and/or the Tresca stress

invariants can be monitored to ensure that the analysis

remains within the assumptions of linearity.

SINV



analogous to the stress components. Note that for linear


E





User’s Manual.





SF










User’s Manual.

SE


SAX2, SAXA1N, SAXA2N)

STH


follows:

1. x-displacement

2. y-displacement

3. z-displacement






1. r-displacement

2. z-displacement






this time.

U


displacements.

V

Acceleration Nodal accelerations, following the same convention as for

displacements.

A




386

Total Displacements The summation of all individual modal components of

displacement. The output follows the same convention as for

the individual modal components.

TU

Total Velocities The summation of all individual modal components of

velocity. The output follows the same convention as for the

individual modal components.

TV

Total Accelerations The summation of all individual modal components of

acceleration. The output follows the same convention as for


TA




RF

Point Forces The forces at the nodes resulting from the imposed loads,

(e.g., the force at a node resulting from pressure distributions

on adjacent elements).

CF

Generalized Displacements

The displacements associated with the modes of vibrations,

each of which have a shape (eigenmode) and associated

frequency (eigenvalue).

GU

Generalized Velocities

The velocities associated with the modes of vibration. GV

Generalized Accelerations

The accelerations associated with the modes of vibration. GA

Strain Energy per Mode

Elastic strain energy for the entire model per each mode. SNE

Kinetic Energy per Mode

Kinetic energy for the entire model per each mode. KE

External Work per Mode

External work for the entire model per each mode. T

Base Motion The base motion (displacement, velocity, or acceleration). BM





ALLEN







Define Damping Direct

When the type of Modal Damping selected is Direct, this subordinate form appears whenever Define

Damping is selected. The data is used to define the *MODAL DAMPING option (see Section 9.6.6 of

the ABAQUS/Standard User’s Manual) with the MODAL parameter set to DIRECT.


388

Define Damping Rayleigh

When the type of Modal Damping selected is Rayleigh, this subordinate form appears whenever Define

Damping is selected. This form defines the data required for the *MODAL DAMPING, RAYLEIGH

option (see Section 9.6.6 of the ABAQUS/Standard User’s Manual).

Base Motion

This subordinate form appears whenever Define Base Motion is selected from the Modal Linear

Transient, Steady State Dynamics, or Viscoelasticity Frequency Domain Solution Parameter forms.

It defines the values on the ∗BASE MOTION option (see Section 9.4.2 of the ABAQUS/Standard

User’s Manual).


Steady State Dynamics


Type is Steady State Dynamics. This generates a *STEADY STATE DYNAMICS procedure (see Section

9.3.13 of the ABAQUS/Standard User’s Manual). A *FREQUENCY procedure may also be created

prior to the *STEADY STATE DYNAMICS procedure, if required.


390

Steady State Dynamics

If the selected solution type is Steady State Dynamics, then the following parameters may be defined on







outputs all six components (S11, S22, S33, S12, S13,

S23). Note that ABAQUS always reports the Cauchy, or

true stress, which is equal to the force per current area. For

more information about element output, see Chapter 3 of


S11, S22, S33,

S12, S13, S23

Ph Angle Stress Component





stress, second principal stress, third principal stress, and

the third stress invariant. These quantities are scalar

quantities which do not vary with a change of coordinate

system. For elastic analyses, the von Mises and/or the

Tresca stress invariants can be monitored to ensure that

the analysis remains within the assumptions of linearity.

SINV

Strain Components This is the total strain value for each component output.

The strain components output depend on the elements

analyzed, analogous to the stress components. Note that

for linear elastic analyses, the total strain is equal to the

elastic strain.

E

Ph Angle Strain Component


Element Energy Magnitudes

A scalar value for the energy content of the element. ELEN

Section Forces Section forces are output for beam elements and include

the axial force, and, as applicable, the shears, bending

moments and bimoment about the local axes. These are

discussed in Section 3.5.1 and Section 7.5.2 of the






SF




axes.These are discussed in Section 3.5.1 and Section

7.5.2 of the ABAQUS/Standard User’s Manual.





SE



STH




392


follows:

1. x-displacement

2. y-displacement

3. z-displacement




Except for axisymmetric elements, where the

displacement and rotation degrees-of-freedom are:

1. r-displacement

2. z-displacement




degree-of-freedom, the seventh displacement component

of an open section beam element, is not supported by

Patran at this time.

U


displacements.

V


displacements.

A

Total Displacements The summation of all individual modal components of

displacement. The output follows the same convention as

for the individual modal components.

TU

Total Velocities The summation of all individual modal components of

velocity. The output follows the same convention as for


TV

Total Accelerations The summation of all individual modal components of

acceleration. The output follows the same convention as

for the individual modal components.

TA


All components of the phase angle of the displacements at

the node.

PU

Phase Angle Total Displacements

All components of the phase angle of the total

displacements at the node.

PTU




Reaction Forces The forces at the nodes which are constrained and so,



RF


All components of the phase angle of the reaction forces

at the node.

PRF

Point Forces The forces at the nodes resulting from the imposed loads,



CF


The displacements associated with the modes of

vibrations, each of which have a shape (eigenmode) and

associated frequency (eigenvalue).

GU

Generalized Velocities The velocities associated with the modes of vibration. GV



Phase Angle Generalized Displacements

The phase angle of displacements associated with the

modes of vibrations, each of which have a shape

(eigenmode) and associated frequency (eigenvalue).

PGU

Phase Angle Generalized Velocities

The phase angle of velocities associated with the modes of

vibration.

PGV

Phase Angle Generalized Accelerations

The phase angle of accelerations associated with the

modes of vibration.

PGA








Whole Model Energies The summation of all the energy of the model. The kinetic,



ALLEN







394

Define Frequencies

The data on this form is used to define the input for the *STEADY STATE DYNAMICS option (see

Section 9.3.13 of the ABAQUS/Standard User’s Manual).

Response Spectrum


Type is Response Spectrum. This generates a *FREQUENCY procedure, and a *RESPONSE

SPECTRUM procedure (see Sections 9.3.5 and 9.3.10, respectively, of the ABAQUS/Standard User’s

Manual). A ∗SPECTRUM option is also created (see Section 7.11.5 of the ABAQUS/Standard

User’s Manual).


Define Response Spectra (Response Spectrum)

This subordinate form appears whenever the Define Response Spectra button is selected on the Response

Spectrum Solution Parameter form.


396

Define Spectrum (Response Spectrum)

This form appears whenever the Define Spectrum button is selected on the Response Spectra form, which

is itself subordinate to the Response Spectrum Solution Parameter Form. Similar forms are used for the

second and third directions.The data on this form will define the *SPECTRUM option (see Section 7.11.5

of the ABAQUS/Standard User’s Manual).


Response Spectrum

If the selected solution type is Response Spectrum, then the following parameters may be defined on the

Output Requests form.


398











S11, S22, S33,

S12, S13, S23



stress, second principal stress, third principal stress, and the






SINV





E





User’s Manual.





SF











SE



STH


follows:

1. x-displacement

2. y-displacement

3. z-displacement






1. r-displacement

2. z-displacement






this time.

U


displacements.

V


displacements.

A




400




RF




CF








GU

Generalized Velocities The velocities associated with the modes of vibration. GV










Whole Model Energies The summation of all the energy of the model. The kinetic,



ALLEN







402

Random Vibration


Type is Random Vibration. This generates a *FREQUENCY procedure and a *RANDOM RESPONSE

procedure (see Sections 9.3.5 and 9.3.9 of the ABAQUS⁄Standard User’s Manual).


Define Spectrum (Random Vibration)

The Spectrum Data Table form is used to define the power spectral density function data for the ∗PSD-

DEFINITION option (see Section 7.11.3 of the ABAQUS/Standard User’s Manual).


404

Random Vibration

If the selected solution type is Random Vibration, then the following parameters may be defined on the












S11, S22,

S33, S12,

S13, S23

R.M.S. Stress Components

The root mean square value of the stress components. RA




stress invariant. These quantities are scalar quantities which

do not vary with a change of coordinate system. For elastic




SINV





E

R.M.S. Strain Components

The root mean square value of the strain components. RE





User’s Manual.





SF










User’s Manual.

SE



STH


as follows:

1. x-displacement

2. y-displacement

3. z-displacement






1. r-displacement

2. z-displacement






this time.

U

Velocities Nodal velocities, following the same convention as

for displacements.

V

Accelerations Nodal accelerations, following the same convention as

for displacements.

A

R.M.S. Relative Displacement

The root mean square value of the displacement components

relative to the base motion.

RU




406

R.M.S. Relative Velocities

The root mean square value of the velocity components


RV

R.M.S. Relative Acceleration

The root mean square value of the acceleration components


RA

Total Displacements The total displacement (including base motion) of the nodes. TU

Total Velocities The total velocity (including base motion) of the nodes. TV

Total Acceleration The total acceleration (including base motion) of the nodes. TA

R.M.S. Total Displacements

The root mean square value of the displacement components

including the base motion.

RTU

R.M.S. Total Velocities

The root mean square value of the velocity components


RTV

R.M.S. Total Accelerations

The root mean square value of the acceleration components


RTA




RF

R.M.S. Reaction Forces

The root mean square value of the modal component of the

reaction forces.

RRF



adjacent elements).

CF





GU

Generalized Velocities

The velocities associated with the modes of vibrations, each of

which have a shape (eigenmode) and associated frequency

(eigenvalue).

GV


The accelerations associated with the modes of vibrations,



GA





dissipation, and viscous dissipation is reported.

