NX Nastran 12 Release Guide

SIEMENS

Contents

Proprietary & Restricted Rights Notice ...... 9

NX Nastran 12 summary of changes ...... 1-1 NX Nastran 12 summary of changes to default settings and inputs ...... 1-1

Dynamics ...... 2-1 Support for Simcenter Motion ...... 2-1 Random analysis control enhancement ...... 2-27 Random analysis output enhancement ...... 2-30 RESVALT parameter removed ...... 2-30 Direct-input, frequency-dependent components ...... 2-30 Output transformation matrices for frequency response analysis ...... 2-44

Acoustics ...... 3-1 Finite Element Method Adaptive Order (FEMAO) ...... 3-1 Acoustics case control command ...... 3-10 Monopole, dipole, and plane wave acoustic sources ...... 3-12 Enforced acoustic pressure with complex data input ...... 3-22 Boundary conditions ...... 3-25 Acoustic materials with complex properties ...... 3-35 Acoustic pressure results ...... 3-37 Support for random acoustic analysis ...... 3-46 Incident and transmitted acoustic power and acoustic power transmission loss results output . . 3-47 Usability improvement for panel and grid contributions ...... 3-59 Acoustic transfer vectors ...... 3-65 Output format for acoustic intensity and acoustic velocity results ...... 3-69

Superelements ...... 4-1 Frequency-dependent external superelements for frequency response analysis ...... 4-1 PVT0 data block in superelement OP2 files ...... 4-12

Multi-step nonlinear solution 401 ...... 5-1 Shell element support ...... 5-1 Bar and beam element support ...... 5-4 Spring and bushing element support ...... 5-5 Nonlinear buckling ...... 5-7 Bolt preload improvements for SOL 401 ...... 5-23 Balanced initial stress-strain ...... 5-30 Contact improvements ...... 5-42 Stress output coordinate system ...... 5-43 Progressive failure analysis ...... 5-44

NX Nastran 12 Release Guide 3 CoContentsntents

User defined material improvements ...... 5-58

Multi-step nonlinear kinematics solution 402 ...... 6-1 Multi-step nonlinear kinematics SOL 402 ...... 6-1 Fourier harmonic solution in SOL 402 ...... 6-14 Cyclic symmetric in SOL 402 ...... 6-16 SOL 402 vs SOL 401 comparison ...... 6-17 SOL 402 .f06 results file ...... 6-18 Linearized buckling solution in SOL 402 ...... 6-20

Performance ...... 7-1 Performance improvements ...... 7-1

Bolt preload ...... 8-1 Bolt preload improvements for linear solutions ...... 8-1

Memory allocation for external applications ...... 9-1 Memory allocation for external applications ...... 9-1

Topology Optimization ...... 10-1 Topology Optimization ...... 10-1

Monitor points ...... 11-1 Monitor points for element results and grid point forces ...... 11-1 Monitor points example ...... 11-32

Miscellaneous ...... 12-1 HDF5 format output files ...... 12-1 Visualization elements ...... 12-2 Separate mechanical and thermal strain ...... 12-11 Modal stress calculation when TEMPERATURE(LOAD) is specified ...... 12-12 P-elements in SOL 200 ...... 12-12

Documentation changes ...... 13-1 Removing documentation for legacy acoustic absorber and barrier elements ...... 13-1 Removing documentation for the legacy VECTOR case control command ...... 13-1

Upward compatibility ...... 14-1 Updated data blocks ...... 14-1 CASECC ...... 14-1 CONTACT ...... 14-5 DIT ...... 14-7 DSCMCOL ...... 14-8 DYNAMIC ...... 14-8 EDOM ...... 14-15 EDT ...... 14-21

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ELRSCALV ...... 14-22 EPT ...... 14-23 EPT705 ...... 14-25 GEOM1 ...... 14-26 GEOM2 ...... 14-27 GEOM3 ...... 14-30 GEOM4 ...... 14-35 LAMA ...... 14-35 MPT ...... 14-36 OACCQ ...... 14-40 OACINT ...... 14-41 OACPWR ...... 14-42 OACVELO ...... 14-43 OBC ...... 14-44 OBOLT ...... 14-46 OBG ...... 14-47 OCKGAP1 ...... 14-47 ODAMGCZD ...... 14-48 ODAMGCZR ...... 14-49 ODAMGCZT ...... 14-51 ODAMGPFD ...... 14-52 ODAMGPFE ...... 14-55 ODAMGPFS ...... 14-56 OEE ...... 14-57 OEF ...... 14-58 OERR ...... 14-84 OES ...... 14-84 OGF ...... 14-140 OJINT ...... 14-148 OPG ...... 14-149 OPRESS ...... 14-149 OQG ...... 14-150 OSHT ...... 14-153 OSLIDE ...... 14-154 OSPDS ...... 14-154 OTEMP ...... 14-156 OUG ...... 14-156 OUGGC ...... 14-157 OUGPC ...... 14-157 OUGRC ...... 14-158 OUMAT ...... 14-158 R1TAB ...... 14-161 New data blocks ...... 14-161 ATVMAP ...... 14-161 OACPWRI ...... 14-162 OACPWRT ...... 14-164 OACTRLS ...... 14-166 OBCKL ...... 14-167 OCONST ...... 14-168

NX Nastran 12 Release Guide 5 CoContentsntents

ODAMGPFR ...... 14-172 OEFMXORD ...... 14-174 ONMD ...... 14-175 TRMBD ...... 14-177 TRMBU ...... 14-178 Updated modules ...... 14-180 ADDVM ...... 14-180 BOLTFOR ...... 14-180 CNTMAPTR ...... 14-181 CNTSTAT ...... 14-181 CONSTF ...... 14-182 CONTOUT ...... 14-182 DOM9 ...... 14-183 DOM10 ...... 14-183 DOM12 ...... 14-184 DOPR1 ...... 14-185 DPD ...... 14-187 ELTPRT ...... 14-187 EMAAC ...... 14-188 EMG ...... 14-188 FOCOEL ...... 14-188 FONOTR ...... 14-189 FRRD1 ...... 14-189 GP1 ...... 14-189 GP3 ...... 14-190 GPAC ...... 14-190 GPFDR ...... 14-190 IFP1 ...... 14-191 INITSNCR ...... 14-191 LAMX ...... 14-191 MATMOD ...... 14-192 MODACC ...... 14-199 MODUSETF ...... 14-199 MPPARV ...... 14-199 MPPOST ...... 14-200 MPPRESS ...... 14-200 NLTRD3 ...... 14-201 OUTPRT ...... 14-203 RANDOM ...... 14-207 SDR2 ...... 14-208 SELA ...... 14-209 SEMA ...... 14-210 SSG1 ...... 14-210 TA1 ...... 14-210 TRLG ...... 14-211 UPGLSTF ...... 14-211 XSELOADS ...... 14-211 XYTRAN ...... 14-212 New modules ...... 14-213

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ACPRESS ...... 14-213 ATVGP ...... 14-213 ATVPARTV ...... 14-214 ATVPOST ...... 14-215 DAYTIM ...... 14-216 DOM13 ...... 14-216 DPDAC ...... 14-217 DSADJC ...... 14-218 EULAN ...... 14-218 FEMAOAC ...... 14-219 FEMAOPRE ...... 14-221 FEMAOPST ...... 14-223 FFREST1 ...... 14-224 FFREST2 ...... 14-225 FFREST3 ...... 14-225 FRFIN ...... 14-226 FRLGAC ...... 14-230 FTCHGM2 ...... 14-231 GPACAO ...... 14-232 MFRQADD ...... 14-233 MODEQEXN ...... 14-234 MODGMATV ...... 14-234 MONEGRP3 ...... 14-236 MONPNT2 ...... 14-237 MONVEC3 ...... 14-237 MPP3 ...... 14-238 TOTLOAD ...... 14-239 TRLOSS ...... 14-240 TRLPSD ...... 14-241

Problem Report (PR) fixes ...... 15-1 Problem Report (PR) fixes ...... 15-1

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Proprietary & Restricted Rights Notice

© 2017 Siemens Product Lifecycle Management Software Inc. All Rights Reserved. This software and related documentation are proprietary to Siemens Product Lifecycle Management Software Inc. Siemens and the Siemens logo are registered trademarks of Siemens AG. Simcenter is a trademark or registered trademark of Siemens Product Lifecycle Management Software Inc. or its subsidiaries in the United States and in other countries. NASTRAN is a registered trademark of the National Aeronautics and Space Administration. NX Nastran is an enhanced proprietary version developed and maintained by Siemens Product Lifecycle Management Software Inc. MSC is a registered trademark of MSC.Software Corporation. MSC.Nastran and MSC.Patran are trademarks of MSC.Software Corporation. All other trademarks are the property of their respective owners. TAUCS Copyright and License TAUCS Version 2.0, November 29, 2001. Copyright (c) 2001, 2002, 2003 by Sivan Toledo, Tel-Aviv University, [email protected]. All Rights Reserved. TAUCS License: Your use or distribution of TAUCS or any derivative code implies that you agree to this License. THIS MATERIAL IS PROVIDED AS IS, WITH ABSOLUTELY NO WARRANTY EXPRESSED OR IMPLIED. ANY USE IS AT YOUR OWN RISK. Permission is hereby granted to use or copy this program, provided that the Copyright, this License, and the Availability of the original version is retained on all copies. User documentation of any code that uses this code or any derivative code must cite the Copyright, this License, the Availability note, and "Used by permission." If this code or any derivative code is accessible from within MATLAB, then typing "help taucs" must cite the Copyright, and "type taucs" must also cite this License and the Availability note. Permission to modify the code and to distribute modified code is granted, provided the Copyright, this License, and the Availability note are retained, and a notice that the code was modified is included. This software is provided to you free of charge. Availability (TAUCS) As of version 2.1, we distribute the code in 4 formats: zip and tarred-gzipped (tgz), with or without binaries for external libraries. The bundled external libraries should allow you to build the test programs on Linux, Windows, and MacOS X without installing additional software. We recommend that you download the full distributions, and then perhaps replace the bundled libraries by higher performance ones (e.g., with a BLAS library that is specifically optimized for your machine). If you want to conserve bandwidth and you want to install the required libraries yourself, download the lean distributions. The zip and tgz files are identical, except that on Linux, Unix, and MacOS, unpacking the tgz file ensures that the configure script is marked as executable (unpack with tar zxvpf), otherwise you will have to change its permissions manually.

NX Nastran 12 Release Guide 9 PrProprietaryoprietary & R&eRestrictedstricted RigRightshts NotNoticeice

HDF5 (Hierarchical Data Format 5) Software Library and Utilities Copyright 2006-2016 by The HDF Group NCSA HDF5 (Hierarchical Data Format 5) Software Library and Utilities Copyright 1998-2006 by the Board of Trustees of the University of Illinois. All rights reserved. Redistribution and use in source and binary forms, with or without modification, are permitted for any purpose (including commercial purposes) provided that the following conditions are met: 1. Redistributions of source code must retain the above copyright notice, this list of conditions, and the following disclaimer.

2. Redistributions in binary form must reproduce the above copyright notice, this list of conditions, and the following disclaimer in the documentation and/or materials provided with the distribution.

3. In addition, redistributions of modified forms of the source or binary code must carry prominent notices stating that the original code was changed and the date of the change.

4. All publications or advertising materials mentioning features or use of this software are asked, but not required, to acknowledge that it was developed by The HDF Group and by the National Center for Supercomputing Applications at the University of Illinois at Urbana-Champaign and credit the contributors.

5. Neither the name of The HDF Group, the name of the University, nor the name of any Contributor may be used to endorse or promote products derived from this software without specific prior written permission from The HDF Group, the University, or the Contributor, respectively.

DISCLAIMER: THIS SOFTWARE IS PROVIDED BY THE HDF GROUP AND THE CONTRIBUTORS "AS IS" WITH NO WARRANTY OF ANY KIND, EITHER EXPRESSED OR IMPLIED. In no event shall The HDF Group or the Contributors be liable for any damages suffered by the users arising out of the use of this software, even if advised of the possibility of such damage

10 NX Nastran 12 Release Guide Chapter 1: NX Nastran 12 summary of changes

NX Nastran 12 summary of changes to default settings and inputs

Default setting changes

Note The following table lists changes to default settings that may produce differences in results between NX Nastran 11 and NX Nastran 12. Default setting changes that produce additional output only are not included in this table.

Input type Default change Keywords None Nastran statement None File management None statements Executive control None statements Case control The default for the interface file request describer on the MBDEXPORT case commands control command has changed from RECURDYN to SCMOTION. The default for the MPCZERO parameter has changed from 1.0E-11 to Parameters 1.0E-7. The default for the AUTO parameter on the NXSTRAT entry has changed Bulk entries from 0 to 1.

Keyword changes

Keyword Keyword description Description of change Activates the Padé via Lanczos krylov New keyword method in SOL 108.

Nastran statement changes System System cell System cell description Description of change cell name Defines the number of rows that are Update of the computer-dependent 205 simultaneously updated during a default rank value sparse symmetric decomposition.

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System System cell System cell description Description of change cell name In SOL 401, defines the output coordinate system for the 3D solids elements CTETRA, CHEXA, CPENTA and CPYRAM elements, 627 New system cell the plane strain elements CPLSTN3, CPLSTN4, CPLSTN6, CPLSTN8, and the plane stress elements CPLSTS3, CPLSTS4, CPLSTS6, CPLSTS8. Determines the case control 640 PRESOUT command to be used for acoustic New system cell pressure output at fluid grids. Controls whether the GDSTAT parallel 649 New system cell solution is used in SOL 401. Controls whether the results are written to an HDF5 format output file 653 New system cell in addition to an OP2 format output file. Turns off the computation of the CBUSH coupling moments which are computed when the connecting grid 665 BSHDCPL New system cell points are not coincident. Applies to all solutions except for SOLs 402, 601, and 701. Activates the Pade via Lanczos 679 KRYLOV New system cell method in SOL 108. Specifies the modulus of elasticity that 687 is used for rigid Lagrange elements New system cell in a model. Controls the number of warning or error messages from temperature 698 New system cell processing from the GP3 module printed to the .f06 file.

File management statement changes

No changes to file management statements.

Executive control statement changes

No changes to executive control statements.

Case control command changes Case control Case control command description Description of change command Added remark on results recovery ACCELERATION Acceleration output request for points on frequency-dependent external superelements. ACINTENSITY Acoustic intensity output Added SORT2 option.

1-2 NX Nastran 12 Release Guide NX Nastran 12 summary of changes

Case control Case control command description Description of change command Added options for random analysis ACPOWER Acoustic power output results. ACVELOCITY Acoustic velocity output Added SORT2 option. ALOAD Acoustic load set selection New case control command Acoustic transfer vector (ATV) ATVOUT New case control command creation specification Added remark on results recovery for points on frequency-dependent external superelements. DISPLACEMENT Displacement output request Added remark that pressure results are separated from the displacement results. Frequency-dependent frequency FRFIN New case control command response function matrix input Frequency-dependent external FRFOUT New case control command superelement creation specification GRDCON Acoustic grid contribution request New case control command Selects grid point imperfections in IMPERF New case control command SOL 401 Selects an initial stress or strain set or INITS New case control command an offset strain set for SOL 401 INPOWER Incident acoustic power output New case control command The Simcenter Motion solver is Creates interface file for multibody now supported and the default for MBDEXPORT and control system software during a the interface file request describer SOL 103, 111, or 112 run. has changed from RECURDYN to SCMOTION. MONITOR Print selection for monitor data New case control command Requests nonlinear buckling in SOL NLARCL New case control command 401 OTMFORC OTM force and moment output New case control command Eliminated the ability to request grid PANCON Acoustic panel contribution request contributions. By default, DISPLACEMENT case control command can no longer PRESSURE Pressure output request output pressure results. The modified PRESSURE case control command needs to be used. SETMC Modal contribution set definition Added PRESSURE response type. Acoustic power transmission loss TRLOSS New case control command output TRPOWER Transmitted acoustic power output New case control command VECTOR Displacement output request Undocumented Added remark on results recovery VELOCITY Velocity output request for points on frequency-dependent external superelements.

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Parameter changes

Parameter Parameter description Description of change For SOL 200 topology optimization, defines the number of design cycles BDMNCON in which the software will delay the New parameter application of any manufacturing constraints. Controls whether the stiffness and damping that the software uses for CBEAR elements is the stiffness and BRSYMFAC damping defined on PBEAR bulk New parameter entries or symmetrized versions of the stiffness and damping defined on PBEAR bulk entries. Selects the inversion method that FLEXINV the software uses when it inverts New parameter FRFFLEX bulk entry data. Determines whether the contribution of the residual vector modes to RESVALT Undocumented the dynamic physical response is considered.

Degree-of-freedom set changes

No changes to degree-of-freedom sets.

Bulk entry changes

Bulk entry Bulk entry description Description of change User specified order adaptation rule ACADAPT for acoustics FEM adaptive order New bulk entry solution User specified order for acoustics ACORDER New bulk entry FEM adaptive order solution ACPLNW Acoustic plane wave source New bulk entry ACPNVEL Acoustic panel normal velocity New bulk entry ACPOLE1 Acoustic monopole source New bulk entry ACPOLE2 Acoustic dipole source New bulk entry ACPRESS Enforced pressure value on grids New bulk entry ACTRAD Acoustic transfer admittance New bulk entry Acoustic load combination with unit ALOAD New bulk entry scale factors Selects acoustic transfer vector (ATV) ATVBULK New bulk entry results for an ATV system run Coupling interface definition for an ATVFS New bulk entry acoustic transfer vector (ATV)

1-4 NX Nastran 12 Release Guide NX Nastran 12 summary of changes

Bulk entry Bulk entry description Description of change The following new parameters have been added to the BCTPARM bulk Control parameters for the contact BCTPARM entry for SOL 401: IPENRAMP, algorithm INTRFC, CTDAMP, CTDAMPN, CTDAMPT, and GAPVAL. CHACAB Acoustic absorber element connection Undocumented CHACBR Acoustic barrier element connection Undocumented Defines a manufacturing condition for DMNCON New bulk entry SOL 200 topology optimization. Defines a lattice type for SOL 200 DMRLAW New bulk entry topology optimization. For topology optimization, the Defines a set of structural responses DRESP1 now includes a compliance that are used for the objective and/or DRESP1 response type. It is defined by design constraints, or for sensitivity including CMPLNCE in the RTYPE analysis purposes field. Selects the elements to be included in DVTREL1 New bulk entry a SOL 200 topology optimization. Direct input of frequency-dependent FRFFLEX New bulk entry dynamic flexibility matrix at points Assigns output type to FRFOTM FRFOMAP New bulk entry results Direct input of frequency-dependent FRFOTM dynamic output transformation matrix New bulk entry at points Direct input of frequency-dependent FRFSTIF New bulk entry dynamic stiffness matrix at points Defines grid point imperfections in IMPERF New bulk entry SOL 401 Combines multiple IMPERF bulk IMPRADD New bulk entry entries in SOL 401 The defaults for the RHO, C, GAMMA, PR, MU, RES, POR, L1, and L2 fields change from "0.0" to "no default". The default for the TORT field changes from "0.0" to "1.0". The input for the RHO, C, GAMMA, Defines material properties for porous MATPOR PR, MU, L1, and L2 fields change materials used as acoustic absorbers from "REAL" to "REAL > 0.0". The input for the RES field changes from "REAL" to "REAL ≥ 0.0". The input for the TORT field changes from "REAL" to "REAL ≥ 1.0". The input for the POR field changes from "REAL" to "0.0 < REAL ≤ 1.0".

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Bulk entry Bulk entry description Description of change Defines constant or nominal material properties for fluid or absorber MAT10C New bulk entry elements in coupled fluid-structural analysis Defines tabular material properties for MATF10C fluid or absorber elements in coupled New bulk entry fluid-structural analysis Integrated load monitor point - MONPNT2 New bulk entry element monitor output results item Integrated load monitor point - sums MONPNT3 New bulk entry grid point forces Defines control parameters for SOL NLARCL New bulk entry 401 nonlinear buckling For SOL 401, the following new Defines solution control parameters NLCNTL parameters have been added to the for SOL 401 NLCNTL bulk entry: MSTAB, MSFAC The following new parameters Defines parameters for solution have been added to the NXSTRAT NXSTRAT control and strategy in advanced bulk entry: ATSNSUB, ATSMASS, nonlinear structural analysis TETINT, DIAGSOL, BOLTDAMP, TFSHIFT Acoustic Impedance/Admittance PAABSF1 New bulk entry Element Property PACABS Acoustic absorber property Undocumented PACBAR Acoustic barrier property Undocumented Property of acoustic transfer PACTRAD New bulk entry admittance Property entry to define a composite property which allows for a different PCOMPG1 New bulk entry failure theory for each layer. SOLs 401 and 402 only Triangular visualization element with PLOTEL3 New bulk entry three grid points Quadrilateral visualization element PLOTEL4 New bulk entry with four grid points Triangular visualization element with PLOTEL6 New bulk entry six grid points Quadrilateral visualization element PLOTEL8 New bulk entry with eight grid points Six-sided hexahedron visualization PLOTHEX element with eight to twenty grid New bulk entry points Five-sided pentahedron visualization PLOTPEN New bulk entry element with six to fifteen grid points Five-sided pyramid visualization PLOTPYR element with five to thirteen grid New bulk entry points Four-sided tetrahedron visualization PLOTTET New bulk entry element with four to ten grid points

1-6 NX Nastran 12 Release Guide NX Nastran 12 summary of changes

Bulk entry Bulk entry description Description of change SEBULK Partitional superelement connection Added the TYPE = "FRFOP2" option For progressive ply failure with the UD damage model in SOL 401, TABLEM5 TABLEM5 is optionally used to define a nonlinear New bulk entry function relating the shear damage (d12) to the thermodynamic force (Y)

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Chapter 2: Dynamics

Support for Simcenter Motion

Now you can generate flexible body data during an NX Nastran SOL 103 run and write it to an OP2 file that is formatted for the Simcenter Motion to read. This capability is similar to the existing capability to write interface files for ADAMS, RecurDyn, and SIMPACK. You use the MBDEXPORT case control command to request that NX Nastran write an interface file for all four of the motion applications. However, some notable differences exist. • For ADAMS, RecurDyn and SIMPACK, NX Nastran can write interface files from a SOL 103, 111, or 112 run. For the Simcenter Motion, NX Nastran can write the interface file from a SOL 103 run only.

• For ADAMS, RecurDyn and SIMPACK, you must include a DTI,UNITS bulk entry in the NX Nastran input file to explicitly define the units. For the Simcenter Motion, because the entire analysis occurs within Pre/Post, this is not necessary.

• Results recovery is supported only for ADAMS and RecurDyn.

• Writing grid point stress and strain data to the interface file is only supported for ADAMS and RecurDyn.

For more information, see the updated MBDEXPORT case control command and “Multi-body Dynamics and Control System Software Interfaces” in the NX Nastran Advanced Dynamic Analysis User’s Guide.

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MBDEXPORT

Multibody Dynamics Export

Creates interface file for multibody dynamics and control system software.

FORMAT:

EXAMPLES: MBDEXPORT SCMOTION FLEXBODY=YES FLEXONLY=NO MBDEXPORT ADAMS STANDARD FLEXBODY=YES FLEXONLY=NO MINVAR=FULL MBDEXPORT OP4=22 STANDARD FLEXBODY=YES MBDEXPORT OP4=22 STATESPACE FLEXBODY=YES MBDEXPORT MATLAB STANDARD FLEXBODY=YES MBDEXPORT MATLAB STATESPACE FLEXBODY=YES

INTERFACE FILE REQUEST DESCRIBERS:

Describer Interface file

SCMOTION Output Simcenter Motion solver OP2 file. (Default)

RECURDYN Output RecurDyn Flex Input (RFI) file.

ADAMS Output ADAMS Interface Modal Neutral File (MNF).

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Describer Interface file

SIMPACK Output SIMPACK Flexible Body Input (FBI) file.

OP4 Output OP4 file.

unit The OP4 file is written to the specified logical unit number. (Integer ≠ 0) If unit > 0, matrices are written to the OP4 file in sparse format. If unit < 0, matrices are written to the OP4 file in full matrix format. The absolute value of the logical unit number must match the unit number on an ASSIGN statement.

MATLAB Output MATLAB script file.

OTHER DESCRIBERS:

Describer Meaning

STANDARD Matrices are based on the second-order representation of the equation of motion. (Default)

STATESPACE Matrices are based on first-order representation of the equation of motion. Valid only when the OP4 or MATLAB interface file request describer is specified.

FLEXBODY Controls whether the interface file is output. Specification of the FLEXBODY describer is required.

NO NX Nastran solution without output of the interface file. (Default)

YES NX Nastran solution with output of the interface file.

FLEXONLY Controls whether the DMAP solution and data recovery occurs after the interface file is output.

YES Interface file output only. (Default)

NO Interface file output and DMAP solution and data recovery.

MINVAR Controls how mass invariants are computed. Valid only when the RECURDYN or ADAMS interface file request describers are specified.

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Describer Meaning

PARTIAL Mass invariants 6 and 8 are not computed when the RECURDYN interface file request describer is specified. (Default) Mass invariants 5 and 9 are not computed when the ADAMS interface file request describer is specified. (Default)

CONSTANT Mass invariants 1, 2, 3, and 8 are computed when the RECURDYN interface file request describer is specified. Mass invariants 1, 2, 6, and 7 are computed when the ADAMS interface file request describer is specified.

FULL All mass invariants are computed.

NONE No mass invariants are computed.

PSETID When the SCMOTION interface file request describer is specified, selects a set of elements that are exported to the OP2 file along with the grids that define their connectivity. The set of elements is defined in the OUTPUT(PLOT) section (including PLOTEL) of the NX Nastran input file. When the RECURDYN or SIMPACK interface file request describer is specified, selects a set of elements that is exported to the interface file. The set of elements is defined in the OUTPUT(PLOT) section (including PLOTEL) of the NX Nastran input file. When the ADAMS interface file request describer is specified, selects a set of elements whose connectivity is exported to face geometry. The set of elements is defined in the OUTPUT(PLOT) section (including PLOTEL) of the NX Nastran input file or on an ADAMS sketch file. Not valid when the OP4 or MATLAB interface file request describers are specified.

NONE Export all grids, geometry and associated modal data. (Default)

setid Export face geometry for elements included in the SET case control command with the same identification number as setid.

ALL Export face geometry for all elements included in SET case control commands.

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Describer Meaning

sktunit Logical unit number for the ADAMS sketch file. Specify sktunit < 0 to distinguish it from the setid. Valid only when the ADAMS interface file request describers is specified.

OUTGSTRS Controls whether grid point stress is written to interface file. Valid only when the RECURDYN or ADAMS interface file request describers are specified.

NO Do not write grid point stress to interface file. (Default)

YES Write grid point stress to interface file.

OUTGSTRN Controls whether grid point strain is written to interface file. Valid only when the RECURDYN or ADAMS interface file request describers are specified.

NO Do not write grid point strain to interface file. (Default)

YES Write grid point strain to interface file.

RECVROP2 Controls whether the FLEXBODY run outputs an NX Nastran OP2 file for use in post processing of results.

NO OP2 file is not output. (Default)

YES OP2 file is output.

CHECK Controls whether debug output is written to the f06 file when RECVROP2=YES.

NO Debug output is not written. (Default)

YES Debug output is written.

NONCUP Controls modal damping output. Valid only when the SCMOTION, ADAMS, OP4 or MATLAB interface file request describers are specified.

-1 Output the full equivalent modal viscous damping matrix. (Default)

-2 Output the diagonal values of the equivalent modal viscous damping matrix only.

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GENERAL REMARKS: 1. Only one choice of SCMOTION, RECURDYN, ADAMS, SIMPACK, OP4, or MATLAB is allowed and must immediately follow the MBDEXPORT command.

2. The describers can be truncated to the first 4 characters.

3. MBDEXPORT must appear above the subcase level.

4. NX Nastran is a unitless code. RecurDyn, ADAMS, and SIMPACK are not. Thus, for a RecurDyn, ADAMS, or SIMPACK FLEXBODY=YES run, you must include a DTI,UNITS bulk entry in the NX Nastran input file. The DTI,UNITS bulk entry specifies the units that are associated with the numerical data in the NX Nastran input file. For RecurDyn and ADAMS FLEXBODY=YES runs, NX Nastran writes the units contained on the DTI,UNITS bulk entry directly to the interface file. When RecurDyn or ADAMS read the interface file, they associate the units with the numerical data contained in the interface file. For SIMPACK FLEXBODY=YES runs, NX Nastran uses the units contained on the DTI,UNITS bulk entry to convert the numerical data that it writes to the interface file to SI (kg-m-sec) units. When SIMPACK reads the interface file, it recognizes that the numerical data contained in the interface file is already in SI (kg-m-sec) units. The format of the DTI,UNITS bulk entry is as follows: DTI UNITS 1 MASS FORCE LENGTH TIME All entries are required. Acceptable character strings are listed below. Mass: KG - kilogram LBM – pound-mass (0.45359237 kg) SLUG – slug (14.5939029372 kg) GRAM – gram (1E-3 kg) OZM – ounce-mass (0.02834952 kg) KLBM – kilo pound-mass (1000 lbm) (453.59237 kg) MGG – megagram (1E3 kg) MG – milligram (1E-6 kg) MCG – microgram (1E-9 kg) NG – nanogram (1E-12 kg) UTON – U.S. ton (907.18474 kg) SLI – slinch (175.1268352 kg)

Force: N – Newton

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LBF – pound-force (4.44822161526 N) KGF – kilograms-force (9.80665 N) OZF – ounce-force (0.2780139 N) DYNE – dyne (1E-5 N) KN – kilonewton (1E3 N) KLBF – kilo pound-force (1000 lbf) (4448.22161526 N) MN – millinewton (1E-3 N) MCN – micronewton (1E-6 N) NN – nanonewton (1E-9 N) CN – centinewton (1E–2 N) (Not valid for ADAMS) P – poundal (0.138254954 N) (Not valid for ADAMS)

Length: M – meter KM – kilometer (1E3 m) CM – centimeter (1E-2 m) MM – millimeter (1E-3 m) MI – mile (1609.344 m) FT – foot (0.3048 m) IN – inch (25.4E-3 m) MCM – micrometer (1E-6 m) NM – nanometer (1E-9 m) A – Angstrom (1E-10 m) YD – yard (0.9144 m) ML – mil (25.4E-6 m) MCI – microinch (25.4E-9 m)

Time:

S – second H – hour (3600.0 sec) MIN-minute (60.0 sec) MS – millisecond (1E-3 sec) MCS – microsecond (1E-6 sec) NS – nanosecond (1E-9 sec) D – day (86.4E3 sec)

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Do not include a DTI,UNITS bulk entry in the NX Nastran input file when the SCMOTION, OP4, or MATLAB interface file request describer is specified. If you do include a DTI,UNITS bulk entry, NX Nastran ignores it.

5. Because in a RecurDyn, ADAMS, or SIMPACK FLEXBODY=YES run the DTI,UNITS bulk entry defines the units, the scaling defined in WTMASS, which is important for units consistency in NX Nastran, is ignored in the output to the interface file. For example, if the model mass is in kilograms, force in Newtons, length in meters, and time in seconds, then WTMASS would equal 1. To ensure that NX Nastran works with the consistent set of kg, N, and m, the DTI,UNITS bulk entry is: DTI UNITS 1 KG N M S

The remarks from this point on are specific to each interface type. SIMCENTER MOTION REMARKS: 1. The generation of standard matrices and the writing of them to a Simcenter Motion OP2 file via OUTPUT2, which is only applicable in a non-restart, residual-only SOL 103 analysis, is initiated by MBDEXPORT SCMOTION FLEXBODY=YES. A specific ASSIGN statement is not required; the data will be written to the standard OP2 file via PARAM,POST,-2. This implies that the user must include PARAM,POST,-2 in the bulk data.

2. The parameter LMODES can be used to control which modes are used to derive the standard matrices.

3. The mode shape output will be reduced to the DOF defined in the DISPLACEMENT case control output request.

4. Because Simcenter Motion requires the constrained Craig-Bampton modes, you must use only the METHOD case control command in the flexbody creation run. The RSMETHOD case control command should not be used because it produces a modal basis that is invalid for Simcenter Motion.

RECURDYN REMARKS: 1. The creation of the RecurDyn Flex Input file is applicable in a non-restart SOL 103, 111, or 112 analysis only. RFI files are named ‘jid_seid.rfi’, where seid is the integer number of the superelement (0 for residual). These files are located in the same directory as the jid.f06 file.

2. You can create flexible body attachment points by defining the component as a superelement or part superelement, in which case the physical external (a-set) grids become the attachment points; or for a residual-only type model, you can use NX Nastran ASET bulk entries to define the attachment points.

3. The eight mass variants are:

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T sp = [xyz] are the coordinates of grid point p in the basic coordinate system.

φp = partitioned orthogonal modal matrix that corresponds to the translational degrees of freedom of grid p.

Ip = inertia tensor p. * φp = partitioned orthogonal modal matrix that corresponds to the rotational degrees of freedom of grid p.

= skew-symmetric matrix formed for each grid translational degree of freedom for each mode. M = number of modes. N = number of grids.

4. To accurately capture the mode shapes when supplying SPOINT/QSET combinations, the number of SPOINTS (ns) should be at least ns=n+(6+p), assuming that residual flexibility is on. In the above equation for ns, the number of modes (n) is specified on the EIGR (METHOD=LAN) or EIGRL bulk entries; the number of load cases is p. In general, you cannot have too many SPOINTs, as excess ones will be truncated with no performance penalty.

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5. For FLEXBODY=YES runs, residual vectors for the component should always be calculated as they result in a more accurate representation of the component shapes with little additional computational effort.

6. OMIT or OMIT1 bulk entries are not supported.

7. Lumped mass formulation (default) is required. Either leave PARAM,COUPMASS out of the input file or supply PARAM,COUPMASS,-1 (default) to ensure lumped mass.

8. CBEND elements are not allowed because they always use a coupled mass formulation. Likewise, the MFLUID fluid structure interface is not allowed because the virtual mass matrix it generates is not diagonal.

9. PARAM,WTMASS,value with a value other than 1.0 may be used with an NX Nastran run generating an RFI. It must have consistent units with regard to the DTI,UNITS bulk entry. Before generating the RFI, NX Nastran will appropriately scale the WTMASS from the physical mass matrix and mode shapes.

10. There is a distinction between how an MBDEXPORT RECURDYN FLEXBODY=YES run handles element-specific loads (such as a PLOAD4 entry) versus those that are grid-specific (such as a FORCE entry), especially when superelements are used. The superelement sees the total element-specific applied load. For grid-specific loads, the loads attached to an external grid will move downstream with the grid. That is to say, it is part of the boundary and not part of the superelement. This distinction applies to a superelement run and not to a residual-only or parts superelement run.

11. The loads specified in NX Nastran generally fall into two categories: non-follower or fixed direction loads (non-circulatory) and follower loads (circulatory). The follower loads are nonconservative in nature. Examples of fixed direction loads are the FORCE entry or a PLOAD4 entry when its direction is specified via direction cosines. Examples of follower loads are the FORCE1 entry or the PLOAD4 entry when used to apply a normal pressure. By default in NX Nastran, the follower loads are always active in SOL 103 and will result in follower stiffness being added to the differential stiffness and elastic stiffness of the structure. In a run with MBDEXPORT RECURDYN FLEXBODY=YES and superelements, if the follower force is associated with a grid description (such as a FORCE1) and the grid is external to the superelement, the follower load will move downstream with the grid. Thus, the downstream follower contribution to the component’s stiffness will be lost, which could yield poor results. This caution only applies to a superelement run and not to a residual-only or a part superelement run.

12. OUTGSTRS and OUTGSTRN entries require the use of standard NX Nastran STRESS= or STRAIN= used in conjunction with GPSTRESS= or GPSTRAIN= commands to produce grid point stress or strain. GPSTRESS(PLOT)= or GPSTRAIN(PLOT)= will suppress grid stress or strain print to the NX Nastran .f06 file.

13. To reduce the FE mesh detail for dynamic simulations, PSETID can include the ID of a SET entry. The SET entry lists PLOTEL or element IDs, whose connectivity

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is exported into the RFI to display the components in RecurDyn. This option can significantly reduce the size of the RFI without compromising accuracy in the FunctionBay simulation providing that the mass invariant computation is requested. With superelement analysis, for any of these elements that lie entirely on the superelement boundary (all of the elements’ grids are attached only to a-set or exterior grids), a SEELT bulk entry must be specified to keep that display element with the superelement component. This can also be accomplished using PARAM, AUTOSEEL,YES. The SEELT entry is not required with parts superelements, as boundary elements stay with their component. If the SET entry points to an existing set from the OUTPUT(PLOT) section, this single set is used explicitly to define elements that are used to select grids to display the component in RecurDyn. If PSETID does not find the set ID in OUTPUT(PLOT), it will search sets in the case control for a matching set ID. This matching set ID then represents a list of OUTPUT(PLOT) defined elements’ sets. The union of which will be used to define a set of PLOTELs or other elements used to select grids to display the component in RecurDyn. If you wish to select all of the sets in the OUTPUT(PLOT) section, then use PSETID=ALL. The following element types are not supported for writing to an RFI, nor are they supported as a ‘type’ entry in a set definition in OUTPUT(PLOT): CAABSF, CAEROi, CDUMi, CHBDYx, CDAMP3, CDAMP4, CELAS3, CELAS4, CMASS3, CMASS4, CRAC2D, CRAC3D, CTWIST, CWEDGE, CWELD, and GENEL.

14. Typical NX Nastran data entry requirements are described below. Typical Parameters: • PARAM,RESVEC,character_value – controls calculation of residual vector modes.

• PARAM,GRDPNT,value - mass invariants 1I, 2I, and 3I will be computed using results of NX Nastran grid point weight generator execution in the basic coordinate system.

Typical Case Control:

• MBDEXPORT RECURDYN FLEXBODY=YES is required for RFI generation.

• METHOD=n is required before or in the first subcase for modal solutions.

• SUPER=n,SEALL=n is useful with multiple superelement models to select an individual superelement as a flexible body. Cannot be used with a linear STATSUB(PRELOAD) run.

• OUTPUT(PLOT) is necessary to define elements used to select grids to display the component in RecurDyn when PSETID=ALL or setid. SET n=list of elements (including PLOTELs) is used to select grids to display the component.

• OUTPUT(POST) is necessary to define volume and surface for grid stress or strain shapes.

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SET n=list is a list of elements for surface definition for grid stress or strain shapes. Stress and strain data in the RFI is limited to the six components (that is, 3 normal and 3 shear) for a grid point for a given mode. SURFACE n SET n NORMAL z3 is used to define a surface for writing stress and strain data. Only one FIBER selection is allowed for each SURFACE, thus the use of the FIBER ALL keyword on the SURFACE case control command will write stresses to the RFI at the Z1 fiber location only. Because the FIBER keyword only applies to stresses, strain data will always be written to the RFI at the MID location. Stress and strain data at grid points can only be written to the RFI for surface and volume type elements (for example, CQUAD and CHEXA). VOLUME n SET n is a volume definition. The default SYSTEM BASIC is required with SURFACE or VOLUME.

• STRESS(PLOT) is necessary for stress shapes.

• STRAIN(PLOT) is necessary for strain shapes.

• GPSTRESS(PLOT) is necessary for grid point stress shapes to be included in the RFI.

• GPSTRAIN(PLOT) is necessary for grid point strain shapes to be included in the RFI. Typical Bulk Data:

• DTI,UNITS,1,MASS,FORCE,LENGTH,TIME is required for RFI generation. For input files containing superelements, this command must reside in the main bulk data section.

• SPOINT,id_list defines and displays modal amplitude.

• SESET,SEID,grid_list defines a superelement (see GRID and BEGIN BULK SUPER=). The exterior grids will represent the attachment points along with the q-set.

• SEELT,SEID,element_list reassigns superelement boundary elements to an upstream superelement.

• RELEASE,SEID,C,Gi is an optional entry that removes DOFs from an attachment grid for which no constraint mode is desired. For example, this allows the removal of rotational degrees of freedom from an analysis where only translational degrees of freedom are required.

• SEQSET,SEID,spoint_list defines modal amplitudes of a superelement (see SEQSET1).

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• SENQSET,SEID,N defines modal amplitudes of a part superelement. It must reside in the main bulk data section.

• ASET,IDi,Ci defines attachment points for a residual-only run (see ASET1).

• QSET1,C,IDi defines modal amplitudes for the residual structure or modal amplitudes for a part superelement (see QSET).

• PLOTEL,EID,Gi can be used, along with existing model elements, to define elements used to select grids to display the components in RecurDyn.

• EIGR,SID,METHOD,… obtains real eigenvalue extraction (see EIGRL).

15. MBDEXPORT and ADAMSMNF case control entries cannot be used in the same analysis run. In other words, a RecurDyn RFI file or an Adams MNF file can be generated during a particular NX Nastran execution, but not both files at the same time. Attempting to generate both files in the same analysis will cause an error to be issued and the execution to be terminated.

16. The RECVROP2=YES option is used when you would like results recovery (using the MBDRECVR case control entry) from an RecurDyn/Flex analysis. This option requires the following assignment command: ASSIGN OUTPUT2='name.out' STATUS=UNKNOWN UNIT=20 FORM=UNFORM be inserted into the file management section of the NX Nastran input file. It will cause an OP2 file with a .out extension to be generated, which then can be used as input into an NX Nastran SOL 103 run using the MBDRECVR case control capability to perform results recovery from an RecurDyn/Flex analysis. FLEXBODY=YES is required with its use. The data blocks output are: MGGEW - physical mass external sort with weight mass removed MAAEW - modal mass KAAE - modal stiffness CMODEXT - component modes. This capability is limited to no more than one superelement per NX Nastran model. Residual-only analyses are supported. If differential stiffness is included, the static portion of the results will not be included in the recovered results when using MBDRECVR.

17. Setting CHECK=YES (which is only available when RECVROP2=YES) is not recommended for large models due to the amount of data that will be written to the f06.

18. The MBDEXPORT data routines use the environment variable TMPDIR for temporary storage during the processing of mode shape data. As a result, TMPDIR must be defined when using MBDEXPORT. TMPDIR should equate to a directory string for temporary disk storage, preferably one with a large amount of free space.

19. Preload conditions are not supported.

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20. To request differential stiffness, include a static subcase that contains the stress-stiffening loads. In another subcase include STATSUB = n where n is the number of the static subcase.

ADAMS REMARKS: 1. The creation of the Adams MNF, which is applicable in a non-restart SOL 103, 111, or 112 analysis only, is initiated by MBDEXPORT ADAMS FLEXBODY=YES (other describers are optional) and the inclusion of the bulk entry DTI,UNITS. MNF files are named ‘jid_seid.mnf’, where seid is the integer number of the superelement (0 for residual). The location of these files is the same directory as the jid.f06 file.

2. You can create flexible body attachment points by defining the component as a superelement or part superelement, in which case the physical external (a-set) grids become the attachment points. For a residual-only type model, you can use standard NX Nastran ASET bulk entries to define the attachment points.

3. The nine mass variants are:

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T sp = [xyz] are the coordinates of grid point p in the basic coordinate system.

φp = partitioned orthogonal modal matrix that corresponds to the translational degrees of freedom of grid p.

Ip = inertia tensor p. * φp = partitioned orthogonal modal matrix that corresponds to the rotational degrees of freedom of grid p.

= skew-symmetric matrix formed for each grid translational degree of freedom for each mode. M = number of modes. N = number of grids.

5. For FLEXBODY=YES runs, residual vectors for the component should always be calculated as they result in a more accurate representation of the component shapes at little additional cost.

6. OMIT or OMIT1 bulk entries are not supported.

7. Lumped mass formulation (default) is required. Either leave PARAM,COUPMASS out of the input file or supply PARAM,COUPMASS,-1 (default) to ensure lumped mass.

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9. PARAM,WTMASS,value with a value other than 1.0 may be used with an NX Nastran run generating an MNF. It must have consistent units with regard to the DTI,UNITS bulk entry. Before generating the MNF, NX Nastran will appropriately scale the WTMASS from the physical mass matrix and mode shapes.

10. There is a distinction between how an MBDEXPORT ADAMS FLEXBODY=YES run handles element-specific loads (such as a PLOAD4 entry) versus those that are grid-specific (such as a FORCE entry), especially when superelements are used. The superelement sees the total element-specific applied load. For grid-specific loads, the loads attached to an external grid will move downstream with the grid. That is to say, it is part of the boundary and not part of the superelement. This distinction applies to a superelement run and not to a residual-only or parts superelement run.