ALLEN




Nonlinear Static


Type is Nonlinear Static. This generates a *STATIC procedure with the associated *STEP option. The

NLGEOM parameter on the *STEP command is included. The NLGEOM parameter is included on the

*STEP option.

More data input is available for defining the Nonlinear Static Solution Parameters shown on the

previous page. Listed below are the remaining parameters contained in this menu if the Riks method is

not selected.

Element Mass Matrix







408

Listed below are the remaining parameters contained in this menu if the Riks method is selected.


Max No of Increments Defines the maximum number of increments that can be used

within a single step. This is a positive integer value. This is the

optional INC parameter on the ∗STEP option.

Initial DELTA-T Defines the initial time increment to be used. This is a real

constant. This will be modified as required if the automatic time

stepping scheme is used. Otherwise, it will be used as a constant

time increment.

Minimum DELTA-T Defines the minimum time increment to be used. This is a real

constant. It is only used for automatic time incrementation. If

ABAQUS finds it needs a smaller time increment than this value,

the analysis is terminated.

Maximum DELTA-T Defines the maximum time increment to be used. This is a real

constant. It is only used for automatic time incrementation. If this

value is not specified, no upper limit is imposed.

Time Duration of Step Defines the total time period of the step. This is a real constant.


Initial Load Fraction Defines the initial load fraction to be applied to the model. This is

a real constant. This is the initial time increment data value on the

∗STATIC command.

Minimum Load Fraction Defines the minimum load fraction which will be added during any

increment. These are real constants.

Maximum Load Fraction Defines the maximum load fraction which will be added during

any increment. These are real constants.

Stopping Condition Indicates which stopping condition is to be used. This can be set to

“Max. no. increments”, “Max. load multiplier”, or “Monitor a

Node.” This indicates which stopping condition data values are to

be defined on the ∗STATIC option.

Max. Load Multiplier This defines the maximum load multiplier allowed before the

iteration will be stopped. This is only used if “Max. load

multiplier,” or “Monitor a Node” are selected.

Node Number Indicates the node ID to be monitored. This is only used if

“Monitor a Node” is selected.


Nonlinear Static

If the selected solution type is Nonlinear Static, then the following parameters may be defined on the


Limit Value Defines the limiting displacement at the node being monitored.

This is only used if “Monitor a Node” is selected.

DOF Number Indicates which degree-of-freedom at this node is to be monitored.

This is only used if “Monitor a Node” is selected.











S11, S22,

S33, S12,

S13, S23




stress invariant. These quantities are scalar quantities which do

not vary with a change of coordinate system. For elastic




SINV





E

Plastic Strains The plastic strain component of the total strain. PE

Creep Strains The creep strain component of the total strain. CE

Elastic Strains The elastic strain component of the total strain. Note that the

elastic strain component is the component from which the

stress is computed.

EE

Inelastic Strains The total strain minus the elastic strain component. IE



410


The energy per unit volume of each element. Strain, plastic,

creep, and viscous dissipative energy densities are reported.

ENER


The energy of each element. Strain, kinetic, plastic, creep, and

viscous dissipative energies are reported.

ELEN




NFORC





User’s Manual.





SF



strains, curvature changes, and twist about the local axes.These

are discussed in Section 3.5.1 and Section 7.5.2 of the





User’s Manual.

SE



STH




Displacement Displacements are output at nodes and are referred to

as follows:

1. x-displacement

2. y-displacement

3. z-displacement






1. r-displacement

2. z-displacement






this time.

U




RF



adjacent elements).

CF





ALLEN

Element Mass Matrix







412



Type is Nonlinear Transient Dynamic. This generates a ∗DYNAMIC procedure, with the associated

∗STEP option. The DIRECT and HAFTOL parameters are available on the ∗DYNAMIC option.


More data input is available for defining the Nonlinear Transient Dynamic Solution Parameters shown

on the previous page. Listed below are the remaining parameters contained in this menu.


Initial DELTA-T Defines the initial time increment to be used. This is a real constant.

This will be modified as required if the automatic time stepping

scheme is used. Otherwise, it will be used as a constant time

increment.



ABAQUS finds it needs a smaller time increment than this value, the

analysis is terminated.





Max Error in Mid Increment Residual

This is the HAFTOL parameter on the ∗DYNAMIC option. See

Section 9.3.4 of the ABAQUS/Standard User’s Manual and Section

5.2.1 of the ABAQUS/Standard Example Problems.


414


If the selected solution type is Nonlinear Transient Dynamics, then the following parameters may be












S11, S22, S33,

S12, S13, S23









SINV





E





stress is computed.

EE





ENER


The energy of each element. Strain, kinetic, elastic, creep,

and viscous dissipative energies are reported.

ELEM


The forces that are found at each node by summing the

element stress contributions at the nodes.

NFORC






User’s Manual.





SF










SW



STH




416


follows:

1. x-displacement

2. y-displacement

3. z-displacement






1. r-displacement

2. z-displacement






this time.

U


displacements.

V


displacements.

A




RF


(e.g., the force at a node resulting from pressure distributions

on adjacent elements).

CF





ALLEN

Element Mass Matrix







Creep


Type is Creep. This generates a ∗VISCO procedure, with the associated ∗STEP option.

More data input is available for defining the Creep Solution Parameters shown on the previous page.

Listed below are the remaining parameters contained in this menu.




scheme is used.

Otherwise, it will be used as a constant time increment.






418

Creep

The strain components output depend on the elements analyzed, analogous to the stress components. In

addition, the total strain component can be separated into its contributory parts (e.g., elastic strain, plastic

strains, etc.) and these are reported separately.





Admissable Error in Strain Increment

This is the CETOL parameter on the ∗VISCO option. See Section

9.3.15 of the ABAQUS/Standard User’s Manual.











S11, S22, S33,

S12, S13, S23









SINV





E







stress is computed.

EE





ENER




ELEM




NFORC





User’s Manual.





SF










SE



STH




420


as follows:

1. x-displacement

2. y-displacement

3. z-displacement






1. r-displacement

2. z-displacement






this time.

U




RF




CF





ALLEN

Element Mass Matrix







Viscoelastic (Time Domain)

This subordinate form appears whenever Solution Parameters is selected and the Solution Type is

Viscoelastic (Time Domain). This generates a ∗VISCO procedure, with the associated ∗STEP command.


422

More data input is available for defining the Viscoelastic (Time Domain) Solution Parameters shown on

the previous page. Listed below are the remaining parameters contained in this menu.

Viscoelastic (Time Domain)

If the selected Solution Type is Viscoelastic (Time Domain), then the following parameters may be





scheme is used. Otherwise, it will be used as a constant time

increment.



















S11, S22, S33,

S12, S13, S23









SINV






E



Elastic Strains The elastic strain component of the total strain. Note that

the elastic strain component is the component from which

the stress is computed.

EE





ENER




ELEM




NFORC





User’s Manual.





SF










SE



STH




424


as follows:

1. x-displacement

2. y-displacement

3. z-displacement






1. r-displacement

2. z-displacement






this time.

U

Reaction Forces The forces at the nodes which are constrained and



RF




CF





ALLEN

Element Mass Matrix









is Viscoelastic (Frequency Domain). This generates a *STEADY STATE DYNAMIC procedure.


If the selected solution type is Viscoelastic (Frequency Domain), then the following parameters may be












S11, S22, S33,

S12, S13, S23









SINV

Ph Angle Stress Components



426





E

Ph Angle Strain Components






User’s Manual.





SF










SE



STH





follows:

1. x-displacement

2. y-displacement

3. z-displacement






1. r-displacement

2. z-displacement






this time.

U


displacements.

V


displacements.

A


The phase angle shift of the relative displacement

components.

PU

Reaction Forces The forces at the nodes which are constrained and so,



RF


The phase angle shift of the reaction force components. PRF




CF




428

Steady State Heat Transfer

This subordinate form appears whenever Solution Parameters is selected and the solution type is Steady

State Heat Transfer. This generates a ∗HEAT TRANSFER, STEADY STATE procedure.

Steady State Heat Transfer

If the selected solution type is Steady State Heat Transfer, then the following parameters may be defined

on the Output Requests form.

Element Mass Matrix






Element Temperature Temperature. TEMP

Heat Flux Current magnitude and components of the heat flux

vector. The integration of points for these values are

located at the Gauss points.

HFL

Nodal Temperatures All temperature values at a node. These will be the

temperatures defined as degrees-of-freedom if heat

transfer elements are connected to the node, or

predefined temperatures if the node is only connected to

stress elements without temperature degrees-of-freedom.

NT

Reaction Fluxes All reaction flux values (conjugate to temperature). RFL




Concentrated Fluxes All concentrated flux values. CFL






430

Transient Heat Transfer

This subordinate option is Transient Heat Transfer. This generates a ∗HEAT TRANSFER procedure.

Transient Heat Transfer

If the selected solution type is Transient Heat Transfer, then the following parameters may be defined on





Element Temperature Temperature. TEMP

Heat Flux Current magnitude and components of the heat flux

vector. The integration of points for these values are

located at the Gauss points.

HFL

Nodal Temperatures All temperature values at a node. These will be the

temperatures defined as degrees-of-freedom if heat

transfer elements are connected to the node, or

predefined temperatures if the node is only connected to

stress elements without temperature degrees-of-freedom.

NT

Reaction Fluxes All reaction flux values (conjugate to temperature). RFL

Concentrated Fluxes All concentrated flux values. CFL



Patran Interface to ABAQUS Preference GuideStep Selection

432

Step Selection

This subordinate form appears whenever the Step Selection button is selected on the main Analysis form.

This form is used to select and order the Job Steps that will be analyzed for the ABAQUS Job.

433Chapter 3 : Running AnalysisRead Input File

Read Input File

It is possible to read an existing ABAQUS input file (jobname.inp) into Patran. This is not a fully

supported feature and must be invoked by setting a special parameter. This is done by editing the

settings.pcl file and adding the following line:

pref_env_set_logical( "shareware_input_file", TRUE )

If this setting is set to TRUE, then an additional Action item will appear under the Analysis form called

Read Input File. This file can exist in the installation, local or home directories.

Patran Interface to ABAQUS Preference GuideRead Input File

434

435Chapter 3 : Running AnalysisABAQUS Input File Reader

ABAQUS Input File Reader

This section describes a software module that reads ABAQUS input files and writes the data to the

MSC/PATRAN database in a form compatible with the MSC/PATRAN ABAQUS preference.

Input Deck Formats

Both fixed format and free format entries are supported. Floating point formats with and without an “E”

in the exponent are supported (e.g. 1.23E6 and 1.23+6 are both supported).

Message File

Informative, warning, and error messages are written to an external file with the name

<input_file_basename>.msg.<version_number> where <input_file_basename> is the portion of the

ABAQUS input file name before the suffix and <version_number> is a unique version number beginning

with 01. After import, this file should be carefully examined to understand what was processed by the

reader and what was not. Sometimes the error messages will indicate where minor editing of the input

deck will convert an unsupported entity to one that can be handled by the reader.

ABAQUS ELSET and NSET Entries

A PATRAN group is created for each ABAQUS ELSET or NSET entry. The name of the group is taken

from the NAME parameter of the ELSET or NSET.

Supported Element Types

When the reader encounters a *ELEMENT entry, the combination of the element type and the ABAQUS

property set entry are used to map the ABAQUS element type to the appropriate PATRAN element type.

In some cases this is not possible because not all ABAQUS element types are currently supported in

PATRAN. In these cases, the reader attempts to find the PATRAN element type that “best” matches the

ABAQUS type. Thus, the ABAQUS elements retain their association to their property set. This allows

the finite element mesh to be edited in PATRAN and an ABAQUS input deck output that can be easily

edited to correct the property entry.

Supported Keywords

The table below describes the ABAQUS keywords that are supported in the current version of

the product.

ABAQUS Keyword Notes

Model Section

*AMPLITUDE A PATRAN time- or frequency-dependent field is created.

*BEAM GENERAL

SECTION

A PATRAN property set is created.

Patran Interface to ABAQUS Preference GuideABAQUS Input File Reader

436

*BEAM SECTION A PATRAN property set is created.

*BOUNDARY A PATRAN LBC set is created for each ABAQUS BOUNDARY and

added to all load cases. Displacement, temperature, velocity, and

acceleration boundary conditions are currently supported.

*CENTROID Location is added to the PATRAN property set.

*CONDUCTIVITY Value is added to the PATRAN material.

*CONTACT NODE SET When referenced in a *CONTACT PAIR, this data is added to a

contact-type LBC set.

*CONTACT PAIR A PATRAN contact-type LBC set is created for each entry in

*CONTACT PAIR.

*CORRELATION

*DAMPING Value is added to the PATRAN material or shell element property set.

*DASHPOT A PATRAN property set is created.

*DENSITY Value is added to the PATRAN material.

*ELASTIC Values are added to the PATRAN material.

*ELCOPY Element Generation Command

*ELEMENT PATRAN elements are created. Both a PATRAN group and a property

set are created with the ELSET name.

*ELGEN PATRAN elements are created.

*ELSET A PATRAN group is created.

*EQUATION A PATRAN MPC is created. The use of node sets in *EQUATION

entries is not currently supported.

*EXPANSION Values are added to the PATRAN material.

*FRICTION The *FRICTION keyword is supported within *GAP, *INTERFACE,

and *SURFACE INTERACTION blocks. The friction properties are

added to the appropriate property or LBC set.

*GAP A PATRAN property set is created.

*HEADING A PATRAN analysis job is created with this description.

*HOURGLASS STIFFNESS The values are added to the appropriate PATRAN property set.

*INCLUDE The referenced file is read. *INCLUDE entries may be nested to any

reasonable depth.

*MASS A PATRAN property set is created.

*MATERIAL A PATRAN material is created.

*MEMBRANE SECTION A PATRAN property set is created.



*MPC A PATRAN MPC is created. The use of node sets in *MPC entries is

not currently supported.

*MODAL DAMPING

*NCOPY Generates additional nodes using NID and X/Y/Z offsets.

*NFILL PATRAN nodes are created. The SINGULAR option is not currently

supported.

*NGEN PATRAN nodes are created. Nodes may be generated along a line or a

circular arc (LINE=C) but not along a parabola (LINE=P).

*NODAL THICKNESS A PATRAN nodal FEM field and property set are created.

*NODE PATRAN nodes are created. If an NSET parameter is specified, a

PATRAN group is created with this name, otherwise the nodes are

added to the default group.

*NSET A PATRAN group is created.

*ORIENTATION Is used to define orientation for homogeneous or laminate material

properties.

*PLASTIC Only HARDENING=ISOTROPIC and HARDENING=KINEMATIC

are currently supported. The RATE parameter is not currently

supported; only the first set *PLASTIC entries for a material are

imported.

*PSD

*RIGID BODY When referenced in a *CONTACT PAIR, this data is added to a


*RIGID SURFACE The *RIGID SURFACE keyword is currently supported in two ways

by the PATRAN, ABAQUS preference. For the older style of

ABAQUS contact, which required the use of IRSx type elements,

*RIGID SURFACE entries were written out for “rigid surface type”

element properties. For the newer style of ABAQUS contact ,which

uses *CONTACT PAIR, geometric curves are selected directly in a

PATRAN contact-type LBC. Only this second usage of *RIGID

SURFACE is supported by the reader. When referenced in a

*CONTACT PAIR entry, curves are created and references to them

added to the contact-type LBC set.

*ROTARY INERTIA A PATRAN property set is created.

*SECTION POINTS Points are added to the PATRAN property set.

*SHEAR CENTER Location is added to the PATRAN property set.

*SHELL GENERAL

SECTION

A PATRAN property set is created.

*SHELL SECTION A PATRAN property set is created.



438

*SOLID SECTION A PATRAN property set is created.

*SPECTRUM

*SPECIFIC HEAT Value is added to the PATRAN material.

*SPRING A PATRAN property set is created.

*SURFACE DEFINITION When referenced in a *CONTACT PAIR, this data is added to a


*SURFACE INTERACTION The only keyword currently supported within this block is

*FRICTION. The keyword parameters and friction data are added to

the appropriate contact-type LBC set.

*SYSTEM PATRAN node locations are transformed to the coordinate system

defined on this entry.

*TRANSFORM A PATRAN coordinate frame is created and used to define the analysis

system for the node.

*TRANSVERSE SHEAR

STIFFNESS

The values are added to the appropriate PATRAN property set.

History Section

*BOUNDARY A PATRAN LBC set is created for each ABAQUS BOUNDARY and

added to the load case for this step. Displacement, temperature,

velocity, and acceleration boundary conditions are currently

supported.

*BUCKLE The parameters associated with this entry are added to the PATRAN

analysis step.

*CFLUX A PATRAN LBC set is created for each ABAQUS CFLUX and added

to the load case for this step.

*CLOAD A PATRAN LBC set is created for each ABAQUS CLOAD and added


*DFLUX A PATRAN LBC set is created for each ABAQUS DFLUX and added


*DLOAD A PATRAN LBC set is created for each ABAQUS DLOAD and added

to the load case for this step. The pressure DLOAD types as well as

GRAV, CENT, CENTRIF, and CORIO are currently supported.

*DYNAMIC The parameters associated with this entry are added to the PATRAN

analysis step.

*FILM A PATRAN LBC set is created for each ABAQUS FILM and added to

the load case for this step.

*FREQUENCY The parameters associated with this entry are added to the PATRAN

analysis step.



Both fixed format and free format entries are supported.

The table below shows the PATRAN element property options that are created when a specific ABAQUS

element type is imported.

*HEAT TRANSFER The parameters associated with this entry are added to the PATRAN

analysis step.

*MODAL DYNAMIC The parameters associated with this entry are added to the PATRAN

analysis step.

*STATIC The parameters associated with this entry are added to the PATRAN

analysis step.

*STEADY STATE

DYNAMICS

The parameters associated with this entry are added to the PATRAN

analysis step.

*STEP A PATRAN load case and an analysis job step are created for each

ABAQUS step. The parameters on the *STEP entry are added to the

analysis step

*TEMPERATURE A PATRAN LBC set is created for each ABAQUS TEMPERATURE

and added to the load case for this step.

*VISCO The parameters associated with this entry are added to the PATRAN

analysis step.