11. The loads specified in NX Nastran generally fall into two categories: non-follower or fixed direction loads (non-circulatory) and follower loads (circulatory). The follower loads are nonconservative in nature. Examples of fixed direction loads are the FORCE entry or a PLOAD4 entry when its direction is specified via direction cosines. Examples of follower loads are the FORCE1 entry or the PLOAD4 entry when used to apply a normal pressure. By default in NX Nastran, the follower loads are always active in SOL 103 and will result in follower stiffness being added to the differential stiffness and elastic stiffness of the structure. In a run with MBDEXPORT ADAMS FLEXBODY=YES and superelements, if the follower force is associated with a grid description (such as a FORCE1) and the grid is external to the superelement, the follower load will move downstream with the grid. Thus, the downstream follower contribution to the component’s stiffness will be lost, which could yield poor results. This caution only applies to a superelement run and not to a residual-only or a part superelement run.

13. To reduce the FE mesh detail for dynamic simulations, PSETID (on the MBDEXPORT Case Control command) defined with a SET entry (i.e. setid) is used to define a set of PLOTELs or other elements used to select grids to display the components in Adams. This option can significantly reduce the size of the MNF without compromising accuracy in the Adams simulation providing that the mass invariant computation is requested. With superelement analysis, for any of these elements that lie entirely on the superelement boundary (all of the elements’ grids attached only to a-set or exterior grids), a SEELT bulk entry must be specified to keep that display element with the superelement component. This can also be accomplished using PARAM, AUTOSEEL,YES. The SEELT entry is not required with parts superelements, as boundary elements stay with their component. If the SET entry points to an existing set from the OUTPUT(PLOT) section, this single set is used explicitly to define elements used to select grids to display the component in Adams. If PSETID does not find the set ID in OUTPUT(PLOT), it will search sets in the case control for a matching set ID. This matching set ID list then

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represents a list of OUTPUT(PLOT) defined elements’ sets, the union of which will be used to define a set of PLOTELs or other elements used to select grids to display the component in Adams. If the user wishes to select all of the sets in the OUTPUT(PLOT) section, then use PSETID=ALL. The following element types are not supported for writing to an MNF, nor are they supported as a ‘type’ entry in a set definition in OUTPUT(PLOT): CAABSF, CAEROi, CDUMi, CHBDYx, CDAMP3, CDAMP4, CELAS3, CELAS4, CMASS3, CMASS4, CRAC2D, CRAC3D, CTWIST, CWEDGE, CWELD, and GENEL. PSETID can also point to a sketch file using PSETID= – sktunit, where sktunit references an ASSIGN statement of the form: ASSIGN SKT=‘sketch_file.dat’,UNIT=sktunit. The grids defined for the elements’ faces in the sketch file, along with all external (i.e. boundary) grids for the superelements, will be the only grids (and their associated data) written to the MNF. The format of the sketch file, which describes the mesh as a collection of faces, must be as follows: face_count face_1_node_count face_1_nodeid_1 face_1_nodeid_2 ... face_2_node_count face_2_nodeid_1 face_2_nodeid_2 ...

Faces must have a node count of at least two. For example, a mesh comprised of a single brick element might be described as follows:

6 4 1000 1001 1002 1003 4 1007 1006 1005 1004 4 1000 1004 1005 1001 4 1001 1005 1006 1002 4 1002 1006 1007 1003 4 1003 1007 1004 1000 Alternatively, the mesh might be described as a stick figure using a collection of lines (two node faces), as shown below:

8 2 101 102 2 102 103 2 103 104 2 104 105 2 105 106 2 106 107 2 107 108 2 108 109

14. Typical NX Nastran data entry requirements are described below. Typical Parameters:

NX Nastran 12 Release Guide 2-17 ChCaphtaeprte2r: 2:DynaDmyincsamics

• PARAM,RESVEC,character_value – controls calculation of residual vector modes.

• PARAM,GRDPNT, value - mass invariants 1I, 2I, and 7I will be computed using results of NX Nastran grid point weight generator execution in the basic coordinate system.

Typical Case Control:

• MBDEXPORT ADAMS FLEXBODY=YES is required for MNF generation.

• METHOD=n is required before or in the first subcase for modal solutions.

• SUPER=n,SEALL=n is useful with multiple superelement models to select an individual superelement as a flexible body. Cannot be used with a linear STATSUB(PRELOAD) run.

• OUTPUT(PLOT) is necessary to define elements used to select grids to display the component in Adams when PSETID=ALL or setid. SET n=list of elements (including PLOTELs) is used to select grids to display the component.

• OUTPUT(POST) is necessary to define volume and surface for grid stress or strain shapes. SET n=list is a list of elements for surface definition for grid stress or strain shapes. Stress and strain data in the MNF is limited to the six components (i.e. 3 normal and 3 shear) for a grid point for a given mode. SURFACE n SET n NORMAL z3 is used to define a surface for writing stress and strain data. Only one FIBER selection is allowed for each SURFACE, thus the use of the FIBRE ALL keyword on the SURFACE case control command will write stresses to the MNF at the Z1 fiber location only. Because the FIBRE keyword only applies to stresses, strain data will always be written to the MNF at the MID location. Stress and strain data at grid points can only be written to the MNF for surface and volume type elements (e.g. CQUAD and CHEXA). VOLUME n SET n is a volume definition. The default SYSTEM BASIC is required with SURFACE or VOLUME.

• STRESS(PLOT) is necessary for stress shapes.

• STRAIN(PLOT) is necessary for strain shapes.

• GPSTRESS(PLOT) is necessary for grid point stress shapes to be included in the MNF.

• GPSTRAIN(PLOT) is necessary for grid point strain shapes to be included in the MNF.

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Typical Bulk Data:

• DTI,UNITS,1,MASS,FORCE,LENGTH,TIME is required for MNF generation. For input files containing superelements, this command must reside in the main bulk data section.

• SPOINT,id_list defines and displays modal amplitude.SESET,SEID,grid_list defines a superelement (see GRID and BEGIN BULK SUPER=). The exterior grids will represent the attachment points along with the q-set.

• SEELT,SEID,element_list reassigns superelement boundary elements to an upstream superelement.

• SEQSET,SEID,spoint_list defines modal amplitudes of a superelement (see SEQSET1).

• SENQSET,SEID,N defines modal amplitudes of a part superelement. It must reside in the main bulk data section.

• ASET,IDi,Ci defines attachment points for a residual-only run (see ASET1).

• QSET1,C,IDi defines modal amplitudes for the residual structure or modal amplitudes for a part superelement (see QSET).

• PLOTEL,EID,Gi can be used, along with existing model elements, to define elements used to select grids to display the components in Adams.

• EIGR,SID,METHOD,… obtains real eigenvalue extraction (see EIGRL).

15. The RECVROP2=YES option is used when you would like results recovery (using the MBDRECVR case control entry) from an Adams/Flex analysis. This option requires the following assignment command: ASSIGN OUTPUT2='name.out' STATUS=UNKNOWN UNIT=20 FORM=UNFORM be inserted into the file management section of the NX Nastran input file. It will cause an OP2 file with a .out extension to be generated, which then can be used as input into an NX Nastran SOL 103 run using the MBDRECVR case control capability to perform results recovery from an Adams/Flex analysis. FLEXBODY=YES is required with its use. The data blocks output are: MGGEW - physical mass external sort with weight mass removed MAAEW - modal mass KAAE - modal stiffness CMODEXT - component modes.

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This capability is limited to no more than one superelement per NX Nastran model. Residual-only analyses are supported. If differential stiffness is included, the static portion of the results will not be included in the recovered results when using MBDRECVR.

16. Setting CHECK=YES (which is only available when RECVROP2=YES) is not recommended for models of realistic size due to the amount of data that will be written to the f06 file.

17. The MBDEXPORT data routines use the environment variable TMPDIR for temporary storage during the processing of mode shape data. As a result, TMPDIR must be defined when using MBDEXPORT. TMPDIR should equate to a directory string for temporary disk storage, preferably one with a large amount of free space.

18. If any damping is defined in the model, an equivalent modal viscous damping will be determined for each mode and written to the MNF. This equivalent modal viscous damping is defined as: T D = ψ Be ψ where D is the equivalent modal viscous damping matrix, ψ is the eigenvector matrix, and Be is the equivalent viscous damping matrix. The equivalent viscous damping matrix is given by:

where G, W3, and W4 are structural damping-related parameters described in the “Parameter Descriptions” section of this guide. By default, the full equivalent modal viscous damping matrix is written to the MNF. To write only the diagonal values of the equivalent modal viscous damping matrix to the MNF, specify NONCUP=–2 or specify PARAM,NONCUP,-2. If both the NONCUP describer and the NONCUP parameter are specified, the NONCUP describer specification takes precedence.

19. Preload conditions are not supported.

20. To request differential stiffness, include a static subcase that contains the stress-stiffening loads. In another subcase include STATSUB = n where n is the number of the static subcase.

21. Cylindrical and spherical nodal displacement coordinate systems (i.e. CD on the GRID bulk entry) are not supported.

SIMPACK REMARKS: 1. The creation of a SIMPACK Flexible Body Input (FBI) file is applicable in a non-restart SOL 103, 111, and 112 analysis only. FBI files are named ‘jid_seid.fbi’, where seid is the integer number of the superelement (0 for residual). The location of these files is the same directory as the jid.f06 file.

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2. The creation of the FBI file is initiated by MBDEXPORT SIMPACK FLEXBODY=YES (other describers are optional) and the inclusion of the bulk entry DTI,UNITS. This is only valid for a Component Mode Synthesis (CMS) analysis. Thus, it is necessary to define the modal coordinates using the SPOINT bulk entry, and to define them to be in the q-set using the QSET/QSET1 or SEQSET/SEQSET1 bulk entries as appropriate.

3. You can create flexible body attachment points by defining the component as a superelement or part superelement, in which case the physical external (a-set) grids become the attachment points; or for a residual-only type model, you can use NX Nastran ASET bulk entries to define the attachment points. Note that the values corresponding to these attachment points in the CMS-reduced mass and stiffness matrices written to the FBI file will be defined in the nodal displacement coordinate systems of these attachment points. The user must account for these coordinate systems when loading or restraining these attachment points within the SIMPACK run.

4. To accurately capture the mode shapes when supplying SPOINT/QSET combinations, the number of SPOINTs (ns) should be at least ns=n+(6+p). In the above equation for ns, the number of modes (n) is specified on the EIGR (METHOD=LAN) or EIGRL bulk entries; the number of load cases is p. In general, you cannot have too many SPOINTs. Excess SPOINTs will be truncated with no performance penalty.

5. OMIT and OMIT1 bulk entries are not supported.

6. Lumped mass formulation (default) is required. Either leave PARAM,COUPMASS out of the input file or supply PARAM,COUPMASS,-1 (default) to ensure lumped mass formulation.

7. CBEND elements are not allowed because they always use a coupled mass formulation. Likewise, the MFLUID fluid structure interface is not allowed because the virtual mass matrix it generates is not diagonal.

8. PARAM,WTMASS,value with a value other than 1.0 may be used with an NX Nastran run generating an FBI file. It must have consistent units with regard to the DTI,UNITS bulk entry. Before generating the FBI file, NX Nastran will appropriately scale the WTMASS from the physical mass matrix and mode shapes.

9. There is a distinction between how an MBDEXPORT SIMPACK FLEXBODY=YES run handles element-specific loads (such as a PLOAD4 entry) versus those that are grid-specific (such as a FORCE entry), especially when superelements are used. The superelement sees the total element-specific applied load. For grid-specific loads, the loads attached to an external grid will move downstream with the grid. That is to say, it is part of the boundary and not part of the superelement. This distinction applies to a superelement run and not to a residual-only or parts superelement run.

10. The loads specified in NX Nastran generally fall into two categories: non-follower or fixed direction loads (non-circulatory) and follower loads (circulatory). The follower loads are nonconservative in nature. Examples of fixed direction loads are

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the FORCE entry or a PLOAD4 entry when its direction is specified via direction cosines. Examples of follower loads are the FORCE1 entry or the PLOAD4 entry when used to apply a normal pressure. By default in NX Nastran, the follower loads are always active in SOL 103 and will result in follower stiffness being added to the differential stiffness and elastic stiffness of the structure. In a run with MBDEXPORT SIMPACK FLEXBODY=YES and superelements, if the follower force is associated with a grid description (such as a FORCE1) and the grid is external to the superelement, the follower load will move downstream with the grid. Thus, the downstream follower contribution to the component’s stiffness will be lost, which could yield poor results. This caution only applies to a superelement run and not to a residual-only or a part superelement run.

11. To reduce the FE mesh detail for dynamic simulations, PSETID can include the ID of a SET entry. PSETID is also used to define the grids to be included in the recovery matrix that is written to the FBI file. The SET entry lists PLOTEL or element IDs, whose connectivity is exported into the FBI file to display the components in SIMPACK. This option can significantly reduce the size of the FBI file without compromising accuracy in the SIMPACK simulation. With superelement analysis, for any of these elements that lie entirely on the superelement boundary (all of the elements’ grids are attached only to a-set or exterior grids), a SEELT bulk entry must be specified to keep that display element with the superelement component. This can also be accomplished using PARAM, AUTOSEEL,YES. The SEELT entry is not required with parts superelements, as boundary elements stay with their component. If the SET entry points to an existing set from the OUTPUT(PLOT) section, this single set is used explicitly to define elements that are used to select grids to display the component in SIMPACK. If PSETID does not find the set ID in OUTPUT(PLOT), it will search sets in the case control for a matching set ID. This matching set ID then represents a list of OUTPUT(PLOT) defined elements’ sets, the union of which will be used to define a set of PLOTELs or other elements used to select grids to display the component in SIMPACK. If you wish to select all of the sets in the OUTPUT(PLOT) section, then use PSETID=ALL. The following element types are not supported for writing to an FBI file, nor are they supported as a ‘type’ entry in a set definition in OUTPUT(PLOT): CAABSF, CAEROi, CDUMi, CHBDYx, CDAMP3, CDAMP4, CELAS3, CELAS4, CMASS3, CMASS4, CPYRAM, CRAC2D, CRAC3D, CTWIST, CWEDGE, CWELD, and GENEL.

12. Typical NX Nastran data entry requirements are described below. Typical Case Control:

• MBDEXPORT SIMPACK FLEXBODY=YES is required for FBI file generation.

• METHOD=n is required before or in the first subcase for modal solutions.

• SUPER=n,SEALL=n is useful with multiple superelement models to select an individual superelement as a flexible body. Cannot be used with a linear STATSUB(PRELOAD) run.

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Typical Bulk Data:

• DTI,UNITS,1,MASS,FORCE,LENGTH,TIME is required for FBI file generation. For input files containing superelements, this command must reside in the main bulk data section.

• SPOINT,id_list defines and displays modal amplitude.

• SESET,SEID,grid_list defines a superelement (see GRID and BEGIN BULK SUPER=). The exterior grids will represent the attachment points along with the q-set.

• SEELT,SEID,element_list reassigns superelement boundary elements to an upstream superelement.

• SEQSET,SEID,spoint_list defines modal amplitudes of a superelement (see SEQSET1).

• SENQSET,SEID,N defines modal amplitudes of a part superelement. It must reside in the main bulk data section.

• ASET,IDi,Ci defines attachment points for a residual-only run (see ASET1).

• QSET1,C,IDi defines modal amplitudes for the residual structure or modal amplitudes for a part superelement (see QSET).

• PLOTEL,EID,Gi can be used, along with existing model elements, to define elements used to select grids to display the components in SIMPACK.

• EIGR,SID,METHOD,… obtains real eigenvalue extraction (see EIGRL).

13. MBDEXPORT and ADAMSMNF case control entries cannot be used in the same analysis run. In other words, a SIMPACK FBI file or an Adams MNF file can be generated during a particular NX Nastran execution, but not both files at the same time. Attempting to generate both files in the same analysis will cause an error to be issued and the solve to be terminated.

14. The RECVROP2=YES option is used when you would like results recovery (using the MBDRECVR case control entry) from a SIMPACK analysis. This option requires the following assignment command: ASSIGN OUTPUT2='name.out' STATUS=UNKNOWN UNIT=20 FORM=UNFORM be inserted into the file management section of the NX Nastran input file. It will cause an OP2 file with a .out extension to be generated, which then can be used as input into an NX Nastran SOL 103 run using the MBDRECVR case control capability to perform results recovery from a SIMPACK analysis. FLEXBODY=YES is required with its use.

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The data blocks output are: MGGEW - physical mass external sort with weight mass removed MAAEW - modal mass KAAE - modal stiffness CMODEXT - component modes. This capability is limited to no more than one superelement per NX Nastran model. Residual-only analyses are supported. If differential stiffness is included, the static portion of the results will not be included in the recovered results when using MBDRECVR.

15. Setting CHECK=YES (which is only available when RECVROP2=YES) is not recommended for models of realistic size due to the amount of data that will be written to the f06 file.

16. The MBDEXPORT data routines use the environment variable TMPDIR for temporary storage during the processing of mode shape data. As a result, TMPDIR must be defined when using MBDEXPORT. TMPDIR should equate to a directory string for temporary disk storage, preferably one with a large amount of free space.

17. Preload conditions are not supported.

18. To request differential stiffness, include a static subcase that contains the stress-stiffening loads. In another subcase include STATSUB = n where n is the number of the static subcase.

OP4 REMARKS: 1. The generation of standard or state-space matrices and the writing of them to an OP4 file via OUTPUT4, which is applicable in a non-restart SOL 103, 111, or 112 analysis only, is initiated by MBDEXPORT OP4=unit STANDARD FLEXBODY=YES, or MBDEXPORT OP4=unit STATESPACE FLEXBODY=YES (other describers are optional) and the inclusion of the ASSIGN file management statement. This ASSIGN statement must be of the form: ASSIGN OUTPUT4=’filename’,UNIT=n,etc. where ‘n’ matches the absolute value for unit on the MBDEXPORT OP4=unit case control command. The number of digits of precision for matrix data is controlled by the DIGITS parameter. For a model with superelements, only one OP4 file will be generated. This OP4 file will be generated for the first superelement (or the residual) that satisfies the conditions defined in Remarks 3 and 4. For standard matrices, if user-defined set U8 is not defined, the residual will be written to the OP4.

2. The parameters LFREQ/HFREQ or LMODES can be used to control which modes are used to derive the standard or state-space matrices.

3. For state-space matrices, user-defined set U7 is used for input DOF. User-defined set U8 is used for output DOF. Refer to the USET/USET1 bulk entries for

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partitioned superelements and refer to the SEUSET/SEUSET1 bulk entries for non-partitioned superelements.

4. For standard matrices, user-defined set U8 is used for output DOF. The mode shape output will be reduced to the DOF defined in DOF set U8. If DOF set U8 is not defined, the mode shape data for all DOF will be written. Refer to the USET/USET1 bulk entries for partitioned superelements and refer to the SEUSET/SEUSET1 bulk entries for non-partitioned superelements.

5. For the state-space option, the OP4 file contains the [A], [B], [C], and [E] state-space matrices. They are defined as AMAT, BMAT, CMAT, and EMAT, respectively. The input and output DOF are defined as U7DOF and U8DOF, respectively with the first column being the grid ID and the second column being the direction code (1 through 6).

6. For the standard option, the OP4 file contains the modal mass, equivalent modal viscous damping, modal stiffness, mode shapes, and modal forces defined as MMASS, MDAMP, MSTIF, U8PHIX, and MFORC, respectively. The physical DOF corresponding one-to-one with the rows of U8PHIX are defined as U8DOF. The first column contains the grid ID and the second column contains the direction code (1 through 6).

7. The RECVROP2=YES option is used when you would like results recovery (using the MBDRECVR case control entry) from a system analysis. This option requires the following assignment command: ASSIGN OUTPUT2=’name.out’ STATUS=UNKNOWN UNIT=20 FORM=UNFORM be inserted into the file management section of the NX Nastran input file. It will cause an OP2 file with a .out extension to be generated, which can then be used as an input into an NX Nastran SOL 103 run using the MBDRECVR case control command. FLEXBODY=YES is required when specifying RECVROP2=YES. The data blocks output are: MGGEW – physical mass external sort with weight mass removed MAAEW – modal mass KAAE – modal stiffness CMODEXT – component modes This capability is limited to one superelement per NX Nastran model. Residual-only analyses are supported. If differential stiffness is included, the static portion of the results will not be included in the recovered results when using MBDRECVR.

8. Setting CHECK=YES (which is only available when RECVROP2=YES) is not recommended for models of realistic size due to the amount of data that will be written to the f06 file.

9. Differential stiffness is only supported for standard second-order system representation. To request differential stiffness, include a static subcase that

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contains the stress-stiffening loads. In another subcase include STATSUB = n where n is the number of the static subcase.

10. By default, the full equivalent modal viscous damping matrix is written to standard or state-space OP4 files. To write only the diagonal values of the equivalent modal viscous damping matrix to OP4 files, specify NONCUP=–2, or specify PARAM,NONCUP,-2. If both the NONCUP describer and the NONCUP parameter are specified, the NONCUP describer specification takes precedence.

MATLAB REMARKS: 1. The generation of standard or state-space matrices and the writing of them to a MATLAB script file, which is applicable in a non-restart SOL 103, 111, or 112 analysis only, is initiated by MBDEXPORT MATLAB STANDARD FLEXBODY=YES, or MBDEXPORT MATLAB STATESPACE FLEXBODY=YES (other describers are optional). The MATLAB script files are named jid_seid.m where seid is the integer number of the superelement (0 for residual). The location of the MATLAB script files is the same directory as the jid.f06 file.

2. The parameters LFREQ/HFREQ or LMODES can be used to control which modes are used to derive the standard or state-space matrices.

3. For state-space matrices, user-defined set U7 is used for input DOF. User-defined set U8 is used for output DOF. Refer to the USET/USET1 bulk entries for partitioned superelements and refer to the SEUSET/SEUSET1 bulk entries for non-partitioned superelements.

5. For the state-space option, the MATLAB script file contains the [A], [B], [C], and [E] state-space matrices. They are defined as AMAT, BMAT, CMAT, and EMAT, respectively. The input and output DOF are defined as U7DOF and U8DOF, respectively with the first column being the grid ID and the second column being the direction code (1 through 6).

6. For the standard option, the MATLAB script file contains the modal mass, equivalent modal viscous damping, modal stiffness, mode shapes, and modal forces defined as MMASS, MDAMP, MSTIF, MSHAP, and MFORC, respectively. The physical DOF corresponding one-to-one with the rows of MSHAP are defined as U8DOF. The first column contains the grid ID and the second column contains the direction code (1 through 6).

7. The RECVROP2=YES option is used when you would like results recovery (using the MBDRECVR case control entry) from a system analysis. This option requires the following assignment command:

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ASSIGN OUTPUT2=’name.out’ STATUS=UNKNOWN UNIT=20 FORM=UNFORM be inserted into the file management section of the NX Nastran input file. It will cause an OP2 file with a .out extension to be generated, which can then be used as an input into an NX Nastran SOL 103 run using the MBDRECVR case control command. FLEXBODY=YES is required when specifying RECVROP2=YES. The data blocks output are: MGGEW – physical mass external sort with weight mass removed MAAEW – modal mass KAAE – modal stiffness CMODEXT – component modes This capability is limited to one superelement per NX Nastran model. Residual-only analyses are supported. If differential stiffness is included, the static portion of the results will not be included in the recovered results when using MBDRECVR.

8. Setting CHECK=YES (which is only available when RECVROP2=YES) is not recommended for models of realistic size due to the amount of data that will be written to the f06 file.

9. To request differential stiffness, include a static subcase that contains the stress-stiffening loads. In another subcase include STATSUB = n where n is the number of the static subcase.

10. By default, the full equivalent modal viscous damping matrix is written to standard or state-space MATLAB script files. To write only the diagonal values of the equivalent modal viscous damping matrix to MATLAB script files, specify NONCUP=–2 or specify PARAM,NONCUP,-2. If both the NONCUP describer and the NONCUP parameter are specified, the NONCUP describer specification takes precedence.

Random analysis control enhancement

Note This enhancement was implemented in NX Nastran 11, but is fully documented in this release.

In SOL 108 and 111, the software can now use the results from the same frequency response subcases in multiple random analyses. In earlier versions of NX Nastran, the software must recalculate the frequency response subcases for each random analysis. This enhancement results in a significant reduction in the computational effort required to perform multiple random analyses, especially when the random analyses reference many frequency response subcases.

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To implement this capability, the RANDOM option for the TYPE describer on the ANALYSIS case control command is now available. Include ANALYSIS = RANDOM in each subcase in which you want to perform a random analysis.

Example

Suppose that a structure is excited by two loads, and you want to evaluate the random response of the structure for two PSD functions using SOL 111. For NX Nastran 12, the subcase structure of the input file can be organized as follows:

SUBCASE 1 $ $ Subcase 1 calculates the normal modes $ ANALYSIS=MODES DISP=ALL $ SUBCASE 2 $ $ Subcase 2 calculates the frequency response of the structure to the $ loading specified by DLOAD 111 at the frequencies specified by $ FREQUENCY set 13 $ FREQUENCY=13 DLOAD=111 $ SUBCASE 3 $ $ Subcase 3 calculates the frequency response of the structure to the $ loading specified by DLOAD 211 at the frequencies specified by $ FREQUENCY set 13 $ FREQUENCY=13 DLOAD=211 $ SUBCASE 4 $ $ Subcase 4 uses the frequency responses from Subcases 2 and 3 to $ calculate the random response of the structure for the PSD function $ specified by RANDOM 100 $ ANALYSIS=RANDOM RANDOM=100 $ SUBCASE 5 $ $ Subcase 5 uses the frequency responses from Subcases 2 and 3 to $ calculate the random response of the structure for the PSD function $ specified by RANDOM 200 $ ANALYSIS=RANDOM RANDOM=200 As you can see, in the above subcase organization, the software calculates each frequency response once regardless of the number of PSD functions that you want to consider.

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Note To use multiple frequency responses in a random calculation: • For SOL 108 or 111, each frequency response must reference the same set of frequencies.

• For SOL 111, if SDAMPING is specified, each frequency response must reference the same SDAMPING specification.

For earlier versions of NX Nastran, the subcase structure of the input file for the same solution must be organized as follows:

SUBCASE 1 $ $ Subcase 1 calculates the normal modes $ ANALYSIS=MODES DISP=ALL $ SUBCASE 2 $ $ Subcase 2 calculates the frequency response of the structure to the $ loading specified by DLOAD 111 at the frequencies specified by $ FREQUENCY set 13 and requests the software calculate the random $ response of the structure for the PSD function specified by $ RANDOM 100 $ RANDOM=100 FREQUENCY=13 DLOAD=111 $ SUBCASE 3 $ $ Subcase 3 calculates the frequency response of the structure to the $ loading specified by DLOAD 211 at the frequencies specified by $ FREQUENCY set 13 $ FREQUENCY=13 DLOAD=211 $ SUBCASE 4 $ $ Subcase 4 recalculates the frequency response of the structure to $ the loading specified by DLOAD 211 at the frequencies specified by $ FREQUENCY set 23 and requests the software calculate the random $ response of the structure for the PSD function specified by $ RANDOM 200 $ RANDOM=200 FREQUENCY=23 DLOAD=111 $ SUBCASE 5

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$ $ Subcase 5 recalculates the frequency response of the structure to $ the loading specified by DLOAD 211 at the frequencies specified by $ FREQUENCY set 23 $ FREQUENCY=23 DLOAD=211

Note In the example, FREQUENCY=13 and FREQUENCY=23 reference FREQi bulk entries that contain the same set of frequencies.

As you can see, in the above subcase organization, the software recalculates the frequency responses for each PSD function that you want to consider. Thus, for this example, the computational effort to calculate the frequency responses is twice the amount expended when you use the ANALYSIS = RANDOM capability.

Random analysis output enhancement Now when you perform a random analysis, the software automatically calculates and outputs the zero-mean crossing for the RMS von Mises stress. The zero-mean crossing for RMS von Mises stress represents the apparent (or dominant) frequency of the response. The software calculates the zero-mean crossing for all of the elements and at all of the same locations that the software calculates the RMS von Mises stress. When the software calculates the zero-mean crossing, it uses the computed spectral density function of the RMS result. In earlier versions of NX Nastran, the software automatically calculates the apparent frequency for all the RMS results except von Mises stress. The software writes the zero-mean crossing for RMS von Mises stress results to the new OESXNO data block.

RESVALT parameter removed Beginning with NX Nastran 12, the RESVALT parameter is removed from the software and documentation. Now to exclude mass and damping effects from the residual vectors, specify the NODYNRSP describer on the RESVEC case control command.

Direct-input, frequency-dependent components In a SOL 108 or 111 frequency response analysis, you can now define frequency-dependent components by direct input of tabular dynamic stiffness versus frequency or dynamic flexibility versus frequency data. With this capability, you can use empirically obtained dynamic stiffness or dynamic flexibility data to represent a component of an assembly.

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The dynamic stiffness represents the cumulative effect of inertia, damping, and stiffness within the component. For example, the dynamic stiffness for an FE model is given as:

where: ω Frequency in radians per unit time [M] Global mass matrix [B] Global viscous damping matrix G Overall structural damping coefficient (PARAM,G) [K] Global stiffness matrix

GE Structural damping coefficient of the elements (GE on material, property, or element entries)

[KE] Stiffness matrix of the elements The dynamic flexibility matrix is the inverse of the dynamic stiffness matrix. The dynamic stiffness is expressed in terms of force per unit displacement (moment per unit angular displacement). However, you can also enter dynamic stiffness data as force per unit velocity or force per unit acceleration (moment per unit angular velocity or moment per unit angular acceleration). The dynamic flexibility is expressed in terms of displacement per unit force (angular displacement per unit moment). However, you can also enter dynamic flexibility data as velocity per unit force or acceleration per unit force (angular velocity per unit moment or angular acceleration per unit moment). The values you enter for dynamic stiffness or dynamic flexibility must align with the physical coordinates and directions of the attachment grid points. If you enter dynamic stiffness data in terms of velocity or acceleration, the software multiplies velocity data by iω and acceleration data by –ω2 to convert the data to force (moment) per unit displacement (angular displacement). If you enter dynamic flexibility data in terms of velocity or acceleration, the software divides velocity data by iω and acceleration data by –ω2 to convert the data to force (moment) per unit displacement (angular displacement). The software then inverts the dynamic flexibility matrix to obtain the dynamic stiffness matrix. Because the unit basis of the dynamic stiffness or flexibility data may differ from the unit basis of the FE model, you can define displacement and force scaling factors. The software uses the scaling factors to convert the dynamic stiffness or flexibility data to the units of the FE model.

Direct frequency response analysis

For a SOL 108 direct frequency response analysis, the software: 1. Adds the dynamic stiffness of the component to the dynamic stiffness of the FE model.

2. Performs the direct frequency response analysis of the combined system.

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Modal frequency response analysis

For a SOL 111 modal frequency response analysis, the software: 1. Performs a real eigenvalue solution on the FE portion of the model only. During this solve, the software ignores the frequency-dependent components and automatically calculates residual vectors for the interface DOF of the attachment grid points.

2. Uses the results of the real eigenvalue solution to transform the dynamic stiffness or flexibility for the component from physical coordinates to modal coordinates.

3. Adds the transformed dynamic stiffness of the component to the modal dynamic stiffness of the FE model.

4. Performs the modal frequency response analysis of the combined system.

User interface requirements

You use the new FRFSTIF or FRFFLEX bulk entries to define the dynamic stiffness or dynamic flexibility for the frequency-dependent component. The dynamic stiffness or dynamic flexibility matrix you define should represent the dynamic stiffness or dynamic flexibility expressed at the interface DOF of the attachment grid points. The FRFSTIF and FRFFLEX bulk entries reference the new TABLED6 bulk entries, which contain the tabular data of dynamic stiffness or dynamic flexibility versus frequency in cycles per unit time. You use the new FRFIN case control command to trigger the addition of the dynamic stiffness for the direct-input, frequency-dependent component to the dynamic stiffness of the FE model. When using the FRFFLEX bulk entry, you can use the FLEXINV parameter to specify the method that the software uses to invert the flexibility data into stiffness data. For more information, see FRFIN, FRFSTIF, FRFFLEX, and TABLED6.

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FRFIN

Frequency-Dependent Frequency Response Function Matrix Input

Selects FRFSTIF, FRFFLEX, or FRFOTM bulk entries to define frequency-dependent frequency response function matrices.

FORMAT:

EXAMPLES: SET 99=230,231,233 FRFIN=99

DESCRIBERS:

Describer Meaning

ALL Select all FRFSTIF, FRFFLEX, and FRFOTM bulk entries.

n Set identification number of a previously appearing SET command. Only FRFSTIF, FRFFLEX, and FRFOTM bulk entries with identification numbers that appear on this SET command are selected. (Integer>0)

NONE No FRFSTIF, FRFFLEX, and FRFOTM bulk entries are selected. (Default)

REMARKS: 1. The FRFIN command must be included above any subcases.

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FRFSTIF

Direct-Input, Frequency-Dependent Component, Stiffness Entry

Defines the dynamic stiffness matrix at grid and scalar points for a frequency-dependent component in a frequency response analysis. The matrix is defined by a single header entry and a column entry for each column in the matrix. The matrix must be square. The numerical data that defines the dynamic stiffness vs. frequency is contained in TABLED6 bulk entries. The dynamic stiffness data on the TABLED6 bulk entries can be defined in terms of force per unit displacement, velocity, or acceleration, or moment per unit angular displacement, velocity, or acceleration.

HEADER ENTRY FORMAT:

1 2 3 4 5 6 7 8 9 10 FRFSTIF ID "0" TYPE SYMFLAG LSCALE FSCALE PSCALE QSCALE

COLUMN 1 FORMAT:

FRFSTIF ID GRID1 COMP1 GRID1 COMP1 TID11 GRID2 COMP2 TID21 GRID3 COMP3 TID31 -etc.-

COLUMN 2 FORMAT:

FRFSTIF ID GRID2 COMP2 GRID1 COMP1 TID12 GRID2 COMP2 TID22 GRID3 COMP3 TID32 -etc.-

COLUMN "N" FORMAT:

FRFSTIF ID GRIDn COMPn GRID1 COMP1 TID1n GRID2 COMP2 TID2n GRID3 COMP3 TID3n -etc.-

EXAMPLE: The following example represents a 4 x 4 unsymmetric dynamic stiffness matrix for a component that is connected to the residual structure at grid 80 (components 1 and 3) and grid 200 (components 2 and 3). Assume the unit basis of the FE model and the FRFSTIF are identical.

FRFSTIF 101 0 VELO 1 FRFSTIF 101 80 1 80 1 11 80 3 21 200 2 31 200 3 41

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FRFSTIF 101 80 3 80 1 12 80 3 22 200 2 32 200 3 42 FRFSTIF 101 200 2 80 1 13 80 3 23 200 2 33 200 3 43 FRFSTIF 101 200 3 80 1 14 80 3 24 200 2 34 200 3 44

FIELDS:

Field Contents ID Unique identification number. (Integer > 0) TYPE Type of data in TABLED6 bulk entries. See Remarks 3 and 4. (Integer = 1, 2, or 3, or character: DISP, VELO, or ACCE; Default = 1) TYPE = 1 or DISP for force per unit displacement vs. frequency or moment per unit angular displacement vs. frequency TYPE = 2 or VELO for force per unit velocity vs. frequency or moment per unit angular velocity vs. frequency TYPE = 3 or ACCE for force per unit acceleration vs. frequency or moment per unit angular acceleration vs. frequency SYMFLAG Symmetry flag. See Remark 5. (Integer = 0 or 1; Default = 0) SYMFLAG = 0 for a symmetric matrix SYMFLAG = 1 for an unsymmetric matrix LSCALE Length scaling factor. See Remark 6. (Real > 0.0; Default = 1.0) FSCALE Force scaling factor. See Remark 6. (Real > 0.0; Default = 1.0) PSCALE Pressure scaling factor. See Remark 6. (Real > 0.0; Default = 1.0) QSCALE Acoustic source strength scaling factor. See Remark 6. (Real > 0.0; Default = 1.0) GRIDi Identification number of the ith connection grid or scalar point and component combination. See Remark 7. (Integer > 0; No default) COMPi Component of the connection grid or scalar point listed in the GRIDi field. (Any one of the integers 1 through 6 for structural grid points; 1 for fluid grid points; 0, 1, or blank for scalar points; see Remark 8 for default behavior) TIDij Identification number of TABLED6 bulk entry that gives the stiffness, kij. See Remark 9. (Integer > 0; No default)

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REMARKS: 1. The FRFIN case control command references FRFSTIF bulk entries.

2. FRFSTIF and FRFFLEX bulk entries cannot have the same identification number.

3. The software uses data expressed in terms of force per unit displacement or moment per unit angular displacement for dynamic stiffness. However, the software permits the data in TABLED6 bulk entries to be expressed in terms of force per unit displacement, velocity, or acceleration, or moment per unit angular displacement, velocity or acceleration. Thus, if the TABLED6 data is expressed in terms of force per unit velocity, force per unit acceleration, moment per unit angular velocity, or moment per unit angular acceleration, the software performs the following conversions to obtain data expressed in terms of force per unit displacement or moment per unit angular displacement: • If TYPE = 2 or VELO, the software multiplies the tabular data by iω.

• If TYPE = 3 or ACCE, the software multiplies the tabular data by -ω2.

4. Angular measures must be in radians and the unit of time used to define velocity, acceleration, angular velocity, and angular acceleration must be the same as the unit of time used to define frequency. For example, for moment per unit angular velocity vs. frequency data, if the unit of time is seconds, angular velocity must be in rad/sec and the frequency must be in Hz.

5. If SYMFLAG = 0, specify entries for the lower tridiagonal of the matrix only.

6. Use the LSCALE, FSCALE, PSCALE, and QSCALE fields to convert the units of the FRFSTIF to the units of the FE model. If TYPE = 2 or 3, the software converts the TABLED6 data to force per unit displacement or moment per unit angular displacement prior to unit conversion. The relationship between the FRFSTIF units, FE model units, and the scaling factors are as follows:

LFE model = LSCALE · LFRFSTIF

FFE model = FSCALE · FFRFSTIF

PFE model = PSCALE · PFRFSTIF

QFE model = QSCALE · QFRFSTIF For example, suppose that the FE model requires the units for dynamic stiffness to be N/mm. If the FRFSTIF data is in lbf/in, use LSCALE = 25.4 and FSCALE = 4.448. As a second example, suppose that the FE model requires the units for dynamic stiffness to be N-mm/rad. If the FRFSTIF data is in lbf-in/rad, use LSCALE = 25.4 and FSCALE = 4.448. After the software performs the units conversion, it adds the values to the dynamic stiffness of the model.

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7. Only DOF that connect the direct-input, frequency-dependent component to the residual structure are valid GRIDi and COMPi combinations.

8. If the COMPi field corresponds to a GRIDi field that references a structural grid point, you must specify a component number in the COMPi field. If the COMPi field corresponds to a GRIDi field that references a fluid grid point, you must enter "1" in the COMPi field. If the COMPi field corresponds to a GRIDi field that references a scalar point, you can enter "0" or "1" in the COMPi field or leave the COMPi field blank.

th 9. Stiffness, kij, represents the contribution to the force at the i grid or scalar point and component combination that results from a unit displacement, velocity, or acceleration at the jth grid or scalar point and component combination.

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FRFFLEX

Direct-Input, Frequency-Dependent Component, Flexibility Entry

Defines the dynamic flexibility matrix at grid and scalar points for a frequency-dependent component in a frequency response analysis. The matrix is defined by a single header entry and a column entry for each column in the matrix. The matrix must be square. The numerical data that defines the dynamic flexibility vs. frequency is contained in TABLED6 bulk entries. The dynamic flexibility data on the TABLED6 bulk entries can be defined in terms of displacement, velocity, or acceleration per unit force, or angular displacement, velocity, or acceleration per unit moment.

HEADER ENTRY FORMAT:

1 2 3 4 5 6 7 8 9 10 FRFFLEX ID "0" TYPE SYMFLAG LSCALE FSCALE PSCALE QSCALE EPS

COLUMN 1 FORMAT:

FRFFLEX ID GRID1 COMP1 GRID1 COMP1 TID11 GRID2 COMP2 TID21 GRID3 COMP3 TID31 -etc.-

COLUMN 2 FORMAT:

FRFFLEX ID GRID2 COMP2 GRID1 COMP1 TID12 GRID2 COMP2 TID22 GRID3 COMP3 TID32 -etc.-

COLUMN "N" FORMAT:

FRFFLEX ID GRIDn COMPn GRID1 COMP1 TID1n GRID2 COMP2 TID2n GRID3 COMP3 TID3n -etc.-

EXAMPLE: The following example represents a 4 x 4 unsymmetric dynamic flexibility matrix for a component that is connected to the residual structure at grid 80 (components 1 and 3) and grid 200 (components 2 and 3). Assume the unit basis of the FE model and the FRFFLEX are identical.

FRFFLEX 101 0 VELO 1 FRFFLEX 101 80 1 80 1 11 80 3 21

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200 2 31 200 3 41 FRFFLEX 101 80 3 80 1 12 80 3 22 200 2 32 200 3 42 FRFFLEX 101 200 2 80 1 13 80 3 23 200 2 33 200 3 43 FRFFLEX 101 200 3 80 1 14 80 3 24 200 2 34 200 3 44

FIELDS:

Field Contents ID Unique identification number. (Integer > 0) TYPE Type of data in TABLED6 bulk entries. See Remarks 3 and 4. (Integer = 1, 2, or 3, or character: DISP, VELO, or ACCE; Default = 1) TYPE = 1 or DISP for displacement per unit force vs. frequency or angular displacement per unit moment vs. frequency TYPE = 2 or VELO for velocity per unit force vs. frequency or angular velocity per unit moment vs. frequency TYPE = 3 or ACCE for acceleration per unit force vs. frequency or angular acceleration per unit moment vs. frequency SYMFLAG Symmetry flag. See Remark 5. (Integer = 0 or 1; Default = 0) SYMFLAG = 0 for a symmetric matrix SYMFLAG = 1 for an unsymmetric matrix LSCALE Length scaling factor. See Remark 6. (Real > 0.0; Default = 1.0) FSCALE Force scaling factor. See Remark 6. (Real > 0.0; Default = 1.0) PSCALE Pressure scaling factor. See Remark 6. (Real > 0.0; Default = 1.0) QSCALE Acoustic source strength scaling factor. See Remark 6. (Real > 0.0; Default = 1.0) EPS Filter for normalized singular values. See Remark 7. (Real > 0.0; Default= 1.0E-11) GRIDi Identification number of the ith connection grid or scalar point and component combination. See Remark 8. (Integer > 0; No default)

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Field Contents COMPi Component of the connection grid or scalar point listed in the GRIDi field. (Any one of the integers 1 through 6 for structural grid points; 1 for fluid grid points; 0, 1, or blank for scalar points; see Remark 9 for default behavior) TIDij Identification number of TABLED6 bulk entry that gives the flexibility, cij. See Remark 10. (Integer > 0; No default)

REMARKS: 1. The FRFIN case control command references FRFFLEX bulk entries.

2. FRFFLEX and FRFSTIF bulk entries cannot have the same identification number.

3. The software uses data expressed in terms of displacement per unit force or angular displacement per unit moment for dynamic flexibility. However, the software permits the data in TABLED6 bulk entries to be expressed in terms of displacement, velocity, or acceleration per unit force, or angular displacement, velocity or acceleration per unit moment. Thus, if the TABLED6 data is expressed in terms of velocity per unit force, acceleration per unit force, angular velocity per unit moment, or angular acceleration per unit moment, the software performs the following conversions to obtain data expressed in terms of displacement per unit force or angular displacement per unit moment: • If TYPE = 2 or VELO, the software divides the tabular data by iω.

• If TYPE = 3 or ACCE, the software divides the tabular data by -ω2.

4. Angular measures must be in radians and the unit of time used to define velocity, acceleration, angular velocity, and angular acceleration must be the same as the unit of time used to define frequency. For example, for angular velocity per unit moment vs. frequency data, if the unit of time is seconds, angular velocity must be in rad/sec and the frequency must be in Hz.

5. If SYMFLAG = 0, specify entries for the lower tridiagonal of the matrix only.

6. Use the LSCALE, FSCALE, PSCALE, and QSCALE fields to convert the units of the FRFFLEX to the units of the FE model. If TYPE = 2 or 3, the software converts the TABLED6 data to displacement per unit force or angular displacement per unit moment prior to unit conversion. The relationship between the TABLED6 units, frequency response analysis units, and the scaling factors are as follows:

LFE model = LSCALE · LFRFFLEX

FFE model = FSCALE · FFRFFLEX

PFE model = PSCALE · PFRFFLEX

QFE model = QSCALE · QFRFFLEX

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For example, suppose that the FE model requires the units for dynamic flexibility to be mm/N. If the FRFFLEX data is in in/lbf, use LSCALE = 25.4 and FSCALE = 4.448. As a second example, suppose that the FE model requires the units for dynamic flexibility to be rad/N-mm. If the FRFFLEX data is in rad/lbf-in, use LSCALE = 25.4 and FSCALE = 4.448. After the software performs the units conversion, it inverts the direct input flexibility matrix to find the corresponding values for stiffness. It then adds the stiffness values to the dynamic stiffness of the model.