Table 3-1 PATRAN Property Options for Each ABAQUS Element

ABAQUS Element Dim Name Option1 Option2

AC1D2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

AC1D3 1D ISL (in plane) Axisymmetric Lagrange Soft Contact

AC2D4 2D Rigid Surface(LBC)

AC2D8 2D 2D Interface Axisymmetric Lagrange Vis Damping

AC3D20 3D Solid Homogeneous Standard Formulation

AC3D8 3D Solid Homogeneous Hybrid

ACAX4 2D Rigid Surface(LBC)

ACAX8 2D 2D Interface Axisymmetric Lagrange Vis Damping

ASI1 0D IRS (single node) Planar Elas Slip Vis Damping

ASI2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

ASI2A 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

ASI3 2D IRS (shell/solid) Elastic Slip Hard

Contact

ASI3A 2D Shell General Large Strain Homogeneous

ASI4 2D IRS (shell/solid) Lagrange Hard

Contact



440

ASI8 2D 2D Interface Axisymmetric Lagrange Vis Damping

B21 1D Beam in XY Plane General Section Standard Formulation

B21H 1D Beam in XY Plane General Section Hybrid

B22 1D Beam in XY Plane General Section Standard Formulation

B22H 1D Beam in XY Plane General Section Hybrid

B23 1D Beam in XY Plane General Section Cubic Interpolation

B23H 1D Beam in XY Plane General Section Cubic Hybrid

B31 1D Beam in Space General Section Standard Formulation

B31H 1D Beam in Space General Section Hybrid

B31OS 1D Beam in Space Open Section Standard Formulation

B31OSH 1D Beam in Space Open Section Hybrid

B32 1D Beam in Space General Section Standard Formulation

B32H 1D Beam in Space General Section Hybrid

B32OS 1D Beam in Space Open Section Standard Formulation

B32OSH 1D Beam in Space Open Section Hybrid

B33 1D Beam in Space General Section Cubic Interpolation

B33H 1D Beam in Space General Section Cubic Hybrid

B34 1D Beam in Space General Section Cubic Initially Straight

C1D2 1D Truss Standard Formulation

C1D2H 1D Truss Hybrid

C1D2T 1D Truss Hybrid

C1D3 1D Truss Standard Formulation

C1D3H 1D Truss Hybrid

C1D3T 1D Truss Standard Formulation

C3D10 3D Solid Homogeneous Standard Formulation

C3D10E 3D Solid Homogeneous Homogeneous

C3D10H 3D Solid Homogeneous Hybrid

C3D10M 3D Solid Homogeneous Modified Formulation

C3D10MH 3D Solid Homogeneous Modified/Hybrid


C3D15E 3D Solid Homogeneous Standard Formulation


C3D15V 3D Solid Homogeneous Standard Formulation

C3D15VH 3D Solid Homogeneous Hybrid




C3D20HT 3D Solid Homogeneous Standard Formulation

C3D20P 3D Solid Homogeneous Standard Formulation

Table 3-1 PATRAN Property Options for Each ABAQUS Element (continued)



C3D20PH 3D Solid Homogeneous Standard Formulation

C3D20R 3D Solid Homogeneous Reduced Integration

C3D20RE 3D Solid Homogeneous Standard Formulation

C3D20RH 3D Solid Homogeneous Hybrid/Reduced

Integration

C3D20RHT 3D Solid Homogeneous Standard Formulation

C3D20RP 3D Solid Homogeneous Standard Formulation

C3D20RPH 3D Solid Homogeneous Standard Formulation

C3D20RT 3D Solid Homogeneous Standard Formulation

C3D20T 3D Solid Homogeneous Standard Formulation





Integration


C3D4E 3D Solid Standard Formulation






C3D8E 3D Solid Homogeneous Hybrid


C3D8HT 3D Solid Homogeneous Hybrid

C3D8I 3D Solid Homogeneous Incompatible Modes

C3D8IH 3D Solid Homogeneous Hybrid/Incompatible

Modes



Integration

C3D8T 3D Solid Homogeneous Hybrid

CAX3 2D 2D Solid Axisymmetric Standard Formulation

CAX3E 2D 2D Solid Axisymmetric Standard Formulation

CAX3H 2D 2D Solid Axisymmetric Hybrid


CAX4E 2D 2D Solid Axisymmetric Standard Formulation


CAX4HT 2D 2D Solid Axisymmetric Standard Formulation




442

CAX4I 2D 2D Solid Axisymmetric Incompatible Modes

CAX4IH 2D 2D Solid Axisymmetric Hybrid/Incompatible

Modes

CAX4P 2D 2D Solid Axisymmetric Standard Formulation

CAX4PH 2D 2D Solid Axisymmetric Standard Formulation

CAX4R 2D 2D Solid Axisymmetric Reduced Integration

CAX4RH 2D 2D Solid Axisymmetric Hybrid/Reduced

Integration

CAX4T 2D 2D Solid Axisymmetric Standard Formulation


CAX6E 2D 2D Solid Axisymmetric Axisymmetric


CAX6M 2D 2D Solid Axisymmetric Modified Formulation

CAX6MH 2D 2D Solid Axisymmetric Modified/Hybrid


CAX8E 2D 2D Solid Axisymmetric Hybrid


CAX8HT 2D 2D Solid Axisymmetric Hybrid

CAX8P 2D 2D Solid Axisymmetric Hybrid

CAX8PH 2D 2D Solid Axisymmetric Hybrid

CAX8R 2D 2D Solid Axisymmetric Reduced Integration

CAX8RE 2D 2D Solid Axisymmetric Hybrid

CAX8RH 2D 2D Solid Axisymmetric Hybrid/Reduced

Integration

CAX8RHT 2D 2D Solid Axisymmetric Hybrid

CAX8RP 2D 2D Solid Axisymmetric Hybrid

CAX8RPH 2D 2D Solid Axisymmetric Hybrid

CAX8RT 2D 2D Solid Axisymmetric Hybrid

CAX8T 2D 2D Solid Axisymmetric Hybrid

CAXA41 2D 2D Solid Axisymmetric Standard Formulation




CAXA4H1 2D 2D Solid Axisymmetric Hybrid




CAXA4R1 2D 2D Solid Axisymmetric Reduced Integration







CAXA4RH1 2D 2D Solid Axisymmetric Hybrid/Reduced

Integration


Integration


Integration


Integration









CAXA8P1 2D 2D Solid Axisymmetric Hybrid









Integration


Integration


Integration


Integration

CAXA8RP1 2D 2D Solid Axisymmetric Hybrid




CGAX3 2D 2D Solid Axisymmetric Standard Formulation




444

CGAX3H 2D 2D Solid Axisymmetric Hybrid



CGAX4I 2D 2D Solid Axisymmetric Incompatible Modes

CGAX4IH 2D 2D Solid Axisymmetric Hybrid/Incompatible

Modes

CGAX4R 2D 2D Solid Axisymmetric Reduced Integration

CGAX4RH 2D 2D Solid Axisymmetric Hybrid/Reduced

Integration

CGAX6 2D 2D Solid Axisymmetric Axisymmetric




CGAX8R 2D 2D Solid Axisymmetric Reduced Integration

CGAX8RH 2D 2D Solid Axisymmetric Hybrid/Reduced

Integration

CGPE10 2D 2D Solid General Plane Strain Standard Formulation

CGPE10H 2D 2D Solid General Plane Strain Hybrid

CGPE10R 2D 2D Solid General Plane Strain Reduced Integration

CGPE10RH 2D 2D Solid General Plane Strain Hybrid/Reduced

Integration





CGPE6I 2D 2D Solid General Plane Strain Incompatible Modes

CGPE6IH 2D 2D Solid General Plane Strain Hybrid/Incompatible

Modes

CGPE6R 2D 2D Solid General Plane Strain Reduced Integration

CGPE6RH 2D 2D Solid General Plane Strain Hybrid/Reduced

Integration






CONN2D2 1D Mech Joint (2D

Model)

ALIGN

AXIAL

BEAM

CARTESIAN

JOIN

JOINTC

LINK

ROTATION

SLOT

TRANSLATOR

WELD

CONN3D2 1D Mech Joint (3D

Model)