7. The software uses the EPS value when singular value decomposition is selected to invert the dynamic flexibility matrix into a dynamic stiffness matrix. Because the dynamic flexibility matrix may be rank deficient, the software removes near-zero singular values prior to inversion. To do so, after the software calculates the eigenvalues, it normalizes them with respect to the eigenvalue that has the largest value. It then removes any eigenvalue whose normalized value is less than the EPS value. To select singular value decomposition as the inversion method, specify PARAM,FLEXINV,SVD.

8. Only DOF that connect the direct-input, frequency-dependent component to the residual structure are valid GRIDi and COMPi combinations.

9. If the COMPi field corresponds to a GRIDi field that references a structural grid point, you must specify a component number in the COMPi field. If the COMPi field corresponds to a GRIDi field that references a fluid grid point, you must enter "1" in the COMPi field. If the COMPi field corresponds to a GRIDi field that references a scalar point, you can enter "0" or "1" in the COMPi field or leave the COMPi field blank.

10. Flexibility, cij, represents the contribution to the displacement, velocity, or acceleration at the ith grid or scalar point and component combination that results from a unit force at the jth grid or scalar point and component combination.

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TABLED6

Dynamic Load Tabular Function, Form 6

Defines a tabular function of the form w(x) = u(x) + iv(x) or w(x) = u(x) eiv(x). | | FORMAT:

1 2 3 4 5 6 7 8 9 10 TABLED6 TID TYPE EXTRAP x1 u1 v1 x2 u2 v2 -etc.- “ENDT”

EXAMPLE:

TABLED6 101 MP 1 10.0 2.9 16.5 20.0 5.2 93.0 30.0 4.9 132.0 40.0 4.1 108.0 ENDT

FIELDS:

Field Contents TID Unique table identification number. See Remark 1. (Integer > 0) TYPE Complex format of response data. (Character: RI or MP; Default = RI) TYPE = RI for real / imaginary TYPE = MP for magnitude / phase EXTRAP Extrapolation option. See Remark 4. (Integer = 0 or 1; Default = 0) EXTRAP = 0 to extrapolate the two starting data points to obtain the table lookup when x < xi, and extrapolate the two ending data points to obtain the table lookup when x > xi EXTRAP = 1 to use the value of the table field at the starting data point for the table lookup when x < xi, and use the value of the table field at the ending data point for the table lookup when x > xi xi Tabular values of the independent variable. (Real ≥ 0; No default) ui Real part of the dependent variable if TYPE = RI. (Real; Default = 0.0) Magnitude of the dependent variable if TYPE = MP. (Real ≥ 0.0; Default = 0.0) vi Imaginary part of the dependent variable if TYPE = RI. (Real; Default = 0.0) Phase of the dependent variable in degrees if TYPE = MP. (Real; Default = 0.0)

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Field Contents “ENDT” Flag indicating the end of the table.

REMARKS: 1. The TID must be unique for all TABLEDi bulk entries.

2. xi must be in either ascending or descending order, but not both.

3. Discontinuities are not allowed. See Figure 2-1.

4. When EXTRAP = 0, the tabular data for the two starting or ending points are linearly extrapolated to obtain values of x that are outside the range of the table. See Figure 2-1. Warning messages are not issued if the tabular data is input incorrectly.

Figure 2-1. Example of Table Extrapolation and Discontinuity

5. At least one continuation entry must be present.

6. Any (xi,ui,vi) combination is ignored by placing “SKIP” in one of the three fields.

7. The end of the table is indicated by the existence of “ENDT” in the field following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag “ENDT”.

8. TABLED6 interpolates the tabular data as follows:

a. If TYPE = RI, the tabular data is converted to magnitude and phase.

b. The magnitudes are linearly interpolated to obtain the lookup value.

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c. The phase angles are linearly interpolated to obtain the lookup value. For this calculation the software uses the smallest subtended angle between the phase angles that are used in the interpolation calculation.

For example, suppose a TABLED6 bulk entry is defined as follows: TABLED6 100 MP 1 + 10.0 2.9 16.5 20.0 5.2 93.0 + 30.0 4.9 132.0 40.0 4.1 326.0 ENDT The lookup value for the magnitude at x = 27.5 is:

The lookup value for the phase angle at x = 27.5 is:

The lookup value for the magnitude at x = 35.0 is:

At x = 35.0, the smallest subtended angle between 132.0° and 326° is 166.0°. Thus, the lookup value for the phase at x = 35.0 is:

9. If xi is frequency, it must be measured in cycles per unit time.

Output transformation matrices for frequency response analysis During results recovery in a SOL 108 or 111 frequency response analysis, the software can now calculate results for grid and scalar points that are not part of the FE model. In a structural frequency response analysis, the results for these points can be linear combinations of: • Displacement results from the FE solve.

• Time derivatives of the displacement results from the FE solve.

• Forces that the software calculates from an FRFSTIF or FRFFLEX bulk entry and the displacement results from the FE solve.

For an acoustic frequency response analysis, the results for these points can be linear combinations of: • Pressure results from the FE solve.

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To get these additional results, you use tabular data to define a frequency-dependent output transformation matrix (OTM) that the software uses to combine the results of the FE solve. The OTM relationship can be expressed mathematically as:

where: {x(ω)} N x 1 input vector of values that are derived from the results of the FE solve [OTM(ω)] M x N output transformation matrix {y(ω)} M x 1 output vector that the software calculates during results recovery Typically, the tabular data that you use to define the OTM is obtained through physical testing. For a SOL 111 modal frequency response analysis, the software performs the OTM calculations after it transforms the results of the FE solve to physical coordinates. As an example of how you might use this new capability, consider performing a frequency response analysis on a model that includes a direct-input, frequency-dependent component that is defined by an FRFSTIF or FRFFLEX bulk entry. When you perform such an analysis, the only results that the software calculates for the component during the FE solve are the responses at the DOF that connect the component to the FE model. To obtain results for other points on the component, you can use the new FRFOTM bulk entry to define an OTM that relates the results at DOF in the FE model to results at the other points on the component. During results recovery, the software uses the OTM and the results of the FE solve to calculate results for these points. You can then assign a physical meaning to the results and use them in post-processing.

OTM in structural frequency response analysis

In a structural frequency response analysis, you can specify displacements, velocities, and accelerations for any DOF in the FE model to populate {x(ω)}. If you are using the OTM capability in conjunction with a direct-input, frequency-dependent component that is defined by an FRFSTIF or FRFFLEX bulk entry, you can also populate {x(ω)} with loads for DOF that connect the direct-input, frequency-dependent component to the FE model. The software calculates velocities and accelerations from the displacements. Because the motion is harmonic, the velocity and acceleration are related to the displacement as follows: • For velocity:

• For acceleration:

where: u Displacement result from the FE solve ω Frequency in radians per unit time

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Because the unit of length for the OTM entries may differ from the unit of length used in the FE model, you can define a length scaling factor (LSCALE field on the FRFOTM bulk entry) that the software uses to convert the displacement results from the FE model unit of length to the OTM unit of length. For example, suppose unit of length in the FE model is mm and the unit of length in the OTM is m. For this case, you enter 1000.0 in the LSCALE field of the FRFOTM bulk entry. When {x(ω)} includes load entries, the software calculates the loads from the FRFSTIF matrix (or the inverse of the FRFFLEX matrix) and the displacements as follows:

Note The inverse of an FRFFLEX matrix is equivalent to an FRFSTIF matrix. Thus, the remainder of this topic refers to the FRFSTIF matrix only.

Because the unit of length for the FRFSTIF matrix may differ from the unit of length used in the FE model, you can define a length scaling factor (LSCALE field on the FRFSTIF bulk entry) that the software uses to convert the displacement results from the FE model unit of length to the FRFSTIF unit of length. For example, suppose unit of length in the FE model is mm and the unit of length in the FRFSTIFF is inches. For this case, you enter 25.4 in the LSCALE field of the FRFSTIF bulk entry. In addition, the unit of force obtained from:

may not be the same as the unit of force used in the OTM calculation. Thus, you can define a force scaling factor (FSCALE field on the FRFOTM bulk entry) that the software uses to convert the force units of {f(ω)} to the force units of the OTM. For example, suppose that the OTM needs the unit of force for {f(ω)} to be N and the unit of force in the FRFSTIFF is lbf. For this case, you enter 4.448 in the FSCALE field of the FRFOTM bulk entry.

Note When a model includes a direct-input, frequency-dependent component that is defined by an FRFSTIF bulk entry, during the FE solve, the software uses the value in the FSCALE field of the FRFSTIF bulk entry to convert the force units of the FRFSTIF entries to the force unit of the FE model.

OTM in acoustic frequency response analysis In an acoustic frequency response analysis, you can specify pressure for any DOF in the FE model to populate {x(ω)}. Because the unit of pressure for the OTM entries may differ from the unit of pressure used in the FE model, you can define a pressure scaling factor (PSCALE field on the FRFOTM bulk entry) that the software uses to convert the pressure results from the FE model unit of pressure to the OTM unit of pressure.

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For example, suppose the unit of pressure in the FE model is Pa and the unit of pressure in the OTM is psi. For this case, you enter 6895.0 in the PSCALE field of the FRFOTM bulk entry.

Interpreting OTM results By default, the software does not assign physical meaning to the values in {y(ω)}. For example, if the values in the OTM represent stiffness, and the values in {x(ω)} represent displacement, you might assume that the software interprets the result of the OTM calculation to be force, but it does not. You can use the FRFOMAP bulk entry to assign a physical meaning to the values in {y(ω)}. • In a structural frequency response analysis, you can designate values in {y(ω)} to be displacements, velocities, accelerations, or forces. If an entry in {y(ω)} is associated with a rotational DOF, the software automatically uses the rotational analog. That is, angular displacement for displacement, moment for force, and so on.

• In an acoustic frequency response analysis, you can designate values in {y(ω)} to be pressures only.

FRFOTM bulk entry To define an OTM, use the new FRFOTM bulk entry as follows: • Reference TABLED6 bulk entries that contain the tabular data that defines how each entry in the OTM varies as a function of frequency in cycles per unit time. The TIDij fields on the FRFOTM bulk entry reference the TABLED6 bulk entries.

• Specify the DOF and type combinations that comprise {x(ω)}. The IGRIDj and ICOMPj fields on the FRFOTM bulk entry specify the DOF. The TYPEj field on the FRFOTM bulk entry specifies whether to use the displacement, velocity, acceleration, or load for the DOF.

• Specify the DOF with which the values in {y(ω)} are associated. The OGRIDi and OCOMPi fields on the FRFOTM bulk entry specify these DOF.

• Define the scaling factors that the software uses to convert the units for the displacement, force, pressure, and acoustic source strength from those used in the OTM to those used in the FE model as follows:

FRFOMAP bulk entry To assign physical meaning to values in {y(ω)}, use the new FRFOMAP bulk entry as follows: • Specify the physical meaning in the YTYPEi field.

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• For each YTYPEi, specify all the YGRIDj and YCOMPj combinations to which to assign that physical meaning type.

FRFIN case control command

To trigger the software to use the FRFOTM bulk entry during results recovery, include the new FRFIN case control command in your input file.

Example problem using an OTM

Suppose you perform a structural frequency response analysis that includes a direct-input, frequency-dependent component defined by an FRFSTIF (or FRFFLEX) bulk entry and you want the software to calculate the following results:

where:

u1, u2,...... , u5 Displacements calculated during the FE solve

f2, f5 Loads calculated during results recovery from the FRFSTIF (or FRFFLEX) matrix and displacements calculated during the FE solve The following table maps each displacement to a grid point and displacement component combination.

Displacement Grid point Component u1 100 3 (1) u2 100 2 u3 108 1 u4 105 3 (1) u5 112 1 (1) DOF that connect the direct-entry, frequency-dependent component to the FE model

The following table maps each result to a grid point and displacement component combination.

Result Grid point Component y1 104 2 y2 121 3 y3 108 2

Note Any grid point and displacement component combination that is used as an input DOF on an FRFOTM bulk entry cannot be used as an output DOF on any FRFOTM bulk entry in the input file. In addition, the output from one OTM cannot be the input to another OTM.

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Assuming the units of the FE model match the units of the OTM matrix, the following table outlines how you specify the FRFOTM bulk entries. In the actual coding of the FRFOTM bulk entries, the cells that contain real values like 2.3, 3.7, and so on, actually contain integer identification numbers of TABLED6 bulk entries that contain the numerical data.

FRFOTM 10 0 FRFOTM 10 100 3 DISP 104 2 2.3 121 3 3.7 FRFOTM 10 100 3 VELO 104 2 3.0 FRFOTM 10 100 2 DISP 104 2 -4.5 FRFOTM 10 100 2 VELO 121 3 6.0 FRFOTM 10 100 2 LOAD 108 2 4.1 FRFOTM 10 108 2 DISP 108 2 6.3 FRFOTM 10 105 3 ACCE 121 3 8.3 FRFOTM 10 112 1 ACCE 108 2 -2.8 FRFOTM 10 112 1 LOAD 104 2 1.6

Suppose that you want to define y1 as a displacement, y2 as an acceleration, and y3 as a load. To do so, you can define an FRFOMAP bulk entry as follows:

FRFOMAP 10 DISP 104 2 ACCE 121 3 LOAD 108 2

Additional resources

For more information, see the new FRFOTM and FRFOMAP bulk entries and the new FRFIN case control command.

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FRFOTM

Output Transformation Matrix Definition

Defines a frequency-dependent output transformation matrix (OTM) that the software uses during results recovery to calculate results for grid and scalar points that are not part of the FE model as follows:

where {x(ω)} are values derived from the results of the FE solve. The OTM is defined by a single header entry and a column entry for each column.

HEADER ENTRY FORMAT:

1 2 3 4 5 6 7 8 9 10 FRFOTM ID "0" LSCALE FSCALE PSCALE QSCALE

COLUMN 1 FORMAT:

FRFOTM ID XGRID1 XCOMP1 XTYPE1 YGRID1 YCOMP1 TID11 YGRID2 YCOMP2 TID21 YGRID3 YCOMP3 TID31 -etc.-

COLUMN 2 FORMAT:

FRFOTM ID XGRID2 XCOMP2 XTYPE2 YGRID1 YCOMP1 TID12 YGRID2 YCOMP2 TID22 YGRID3 YCOMP3 TID32 -etc.-

COLUMN "N" FORMAT:

FRFOTM ID XGRIDn XCOMPn XTYPEn YGRID1 YCOMP1 TID1n YGRID2 YCOMP2 TID2n YGRID3 YCOMP3 TID3 -etc.-

Note The column format for each non-null column begins with an XGRIDj, XCOMPj, and XTYPEj combination. The continuation of the column format lists all of the YGRIDi and YCOMPi combinations that the XGRIDj, XCOMPj, and XTYPEj combination contributes to. YGRIDi and YCOMPi combinations that do not contribute can be omitted from the list. The order that the YGRIDi and YCOMPi combinations are listed is arbitrary.

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EXAMPLE: The following example represents a 2 row by 4 column OTM where the output at grid 100 (component 2) and grid 150 (component 3) are calculated as a linear combination of the displacements at grid 80 (components 1 and 3) and the velocities at grid 200 (components 2 and 3). Assume that the unit basis of the FE model and the OTM are identical.

FRFOTM 101 0 FRFOTM 101 80 1 DISP 100 2 11 150 3 21 FRFOTM 101 80 3 DISP 100 2 12 150 3 22 FRFOTM 101 200 2 VELO 100 2 13 150 3 23 FRFOTM 101 200 3 VELO 100 2 14 150 3 24

FIELDS:

Field Contents ID Unique identification number. (Integer > 0) LSCALE Length scaling factor. See Remark 4. (Real > 0.0; Default = 1.0) FSCALE Force scaling factor. See Remark 4. (Real > 0.0; Default = 1.0) PSCALE Pressure scaling factor. See Remark 4. (Real > 0.0; Default = 1.0) QSCALE Acoustic source strength scaling factor. See Remark 4. (Real > 0.0; Default = 1.0) XGRIDj Identification number of the jth input grid or scalar point. See Remark 5. (Integer > 0; No default) XCOMPj Component of the grid or scalar point listed in the XGRIDj field. See Remark 5. (Any one of the integers 1 through 6 for structural grid points; 1 for fluid grid points; 0, 1, or blank for scalar points; see Remark 6 for default behavior) XTYPEj Result type of the XGRIDj and XCOMPj combination. See Remarks 8 and 9. (Integer = 1, 2, or 3, or character; Default = 1) = 0 or LOAD for force or acoustic source strength = 1 or DISP for displacement or pressure = 2 or VELO for velocity = 3 or ACCE for acceleration YGRIDi Identification number of the ith output grid or scalar point. See Remark 5. (Integer > 0; No default)

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Field Contents YCOMPi Component of the grid or scalar point listed in the YGRIDi field. See Remark 5. (Any one of the integers 1 through 6 for structural grid points; 1 for fluid grid points; 0, 1, or blank for scalar points; see Remark 10 for default behavior) TIDij Identification number of TABLED6 bulk entry that corresponds to the ith output grid or scalar point and component combination, and the jth input grid or scalar point, component, and result type combination. See Remark 7. (Integer > 0; No default)

REMARKS: 1. The FRFIN case control command references FRFOTM bulk entries.

2. Unlike the FRFFLEX and FRFSTIF bulk entries, the FRFOTM bulk entry does not add stiffness to the model. Its only use is to recover results for the DOF specified by YGRIDi and YCOMPi combinations. The intended use for the FRFOTM bulk entry is to recover results for grid or scalar point, component, and result type combinations on a substructure that is defined by FRFFLEX or FRFSTIF bulk entries. However, other applications are possible.

3. The OTM relates the input at XGRIDj, XCOMPj, and XTYPEj combinations to the output at YGRIDi and YCOMPi combinations as follows:

The OTM is an M x N matrix, where M is the total number of YGRIDi and YCOMPi combinations and N is the total number of XGRIDj, XCOMPj, and XTYPEj combinations.

4. Use the LSCALE, FSCALE, PSCALE, and QSCALE fields to convert the units of the FE model to the units of the OTM as follows:

LFE model = LSCALE · LOTM

FFE model = FSCALE · FOTM

PFE model = PSCALE · POTM

QFE model = QSCALE · QOTM For example, enter 1000.0 in the LSCALE field if the unit of length in the FE model is millimeters and the unit of length in the OTM is meters.

5. Any XGRIDj and XCOMPj combination that is used as an input DOF on an FRFOTM bulk entry cannot be used as a YGRIDi and YCOMPi combination on any FRFOTM bulk entry in the input file. In addition, the output from one OTM cannot be the input to another OTM.

6. If the XCOMPj field corresponds to a XGRIDj field that references a structural grid point, you must specify a component number in the XCOMPj field.

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If the XCOMPj field corresponds to a XGRIDj field that references a fluid grid point, you must enter "1" in the XCOMPj field. If the XCOMPj field corresponds to a XGRIDj field that references a scalar point, you can enter "0" or "1" in the XCOMPj field or leave the XCOMPj field blank.

7. Angular measures must be in radians and the unit of time used to define velocity, acceleration, angular velocity, and angular acceleration must be the same as the unit of time used to define frequency. For example, for moment per unit angular velocity vs. frequency data, if the unit of time is seconds, angular velocity must be in rad/sec and the frequency must be in Hz.

8. XTYPEj = 0 or LOAD is a valid selection only if a FRFFLEX or FRFSTIF bulk entry with the same ID as the FRFOTM bulk entry is present, and the corresponding XGRIDj and XCOMPj combination are DOF that connect a direct-entry, frequency-dependent component to the FE model.

9. If XTYPEj = 0 or LOAD, the software uses the FRFFLEX or FRFSTIF bulk entry with the same ID as the FRFOTM bulk entry and the displacement results from the FE solve to calculate the load to use in the OTM calculation. If XTYPEj = 1 or DISP, the software uses: • In a structural frequency response analysis, the displacement result from the FE solve.

• In an acoustic frequency response analysis, the pressure result from the FE solve.

If XTYPEj = 2 or VELO, the software uses the displacement result from the FE solve multiplied by iω. If XTYPEj = 3 or ACCE, the software uses the displacement result from the FE solve multiplied by -ω2.

10. If the YCOMPi field corresponds to a YGRIDi field that references a structural grid point, you must specify a component number in the YCOMPi field. If the YCOMPi field corresponds to a YGRIDi field that references a fluid grid point, you must enter "1" in the YCOMPi field. If the YCOMPi field corresponds to a YGRIDi field that references a scalar point, you can enter "0" or "1" in the YCOMPi field or leave the YCOMPi field blank.

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FRFOMAP

Assigns Output Type to FRFOTM Results

Assigns an output type to the results calculated from FRFOTM bulk entries.

FORMAT:

1 2 3 4 5 6 7 8 9 10 FRFOMAP ID YTYPE1 YGRID1 YCOMP1 YGRID2 YCOMP2 YGRID3 YCOMP3 YGRID4 YCOMP4 -etc.- YTYPE2 YGRID1 YCOMP1 YGRID2 YCOMP2 YGRID3 YCOMP3 YGRID4 YCOMP4 -etc.- -etc.-

ALTERNATE FORMAT: Use to assign the same type to all output grid / component combinations.

FRFOMAP ID YTYPE1 "ALL"

EXAMPLE: This is a continuation of the example provided with the FRFOTM bulk entry. The following FRFOMAP defines the output at grid 100 (component 2) as displacement and the output at grid 150 (component 3) as velocity.

FRFOMAP 101 DISP 100 2 VELO 200 3

FIELDS:

Field Contents ID Identification number of the corresponding FRFOTM bulk entry. See Remark 1. (Integer > 0) YTYPEj Type of output. (Integer = 0, 1, 2, 3, or 4, or character; Default = 0) = 0 or NONE for user-defined = 1 or DISP for displacement or pressure = 2 or VELO for velocity = 3 or ACCE for acceleration = 4 or LOAD for load YGRIDi Identification number of the ith output grid or scalar point and component combination. See Remark 2. (Integer > 0; No default)

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Field Contents YCOMPi Component of the grid or scalar point listed in the YGRIDi field. (Any one of the integers 1 through 6 for structural grid points; 1 for fluid grid points; 0, 1, or blank for scalar points; see Remark 3 for default behavior) ALL Assigns the specified YTYPEj to all YGRIDi and YCOMPi combinations in the FRFOTM output.

REMARKS: 1. Although the use of FRFOMAP bulk entries is optional, an FRFOMAP bulk entry can be specified for each FRFOTM bulk entry.

2. Only YGRIDi and YCOMPi combinations that are listed on the corresponding FRFOTM bulk entry are valid entries. The software assigns YTYPE = NONE to any YGRIDi and YCOMPi combinations that are listed on the corresponding FRFOTM bulk entry, but are not listed on the FRFOMAP bulk entry.

3. If the YCOMPi field corresponds to a YGRIDi field that references a structural grid point, you must specify a component number in the YCOMPi field. If the YCOMPi field corresponds to a YGRIDi field that references a fluid grid point, you must enter "1" in the YCOMPi field. If the YCOMPi field corresponds to a YGRIDi field that references a scalar point, you can enter "0" or "1" in the YCOMPi field or leave the YCOMPi field blank.

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Chapter 3: Acoustics

Finite Element Method Adaptive Order (FEMAO)

NX Nastran now supports the Finite Element Method Adaptive Order (FEMAO) method.

Finite Element Method Adaptive Order (FEMAO) is a higher-order polynomial method for acoustic and vibro-acoustic analyses. It provides more accurate results and faster solve times by adapting the computational effort to the complexity of the analysis. You can use FEMAO with SOL 108.

Working principles of the FEMAO method

The FEMAO method adapts each element’s basis of shape functions at each frequency to provide an accurate representation of the acoustic pressure inside the element. The FEMAO method uses:

• Higher-order acoustic shape functions for high frequencies, large elements, or a combination of both.

• Lower-order acoustic shape functions for low frequencies, small elements, or a combination of both.

The order of shape functions in an element can be as high as polynomial order 10. At order 1, an element that uses linear shape functions can span only 1/8 to 1/6 of a wavelength. With the standard (fixed low-order) FEM method, you need 6 to 8 elements per wavelength. The maximum admissible frequency would be x Hz. However, at order 10 with FEMAO, you need only about a 6/10 element per wavelength. The maximum admissible frequency would be 10x Hz. Thus, if you use FEMAO, you can use the same mesh to compute frequencies more than 10 times higher than with standard FEM. The following example shows the same 2D mesh with different element orders for two frequencies:

f = 100Hz f = 1000Hz

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When you use FEMAO, you specify the level of accuracy you want in an NX Nastran adaptation rule. To ensure the chosen accuracy, the FEMAO method chooses the optimal polynomial order of shape functions per element. The order adaptation is based on the following parameters:

Parameter Modeling considerations Solver behavior You can use larger elements for voids and local mesh refinement near geometric boundaries to FEMAO automatically chooses accurately capture the geometric Element size the order per element by taking of the acoustic domain (for the element size into account. example, an engine surface) or where local variations of the fluid properties exist. FEMAO uses lower-order shape functions (lower number DOFs per element) at low You can use larger elements frequencies, and higher-order even if you need to capture a shape functions (higher number Frequency high maximum frequency of DOFs per element) at high interest in the mesh. frequencies. The solver can return the maximum admissible frequency as a quality result. You can define the speed of FEMAO incorporates the sound using the NX Nastran specified speed of sound Local speed of sound material bulk entries MAT10, per element to determine the MAT10C, MATF10C, and element order (shape functions). MATPOR. The FINE adaptation rule uses You can use the NX Nastran more higher-order elements bulk entry ACADAPT to define at lower frequencies, and for Adaptation rule the adaptation rule, and set the the same mesh, the COARSE rule to COARSE, STANDARD, adaptation rule uses more or FINE. lower-order elements at lower frequencies. You can use the NX Nastran FEMAO automatically chooses bulk entry ACORDER to control 1 for the lowest and 10 for the Polynomial order the lowest and highest allowed highest polynomial order unless polynomial order for the entire limits are specified. model.

Shape functions

A large number of polynomial shape functions is required to represent the pressure field within each element. In first-order, linear elements, the number of shape functions and DOFs is the same as the number of physical nodes in the element. In higher-order elements, the number of shape functions and DOFs is much higher. Because FEMAO adapts the order on a per element and per frequency basis, it allows a more efficient representation of the pressure field.

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Note FEMAO uses the hierarchical Lobatto shape functions, which are more flexible and efficient than the Lagrangian shape functions used in standard (low-order) FEM. (For detailed information on shape functions, see Reference.)

The following table outlines typical numbers of shape functions defined on a tetrahedral element as a function of the order. Internal (vertex + Order External (bubble) Total shape functions edge + face) 1 4 0 4 2 10 0 10 3 20 0 20 4 34 1 35 5 52 4 56 6 74 10 84 7 100 20 120 8 130 35 165 9 164 56 220 10 202 84 286

Four types of shape functions are shown below on a tetrahedral element:

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FEMAO benefits

• Accuracy through element order Standard FEM does not adjust the element order (shape functions). In standard FEM, you typically use a single mesh for the full frequency range of the analysis, which results in an over-discretized model at lower frequencies. At higher frequencies, the standard FEM model becomes under-discretized and less accurate. It may even miss the targeted accuracy because no automatic correction is in place.

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FEMAO, however, adjusts the element order automatically, and the model is represented each time with the right number of DOFs for each frequency to reach the desired accuracy.

• Performance through adaptivity An over-discretized model results in longer solve times. In FEMAO, however, the order adaptation for each frequency guarantees the optimal model size and consequently the optimal solve time for each frequency. This yields much faster computation times compared to the fixed number of DOFs approach that standard FEM uses.

Computation by FEMAO as a function of time and frequency

• Performance through shape function efficiency The higher-order shape function basis is also more efficient in capturing the acoustic pressure field within each element compared to a standard first-order or second-order elements-based FEM approach. For example, if you fill a volume with large elements using higher-order shape functions, which results in more DOFs and shape functions in a single element, and then fill the same volume with small elements using first-order or second-order shape functions as in standard FEM, the total number of DOFs to reach the same accuracy is higher for the standard FEM than for the FEMAO method. Thus, FEMAO becomes more efficient as the frequency increases.

• Pre-processing FEMAO allows you to use large elements in the acoustic domain. This results in a lean FEMAO model that contains fewer elements than an equivalent standard FEM model. This also means that you can mesh the model faster in any pre-processor, and a coarser-meshed model improves graphics performance.

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The below images show the differences between a typical FEM mesh, a FEMAO mesh, and a FEMAO mesh with local refinement. For a 1 meter box, all are designed for a frequency of 3000 Hz.

FEM mesh FEMAO mesh FEMAO mesh with local refinement

A coarse mesh may not represent the boundary accurately or provide an accurate solution, so a standard FEM model must use many small elements for an accurate high-frequency solution. In FEMAO, you should ensure that the spatial variations of the geometry, fluid properties (sound velocity and density), and boundary conditions (velocity and admittance) are well represented by the geometrically linear or the quadratic mesh. For this, you can use local refinement.

Example Consider a velocity boundary condition, which is applied as acoustic panel velocity on the fluid mesh, with spatial variations of the order of a centimeter required on two faces of the unit box. The FEM mesh (2) typically yields a poor representation. Therefore, you should use mesh local refinements (3). However, if the vibrations originate from a meshed structural panel next to the free fluid faces, the FEMAO mesh (2) with coarse elements at the fluid structure interface is supported. In this case, the coupling matrix also includes the higher-order DOFs of the coarse fluid elements. The structural mesh must be discretized finely enough to capture the spatial variations in the velocity boundary condition it imposes on the fluid.

Maximum frequency

f • The maximum frequency of a FEMAO mesh is reached when the order of any element Pe is greater than 10. If you assume 8 elements per wavelength for linear elements, the edge size to use is

h < (1/8) * (c0 / fmax) For higher-order elements this becomes f h < (Pe / 8) * (c0 / fmax) This means that the maximum frequency can be estimated by

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where: f o Pe is the order of the element.

o c0 is the speed of sound in the ambient medium.

o h is the element dimension.

However, the Lobatto shape function basis of FEMAO is more efficient compared to standard FEM. This means that at higher orders, fewer DOFs can be used per wavelength to represent the acoustic field accurately. When the ACADAPT adaptation rule is: o Coarse, 2.2 times fewer DOFs can be used per wavelength.

o Standard, 2 times fewer DOFs can be used per wavelength.

o Fine, 1.6 times fewer DOFs can be used per wavelength.

The maximum frequency criterion therefore becomes

Bulk entries When you use FEMAO, make sure that your model uses the correct bulk entries: • For a simple acoustic source, use the new acoustic monopole source ACPOLE1. Do not use ACSRCE.

• For a damping and stiffness absorber, use CAABSF with the new bulk entry PAABSF1. Do not use the CAABSF/PAABSF combination.

• For gluing features, use the new ACTRAD bulk entry to enforce acoustic continuity across two surfaces of acoustic meshes. Do not use BGSET and BGADD.

Note The software ignores unsupported bulk entries.

Workflow 1. Create a SOL 108 acoustic or vibro-acoustic solution.

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2. Set the following bulk entries: a. ACADAPT to invoke the FEMAO solution and to define the adaptation (refinement) rule.

Note The RULE parameter ensures that the numerical error stays within an acceptable range. This allows you to perform and compare multiple solutions with the same mesh, but different RULE values.

b. ACORDER to specify the lowest and highest allowed polynomial order for FEMAO.

Reference

Efficient implementation of high-order finite elements for Helmholtz problems, Hadrien Bériot, Albert Prinn, and Gwénaël Gabard, International Journal for Numerical Methods in Engineering, 2015.

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ACADAPT

Order Adaptation Rule for Acoustics FEM Adaptive Order Solution (FEMAO) Method

Invokes the FEMAO method for both uncoupled acoustic and coupled vibro-acoustic analyses.

FORMAT:

1 2 3 4 5 6 7 8 9 10 ACADAPT RULE

EXAMPLE:

ACADAPT COARSE

FIELDS:

Field Contents RULE Type of adaptation rule. (Character; "COARSE", "STANDARD", or "FINE"; Default = "STANDARD")

REMARKS: 1. ACADAPT is only supported in SOL 108 acoustic or vibro-acoustic analyses.

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ACORDER

Order for Acoustics FEM Adaptive Order (FEMAO) Method

Defines the polynomial order for the FEMAO method.

FORMAT:

1 2 3 4 5 6 7 8 9 10 ACORDER ORDER NUMBER

EXAMPLES:

ACORDER MINIMUM 2

ACORDER MAXIMUM 8

FIELDS:

Field Contents ORDER Type of adaptive order. (Character = "MINIMUM" or "MAXIMUM"). See Remark 3. NUMBER Adaptive order number. (1 ≤ Integer ≤ 10) If ORDER = "MINIMUM", the default value for NUMBER = 1. If ORDER = "MAXIMUM", the default value for NUMBER = 10.

REMARKS: 1. ACORDER is supported in SOL 108 with FEMAO for both uncoupled acoustics and coupled vibro-acoustic analyses.

2. The specified order is applied to the entire model.

3. If ACORDER has no arguments or does not exist, the software uses all of the following arguments: a. ORDER = "MINIMUM" and NUMBER = 1.

b. ORDER = "MAXIMUM" and NUMBER = 10.

Acoustics case control command NX Nastran is expanded to include the new enforced acoustic pressure load with complex data input, panel normal velocity boundary condition, and monopole, dipole, and plane wave sources. Use the new case control command ALOAD to specify these new acoustic loads, boundary condition, and sources. ALOAD can optionally reference a corresponding bulk entry ALOAD. This bulk entry allows you to specify a load combination, but it does not currently support scaling of loads. For detailed information on the new acoustic loads and sources, see the Acoustics User’s Guide.

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ALOAD

Acoustic Load Set Selection

Selects an acoustic load or source to be applied in a frequency response problem.

FORMAT: ALOAD=n

EXAMPLES: ALOAD=57

DESCRIBERS:

Describer Meaning n Set identification of an ALOAD, ACPOLE1, ACPOLE2, ACPLNW, ACPNVEL, or ACPRESS bulk entry. (Integer > 0)

REMARKS: None.

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ALOAD

Acoustic Load Combination with Unit Scale Factors

Defines an acoustic loading condition for frequency response as a linear combination of load sets defined via ACPOLE1, ACPOLE2, ACPLNW, ACPNVEL, and ACPRESS bulk entries.

FORMAT:

1 2 3 4 5 6 7 8 9 10 ALOAD SID L1 L2 L3 L4 L5 L6 L7 L8 L9 L10 L11 L12 L13 -etc.-

EXAMPLE:

ALOAD 200 8 9 200

FIELDS:

Field Contents SID Load set identification number. (Integer > 0) Li Load set identification numbers defined on entry types listed above. (Integer > 0; No default)

REMARKS: 1. Dynamic load sets must be selected in the Case Control section with ALOAD = SID.

2. Load set IDs (Li) must be unique.

3. An ALOAD entry may not reference a set identification number defined by another ALOAD entry.

Monopole, dipole, and plane wave acoustic sources

NX Nastran now supports acoustic monopole, dipole, and plane wave sources in SOL 108 and SOL 111.

Acoustic monopole source

An acoustic monopole is a pulsating sound source that radiates equally in all directions.

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Note The plus sign means that the monopole source expands.

In NX Nastran FEM acoustics, you can create acoustic monopoles:

• Inside the meshed fluid volume at a fluid grid point or inside an element.

• Outside the meshed fluid volume.

The monopole source generates an incident sound field at a location of a distance R due given by

where:

• is the monopole amplitude.

• R is the distance from the source.

• k is the wave number.

The monopole source can also be specified by its volume velocity Qs. The relationship between the monopole amplitude and volume velocity is given by

Another method you can use to specify the monopole source is to use its acoustic power.

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where: • is the fluid density.

• c is the speed of sound.

You use the new bulk entry ACPOLE1 to specify a monopole source. • The bulk entry supports power and monopole amplitude inputs that can be constant or frequency dependent.

• In ACPOLE1, the source location is defined by the coordinate that can be inside or outside of the meshed fluid volume. For sources outside the FEM mesh, you specify an AMLREG on all or part of the free faces of the fluid model. This captures the effect of the monopole incident field inside the fluid domain.

• ACPOLE1 inherits the density and speed of sound from the location of the monopole source. If the source is outside the meshed fluid volume, the fluid properties are acquired by averaging the properties used in those fluid elements that their free faces are used in the definition of the AMLREG.

Acoustic dipole source

The dipole source can be visualized as an oscillating sphere with no deformation as shown in the image below. The fluid near the source moves back and forth to produce sound. Unlike a monopole source, the sound does not radiate equally in all directions.

Also, the dipole source can be visualized as two out-of-phase monopole sources separated by a distance, where one monopole contracts (- sign) and the other one (+ sign) expands. In this case, the dipole generates a sound field that can be written as

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(1) Evaluation point

where: • d is the distance between two out of phase monopole sources.

• r is the line that connects the midpoint between the monopole sources and the evaluation point (1).

• is the angle between the line that connects those monopole sources and the line that connects the evaluation point (1) and the midpoint between the monopole sources.

To specify the dipole source in your simulation, you define the dipole moment Sd where: • S is the source strength.

• d is the direction vector.

You use the new ACPOLE2 bulk entry to specify a dipole source. The bulk entry supports: • The definition of the dipole moment in a coordinate system.

• The source location inside or outside the meshed fluid volume. If the source is outside the meshed fluid volume, you must define an AMLREG bulk entry to account correctly for the incident field from the dipole.

Acoustic plane wave source

A plane wave source generates a plane wave on only one side of the space, in the positive direction of the source vector.

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(1) Incident field (2) Vector (3) Position (4) Non-incident field

The incident acoustic pressure pi due to a plane wave source is

where: • A is the amplitude of the plane wave.

• k is the wave number.

• d is the perpendicular distance from the plane source.

Note • NX Nastran uses surface integration to compute acoustic power. For a monopole source, you can create a spherical microphone mesh that encloses the source, and the software computes the acoustic power on this sphere. This also means that you can define acoustic power for a monopole source. However, for plane waves, you cannot define acoustic power because the plane waves are infinitely large in terms of direction, and the surface integration would result in infinite numbers.

• You can use a preprocessor, such as Pre/Post, to create a collection of discrete plane wave sources equally distributed in space that model an acoustic diffuse field. This collection is usually used for a random vibro-acoustic analysis.

You use the new bulk entry ACPLNW to specify a plane wave acoustic source and define location, direction, and amplitude that can be constant or frequency dependent.

If the monopole, dipole, and plane wave sources are outside of the meshed fluid volume, you must define an AMLREG bulk entry to correctly account for the incident field of these sources inside the meshed fluid volume. Also, in this case, a new incident-scattered formulation is used in NX Nastran FEM acoustics.

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ACPOLE1

Acoustic Monopole Source

Defines an acoustic monopole source

FORMAT:

1 2 3 4 5 6 7 8 9 10 ACPOLE1 SID TYPE FORM A TR/TM TI/TP CID X1 X2 X3

EXAMPLES:

ACPOLE1 200 POWER PHASE 2.0 300 60.0

FIELDS:

Field Contents SID Load set identification number. (Integer > 0) TYPE Monopole source type. (Character; "AMP" or "POWER"; Default = AMP) If TYPE = AMP, define the monopole source in terms of source amplitude. If TYPE = POWER, define the monopole source in terms of power. FORM Format to define the monopole amplitude or power. (Character; "REAL" or "PHASE"; Default = REAL) If FORM = REAL, define the monopole amplitude in rectangular format (real and imaginary). If FORM = PHASE, define the monopole amplitude or power in polar format (magnitude and phase). See Remark 3. A Scale factor for TR, TI, or TM. (Real; Default = 1.0) TR Real part of the amplitude of monopole source. (Real or Integer; Default = 0.0) For a constant amplitude, enter a real value. For a frequency-dependent amplitude, enter the ID of the TABLEDi bulk entry that contains the amplitude as a function of frequency.

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Field Contents TM Magnitude of the amplitude or power of monopole source. (Real or Integer; Default = 0.0) For a constant amplitude or power, enter a real value. For a frequency-dependent amplitude or power, enter the ID of the TABLEDi bulk entry that contains the amplitude as a function of frequency. TI Imaginary part of the amplitude of monopole source. (Real or Integer; Default = 0.0) For a constant amplitude, enter a real value. For a frequency-dependent amplitude, enter the ID of the TABLEDi bulk entry that contains the amplitude as a function of frequency. TP Phase angle in degrees of the amplitude or the power of monopole source. (Real or Integer; Default = 0.0) For a constant amplitude or power, enter a real value. For a frequency-dependent amplitude or power, enter the ID of the TABLEDi bulk entry that contains the amplitude as a function of frequency. CID Identification number of coordinate system in which the location of monopole is defined. (Integer ≥ 0 or blank; Default = blank). See Remark 4. X1, X2, X3 Location of monopole source in coordinate system CID. (Real; Default= 0.0)

REMARKS: 1. ACPOLE1 is supported by the FEM Adaptive Order (FEMAO) method.

2. The SID must be unique with respect to ALOAD.

3. If TYPE = POWER, the FORM can only be defined as PHASE.

4. A CID of zero or blank (the default) references the basic coordinate system.

5. You can also define a monopole source with the ACSRCE bulk entry. However, ACSRCE is not supported by FEMAO.

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ACPOLE2

Acoustic Dipole Source

Defines an acoustic dipole source

FORMAT:

1 2 3 4 5 6 7 8 9 10 ACPOLE2 SID FORM CID1 X1 X2 X3 CID2 A1 TR1/TM1 TI1/TP1 A2 TR2/TM2 TI2/TP2 A3 TR3/TM3 TI3/TP3

EXAMPLES:

ACPOLE2 300 REAL 2 1.0 1.0 1.0 0.1 0.1 0.2 0.2

FIELDS:

Field Contents SID Load set identification number. (Integer > 0) FORM Format to define the dipole moment. (Character; "REAL" or "PHASE"; Default = REAL) If FORM = REAL, define the dipole moment in rectangular format (real and imaginary). If FORM = PHASE, define the dipole moment in polar format (magnitude and phase). CID1 Identification number of coordinate system in which the location of dipole is defined. (Integer ≥ 0 or blank; Default = blank). See Remark 3. X1, X2, X3 Location of dipole source in coordinate system CID1. (Real; Default = 0.0) CID2 Identification number of coordinate system in which the dipole moment is defined. (Integer ≥ 0 or blank; Default = blank). See Remark 3. Ai The scale factor for TRi, TIi, or TMi. (Real; Default = 1.0) TRi Real part of dipole moment in the coordinate system CID2. (Real or Integer; Default = 0.0) For a constant moment, enter a real value. For a frequency-dependent moment, enter the ID of the TABLEDi bulk entry that contains the moment as a function of frequency.

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Field Contents TMi Magnitude of dipole moment in the coordinate system CID2. (Real or Integer; Default = 0.0) For a constant moment, enter a real value. For a frequency-dependent moment, enter the ID of the TABLEDi bulk entry that contains the moment as a function of frequency. TIi Imaginary part of dipole moment in the coordinate system CID2. (Real or Integer; Default = 0.0) For a constant moment, enter a real value. For a frequency-dependent moment, enter the ID of the TABLEDi bulk entry that contains the moment as a function of frequency. TPi Phase angle in degrees of dipole moment. (Real or Integer; Default = 0.0) For a constant phase angle, enter a real value. For a frequency-dependent phase angle, enter the ID of the TABLEDi bulk entry that contains the phase angle as a function of frequency.

REMARKS: 1. ACPOLE2 is supported by the FEM Adaptive Order (FEMAO) method.

2. The SID must be unique with respect to ALOAD.

3. A CID1 or CID2 of zero or blank (the default) references the basic coordinate system.

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ACPLNW

Acoustic Plane Wave Source

Defines an acoustic plane wave source. FORMAT:

1 2 3 4 5 6 7 8 9 10 ACPLNW SID FORM A TR/TM TI/TP CID1 X1 X2 X3 CID2 N1 N2 N3

EXAMPLES:

ACPLNW 200 PHASE 0.5 20. 2 100.0 0.0 0.0 3 0.0 1.

FIELDS:

Field Contents SID Load set identification number. (Integer > 0) FORM Format to define the plane wave amplitude. (Character; "REAL" or "PHASE"; Default = REAL) If FORM = REAL, define the plane wave amplitude in rectangular format (real and imaginary). If FORM = PHASE, define the plane wave amplitude in polar format (magnitude and phase). A Scale factor for TR, TI, or TM. (Real; Default = 1.0) TR Real part of plane wave amplitude. (Real or Integer; Default = 0.0) For a constant real amplitude, enter a real value. For a frequency-dependent amplitude, enter the ID of the TABLEDi bulk entry that contains the real amplitude as a function of frequency. TM Magnitude of plane wave amplitude. (Real or Integer; Default = 0.0) For a constant amplitude, enter a real value. For a frequency-dependent amplitude, enter the ID of the TABLEDi bulk entry that contains the magnitude as a function of frequency. TI Imaginary part of plane wave amplitude. (Real or Integer; Default = 0.0) For a constant imaginary amplitude, enter a real value. For a frequency-dependent amplitude, enter the ID of the TABLEDi bulk entry that contains the imaginary amplitude as a function of frequency.