ALIGN

AXIAL

BEAM

CARDAN

CARTESIAN

CONSTANT

VELOCITY

CVJOINT

CYLINDRICAL

EULER

FLEXION-TORSION

HINGE

JOIN

JOINTC

LINK

PLANAR

RADIAL-THRUST

REVOLUTE

ROTATION

SLIDE-PLANE

SLOT

TRANSLATOR

UJOINT

UNIVERSAL

WELD

CPE3 2D 2D Solid Plane Strain Standard Formulation

CPE3E 2D 2D Solid Plane Strain Plane Strain

CPE3H 2D 2D Solid Plane Strain Hybrid


CPE4E 2D 2D Solid Plane Strain Reduced Integration




446


CPE4HT 2D 2D Solid Plane Strain Reduced Integration

CPE4I 2D 2D Solid Plane Strain Incompatible Modes

CPE4IH 2D 2D Solid Plane Strain Hybrid/Incompatible

Modes

CPE4R 2D 2D Solid Plane Strain Reduced Integration

CPE4RH 2D 2D Solid Plane Strain Hybrid/Reduced

Integration

CPE4T 2D 2D Solid Plane Strain Reduced Integration


CPE6E 2D 2D Solid Plane Strain Standard Formulation



CPE8E 2D 2D Solid Plane Strain Reduced Integration


CPE8HT 2D 2D Solid Plane Strain Reduced Integration

CPE8P 2D 2D Solid Plane Strain Standard Formulation

CPE8PH 2D 2D Solid Plane Strain Hybrid

CPE8R 2D 2D Solid Plane Strain Reduced Integration

CPE8RE 2D 2D Solid Plane Strain Reduced Integration

CPE8RH 2D 2D Solid Plane Strain Hybrid/Reduced

Integration

CPE8RHT 2D 2D Solid Plane Strain Reduced Integration

CPE8RP 2D 2D Solid Plane Strain Reduced Integration

CPE8RPH 2D 2D Solid Plane Strain Hybrid/Reduced

Integration

CPE8RT 2D 2D Solid Plane Strain Reduced Integration

CPE8T 2D 2D Solid Plane Strain Reduced Integration

CPS3 2D 2D Solid Plane Stress Standard Formulation

CPS3E 2D 2D Solid Plane Stress Plane Stress


CPS4E 2D 2D Solid Plane Stress Reduced Integration

CPS4I 2D 2D Solid Plane Stress Incompatible Modes

CPS4R 2D 2D Solid Plane Stress Reduced Integration

CPS4T 2D 2D Solid Plane Stress Reduced Integration


CPS6E 2D 2D Solid Plane Stress Standard Formulation

CPS6M 2D 2D Solid Plane Stress Modified Formulation





CPS8E 2D 2D Solid Plane Stress Standard Formulation

CPS8R 2D 2D Solid Plane Stress Reduced Integration

CPS8RE 2D 2D Solid Plane Stress Standard Formulation

CPS8RT 2D 2D Solid Plane Stress Standard Formulation

CPS8T 2D 2D Solid Plane Stress Standard Formulation

DASHPOT1 0D Grounded Damper Linear

DASHPOT2 1D Damper Linear Fixed Direction

DASHPOTA 1D Damper Linear Standard Formulation

DC1D2 1D Link

DC1D2E 1D Link

DC1D3 1D Link

DC1D3E 1D Link

DC2D3 2D 2D Solid Planar Standard Formulation




DC3D10 3D Solid Standard Formulation






DCAX3 2D 2D Solid Axisymmetric Standard Formulation




DCC1D2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

DCC1D2D 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

DCC2D4 2D 2D Solid Planar Convection/Diffusion

DCC2D4D 2D 2D Solid Planar Convection/Diffusion

with Dispersion Control

DCC3D8 3D Solid Convection/Diffusion

DCC3D8D 3D Solid Convection/Diffusion

with Dispersion

Control

DCCAX2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

DCCAX2D 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

DCCAX4 2D 2D Solid Axisymmetric Convection/Diffusion




448

DCCAX4D 2D 2D Solid Axisymmetric Convection/Diffusion

with Dispersion Control

DINTER1 1D 1D Interface

DINTER2 2D 2D Interface Planar

DINTER2A 2D 2D Interface Axisymmetric

DINTER3 2D 2D Interface Planar

DINTER3A 2D 2D Interface Axisymmetric Lagrange Vis Damping



DS4 2D Shell Homogeneous

DS8 2D Shell Homogeneous

DSAX1 1D Axisym Shell Homogeneous

DSAX2 1D Axisym Shell Homogeneous

ELBOW31 1D Beam in Space Curved with Pipe

Section


ELBOW31B 1D Beam in Space Curved with Pipe

Section

Ovalization Only

ELBOW31C 1D Beam in Space Curved with Pipe

Section

Ovaliz Only with

Approximated Fourier

ELBOW32 1D Beam in Space Curved with Pipe

Section


F2D2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

F3D3 2D Shell General Large Strain Homogeneous

F3D4 2D Rigid Surface(LBC)

FAX2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

FLINK 1D Link

GAPCYL 1D Gap Cylindrical True Distance

GAPSPHER 1D Gap Spherical Elas Slip Vis Damping

GAPUNI 1D Gap Uniaxial Lagrange Vis Damping

No Sep

INTER1 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

INTER1P 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

INTER1T 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

INTER2 2D IRS (shell/solid) Lagrange Hard

Contact

INTER2A 2D 2D Interface Axisymmetric Lagrange Hard Contact

INTER2AT 2D 2D Interface Axisymmetric Lagrange Hard Contact

INTER2T 2D IRS (shell/solid) Lagrange Hard

Contact




INTER3 2D 2D Interface Axisymmetric Lagrange Vis Damping

INTER3A 2D 2D Interface Axisymmetric Lagrange Vis Damping

INTER3AP 2D 2D Interface Axisymmetric Lagrange Vis Damping

INTER3AT 2D 2D Interface Axisymmetric Lagrange Vis Damping

INTER3P 2D 2D Interface Axisymmetric Lagrange Vis Damping

INTER3T 2D 2D Interface Axisymmetric Lagrange Vis Damping

INTER4 3D 3D Interface Lagrange Vis

Damping

INTER4T 3D 3D Interface Lagrange Vis

Damping

INTER8 3D 3D Interface Elas Slip Vis Damping

INTER8T 3D 3D Interface Elas Slip Vis Damping

INTER9 3D 3D Interface Lagrange Vis

Damping

IRS12 0D IRS (single node) Planar Elas Slip Vis Damping

IRS13 0D IRS (single node) Planar Elas Slip Vis Damping

IRS21 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

IRS21A 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

IRS22 1D ISL (in plane) Axisymmetric Lagrange Soft Contact

IRS22A 1D ISL (in plane) Axisymmetric Lagrange Soft Contact

IRS3 2D IRS (shell/solid) Elastic Slip Hard

Contact

IRS31 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

IRS32 1D ISL (in plane) Axisymmetric Lagrange Soft Contact

IRS4 2D IRS (shell/solid) Lagrange Hard

Contact

IRS9 2D IRS (shell/solid) Lagrange Hard

Contact

ISL21 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

ISL21A 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

ISL21AT 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

ISL21T 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

ISL22 1D ISL (in plane) Axisymmetric Lagrange Soft Contact

ISL22A 1D ISL (in plane) Axisymmetric Lagrange Soft Contact

ISL22AT 1D ISL (in plane) Axisymmetric Lagrange Soft Contact

ISL31 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

ISL31A 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

ISL32 1D ISL (in plane) Axisymmetric Lagrange Soft Contact

ISL32A 1D ISL (in plane) Axisymmetric Lagrange Soft Contact




450

ISP1 0D IRS (single node) Planar Elas Slip Vis Damping

ISP1T 0D IRS (single node) Planar Elas Slip Vis Damping

ISP3 2D Shell Thick Homogeneous

ISP4 2D Shell General Large Strain Homogeneous

ISP4T 2D Shell General Large Strain Homogeneous

JOINTC 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

LS6 2D Shell Thin Homogeneous

M3D3 2D Membrane Standard Formulation


M3D4R 2D Membrane Reduced Integration






MASS 0D Mass

MAX1 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

MAX2 1D ISL (in plane) Axisymmetric Lagrange Soft Contact

MGAX1 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

MGAX2 1D ISL (in plane) Axisymmetric Lagrange Soft Contact

PIPE21 1D Beam in XY Plane Pipe Section Standard Formulation

PIPE21H 1D Beam in XY Plane Pipe Section Hybrid


PIPE22H 1D Beam in XY Plane Pipe Section Hybrid


PIPE31H 1D Beam in XY Plane Pipe Section Standard Formulation

PIPE32 1D Beam in Space Pipe Section Standard Formulation

PIPE32H 1D Beam in Space Pipe Section Standard Formulation

R2D2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

R3D3 2D Rigid Surface(LBC)

R3D4 2D Rigid Surface(LBC)

RAX2 1D IRS (planar/axisym) Axisymmetric Elastic Slip Hard Contact

RB2D2 1D Rigid Line(LBC)

RB3D2 1D Rigid Line(LBC)

ROTARYI 0D Rotary Inertia

S3 2D Shell Thick Homogeneous

S3R 2D Shell General Large Strain Homogeneous

S4 2D Shell General Large Strain Homogeneous

S4R 2D Shell Thick Homogeneous




S4R5 2D Shell Thin Homogeneous

S8R 2D Shell Thick Homogeneous


S8RT 2D Shell Thick Homogeneous


SAX1 1D Axisym Shell Homogeneous

SAX2 1D Axisym Shell Homogeneous

SAX2T 1D Axisym Shell Homogeneous

SAXA11 1D Axisym Shell Homogeneous








SPRING1 0D Grounded Spring Linear

SPRING2 1D Spring Linear Fixed Direction

SPRINGA 1D Spring Linear Standard Formulation

STRI3 2D Shell Thick Homogeneous

STRI35 2D Shell Thin Homogeneous

STRI65 2D Shell Thick Homogeneous

T2D2 1D Truss Hybrid

T2D2E 1D Truss Hybrid

T2D2H 1D Truss Hybrid

T2D2T 1D Truss Hybrid

T2D3 1D Truss Standard Formulation

T2D3E 1D Truss Standard Formulation

T2D3H 1D Truss Standard Formulation

T2D3T 1D Truss Standard Formulation


T3D2E 1D Truss Hybrid


T3D2T 1D Truss Hybrid


T3D3E 1D Truss Standard Formulation


T3D3T 1D Truss Standard Formulation




452

Under some circumstances, the values of the option menus in Patran (Option 1 and Option 2) may be

different than shown in the table. This is often the case when the ABAQUS element is one that is not

directly supported by the Patran interface and the translator is making a “best guess” at which Patran

element to choose. For many beam elements in the table, Option 1 is shown as “General Section”.

Depending on the beam cross section type defined on the *BEAM SECTION or *BEAM GENERAL

SECTION entry, Option 1 may be General Section, Box Section, Circular Section, Hexagonal Section, I

Section, Pipe Section, Rectangular Section, or Trapezoid Section. For the 3D solid elements and shell

elements in the table, Option 1 is shown as Homogeneous. Depending on the *SHELL SECTION or

*SHELL GENERAL SECTION entry, Option 1 may be either Homogeneous or Laminate.