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Field Contents TP Phase angle in degrees of plane wave amplitude. (Real or Integer; Default = 0.0) For a constant phase angle, enter a real value. For a frequency-dependent phase angle, enter the ID of the TABLEDi bulk entry that contains the phase angle as a function of frequency. CID1 Identification number of coordinate system in which the location of plane wave is defined. (Integer ≥ 0 or blank; Default = blank). See Remark 3. X1, X2, X3 Location of plane wave in coordinate system CID1. (Real; Default= 0.0) CID2 Identification number of coordinate system in which the direction of plane wave is defined. (Integer ≥ 0 or blank; Default = blank). See Remark 3. N1, N2, N3 Direction of plane wave in coordinate system CID2. (Real; Default= 0.0)

REMARKS: 1. ACPLNW is supported by the FEM Adaptive Order (FEMAO) method.

2. The SID must be unique with respect to ALOAD.

3. A CID1 or CID2 of zero or blank (the default) references the basic coordinate system.

4. N1, N2, and N3 cannot be all equal to zero.

Enforced acoustic pressure with complex data input

When acoustic pressures on certain grids are known beforehand (for example, the pressures are identified through measurement or previous calculation), you can apply them using the new enforced acoustic pressure card ACPRESS. SOL 108 and SOL 111 acoustic and vibro-acoustic solutions support ACPRESS. ACPRESS supports complex data and the definition of: • Magnitude and phase of pressure on multiple grids.

• Constant and frequency dependency.

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Note NX Nastran adds the degrees of freedom referenced by ACPRESS to the s-set. For detailed information on the s-set, see the Understanding Sets and Matrix Operations chapter in the User’s Guide.

Prior to NX Nastran 12, you can define enforced acoustic pressure with the RLOAD1, SPC1, and SPCD bulk entries.

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ACPRESS

Enforced Pressure Value on Grids

Defines an enforced pressure value for a frequency response analysis

FORMAT:

1 2 3 4 5 6 7 8 9 10 ACPRESS SID FORM A TR/TM TI/TP G1 G2 G3 "THRU" G4 "BY" n G5 G6 -etc.-

EXAMPLES:

ACPRESS 200 REAL 1.0 -3.0 5001

FIELDS:

Field Contents SID Load set identification number. (Integer > 0) FORM Format to define the pressure value. (Character; "REAL" or "PHASE"; Default = REAL) If FORM = REAL, define the pressure in rectangular format (real and imaginary). If FORM = PHASE, define the pressure in polar format (magnitude and phase). A Scale factor for TR, TI, or TM. (Real; Default = 1.0) TR Real part of pressure. (Real or Integer; Default = 0.0) For a constant pressure, enter a real value. For a frequency-dependent pressure, enter the ID of the TABLEDi bulk entry that contains the pressure as a function of frequency. TM Magnitude of the pressure. (Real or Integer; Default = 0.0) For a constant pressure, enter a real value. For a frequency-dependent pressure, enter the ID of the TABLEDi bulk entry that contains the pressure as a function of frequency. TI Imaginary part of the pressure. (Real or Integer; Default = 0.0) For a constant pressure, enter a real value. For a frequency-dependent pressure, enter the ID of the TABLEDi bulk entry that contains the pressure as a function of frequency.

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Field Contents TP Phase angle in degrees of the pressure. (Real or Integer; Default = 0.0) For a constant phase angle, enter a real value. For a frequency-dependent phase angle, enter the ID of the TABLEDi bulk entry that contains the pressure as a function of frequency. Gi Grid identification number. (Integer > 0; No default) G3 Grid identification number. (G4 > G3; Integer > 0; No default) "THRU" G4 "BY" Specifies an increment for a THRU specification. (Character; No default) n Increment for THRU range. (Integer > 0; No default)

REMARKS: 1. ACPRESS is supported by the FEM Adaptive Order (FEMAO) method.

2. The SID must be unique with respect to ALOAD.

3. The continuation field is optional.

Boundary conditions NX Nastran now supports acoustic panel normal velocity, constant real and imaginary impedance and admittance, and transfer admittance boundary conditions in SOL 108 and SOL 111. The acoustic panel normal velocity and transfer admittance boundary conditions are required for acoustic workflows such as muffler transmission loss. Transmission Loss is a measure of a product’s ability to reduce sound.

Acoustic panel normal velocity

NX Nastran supports an acoustic panel normal velocity boundary that can be applied to 2D acoustic element faces, for example, free faces of a 3D fluid element. This velocity boundary can be: • Used to represent acoustically rigid yet vibrating panels. In such case, the applied panel velocity corresponds with the particle velocity of the fluid in front of the panels.

• Combined with an acoustic impedance or admittance on the same panel. In such case, the acoustic panel normal velocity represents the structural vibration of an acoustically treated and therefore soft panel. Also, the particle velocity of the fluid in front of the panel is different from the structural panel velocity, which is pre-defined.

You use the new bulk entry ACPNVEL to specify the boundary. ACPNVEL supports the definition of:

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• Magnitude and phase of acoustic velocity.

• Constant or frequency-dependent complex velocity.

Impedance or admittance Prior to NX Nastran 12, the acoustic absorber element CAABSF defines frequency-dependent impedance or admittance boundary conditions. When CAABSF references the physical property PAABSF, it supports the constant equivalent structural damping coefficient B and stiffness coefficient K. Beginning with NX Nastran 12, constant real and imaginary impedance and admittance is also supported on a 2D fluid free surface when CAABSF references the new physical property PAABSF1.

Note • Parabolic element faces are also supported because only corner grids are used to define the element faces.

• Point and line impedance are not supported in the acoustic method introduced in NX Nastran 11 which includes AML, porous materials, and microphone elements.

• Point and line impedance are only supported through CAABSF that references PAABSF if the system cell 617 (ACFORM) is set to 0. ACFORM = 0 reverts to the NX Nastran 10 acoustics behavior.

• While PAABSF is not supported by the FEM Adaptive Order (FEMAO) method, PAABSF1 is supported by both the standard FEM and the FEM Adaptive Order (FEMAO) method.

Transfer admittance NX Nastran 12 supports the definition of transfer admittance between two sets of acoustic free faces for SOL 108 and SOL 111. The transfer admittance defines a relationship between the acoustic velocities and the pressures on one side of the surface, and the acoustic velocities and the pressures on the other side of the surface. You use the new bulk entry ACTRAD that references PACTRAD to specify the transfer admittance. The admittance can be measured, calculated from Mechel's formula, or derived from transfer matrices. In its most general form, the transfer admittance is expressed as

where:

• n1 is the normal velocity on the nodes of the face selection.

• n2 is the normal velocity on the nodes of the second face selection.

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• 1 is the pressure on the nodes of the first face selection.

• 2 is the pressure on the nodes of the second face selection.

• 1, 2, 4, and 5 are complex admittance coefficients.

• 3 and 6 are complex source coefficients.

The six coefficients 1 through 6 are determined by the nature of the relation. Because these coefficients have the dimension [velocity/pressure], they are called transfer admittance coefficients.

Note The matrix element values depend on the structure between the nodes defined at two sides of the surface. For example, in a physical problem, the two sides represent two sides of a wall that contains perforations. Instead of modeling the perforations by using many small elements, you model only the volumes on both sides of the wall, and you capture the effect of the perforations, which causes the acoustic results between both sides of the wall to be coupled, through the transfer admittance matrix. In this case, the nature of the relation encompasses the number of holes and their porosity, the viscosity of the fluid in the holes, and so on. These are the parameters in the Mechel's formula to derive the transfer admittance values.

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ACPNVEL

Acoustic Panel Normal Velocity

Defines panel normal velocity on fluid free surfaces.

FORMAT:

1 2 3 4 5 6 7 8 9 10 ACPNVEL SID FORM A TR/TM TI/TP BID

EXAMPLES:

ACPNVEL 200 REAL 0.2 0.5 300

FIELDS:

Field Contents SID Load set identification number. (Integer > 0) FORM Format to define the panel normal velocity. (Character; "REAL" or "PHASE"; Default = REAL) If FORM = REAL, define the panel normal velocity in rectangular format (real and imaginary). If FORM = PHASE, define the panel normal velocity in polar format (magnitude and phase). A Scale factor for TR, TI, or TM. (Real; Default = 1.0) TR Real part of velocity. (Real or Integer; Default = 0.0) For a constant velocity, enter a real value. For a frequency-dependent velocity, enter the ID of the TABLEDi bulk entry that contains the velocity as a function of frequency. TM Magnitude of velocity. (Real or Integer; Default = 0.0) For a constant velocity, enter a real value. For a frequency-dependent velocity, enter the ID of the TABLEDi bulk entry that contains the velocity as a function of frequency. TI Imaginary part of velocity. (Real or Integer; Default = 0.0) For a constant velocity, enter a real value. For a frequency-dependent velocity, enter the ID of the TABLEDi bulk entry that contains the velocity as a function of frequency.

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Field Contents TP Phase angle in degrees of velocity. (Real or Integer; Default = 0.0) For a constant phase angle, enter a real value. For a frequency-dependent phase angle, enter the ID of the TABLEDi bulk entry that contains the velocity as a function of frequency. BID Identification number of BSURFS bulk entry that normal velocity is applied to. (Integer > 0; No default)

REMARKS: 1. ACPNVEL is supported by the FEM Adaptive Order (FEMAO) method.

2. The SID must be unique with respect to ALOAD.

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PAABSF1

Acoustic Impedance or Admittance Element Property

Defines the properties of a frequency-dependent acoustic impedance or admittance element.

FORMAT:

1 2 3 4 5 6 7 8 9 10 PAABSF1 PID PTYPE FORM ZR ZI

EXAMPLE:

PAABSF1 100 IMP -0.01 20.0

FIELDS:

Field Contents PID Property identification number that matches the identification number of the corresponding CAABSF entry. (Integer > 0) PTYPE Type of the acoustic element property. (Character; "IMP" or "ADM"; Default = IMP) If PTYPE = IMP, define the impedance property. If PTYPE = ADM, define the admittance property. FORM Format to define the impedance or admittance. (Character; Default = REAL) If FORM = REAL, define the impedance or admittance in rectangular format (real and imaginary). If FORM = PHASE, define the impedance or admittance in polar format (magnitude and phase). ZR Real part of impedance or admittance. (Real or Integer; Default = 0.0) For a constant impedance or admittance, enter a real value. For a frequency-dependent impedance or admittance, enter the ID of the TABLEDi bulk entry that contains the impedance or admittance as a function of frequency. See Remark 2. ZI Imaginary part of impedance or admittance. (Real or Integer; Default = 0.0) For a constant impedance or admittance, enter a real value. For a frequency-dependent impedance or admittance, enter the ID of the TABLEDi bulk entry that contains the impedance or admittance as a function of frequency. See Remark 2.

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REMARKS: 1. CAABSF in combination with PAABSF1 is supported by the FEM Adaptive Order (FEMAO) method.

2. ZR and ZI cannot both be equal to zero.

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ACTRAD

Acoustic Transfer Admittance

Defines transfer admittance for acoustics

FORMAT:

1 2 3 4 5 6 7 8 9 10 ACTRAD TID PID BIDS BIDT AREA SDIST ANGLE

EXAMPLES:

ACTRAD 300 400 5 6 0.001 30.

FIELDS:

Field Contents TID Identification number of transfer admittance. (Integer > 0) PID Identification number of the PACTRAD bulk entry. (Integer > 0 or blank; Default = blank). See Remark 3. If PID = blank, the transfer admittance continuity is defined between the source and target region. BIDS Acoustic source region identification number for transfer admittance pairing. (Integer > 0; Default = blank) BIDT Acoustic target region identification number for transfer admittance pairing. (Integer > 0; Default = blank) AREA Area correction factor. (Real ≥ 0.0; Default = 0.0). See Remark 3. SDIST Search distance for transfer admittance region. (Real > 0.0; Default = 10.0) Angle Angular tolerance in degrees used to decide whether the acoustic source and target region can be considered as overlapping. If the angle between the normal of the acoustic source and target region exceeds this value, they cannot be coupled. (Real > 0.0; Default = 60.0)

REMARKS: 1. ACTRAD is supported by the Finite Element Method Adaptive Order (FEMAO) method.

2. The TID must be unique with respect to ACTRAD.

3. If PID = blank, the AREA input is ignored. If AREA = blank or 0.0, the solver automatically computes the area correction factor.

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If AREA > 0.0, the input value is used.

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PACTRAD

Property of Acoustic Transfer Admittance

Defines the property of transfer admittance for acoustics.

FORMAT:

1 2 3 4 5 6 7 8 9 10 PACTRAD PID A1R A1I A2R A2I A3R A3I A4R A4I A5R A5I A6R A6I

EXAMPLES:

PACTRAD 300 0.3 0.3 0.4 0.4 0.5 0.5 0.6 0.6 0.1 0.1 0.2 0.2

FIELDS:

Field Contents PID Identification number of the parameters of acoustic transfer admittance. (Integer > 0) AiR Real parameters for transfer admittance. (Real or Integer; Default = 0.0) (i = 1,2,3...) For a constant transfer admittance, enter a real value. For a frequency-dependent transfer admittance, enter the ID of the TABLEDi bulk entry that contains the transfer admittance as a function of frequency. See Remark 3. AiI Imaginary parameters for transfer admittance. (Real or Integer; Default = 0.0) (i = 1,2,3...) For a constant transfer admittance, enter a real value. For a frequency-dependent transfer admittance, enter the ID of the TABLEDi bulk entry that contains the transfer admittance as a function of frequency. See Remark 3.

REMARKS: 1. The PID must be unique with respect to each PACTRAD.

2. AiR and AiI cannot both be equal to zero, except for 3 and 6.

3. Ai are the transfer admittance coefficients that define the relationship of normal velocity and pressure between the two surfaces. In its most general form, this relationship is expressed as

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where:

• n1 is the normal velocity on the nodes of the first face selection or normal velocity on the positive sides of the element selection.

• n2 is the normal velocity on the nodes of the second face selection or normal velocity on the negative sides of the element selection.

• 1 is the pressure on the nodes of the first face selection or pressure on the positive sides of the element selection.

• 2 is the pressure on the nodes of the second face selection or pressure on the negative sides of the element selection.

• 1, 2, 4, and 5 are complex admittance coefficients.

• 3 and 6 are complex source coefficients.

The six coefficients 1 through 6 are determined by the nature of the relation (see Acoustics User's Guide). Because these coefficients have the dimension [velocity/pressure], they are called transfer admittance coefficients.

Acoustic materials with complex properties

The new acoustic material bulk entries MAT10C and MATF10C allow users to input complex density and speed of sound for SOL 108 and 111. • MAT10C allows you to define constant or nominal properties.

• MATF10C allows you to define material properties in tabular format.

For example, in a SOL111, when a modal analysis is first performed, the nominal value is used to calculate the eigenvalue and eigenvector. In the frequency response, however, the actual value is used if MATF10C is specified.

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MAT10C

Fluid or Absorber Material Property Definition in Complex Format

Defines constant or nominal material properties for fluid or absorber elements in coupled fluid-structural analysis.

FORMAT:

1 2 3 4 5 6 7 8 9 10 MAT10C ID FORM RHOR RHOI CR CI

EXAMPLE:

MAT10C 100 3 -0.01 20.0 5

FIELDS:

Field Contents ID Material identification number. (Integer > 0) FORM Format to define the fluid density and speed of sound. (Character; "REAL" or "PHASE"; Default = REAL) If FORM = REAL, define the fluid density and speed of sound in rectangular format (real and imaginary). If FORM = PHASE, define the fluid density and speed of sound in polar format (magnitude and phase). RHOR Real part of density. (Real; Default = 0.0) RHOI Imaginary part of density. (Real; Default = 0.0) CR Real part of speed of sound. (Real; Default = 0.0) CI Imaginary part of speed of sound. (Real; Default = 0.0)

REMARKS: 1. RHOR and RHOI cannot both be equal to zero.

2. CR and CI cannot both be equal to zero.

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MATF10C

Fluid or Absorber Material Property Definition in Complex Format

Defines tabular material properties for fluid or absorber elements in coupled fluid-structural analysis. FORMAT:

1 2 3 4 5 6 7 8 9 10 MATF10C ID TIDRHOR TIDRHOI TIDCR TIDCI

EXAMPLE:

MATF10C 100 501 502 601 602

FIELDS:

Field Contents ID Material identification number. (Integer > 0) TIDRHOR Identification number of TABLEDi bulk entry which defines the real part of density. (Integer > 0; Default = 0) TIDRHOI Identification number of TABLEDi bulk entry which defines the imaginary part of density. (Integer > 0; Default = 0) TIDCR Identification number of TABLEDi bulk entry which defines the real part of speed of sound. (Integer > 0; Default=0) TIDCI Identification number of TABLEDi bulk entry which defines imaginary part of speed of sound. (Integer > 0; Default=0)

REMARKS: 1. If TIDRHOR, TIDRHOI, TIDCR, or TIDCI field = blank, the corresponding value specified in MAT10C will be used in the computation.

2. TIDRHOR, TIDRHOI, TIDCR, or TIDCI cannot be all equal to zero.

3. MATF10C will be used only when MAT10C with the same ID is specified.

4. The FORM specified in MAT10C bulk entry will be applied to MATF10C bulk entry.

Acoustic pressure results PRESSURE and DISPLACEMENT case control commands are no longer interchangeable. You can now use the PRESSURE case control command to request only the output of acoustic pressure results at fluid points. Thus, the pressure results are separated from the displacement results in the NX Nastran results file. You can also use this case control command to obtain acoustic pressure at fluid grids referenced by microphone elements.

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Note • The new system cell 640 (PRESOUT) is available to revert to the pre-NX Nastran 12 behavior, where DISPLACEMENT and PRESSURE case control commands are interchangeable.

• If you submit a legacy input file that contains a DISPLACEMENT case control command requesting pressure output at fluid grids and system cell 640 (PRESOUT): = 1 (Default), NX Nastran only outputs the displacements.

= 0, NX Nastran reverts to the pre-NX Nastran 12 behavior.

Also, the bulk entries RCROSS and RCROSSC that define the quantities for computing cross-power spectral density and cross-correlation functions in a random analysis are enhanced by including an acoustic response quantity type.

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PRESSURE

Pressure Output Request for Fluid Grid Points

Requests the form and type of pressure output for fluid grid points.

FORMAT:

EXAMPLES: PRESSURE=5 PRESSURE(REAL)=ALL PRESSURE(SORT2,PUNCH,REAL)=ALL

DESCRIBERS:

Describer Meaning

SORT1 Output is presented as a tabular listing of grid points for each load, frequency, eigenvalue, or time, depending on the solution sequence. (Default)

SORT2 Output is presented as a tabular listing of load, frequency or time for each grid point.

PRINT The printer is the output medium. (Default)

PUNCH The punch file is the output medium.

PLOT Generates, but does not print, pressure data.

REAL or IMAG Requests rectangular format (real and imaginary) of complex output. Use of either REAL or IMAG yields the same output. (Default)

PHASE Requests polar format (magnitude and phase) of complex output. Phase output is in degrees.

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Describer Meaning

TOTAL Outputs the total pressure for the incident-scattered formulation. (Default)

SCATR Outputs the scattered pressure for the incident-scattered formulation.

PSDF Requests that the power spectral density function be calculated for random analysis post-processing. The request must be made above the subcase level and RANDOM must be selected in the Case Control. See Remark 4.

ATOC Requests that the autocorrelation function be calculated for random analysis post-processing. The request must be made above the subcase level and RANDOM must be selected in the Case Control. See Remark 4.

CRMS Requests that the cumulative root mean square function be calculated for random analysis post-processing. Request must be made above the subcase level and RANDOM must be selected in the Case Control. See Remark 4.

RMS Requests that the root mean square and zero crossing functions be calculated for random analysis post-processing. Request must be made above the subcase level and RANDOM must be selected in the Case Control. (Default) See Remark 4.

RALL Requests that all of PSDF, ATOC, RMS, and CRMS be calculated for random analysis post-processing. The request must be made above the subcase level and RANDOM must be selected in the Case Control. See Remark 4.

RPRINT Writes random analysis results to the print file. (Default) See Remark 4.

NORPRINT Disables the writing of random analysis results to the print file. See Remark 4.

RPUNCH Writes random analysis results to the punch file. See Remark 4.

ALL Outputs acoustic pressure for all points.

NONE Outputs acoustic pressure for no points.(Default)

n Sets identification of a previous SET command. Only acoustic pressure of points with identification numbers that appear on this SET command are output. (Integer > 0)

REMARKS: 1. Both PRINT and PUNCH may be requested.

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2. By default, the PRESSURE case control command requests pressure output at fluid grid points only and the DISPLACEMENT case control command requests displacement at structural grid points only. In versions prior to NX Nastran 12, the PRESSURE and DISPLACEMENT case control commands were interchangeable. Use SYSTEM(640) to revert to the pre-NX Nastran 12 behavior.

3. PRESSURE = NONE overrides an overall output request.

4. The following applies to random solutions: • By default, frequency response results are not output. If you want both random output and frequency response output, specify SYSTEM(524) = 1 or RANFRF = 1 in the input file. The PRINT, PUNCH, and PLOT describers control the frequency response output. The RPRINT, NORPRINT, and RPUNCH describers control the random output.

• The SORT1 and SORT2 describers control the output format for the frequency response output only. The output format for random results is controlled using the RPOSTS1 describer on the RANDOM case control command or the parameter RPOSTS1, except for RMS results, which are only available in SORT1 format.

• You can select any combination of the PSDF, ATOC, RMS, and CRMS describers. The RALL describer selects all four.

• Autocorrelation (ATOC) calculations require the RANDT1 bulk entry.

5. Any structural points that you include in SET = n are ignored.

6. During a SOL 108 or SOL 111 frequency-dependent external superelement creation run, on the SET case control command that is referenced by the PRESSURE case control command, include any points at which you want to recover results during the system run.

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RCROSS

Cross-Power Spectral Density and Cross-Correlation Function Output

Defines a pair of response quantities for computing the cross-power spectral density and cross-correlation functions in random analysis.

FORMAT:

1 2 3 4 5 6 7 8 9 10 RCROSS SID RTYPE1 ID1 COMP1 RTYPE2 ID2 COMP2 CURID

EXAMPLES:

RCROSS 20 DISP 50 2 STRESS 150 8 4

RCROSS 200 PRESS 101 1 DISP 50 2

FIELDS:

Field Contents SID Case control RCROSS identification number for cross-power spectral density and cross-correlation functions. (Integer>0) RTYPEi Type of response quantity. At least one field must be selected. See Remark 2. (Character or blank) IDi Element, grid, or scalar point identification number. (Integer > 0) COMPi Component code (item) identification number. See Remark 3. (Integer > 0) CURID Curve identification number. See Remark 5. (Integer > 0 or blank)

REMARKS: 1. This entry is required for computing the cross-power spectral density and cross-correlation functions. SID must be selected with the case control command (RCROSS=SID). Fields RTYPE1, ID1, and COMP1 represent the first response quantity; fields RTYPE2, ID2, and COMP2 represent the second response quantity.

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2. The keywords for field RTYPEi are listed as follows:

Keyword Meaning DISP Displacement Vector VELO Velocity Vector ACCEL Acceleration Vector OLOAD Applied Load Vector SPCF Single-point Constraint Force Vector MPCF Multi-point Constraint Force Vector STRESS Element Stress STRAIN Element Strain FORCE Element Force PRESS Acoustic Pressure

If either RTYPE1 or RTYPE2 is blank, then the blank field takes the default from the defined field.

3. For elements, the item code COMPi represents a component of the element stress, strain or force and is described in Tables “Element Stress-Strain Item Codes” and “Element Force Item Codes”. For an item having both a real and imaginary part, the code of the real part must be selected. This is required for computing both the cross-power spectral density function and cross-correlation function. For grid points, the item code is one of 1,2,3,4,5, and 6, which represent the mnemonics T1, T2, T3, R1, R2, and R3, respectively. For scalar points or PRESS, always use 1.

4. Elements defined as a laminate cannot be selected by the RCROSS entry. The RCROSSC entry should be used to request cross-power spectral density and cross-correlation function output for shell composites defined with the PCOMP and PCOMPG property entries, and solid element composites defined with the PCOMPS property entry.

5. Field CURID is optional. It is for your convenience to identify the output by using a single index.

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RCROSSC

Cross-Power Spectral Density and Cross-Correlation Function Output for Shell and Solid Element Composites

Defines a pair of response quantities for computing the cross-power spectral density and cross-correlation functions in random analysis for shell and solid element composites.

FORMAT:

1 2 3 4 5 6 7 8 9 10 RCROSSC SID RTYPE1 ID1 COMP1 PLY1 RTYPE2 ID2 COMP2 PLY2 CURID

EXAMPLES:

RCROSSC 20 DISP 50 2 STRESS 150 8 2 4

RCROSSC 200 PRESS 101 1 STRESS 150 8 2 4

FIELDS:

Field Contents SID RCROSS case control command identification number. (Integer>0) RTYPEi Response quantity. (Character; For default behavior, see Remark 2) IDi Element, grid, or scalar point identification number. (Integer > 0; No default) COMPi Component (item) code identification number. See Remark 3. (Integer > 0; No default) PLYi Ply number. (Integer ≥ 0; For default behavior, see Remark 4) CURID Optional curve identification number. See Remark 5. (Integer > 0; No default)

REMARKS: 1. The RCROSSC entry is used to request cross-power spectral density and cross-correlation function output for shell composites defined with the PCOMP and PCOMPG property entries, and solid element composites defined with the PCOMPS property entry.

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2. The keywords for field RTYPEi are listed as follows:

If either the RTYPE1 or RTYPE2 field is blank, then the blank field defaults to the response quantity listed in the defined field.

3. For elements, the component (item) code COMPi represents a component of the element stress, strain or force as described in the “Element Stress (or Strain) Item Codes” and “Element Force Item Codes” tables. For an item having both a real and imaginary part, the code of the real part must be selected. This is required for computing both the cross-power spectral density function and cross-correlation function. For grid points, the item code is one of 1,2,3,4,5, and 6, which represent T1, T2, T3, R1, R2, and R3, respectively. For scalar points or PRESS, always use 1.

4. PLY1 and PLY2 cannot both be zero or blank. If it is desired to have both zero, use the RCROSS bulk entry. For a non-composite element, grid point, or scalar point, specify PLYi = 0 or leave the PLYi field blank. For a non-composite element, grid point, or scalar point, if PLYi > 0, the ply number specification is ignored. For a composite element, if PLYi = 0 or the PLYi field is blank or PLYi is greater than the actual number of plies, the ply number specification is ignored.

5. To identify the output with a single index, specify the index in the CURID field.

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Support for random acoustic analysis For distributed acoustic plane wave problems, you can now perform power spectral density (PSD) random acoustics analysis. This capability is supported for both SOL 108 and SOL 111. In earlier versions of the software, you are limited to deterministic acoustic analysis. To request that the software calculate the random response, in your input file include the RANDOM case control command. Then, organize the subcases as follows: 1. Create a frequency response subcase for each acoustic loading. Make sure that all of these subcases reference the same set of frequencies. The acoustic loads can include acoustic monopole, dipoles, or plane waves. A typical acoustic loading, is that of an acoustic diffuse field. You can represent an acoustic diffuse field with a number of subcases that each contain an acoustic plane wave source. Orient each plane wave source differently with respect to the object that sees the acoustic diffuse field. For example, the object might be a panel or a spacecraft. To define a diffuse acoustic field, you can define these sources as uncorrelated sources in a RANDOM subcase by specifying the diagonal (auto-PSD) factors in the RANDPS bulk entries only.

2. Below the frequency response subcases, include a random analysis subcase for each PSD function that you want to evaluate. Include ANALYSIS = RANDOM in these subcases. The software uses the frequency response functions that are calculated in the immediately preceding frequency response subcases as the inputs to the random calculations.

Example Suppose that the fluid in a vibro-acoustic problem is excited by three plane wave loadings, and you want to evaluate the acoustic random response for two PSD functions. You can organize the subcase structure of the input file as follows: SUBCASE 1 $ $ Subcase 1 calculates the frequency response function for the $ loading specified by ALOAD 111 at the frequencies specified by $ FREQUENCY set 13 $ FREQUENCY=13 ALOAD=111 $ SUBCASE 2 $ $ Subcase 2 calculates the frequency response function for the $ loading specified by ALOAD 211 at the frequencies specified by $ FREQUENCY set 13 $ FREQUENCY=13 ALOAD=211 $ SUBCASE 3 $ $ Subcase 3 calculates the frequency response function for the $ loading specified by ALOAD 311 at the frequencies specified by $ FREQUENCY set 13 $

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FREQUENCY=13 ALOAD=311 $ SUBCASE 4 $ $ Subcase 4 uses the frequency responses from Subcases 1-3 to $ calculate the random response of the structure for the PSD function $ specified by RANDOM 100 $ ANALYSIS=RANDOM RANDOM=100 $ SUBCASE 5 $ $ Subcase 5 uses the frequency responses from Subcases 1-3 to $ calculate the random response of the structure for the PSD function $ specified by RANDOM 200 $ ANALYSIS=RANDOM RANDOM=200

Incident and transmitted acoustic power and acoustic power transmission loss results output

For SOL 108 and 111, you can now request results output for incident acoustic power, transmitted acoustic power, and acoustic power transmission loss in deterministic and random acoustic analysis. In NX Nastran 11, you were limited to output of acoustic power results. Because acoustic power results include both incident and scattered (reflected) components, the new output requests allow you to examine acoustic results in more detail and compute acoustic transmission loss. • To isolate the acoustic power that is incident on a surface like a 2D microphone mesh or a set of acoustic free faces (BSURFS) and that is attributable to acoustic sources like monopoles or acoustic plane waves, but not reflections, use the INPOWER case control command.

• To request the acoustic power that is transmitted through an automatically matched layer (AML) region or a 2D microphone mesh that includes both incident and scattered components, use the TRPOWER case control command.

• To request the acoustic power transmission loss, use the TRLOSS case control command. The software calculates the acoustic power transmission loss from the INPOWER and TRPOWER results as follows:

Calculating acoustic power transmission loss through a structural panel

As an example, you can use TRLOSS to calculate the acoustic power transmission loss through a structural panel.

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In a laboratory setting, you can measure the acoustic power transmission loss through a structural panel by mounting the panel in an aperture of a wall between two rooms. One room is reverberant and contains a diffuse acoustic plane wave source. The other room is anechoic and has no pure acoustic sources. The anechoic room also contains the instrumentation for measuring the acoustic power. Because the room is anechoic, you measure the acoustic power that radiates from the panel, and the measurement is not influenced by reflections.

A simulation for such a laboratory setup is shown below:

AMLREG1 (reverberant side)

Structural panel

Acoustic free faces (reverberant side)

AMLREG2 (anechoic side)

Figure 3-1. Panel test

In the simulation, both rooms are represented by fluid meshes using AML regions. AMLREG1 represents the reverberant room where the fluid domain opens to the half space in front of the panel. The acoustic power source within the reverberant room can be modeled by a set of random plane waves that are typically outside the fluid mesh. AMLREG2 represents the anechoic room where the fluid domain opens to the half space behind the panel.

1. Use INPOWER to calculate the incident acoustic power on the free acoustic faces on the reverberant room side that couple with the panel.

2. Use TRPOWER to calculate the acoustic power flowing through AMLREG2.

3. Use TRLOSS to calculate the acoustic power transmission loss through the panel.

Random results

If you request random results with the INPOWER, TRPOWER, and TRLOSS case control commands, only real output is supported. Thus, these case control commands do not honor the following specifications:

• RANCPLX = 1 on the RANDOM case control command

• PARAM,RANCPLX,1

For more information, see the new INPOWER, TRPOWER, and TRLOSS case control commands, and the updated ACPOWER case control command.

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ACPOWER

Acoustic Power Results Output

Acoustic power results output request for AML regions or 2D microphone elements (SORT2 results only).

FORMAT:

EXAMPLES: SET 123=3,6,9 ACPOWER(AMLREG=123) SET 5=5,10 ACPOWER(GROUP=5,PRINT,PUNCH,PHASE) ACPOWER=NO ACPOWER

DESCRIBERS:

Describer Meaning

AMLREG = Calculate acoustic power results for all AMLREG bulk entries. ALL (Default)

AMLREG = Do not calculate acoustic power results for any AMLREG bulk NONE entries.

AMLREG = na na (integer>0) is the identification number of the SET case control command that lists the identification numbers of AMLREG bulk entries at which to calculate acoustic power results. See Remark 3.

GROUP = ng ng (integer>0) is the identification number of the SET case control command that lists the identification numbers of GROUP bulk entries that contain the 2D microphone elements at which to calculate acoustic power results. See Remark 3.

PRINT Write the acoustic power results to the print (.f06) file. (Default)

NOPRINT Do not print the acoustic power results.

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Describer Meaning

PUNCH Write the acoustic power results to the standard punch (.pch) file.

REAL or IMAG Requests rectangular format (real and imaginary) of complex output. Use of either REAL or IMAG yields the same output. (Default)

PHASE Requests polar format (magnitude and phase) of complex output. Phase output is in degrees.

Write the random analysis results to the print (.f06) file. See RPRINT Remark 5. (Default)

Do not write the random analysis results to the print file. See NORPRINT Remark 5.

Write the random analysis results to the punch (.pch) file. See RPUNCH Remark 5.

Honor describer settings and calculate and output acoustic power YES results. (Default)

Ignore describer settings and do not calculate or output acoustic NO power results. See Remark 5.

REMARKS: 1. The PRESSURE case control command settings determine whether the acoustic power results are total or scattered.

2. Both PRINT and PUNCH may be requested.

3. Only AML regions or 2D microphone elements referenced in GROUP bulk entries are processed for acoustic power results. Either or both of the AMLREG and GROUP describers must be specified. Microphone elements must reference a PMIC property.

4. Acoustic power results are written to the op2 file, if PARAM, POST,-1 or PARAM,POST,-2.

5. The following applies to random solutions:

• By default, frequency response results are not output. If in addition to random output, frequency response output is desired, specify SYSTEM(524)=1 or RANFRF=1 in the input file. The PRINT, NOPRINT, PUNCH describers control the frequency response output. The RPRINT, NORPRINT, RPUNCH describers control the random output.

• Only SORT2 output format is available for the frequency response and random results output.

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• Only real random analysis results are generated regardless of how the RANCPLX describer on the RANDOM case control command or the RANCPLX parameter are specified.

• Only the power spectral density function (PSDF) is calculated. For RANDPS bulk entries that refer to n subcases, when i = j the results in W/Hz are computed as follows:

If i ≠ j, then a warning message is issued and the RANDPS bulk entries are ignored. For more information, see the RANDPS bulk entry.

• Use ACPOWER=NO within a subcase to override a ACPOWER specification above the subcase level.

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INPOWER

Incident Acoustic Power Results Output

Incident acoustic power results output request for 2D microphone elements or acoustic free faces (SORT2 results only).

FORMAT:

EXAMPLES: SET 5=5,10 INPOWER(GROUP=5,PRINT,PUNCH,PHASE) SET 6=100 INPOWER(FACES=6) INPOWER=NO

DESCRIBERS:

Describer Meaning

FACES = nf nf (integer>0) is the identification number of the SET case control command that lists the identification numbers of BSURFS bulk entries that contain the acoustic free faces at which to calculate incident acoustic power results. See Remark 2.

PRINT Write the incident acoustic power results to the print (.f06) file. (Default)

NOPRINT Do not print the incident acoustic power results.

PUNCH Write the incident acoustic power results to the standard punch (.pch) file.

REAL or IMAG Requests rectangular format (real and imaginary) of complex output. Use of either REAL or IMAG yields the same output. (Default)

PHASE Requests polar format (magnitude and phase) of complex output. Phase output is in degrees.

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Describer Meaning

RPRINT Write the random analysis results to the print (.f06) file. See Remark 4. (Default)

NORPRINT Do not write the random analysis results to the print file. See Remark 4.

RPUNCH Write the random analysis results to the punch (.pch) file. See Remark 4.

Honor describer settings and calculate and output incident YES acoustic power results. (Default)

Ignore describer settings and do not calculate or output incident NO acoustic power results. See Remark5.

REMARKS: 1. Both PRINT and PUNCH may be requested.

2. Only 2D microphone elements referenced in GROUP bulk entries or acoustic free faces at the structural boundary referenced on BSURFS bulk entries are processed for incident acoustic power results. Either the GROUP describer or the FACES describer must be specified, but not both. Microphone elements must reference a PMIC property.

3. Incident acoustic power results are written to the op2 file, if PARAM, POST,-1 or PARAM,POST,-2.

4. The following applies to random solutions: • By default, frequency response results are not output. If in addition to random output, frequency response output is desired, specify SYSTEM(524)=1 or RANFRF=1 in the input file. The PRINT, NOPRINT, PUNCH describers control the frequency response output. The RPRINT, NORPRINT, RPUNCH describers control the random output.

• Only SORT2 output format is available for the frequency response and random results output.

• Only real random analysis results are generated regardless of how the RANCPLX describer on the RANDOM case control command or the RANCPLX parameter are specified.

• Only the power spectral density function (PSDF) is calculated. For RANDPS bulk entries that refer to n subcases, when i = j the results in W/Hz are computed as follows:

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If i ≠ j, then a warning message is issued and the RANDPS bulk entries are ignored. For more information, see the RANDPS bulk entry.

5. Use INPOWER=NO within a subcase to override a INPOWER specification above the subcase level.

6. The computed incident power takes into account the incident acoustic energy from the ACPOLE1, ACPOLE2, and ACPLNW acoustic sources only, and not from acoustic sources like ACPNVEL that can contain a scattered component.

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TRPOWER

Transmitted Acoustic Power Results Output

Transmitted acoustic power results output request for AML regions or 2D microphone elements (SORT2 results only).

FORMAT:

EXAMPLES: SET 123=3,6,9 TRPOWER(AMLREG=123) SET 5=5,10 TRPOWER(GROUP=5,PRINT,PUNCH,PHASE) TRPOWER=NO TRPOWER

DESCRIBERS:

Describer Meaning

AMLREG = Calculate transmitted acoustic power results for all AMLREG bulk ALL entries. (Default)

AMLREG = Do not calculate transmitted acoustic power results for any NONE AMLREG bulk entries.

AMLREG = na na (integer>0) is the identification number of the SET case control command that lists the identification numbers of AMLREG bulk entries at which to calculate transmitted acoustic power results. See Remark 2.

PRINT Write the transmitted acoustic power results to the print (.f06) file. (Default)

NOPRINT Do not print the transmitted acoustic power results.

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Describer Meaning

PUNCH Write the transmitted acoustic power results to the standard punch (.pch) file.

REAL or IMAG Requests rectangular format (real and imaginary) of complex output. Use of either REAL or IMAG yields the same output. (Default)

PHASE Requests polar format (magnitude and phase) of complex output. Phase output is in degrees.

RPRINT Write the random analysis results to the print (.f06) file. See Remark 4. (Default)

NORPRINT Do not write the random analysis results to the print file. See Remark 4.

RPUNCH Write the random analysis results to the punch (.pch) file. See Remark 4.

Honor describer settings and calculate and output transmitted YES acoustic power results. (Default)

Ignore describer settings and do not calculate or output NO transmitted acoustic power results. See Remark 5.

REMARKS: 1. Both PRINT and PUNCH may be requested.

2. Only AML regions and 2D microphone elements referenced in GROUP bulk entries are processed for transmitted acoustic power results. The AMLREG describer and the GROUP describer can be specified simultaneously. Microphone elements must reference a PMIC property. Any other entities that are contained in a GROUP that is referenced by TRPOWER are ignored.

3. Transmitted acoustic power results are written to the op2 file if PARAM, POST,-1 or PARAM,POST,-2.

• Only SORT2 output format is available for the frequency response and random results output.

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• Only real random analysis results are generated regardless of how the RANCPLX describer on the RANDOM case control command or the RANCPLX parameter are specified.

• Only the power spectral density function (PSDF) is calculated. For RANDPS bulk entries that refer to n subcases, when i = j the results in W/Hz are computed as follows:

If i ≠ j, then a warning message is issued and the RANDPS bulk entries are ignored. For more information, see the RANDPS bulk entry.

5. Use TRPOWER=NO within a subcase to override a TRPOWER specification above the subcase level.

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TRLOSS

Acoustic Transmission Loss Results Output

Acoustic transmission loss results output request (SORT2 results only).

FORMAT:

EXAMPLES: TRLOSS(PRINT,PUNCH) TRLOSS=NO TRLOSS

DESCRIBERS:

Describer Meaning

PRINT Write the transmitted acoustic power results to the print (.f06) file. (Default)

NOPRINT Do not print the transmitted acoustic power results.

PUNCH Write the transmitted acoustic power results to the standard punch (.pch) file.

RPRINT Write the random analysis results to the print (.f06) file. See Remark 7. (Default)

NORPRINT Do not write the random analysis results to the print file. See Remark 7.

RPUNCH Write the random analysis results to the punch (.pch) file. See Remark 7.

Honor describer settings and calculate and output transmitted YES acoustic power results. (Default)

Ignore describer settings and do not calculate or output NO transmitted acoustic power results. See Remark 8.

REMARKS: 1. Both PRINT and PUNCH may be requested.

2. TRLOSS results are always real values.

3. To produce transmission loss results for a specific subcase, the subcase must request both incident acoustic power (INPOWER) and transmitted acoustic power (TRPOWER) results. TRLOSS can be requested for frequency response or random subcases.

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4. For frequency response analysis, transmission loss is computed from:

5. For random PSD analysis, the transmission loss is computed from:

6. Transmission loss results are written to the op2 file if PARAM, POST,-1 or PARAM,POST,-2.

7. The following applies to random solutions:

• Only SORT2 output format is available for the frequency response and random results output.

• Only real random analysis results are generated regardless of how the RANCPLX describer on the RANDOM case control command or the RANCPLX parameter are specified.

8. Use TRLOSS=NO within a subcase to override a TRLOSS specification above the subcase level.

9. The computed incident power takes into account the incident acoustic energy from the ACPOLE1, ACPOLE2, and ACPLNW acoustic sources only, and not from acoustic sources like ACPNVEL that can contain a scattered component.

Usability improvement for panel and grid contributions

Now you can only use the PANCON case control command to request panel contributions. To request grid contributions, you must use the new GRDCON case control command. In earlier versions of NX Nastran, you use the PANCON case control command to request both grid and panel contributions. However, because you can only include a single PANCON case control command in an input file, the software is limited to writing both the grid and panel contributions in the same output format. With the removal of the grid contributions request from the PANCON case control command, and the addition of the new GRDCON case control command, you can now direct the software to write grid contributions to one output format and panel contributions to another.

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For example, you can use a PANCON case control command to write panel contributions in the SORT2 output format, and use a GRDCON case control command to write grid contributions in the SORT1 output format. When using NX Nastran 12, if you run a legacy input file that contains a PANCON case control command that requests grid contributions, a fatal error occurs. To avoid the fatal error, you can edit the legacy input file as follows: 1. If the PANEL describer is set to NONE, remove the PANCON case control command altogether. If the PANEL describer is unspecified or is not set to NONE, remove any TOPG and GRID describer specifications from the PANCON case control command.

2. Write a GRDCON case control command that contains the TOPG and GRID describer specifications that you removed from the PANCON case control command.

For more information, see the updated PANCON case control command and the new GRDCON case control command.

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GRDCON

Acoustic Contribution Request for Grids of Structural Panels

Requests acoustic contribution results for the grids of structural panels and for the residual.

FORMAT:

EXAMPLES: GRDCON=123 GRDCON(SORT1,PHASE,PRINT,PUNCH,BOTH,TOPG=5)=ALL

DESCRIBERS:

Describer Meaning SORT1 Present output as a tabular listing of grids for each frequency. (Default) SORT2 Present output as a tabular listing of frequency for each grid. REAL or Requests rectangular format (real and imaginary) of complex output. IMAG Use of either REAL or IMAG yields the same output. (Default) PHASE Requests polar format (magnitude and phase) of complex output. Phase output is in degrees. PRINT Write acoustic grid contribution results to the print (.f06) file. (Default)

NOPRINT Do not print the acoustic grid contribution results.

PUNCH Write acoustic grid contribution results to the standard punch (.pch) file. ABS Output acoustic grid contributions in absolute terms. (Default)

NORM Output acoustic grid contributions in normalized terms. BOTH Output acoustic grid contributions in both absolute and normalized terms. TOPG = ALL List all of the structural grids in the output. The output is sorted in descending order from the structural grid having the greatest contribution. (Default)

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Describer Meaning pg (integer>0) is the number of structural grids to list in the output that have the greatest contribution to the response at TOPG = pg each frequency. The output is sorted in descending order from the structural grid having the greatest contribution. If pg = 0, no structural grid contributions are output, only totals. SOLUTION Perform the contribution calculations at all frequencies defined by = ALL the FREQUENCY case control commands. (Default) setf (integer>0) is the identification number of the SET case control SOLUTION command that contains the frequencies at which to perform the = setf contribution calculations. GRID = ALL Output contributions for all structural grids that are part of the acoustic coupling matrix. (Default) setg (integer>0) is the identification number of the SET case control command that contains the grids at which to output the contribution GRID = setg results. Any grid in the set that is not part of the coupling matrix is ignored. n Calculate grid contributions for the list defined by the SETMC case control command that has set identification number n (integer>0). Any response listed in SETMC = n that is not an acoustic response is ignored. ALL Calculate grid contributions for all the SETMC case control commands specified in and above the current subcase. Any response listed in the SETMC case control commands that is not an acoustic response is ignored. (Default) NONE Do not calculate grid contributions. This is useful to turn off contribution output for a specific subcase.

REMARKS: 1. Both PRINT and PUNCH may be requested.

2. GRDCON = NONE overrides an overall output request.

3. SOL 108 and 111 are supported.

4. The parameters LFREQ, LFREQFL, HFREQ, HFREQFL, LMODES, and LMODESFL are supported.

5. The SOLUTION keyword can be abbreviated to SOLU.

6. The SET case control command referenced by SOLUTION = setf must contain real values for frequencies. Using integer values may lead to unintended results.

7. GRDCON supports results for microphone points.

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PANCON

Acoustic Contribution Request for Structural Panels

Requests acoustic contribution results for structural panels and for the residual.

FORMAT:

EXAMPLES: PANCON=123 PANCON(SORT1,PHASE,PRINT,PUNCH,BOTH,TOPP=5)=ALL

DESCRIBERS:

Describer Meaning SORT1 Present output as a tabular listing of panels for each frequency. SORT2 Present output as a tabular listing of frequency for each panel. (Default) REAL or Requests rectangular format (real and imaginary) of complex output. IMAG Use of either REAL or IMAG yields the same output. (Default) PHASE Requests polar format (magnitude and phase) of complex output. Phase output is in degrees. PRINT Write acoustic panel contribution results to the print (.f06) file. (Default) NOPRINT Do not print the acoustic panel contribution results.

PUNCH Write acoustic panel contribution results to the standard punch (.pch) file. ABS Output acoustic panel contributions in absolute terms. (Default)

NORM Output acoustic panel contributions in normalized terms. BOTH Output acoustic panel contributions in both absolute and normalized terms. TOPP = ALL List all of the structural panels in the output. The output is sorted in descending order from the structural panel having the greatest contribution.

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Describer Meaning TOPP = pp pp (integer>0) is the number of structural panels to list in the output that have the greatest contribution to the response at each frequency. The output is sorted in descending order from the structural panel having the greatest contribution. If pp = 0, no structural panel contributions are output, only totals. (Default=5) SOLUTION Perform the contribution calculations at all frequencies defined by = ALL the FREQUENCY case control commands. (Default) SOLUTION setf (integer>0) is the identification number of the SET case control = setf command that contains the frequencies at which to perform the contribution calculations. PANEL = Output contributions for all panels defined by PANEL bulk entries. ALL (Default) setp (integer>0) is the identification number of the SET case PANEL = control command that contains the panels at which to output the setp contribution results. n Calculate panel contributions for the list defined by the SETMC case control command that has set identification number n (integer>0). Any response listed in SETMC = n that is not an acoustic response is ignored. ALL Calculate panel contributions for all the SETMC case control commands specified in and above the current subcase. Any response listed in the SETMC case control commands that is not an acoustic response is ignored. (Default) NONE Do not calculate panel contributions. This is useful to turn off contribution output for a specific subcase.

REMARKS: 1. Both PRINT and PUNCH may be requested.

2. PANCON = NONE overrides an overall output request.

3. SOL 108 and 111 are supported.

4. PANCON supports results for microphone points.

5. The parameters LFREQ, LFREQFL, HFREQ, HFREQFL, LMODES, and LMODESFL are supported.

6. The SOLUTION and PANEL keywords can be abbreviated to SOLU and PANE, respectively.

7. The SET case control command referenced by SOLUTION = setf must contain real values for frequencies. Using integer values may lead to unintended results.

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8. The SET case control command referenced by PANEL = setp must contain the alphanumeric name of existing panels defined by PANEL bulk entries.

Acoustic transfer vectors You can now use acoustic transfer vectors (ATV) to solve external acoustics problems. An ATV is a frequency-dependent acoustical representation of fluid volume that you can use in SOL 108 and 111 acoustic analysis. ATVs relate the response at microphone points and 2D microphone elements to excitation at the fluid-structure (coupling) interface. The primary benefit of ATVs is computational efficiency. ATVs are similar to output transformation matrices (OTMs). They both use a matrix to relate the response at specific spatial locations or over specific regions to the excitation at specific locations or from specific regions. (For more information on OTMs, see Output transformation matrices.) For example, suppose you want to examine how the acoustic response at specific locations to structural excitation varies with respect to structural materials, loads, and so on. Rather than solving the entire acoustics problem repeatedly, you can solve the acoustics problem once to create an ATV, and then use the ATV repeatedly to examine how the response varies. To use the ATV capability, two NX Nastran runs are required. • The first run is the ATV computation run. During this run, the software creates and writes the matrix representation of the ATV to an OP2 file. The ATV computation run must be SOL 108.

• The second run is the ATV response run. During this run, the software retrieves and uses the matrix representation of the ATV to calculate the acoustic response at microphone points and elements to the excitation of the structural portion of the model. The ATV response run can be either SOL 108 or 111 and can use one ATV only.

The ATV capability is supported by a new case control command and two new bulk entries. In the ATV computation run: • Use the ATVOUT case control command to trigger the creation of the ATV, reference the ATVFS bulk entry that specifies the coupling interface, and reference the SET case control command that specifies the microphone elements that comprise 2D microphone meshes.

• Use the new ATVFS bulk entry to specify the BSURFS bulk entries that define the coupling interface.

• Use a FREQi bulk entry to specify the frequencies at which the software calculates the matrix representation of the ATV.

Note During the ATV response run, the software interpolates ATV data over the frequency range defined by the FREQi bulk entry. Because the software does not extrapolate ATV data, a fatal error occurs if the frequency is out of the range defined by the FREQi bulk entry.

In the ATV response run:

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• Use the new ATVBULK bulk entry to select the OP2 file that contains the matrix representation of the ATV and to offset the element, grid point, and property IDs in the ATV to ensure that they are unique from those in the structural portion of the model.

• Use an ACMODL bulk entry to specify the coupling interface parameters.

• Use the PRESSURE case control command to request acoustic pressure results at microphone points.

• Use the PANCON case control command to request the acoustic pressure at microphone points that are attributable to the vibration of selected structural panels. o Use PANEL bulk entries to define the structural panels.

o Use SETMC case control commands to specify the microphone points. For microphone points, specify RTYPE = PRES.

• Use the GRDCON case control command to request the response at microphone points to vibration at structural grids.

• Use the MODCON case control command to request the contribution of modes to the acoustic pressure at microphone points. This is valid for a SOL 111 ATV response run only. o Use SETMC case control commands to specify the microphone points. For microphone points, specify RTYPE = PRES.

For more information, see the new ATVOUT case control command and the new ATVBULK and ATVFS bulk entries.

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ATVOUT

ATV Creation Specification

Specifies requirements for the creation of an acoustic transfer vector (ATV).

FORMAT:

EXAMPLES: ATVOUT(ATVOP2=33,ATVFS=110)=200

DESCRIBERS:

Describer Meaning

ATVOP2 = unit unit (integer>0) is the Fortran unit number for the .op2 file to which the ATV results are written. See Remark 2.

ATVFS = sid sid (integer>0) is the identification number of the ATVFS bulk entry that defines the set of fluid element faces that define the coupling interface.

ALL Output ATV results for all microphone elements. See Remark 6. (Default)

n n (integer>0) is the identification number of a previously appearing SET case control command that contains microphone element identification numbers at which to output the ATV results. See Remark 6.

REMARKS: 1. ATVOUT is valid for SOL 108 only. If ATVOUT is included in the input file for any other solution, the software issues a user fatal message.

2. For specifying ATVOP2 = unit, an appropriate ASSIGN OUTPUT2 statement must be present in the File Management Section of the input file.

3. An OUTPUT2 file created from a LP-64 executable ATV creation run cannot be used in an ILP-64 Nastran executable system run and vice versa. Note that beginning in NX Nastran 12, only the ILP-64 executable is available.

4. ATVOUT can only be specified above subcases. If ATVOUT is included in a subcase, it is ignored.

5. Only one ATVOUT can be included in an input file.

6. ATV output is controlled by the specification of ALL or n only. Any other output-related case control commands like DISPLACEMENT or PRESSURE are ignored.

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ATVBULK

Selects ATV results for an ATV system run

Specifies the Fortran unit number for the OUTPUT2 file that contains the ATV results, and the element, grid point, and element property offsets to be used in an ATV system run.

FORMAT:

1 2 3 4 5 6 7 8 9 10 ATVBULK UNITNO EOFFSET GOFFSET POFFSET

EXAMPLE:

ATVBULK 33 1000 2000 20

FIELDS:

Field Contents UNITNO Fortran unit number for the OUTPUT2 file that contains the ATV results. See Remarks 1 and 2. (Integer > 0; No default) EOFFSET Element ID offset. See Remark 3. (Integer > 0; Default = 0) GOFFSET Grid point ID offset. See Remark 3. (Integer > 0; Default = 0) POFFSET Element property ID offset. See Remark 3. (Integer > 0; Default = 0)

REMARKS: 1. For specifying UNITNO, an appropriate ASSIGN OUTPUT2 statement must be present in the File Management Section of the input file.

2. An OUTPUT2 file that is created during a LP-64 Nastran executable ATV creation run cannot be used in an ILP-64 Nastran executable system run and vice versa. Note that beginning in NX Nastran 12, only the ILP-64 executable is available.

3. The element, grid, and element property IDs associated with the ATV results must be unique from element, grid, and element property IDs in the system run. To assure that they are unique, specify appropriate element, grid, and element property ID offsets.

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ATVFS

Coupling interface definition for an ATV

Defines the interface that couples the acoustic transfer vector (ATV) to the structure in the ATV system run.

FORMAT:

1 2 3 4 5 6 7 8 9 10 ATVFS SID ID1 ID2 ID3 ID4 ID5 ID6 ID7 ID8 -etc-

EXAMPLE:

ATVFS 100 201 202

FIELDS:

Field Contents SID Set identification number of the fluid element faces that define the coupling interface. See Remark 1. (Integer > 0; No default) IDi Identification number of BSURFS bulk entries that list the fluid element faces that define the coupling interface. (Integer>0; No default)

REMARKS: 1. SID is referenced by the ATVFS describer specification on the ATVOUT case control command.

Output format for acoustic intensity and acoustic velocity results

You can now request that acoustic intensity and acoustic velocity results be output in the SORT2 format. The SORT2 format allows you to more easily examine how acoustic intensity and acoustic velocity at a particular DOF vary with respect to frequency. In earlier versions of the software, only the SORT1 format is available for these results. For more information, see the ACINTENSITY and ACVELOCITY case control commands.

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ACINTENSITY

Acoustic Intensity Output

Acoustic intensity output request at microphone points.

FORMAT:

EXAMPLES: SET 123=5,10,15,25 ACINTENSITY=123 SET 5=6,8,11 ACINTENSITY(PRINT,PUNCH,PHASE)=5

DESCRIBERS:

Describer Meaning

SORT1 Present output as a tabular listing of grids for each frequency. (Default)

SORT2 Present output as a tabular listing of frequency for each grid.

PRINT The print file (.f06) will be the output medium. (Default)

NOPRINT Generates, but does not print intensity results.

PUNCH The standard punch file (.pch) will be the output medium.

REAL or IMAG Requests rectangular format (real and imaginary) of complex output. Use of either REAL or IMAG yields the same output. (Default)

PHASE Requests polar format (magnitude and phase) of complex output. Phase output is in degrees.

n ID of SET case control command containing the list of identification numbers of fluid grids referenced by microphone elements at which to calculate acoustic intensity results. (Integer > 0)

ALL Requests acoustic intensity results for all microphone elements in the model.

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Describer Meaning

NONE Turns this output request off; useful for controlling output requests across subcases.

REMARKS: 1. The PRESSURE case control command settings determine whether the acoustic intensity results are based on total or scattered pressure.

2. Acoustic intensity results will be written to the op2 file, if the value of PARAM, POST is -1 or -2.

3. When the fluid domain is represented by an acoustic transfer vector (ATV), acoustic particle velocity and acoustic intensity results cannot be computed, and the ACINTENSITY and ACVELOCITY case control commands are ignored.

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ACVELOCITY

Acoustic Velocity Output

Acoustic velocity output request at microphone points.

FORMAT:

EXAMPLES: SET 123=5,10,15,25 ACVELOCITY=123 SET 5=6,8,11 ACVELOCITY(PRINT,PUNCH,PHASE)=5

DESCRIBERS:

Describer Meaning

SORT1 Present output as a tabular listing of grids for each frequency. (Default)

SORT2 Present output as a tabular listing of frequency for each grid.

PRINT The print file (.f06) will be the output medium. (Default)

NOPRINT Generates, but does not print, acoustic velocity.

PUNCH The standard punch file (.pch) will be the output medium.

REAL or IMAG Requests rectangular format (real and imaginary) of complex output. Use of either REAL or IMAG yields the same output. (Default)

PHASE Requests polar format (magnitude and phase) of complex output. Phase output is in degrees.

n ID of SET case control command containing the list of identification numbers of fluid grids referenced by microphone elements at which to calculate acoustic velocity results. (Integer > 0)

ALL Request acoustic velocity results for all microphone elements in the model.

NONE Turns this output request off; useful for controlling output requests across subcases.

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REMARKS: 1. The PRESSURE case control command settings determine whether the acoustic velocity results are based on total or scattered pressure.

2. Acoustic velocity results will be written to the op2 file, if the value of PARAM, POST is -1 or -2.

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Chapter 4: Superelements

Frequency-dependent external superelements for frequency response analysis

During a SOL 108 or 111 frequency response analysis superelement creation run, you can now create frequency-dependent external superelements. You can then use the frequency-dependent external superelement in a SOL 108 or 111 system run. In earlier versions of NX Nastran, you cannot create frequency-dependent external superelements. The primary advantages of frequency-dependent external superelements are as follows:

• Unlike conventional superelements that include boundary DOF and component modes, frequency-dependent superelements contain only boundary DOF, which improves computational efficiency.

• Unlike conventional superelements, frequency-dependent superelements support frequency-dependent material properties.

The primary disadvantage of frequency-dependent external superelements are as follows:

• Because the superelement creation run is performed repeatedly at multiple frequencies, more computational effort is required up front.

• Because each superelement creation run generates the dynamic stiffness matrix for the boundary DOF and a data recovery matrix for displacement data recovery, more disk storage is required.

During the SOL 108 or 111 system run, the software adds the dynamic stiffness for the boundary DOF to the dynamic stiffness of the residual structure and uses the data recovery matrices to calculate displacement, velocity, and acceleration output. The workflow to use frequency-dependent superelements is essentially identical to the workflow to create and use conventional external superelements. First you perform a SOL 108 or 111 superelement creation run. In the input file for the superelement creation run, use the FRFOUT case control command in place of the EXTSEOUT case control command. The FRFOUT case control command triggers the software to:

1. Create the frequency-dependent dynamic stiffness matrices for the boundary DOF and the data recovery matrices for displacement data recovery.

2. Write the frequency-dependent dynamic stiffness matrices for the boundary DOF and data recovery matrices to the OP2 file.

To define the frequencies at which the software calculates the dynamic stiffness matrices for the boundary DOF and the data recovery matrices, use a FREQ bulk entry.

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During the SOL 108 or 111 system run, the software uses the FRFOUT files that are generated by the superelement creation run. To trigger the software to read the FRFOUT files from the superelement creation run, use the SEBULK bulk entry with the TYPE field set to FRFOP2. For more information, see the new FRFOUT case control command and the updated SEBULK bulk entry.

Component reduction methods

The software supports the following methods for reducing a component to a frequency-dependent external superelement during a superelement creation run: • For SOL 108 direct frequency response analysis: o Schur complement reduction This is the default method when you specify SOL 108.

o Schur complement reduction with component modes The software uses this method when you include a METHOD case control command and a QSETi bulk entry in the input file for the superelement creation run.

• For SOL 111 modal frequency response analysis, modal reduction.

For more information on these reduction methods, see Frequency-Dependent External Superelements in the Superelement User's Guide.

Example

Perform a SOL 108 frequency response analysis on the structure depicted in Figure 1. Assume that the beam is steel and has a 20.0 mm diameter cross section. Model the left half of the beam as a frequency-dependent external superelement. Use Schur complement reduction without component modes. Use the following values for the undefined quantities in Figure 1: L = 200.0 mm

M = 200.0 kg

iωt f1(t) = 50.0e N

iωt f2(t) = -50.0e N

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Figure 4-1. Beam with concentrated masses that is subject to harmonic excitation The following input file is for the superelement creation run. The left half of the beam is modeled with ten CBEAM elements. The ASET1 bulk entry specifies the boundary DOF. ASSIGN output2='frf.out',unit=89 $ SOL 108 DIAG 8, 15, 56 $ CEND $ DISP(phase)=all FREQ=100 SPC=100 $ FRFOUT(asmbulk,extbulk,geom, extid=10, dmigop2=89, solve,asmbulk) $ BEGIN BULK $ $ Units: N, mm, sec, C $ FREQ1, 100, 10.0, 10.0, 9 $ SPC1, 100, 123456, 1 $ GRID, 1, 0, -100.0, 0.0, 0.0 GRID, 2, 0, -90.0, 0.0, 0.0 GRID, 3, 0, -80.0, 0.0, 0.0 GRID, 4, 0, -70.0, 0.0, 0.0 GRID, 5, 0, -60.0, 0.0, 0.0 GRID, 6, 0, -50.0, 0.0, 0.0 GRID, 7, 0, -40.0, 0.0, 0.0 GRID, 8, 0, -30.0, 0.0, 0.0 GRID, 9, 0, -20.0, 0.0, 0.0 GRID, 10, 0, -10.0, 0.0, 0.0

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GRID, 11, 0, 0.0, 0.0, 0.0 $ CBEAM, 101, 100, 1, 2, 0.0, 1.0, 0.0 CBEAM, 102, 100, 2, 3, 0.0, 1.0, 0.0 CBEAM, 103, 100, 3, 4, 0.0, 1.0, 0.0 CBEAM, 104, 100, 4, 5, 0.0, 1.0, 0.0 CBEAM, 105, 100, 5, 6, 0.0, 1.0, 0.0 CBEAM, 106, 100, 6, 7, 0.0, 1.0, 0.0 CBEAM, 107, 100, 7, 8, 0.0, 1.0, 0.0 CBEAM, 108, 100, 8, 9, 0.0, 1.0, 0.0 CBEAM, 109, 100, 9, 10, 0.0, 1.0, 0.0 CBEAM, 110, 100, 10, 11, 0.0, 1.0, 0.0 $ PBEAML, 100, 100, , rod, , 10.0 $ MAT1, 100, 2.040+5, , 0.29, 7.86-12, 12.0-6, 0.0, 0.02 $ CONM2, 1001, 6, 0, 0.2 $ ASET1, 123456, 11 $ ENDDATA

The following input file is for the system run. The right half of the beam is modeled with ten CBEAM elements. The harmonic excitation forces are modeled with RLOAD2, DAREA, and TABLED1 bulk entries. ASSIGN inputt2='frf.out', unit=100 $ SOL 108 DIAG 8, 15, 56 $ CEND $ DISP(phase)=all FREQ=100 SPC=100 DLOAD=100 $ BEGIN BULK $ $ Units: N, mm, sec, C $ FREQ1, 100, 10.0, 10.0, 9 $ SPC1, 100, 123456, 11 $ GRID, 1, 0, 0.0, 0.0, 0.0 GRID, 2, 0, 10.0, 0.0, 0.0 GRID, 3, 0, 20.0, 0.0, 0.0 GRID, 4, 0, 30.0, 0.0, 0.0 GRID, 5, 0, 40.0, 0.0, 0.0 GRID, 6, 0, 50.0, 0.0, 0.0 GRID, 7, 0, 60.0, 0.0, 0.0

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GRID, 8, 0, 70.0, 0.0, 0.0 GRID, 9, 0, 80.0, 0.0, 0.0 GRID, 10, 0, 90.0, 0.0, 0.0 GRID, 11, 0, 100.0, 0.0, 0.0 $ CBEAM, 101, 100, 1, 2, 0.0, 1.0, 0.0 CBEAM, 102, 100, 2, 3, 0.0, 1.0, 0.0 CBEAM, 103, 100, 3, 4, 0.0, 1.0, 0.0 CBEAM, 104, 100, 4, 5, 0.0, 1.0, 0.0 CBEAM, 105, 100, 5, 6, 0.0, 1.0, 0.0 CBEAM, 106, 100, 6, 7, 0.0, 1.0, 0.0 CBEAM, 107, 100, 7, 8, 0.0, 1.0, 0.0 CBEAM, 108, 100, 8, 9, 0.0, 1.0, 0.0 CBEAM, 109, 100, 9, 10, 0.0, 1.0, 0.0 CBEAM, 110, 100, 10, 11, 0.0, 1.0, 0.0 $ PBEAML, 100, 100, , rod, , 10.0 $ MAT1, 100, 2.040+5, , 0.29, 7.86-12, 12.0-6, 0.0, 0.02 $ CONM2, 1001, 6, 0, 0.2 $ RLOAD2, 100, 101, 0.0, 0.0, 1001, 0.0, 0 DAREA, 101, 1, 2, 50.0 DAREA, 101, 6, 2, -50.0 $ TABLED1, 1001, , 0.0, 1.0, 1000.0, 1.0, endt $ SEBULK, 10, frfop2, , , , , 100 $ BEGIN SUPER 10 $ INCLUDE './beam_model.pch' $ ENDDATA

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FRFOUT

Frequency-Dependent External Superelement Creation Specification

Creates a frequency-dependent external superelement using Schur complement reduction.

FORMAT:

EXAMPLES: FRFOUT FRFOUT(ASMBULK,EXTID=100) FRFOUT(ASMBULK,EXTID=100,GEOM) FRFOUT(ASMBULK,EXTID=100,DMIGOP2=99)

DESCRIBERS:

Describer Meaning

ASMBULK Generate bulk entries related to the subsequent superelement assembly process and store them on the assembly punch file (.asm). This data is to be included in the main bulk portion of the subsequent assembly solution. See Remarks 3 and 5.

EXTBULK Generate and store bulk entries for the external superelement on the standard punch file (.pch). This data is used in the BEGIN SUPER portion of the bulk section of the subsequent assembly solution. If EXTBULK is not specified, the subsequent assembly solution retrieves the required data for the external superelement from the OP2 file. See Remarks 4 and 5.

GEOM Store full model geometry. See Remark 10.

SOLVE Compute the response to the input load with the reduced FRF matrices and loads. Data recovery to the analysis DOFs uses the same back transformations that are used for the output transformation matrix (OTM) generation. Data recovery is performed the same way in a modal solution as in a direct solution.

EXTID = seid seid (integer > 0) is the frequency-dependent superelement ID to be used in the SEBULK and SECONCT bulk entries stored on the assembly punch file (.asm) if ASMBULK is specified. See Remarks 2, 3, and 4.

DMIGOP2 = Store the boundary matrices as DMIG bulk entries on an unit OUTPUT2 file whose Fortran unit number is given by unit (integer>0). See Remarks 6 and 7.

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REMARKS: 1. The default is to output the frequency-dependent impedance and loads. Use the NOLOAD option to disable the load output.

2. EXTID and an seid value must be specified if one or more of ASMBULK or EXTBULK are specified.

3. If ASMBULK is specified, the following bulk entries are generated and stored on the assembly punch file (.asm): SEBULK seid …

SECONCT seid …

GRID entries for the boundary points

CORD2x entries associated with the above GRID entries

4. If EXTBULK is specified, the following bulk entries are generated and stored on the standard punch file (.pch): BEGIN SUPER seid …

GRID entries for the boundary points

CORD2x entries associated with the above GRID entries

EXTRN

ASET/ASET1

5. The punch output resulting from FRFOUT usage is determined by ASMBULK and EXTBULK as follows: • No ASMBULK or EXTBULK results in no punch output.

• ASMBULK, but no EXTBULK, results in punch output being generated and stored on the assembly punch file (.asm). See Remark 3.

• ASMBULK and EXTBULK results in punch output consisting of two distinct and separate parts. One part is generated and stored on the assembly punch file (.asm) as indicated in Remark 3. The other part is generated and stored on the standard punch file (.pch) as indicated in Remark 4.

6. If DMIGOP2 = unit is specified, an appropriate ASSIGN OUTPUT2 statement must be present in the File Management Section (FMS) for the absolute value of unit. An OUTPUT2 file created during a LP-64 Nastran executable superelement creation run cannot be used in a ILP-64 Nastran executable system run and vice versa. Note that beginning in NX Nastran 12, only the ILP-64 executable is available.

7. The default unit number for the DMIGOP2 describer is 30. To change the default unit number, use the EXTUNIT parameter.

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8. The creation of a frequency-dependent external superelement using FRFOUT involves running a NX Nastran job with the following additional data: • The data for the creation of the frequency-dependent external superelement is specified by the FRFOUT case control command, which must appear above the subcase level.

• The boundary points of the frequency-dependent external superelement are specified by ASET/ASET1, CSET/CSET1, BNDFIX/BNDFIX1, and BNDFREE/BNDFREE1 bulk entries.

• If the creation involves component mode reduction, the optional generalized coordinates are specified using QSET/QSET1 bulk entries. The boundary data for the component mode reduction may be specified using the BNDFIX/BNDFIX1 and BNDFREE/BNDFREE1 bulk entries (or their equivalent BSET/BSET1 and CSET/CSET1 bulk entries). (The default scenario assumes that all boundary points are fixed for the component mode reduction.)

9. To include differential stiffness in the definition of a frequency-dependent external superelement, two subcases are required in the creation run. The first subcase is a static subcase. The second subcase performs the analysis and generation of the frequency-dependent external superelement. To obtain the displacement field used to generate the differential stiffness effects, include a STATSUB case control command in the second subcase that references the first subcase. Always include the EXTSEOUT case control command above the subcase level. An example of the required setup is as follows: … SOL 111 CEND TITLE = … EXTSEOUT(…) $ SUBCASE 1 $ STATIC SUBCASE $ SUBCASE 2 $ DYNAMIC SUBCASE TSTEP = 100 STATSUB = 1 METHOD = 10 DLOAD = 20 BEGIN BULK …

For accuracy and consistency, the loads used to generate differential stiffness for the frequency-dependent external superelement during the creation run should be the same loads used in the system run without any scaling. If the loads are scaled by a non-unity scaling factor from a case control command like P2G or a bulk entry like LOAD, the differential stiffness portion of the frequency-dependent external superelement impedance will no longer be consistent with the applied loads.

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10. The GEOM describer outputs geometry data blocks GEOM1EXA, GEOM2EXA, and GEOM4EXA that contain all of the frequency-dependent external superelement geometry to support post-processing. By default, the full geometry is not exported; the GEOM describer must be explicitly defined to have these geometry data blocks written.

11. The OFREQ command should not be specified and is ignored for the frequency-dependent external superelement creation.

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SEBULK

Partitional Superelement Connection

Defines superelement boundary search options and a repeated, mirrored, or collector superelement.

FORMAT:

1 2 3 4 5 6 7 8 9 10 SEBULK SEID TYPE RSEID METHOD TOL LOC UNITNO

EXAMPLES:

SEBULK 14 REPEAT 4 AUTO 1.0E-3

SEBULK 101 FRFOP2 AUTO 1.0E-3 99

FIELDS:

Field Contents SEID Partitioned superelement identification number. (Integer > 0) TYPE Superelement type. (Character; No Default) PRIMARY Primary REPEAT Identical. See Remark 1. MIRROR Mirror. See Remarks 1 and 6. COLLCTR Collector. See Remark 7. EXTERNAL External. See Remark 8. EXTOP2 External using an OP2 file created in an earlier run. See Remark 8. EXTOP4 External using an OP4 file created in an earlier run.See Remark 8. External using an OP2 file created in an earlier run. FRFOP2 See Remarks 10 and 11. RSEID Identification number of the reference superelement, used if TYPE=“REPEAT” and “MIRROR”. (Integer≥0; Default=0) METHOD Method to be used when searching for boundary grid points. (Character: “AUTO” or “MANUAL”; Default=“AUTO”) TOL Location tolerance to be used when searching for boundary grid points. (Real; Default=10E-5)

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Field Contents LOC Coincident location check option for manual connection option. (Character: “YES” or “NO”; Default=“YES”) UNITNO Fortran unit number for the OUTPUT2 or OP4 file (applicable and meaningful only when TYPE = ”EXTOP2”, “EXTOP4”, or "FRFOP2").

REMARKS: 1. The TYPE=“REPEAT” or “MIRROR” does not include superelements upstream of the reference superelement. A repeated or mirrored superelement can have boundaries, loads, constraints, and reduction procedures that are different than the reference superelement.

2. METHOD=“MANUAL” requires SECONCT entries. SEBNDRY and SEEXCLD, which reference SEID, will produce a fatal message.

3. SECONCT, SEBNDRY, and SEEXCLD entries can be used to augment the search procedure and/or override the global tolerance.

4. For combined automatic and manual boundary search, the METHOD=“AUTO” should be specified and connections should be specified on a SECONCT entry.

5. TOL and LOC are the default values that can be modified between two superelements by providing the required tolerance on the SECONCT entry.

6. TYPE=“MIRROR” also requires specification of a SEMPLN entry.

7. TYPE=“COLLCTR” indicates a collector superelement, which does not contain any grids or scalar points.

8. For TYPE = “EXTERNAL”, “EXTOP2”, or “EXTOP4”, see discussion under the description of the EXTSEOUT case control command for employing external superelements using the two-step procedure. For employing external superelements using the three-step procedure, see discussion under the description of the EXTOUT parameter.

9. This entry will only work if PART superelements (BEGIN SUPER) or external superelements created by employing the EXTSEOUT case control entry exist.

10. Specify TYPE = "FRFOP2" for frequency-dependent boundary matrices that are valid for SOL 108 and 111 only.

11. For TYPE = "FRFOP2", the boundary DOF must connect to the residual structure (SEID=0).

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PVT0 data block in superelement OP2 files

To allow for differences in units between an external superelement and the residual, the PVT0 data block is now written to external superelement OP2 files. The PVT0 data block contains the units data that is specified on the DTI,UNITS bulk entry for the external superelement.

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Shell element support Solution 401 now supports shell elements defined with the CTRIAR, CQUADR, CTRIA6, and CQUAD8 entries. CQUAD4 and CTRIA3 elements are also supported as inputs, and the software will treat them as CQUADR and CTRIAR elements. The shell elements are supported in the subcase types STATIC, PRELOAD, and MODAL. They are not supported in the BUCKLING, CYCLIC and FOURIER subcase types. The existing PSHELL is supported. In addition, the new PCOMPG1 property entry is available to define a composite property which allows for a different failure theory for each layer. The shell element using the PSHELL bulk entry supports geometry nonlinear conditions (large displacement, large rotation, and contact) and material nonlinear (plasticity and creep). When you use a nonlinear plastic or creep material, the NLAYERS parameter is supported to define the number of integration points through the thickness. The NLAYERS parameter supports 3, 5, 7, and 9 points through the thickness. A composite shell element using the PCOMPG1 property bulk entry supports the geometry nonlinear conditions, but does not support material nonlinear. The ZOFF field on the element entry is supported to offset the element reference plane.

PSHELL property • The MID1, MID2, and MID3 are all required. MID1 and MID2 must be explicitly defined, and the MID3 field defaults to the MID2 value.

• MID4 is optional. If MID4 is defined, MID1 and MID2 must be defined. MID4 is applied with respect to the element plane regardless if ZOFF is defined or not. A ZOFF definition on the element entry produces a coupling independent of the MID4. As a result, defining both MID4 and ZOFF together will create two independent sources of coupling. If you define both MID4 and ZOFF, the MID4 should represent an additional coupling which is unique to the ZOFF coupling.

• When plastic or creep nonlinear materials are defined, the MID1, MID2, and MID3 must all be the same, and MID4 must be undefined.

• The Z1 and Z2 fields on the PSHELL, which define fiber distances for stress calculations in other solution types, are not supported by SOL 401.

PCOMPG1 property • The new PCOMPG1 property entry is available to define a composite property which allows for a different failure theory for each layer.

• The existing MATFT defines the failure theory allowables for both shell and solid composites. MATFT is required to define allowables with the MAT9 and MAT11 material entries. If you are using the MAT1 material entry, you can optionally define the allowables with the MATFT, or you can

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specify them on the MAT1 entry directly. For shell composites, only FT = HILL/HOFF/TSAI/STRN are supported (NO FT = STRS/TS), and the transverse material properties are ignored for shells: FT = HILL/HOFF: Zt, Zc, S13, S23 are ignored. FT = TSAI: Zt, Zc, S13, S23, F13, F23 are ignored. FT = STRN: Zet, Zec, Se13, Se23 are ignored.

• When a composite property is used, the software does not create a smeared, homogeneous shell representation using classical lamination theory. Instead, an integration scheme similar to what is used for solid composites is used.

• Failure index and strength ratio output are supported for all failure indices.

Material support

• The MAT1 and MATT1 bulk entries define isotropic materials for any shell and composite property.

• The MAT2 and MATT2 bulk entries define anisotropic materials for any shell and composite property.

• The MAT8 and MATT8 bulk entries define orthotropic materials for any shell and composite property.

• The MAT9 and MATT9 bulk entries define anisotropic materials for any shell and composite property.

• The MAT11 and MATT11 bulk entries define orthotropic materials for any shell and composite property.

• The nonlinear plastic and creep material are only supported for the PSHELL.

• User defined materials defined with the UMAT external program are only supported for the PSHELL property.

Material coordinate system The material coordinate system is used to define the orientation of material properties when orthotropic or anisotropic materials are selected. In addition, stress and strain results are always output in the material coordinate system. The material coordinates are updated when large rotation occurs. The X-axis of the material coordinate system for the shell element is determined as follows:

• Option 1: If a material coordinate system is not explicitly selected on the element entry, the X-axis of the material coordinate system is, by default, aligned with the element edge defined by grid points G1 and G2. The X-axis can optionally be rotated by defining THETA on the element entry.

• Option 2: A material coordinate system can be selected with the MCID field on the element entry. The X-axis of the selected material coordinate system is projected onto the plane of the shell to define the shell material X-axis.

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In addition, if a composite property is used for the element with the PCOMPG1 entry, a unique THETA value can be defined for each ply. The THETA on the ply rotates the material x-axis for each ply relative to the element material x-axis as described above. The material Z-axis is the positive out-of-plane shell normal defined by the right-hand-rule and the grid point connection order. The material Y-axis is determined by the cross product of the material X-axis and Z-axis. Supported Loads • Pressure loads are supported with the PLOAD, PLOAD2, or PLOAD4 bulk entries.

• General loads are supported with the FORCE, FORCE1, FORCE2, MOMENT, MOMENT1, MOMENT2, DAREA, and SLOAD.

• Body loads are supported with the ACCELi, GRAV, RFORCE, and RFORCE1. The RFORCE2 is not supported.

• Temperature loads with variation through the element thickness are not supported using the TEMPP1 bulk entry.

Shell element output summary • Engineering stress and strain are always output.

• Stress and strain results are always output in the material coordinate system. The material coordinates are updated when large rotation occurs and large displacements effects are requested with PARAM,LGDISP,1.

• Shell elements using a PSHELL support stress/strain results at grid or Gauss points. Stress and strain is computed at the top and bottom of the element. The STRCUR describer, which requests output at the middle plane, is not supported.

• Composite shell elements using the PCOMPG1 entry only supports stress/strain results at grid points.

• The CENTER, CUBIC, or SGAGE options on the STRESS and STRAIN case control commands are not supported.

• The OMID parameter which is used in other solutions to output stress and strain in the element coordinate system is not supported.

• The Z1 and Z2 fields on the PSHELL, which define fiber distances for stress calculations for other solution types, is not supported by SOL 401.

• For composite shell elements, FI and SR is supported for all failure indices.

• New item codes have been created for the SOL 401 shell element output.

• The FORCE case control command can be used to request shell element resultants in material coordinates.

• Grid point forces are supported.

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• Shell elements support surface-to-surface contact and surface-to-surface glue. Edge-to-edge and surface-to-edge glue is not supported for shells in SOL 401. Both glue and contact results are support for the shell elements.

Additional information

• The SNORM parameter and bulk entry are only supported by the CTRIAR and CQUADR elements.

• The K6ROT parameter and bulk entry are only supported by the CTRIA6 and CQUAD8 elements.

Bar and beam element support Solution 401 now supports bar and beam elements defined with the CBAR and CBEAM entries. The bar and beam elements support large displacements and rotations when large displacements are requested with PARAM,LGDISP,1.

Physical properties

• The existing PBAR and PBARL entries define the physical properties for the BAR element.

• The existing PBEAM and PBEAML entries define the physical properties for the BEAM element.

• The intermediate stations defined with the X/XB field are permitted on the PBEAM and PBEAML entries if, for example, the beam cross section properties change in the middle. Although, output requests are only supported at the ends A and B. The software ignores output requests at the intermediate locations (0 < X/XB < 1.0).

Materials

• Only the MAT1 and MATT1 are supported.

• Plasticity and creep are not supported.

Supported loads

• The PLOAD1 bulk entry is supported to apply distributed loads.

• General loads supported by SOL 401 are also supported with bar and beam elements. For example, forces using the FORCE, FORCE1, and DAREA bulk entries, and body loads defined with the ACCELi, GRAV, and RFORCEi bulk entries. Bar and beam element output summary

• Element results include stress, element force, total strain, elastic strain, and thermal strain.

• Stress and force output requests are only supported at the ends A and B. The software ignores output requests at the intermediate locations (0 < X/XB < 1.0).

• Stress, strain, and force results are always output in the element coordinate system. The element coordinates are updated when large rotation occurs and large displacements effects are requested with PARAM,LGDISP,1.

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• The stress & strain output is similar to the existing format for other solutions, except that the minimum and maximum values (S-MIN and S-MAX), and the margin of safety values (M.S. -T, and M.S. -C) are not computed by SOL 401.

• The reported stresses SXC, SXD, SXE, and SXF are a combination of the normal and bending stress reported in the element axial direction at the cross section locations C, D, E, and F.

• The element force output includes the bending moment and shear force in planes 1 and 2, axial force, total torque, and warping torque.

Spring and bushing element support You can now use the CELAS1, CELAS2, CBUSH1D, and CBUSH elements in SOL 401 for stiffness definitions. CELAS1 - Scalar Spring Connection • A single CELAS1 element connects two degrees-of-freedom at two different grid points. It behaves as a simple extension/compression or rotational spring, carrying either force or moment loads.

• If you define the CELAS1 element between non-coincident grid points, the CELAS1 element does not account for the distance between the connecting grid points when transfering loads. This is important when you expect your spring stiffness to carry tranverse loads. The CELAS1 element is safe to use when connecting coincident grid points. The CBUSH element is recommend when connecting non-coincident grid points.

• With the CELAS1 element, you can define either a constant or a nonlinear stiffness. o You define the constant stiffness in the Ki field on the PELAS entry. The constant spring stiffness definition is independent of the displacement.

o You define the nonlinear spring when the CELAS1 references both the PELAS and PELAST bulk entries. The TKNID field on the PELAST entry selects a TABLEDi entry, which defines the force versus displacement data.

• The CELAS1 element does not support large displacement effects when PARAM,LGDISP,1 is defined. You can include the CELAS1 element in a solution with PARAM,LGDISP,1 defined, but it should not be located in a region of the model where large rotations occur. If you define the CELAS1 as a nonlinear spring, the software uses the nonlinear spring defintion whether large displacements are turned on or off.

• You can request force and stress output for the CELAS1 element.

CELAS2 - Scalar Spring Connection • A single CELAS1 element connects two degrees-of-freedom at two different grid points. It behaves as a simple extension/compression or rotational springs, carrying either force or moment loads.

• If you define the CELAS2 element between non-coincident grid points, the CELAS2 element does not account for the distance between the connecting grid points when transfering loads. This is

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important when you expect your spring stiffness to carry tranverse loads. The CELAS2 element is safe to use when connecting coincident grid points. The CBUSH element is recommend when connecting non-coincident grid points.

• The CELAS2 element only supports a constant spring stiffness which is independent of the displacement. This stiffness is defined in the Ki field on the CELAS2 entry. No property entry is used with the CELAS2 element.

• The CELAS2 element does not support large displacement effects when PARAM,LGDISP,1 is defined. You can include the CELAS2 element in a solution with PARAM,LGDISP,1 defined, but it should not be located in a region of the model where large rotations occur.

• You can request force and stress output for the CELAS2 element.

CBUSH1D - Rod Type Spring Connection • The CBUSH1D element is a one dimensional axial spring.

• The CBUSH1D element stiffness and forces are only axial. It can be used to define an axial spring between coincident or non-coincident grid points. When the grid points are coincident, the x-axis of the coordinate system selected with the CID field on the CBUSH1D entry becomes the axial direction. When the grid points are non-coincident, the line from grid point A to grid point B is the element axis.

• A CBUSH1D element connecting non-coincident grid points supports large displacement effects when PARAM,LGDISP,1 is defined. The CBUSH1D element with non-coincident grid points is the only spring element in SOL 401 which supports large displacements. A CBUSH1D element connecting coincident grid points does not support large displacement effects when PARAM,LGDISP,1 is defined. In this case, the CBUSH1D element axis remains fixed.

• The CBUSH1D element supports either a constant or a nonlinear stiffness option. The constant spring stiffness definition is independent of the displacement and is defined with the K field on the on the PBUSH1D entry. The nonlinear spring definition is a force versus displacement table. The software uses the nonlinear spring data when large displacements are turned on or off with the parameter LGDISP. The nonlinear spring is defined by the following fields in the continuation row on the PBUSH1D entry:

o “SPRING” should be defined in the field 2 of the continuation row.

o "TABLE" should be defined in field 3 of the continuation row.

o The ID of a TABLEDi entry should be defined in field 4 of the continuation row.

o The TABLEDi entry defines the force versus displacement relationship.

• You can request force and stress output for the CBUSH1D element.

CBUSH - Defines a generalized spring.

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• A unique feature of the CBUSH element relative to the other spring elements is that it accounts for the distance between the connecting grid points when transfering loads. As a result, it is a safe choice for connecting either coincident or non-coincident grid points.

• The CBUSH entry supports either a constant, or a nonlinear stiffness option: o The constant spring stiffness definition is independent of the displacement. This stiffness is defined in a “K” row on the PBUSH entry, following by a stiffness value for each of the six degree-of-freedom.

o The nonlinear spring definition is a force versus displacement table. The nonlinear spring is defined when the CBUSH entry references both the PBUSH and PBUSHT bulk entries. The TKNIDi fields on the PBUSHT select the force versus displacement tables. The software uses the nonlinear spring when large displacements are turned on or off with the parameter LGDISP.

• The CBUSH element does not support large displacement effects when PARAM,LGDISP,1 is defined. You can include the CBUSH element in a solution with PARAM,LGDISP,1 defined, but it should not be located in a region of the model where large rotations occur.

• You can request force, stress, and strain output for the CBUSH element.

• The new system cell 665 is available to globally turn off the computation of the CBUSH coupling moments when the connecting grid points are not coincident. The new system cell applies to all solutions except for SOLs 402, 601, and 701. SYSTEM(665) = 0 (default) The coupling moments are computed. SYSTEM(665) = 1 The coupling moments are not computed.

Nonlinear buckling A nonlinear buckling analysis is used to accurately determine what the critical buckling load is and how a structure behaves after it has buckled. You can now request a nonlinear buckling analysis in a SOL 401 statics subcase. You can choose from one of the following three arc-length methods: • Riks arc-length method

• Modified Riks arc-length method

• Crisfield arc-length method

To request the nonlinear buckling analysis, your statics subcase should include the standard ANALYSIS=STATICS command along with the new NLARCL=ID case control command. The ID on the NLARCL command selects the new NLARCL bulk entry which defines the nonlinear buckling parameters. The NLARCL command in the subcase is the trigger which the software uses to start the nonlinear buckling analysis. The referenced NLARCL bulk entry is also required, even when the default values are used. The nonlinear buckling statics subcase must be either the first subcase, or the last in a sequence of static subcases. A nonlinear buckling statics subcase can only be followed by a modal subcase.