Chapter 4: Read Results

Patran Interface to ABAQUS preference Guide

4 Read Results

� Review of the Read Results Form 454

� Translation Parameters 457

� Select Results File 458

� Data Translated from the Analysis Code Results File 463

� Key Differences between Attach and Translate Methods 464

� Delete Result Attachment Form 466

Patran Interface to ABAQUS preference GuideReview of the Read Results Form

454

Review of the Read Results Form

By choosing the Analysis toggle located on the Patran main form, an Analysis form will appear.

Selecting Read Results as the Action on the Analysis form allows you to read results data into the Patran

database from a text (“jobname”.fin) or binary (“jobname”.fil) ABAQUS results file, or to

access ABAQUS results directly from an ABAQUS results output database (“jobname”.odb). Other

forms that are accessible from here are used to define translation parameters and select the ABAQUS

results file. These forms are described on the following pages.

Upgrading ABAQUS ODB Results Files

Since the ABAQUS DRA in Patran is integrated with the ABAQUS 6.3-1 libraries, you must make sure

your ODB results files have been upgraded to 6.3 before attempting to attach to them from within Patran.

This can be done in one of two ways:

Manually Upgrade ODB Files

The procedure for upgrading ODB files is part of ABAQUS:

abaqus upgrade job=job-name odb=old-odb-file-name

Automatic Upgrade of ODB Files

If you want to automatically upgrade your older ODB results files, you can set the following

environment variable:

Setenv ABAQUS_DRA_UPGRADE_ODB=YES

By setting this variable, Patran will make a copy of the ODB results file and upgrade the copy to the

current version of ABAQUS.

455Chapter 4: Read ResultsReview of the Read Results Form

Read Results Form

Read Results defines the type of data to be read from the analysis code results file into Patran. The Object

box may only be set to Results Entities.

Patran Interface to ABAQUS preference GuideReview of the Read Results Form

456

Flat File Results

In some cases, the translation will not be able to write the data directly into the Patran database. In those

cases, a text file will be created containing all the instructions as to how this data is to be loaded into the

database. This file can be transferred between computers if necessary, then read into the proper database

using the File Import functionality. The full functionality of this form is described in Working with Files

(p. 45) in the Patran Reference Manual.

457Chapter 4: Read ResultsTranslation Parameters

Translation Parameters

The Translation Parameters form is used to define filters for the data being accessed.

Attach Method

There is only one filter control for the Attach method, which indicates whether or not to allow access to

the results invariants, as calculated by Abaqus.

Translate and Control File Methods

Translation parameters for the Translate and Control File methods include the results filtering options

based on the step number and the increment number. If none of the options are specified, then all the

results will be translated. If only step is specified, then all the increments in that step will be translated.

If only increment is specified, then that increment for the first step will be translated. If both step and

increment are specified, then only the increment for that step will be translated.

Patran Interface to ABAQUS preference GuideSelect Results File

458

Select Results File

The Select file form allows you to select a file to be read. There are several features available. This form

is brought up when you select the Select Results File button on the Read Results form. The default file

filters will change depending on the Current analysis code in the Preferences menu.

Results Created in Patran

For direct ODB access (Attach method), no results are created in Patran, and all result types represented

within the field output data in the ODB file are available for postprocessing.

The following table indicates all the possible results quantities which can be loaded into the Patran

database during results translation (Translate method) from ABAQUS. The Primary and Secondary

Labels are the items you select from the postprocessing menus. The Type indicates whether the results

are Scalar, Vector, or Tensor. This determines which postprocessing techniques will be available to view

this results quantity. Post Codes indicates which ABAQUS element post codes the data comes from. The

Description gives a brief discussion about the results quantity. The Output Requests forms use the actual

459Chapter 4: Read ResultsSelect Results File

primary and secondary labels that will appear in the results. For example, if “Strain, Elastic” is selected

on the Element Output Requests form, the “Strain, Elastic” is created for postprocessing.

Table 4-1 Results Quantities Loaded into Patran During Translation

Primary Label Secondary Label TypeResults

Key

Acceleration Generalized Rotational Vector 303

Generalized Translational Vector 303

Rotational Vector 103

Translational Vector 103

Base Motion Rotational Vector 304


Change in Length Components Tensor 21

Concentrated Flux (Nodal) Layer or Section Points Scalar 206

Concentrated Load Vector 106

Moment Vector 106

Deformation Displacements Vector 101

Rotations Vector 101

Displacements Generalized Displacements Vector 301

Generalized Rotations Vector 301

Elastic Strain Components Tensor 25

Energy Density Artificial Strain Energy Scalar 14

Creep Dissipation Scalar 14

Plastic Dissipation Scalar 14

Strain Energy Scalar 14

Viscous Dissipation Scalar 14

Energy in Element Artificial Strain Energy Scalar 19

Creep Dissipation Scalar 19

Kinetic Energy Scalar 19

Plastic Dissipation Scalar 19

Strain Energy Scalar 19

Viscous Dissipation Scalar 19

Total Energy Total Artificial Strain Energy Scalar 1999

Total Creep Dissipation Scalar 1999

Total Energy Loss at Impact Scalar 1999

Total External Work Scalar 1999

Total Kinetic Scalar 1999

Total Plastic Dissipation Scalar 1999

Total Strain Scalar 1999

Total Viscous Dissipation Scalar 1999

Force and Shear Force Components Tensor 11


460

Force Components Tensor 11

Frequency Steady State Dynamics Scalar 2000

Heat Flux (Nodal) Components Vector 10

Heat Flux Components Vector 28

Magnitude Scalar 28

Inelastic Strain Components Tensor 24

Internal Flux (Nodal) Layer or Section Points Scalar 214

Internal Forces Components at Element Node Vector 15

Mass Flux Components Vector 39

Magnitude Scalar 39

Modal Composite Damping Scalar 1980

Effective Mass Scalar 1980

Eigen Values Scalar 1980

Generalized Mass Scalar 1980

Participation Factor Scalar 1980

Mag-Phase Strain Components Tensor 65

Mag-Phase Stress Components Tensor 62

Phase Angle Generalized Displacements Vector 305

Generalized Rotational Acceleration Vector 307

Generalized Rotational Velocities Vector 306

Generalized Rotations Vector 305

Generalized Translational Accelerations Vector 307

Generalized Translational Velocities Vector 306

Mag-Phase Reaction Force Vector 135

Mag-Phase Reaction Moment Vector 135

Mag-Phase Displacements Displacements Vector 111

Mag-Phase Acceleration Rotational Vector 137

Mag-Phase Velocity Rotational Vector 136

Mag-Phase Displacements Rotations Vector 111

Mag-Phase Velocity Translational Vector 136

Mag-Phase Total

Displacement


Mag-Phase Total

Acceleration


Mag-Phase Total Velocity Rotational Vector 139

Mag-Phase Total

Displacement


Mag-Phase Total

Acceleration


Table 4-1 Results Quantities Loaded into Patran During Translation (continued)


Key

461Chapter 4: Read ResultsSelect Results File

Mag-Phase Total Velocity Translational Vector 139

Mag-Phase Acceleration Translational Vector 137

Plastic Strain Components Tensor 22

Equivalent Scalar 22

Magnitude Scalar 22

Yield Flag Scalar 22

Pressure and Shear

Stresses

Components Tensor 11

RMS Strain Components Tensor 66

RMS Stress Components Tensor 63

Reaction Force Vector 104

Moment Vector 104

Relative Displacements

and Shear Slips


Rel. Normal & Tangential

Displacements


Residual Flux (Nodal) Layer and Section Points Scalar 204

Root Mean Square Reaction Forces Vector 134

Reaction Moments Vector 134

Relative Displacements Vector 123

Relative Rotational Accelerations Vector 131

Relative Rotational Velocities Vector 127

Relative Rotations Vector 123

Relative Translational Velocities Vector 127

Total Displacements Vector 124

Total Rotational Accelerations Vector 132

Total Rotational Velocities Vector 128

Total Rotations Vector 124

Total Translational Accelerations Vector 132

Total Translational Velocities Vector 128

Relative Translational Accelerations Vector 131

Strain Components Tensor 21



Key


462

Stress 1st Principal Scalar 12

2nd Principal Scalar 12

3rd Principal Scalar 12

3rd Stress Invariant Scalar 12


Hydrostatic Pressure Scalar 12

Maximum Stress in Section Scalar 16

Mises Scalar 12

Tresca Scalar 12

Temperature (Nodal) Layer or Section Points Scalar 201

Temperature Element Centroidal Temperature Scalar 2

Total Acceleration Rotational Vector 115


Total Displacement Rotational Vector 113


Total Velocity Rotational Vector 114


Total Creep Time Scalar 2000

Dynamic Time Scalar 2000

Heat Transfer Time Scalar 2000

Soils Time Scalar 2000

Time Scalar 2000

Velocity Generalized Rotational Vector 302

Generalized Translational Vector 302



Creep Strain Components Tensor 23

Equivalent Scalar 23

Magnitude Scalar 23

Yield Flag Scalar 23



Key

463Chapter 4: Read ResultsData Translated from the Analysis Code Results File

Data Translated from the Analysis Code Results File

When reading model data from an ABAQUS results file, the following table defines all the data which

will be created. No other model data is extracted from the results file. This data should be sufficient for

evaluating any results values.

Item Results Key Description

Nodes 1901 Node ID

Nodal Coordinates

Elements 1900 Element ID

Nodal Connectivity

Groups n/a, ODB access only Group name

Node and Element references

Groups are generated for each part instance, as well as for each

node and element set.