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• If the nonlinear buckling statics subcase is the first subcase, all of the loads defined in the current subcase are incrementally applied by the software during the arc-length solution.

• If the nonlinear buckling statics subcase is the last subcase and it is sequentially dependent, the loads applied in the previous subcase are held constant in the current subcase. The difference between the load defined in the nonlinear buckling statics subcase and the load from the previous subcase is computed. This load difference is incrementally applied by the software during the arc-length solution.

You select loads in a nonlinear buckling statics subcase with either the LOAD=n or DLOAD=n case control commands. Although, you cannot increment loads in a nonlinear buckling statics subcase with a TSTEP1 bulk entry since the software increments the loads for you. If you define a TSTEP1 entry in a nonlinear buckling statics subcase, you must define it with a constant time. That is, it must have an end time (Tend) which is the same as the start time for that subcase. In addition, the output frequency option Nout on the TSTEP1 entry is ignored in a nonlinear buckling statics subcase. The output frequency is instead controlled by the NOUTAL parameter on the NLARCL bulk entry. If you want to define a specific load sequence up to the point of buckling, you can do this with static subcases without buckling defined before your nonlinear buckling statics subcase. In these previous static subcases, you can increment loads with the TSTEP1 bulk entry. The new NLARCL bulk entry has the following solution parameters: = RIKS selects the Riks arc-length method TYPE = MRIKS selects the modified Riks arc-length method (Default) = CRIS selects the Crisfield arc-length method Minimum allowable arc-length adjustment ratio between increments for the adaptive MINALR arc-length method. (0.0=1.0, Default=4.0) Defines the overall upper and lower bounds on the load increment /arc-length in MAXR the subcase. Scale factor for controlling loading contribution in the arc-length constraint. SCALE (Real>0.0; Default = 0.0) Desired number of iterations for convergence to be used for the adaptive arc-length DESITER adjustment. (Integer>0, Default=12) Maximum number of controlled load increments done in the arc-length subcase MXINC (Integer>0; default=20) Initial load factor. This load factor will be used to compute initial arc-length (REAL>0, LDFACIN DEFAULT=1.0). Skip factor for output of the incremental results. Output always occurs at the final increment. For example, if you define NOUTAL=2, output occurs at every other NOUTAL converged solution increment and for the final increment. If you define NOUTAL=0, output only occurs at the final increment. (Integer≥0; Default=1) Maximum value of load-factor at which solution will be terminated. (Real, Default = MXLDFAC 1.0)

Initial Imperfections You define the X,Y,Z location of a grid point on the GRID entry. An option is now available to adjust this location with a +/- delta X,Y,Z position. For example, if a grid point is defined on the GRID

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entry at 1.0, 1.0, 0.0, and a delta of .2, 0.0, 0.0 is defined, the new modeled location for this grid point becomes 1.2, 1.0, 0.0. This location adjustment is useful in the nonlinear buckling analysis to define an imperfection. For example, an imperfection on the side of a cylinder which is under axial compression will impose a deliberate location for buckling.

The grid point imperfections are selected with the new IMPERF case control command which selects the new IMPERF or IMPRADD bulk entries. The IMPRADD entry allows you to combine multiple IMPERF entries, and scale the referenced imperfection sets either independently or collectively.

The IMPERF case control command must be defined globally (above the subcases). As a result, the updated location of the referenced grid points applies to all subcases.

Restrictions

• The software issues a fatal error if LGDISP=-1 and an arc-length solution is requested.

• The software issues a fatal error if an arc-length solution is requested in the context of a Simcenter Multiphysics solution.

• The software issues a fatal error if a sequentially dependent STATICS or PRELOAD subcase follows an arc-length subcase.

• The software issues a fatal error if a sequentially dependent arc-length subcase follows another sequentially dependent arc-length subcase.

• An enforced displacement defined with the SPCD bulk entry is held constant in a nonlinear buckling solution.

Arc-length theory

The concept of the arc-length method is to modulate the applied loads in order to produce solutions with displacement increments of manageable size of a given load step. In order to modulate the applied load, an additional variable, the load factor, and a constraint equation are introduced. There are various approaches to providing a constraint equation.

Consider a residual load {R}.

Equation 5-1. where F represents the internal forces, and the total external load P is expressed as:

Equation 5-2. where P0 denotes the applied load at the end of the preceding subcase, ΔP represents the load increment in the current subcase, and μ is the load factor varying from 0 to 1, but not limited to this range, within the subcase. Linearizing {R} about (u,μ), R(u,μ) can be expressed as:

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Equation 5-3. Based on the above equations, the equilibrium condition at (u+Δu, μ+Δμ) dictates that

Equation 5-4.

where, is the follower matrix, is the stiffness matrix , and . The iteration equation can be derived by rearranging Equation 5-4:

Equation 5-5. where the follower matrix is omitted. The iterative process can be established by decomposing the equation above into two parts:

Equation 5-6. Then the trial solution is obtained by

Equation 5-7. with

Equation 5-8. where Δμ can be obtained from the constraint equation. Riks Method and Its Variations The displacement increment is limited by a constraint equation:

Equation 5-9.

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where w is a scaling factor you specify with the SCALE parameter on the NLARCL bulk entry, and Δl is defined by

Equation 5-10. You define the initial value of Δμ with the LDFACIN parameter on the NLARCL bulk entry. The constraint of Equation 5-9 has a disparity in the dimension by mixing the displacements with the load factor. For this reason, the scaling factor (w) is introduced so that you can scale μ to the appropriate dimension or delete the Δμ term. The default value of w is zero as demonstrated in Figure 5-4. The iteration follows the path on the plane normal to the initial tangent as shown in Figure 5-1. Therefore the subsequent iterations (i > 1) must satisfy

Equation 5-11. Recalling that the first iteration should result in

Equation 5-12. Equation 5-11 may be reduced to

Equation 5-13. from which the load factors for the subsequent iterations are determined by

Equation 5-14. and

Equation 5-15.

Notice that the normal plane does not change during the iteration by Riks method. In addition, {ΔuP} remains constant if the iteration process is the modified Newton's method.

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Alternatively, the normal plane may be updated at every iteration. If the normal plane is to be normal to the cumulative incremental displacements for the preceding iterations as shown in Figure 5-2, the orthogonality condition in Equation 5-11 should be modified to:

Equation 5-16. The increment in the load factor for i > 1 is obtained by solving Equation 5-16,

Equation 5-17. This variation of Riks method has an advantage over the Crisfield method as it avoids the solution of a quadratic equation. Crisfield Method Instead of iterating on the normal plane, the solution is sought on the surface defined by Equation 5-9 with an arc-length of Δl as depicted in Figure 5-3,

Equation 5-18. This constraint can be interpreted as keeping the incremental displacement constant, if w=0, as shown in Figure 5-4. Substituting Equation 5-8 into the preceding equation, we obtain a quadratic equation in terms of Δμ:

Equation 5-19. where

Equation 5-20. Since the Crisfield method leads to a quadratic equation, the selection of the proper root of this equation becomes the most critical process for the success of this method. There are two roots to Equation 5-19,

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Equation 5-21. The root is chosen so that the angle between two vectors {ui-1 - uo} and {ui - uo} is less than 90 degrees,

Equation 5-22. There are cases where no roots can be found. Such is the case when the trial solution is far from the true solution and stays outside the region covered by the arc-length. In this case, the trial solution vector is scaled so that the direction vector intersects with the surface defined by Equation 5-18. The wrong choice of the root could cause an unintentional loading path reversal, by which the solution returns to the previous state. Such cases can be detected by checking the orthogonality of the incremental displacements of the two successive solutions. If this case is detected, the root is chosen so that the angle between {ui - uo} and {ui - uo} is an acute angle. Adaptive Arc-Length Method It is difficult to estimate a proper arc-length for multi-degree-of-freedom problems. The initial arc-length for the Crisfield method can be determined by

Equation 5-23. with Δμ1 = μ1 = LDFACIN parameter on the NLARCL bulk entry. You can define the maximum number of increments in the subcase with the MXINC parameter on the NLARCL bulk entry. The arc-length should be continuously updated at every increment using the information gathered during the preceding increment. One method is to reduce the arc-length if it requires an excessive number of iterations to attain a converged solution,

Equation 5-24.

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where Id is the desired number of iterations for convergence and defined with the DESITER parameter on the NLARCL bulk entry, and Imax is the number of iterations required for convergence from the preceding step. The adaptive process should be based on the arc-length ratio,

Equation 5-25. Combining two criteria, the new arc-length ratio is adapted to the nonlinearity by

Equation 5-26. In order to maintain the stability for the adaptive process, ALRATIO should also be bounded, MINALR < ALRATIO < MAXALR You can define the parameters MINALR and MAXALR on the NLARCL bulk entry, which have the defaults of 0.25 and 4., respectively. If the adjusted ALRATIO falls outside the bounds, ALRATIO is reset to the limit. Then the arc-length is updated at the beginning of the next step based on ALRATIO as follows:

Δlnew = ALRATIO * Δlold In the unstable regime where the stiffness is negative, the load factor decreases with a forward step. When this happens, the sign of Δμ1 should be reversed. This possibility should be examined at the beginning of each increment. The sign can be determined by the sign of a dot product,

Equation 5-27. An adaptive bisection algorithm is also incorporated to cope with divergent cases. If the iterative process using the arc-length method tends to diverge, the arc-length is bisected. The bisection is combined in concert with the stiffness matrix update strategy. The bisection procedure continues until the iterative process is stabilized and a converged solution is found. However, the number of contiguous bisections is limited by the parameter MAXBIS on the NLCNTL bulk entry. The variable arc-length at every increment invokes the recovery from the bisection process once the difficulties in convergence are overcome.

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Figure 5-1. Riks Method

Figure 5-2. Modified Riks Method

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Figure 5-3. Crisfield Method - Arc-length in terms of Combined Variables

Figure 5-4. Crisfield Method - Arc-length in terms of Displacements

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NLARCL

SOL 401 nonlinear buckling request

Requests a nonlinear buckling solution in a SOL 401 statics subcase

FORMAT: NLARCL=n

EXAMPLES: NLARCL=33

DESCRIBERS:

Describer Meaning n Set identification number of a NLARCL bulk entry. (Integer>0)

REMARKS: 1. To request the nonlinear buckling analysis in SOL 401, your statics subcase should include the standard ANALYSIS=STATICS command and the NLARCL command. The ID on the NLARCL command selects the NLARCL bulk entry which defines the nonlinear buckling parameters.

2. The NLARCL command in the subcase is the trigger which the software uses to start the nonlinear buckling analysis. The referenced NLARCL bulk entry is also required, even when the default values are used.

3. The nonlinear buckling statics subcase must be either the first subcase, or the last in a sequence of static subcases. A nonlinear buckling statics subcase can only be followed by a modal subcase. a. If the nonlinear buckling statics subcase is the first subcase, all of the loads defined in the current subcase are incrementally applied by the software during the arc-length solution.

b. If the nonlinear buckling statics subcase is the last subcase and it is sequentially dependent, the loads applied in the previous subcase are held constant in the current subcase. The difference between the load defined in the nonlinear buckling statics subcase and the load from the previous subcase is computed. This load difference is incrementally applied by the software during the arc-length solution.

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IMPERF

SOL 401 Grid Point Position Deltas

Selects grid point position deltas in SOL 401.

FORMAT: IMPERF=n

EXAMPLES: IMPERF=33

DESCRIBERS:

Describer Meaning n Set identification number of an IMPRADD or IMPERF bulk entry. (Integer>0)

REMARKS: 1. This command is only supported in SOL 401.

2. The IMPERF case control command must be defined globally (above the subcases). As a result, the updated location of the referenced grid points applies to all subcases.

3. You can use the IMPERF bulk entry to adjust the X,Y,Z location of a grid point with a positive or negative delta.

4. The set identification number n can refer to a IMPRADD entry which then combines multiple IMPERF entries, or it can refer to an individual IMPERF entry.

5. The deltas are also referred to as imperfections since they can be used in a nonlinear buckling solution to induce a buckling condition.

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NLARCL

SOL 401 Nonlinear Buckling Control

Defines control parameters for SOL 401 nonlinear buckling. FORMAT:

1 2 3 4 5 6 7 8 9 10 NLARCL ID PARAM1 VALUE1 PARAM2 VALUE2 PARAM3 VALUE3 PARAM4 VALUE4 PARAM5 VALUE5 -etc-

EXAMPLE:

NLARCL 1 TYPE CRIS MINALR 0.25 MAXALR 4.0 SCALE 0.0

FIELDS:

Field Contents

SID Identification number. (Integer > 0) PARAMi Name of the NLARCL parameter. Allowable names are given in the parameter listing below. (Character) VALUEi Value of the parameter. (Real, Integer, or Character)

NLARCL PARAMETERS:

Table 5-1.

Name Description

TYPE = RIKS selects the Riks arc-length method = MRIKS selects the modified Riks arc-length method (Default) = CRIS selects the Crisfield arc-length method MINALR Minimum allowable arc-length adjustment ratio between increments for the adaptive arc-length method. (0.00.0; Default = 20.0) SCALE Scale factor for controlling loading contribution in the arc-length constraint. (Real>0.0; Default = 0.0)

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Table 5-1.

Name Description

DESITER Desired number of iterations for convergence to be used for the adaptive arc-length adjustment. (Integer>0, Default=12) MXINC Maximum number of controlled load increments done in the arc-length subcase (Integer>0; Default=20) LDFACIN Initial load factor. This load factor will be used to compute initial arc-length (Real>0, Default=1.0). NOUTAL Skip factor for output of the incremental results. Output always occurs at the final increment. For example, if you define NOUTAL=2, output occurs at every other converged solution increment and for the final increment. If you define NOUTAL=0, output only occurs at the final increment. (Integer≥0; Default=1) MXLDFAC Maximum value of load-factor at which solution will be terminated. (Real, Default = 1.0)

2. The NLARCL case control command in a statics subcase is the trigger which the software uses to start the nonlinear buckling analysis. The referenced NLARCL bulk entry is also required, even when the default values are used.

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IMPERF

SOL 401 Grid Point Position Deltas

Defines grid point position deltas for SOL 401.

FORMAT:

1 2 3 4 5 6 7 8 9 10 IMPERF SID CS GRID 1 ΔX1 ΔY1 ΔZ1 GRID 2 ΔX2 ΔY2 ΔZ2 -etc-

EXAMPLE:

IMPERF 2 0 1 -0.008 0.0367 0.234 2 0.001 -0.0005 0.067

FIELDS:

Field Contents SID Set identification number. (Integer > 0) CS Coordinate system in which deltas are specified. (Integer > 0; Default=0) GRIDi Grid point identification number. (Integer > 0) ΔXi, ΔYi, Grid point position deltas (Real; No default) ΔZi

REMARKS: 1. Only supported in SOL 401.

2. You can use the IMPERF bulk entry to adjust the X,Y,Z location of a grid point with a positive or negative delta.

3. The IMPERF case control command which references a IMPERF bulk entry must be defined globally (above the subcases). As a result, the updated location of the referenced grid points applies to all subcases.

4. The grid point deltas are also referred to as imperfections since they can be used in a nonlinear buckling solution to induce a buckling condition.

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IMPRADD

SOL 401 Union of Grid Point Position Delta Sets

Defines a union of grid point position delta sets defined with multiple IMPERF bulk entries for SOL 401.

FORMAT:

1 2 3 4 5 6 7 8 9 10 IMPRADD SID S S1 I1 S2 I2 S3 I3 S4 I4 -etc-

EXAMPLE:

IMPRADD 1 1.000 1.000 1 1.2 2 0.25 3 -1.5 7

FIELDS:

Field Contents SID Overall set identification number referenced on the IMPERF case control command. (Integer > 0) S Overall scale factor (Real, Default=1.0) Si Scale factor for individual IMPERF bulk entries. (Real, Default=1.0) Set identification numbers of individual IMPERF bulk entries. (Integer Ii > 0)

REMARKS: 1. Only supported in SOL 401.

2. SID must be unique to other IMPRADD entries.

3. The IMPRADD entry allows you to combine multiple IMPERF bulk entries into a single set and optionally scale the referenced individual sets either independently or collectively.

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Bolt preload improvements for SOL 401

The SOL 401 bolt preload method iterates to determine the uniform axial strain which produces the axial bolt force you request. The software then reapplies the computed strain for the consecutive subcases. The initial strain method is selected by defining ETYPE=3 on the BOLT bulk entry.

A new optional cut-plane method is available for SOL 401 and selected by defining ETYPE=2 on the BOLT bulk entry. With the new cut-plane method, the software cuts the bolt in half, it creates new grid points such that grid pairs exist at the cut, it creates a glue connection at the cut with the axial stiffness zeroed out, it evenly distributes the opposing axial bolt force to the grids on each side of the cut, then it solves a statics solution to determine the axial displacement of each bolt half. The software then stiffens the axial glue connection which holds the grid pairs in their relative deformed state for the consecutive subcases.

Both the existing ETYPE=3 uniform strain method and the new ETYPE=2 cut-plane method produce accurate results, including when the bolt bends or when large rotations occur with geometry nonlinear.

Two advantages of the new ETYPE=2 cut-plane method are:

• Since the software does not need to iterate on the axial strain, this method can be more efficient.

• Since the inputs are consistent with SOL 101, it is easier to convert an input file from SOL 101 to SOL 401.

Both the ETYPE=3 uniform strain method, and the ETYPE=2 cut-plane method allow you to model bolts with either the 3D solid elements CHEXA, CPENTA, and CTETRA, or the 2D plane stress elements CPLSTS3, CPLSTS4, CPLSTS6, and CPLSTS8. A preload subcase is required, and it can include geometric and material nonlinear conditions.

Note that all of the BOLT bulk entries referenced in the same input file must be either ETYPE=2, or all ETYPE=3. A fatal error will occur if BOLT entries with both ETYPE=2 and ETYPE=3 are referenced.

See the updated BOLT entry.

Defining a BOLT bulk entry for the cut-plane method (ETYPE=2)

The cut-plane method requires that you use the ETYPE=2 input format on the BOLT bulk entry. With this format, you list the grid point IDs connected to the element edges (2D bolt) or faces (3D bolt) where the software will cut the bolt. You define the list of grid points in the Gi fields on the BOLT entry.

You optionally define the CSID and IDIR fields on the BOLT bulk entry:

• The bolt coordinate system can optionally be defined on the CSID field.

• The bolt axial direction can optionally be defined on the IDIR field.

Alternately, if you leave both the CSID and IDIR fields blank, the software will automatically determine the coordinate system and the bolt axis. In this case, the grid points listed in Gi must be coplanar.

When you define IDIR as non-zero, the software does not determine the bolt axis, and the grid points listed in Gi do not need to be coplanar. Although, it is recommended that they are approximately on a plane perpendicular to the bolt axis you defined.

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Note For the NX Nastran 12 release, when using the new ETYPE=2 cut-plane method, the grid points listed in Gi should be coplanar, or at least close to coplanar. If your bolt cut-plane is not planar, your solution results may not be accurate. If you define a ETYPE=2 bolt with a non-planar cut-plane, the software will still solve without a warning. If the grid points listed on Gi are not coplanar, you should use the uniform strain method by defining the ETYPE=3 bolt.

When you use the cut-plane method and you choose to define your preload on an associated BOLTFRC bulk entry, you can define your preload on an associated BOLTFRC bulk entry as a displacement or a force. The STRAIN preload option on the BOLTFRC bulk entry is not supported with the cut-plane method and will cause a fatal error if defined. If you use the displacement option, the value you enter is the total shortening of the bolt length as result of your bolt preload. The LEN field on the BOLTFRC bulk entry which defines the bolt length is ignored when you use the cut-plane method. Defining a BOLT bulk entry for the uniform strain method (ETYPE=3) The uniform strain method requires that you use the ETYPE=3 input format on the BOLT bulk entry. With this format, you list all of the 2D or 3D element IDs which define the bolt. You optionally define the CSID and IDIR fields on the BOLT bulk entry: • The bolt coordinate system can optionally be defined on the CSID field, and the bolt axial direction can optionally be defined on the IDIR field.

• Alternately, if you leave both the CSID and IDIR fields blank, the software will automatically determine the coordinate system and the bolt axis.

You optionally define the GP field on the BOLT bulk entry: • You can optionally define the GP field identification number of the grid point where the bolt cross sectional area is calculated. The grid point you enter must be included in the connectivity of elements that are used to model the bolt. As a best practice, you should select GP such that it is near the middle of the cross section of the bolt.

• Alternately, if you leave the GP field blank, the software will automatically determine a middle location to compute the cross sectional area.

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BOLT

Bolt definition

Selects the elements to be included in the bolt preload calculation. FORMAT FOR ETYPE = 1:

1 2 3 4 5 6 7 8 9 10 BOLT BID ETYPE EID1 EID2 EID3 EID4 EID5 EID6 EID7 “THRU” EID8 “BY” INC -etc-

FORMAT FOR ETYPE = 2:

1 2 3 4 5 6 7 8 9 10 BOLT BID ETYPE CSID IDIR G1 G2 G3 G4 G5 “THRU” G6 “BY” INC -etc-

FORMAT FOR ETYPE = 3:

1 2 3 4 5 6 7 8 9 10 BOLT BID ETYPE CSID IDIR GP EID1 EID2 EID3 EID4 EID5 EID6 EID7 EID8 EID9 “THRU” EID10 “BY” INC -etc-

EXAMPLES: ETYPE = 1 for SOLs 101, 103, 105, 107 through 112

BOLT 4 1 11

ETYPE = 1 for SOL 601

BOLT 4 1 11 8 2 1 20 14 15 16 28 30 33

ETYPE = 2

BOLT 8 2 4 3 12 23 55 128 133 THRU 165

ETYPE = 3

BOLT 9 3 1 3 148 56 24 43 21 73 52 62 41 106 THRU 202

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FIELDS:

Field Contents BID Bolt identification number. (Integer > 0) ETYPE Element type. (Integer; No default) = 1 to model bolts with CBAR and CBEAM elements in SOLs 101, 103, 105, 107 through 112, 402, and 601. = 2 to model bolts with CHEXA, CPENTA and CTETRA elements in SOLs 101, 103, 105, 107 through 112, 401 and 402. = 3 to model bolts with CHEXA, CPENTA, CTETRA, CPLSTS3, CPLSTS4, CPLSTS6, and CPLSTS8 elements in SOLs 401 and 402, or CHEXA, CPENTA, CPYRAM, and CTETRA elements in SOL 601. “BY” Specifies an increment when using THRU option. (Character) INC Increment used with THRU option. (Integer; Default = 1) INC > 0 can be defined, for example ...106,THRU,126,BY,INC,2 INC < 0 can be defined, for example ...126,THRU,106,BY,INC,-2

FIELDS FOR ETYPE = 1:

Field Contents EIDi Selects element identification numbers to include in the bolt preload calculation. See Remark 2 and SOL 601 Remark 1. (Integer > 0, or using “THRU”; EID7 < EID8 for THRU option; No default)

FIELDS FOR ETYPE = 2:

Field Contents CSID Identification number of the coordinate system used to define the bolt axis. For the basic coordinate system, CSID = 0. (Integer ≥ 0; See Remark 7 for default behaviour.) IDIR Direction of bolt axis relative to CSID. (Integer; See Remark 7 for default behaviour.) = 1 for the X direction = 2 for the Y direction = 3 for the Z direction See SOL 401 Remark 2. See SOL 402 Remark 6.

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Field Contents Gi Identification numbers of grid points that form a cross section through the bolt. See Remarks 3 and 4. (Integer ≥ 0; No default)

FIELDS FOR ETYPE = 3:

Field Contents EIDi Selects element identification numbers to include in the bolt preload calculation. All elements representing the bolt must be included in EIDi, and have the same PID. (Integer > 0, or using “THRU”; EID7 < EID8 for THRU option; No default) CSID Identification number of the coordinate system used to define the bolt axis. For the basic coordinate system, CSID = 0. (Integer ≥ 0; Default=0) IDIR Direction of bolt axis relative to CSID. (Integer; Default = 0)

= 0 for automatic determination of the bolt axis. = 1 for the X direction = 2 for the Y direction = 3 for the Z direction See SOL 401 Remark 3. See SOL 402 Remarks 1, 2 and 3 . See SOL 601 Remark 2. GP For SOL 401, the identification number of the grid point where the bolt cross sectional area is calculated. See Remarks 3 and 5. See also SOL 401 Remark 3. (Integer > 0 or blank) For SOL 402, the identification number of the grid point where the bolt cross sectional area is calculated. See Remark 3. See also SOL 402 Remarks 4 and 5. (Integer > 0; No default) For SOL 601, the identification number of the grid point where the bolt is split. See Remark 3 and SOL 601 Remarks 3 and 4. (Integer ≥ 0 or blank)

REMARKS: 1. Each BOLT entry defines a single physical bolt which can be composed of multiple elements.

2. If multiple CBAR and CBEAM elements are used to model a bolt in SOL 101, 103, 105, 107 through 112, only one of the elements must be listed on the BOLT entry. Enter the element ID in the EID1 field.

3. Any grid point listed in the Gi or GP fields must be included in the connectivity of elements that are used to model the bolt.

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4. Gi must select enough GRID entries to define a cross section through the bolt. The selected Gi can only be included on a single BOLT entry. The grids can be listed in any order on the BOLT entry. For parabolic elements, mid-nodes must also be listed. Any Gi listed on a BOLT entry cannot be used in the connectivity of a solid composite element or be included in an SPC. The software splits the bolt mesh by duplicating each Gi on the BOLT entry. The identification numbers for the duplicated grid points start at the highest user-defined grid ID in the model plus one and continue sequentially higher. A pressure load cannot be applied to any face of an element if the connectivity of the element includes a Gi listed on a BOLT entry.

5. As a best practice, select GP such that it is near the middle of the cross section of the bolt.

6. In SOL 105, both the bolt preload and service load are scaled to determine the buckling load.

7. For SOLs 101, 103, 105, 107 through 112, if you leave both the CSID and IDIR fields blank, the software automatically determines the coordinate system and the bolt axis. In order to do this computation, the grid points listed in the Gi fields must lie approximately on a plane perpendicular to the intended bolt axis. If the cut you define is not close to being planar, a fatal error will occur. In addition, if the cut is planar but the plane is not perpendicular to the intended bolt axis, the software computed coordinate system and bolt axis will be skewed from the intended bolt axis, and your preloads will not be accurate. Regardless if the CSID and IDIR fields are defined or not defined, when using the ETYPE=2 cut-plane method, the grid points listed in Gi should be coplanar, or at least close to coplanar. If your bolt cut-plane is not planar, your solution results may not be accurate. If you define a ETYPE=2 bolt with a non-planar cut-plane, the software will still solve without a warning.

8. For SOL 101, when you define a bolt with ETYPE=2, the software cuts the bolt in half, it creates new grid points resulting in grid pairs at the cut, it evenly distributes the opposing axial bolt force to the grids on each side of the cut, and it solves a statics solution to determine the axial displacement of each bolt half. The software then holds the grid pairs in their relative deformed state for the consecutive static solution. Begininning in NX Nastran 12, the software creates a glue connection at the cut which holds the grid pairs in their relative deformed state. The glue based approach accounts for bending along the bolt axis since rotational stiffness is included in the glue condition. The glue approach is supported by the default sparse solver, but not supported by the element iterative solver in SOL 101. If you run with the element iterative solver in SOL 101 and you have defined the ETYPE=2 bolt, the software will revert to an MPC approach. The MPC approach accounts for the axial stiffness, but not the rotations. As a result, bending is not accounted for with the MPC approach.

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REMARKS RELATED TO SOL 601: 1. All CBAR and CBEAM elements used to model the bolt must be included in EIDi list and they all must have the same PID.

2. When IDIR = 0 or blank (default), the direction of the bolt axis is automatically determined by the software to coincide with minimum principal moment of inertia of the bolt. CSID is ignored when IDIR = 0 or blank.

3. The software splits the bolt mesh at the grid point entered in the GP field.

4. GP = 0 or blank is allowed only if IDIR = 0 or blank. In this case, the location of the bolt plane is automatically determined by the program.

REMARKS RELATED TO SOL 401: 1. All of the BOLT bulk entries referenced in the same input file must be either TYPE=2, or all TYPE=3. A fatal error will occur if BOLT entries with both TYPE=2 and TYPE=3 are referenced.

2. ETYPE=2 remarks.

• When using the ETYPE=2 cut-plane method, the grid points listed in Gi should be coplanar, or at least close to coplanar. If your bolt cut-plane is not planar, your solution results may not be accurate. If you define a ETYPE=2 bolt with a non-planar cut-plane, the software will still solve without a warning. If the grid points listed on Gi are not coplanar, you should use the uniform strain method by defining the ETYPE=3 bolt.

• When CSID and IDIR are both blank, the software automatically determines the coordinate system and the bolt axis. In this case, the grid points listed in Gi must be coplanar.

• If you define IDIR as non-zero, the software does not determine the bolt axis. In this case, the grid points listed in Gi do not need to be coplanar. Although, it is recommended that they are approximately on a plane perpendicular to the bolt axis.

3. ETYPE=3 remarks.

• When CSID and IDIR are blank, the software automatically determines the coordinate system and the bolt axis.

• When GP blank, the software automatically determines a middle location to compute the cross sectional area.

4. Composite solid elements (PCOMPS property card) are not supported for preloaded bolts.

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REMARKS RELATED TO SOL 402: 1. When IDIR = 0 or blank (default), the direction of the bolt axis is automatically determined by the software to coincide with minimum principal moment of inertia of the bolt. CSID is ignored when IDIR = 0 or blank.

2. When IDIR is not specified, internal faces along the bolt cut are connected using contact elements. When it is specified, each face of the bolt cut are connected to an RBE3 element and both elements are linked to the same master node.

3. If IDIR >0, the cut cannot be perpendicular to the bolt axis.

4. The software splits the bolt mesh at the grid point entered in the GP field.

5. If GP = 0 or blank, the location of the bolt plane is automatically determined by the program.

6. When ETYPE = 2, if grid points of the cut are not coplanar, IDIR must be specified.

7. ETYPE=2 is the preferred method to model bolts.

Balanced initial stress-strain The option to apply an unbalanced initial stress-strain became available in NX Nastran 11. An unbalanced initial stress-strain results in deformation when applied to an unconstrained body with the possibility of residual stress. For example, since approximate methods are used to measure residual stress, the application of the residual stress in your finite element analysis as an initial condition may not result in a state of complete equilibrium, and instead may result in both residual stress and deformation. Note that the definition of an NX Nastran unbalanced initial stress-strain references the unconstrained body, although, an initial stress-strain can be applied to constrained or unconstrained models. A new method is available in NX Nastran 12 which you can use to balance an unbalanced initial stress-strain. The method removes the unbalanced part by removing the strains which produce a deformation. After you use the new balancing method, your initial stress-strain will produce a self-equilibrating stress state and no deformations. The method requires that a part of your unbalanced initial stress-strain is actually balanced. Offset solution The balancing method requires that you first run a static offset-solution to obtain the total strain output as a result of your unbalanced initial stress-strain with the model unconstrained. You only apply the unbalanced initial stress-strain in the offset solution. No temperature loads, mechanical loads, or enforced displacements are applied for this step.

Since there is no thermal strain {εth}, the total strain output {ε} from the offset-solution is computed as:

{ε} = {εe} + {εin} - {ε0} where, {ε} = total strains you can request with the STRAIN case control command,

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{εe} = elastic strains you can request with the ELSTRN case control command,

{εin}= inelastic strains you can request with the PLSTRN or CRSTRN case control commands,

{ε0} = initial strains you can request with the OSTNINI case control command.

The part of the unbalanced initial stress-strain {ε0} which yields a stress is included in the elastic strain {εe} and possibly the inelastic strain {εin} if you have included any nonlinear materials. After removing {εe} and {εin} from the unbalanced initial stress-strain {ε0}, the total strain {ε} output from the offset solution includes only the part of the initial stress-strain which causes deformation.

You will use the total strain {ε} output from the offset-solution as an offset strain {εoff} in the consecutive solution. The total strain output is requested with the STRAIN=ALL case control command. If your model contains multiple components, each with a unique balanced initial strain, you can run an offset-solution for each component separately. The offset strains can be used in a consecutive assembly solution. Note that, regardless if your initial stress-strain is applied to all locations on a component or to only a portion, the offset strains are the total strains at all locations on that component. To allow the static offset-solution to complete with the unconstrained condition, a matrix stabilization option is available. Setting the new parameter MSTAB to 1 on the NLCNTL bulk entry will turn on the option. In addition, the new MSFAC parameter is available to define a scale factor for matrix stabilization. Specifically, when you define MSTAB=1, the software scales the diagonal terms by the factor (1+MSFAC). Balanced solution Once your offset strains are computed, you can run the consecutive balanced solution that includes your initial stress-strain {ε0}, your offset strain {εoff}, and any other loads (temperature loads, mechanical loads, enforced displacements). You can optionally run a consecutive balanced solution as unconstrained with only your initial stress-strain {ε0} and your offset strain {εoff} to verify that the strain offsets have removed all deformation leaving only the stress state. You can use the matrix stabilization option (MSTAB=1) in the verification solution if you choose to keep your model unconstrained for this step. Finally, you can apply initial stress-strain {ε0} and your offset strain {εoff} in a balanced component or assembly solution which includes any load types and constraints. During the balanced solution, the offset strains are included in the internal force calculation to compensate for the deformations caused by your initial stress-strain. See Balanced stress-strain computation for details. Defining a balanced initial stress or strain condition The new INITS(OFFSET) case control command and INITSO bulk entry are available to input the offset strain. Multiple INITSO bulk entries can be combined with the existing INITADD bulk entry. You define the initial stress-strain with the INITS case control command, which selects the INITS bulk entry. You can also define multiple INITS bulk entries, each with a unique ID, and then combine them using the INITADD bulk entry. The INITADD entry is selected with the ID on the INITS case control. The INITS case control command must be defined globally, above the subcases. It is reapplied in every static subcase. The software does not need to associate a balanced initial stress-strain definition with an offset strain definition in the balanced solution. As a result, the SID defined on the INITS(OFFSET) command

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selecting your offset strains, and the SID defined on the INIT command selecting your unbalanced initial stress-strain can match, or not match. There is no software requirement either way. You cannot define an initial stress-strain on the newly supported beam and shell elements, although, these elements can be included in the solution which includes an initial stress-strain. Multiple initial stress-strain at the same location Currently, if you define initial stress-strain on the same grid or element corner location, a fatal error occurs. In NX Nastran 12, this will no longer be a restriction. You can now define multiple unbalanced and balanced initial stress-strain at the same location. They can also be defined using different coordinate systems. The software first converts all stress definitions to strain, then it transforms all strain into the basic coordinate system, and finally it adds the strains defined at common locations. Balanced stress-strain computation The reference (modeled) configuration of a component with balanced initial stress/strain includes initial strains. Therefore, under the deformation field resulting from combined initial strains and service loads, the total strains measured from the reference configuration is given by:

{ε} = f({u}) + {εoff} where, f({u}) = [B]{u} with [B] being the strain displacement matrix for small strain formulation. The total strains are decomposed as:

{ε} = {εe} + {εth} + {εin} - {ε0} where, {ε} = total strains which you can request with the STRAIN case control command,

{εe} = elastic strains you can request with the ELSTRN case control command,

{εth} = thermal strains you can request with the THSTRN case control command,

{εin} = inelastic strains you can request with the PLSTRN case control command,

{ε0} = initial strains you can request with the OSTNINI case control command. The elastic strains are obtained as,

{εe} = {ε} - {εth} - {εin} + {ε0} In terms of balanced strain offsets, and assuming small strain formulation, the elastic strains are given by

{εe} = [B]{u} - {εth} - {εin} + ({ε0} + {εoff})

For components in the model without initial strains, {ε0} = {0} and {εoff} = {0}. For the components with unbalanced initial strains, {εoff} = {0}. Note that if you request the total strain output {ε} for the balanced solution with the STRAIN case control command, the software will add the offset strain back to the total as if it was never removed for the solution. As a result, the total strain computation when a balanced initial stress-strain is defined is the same as when an unbalanced initial stress-strain is defined.

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Converting an initial stress to an initial strain

If you define an initial stress {σ0}, the software converts this to a corresponding initial strain {ε0} by using the elasticity matrix {D0} at the reference temperature Tref. -1 {ε0} = {D0} {σ0} Defining an initial stress or strain condition The option to define an initial stress or strain condition is available on all elements in SOL 401 except for beam elements, shell elements, plane strain elements, generalized plane strain elements, solid composite elements, and rigid elements. You define the initial stress or strain with the INITS case control command, which selects the INITS bulk entry. The INITS case control command must be defined globally, above the subcases. It is reapplied in every static subcase. The first row on the INITS bulk entry includes the following fields. • The TYPE field defines the data type: TYPE=STRESS or TYPE=STRAIN

• The CSYS field selects the coordinate system for the stress or strain components. The default is the basic coordinate system. CSYS = -1 can also be defined to select the material system.

• The LOC field defines the location: LOC= GRID: Specifies that data is defined at grid points. LOC= NOE: Specifies that data is defined on an element at grid locations. This can include corner and/or midside grid locations.

You define the stress or strain data on the consecutive rows on the INITS entry. The software assumes the data is either engineering stress or engineering strain. The format of these rows depends on the data location defined in the LOC field, and the element type. Format for the 3D solid elements CTETRA, CHEXA, CPENTA and CPYRAM: Stress at grid points (TYPE=STRESS, LOC=GRID): GRID ID Sxx Syy Szz Sxy Syz Szx ....

Strain data at grid points (TYPE=STRAIN, LOC=GRID): GRID ID Exx Eyy Ezz Exy Eyz Ezx ...

Stress data at the element corners (TYPE=STRESS, LOC=NOE): ElemID GRIDID Sxx Syy Szz Sxy Syz Szx ...

Strain data at the element corners (TYPE= STRAIN, LOC=NOE): ElemID GRIDID Exx Eyy Ezz Exy Eyz Ezx ... For the plane stress elements CPLSTS3, CPLSTS4, CPLSTS6, CPLSTS8, the software uses both in-plane and out-of-plane initial strain values. Although, only in-plane initial stress values are used. For example, the following formats should be used when the plane stress elements are defined on the XY plane, and the basic coordinate system (default) is used. For elements defined on the XZ plane, Sxx, Szz, Szx or Exx, Eyy, Ezz, Ezx would be defined.

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Stress data at grid points (TYPE=STRESS, LOC=GRID): GRID ID Sxx Syy Sxy ...

Strain data at grid points (TYPE=STRAIN, LOC=GRID): GRID ID Exx Eyy Ezz Exy ...

Stress data at the element corners (TYPE=STRESS, LOC=NOE): ElemID GRIDID Sxx Syy Sxy ...

Strain data at the element corners (TYPE= STRAIN, LOC=NOE): ElemID GRIDID Exx Eyy Ezz Exy ... For the axisymmetric elements CQUADX4, CQUADX8, CTRAX3, CTRAX6, in-plane (radial and axial) and out-of-plane (theta) initial stress or strain values are used by the software. For example, the following formats should be used when the axisymmetric elements are defined on the XY plane, and the basic coordinate system (default) is used. For elements defined on the XZ plane, Sxx, Szz, Szx or Exx, Ezz, Ezx should be defined. Stress data at grid points (TYPE=STRESS, LOC=GRID): GRID ID Sxx Syy Szz Sxy ...

Strain data at grid points (TYPE= STRAIN, LOC=GRID): GRID ID Exx Eyy Ezz Exy ...

Stress data at the element corners (TYPE=STRESS, LOC=NOE): ElemID GRIDID Sxx Syy Szz Sxy ...

Strain data at the element corners (TYPE= STRAIN, LOC=NOE): ElemID GRIDID Exx Eyy Ezz Exy ... For the plane stress and axisymmetric elements, if you select a coordinate system other than the basic system in the CSYS field on the INITS entry, the software first transforms the data into the basic system, and then uses the components consistent with the formats described above. The option to output the initial strains using the OSTNINI case control command is available. The output can be requested at either the grid or corner Gauss locations on elements. The OSTNINI command must be defined globally, and the output occurs once at the beginning of the solution. The strains are output in the basic coordinate system. Additional information: • Initial stress and strain can be defined on a subset of the model. The software assumes a value of 0.0 at the locations where data is undefined. An exception is when data is undefined at a mid-side grid point, and data is defined at both or either related corners. In this case, the software interpolates a value for that mid-side grid point.

• The option to apply an initial stress or strain condition before applying other loads in an initial subcase is available to help convergence. The first subcase should have Tend=0.0 on the

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TSTEP1 entry and no load set selected. The number of increments can optionally be defined with NINC on the TSTEP1 entry to increment the initial stress or strain. When NINC=1 (default), the initial stress or strain is applied in a single step. When NINC>1, the initial stress or strain is ramped. A service load cannot be defined when ramping initial stress or strain with NINC>1.

• The software converts an initial stress to an initial strain using the elastic modulus defined on the MATi entries. If you define MATTi bulk entries to define the elastic modulus as temperature dependent, the software uses the initial temperatures selected by the TEMPERATURE(INIT) case control command to evaluate the temperature dependent elastic modulus. Data on the MATS1 bulk entry, if defined, is not used to convert stress to strain.

• You can define multiple INITS bulk entries, each with a unique ID, and then combine them using the INITADD bulk entry. The INITADD entry is selected with the ID on the INITS case control. The INITS entries selected by the INITADD entry must be all TYPE=STRESS or all TYPE=STRAIN. As a result, you cannot mix initial stress and initial strain definitions in the same input file.

• If you define data on the same grid or element corner location, a fatal error occurs.

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INITSO

Defines initial strain offsets in SOL 401.

Defines initial strain offsets in SOL 401. FORMAT OF INITIAL OFFSET STRAIN DEFINED ON GRID POINTS (TYPE=STRAIN AND LOC=GRID):

1 2 3 4 5 6 7 8 9 10 INITS SID STRAIN GRID CSYS GRID ID Exx Eyy Ezz Exy Eyz Ezx GRID ID Exx Eyy Ezz Exy Eyz Ezx ......

FORMAT OF INITIAL OFFSET STRAIN AT ELEMENT GRID LOCATIONS (TYPE=STRAIN AND LOC = NOE):

1 2 3 4 5 6 7 8 9 10 INITS SID STRAIN NOE CSYS Elem ID GRID ID Exx Eyy Ezz Exy Eyz Ezx Elem ID GRID ID Exx Eyy Ezz Exy Eyz Ezx ......

EXAMPLE:

1 2 3 4 5 6 7 8 9 10 INITS 3 STRAIN NOE 0 12 3 .0045 .0342 .00015 12 28 .00012 .0035 .00015 12 65 .00012 .0035 .00015 12 72 .00012 .0035 .00015

FIELDS:

Field Contents SID Initial stress or strain set identification number. (Integer>0; also see Remark 3)

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Field Contents TYPE Offset strains can only be defined as TYPE=STRAIN. This field must be defined. (Character) LOC The location where the data is defined. There is no default value for this field. This field must be defined. (Character) = GRID for data on grid points. = NOE for data on an element at grid locations. This can include corner and/or midside grid locations. CSYS Selects a coordinate system to define the initial stress or strain orientation. (Integer) = -1 Material coordinate system is used. = 0 Basic coordinate system is used. (Default) > 0 Selects a specific CSYS. Exx,Eyy,Ezz, Engineering offset strains representing the symmetric portion of the strain tensor. (Real) Exy,Eyz,Ezx When LOC=GRID: GRID ID Grid point ID where data is applied. (Integer>0) When LOC=NOE: Elem ID Element where the data is applied. (Integer>0) GRID ID Grid point ID defining a location on the element. (Integer>0)

REMARKS: 1. The ID of all INITSO and INITADD entries must be unique.

2. Multiple INITSO bulk entries can be defined, each with a unique ID, then combined with the INITADD entry. The INITADD entry is selected with the ID on the INITSO case control. The INITADD entry must include either all INITSO, or all INITS.

3. The option to define an initial stress or strain is available on all elements in SOL 401 except for the plane strain elements including the generalized plane strain elements, solid composite elements defined with the PCOMPS entry, rigid, beam, and shell elements.

4. The INITSO case control must be defined above the subcases (globally), and is reapplied in each static subcase. If you want to include the effects of initial stress or strain including any other load in a normal modes subcase, you should include a static subcase before the sequentially dependent normal modes subcase.

5. For the plane stress and axisymmetric elements, if you select a coordinate system other than the basic system in the CSYS field on the INITS entry, the software first

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transforms the data into the basic system, then uses the components consistent with the formats described below. For the plane stress elements CPLSTS3, CPLSTS4, CPLSTS6, CPLSTS8, both in-plane and out-of-plane initial strain values are used by the software. For the axisymmetric elements CQUADX4, CQUADX8, CTRAX3, CTRAX6, in-plane (radial and axial) and out-of-plane (theta) initial offset strain values are used by the software.