Patran Interface to ABAQUS preference GuideKey Differences between Attach and Translate Methods

464

Key Differences between Attach and Translate Methods

The most obvious difference between direct ODB access (Attach method) and results translation

(Translate method) is that the results are not imported into the Patran database in the case of the former,

while they are for the latter. Direct access avoids redundancy and saves disk space, while Translation uses

more disk space, but takes less time to retrieve results for postprocessing.

The following sections describe other differences that users should be aware of, before deciding which

method to use.

Result Type Naming Conventions

The names used for the result types within an ODB attachment come directly from the field output

description fields of the ODB database. Using the “direct access” philosophy of bringing the data in as-

is, there is no attempt to map those names to the same names used by the Translate method (listed in

Table 4-1).

Therefore, direct ODB access will use Abaqus terminology exclusively in generating the result type

names. The primary name is equal to the field output description field, while the secondary name is the

field output key. For example, the stress tensor result type is “Stress components, S”, where “Stress

components” is the field output description, and “S” is the field output key.

Vector vs. Scalar Moment and Rotational Results

For results such as reaction moments or rotational displacements, the ODB database saves space by only

storing results for the non-zero component, whenever possible. So, if non-zero values for moments only

occur in the Z component, then the ODB database stores it as a scalar result (e.g. key RM3). However,

the Translate method will import the results as vector results, with the X and Y values always being zero.

This difference may cause confusion when comparing translated results against direct ODB access via

the quick or fringe plot operations, where reaction moments and rotational displacements are concerned.

The default “invariant” for fringe plots of vector data is “Magnitude”, which is always a positive value.

If the magnitude of the translated vector data is compared against the ODB scalar data, then they will not

always match (all negative data from the ODB access will be flipped positive in the translated plot). To

compare “apples with apples”, one must display the appropriate component (Z from our example) from

the translated case, and compare that against the scalar (key RM3) from the direct ODB access case.

465Chapter 4: Read ResultsKey Differences between Attach and Translate Methods

Reaction Forces

During translation, only non-zero reaction force data is imported. Direct ODB access, on the other hand,

returns zero vectors for any nodes that do not have any reaction forces. This makes no difference for the

display of reaction force vectors; however, if one displays a fringe plot distribution of the reaction forces,

the fringe plots vary between translation and direct ODB access dramatically. The translation plot is all

black, with only the min/max values displayed on a hidden line plot; while the ODB fringe plot shows a

color distribution from the zero values (white over most of the model) to the non-zero values. For the

latter, the contours only vary over elements with nodes having non-zero reaction forces.

Patran Interface to ABAQUS preference GuideDelete Result Attachment Form

466

Delete Result Attachment Form

The following form may be used to remove a results attachment, created via the Attach method, from

the database.

Chapter 5 : Files


5 Files

� Files 468

Patran Interface to ABAQUS Preference GuideFiles

468

Files

There are several files associated which are either used or created by the Patran ABAQUS Application

Preference. The following table describes each file and how it is used. In the definition of the file names,

any occurrence of “jobname” would be replaced with the jobname the user assigns.

File Name Description

jobname.db This is the Patran database from which the model data is read during an

analyze pass, and into which model and⁄or results data is written during

a Read Results pass.

jobname.jbm

jobname.jbr

These are small files used to pass certain information between Patran and

the Application Preference during translation. You should never have

need to do anything directly with these files.

jobname.inp This is the ABAQUS input file created by the interface.

jobname.fil This is the ABAQUS results file which is read by the Read Results pass.

jobname.flat This file may be generated during a Read Results pass. If the results

translation cannot, for any reason, write data directly into the jobname.db

Patran database, it will create this jobname.flat file.

jobname.msg These message files contain any diagnostic output from the translation,

either forward or reverse.

AbaqusExecute This is a UNIX script file which is called on to submit both the forward

PAT3ABA translation program, as well as to submit ABAQUS after

translation is complete. This file should be customized for your

particular site installation.

ResultsSubmit This is another UNIX script which is called on to submit the reverse,

ABAPAT3 translation program. This file should also be customized for

your particular site.

load_abaqus.ses This file is only used when creating a new Patran template database. This

file loads in all the element, material, MPCs and loads and boundary

condition tables for the Patran ABAQUS product.

Chapter 6 : Errors/Warnings

Patran Intreface to ABAQUS Preference Guide

6 Errors/Warnings

� Errors/Warnings 470

Patran Intreface to ABAQUS Preference GuideErrors/Warnings

470

Errors/Warnings

There are several error or warning messages which may be generated by the Patran ABAQUS

Application Preference.

Message Description

Fatal This error stops the translation and exits the Preference.

Warning Some expected action did not execute. Translation continues. Check

the .msg file.

Information General Messages about the translation.

jp`Kc~íáÖìÉ=nìáÅâ=pí~êí=dìáÇÉ

I n dex


få

Ç

É

ñ=

Index

Numerics1D interface, 96, 104, 151

2D interface, 101, 104

2D orthotropic, 81

2D orthotropic lamina, 54

2D solid, 100, 104

3D anisotropic, 56, 84

3D anisotropic thermal, 88

3D interface, 103, 105, 312

3D orthotropic, 55, 82

3D orthotropic thermal, 87

Aabapat3, 4

ABAQUS, 3

abaqus.plb, 4, 5

AbaqusExecute, 468

AbaqusSubmit, 5, 7

acceleration, 334, 340

Acommand, 7

amplitude, 14

analysis, 354

arbitrary beam, 127

area moment I12, 126

average shear stiffness, 254

axisymmetric 2D interface, 279

axisymmetric ISL, 156

axisymmetric shell, 95, 104, 148

laminate, 149

axisymmetric solid, 273

Bbase motion, 15, 388

beam, 28, 32

circular, 122

cross-sectional shape, 122

elements, 16, 17, 18

general section, 11, 117, 125

hexagonal, 122

in space, 93

in XY plane, 92

section, 11

bifurcation buckling, 365, 373, 374

bilinear, 28, 36

boundary, 14, 15

box beam, 119

buckle, 15

CC biquad, 29, 39

cap

hardening, 13, 78

plasticity, 13

centrifugal force, 339

centroid, 11

centroid coordinate, 126

CETOL, 418

CFLUX, 15

change material status, 52

circular beam, 122

solid, 122

clearance zero damping, 114, 117, 153

clearance zero-pressure, 114, 117, 153

CLOAD, 15

combined creep test data, 71

combined test data, 13

composite, 56, 88, 319

conductivity, 13

constitutive models, 52

control, 104

convection, 104, 334, 348

convection/diffusion, 320, 323


472

coordinate frames, 22

Coriolis force, 339

correlation, 15

creep, 13, 54, 55, 56, 79, 80, 367, 417, 418

creep test data, 71

cubic hybrid, 92, 93

cubic initially straight, 93

cubic interpolation, 92, 93

curved pipe, 130

Ddamper, 94

damping, 13

direct, 387

Rayleigh, 388

zero clearance, 114, 117, 153

dashpot, 12

elements, 19

DASHPOT1, 110

DASHPOT2, 142, 144

DASHPOTA, 141, 143

deformation plasticity, 13, 54, 73

degree-of-freedom, 30

density, 13, 67, 88

DFLUX, 15

diffusion, 104

direct linear transient, 365, 376, 377

direct steady state dynamics, 365, 380

direct text input, 360, 363

dispersion, 104

displacement, 334, 337

DLOAD, 15

Drucker-Prager, 13, 77

dynamic, 15

Eeigenvalue, 364

eigenvalue buckling, 365

EL

file, 16, 362

print, 16, 362

elastic, 13, 53, 54, 55, 56, 58, 81, 82, 83

elastic slip, 113, 116, 152, 154, 157, 160, 162,

165, 168, 170, 278, 280, 282, 314

hard contact, 92

no separation, 92

soft contact, 92

vis damping, 92

vis damping no separation, 92

elbow, 29, 42

elements, 19

MPC, 42

ELBOW31, 42, 130

ELBOW31B, 130

ELBOW32, 42, 130

element, 11, 25

definition, 11

matrix output, 16, 362

properties, 90

elements

beam, 16, 17, 18

dashpot, 19

elbow, 19

gap, 20

heat transfer, 20, 21

mass, 19

membrane, 18

rigid surface contact, 20

rotary inertia, 19

shell, 19

slide line contact, 20

small sliding contact, 20

spring, 19

ELSET, 11, 352

end step, 15

energy

file, 16, 362

print, 16, 362

engineering constants, 82

equation, 14, 28, 31

expansion, 13, 67

explicit, 28

Ffatal, 470

473INDEX

file

EL, 16, 362

energy, 16, 362

format, 16, 362

modal, 16, 362

node, 16, 362

output definition, 16

film, 15

finite elements, 23

flat file results, 456

force, 334, 337

Frac Clearance Const Damping, 114, 117, 153

fraction of critical damping, 59

frequency, 15, 394

friction, 12, 112

Friction in Dir_1, 113, 116

Friction in Dir_2, 116

Ggap, 12, 95

conductance, 12, 317, 324

cylindrical, 145

elements, 20

radiation, 12, 317, 324

spherical, 147

uniaxial, 145

GAPCYL, 146

GAPSPHER, 147

GAPUNI, 146

general beam, 117, 124

general large strain, 266

general thick, 262

general thick shell

laminated, 264

general thin, 258

general thin shell

laminated, 261

gravity loads, 339

grounded damper, 92

grounded spring, 92

group, 352

HHAFTOL, 412, 413

hard contact, 114, 117, 153, 155, 158, 160, 163,

166, 169, 171, 278, 281, 283, 314

harmonic loading, 365

heat flux, 334, 349

heat source, 334, 349

heat transfer, 15

elements, 20, 21

hexagonal beam, 122

Hilber-Hughes-Taylor operator, 365

host, 7

hourglass stiffness, 12, 255

bending, 254, 257, 260, 263, 266, 269

membrane, 254, 257, 260, 263, 266, 269

normal, 254, 257, 260, 263, 266, 269

hybrid, 92, 93, 100, 269, 310

integration, 100

modes, 100

hyperbolic, 80

hyperelastic, 13, 53, 60, 61, 62, 63, 64, 65, 66,

68

hyperfoam, 13, 67

Iimport input file, 433

incompatible modes, 100, 269, 270, 272, 273,

274, 310

inertia

rotary, 12

inertial load, 334, 339

information, 470

initial conditions, 14

initial temperature, 334, 350

initial velocity, 334, 339

input data, 334

interface, 12, 112

IRS, 97, 102, 112, 115

axisymmetric, 167

beam/pipe, 169

planar, 164

shell/solid, 281

single node, 92

IRS12, 112

IRS13, 115

I-section, 123

ISL, 96, 97


474

isotropic, 53, 58, 75

thermal, 86

Jjobname.db, 468

Kkinematic, 76

constraints, 14

LLagrange

hard contact, 92

no separation, 92

soft contact, 92

vis damping, 92

vis damping no separation, 92

Lamina, 81

laminate, 56, 89

large strain, 265

latent heat, 13

linear, 28, 34

linear damper, 109, 141, 142

grounded, 109

linear spring, 108, 137, 138

grounded, 108

linear static, 364, 368, 369

linear surf-surf, 28

linear surf-surf MPC, 34

linear surf-vol, 28

linear surf-vol MPC, 34, 35

linear vol-vol, 28

linear vol-vol MPC, 36

link, 28, 33, 104

load cases, 351, 362

loading definition, 15

loads and boundary conditions, 332

L-section beam, 132

Mmass, 12, 92, 106

elements, 19

mass proportional damping, 59

material, 13

change status, 52

definition, 13

orientation, 14

temperature dependent, 53

materials, 51

form, 52

maximum friction stress, 114, 117, 152

maximum negative pressure, 114, 117, 153

maximum overclosure, 114, 117, 153

membrane, 101, 275

elements, 18

Mises/Hill, 74, 75, 76

modal

damping, 15

dynamic, 15

file, 16, 362

print, 16, 362

steady state dynamics, 365

modal linear transient, 365, 383, 384

modified Drucker-Prager/Cap, 78

Moony Rivlin, 62

MPC, 14

elbow, 42

explicit, 31

linear surf-surf, 34

linear surf-vol, 34, 35

linear vol-vol, 36

pin, 43

quad surf-surf, 37

quad surf-vol, 37, 38

quad vol-vol, 39

revolute, 44

rigid fixed, 32

rigid pinned, 33

slider, 40

SS bilinear, 48

SS linear, 47

SSF bilinear, 49

tie, 43

universal, 47

V Local, 46

multi-point constraints, 27

Nnatural frequency, 364, 371

475INDEX

Neo Hookean, 62

Newton’s method, 366

no compression, 13

no sliding contact, 114, 117, 153

no tension, 13

node, 11, 23

definition, 11

file, 16, 362

print, 16, 362

nondeterministic continuous excitation, 366

nonlinear damper, 110, 143, 144

grounded, 110

nonlinear spring, 109, 139, 140

grounded, 109

nonlinear static, 366, 407, 409

nonlinear transient dynamic, 367, 412, 414

NSET, 11, 23, 352

Oobject tables, 336

Ogden, 60, 61, 63, 64, 66, 68

open beam, 134

optional controls, 359

orientation, 14, 22, 89

system, 253

output requests, 362

Pparallel ISL, 158

pat3aba, 4

peak response, 366

perfect plasticity, 74

pin, 43

pin MPC, 43

pipe beam, 123

planar

2D interface, 277

ISL, 153

test data, 13

plane strain, 269, 270

plane stress, 272

plastic, 13, 54, 55, 56, 74, 75, 76, 77, 78

point mass, 106

Poisson parameter, 118, 121, 126, 128, 133,

136

Poisson’s ratio, 67

polynomial, 60, 62, 63, 65

potential, 13

power spectral density, 403

preferences, 10

analysis, 10

preprint, 16

prescribed boundary conditions, 15

pressure, 334, 337

pressure zero clearance, 114, 117, 153

pre-tension, 347

print, 16, 362

definition, 16

EL, 16, 362

energy, 16, 362

modal, 16, 362

node, 16, 362

procedure definition, 15

Prony, 70, 367

property definition, 11

PSD-Definition, 14

Qquad surf-surf, 29

quad surf-surf MPC, 37

quad surf-vol, 29

quad surf-vol MPC, 37, 38

quad vol-vol, 29

quad vol-vol MPC, 39

quadratic, 29, 37

Rradial ISL, 161

random response, 15

random vibration, 366, 402, 403, 404

rate dependent, 13

read input file, 433

read results, 454, 455

read temperature file, 368

rebar 2D, 285

rectangular beam, 124

reduced integration, 100, 269, 270, 272, 273,

274, 275, 310

reference temperature, 59

relaxation test data, 72


476

response spectrum, 15, 366, 394, 395, 396, 397

restart, 14

restart parameters, 358

results file

select, 458

ResultsSubmit, 5, 468

revolute, 29, 44

revolute MPC, 44

rigid

fixed, 28

pinned, 28

rigid fixed MPC, 32

rigid line, 98

LBC, 175

rigid pinned MPC, 33

rigid surf, 98, 102

rigid surface, 11, 112, 115, 165, 167, 170, 171,

172, 174, 175, 281, 283

axisymmetric, 173

Bezier 2D, 174

Bezier 3D, 283

cylindrical, 172

LBC, 284

segments, 171

rigid surface contact

elements, 20

ROTARI, 107

rotary inertia, 12, 92, 107

elements, 19

rough (no slip) friction, 114, 117, 153, 155, 158,

160, 163, 166, 169, 278, 281, 283, 314

rough parameter, 171

SScratchdir, 7

section point coordinate, 126

shear centroid coordinate, 126

shear factor, 118, 121, 126, 129, 134, 136

shear test data, 13

shell, 100, 104

elements, 19

general section, 12, 262

section, 12, 255

simple shear test data, 14

slide line, 11, 97, 163

slide line contact

elements, 20

slider, 29, 40

slider MPC, 40

sliding friction, 113, 154, 157, 159, 162, 165,

168, 170, 282

slip tolerance, 113, 116, 152

small sliding contact

elements, 20

soft contact, 114, 117, 153, 155, 158, 160, 163,

166, 169, 171, 278, 280, 283, 314

solid, 103, 105, 310

solid section, 12

solution types, 364

specific heat, 14, 88

spectrum, 14

spring, 12, 94

elements, 19

SPRING1, 108, 109

SPRING2, 138, 140

SPRINGA, 137, 139

SS bilinear, 29, 30, 38, 48

SS bilinear MPC, 48

SS linear, 28, 30, 35, 47

SS linear MPC, 47

SSF bilinear, 30, 49

SSF bilinear MPC, 49

standard formulation, 92, 93, 100, 104

static, 15, 334

steady state dynamics, 15, 389, 390

steady state heat transfer, 367, 428

steady state response, 365

step, 15

creation, 361

initialization, 15

selection, 432

termination, 15

stiffness

hourglass, 12

transverse shear, 13

stiffness in stick, 113, 117, 152

stiffness proportional damping, 59

strain, 79

surface contact, 12, 279

477INDEX

Ttabular formula, 69

tangent elastic moduli, 364

TAUMAX, 152, 155, 158, 160, 163, 166, 169,

171, 278, 280, 283, 314

temperature, 15, 334, 338

thermal, 334, 348

temperature dependent material, 53

test data

combined, 13

creep, 71

creep combined, 71

Ogden, 66

planar, 13

relaxation, 72

shear, 13

simple shear, 14

uniaxial, 14

volumetric, 14

thermal 1D interface, 317

thermal axisymmetric shell, 315

laminated, 316

thermal expansion coefficient, 59, 67

thermal interface

planar, 321

solid, 324

thermal link, 314

thermal planar solid, 320

thermal shell, 318

laminated, 319

thermal solid, 323

thermal strain, 59

thick shell, 255

laminated, 257

thin shell, 252

laminated, 254

tie, 29, 43

tie MPC, 43

time, 79

time dependent loading, 365

torsional constant, 126, 135

transform, 11, 22

transient, 335

transient heat transfer, 367, 430

translation parameters, 357, 457

transverse shear stiffness, 13, 122, 125, 127

trapezoid beam, 124

true distance, 95

truss, 94, 136

Uuniaxial test data, 14

universal, 30, 47

universal MPC, 47

VV Local, 29, 46

V Local MPC, 46

velocity, 334, 340

VISCO, 15, 417

viscoelastic, 14, 54, 55, 56, 69, 70, 71, 72

frequency domain, 367, 425

time domain, 367, 421, 422

volumetric pressure, 67

volumetric test data, 14, 67

Wwarning, 470

warping constant, 136

wavefront minimization, 14

XXY plane

definition, 126, 128

Yyield, 14


478

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