6. Initial offset strains can be defined on a subset of the model. The software assumes a value of 0.0 at the locations where data is undefined. An exceptiion is when data is undefined at a mid-side grid point, and data is defined at both or either of the related corners. In this case, the software will interpolate a value for that mid-side grid point.

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INITS

Defines initial stress or strain state in SOL 401.

FORMAT OF INITIAL STRESS DEFINED ON GRID POINTS (TYPE=STRESS AND LOC=GRID):

1 2 3 4 5 6 7 8 9 10 INITS SID STRESS GRID CSYS GRID ID Sxx Syy Szz Sxy Syz Szx GRID ID Sxx Syy Szz Sxy Syz Szx ......

FORMAT OF INITIAL STRESS DEFINED AT ELEMENT GRID LOCATIONS (TYPE=STRESS AND LOC = NOE):

1 2 3 4 5 6 7 8 9 10 INITS SID STRESS NOE CSYS Elem ID GRID ID Sxx Syy Szz Sxy Syz Szx Elem ID GRID ID Sxx Syy Szz Sxy Syz Szx ......

FORMAT OF INITIAL STRAIN DEFINED ON GRID POINTS (TYPE=STRAIN AND LOC=GRID):

1 2 3 4 5 6 7 8 9 10 INITS SID STRAIN GRID CSYS GRID ID Exx Eyy Ezz Exy Eyz Ezx GRID ID Exx Eyy Ezz Exy Eyz Ezx ......

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FORMAT OF INITIAL STRAIN AT ELEMENT GRID LOCATIONS (TYPE=STRAIN AND LOC = NOE):

1 2 3 4 5 6 7 8 9 10 INITS SID STRAIN NOE CSYS Elem ID GRID ID Exx Eyy Ezz Exy Eyz Ezx Elem ID GRID ID Exx Eyy Ezz Exy Eyz Ezx ......

EXAMPLE:

1 2 3 4 5 6 7 8 9 10 INITS SID STRAIN NOE 0 12 3 .0045 .0342 .00015 12 28 .00012 .0035 .00015 12 65 .00012 .0035 .00015 12 72 .00012 .0035 .00015

FIELDS:

Field Contents SID Initial stress or strain set identification number. (Integer>0; also see Remark 3) TYPE Defines if the defined data is initial stress or initial strain. There is no default value for this field. This field must be defined. (Character) = STRAIN for initial strain. = STRESS for initial stress. LOC The location where the data is defined. There is no default value for this field. This field must be defined. (Character) = GRID for data on grid points. = NOE for data on an element at grid locations. This can include corner and/or midside grid locations.

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Field Contents CSYS Selects a coordinate system to define the initial stress or strain orientation. (Integer) = -1 Material coordinate system is used. = 0 Basic coordinate system is used. (Default) > 0 Selects a specific CSYS. Exx,Eyy,Ezz, Engineering normal strains and engineering shear strains. (Real) Exy,Eyz,Ezx Sxx,Syy,Szz, Engineering normal stresses and engineering shear stresses. (Real) Sxy,Syz,Szx, When LOC=GRID: GRID ID Grid point ID where data is applied. (Integer>0) When LOC=NOE: Elem ID Element where the data is applied. (Integer>0) GRID ID Grid point ID defining a location on the element. (Integer>0)

REMARKS: 1. The ID of all INITS and INITADD entries must be unique.

2. The option to define an initial stress or strain is available on all elements in SOL 401 except for the plane strain elements including the generalized plane strain elements, solid composite elements defined with the PCOMPS entry, and rigid elements.

3. The INITS case control must be defined above the subcases (globally), and is reapplied in each static subcase. If you want to include the effects of initial stress or strain including any other load in a normal modes subcase, you should include a static subcase before the sequentially dependent normal modes subcase.

4. For the plane stress and axisymmetric elements, if you select a coordinate system other than the basic system in the CSYS field on the INITS entry, the software first transforms the data into the basic system, then uses the components consistent with the formats described below. For the plane stress elements CPLSTS3, CPLSTS4, CPLSTS6, CPLSTS8, both in-plane and out-of-plane initial strain values are used by the software. Although, only in-plane initial stress values are used. For example, when the plane stress elements are defined on the XY plane and the basic coordinate system is used to define the initial stress or strain, Sxx, Syy, Sxy or Exx, Eyy, Ezz, Exy should be defined. For elements defined on the XZ plane, Sxx, Szz, Szx or Exx, Eyy, Ezz, Ezx should be defined.

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For the axisymmetric elements CQUADX4, CQUADX8, CTRAX3, CTRAX6, in-plane (radial and axial) and out-of-plane (theta) initial stress or strain values are used by the software. For example, when the axisymmetric elements are defined on the XY plane and the basic coordinate system is used to define the initial stress or strain, Sxx, Syy, Szz, Sxy or Exx, Eyy, Ezz, Exy should be defined. For elements defined on the XZ plane, Sxx, Syy, Szz, Szx or Exx, Eyy, Ezz, Ezx should be defined.

5. Initial stress and strain can be defined on a subset of the model. The software assumes a value of 0.0 at the locations where data is undefined. An exceptiion is when data is undefined at a mid-side grid point, and data is defined at both or either of the related corners. In this case, the software will interpolate a value for that mid-side grid point.

6. The software converts initial stress to strain using the elastic modulus. Stress/strain data and the yield point on the MATS1 bulk entry, if defined, are not used to convert stress to strain.

7. Multiple INITS bulk entries can be defined, each with a unique ID, then combined with the INITADD entry. The INITADD entry is selected with the ID on the INITS case control. The INITS entries selected by the INITADD entry must be all TYPE=STRESS or all TYPE=STRAIN. As a result, you cannot mix initial stress and initial strain definitions in the same input file.

8. If data is defined on the same grid or element location, a fatal error will occur.

Contact improvements NX Nastran 12 includes the following new parameters on the BCTPARM bulk entry for surface-to-surface and edge-to-edge contact. • The new IPENRAMP parameter is available to request that the software ramp the removal of initial penetrations when INIPENE = 0 or 1. Initial penetrations can exist due to geometry or mesh irregularities between source and target faces or edges. (Integer; Default=0) = 0 (Default) No ramping is applied in the constant time subcase. = 1 The initial penetrations are ramped in a subcase using the load factor.

• The new INTRFC parameter is available to select the interface behavior between source and target regions. (Integer; Default=1) = 0 Inactive No interaction between the source and target regions. = 1 Standard (Default) Standard segment-segment contact algorithm with large sliding (pairing updates) and friction. = 2 No Sliding Does not allow sliding by assuming infinite friction. Source and target regions can separate. = 3 Bonded/Tied No relative displacement is permitted in both normal and tangential directions.

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= 4 No Separation No relative displacement in normal direction. Frictionless small sliding (no pairing updates) in tangential directions. = 5 Small sliding Simplified contact algorithm with no pairing updates or friction.

• The new CTDAMP parameter is available to request the stabilization damping option when you are relying on the contact condition to prevent rigid body conditions, but the contact condition is not active. = 0 (Default) No stabilization damping. = 1 Stabilization damping applied only in the first subcase and it is ramped down to zero by the end of the subcase. The stabilization damping is only applied this way when the entire pair status is open. = 2 Stabilization damping applied always as long as the pair status is open. = 3 Stabilization damping applied always regardless of the time and the pair status.

• If you request stabilization damping with the CTDAMP parameter, the new CTDAMPN parameter is available to either scale the normal damping value which the software automatically computes, or to define the normal damping value explicitly. (0.0

• If you request stabilization damping with the CTDAMP parameter, the new CTDAMPT parameter is available to either scale the tangential damping value which the software automatically computes, or to define the normal damping value explicitly. (0.0

• The new GAPVAL parameter is available to optionally define a constant gap or penetration between the source and target regions when INIPENE = 3. A negative GAPVAL means initial penetrations which will be eliminated. (Real; Default = 0.0)

Stress output coordinate system

Previously, SOL 401 would output stress and strain in basic coordinates for the 3D solid, plane strain, and plane stress elements. Now, SOL 401 outputs stress and strain in the body-fixed material coordinate system. The body-fixed material coordinate system is the material coordinate system relative to the deformed state.

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The transformation matrix from the initial or the body-fixed material coordinate system to the basic coordinate system is written to the new TRMBU or TRMBD datablocks, respectively, for post processors. The SYSTEM(627)=0 setting is available to optionally revert the stress and strain output for the 3D solid, plane strain, and plane stress elements back to the basic coordinate system. • SYSTEM(627)=0 - SOL 401 outputs stress and strain on the 3D solid, plane strain, and plane stress elements in the basic coordinate system.

• SYSTEM(627)=1 (Default) - SOL 401 outputs stress and strain on the 3D solid, plane strain, and plane stress elements in the body-fixed material coordinate system.

System cell 627 specifically applies to the 3D solids elements CTETRA, CHEXA, CPENTA and CPYRAM elements, the plane strain elements CPLSTN3, CPLSTN4, CPLSTN6, CPLSTN8, and the plane stress elements CPLSTS3, CPLSTS4, CPLSTS6, CPLSTS8. The system cell 627 does not apply to the beam, shell, and cohesive elements. The following summarizes the stress and strain output for these elements. • For the newly supported CBAR and CBEAM elements, the stress, strain, and element force (beam resultants) are always output in the body-fixed element coordinate system. CBAR and CBEAM elements only support isotropic materials. As a result, they do not have a material coordinate system.

• For the newly supported CTRIAR, CQUADR, CTRIA6, and CQUAD8 elements along with the CQUAD4 and CTRIA3 elements which are automatically converted to CQUADR and CTRIAR elements, the stress, strain, and element force (shell resultants) are always output in the body-fixed material coordinate system.

• For the cohesive elements, the relative displacements and tractions are always output in the body-fixed material coordinate system.

Progressive failure analysis The unidirectional fibre reinforced ply damage model (UD) became available in NX Nastran 11 to define progressive ply failure for solid element composites in SOL 401. This model is referred to as the UD ply failure model. The UD ply failure model is selected by entering UD in the PPFMOD field on the MATDMG entry. The following two ply failure enhancements are now available. 1. The shear damage (d12) for the UD ply failure model now supports a nonlinear function of thermodynamic force Y. You can specify the nonlinear function with the TABLEM5 bulk entry, which is referenced by the TID field on the MATDMG bulk entry. The TABLEM5 specifies the function d12=f(sqrt(Y)), where d12 is the y data, and sqrt(Y) is the x data.

2. A new enhanced unidirectional fibre reinforced ply damage model (EUD) is available. You can select the new model by entering EUD in the PPFMOD field on the MATDMG entry. Relative to the UD model, the EUD model allows for additional damage caused by fiber-matrix debonding and transverse cracking. The MATDMG bulk entry includes a new input format specifically for the EUD definition.

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Additional details:

• The UD and EUD models are both supported by composite solid elements.

• The UD and EUD models only support orthotropic materials. The material ID defined for a composite ply on the PCOMPS entry references a MAT11 and a MATDMG. You enter PFA in the FTi field on the PCOMPS entry.

• The UD and EUD models both require that you specify PARAM,MATNL,1 to activate the damage property. By default, PARAM,MATNL,-1, and PFA behavior is turned off.

• The UD and EUD models both support geometry nonlinear.

• You can include both the UD and EUD models on different plies on the same composite defined with the PCOMPS entry.

• The PFRESULTS case control command includes the CRKDSTY describer to request the crack density output. The ODAMGPFR datablock stores the crack density output. When you include the CRKDSTY describer on the PFRESULTS command, the EUD model outputs the transverse crack density output. It is a scalar value reported at the mid ply location for each ply at the element corners. The crack density is dimensionless.

• Both the UD and EUD models allow you to include coupling with plasticity. If you have included the coupling with plasticity, you can define the PLSTRN case control command in a subcase to request plastic strain output at grid points. The plastic strain at the Gauss points is not computed for composite solids.

• You can define six damage variables for the EUD method; d11, d22, d33, d12, d23, d13, which correspond to the variables df, d', d', d, d23, d in the constitutive model, respectively. You can include the DAMAGE describer on the PFRESULTS command to request the damage output. The damage values are reported at the mid ply location (per ply at the element corners). For both the UD and EUD models, damage values are computed relative to the ply coordinate system and are scalar quantities.

• For both the UD and EUD models, when you include the STATUS describer on the PFRESULTS command, a damage status is computed as an element result. The integer meaning of each damage status (0, 1, 2, or 3) is documented on the PFRESULTS command.

• For both the UD and EUD models, within a single ply, if the worst damage value is greater than 0.0 on a Gauss point, the software considers the ply as damaged. If the worst damage value on all Gauss points reaches the maximum allowed damage value specified in the DMAX field on the MATDMG entry, the ply has completely failed. The DMAX default is 0.999.

• For both the UD and EUD models, the dissipated energy requested with the ENERGY describer on the PFRESULTS case control command represents the energy dissipated due to damage and plasticity in the material. The output is a single scalar value per element.

• For both the UD and EUD models, stress and strain can be requested for specific elements, by ply and in the ply coordinate system. The plastic strain is only output at the middle location of each ply.

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• The shear damage (d12) used for the UD ply failure model can be defined as a linear or nonlinear function of the thermodynamic force Y. You can specify the nonlinear function with the TABLEM5 bulk entry, which is referenced by the TID field on the MATDMG bulk entry. The TABLEM5 specifies the function d12=f(sqrt(Y)), where d12 is the y data, and sqrt(Y) is the x data.

Enhanced unidirectional (EUD) ply model

You can select the EUD model by entering EUD in the PPFMOD field on the MATDMG entry. Relative to the UD model, the EUD model allows for additional damage caused by fiber-matrix debonding and transverse cracking. The MATDMG bulk entry includes an input format specifically for the EUD definition. EUD model - Elastic strain and thermodynamic forces The consititutive model for the EUD model is:

with,

and,

where,

df is the damage variable linked to fibers direction,

d, d', and d23 are the three damage variables linked to diffuse damage, with,

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are the three damage variables linked to transverse cracking, the superscript 0 is related to the undamaged material, and [x+] is 1 when x is positive, and 0 otherwise. EUD model - Thermodynamic forces Thermodynamic forces are obtained by taking the derivative of the potential with respect to the damage variables, taking the mean value over the ply thickness:

where,

is the mean value of x over the ply thickness,

is x when x is positive, and 0 otherwise, h is the ply thickness, and hc is a critical thickness defining the threshold between thin and thick ply behaviour.

For external plies, min(h,hc) should be replaced by min(2h,hc). EUD model - Evolution laws of the damage variable linked to fibers First, a "static" damage w is computed. Its evolution is a function of the thermodynamic forces described above:

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where,

are the breaking thresholds in traction and compression,

Yc is a critical thermodynamic force, k is a coupling coefficient. If a delay effect is considered, the damage becomes,

where,

τc and ac,

dmax is the maximum fibers damage.

In option, w can be limited to dmax before taking into account the time delay effect. EUD model - Evolution laws of damage variables linked to diffuse damage First, a "static" damage w is computed. Its evolution is a function of the thermodynamic forces described above,

Y0 is a fiber/matrix debonding threshold,

YC is a critical thermodynamic force,

b2 is a coupling coefficient. If a delay effect is considered, the damages become,

where,

τc and ac are parameters of the delay law,

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b3 is a coupling coefficient between the damage variables, ds is the maximum diffuse damage.

In option, w can be limited to ds before taking into account the time delay effect. Diffuse damages are not influenced by the damage linked to the fibers. EUD model - Evolution laws of damage variables linked to transverse cracking

We have , where ρ is the crack density. The rupture envelope is written,

where,

τc and ac are parameters of the delay law, b3 is a coupling coefficient between the damage variables,

ρs is the maximum crack damage. EUD model and plasticity We define the effective stresses,

A yield criteria is defined as a function of the effective stresses,

where, R(p)=Kpɣ is the yield function, p is the cumulated plastic strain,

R0 is the initial plasticity threshold, a is a coupling coefficient, K and ɣ are material parameters given by experimental testing. The plastic strain velocities are given by,

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EUD model - Specifying material properties and parameters

The following table shows where you specify the various material properties and parameters used in the EUD model.

Material proy or parameter Bulk entry (field name) 0 0 0 Ei , Gij , νij MAT11 b2 MATDMG (B2 field) b3 MATDMG (B3 field) h PCOMPS (TRi field) τc MATDMG (TAU field) ac MATDMG (ADEL field) dmax MATDMG (DMAX field) a MATDMG (A field) R0 MATDMG (LITK field) Κ MATDMG (BIGK field) Y MATDMG (EXPN field) ζ+ MATDMG (KSIT field) ζ- MATDMG (KSIC field) T Ydf MATDMG (Y11LIMT field) C Ydf MATDMG (Y11LIMC field) Y0 MATDMG (Y012 field) Yc MATDMG (YC12 field) K MATDMG (K field) ds MATDMG (DS field) C GI MATDMG (GIC field) C GII MATDMG (GIIC field) C GIII MATDMG (GIIIC field) ρs MATDMG (RO1 field) min(h,hc) MATDMG (HBAR field) ɑ MATDMG (ALPHA field) Controls if delay effect is used before applying the maximum MATDMG (USER field) damage.

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MATDMG

Material Properties for Progressive Ply Failure

Defines material properties and parameters for progressive ply failure in composite solid elements. Used in combination with MAT11 entries that have the same MID. Valid for SOLs 401 and 402.

FORMAT:

1 2 3 4 5 6 7 8 9 10 MATDMG MID PPFMOD COEF1 COEF1 COEF1 -etc-

FORMAT FOR PPFMOD="UD":

1 2 3 4 5 6 7 8 9 10 MATDMG MID UD Y012 YC12 YS12 YS22 Y11LIMT Y11LIMC KSIT KSIC B2 B3 A LITK BIGK EXPN TAU ADEL PLYUNI TID HBAR DMAX PE

FORMAT FOR PPFMOD="EUD":

1 2 3 4 5 6 7 8 9 10 MATDMG MID EUD Y012 YC12 K ALPHA Y11LIMT Y11LIMC KSIT KSIC B2 B3 A LITK BIGK EXPN TAU ADEL USER R01 HBAR DMAX DS GIC GIIC GIIIC

EXAMPLE:

MATDMG 3 UD 0.1 12.0 10.0 0.08 5.7 1.0E16 8.0 0.3 0.5 0.9 20.0 750.0 0.4 0.0001 0.43

FIELDS:

Field Contents MID Material identification number. (Integer > 0) PPFMOD Progressive ply failure model. Allowable entries are: “UD” for the unidirectional ply model. “EUD” for the enhanced unidirectional ply model. (Character; No default) If PPFMOD="UD"

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Field Contents

Y012 Energy threshold for shear damage d12. (Real > 0; For default behavior, see Remark 1)

YC12 Critical value of energy for shear damage d12. (Real > 0; For default behavior, see Remark 1)

YS12 Limit value of energy for shear damage d12. (Real > 0.0; No default) YS22 Limit energy in the matrix direction. (Real > 0.0; No default) Y11LIMT Energy threshold in tension for the fiber direction. (Real > 0.0; No default) Y11LIMC Energy threshold in compression for the fiber direction. (Real > 0.0; No default) KSIT Nonlinearity coefficient in tension for the fiber direction. See Remark 2. (Real; Default = 0.0) KSIC Nonlinearity coefficient in compression for the fiber direction. See Remark 2. (Real; Default = 0.0) B2 Coupling coefficient. (Real ≥ 0.0; Default = 0.0) B3 Coupling coefficient between the damage variables. (Real > 0.0; Default = 1.0) A Coupling coefficient. (Real ≥ 0.0; Default = 0.0) LITK Initial plastic threshold. (Real > 0.0; Default = 1.0E15) BIGK Parameter for Plastic Law. (Real ≥ 0.0; Default = 0.0) EXPN Exponent for Plastic Law. (Real ≥ 0.0; Default = 0.0) TAU Time constant. See Remark 3. (Real; Default = 0.0) ADEL Parameter for delay. See Remark 4. (Real > 0.0; Default = 1.0) PLYUNI Control parameter for the application of nonlinearity coefficients. (Integer = 0 or 1; Default = 0) 0: Nonlinearity coefficients are applied to stress. 1: Nonlinearity coefficients are applied to strain. Table identification number of a TABLEM5 entry. Used to TID define a nonlinear damage evolution law for in-plane shear. Integer ≥ 0 or blank; for default behavior, see Remark 1) HBAR Transition thickness of ply. (Real ≥ 0.0; Default = 0.0)

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Field Contents DMAX Maximum damage value at a Gauss point. (0.0 < Real ≤ 0.999; Default = 0.999) PE 3D effect parameter. (Integer = 0 or 1; Default = 0) 0: Plane stress effect option. The effect of damage in the normal and shear stress associated with the out-of-plane direction are ignored. 1: 3D stress effect option. The effect of damage in the normal and shear stress associated with the out-of-plane direction are included. If PPFMOD="EUD" Y012 Fiber/matrix debonding threshold. (Real > 0.0; No default). YC12 Critical thermodynamic force. (Real > 0.0; No default). K Coupling coefficient to account for the contribution of thermodynamic force Yd to fiber damage in compression. Yd is thermodynamic force linked to shear stress σ12 and σ13. (Real >=0.0; Default=0.0). ALPHA Parameter given by the user to define the relationship for three crack modes in rupture envelope. (Real > 0.0; Default=1.0). Y11LIMT Energy threshold in tension for the fiber direction. (Real > 0.0; No default). Y11LIMC Energy threshold in compression for the fiber direction. (Real > 0.0; No default). KSIT Nonlinearity coefficient in tension for the fiber direction. See Remark 2. (Real; Default = 0.0). KSIC Nonlinearity coefficient in compression for the fiber direction. See Remark 2. (Real; Default = 0.0). B2 Coupling coefficient to account for the contribution of thermodynamic force Yd’ to shear damage variable d. where d is the damage variable linked to shear stress σ12 and σ13. Yd’ is the thermodynamic force linked to normal stress σ22 and σ33. (Real ≥ 0.0; Default = 0.0). B3 Coupling coefficient between damage variables d and d’; (Real ≥ 0.0; Default = 0.0). A Coupling coefficient for plasticity; (Real>=0; Default=0.0). LITK Initial plastic threshold. (Real > 0.0; Default = 1.0E15). BITK Parameter for Plastic Law. (Real ≥ 0.0; Default = 0.0).

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Field Contents EXPN Exponent for Plastic Law. (Real ≥ 0.0; Default = 0.0). TAU Time constant. See Remark 3. (Real; Default = 0.0). ADEL Parameter for delay. See Remark 4. (Real > 0.0; Default = 1.0). USER If USER is equal to 1, static damage w is limited to the maximum damage before taking into account time delay effect. If USER is equal to 0, the “delayed” damage d after taking into account time delay effect is limited to the maximum damage. (Integer 0, 1; Default = 0). R01 Maximum transverse micro-cracking density. (Real; Default = 0.7). HBAR A critical thickness defining the threshold between thin and thick ply behavior. (Real ≥ 0.0; Default = 0.0). DMAX Maximum fiber damage value at a Gauss point. (0.0 < Real ≤ 0.999; Default = 0.999). DS Maximum diffuse damage value at a Gauss point. (0.0 < Real ≤ 0.999; Default = 0.55). GIC Critical mode I crack energy release rates for the ply. (Real > 0.0; No default). GIIC Critical mode II crack energy release rates for the ply. (Real > 0.0; No default). GIIC Critical mode III crack energy release rates for the ply. (Real > 0.0; No default).

REMARKS: 1. An error message is issued if the Y012 and YC12 fields are both blank, or if the Y012 field or the YC12 field is defined and the other is not.

2. The software uses the nonlinearity coefficients KSIT and KSIC to calculate the elastic modulus in the fiber direction as a nonlinear function of stress if PLYUNI = 0, or strain if PLYUNI = 1.

3. Use a positive value to define time delay. The software interprets negative values as zero time delay.

4. If TAU ≤ 0.0, there is no time delay and the ADEL field is ignored.

5. To define a nonlinear damage model for shear, you should leave the Y012 and YC12 fields blank and use the TID field to reference a TABLEM5 entry. On the TABLEM5 entry, you will include tabular data that defines how shear damage d12 varies as a function of thermodynamic force Y. An error message is issued if the

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Y012, YC12, and TID fields are all defined or are all blank, or if the Y012 field or the YC12 field is defined and the other is not.

6. For the UD model, the software uses the nonlinearity coefficients KSIT and KSIC to calculate the elastic modulus in the fiber direction as a nonlinear function of stress if PLYUNI= 0, or strain if PLYUNI = 1. For the EUD model, the software uses the nonlinearity coefficients KSIT and KSIC to calculate the elastic modulus in the fiber direction as a nonlinear function of strain.

7. You should enter the time delay as a positive value. The software interprets a negative time delay value as zero.

8. If TAU ≤ 0.0, there is no time delay and the ADEL field is ignored.

9. The shear damage (d12) used for the UD ply failure model can be defined as a linear or nonlinear function of the thermodynamic force Y. You can specify the nonlinear function with the TABLEM5 bulk entry, which is referenced by the TID field on the MATDMG bulk entry. The TABLEM5 specifies the function d12=f(sqrt(Y)), where d12 is the y data, and sqrt(Y) is the x data.

10. The coupling coefficient A determines if the normal stress in the transverse direction σ22 and the normal stress in the out-of-plane direction σ33 are taken p into consideration when plasticity occurs. For example, if A=0.0, then ε 22 and p ε 33, and the contribution of σ22 and σ33 to the yielding surface are ignored. The ɣ radius of the yielding surface follows the rule specified by R0+Kε p, where εp is the equivalent plastic strain, Ro is specified by LITK, K is specified by BIGK, and ɣ is specified by EXPN.

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TABLEM5

Tabular Function for Progressive Ply Failure

For progressive ply failure with the UD damage model in SOL 401, TABLEM5 is optionally used to define a nonlinear function relating the shear damage (d12) to the thermodynamic force (Y). TABLEM5 can only be referenced by the TID field on a MATDMG entry with PPFMOD=UD defined. FORMAT:

1 2 3 4 5 6 7 8 9 10 TABLEM5 TID EXTRAP X1 Y1 X2 Y2 X3 Y3 -etc.- "ENDT"

EXAMPLE:

TABLEM5 1 0.0 1.0 1.0 2.0 2.0 3.0 ENDT

FIELDS:

Field Contents TID Table identification number. (Integer > 0) EXTRAP Extrapolation option. (Integer= 0 or 1; Default=0) • If EXTRAP = 0, extrapolate the two starting data points to obtain the table look up when x < xi, and extrapolate the two ending data points to obtain the table look up when x > xi.

• If EXTRAP = 1, use the value of the table field at the starting data point for the table look up when x < xi, and use the value of the table field at the ending data point for the table look up when x > xi. Xi, Yi Tabular values. Xi are the thermodynamic force values. Yi are the the shear damage values. (Real) “ENDT” Flag indicating the end of the table.

REMARKS: 1. The TABLEM5 entry can only be referenced by the TID field on the MATDMG entry. The TABLEM5 entry defines the shear damage nonlinear function d12=f(sqrt(Y)), where d12 is the yi data, and sqrt(Y) is the xi data. Y in the function is the thermodynamic force.

2. The linear shear damage d12 is computed using Y012 and YC12, which you define on the MATDMG entry. Linear and nonlinear parameters can not be specified at the same time: An error message will be issued if the Y012, YC12, and TID fields on the MATDMG entry are either all defined or are all blank, or if the Y012 field or the YC12 field is defined and the other is not.

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3. Xi must be in either ascending or descending order, but not both. No warning message is issued if tabular data is input incorrectly.

4. Discontinuities may be specified between any two points except the two starting points or the two end points. For example, in Figure 5-5, discontinuities are allowed only between points X2 through X7. The value of Y at X3 in Figure 5-5 is:

y = (y3 + y4) / 2

5. At least one continuation entry must be specified.

6. Any xi, yi pair may be ignored by placing “SKIP” in either of the two fields.

7. The end of the table is indicated by the existence of “ENDT” in either of the two fields following the last entry. An error will occur if any continuations follow the entry containing the end-of-table flag “ENDT”.

8. The tabular data is interpolated for values of x that lie within the range of the tabular data and, when EXTRAP=0, the tabular data is extrapolated from the two starting or end points for values of x that lie outside the range of the tabular data. The value y that the software returns for the shear damage at thermodynamic force x is:

where yT(x) is the table look up at x. The table look-up is performed using linear interpolation within the table and linear extrapolation outside the table using the two starting or end points if EXTRAP = 0.

Figure 5-5. Example of Table Extrapolation and Discontinuity

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User defined material improvements

In NX Nastran 11, SOL 401 began supporting externally computed, user defined material models. You can define material models by developing and compiling an external routine. The MUMAT bulk entry is available to define the material data in the NX Nastran input file. The MUMAT entry in your input file is the trigger NX Nastran uses to call the external routine. The elements referencing the MUMAT entry material ID use an associated material law defined in the external material routine NXUMAT. The elements referencing the MUMAT entry must also reference MATi, and optional MATTi entries. NX Nastran uses the MATi / MATTi properties to compute an initial elastic stiffness. The initial elastic stiffness computed by NX Nastran, the data defined on the MATi, MATTI, and TABLEMi entries, and the data defined on the MUMAT entry, are all passed from NX Nastran to the external routine. Now in NX Nastran 12, you can optionally have your external routine update the elastic stiffness computed initially by NX Nastran, and then have the external routine pass this updated stiffness back to NX Nastran to use for the initial computations. The following two compiled example routines and NX Nastran input files are included with the NX Nastran installation to demonstrate the new initial stiffness update.

MODNAME1 Input File Description Hook matrix of initial stiffness for solid EHOOK nxumatex11.dat elements Hook matrix of initial stiffness for cohesive CZEHOOK nxumatex12.dat elements

See User defined materials in the Multi-Step Nonlinear User's Guide for details.

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Multi-step nonlinear kinematics SOL 402

A new NX Nastran solution sequence, SOL 402 - NLSTPKIN, is now available. SOL 402 is a multi-step, structural solution that supports a combination of subcase types (static linear, static nonlinear, nonlinear dynamic, preload, modal, Fourier, buckling) and large rotation kinematics.

Subcase analysis type Initial static / steady-state computation Geometric nonlinear effects Subcase sequencing Defining solution time steps Boundary conditions Mechanical loads Thermal input Element support Material support Glue support Contact support Nonlinear parameters Solver support Cyclic symmetry analysis Fourier analysis Buckling analysis Supported output Input summary Results file Input file example SOL 402 vs SOL 401

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Subcase analysis type SOL 402 allows a combination of the following subcases. The ANALYSIS case control command defines the subcase analysis type. STATICS (Nonlinear) static analysis. DYNAMICS (Nonlinear) dynamic analysis, including damping and inertia effects. MODES Normal Modes. PRELOAD Bolt Preload subcase computation. CYCMODES Cyclic Normal Modes. FOURIER Fourier Normal Modes. BUCKLING Buckling Modes (Incremental Stability) The ANALYSIS case control command does not have a default in SOL 402. Initial static / steady-state computation You define an initial condition with the IC case control command which references the TIC bulk entry. You can control the computation of initial conditions using the parameter IREF on the NLCNTLG entry. No initial static or steady-state computation are performed by default. An initial static computation can be used to define initial displacements. An initial steady-state computation can be used in a dynamics subcase to define initial velocities. Geometric nonlinear effects The parameter LGDISP turns the nonlinear large displacement capability on/off. If you define the parameter LGDISP for SOL 402, you must include it in the bulk data portion of your input file. The single PARAM,LGDISP setting is global and applies to all subcases. • PARAM,LGDISP,-1 (default) - Large displacement effects are turned off for ANALYSIS=STATIC, ANALYSIS=PRELOAD or ANALYSIS=DYNAMICS subcases. For further ANALYSIS=MODES, ANALYSIS=CYCMODES or ANALYSIS=FOURIER subcases, second order effects are ignored, in particular the stress stiffening effect of the previous static subcase. As a consequence, further ANALYSIS=BUCKLING subcases are not allowed. Small strains are assumed and follow the Engineering strain law.

• PARAM,LGDISP,1 - Large displacement effects are turned on for ANALYSIS=STATIC, ANALYSIS=PRELOAD, or ANALYSIS=DYNAMICS subcases. For further ANALYSIS=MODES, ANALYSIS=CYCMODES, or ANALYSIS=FOURIER subcases, second order effects are taken into account, in particular the stress stiffening effect of the previous static subcase. For further ANALYSIS=BUCKLING subcases, nonlinear effects are split in two terms: a dead load part and a varying part. The varying part is related to the loads variation from its latest static equilibrium. Small strains are assumed and follow the Piola-Kirchoff strain law.

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The parameter LGSTRN turns on/off large strains, displacements, and rotations. • PARAM,LGSTRN,0 (default) — Small strains are assumed.

• PARAM,LGSTRN,1 — Large strains, displacements, and rotations are assumed (that is, LGDISP is automatically set to 1). Large strain formulation is applicable to all elements. In particular, nonlinear material laws will switch to a Cauchy stress and Logarithmic strain. All TABLES1 stress/strain hardening curves should also use the same convention.

Subcase sequencing Subcase sequencing in SOL 402 defines the initial state for a subcase. You can use the SEQDEP case control command to define any subcase as sequentially dependent (SD), or non-sequentially dependent (NSD). SOL 402 uses time as the variable to increment loads. Both SD and NSD subcases in SOL 402 always use the final time from the previous subcase for their start time. • SEQDEP=YES (default) - The subcase is an SD subcase. An SD subcase uses the final computation state from the previous subcase for its starting state (for example, stress, strain, and displacements). An SD subcase ignores the RSUB parameter on the new NLCNTL2 bulk entry.

• SEQDEP=NO - The subcase is an NSD subcase. By default, an NSD subcase does not use a previous computation state for its starting state. However, an NSD subcase can optionally reload the computation state from the end of any previous subcase using the RSUB=n parameter on the NLCNTL2 bulk entry, where n can be -1, 0, or >0:

-1 Same behavior as SEQDEP=YES. 0 Subcase does not use a computation state from a previous subcase for its starting state (default for SEQDEP=NO). >0 Restart from the end of subcase n, where n references a previous subcase number.

In an ANALYSIS=PRELOAD subcase, the start time must be equal to the end time. For ANALYSIS=STATIC and DYNAMICS subcases, the end time must be greater than the start time. An ANALYSIS=PRELOAD subcase can be defined after an ANALYSIS=STATIC or DYNAMICS subcase. The ANALYSIS=PRELOAD subcase can only contain bolt forces and/or contact definitions. Defining solution time steps Both the TSTEP and TSTEP1 entries are supported in SOL 402, but we recommend the TSTEP1 entry. You cannot use both definitions in the same model. When more than one subcase is specified in the case control, the TSTEP1 entry is required in all subcases assigned by ANALYSIS = STATIC, PRELOAD, and DYNAMICS. The TSTEP1 bulk entry defines the time step intervals at which a solution is generated and output.

1 2 3 4 5 6 7 8 9 10 TSTEP1 SID Tend1 Ninc1 Nout1

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1 2 3 4 5 6 7 8 9 10 Tend2 Ninc2 Nout2

Tend3 Ninc3 Nout3

-etc.-

Output always occurs at Tendi and every Nouti specified increment.

Nouti controls the frequency of results output. The table below summarizes the input options. Nout Output frequency YES Output occurs at all increments defined on TSTEP1. END Output occurs at the end time. ALL Output occurs at all increments on TSTEP1 and any software subincrements. Integer ≥ 0 Output is computed at every Nout increment specific with TSTEP1.

Automatic time stepping strategy is turned on by default and can be controlled using the NLCNTL2 parameters CIBL, DTI0, HMIN, HMAX, RUP, and RDOWN. Time stepping is not allowed for an ANALYSIS=BUCKLING subcase because SOL 402 performs static buckling. Constraints SOL 402 supports constraints defined with the SPC, SPCD, and MPC entries. Additional information: • SPCs are allowed to change between subcases, but the SPCD and MPC boundary conditions are not allowed to change between subcases. Unlike most other NX Nastran solutions, SOL 402 does not require any SPC (or SPC1) companion card to fix the degrees-of-freedom that also have an imposed displacement. Any fixation would have priority over the imposed displacement, which would then be ignored with a warning message. The absence of the companion card should be tagged in the input file using the system cell SYS674=1, which is written automatically if you create an SOL 402 input file using Simcenter.

• However, if running with a SOL 402 input file that was originally exported with companion cards (for example, exported as SOL 401), the solver will treat the companion card correctly, provided that SYS674=0 (or is not defined).

• If you define an SPC with a nonzero Di value, you must request an initial static computation with the IREF parameter of the NLCNTLG entry.

• If a SPCD is defined in one subcase, in all the other subcases where it is not defined, its value is forced to zero, that is the DOFs are not free.

Mechanical loads SOL 402 supports the following mechanical loads: • FORCE, FORCE1, FORCE2 MOMENT, MOMENT1, MOMENT2

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• GRAV RFORCE, RFORC1

• PLOAD1, PLOAD2, PLOAD4, PLOADE1, PLOADX1

• BOLTD, BOLTFOR

• LOAD, TLOAD1

Dynamic tabular load definitions TABLED1, TABLED2, TABLED3, TABLED4 are also supported. Additional information: • For the TABLED1 dynamic load tabular function, only the linear-linear case is allowed.

• FORCE1, FORCE2, MOMENT1, MOMENT2 used in a large displacement analysis (PARAM,LGDISP,1) act as follower forces.

• For bolt loads: o SOL 402 does not support bolt sequence (BOLTSEQ).

o You can combine several bolt preloads in the same subcase. But if you want to apply several bolt preloads sequentially, define each bolt preload in a separate subcase.

o If the bolt load is imposed in an ANALYSIS=PRELOAD, the load will be gradually activated during the subcase, from 0 at the beginning of the subcase, to reach its full value at the end of the subcase (ramp-up effect).

o If the bolt load is imposed in a regular subcase (not ANALYSIS=PRELOAD), the bolt load is a function of time; the bolt force varies linearly from its value at the beginning of the subcase to its imposed value at the end.

• ACCEL/ACCEL1 are not supported but can be replaced by GRAV, RFORCE, or RFORCE1.

• There is no difference in the use of loads in STATICS or DYNAMICS subcases.

• Transient initial condition (TIC) are constraints, not loads.

Thermal input

A thermal load requires a load temperature (Tload), an initial temperature (Tinit), and a reference temperature (Tref). Thermal strain is calculated by

ε = αload(Tload – Tref) – αinit(Tinit – Tref) where:

• Tload is the temperature load that induces a thermal strain. See the TEMP, TEMPD, or DTEMP bulk entries, and TEMP(LOAD) case control commands. The TEMP entry defines a temperature on a grid point. The TEMPD entry defines a temperature for all grid points in which a TEMP entry is not defined.

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The TEMP(LOAD) case control command selects either the TEMP or TEMPD bulk entries.

• Tinit is the strain free temperature used in the analysis. See the TEMP(INIT) case control command. The TEMP(INIT) case control command selects either the TEMP or TEMPD bulk entries.

• Tref is the initial temperature used when computing the temperature-dependent coefficient of thermal expansion, and is defined on the MATi entry.

SOL 402 supports the following thermal loads: TEMP, TEMPD, DTEMP, TEMPEX, DTEMPEX Additional information: • Thermal loads can be used in both static and dynamics analyses. Thermal loads can be time dependent.

• If TEMP(INIT) is not specified, then the initial temperatures are assumed to be 0.0 for the material parameters evaluation (see TREF on the MATi bulk entries).

• If neither TEMPERATURE(LOAD) nor TEMPERATURE(INITIAL) is defined, MATTi temperature dependent material properties are ignored.

• If TEMP(INIT) is defined but neither TEMPERATURE(LOAD) nor a time-dependent temperature load using DLOAD entry is defined, TEMPERATURE(LOAD) defaults to TEMPERATURE(INITIAL). As a result, thermal strain is zero.

• If TEMP(INIT) is not specified but TEMP(LOAD) is, a fatal error is issued.

• In dynamic analyses, you can also load thermal-solved temperatures through the TEMPEX or DTEMPEX bulk entries.

Element support SOL 402 supports the following elements: • 0D elements: CELAS1, CELAS2, CMASS1, CMASS2, CDAMP1, CDAMP2

• 1D (line) elements: CBAR, CBEAM, CROD, CONROD

• 2D elements o Shell elements: CQUAD4, CQUAD8,CTRIA3, CTRIA6

o Plate elements: CQUADR, CTRIAR

o 2D Plane Strain elements: CPLSTN3, CPLSTN4, CPLSTN6, CPLSTN8

o 2D Plane Stress elements: CPLSTS3, CPLSTS4, CPLSTS6, CPLSTS8

• 3D elements o CHEXA, CPYRAM, CTETRA, CPENTA

o 3D Axisymmetric elements: CTRAX3, CTRAX6, CTRIAX, CQUADX4, CQUADX8, CQUADX

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o 3D Cohesive elements: CHEXCZ, CPENTCZ

o 3D Rigid elements: RBAR, RBE2, RBE3

• Special element types: CBUSH, CONM1, CONM2, CBUSH1D, CGAP

Additional information: • CQUAD element is not supported in SOL 402. Instead, use CPLSTN*.

• CQUAD4 element is supported only if system cell 370 is turned on. Otherwise, a fatal error is issued. Use CQUADR instead, or turn on the system cell.

• CQUAD4 and CQUADR elements follow the Mindlin first order formulation, and CQUAD8 elements follow the heterosis second order integration formulation.

• SOL 402 does not support chocking elements.

• For CTRIA3, CQUAD4, CTRIAR, or CQUADR elements, you can set the PARAM,SNORM parameter to automatically generate grid point normals (based on the average normal between adjacent elements) to solve discontinuities of normals orientations in adjacent shells.

• Results are output in the material coordinate system. If these axes are not specified, output will be: o In the element coordinate systems for solid elements, which is the basic coordinate system unless another one is specified on the property card using CORDM of the PSOLID bulk entry.

o In the element coordinate systems for shell elements, which is parallel to the first edge G1-G2.

Material support SOL 402 supports the following materials (with optional temperature dependencies): • Isotropic: MAT1 (+MATT1)

• Orthotropic: MAT11 (+ MATT11), MAT3 (+MATT3), MAT8 (+ MATT8)

• Anisotropic: MAT2 (+ MATT2), MAT9 (+ MATT9)

• Hyperelastic: MATHE, MATHM, MATHEV, MATHP

• Creep: MATCRP and CREEP (+ MATTC)

• Ply failure: MATDMG

• Material for cohesive elements: MATCZ

Additional information: • MATS1 bulk entry can be used to specify stresses dependence to MAT1, MAT3, MAT9, or MAT11. However, the Yield function is limited to the von Mises law.

• In MATHP, the order of the distortional strain energy polynomial function is limited to 4.

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• The choice of the stress-strain measure for all material laws is defined in the NLCNTLG entry.

• If the MATNL parameter is set to -1 (PARAM,MATNL, -1): o Plasticity effects of MATS1 materials are turned off. This can also be enabled on a subcase-by-subcase basis using NLTNCL2 PLASTIC.

o Creep effects of the MATCRP materials are turned off. This can also be enabled on a subcase-by-subcase basis using NLTNCL2 CREEP.

o Damage material properties for cohesive elements of the MATCZ materials are discarded.

Glue support • SOL 402 supports only the BGOPT parameter of the BGPARM bulk entry.

• Depending on the source and target region defined in the BGSET bulk entry and the BGOPT parameter of the BGPARM entry, you can set up the following gluing types: BGPARM: BGOPT BGSET: source/target Gluing characteristics parameter Edge to edge gluing for shells, plane strain, BEDGE/BEDGE or plane stress elements. BSURFS/BEDGE Faces of solid to edges of shells gluing. BSURFS/BSURFS Solids to solids gluing. BSURFS/BSURF Nodes of solids to shells faces gluing. Nodes of shells to faces of solids gluing. BEDGE/BSURFS The source node rotation is computed as the mean rotation of the target solid face. Nodes of shells to shells gluing The source node rotation is computed as the 3 (default) BEDGE/BSURF mean rotation of the target shell. Three additional kinematics constraints are 2 used to drive the source node rotation. Shells to shells gluing The source node rotation is computed as the 3 (default) mean rotation of the target shell. BSURF/BSURF Three additional kinematics constraints are 2 used to drive the source node rotation. 1 Rotations are free. Shells to faces of solids gluing. Three additional kinematics constraints are BSURF/BSURFS 3 (default) used to drive the source node rotation. 1 Rotations are free. BSURF/BEDGE N/A

Contact support In SOL 402, you can define a node-to-surface contact, with or without friction. In the BCTSET bulk entry, you define the contact pairs, while you use the BCTPAR2 entry to define the contact parameters. Additional information on the BCTPAR2 entry:

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• In a subcase where contact is defined, the contact condition is gradually activated during the subcase such that it is fully activated by the end of the subcase (ramp-up effect).

• The ramp-up of contact conditions occurs for all subcases except for the first one. By default in the first subcase, contact conditions are immediately active at the beginning of the simulation (time = 0.). However, you can optionally define ACTIVE=0 on the BCTPAR2 bulk entry to request the ramp-up of contact conditions in the first subcase.

• Similarly, in a subcase in which contact is not defined, but was defined in the previous subcase, the contact conditions will be gradually disabled (ramp-down effect).

• SOL 402 does not support birth/death time for contacts. The activation/deactivation is only possible at the subcase level.

• You can request the large displacement contact formulation by setting DISP=2 on the BCTPAR2 bulk entry to force the contact conditions to be updated when large sliding occurs. The DISP=2 formulation is also automatically activated when you request large displacement effects with the setting PARAM,LGDISP,1, or when you request large strains and displacement effects with the setting PARAM,LGSTRN,1.

• The SEGNORM parameter on the BCTPAR2 bulk entry can be defined to request continuous contact segment normals when the normals of two adjacent faces in contact present severe discontinuities.

Nonlinear parameters You can define solution control parameters either globally (NLCNTLG bulk entry) or by subcase (NLCNTL2 bulk entry). On the NLCNTLG bulk entry, you can choose the following: • The stress-strain measure for all material laws (Kirchoff, Cauchy, Biot, and so on) using STRMEAS.

• Symmetric or unsymmetric matrices for subcases ANALYSIS=STATIC, PRELOAD or DYNAMICS.

• The solver (RESO). See Solver Support.

On the NLCNTL2 bulk entry: • You can choose between fixed time steps or automatic time stepping. You can also control the time step size (minimum, maximum, increase ratio).

• You can control the equilibrium iteration and convergence of the solution.

• You can use the IMPL parameter to define the time integration scheme (Newmark, HHT, or Generalized-alpha) for DYNAMICS subcases. You can also control the integration error.

• You can use the LVAR and TVAR parameters to define if time unassigned loads and temperatures are ramped (default) or stepped.

• For a non-sequentially dependent (NSD) static subcase (SEQDEP=NO), you can optionally reload the computation state from the end of a previous subcase using the RSUB=n parameter.

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Solver support SOL 402 supports the sparse direct solver (default) or the parallel solver. The element iterative solver is not supported. • On the NLCNTLG bulk entry, you can choose the Skyline, Sparse, or parallel solver using the RESO parameter.

• For the parallel solver, SOL 402 supports distributed-memory parallel processing (DMP) and shared-memory parallel processing (SMP).

• The Nastran command MPI402 keyword specifies the maximum number of CPUs selected for distributed-memory parallel processing. The NASTRAN command PARALLEL sets the number of MKL threads.

Cyclic symmetry analysis See Cyclic symmetric in SOL 402. Fourier analysis See Fourier harmonic solution in SOL 402. Buckling analysis See Linearized buckling solution in SOL 402. Supported case control output requests SOL 402 supports only SORT1 data. SORT2 is not supported. Case control Description ACCELERATION Requests accelerations. BCRESULTS Requests contact forces and tractions. BGRESULTS BOLTRESULTS Requests bolt results. CRSTRN Requests creep strain at grid points. CZRESULT Requests results output for cohesive elements. DISPLACEMENT Requests displacement output. EKE Requests element kinetic energy output. ELSUM Requests output of an element property summary. ESE Requests the output of the strain energy. FORCE Requests element force output. GPFORCE Requests grid point force balance at selected grid points. HOUPUT Requests harmonic output for cyclic symmetry and axisymmetric models. MEFFMASS Requests modal effective mass output in a modal subcase. MONVAR Selects degree-of-freedom for a displacement monitor plot. MPCFORCES Requests the form and type of multipoint force of constraint vector output. OLOAD Requests the form and type of applied load vector output. OMODES Requests a set of modes for output. OTEMP Requests temperature output. PFRESULTS Requests progressive failure results output for composite solid elements.

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PLSTRN Requests plastic strain at grid points. SET Defines a set of element or grid point numbers to be plotted. SETMC Set definitions for modal, panel, and grid contribution results. SETMCNAME Specifies the title of a displacement monitor plot. SHELLTHK Requests shell thickness output. SPCFORCES Requests single-point force of constraint vector output. STRAIN Requests element strain output. STRESS Requests element stress output. THSTRN Requests thermal strain at grid points on elements. VELOCITY Requests the form and type of velocity vector output.

Input summary You can use the following parameters with SOL 402.

ALPHA1 LGDISP POST ALPHA2 LGSTRN SNORM F56 MATNL UNITSYS K6ROT NLAYERS

You can use the following case control commands with SOL 402.

ACCELERATION DLOAD METHOD SPC ANALYSIS DTEMP MONVAR SPCFORCES BCRESULTS EKE MPC STRAIN BCSET ELSUM MPCFORCES STRESS BGRESULTS ESE NLCNTL SUBCASE BGSET FORCE OLOAD SUBTITLE BOLTLD GPFORCE OTEMP TEMPERATURE BOLTRESULTS HARMONICS PFRESULTS THSTRN CRSTRN HOUTPUT PLSTRN TITLE CYCFORCES IC SEQDEP TSTEP CYCSET LABEL SET VELOCITY CZRESULTS LOAD SETMC DISPLACEMENT MEFFMASS SHELLTHK

You can use the following bulk entries with SOL 402.

BCPROP CPLSTN6 MAT3 PLOAD1 BCPROPS CPLSTN8 MAT8 PLOAD2 BCRPARA CPLSTS3 MAT9 PLOAD4 BCTADD CPLSTS4 MAT11 PLOADE1 BCTPAR2 CPLSTS6 MATCID PLOADX1 BCTSET CPLSTS8 MATCRP PLPLANE BEDGE CPYRAM MATCZ PLSOLID

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BGADD CQUAD MATDMG PMASS BGPARM CQUAD4 MATFT PPLANE BGSET CQUAD8 MATHE PROD BOLFRC CQUADR MATHEM PSHELL BOLT CQUADX4 MATHEV PSHL3D BOLTFOR CQUADX8 MATS1 PSOLCZ BOLTLD CREEP MATT2 PSOLID BSURF CROD MATT3 RBAR BSURFS CTETRA MATT8 RBE2 CBAR CTRAX3 MATT9 RBE3 CBEAM CTRAX6 MATT11 RFORCE CBUSH CTRIA3 MATTC RFORCE1 CBUSH1D CTRIA6 MOMENT SPC CDAMP1 CTRIAR MOMENT1 SPC1 CDAMP2 CYCADD MOMENT2 SPCADD CELAS1 CYCAXIS MPC SPCD CELAS2 CYCSET MPCADD TABLED1 CGAP DLOAD NLCNTG TABLED2 CHEXA DTEMP NLCNTL2 TABLED3 CHEXZ ECHOOFF PBAR TABLED4 CMASS1 ECHOON PBARL TABLEM1 CMASS2 EIGB PBEAM TABLEM2 CONM1 EIGR PBEAML TABLEM3 CONM2 EIGRL PBUSH TABLEM4 CONROD ENDDATA PBUSH1D TABLEM5 CORD1C FORCE PBUSHT TABLES1 CORD1R FORCE1 PCOMP TABLEST CORD1S FORCE2 PCOMPG TEMP CORD2C GRAV PCOMPG1 TEMPD CORD2R GRID PCOMPS TIC CORD2S GROUP PDAMP TLOAD1 CPENTA INCLUDE PELAS TSTEP CPENTCZ LOAD PELAST TSTEP1 CPLSTN3 MAT1 PGAP CPLSTN4 MAT2 PLOAD

You can use the following NASTRAN system cells in SOL 402:

57 107 143 144 370

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442 525 674

The following NASTRAN command keyword is specific to SOL 402:

MPI402

Results file See SOL 402 .f06 results file. Input file example NASTRAN SYSTEM(674) = 1 assign output2='samcefnl.op2', unit=21 SOL 402,106 CEND $* $* +------+ $* ! CASE CONTROL ! $* +------+ $* ECHO = NONE DISPLACEMENT(PLOT,PRINT) = ALL SPC = 100 $* Subcase 1 : transient analysis SUBCASE 1 ANALYSIS = TRANSIENT LABEL = Transient step 1 TSTEP = 201 IC = 301 SUBCASE 2 ANALYSIS = TRANSIENT LABEL = Transient step 2 TSTEP = 202 IC = 302 SEQDEP = NO $* $* +------+ $* ! BULK DATA ! $* +------+ $* BEGIN BULK $* $* PARAM CARDS $* ======$* PARAM OMACHPR YES PARAM POST -2 $* $* GRID CARDS $* ======$--01--><--02--><--03--><--04--><--05--><--06--><--07--><--08--><--09--><--10--> GRID 1 0 0.0 0.0 0.0 0

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GRID 2 0 100.0 0.0 0.0 0 $* $* ELEMENT CARDS $* ======$--01--><--02--><--03--><--04--><--05--><--06--><--07--><--08--><--09--><--10--> CDAMP1 2 2 1 1 2 1 CONM1 1 2 0 1.00E-3 CELAS1 3 3 1 1 2 1 $* $* PROPERTY CARDS $* ======$--01--><--02--><--03--><--04--><--05--><--06--><--07--><--08--><--09--><--10--> PDAMP 2 5.03E-4 PELAS 3 1.58E-3 $* $* LOAD AND CONSTRAINT CARDS $* ======$--01--><--02--><--03--><--04--><--05--><--06--><--07--><--08--><--09--><--10--> SPC 100 1 123456 0.0000 SPC 100 2 23456 0.0000 $* $* TSTEP CARDS $* ======$--01--><--02--><--03--><--04--><--05--><--06--><--07--><--08--><--09--><--10--> TSTEP1 201 10.0 10000 100 TSTEP1 202 20.0 10000 100 $* $* INITIAL CONDITIONS $* ======$--01--><--02--><--03--><--04--><--05--><--06--><--07--><--08--><--09--><--10--> TIC 301 2 1 2.0 2.5 TIC 302 2 1 1.0 1.5 $* ENDDATA SOL 402 vs SOL 401 comparison See SOL 402 vs SOL 401 comparison.

Fourier harmonic solution in SOL 402

A Fourier normal modes subcase is available in SOL 402 for models that include axisymmetric elements. The subcase is designated with the ANALYSIS=FOURIER and HARMONICS=N case control commands in the subcase. The conventional axisymmetric element includes radial and axial degrees-of-freedom with no variation in theta. In the Fourier normal modes subcase, the axisymmetric element has radial, axial, and theta degrees-of-freedom. In addition, the degrees-of-freedom are represented with harmonic terms of a Fourier series of the form:

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where: c=cos(kθ) and s=sin(kθ), k is the harmonic number,

are symmetric displacements, and

are antisymmetric displacements.

Both symmetric and antisymmetric displacements are computed by NX Nastran for a particular harmonic k. With the Fourier normal modes subcase, you request which harmonic numbers in a modal solution should occur, and the harmonic terms for modal output. For each harmonic number in which you request modes and output, the software can compute the symmetric and antisymmetric displacements, stress, strain, SPC force, and grid point forces. You can use the typical case control commands to request the output. You can then optionally use the Simcenter post processor to display the physical results on either a 3D segment, or on a full 360-degree model display. Static and modal (non-Fourier normal modes) subcases can also be included in the input, and are designated with the case control commands ANALYSIS=STATICS or ANALYSIS=MODES. However, the conventional axisymmetric element formulation is used in the static and modal subcases. In addition to axisymmetric elements, the plane stress elements can also be included with the Fourier normal modes subcase. For grid points that are defined on the rotation axis, in addition to any conditions that you defined, NX Nastran automatically applies the following SPC and MPC conditions during the solution. • For the harmonic index k=0, NX Nastran fixes DOF 1, 2.

• For the harmonic index k=1, NX Nastran fixes DOF 3, and it creates the MPC condition Ux = Uy for the cosine terms, and the MPC condition Ux = -Uy for the sine terms.

All harmonic terms are treated all together in a unique system of equations. As a consequence: • For modal analysis, eigenvalues are sorted in increasing order independently of harmonic. Depending on the physical configuration, each eigenmode is associated with one harmonic. Modes are not sorted in increasing harmonic number.

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• For static analysis, even if loading is axi-symmetrical (harmonic 0), one higher harmonic can be excited. For instance, a cylinder axially loaded (harmonic 0) can buckle laterally (harmonic 1) or a cylindrical tank subjected to an external pressure (harmonic 0) can buckle in a double wave shape (harmonic 2).

Fourier normal modes subcase input summary • The ANALYSIS=FOURIER case control command should be defined in the subcase in which you are requesting the Fourier normal modes subcase in SOL 402.

• The HARMONICS case control command requests the specific harmonics in which modes will be computed. The SET entry then lists the harmonic numbers to be computed, including "0" to request the zeroth harmonic. Since there is an infinite number of harmonics in the Fourier normal modes analysis, the describer "ALL" is not supported in the ANALYSIS= FOURIER subcase.

• The HOUTPUT case control command optionally requests the harmonics to output modes. "ALL" requests output for every harmonic requested on the HARMONICS command. An integer can be defined to select the SID of a SET bulk entry listing the harmonic numbers to be output. These IDs typically represent a subset of the IDs requested on the HARMONICS command. The C, S, C*, and S* describers on the HOUTPUT command are not supported by SOL 402.

• The METHOD case control command selects the EIGRL bulk entry, which then defines the eigenvalue solution options, for example, the lower- and upper-frequency ranges and the number of modes.

Cyclic symmetric in SOL 402 The cyclic solution method takes advantage of cyclic symmetry to reduce the time needed to create and solve a full 360-degree model. To use this method, you create a 3D-solid element model that represents a fundamental segment. The fundamental segment represents a structure that is made up of N repetitions, where each repetition can be obtained by rotating the fundamental segment an angle that is an integer multiple of 2π/N. Cyclic symmetry solution in SOL 402 follows the same capabilities as the cyclic symmetry in SOL 401 (see ) except for the following limitations. HARMONICS limitations In SOL 402, the following limitations apply to the HARMONICS case control command that requests the solution harmonics: • HARMONICS=ALL is not allowed.

• HARMONICS=n defines a SET number that contains only one unique harmonic to solve. If you want to solve several harmonics, you must define one ANALYSIS=CYCMODES subcase per harmonic to solve.

Miscellaneous limitations You cannot use the parameters STRESSK, SPINK, and FOLLOWK of the NLCNTL bulk entry to request stress stiffening, spin softening, and follower stiffness because the NLCNTL entry is not supported in SOL 402.

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Cyclic modes subcase input summary • The ANALYSIS=CYCMODES case control command is defined in the specific subcases in which you are requesting the cyclic modes solution method.

• The HARMONICS case control command requests the specific harmonic in which modes are computed. You cannot use the "ALL" request. You must define the SID of a SET bulk entry, and the SET entry lists the unique harmonic number to be computed. If you want to solve several harmonics, you must define one ANALYSIS=CYCMODES subcase per harmonic to solve.

• The HOUTPUT case control command optionally requests the harmonics to output modes. "ALL" requests output for the unique harmonic requested on the HARMONICS command. The C, S, C*, and S* describers on the HOUTPUT command are not supported by SOL 402.

• The METHOD case control command selects the EIGRL bulk entry which then defines the eigenvalue solution options, for example, the lower- and upper-frequency ranges and the number of modes. Since a single EIGRL entry is selected in a subcase, the same EIGRL options are used when the software computes the modes for each harmonic.

SOL 402 vs SOL 401 comparison Contact 1. In SOL 401, the OFFSET distance can be defined per contact region (BCRPARA bulk entry). In SOL 402, the OFFSET distance is defined at the contact level (BCTPAR2 entry).

2. In SOL 401, a contact with shells automatically take the half thicknesses of the shells into account. In SOL 402, you must manually take the half thicknesses of the shells into account with the OFFSET parameter.

Bolt 1. In SOL 401, you cannot model bolts with CBAR/CBEAM elements. In SOL 402, you can model bolts with beams.

2. In SOL 401, you cannot use CPYRAM and composite solids for a BOLT of the ETYPE=3 type. In SOL 402, you can if the cut is planar.

3. Initial strain bolt preload force is allowed in SOL 401, not in SOL 402.

4. Bolt loading sequence (BOLTSEQ) is allowed in SOL 401, not in SOL 402. In SOL 402, bolts are activated for the whole subcase time interval.

Subcases 1. In SOL 401, a NSD subcase (SEQDEP = NO) has a start time of zero. In addition, a non-sequentially dependent static or modal subcase does not use the displacement/stress/strain state from the previous static subcase.

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In SOL 402, a NSD subcase uses the final time from the previous subcase for its start time. But the computation state (stresses, state variables, and so on) can be reloaded from the end of any of the previous subcases through the RSUB parameter of the NLCNTL2 bulk entry.

Miscellaneous

1. In SOL 401, you can apply an enforced motion (parameter Di of the SPC bulk entry) in any subcase. In SOL 402, enforced motion is always global and you must request an initial static computation with the IREF parameter of the NLCNTLG entry.

2. In SOL 401, SPCD can vary from a subcase to another. In SOL 402, SPCD must be global and cannot vary from one subcase to another because if an SPCD is defined in one subcase, in all the other subcases where it has not been defined, its value is forced to zero instead of being free.

3. TSTEP bulk entry is compulsory for a transient analysis in SOL 401, but not in SOL 402

4. Strategy parameters must be defined in the NLCNTL bulk entry for SOL 401, but in the NLCNTL2 bulk entry for SOL 402.

SOL 402 .f06 results file The output file that you will use most frequently is the .f06 file. The software writes this file to FORTRAN unit 6. The .f06 file contains all the requested results from your analysis, such as the displacements, stresses, and element forces, as well as any diagnostic messages. The information in the .f06 file is critical for model checkout and debugging.

Structure of the file in SOL 402

The .f06 file contains the results of the NX Nastran job and also includes the output file of the Samcef MECANO run (also called the MECANO RES file). The MECANO output file is included in the .f06 Nastran file between the starting lines: DYNAMIC ALLOCATION OF MEMORY ======USER REQUESTED WORKSPACE 12000000 WORDS ( 96 MBYTES) Module: M E C A N O

and the finishing lines: ------File size statistics File name Size ------./T40959_9/sim1-sol_402_me.w01 16560 Bytes ./T40959_9/sim1-sol_402_me.w02 12488 Bytes ./T40959_9/sim1-sol_402_me.w03 147520 Bytes

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The following sections describe the most important contents of the .f06 file that you need to search for results or to diagnose problems.

Searching for errors, warnings, or information messages Important MECANO messages have the following headers:

• %%%Enn-xxx for error messages.

• %%%Ann-xxx for warnings.

• %%%Inn-xxx for informative messages. where:

• nn is the message id.

• xxx is the message keyword; typically, the Samcef FORTRAN routine issues the message.

• is the message short description.

Several lines of text may follow the message to complete the message description. The following table lists the most important error message keywords.

%%%Enn-xxx Description MMFERR All errors related to the BOEING solver: pivoting, memory zone, and so on. All errors related to element generation: missing or inconsistent physical ASGEN properties, and so on. All errors related to materials definitions: missing property, data OVVExx inconsistency, and so on. All errors related to .sdb database access: memory zone, opening and DGOPPA saving the file, and so on. All errors related to the writing of data in files: disk space, permissions, WRITES and so on. CONTAC All errors related to contact conditions: convergence, and so on.

Checking convergence

You can check the solution convergence by searching for the TIME STEP entries:

TIME STEP NR 1 (TIME 5.000000000E-02) #

Is the entry for all indicators regarding a specific time step value.

->ACCEPTED TIME STEP, ERROR = 6.667E-01 H RATIO= 1.000E+00 H = 5.000E-02

Indicates the converged state of the time step and the related convergence values.

->REJECTED TIME STEP, ERROR = 6.667E-01 H RATIO= 1.000E+00 H = 5.000E-02

Indicates the non-converged (and rejected) state of the time step and the related convergence values.

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For each time step, a list of indicators is given for each Newton iteration. In the listing, you find this information in a printout table like: NEWTON ITERATIONS : ------ITER. TESF TESE TESQ RES ALGO CPU# 1 6.2322E-01 1.0000E+00 1.0000E+00 3.1767E+03 NR 1.05# 2 3.3973E-02 1.4139E+00 5.2422E+00 2.5920E+03 NR 1.05#

where ITER is the iteration number and where the most important parameters to watch are: TESF The force convergence test value. This is the norm of the residual vector to the sum of internal, external, and inertia forces incremented by a reference value given by the REFP parameter of the NLCNTL2 bulk entry. TESE The energy convergence test value. This is the square root of the ratio of the product of the residue by the variation of the displacement during one iteration to the sum of kinetic, internal, and external energies incremented by a reference value given by the REFE parameter of the NLCNTL2 bulk entry. TESQ The norm of the displacement increment divided by the sum position vector incremented by a reference value given by the REFU parameter of the NLCNTL2 bulk entry.

All these parameters have to decrease during the iterations of a time step. Convergence is reached when the test value lies under a convergence threshold:

• For TESF, the threshold is given by the PRCR parameter of the NLCNTL2 bulk entry.

• For TESE, the threshold is given by the PRCE parameter of the NLCNTL2 bulk entry.

• For TESQ, the threshold is given by the PRCQ parameter of the NLCNTL2 bulk entry.

For more details on convergence problems, see Listing of results and messages in the Non linear mechanics - Analysis manual of the Samcef documentation.

Browsing contact conditions

In the listing file, you can browse the contact conditions by searching for the MCT keyword. The MCT number in the listing matches the CSID parameter of the BCTSET bulk entry. In the case of non-convergence, a global status of the contact conditions is printed in the .f06 file. For more information on this status and how to understand the printed data, see Convergence problems and Summary of contact status in case of divergence in the Samcef documentation.

Linearized buckling solution in SOL 402 The BUCKLING analysis in SOL 402 performs an incremental stability, which is also called initial bifurcation analysis or linearized buckling analysis.

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A model can buckle in different shapes under different levels of loading. The shape the model takes while buckling is called the buckling mode shape, and the loading is called the critical or buckling load. The linearized buckling approach solves an eigenvalue problem around a reference state and estimates the critical buckling factors and the associated buckling mode shapes. Usually, you are interested in the lowest mode because it is associated with the lowest critical load. The buckling load factor (BLF) is the ratio of the buckling loads to the applied loads. Buckling load factor (BLF) Buckling status The applied loads are less than the estimated 1 < BLF critical loads. Buckling is not expected. The applied loads exceed the estimated critical 0 < BLF < 1 loads. Buckling is expected. The applied loads are exactly equal to the BLF = 1 estimated critical loads. Buckling is expected. The buckling occurs when the directions of the applied loads are all reversed. For example, if BLF = -1 a rod is under tensile load, the BLF should be negative. The rod will never buckle. -1 < BLF < 0 Buckling is predicted if you reverse all loads. Buckling is not expected even if you reverse BLF < -1 all loads.

Note A structure can have both positive and negative buckling load factors. For example, for a cylindrical pipe under internal pressure supported by columns, the vessel will never buckle as it is under tension; however, the columns may buckle as they are under compression.

Workflow

1. After at least one STATICS subcase, SUBCASE n, you define a BUCKLING subcase n+1. For instance:

SUBCASE 3 ANALYSIS = STATICS LABEL = Loading up to 100. [1-100] TSTEP = 102 $ SUBCASE 4 ANALYSIS = BUCKLING LABEL = Buckling analysis at 100 load METHOD = 40 SEQDEP = YES EKE(PRINT,THRESH=0.3) = ALL

2. The BUCKLING subcase will use the final computation state of the previous SUBCASE n as the reference state and computes a new state at tn + 1 second, where tn is the latest computation time of the SUBCASE n.

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3. The loads in the model that do not vary in between the time interval [tn, tn + 1 sec] are considered as dead loads: they are applied on the structure but are not involved in the buckling process.

The loads in the model that vary in between the time interval [tn, tn + 1 sec] are considered as life loads: these are the loads that are involved in the buckling process.

Note

It is then important that the definition time range of the loads covers the interval [tn, tn + 1 sec].

Note You can repeat the sequence "STATICS subcase then BUCKLING subcase" several times.

Example

Note The following examples show the most important entries that are relevant to the BUCKLING workflow.

Case Control.

NASTRAN SYSTEM(674)=1 $ ASSIGN OUTPUT2='samcefnl.op2',UNIT=21 $ SOL 402 CEND $* $*$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ $* $* CASE CONTROL $* $*$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ $* TITLE = Buckling analyses of a compressed plate SUBTITLE = Several load levels ECHO = UNSORT SPC = 1 DLOAD = 2 METHOD = 10 DISPLACEMENT(PRINT) = ALL STRESS(PRINT) = ALL $ SUBCASE 1 ANALYSIS = STATICS LABEL = First Loading [0-1] TSTEP = 101 $

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SUBCASE 2 ANALYSIS = BUCKLING LABEL = Buckling analysis with unitary load METHOD = 20 SEQDEP = YES EKE(PRINT,THRESH=0.3) = ALL $ SUBCASE 3 ANALYSIS = STATICS LABEL = Loading up to 100. [1-100] TSTEP = 102 $ SUBCASE 4 ANALYSIS = BUCKLING LABEL = Buckling analysis at 100 load METHOD = 40 SEQDEP = YES EKE(PRINT,THRESH=0.3) = ALL $ SUBCASE 5 ANALYSIS = STATICS LABEL = Loading up to 250. [100-250] TSTEP = 103

Time steps definition

TSTEP1 101 0.01 1 END TSTEP1 102 1.0 1 END TSTEP1 103 2.5 1 END

Loads

$ $ Loading $ $------1------2------3------4------5------6------7------8------9------10 DLOAD 2 1. 1. 3 TLOAD1 3 33 0 load 4 TABLED2 4 0. + 0. 0. 0.01 0. 10. 10. ENDT

In this example, the first buckling uses the loads time definition "buckling" interval of [0.01, 1.01], and the second buckling uses the interval of [1.0, 2.0]. The loads are well defined in these intervals.

Output in the .f06 results file THERE ARE 8 EIGENVALUES BETWEEN 0.000E+00 AND 5.000E+02 RESULTS AT ITERATION 10, NUMBER OF VECTORS : 30 EIGENVALUE BUCKLING FACTOR 1 -4.072133E-03 4.428440E+00 2 -4.770635E-03 4.038430E+01

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3 -7.414269E-03 1.151249E+02

6-24 NX Nastran 12 Release Guide Chapter 7: Performance

Performance improvements

Direct frequency response performance

The following new performance options are available for the direct frequency response solution (SOL 108). • Iterative solver for frequency-dependent solution NX Nastran’s global iterative solver now supports frequency-dependent solutions. To activate the global iterative solver in SOL 108, set either NASTRAN ITER = YES in the Nastran input file or add iter = yes to the Nastran command line.

• Padé via Lanczos (PvL) For models that have frequency-dependent matrices, you can request the new Padé via Lanczos (PvL) approach. The PvL approach utilizes factorization of the matrix at selected frequencies for all responses and depending on the number of frequencies computed, reduces the problem size.

To request the PvL approach, set either the new keyword krylov or the new system cell 679 (krylov) to YES.

NASTRAN KRYLOV = YES

Note • The iterative solver support for frequency-dependent solutions and the Padé via Lanczos (PvL) approach are mutually exclusive.

• If you request both PvL and global iterative solver solution, the PvL approach will take precedence over the frequency-dependent iterative solver approach.

Geometric Domain Static Analysis (GDSTAT) extension

GDSTAT is a parallel solution for the linear static analysis of large models. The GDSTAT method is added to SOL 401 for fast static analysis. The performance of GDSTAT depends on the size of the boundary produced by the graph-based (GPART = 1) domain partition. When the boundary size is small, GDSTAT is most efficient. For most cases, DMP = 2 or DMP = 4 is sufficient.

You can use system cell 649 to control GDSTAT in SOL 401. = 0 (default) Does not select GDSTAT. That is, NX Nastran performs serial processing.

= 1 Selects GDSTAT with null columns in the stiffness matrix.

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= 2 Selects GDSTAT after null columns are removed from the stiffness matrix.

Use SYSTEM(649) = 1 for most parallel processing cases. However, for models with large open contact patches, which generally include a large number of null columns, you may see a performance increase with SYSTEM(649) = 2. For more information about parallel solutions, see the Parallel Processing User's Guide.

Improved sparse decomposition

The default value for the rank keyword (system cell 205) is changed from 32 to 128 for better Shared Memory Parallel (SMP) performance. The rank keyword determines the number of rows that are simultaneously updated during the decomposition.

7-2 NX Nastran 12 Release Guide Chapter 8: Bolt preload

Bolt preload improvements for linear solutions

The following bolt preload improvements are available for the linear solutions 101, 103, 105, 107 through 112. Also see Bolt preload improvements for SOL 401. Automatic bolt coordinate system and bolt axis To model bolts with CHEXA, CPENTA and CTETRA elements for the linear solutions, you use the ETYPE=2 input format described on the BOLT bulk entry. This format includes the CSID and IDIR fields which define the bolt coordinate system and the bolt axis, respectively. Previously, a BOLT bulk entry with ETYPE=2 defined for a linear solution required that you define both the CSID and IDIR fields. Now in NX Nastran 12, if you leave both the CSID and IDIR fields blank, the software will automatically determine the coordinate system and the bolt axis. The BOLT bulk entry defined with ETYPE=2 requires that you list the grid point IDs on the Gi fields which are connected to the element faces where the software will cut the bolt. When you leave both the CSID and IDIR fields blank, the software requires that the element faces which are associated with the grid points listed on the BOLT entry lie approximately on a plane perpendicular to the intended bolt axis. This is important for the software to automatically compute the bolt coordinate system and the bolt axis. If you leave both the CSID and IDIR fields blank, and the cut you define is not close to being planar, a fatal error will occur. In addition, if the cut is planar but the plane is not perpendicular to the intended bolt axis, the software computed coordinate system and bolt axis will be skewed from the intended bolt axis, and your preloads will not be accurate.

Note For the NX Nastran 12 release, regardless if the CSID and IDIR fields are defined or not defined, when using the ETYPE=2 cut-plane method, the grid points listed in Gi should be coplanar, or at least close to coplanar. If your bolt cut-plane is not planar, your solution results may not be accurate. If you define a ETYPE=2 bolt with a non-planar cut-plane, the software will still solve without a warning.

ETYPE=2 bolt glue approach When you define a bolt with ETYPE=2 on the BOLT bulk entry, the software cuts the bolt in half, it creates new grid points resulting in grid pairs at the cut, it evenly distributes the opposing axial bolt force to the grids on each side of the cut, and it solves a statics solution to determine the axial displacement of each bolt half. The software then holds the grid pairs in their relative deformed state for the consecutive static solution. Previously, the software would apply MPC conditions between the grid pairs to hold them in their relative deformed state.

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Now, the software creates a glue connection at the cut which holds the grid pairs in their relative deformed state. The glue based approach accounts for bending along the bolt axis since rotational stiffness is included in the glue condition. The MPC approach accounts for the axial stiffness, but not the rotations. As a result, bending is not accounted for with the MPC approach.

Note The glue approach is not supported by the element iterative solver in SOL 101. If you run with the element iterative solver in SOL 101 and you have defined the ETYPE=2 bolt, the software will revert to the MPC approach.

Bolt preload specified by BOLTFOR bulk entry Previously, linear solutions only supported the BOLTFOR bulk entry to define a bolt preload force. You can now use the BOLTFRC bulk entry with TYPE=LOAD to define the bolt preload as a force. A bolt force defined with the BOLTFRC bulk entry with TYPE=LOAD or with the BOLTFOR bulk entry are equivalent. The DISPLACEMENT and STRAIN preload options on the BOLTFRC bulk entry are not supported for the linear solutions and will cause a fatal error if defined.

8-2 NX Nastran 12 Release Guide Chapter 9: Memory allocation for external applications

Memory allocation for external applications

When you run SOLs 402, 601, 701, or a SOL 108 acoustic solution which includes FEMAO, NX Nastran calls an external application after it processes the input file. Prior to calling these external applications, NX Nastran automatically reduces most of the memory you had requested with the mem keyword. As a result, more memory is available for the external application. NX Nastran releases as much memory as possible prior to calling the external application, and it exports an environment variable that declares the amount of memory released. The external application reads this environment variable and limits its allocation of memory to that amount. This guarantees that NX Nastran and the external applications use only the memory that you request. The reduced amount of memory will be the difference between the amount specified by the mem keyword and the amount required by the Nastran Executive System. The amount required by the Nastran Executive System is approximately 200 MB plus the amounts specified by the bpool and smem keywords, or 10% of the memory specified by the mem keyword, whichever is greater.

Note • Memory requested on the command line is the high-water mark.

• Memory reduction will not occur if half of the mem value is less than that required by the Nastran Executive System.

• The memory allocation for external applications occurs automatically. You do not need to request it.

• The amount of memory that NX Nastran reduces for the external application is labeled as Dynamic Memory in the .f04 file.

• NX Nastran calls external applications with the ISHELL module, or launches them by loading a DLL and executing the external application in the DLL.

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Chapter 10: Topology Optimization

Topology Optimization

Beginning with NX Nastran 12, you can use the NX Nastran optimization solution sequence (SOL 200) to run a topology optimization. The SOL 200 topology optimization removes material in a way that is consistent with your objective function and constraints. You can request a single topology optimization solution across multiple analysis types including statics and dynamics. The software removes material during the analysis by reducing the Young’s Modulus and the normalized mass density (NMD). Note that, since you can replace mass density with weight density on the MATi bulk entry, all following discussion of normalized mass density (NMD) also refers to the weight density case. The software automatically creates a design variable for each element you select for the optimization. The NMD begins with a value of 1.0 which means that all of the element material is present. It is reduced during the analysis as the software removes material during optimization. An NMD value approaching 0.0 indicates that most of an element's material has been removed. It should be noted that if the weight density of the material is input instead of the mass density, then the same arguments in SOL 200 topology optimization hold for normalized weight density. The NMD result is output for each element you defined as active for the optimization. This output appears under the heading “Normalized Mass Density” in the .f06 file, when requested with the parameter NASPDV, and in the new ONMD data block if an .op2 file is requested with the appropriate PARAM, POST setting (-1 or -2). New tools are available in Simcenter Pre/Post 12.0 for you to post process the NMD results. These tools include the option to output smoothed geometry in STL or in bulk data format. You can then import these smoothed formats back into Simcenter Pre/Post, create a new meshed model based on the new topology, then use the updated model for visualization and further analysis. The new SOL 200 capability replaces the topology optimization that was available in NX Nastran 11. The input requirements for the new SOL 200 capability are not the same as those for the NX Nastran 11 topology optimization capability. As in previous NX Nastran releases, you can use SOL 200 to run a parametric optimization, although currently it is not advisable to run simultaneously with topology optimization. In general, the inputs to define the SOL 200 topology optimization are the same as the inputs used to define the SOL 200 parametric optimization. The most significant difference is the new DVTREL1 bulk entry. The SOL 200 topology optimization inputs are as follows: Design Variables Design variables define your allowable changes to the finite element model. For topology optimization, the software automatically creates a design variable for the elements that you select for the optimization.

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You use the new DVTREL1 bulk entry to select the elements to be included or not to be included in the topology optimization. The GRPID field on the DVTREL1 entry references the ID of a GROUP bulk entry that specifies a list of elements. The following elements are topology optimizable elements: • The 3D solid elements CHEXA, CPENTA, CPYRAM, CTETRA

• The shell elements CTRIA3, CTRIA6. CTRIAR, CQUAD4, CQUAD8, CQUADR

In the referenced GROUP bulk entry, you can include elements that are topology optimizable elements and elements that are not topology optimizable elements. However, only topology optimizable elements are considered for the relevant DVTREL1 bulk entry. The elements that you select for the topology optimization can only reference an isotropic material defined with the MAT1 bulk entry. Elements in the model that are not selected for topology optimization can reference other material bulk entries. The DVTREL1 entry is the only bulk entry you need to define to invoke topology optimization. The fields on the DVTREL1 entry are described as follows: The STATE field on the DVTREL1 entry allows you to optionally specify that the elements referenced in the GROUP field are either ACTIVE or FROZEN. The software creates design variables and other relevant data for active elements, but not for frozen elements. The STATE field default is ACTIVE. The following examples demonstrate how the STATE field is used. • If you define one or multiple DVTREL1 entries and FROZEN is defined in the STATE field for all, the elements that are not referenced by a DVTREL1 entry are active. This scenario is useful when you are designating most of your model as active except for a few elements. You only need to reference the few frozen elements on one or more DVTREL1 entries.

• If you define one or multiple DVTREL1 entries and all use the default for the STATE field (ACTIVE), only the elements designated as ACTIVE are active. The elements that are not referenced by a DVTREL1 entry are frozen.

• If you define multiple DVTREL1 entries and some use the default for the STATE field (ACTIVE) and some have FROZEN defined, those elements that appear in both types of lists will be treated as frozen. Elements not in either type of list, that is, not referenced by DVTREL1 entries, will also be frozen.

Note that other elements that are not 3D solids or shell elements can be included in the model and their stiffness and mass are included in the analysis. The software simply does not create a design variable for these elements, so their stiffness and mass remain constant during the topology optimization process. The DVID1 field on the DVTREL1 entry allows you to optionally control the identification numbers for the auto-generated design variables. The software auto-generates a DESVAR entry for each element that is active. If used, the DVID1 field is interpreted differently for the various STATE field scenarios. • When FROZEN is defined in the STATE field for all DVTREL1 entries, the design variable ID numbering for the active elements begins with the largest DVID1 found among all DVTREL1 entries. If none of the DVTREL1 entries have the DVID1 field defined, the element IDs of the active elements become the design variable IDs with an automatic offset applied if a conflict occurs.

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If DVID1 is undefined, the element IDs of the active elements become the design variable IDs with an automatic offset applied if a conflict occurs. You can optionally restart a new solution using design variable values from the best design cycle of a previous solution. For this purpose, the original input file should include the following case control command: ECHO=PUNCH(BSTBULK) This will create a jobname.pch file with the best design cycle bulk data. For the consecutive solution, using a copy of your original input file, you will replace the bulk data with the updated bulk data stored in the punch file jobname.pch. You can also restart the new solution using design variable values from the last design cycle of a previous solution. The original input file should include the following case control command: ECHO=PUNCH(NEWBULK) Note that, in both cases, the DSVFLG field on the DVTREL1 entries is automatically written out with a value of 1 to the punch file. This indicates that the design variable values now start with those in the punch file, where the DESVAR data is now in an expanded form. For the consecutive solution, if the only item written into the punch file is the updated bulk data, you can alternatively replace the original bulk data with the following line: include jobname.pch Design responses The first-level design response selects an output such as weight (or mass, depending on how the material density is defined), stress, or displacement. You create first-level responses with the DRESP1 bulk entry. The second-level and third-level responses combine many responses and other items, such as design variable values, using mathematical relationships. You create second-level responses with the DRESP2 bulk entry and third-level responses with the DRESP3 bulk entry. The second-level response uses the mathematical relationships available on the DEQATN bulk entry or a limited number of defined functions, such as AVG for averaging values. The third-level response is computed with an external program that you would need to connect to the NX Nastran run. As a result, you can use sophisticated mathematical relationships and external software when computing a third-level response. For example, to minimize the compliance value from a single load case, you would use the DRESP1 entry. If you want to minimize the maximum of three separate compliance values from three separate load cases (for a MinMax solution), currently you will need to use a more sophisticated approach, such as either the Beta Method or a combination of the DRSPAN case control and the DRESP2 bulk entries. These methods are described below under Design responses across subcases. These methods are slightly more involved to formulate in terms of standard NX Nastran input data. A simplified approach will be available with the NX Nastran maintenance package 12.0.0 MP1 for the

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special case of CMPLNCE (compliance) response. See NX Nastran maintenance package 12.0.0 MP1 for a description of the simplified approach. The design response must be referenced by a design objective or by a design constraint to be considered in the optimization process. • A design objective works to minimize or maximize a response.

• A design constraint places bounds on a response.

• The stress, strain, and force responses require an item code that specifies the type of element output and the component.

For example, a linear stress response at the center of a CQUAD4 (element code “33”), the von Mises stress at the Z1 fiber location (bottom side of the element) uses item code 9. For a list of item codes, see Item Codes in the NX Nastran Quick Reference Guide. In addition to the existing responses available on the DRESP1 entry, the new compliance design response is now available for a static subcase. Compliance is a meaure of flexibility and is represented by the integration across the FE model of the dot product of the strain and stress tensors. It is also identically twice the total strain energy for a given subcase. You define the new compliance design response by including CMPLNCE in the RTYPE field on the DRESP1 entry. Design objective The design objective is the single overall goal of the optimization. You define the single objective with the DESOBJ case control command, which selects a design response. Design objectives can use the first-level responses (DRESP1 entry), or they can use second-level (DRESP2 entry) or third-level (DRESP3 entry) responses. The DRESP2 and DRESP3 responses can be used to define sophisticated combinations of responses and computations, as well as to help in problem set-up, such as for MinMax problems. • You define a single design response for the design objective.

• You choose to either minimize or maximize the design response.

• You can define the design objective for the solution (globally, above the subcases) or for only a specific subcase.

For example, the objective to minimize weight is commonly defined globally. However, the objective to minimize the x-displacement at a grid point can normally only be defined for a specific subcase. For more sophisticated cases, as with MinMax problems, there are methods that allow responses computed across many subcases to be combined into a single global response. As a result, if you define an objective above the subcases (globally) and you reference a response that is subcase dependent such as compliance or displacement, and you have multiple subcases for which you may or may not want this response computed, you must currently make yourself familiar with these methods. See Design responses across subcases. Design constraints on response Design constraints on response define limits on specific responses of your FE model. The optimization algorithm works within the scope of your constraints as it changes design variables while attempting to meet your overall design objective.

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• You define design constraints for the solution (globally, above the subcases) with the DESGLB case control command. Design constraints defined globally can use the first-level responses (DRESP1) weight or volume, or they can use second-level (DRESP2) or third-level (DRESP3) responses computed as a combination of many response types defined at the subcase level as well as other data types. However, to be combined into a global response, the subcase dependent responses should be exclusively assigned to their respective subcases by way of the DRSPAN case control command. Alternatively, the Beta Method can be used to combine subcase dependent responses by a more roundabout though often smoother approach, where some other function is eventually assigned to the objective function or constraint. See Design responses across subcases for a description of these methods.

• You define design constraints in a subcase with the DESSUB case control command. You can use any type of subcase related response at the subcase level.

Both the DESGLB and the DESSUB commands select the DCONSTR or a DCONADD bulk entry, which reference specific design responses defined with the DRESPi bulk entries. The same design response can be selected in multiple design constraints from different subcases, as long as that response is not exclusively assigned to a particular subcase with the DRSPAN case control command. A single DESSUB entry can reference multiple DCONSTR entries with the same ID, but on different responses. Subcase types You can include multiple subcases in a single SOL 200 topology optimization solution. You use the ANALYSIS case control command to designate the subcase type. The following subcase types are supported: Statics, Normal Modes, Modal Frequency, Modal Transient, and Buckling (also requires a Static subcase). For example, several static subcases and a normal modes subcase could all be included. Displacement and stress results from the static subcases, along with specific eigenvalues from the normal modes subcase, can all be used as design responses and referenced by design constraints or by the single objective. SOL 200 parameters – Bulk Data There are numerous parameters that control various aspects of the optimization process. You define some of these parameters on the DOPTPRM bulk entry and others using the PARAM bulk entry. The following is a partial list of some of the key parameters that you can use in a SOL 200 topology optimization. See the DOPTPRM bulk entry and Parameter Descriptions in the Quick Reference Guide for a listing of all parameters and their full descriptions. You can define the following parameters on the DOPTPRM bulk entry: • DESMAX – Defines the maximum number of design cycles to be performed.

• EDVOUT – Defines what fraction of DVEREL1 generated design variables with increased and decreased values are to be printed into the Design Variable History at the end of the f06 file, as well as at requested cycles.

• GMAX – Maximum constraint violation allowed for a feasible design.

You can define the following key parameters with the PARAM bulk entry:

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• BDMNCON – Defines the number of the design cycle at which the software will start the application of any manufacturing constraints, except for planar symmetry manufacturing constraints. (Default=10)

• DESPCH – Defines the frequency in which the solver writes the updated design variables and other updated bulk data output, such as designed property types, to the file jobname.pch.

• DESPCH1 – Defines the level of detail in which the solver writes design cycle output to the file jobname.pch.

• NASPDV – Defines if the topology optimization design variables are to be written to the .f06 file. The software automatically creates the design variables for the elements that you select for the optimization. This output can be substantial for large models. o NASPDV = 0 (Default) The topology optimization design variables are not written to the .f06 file.

o NASPDV = 1 The topology optimization design variables are written to the .f06 file.

• NASPRT – The frequency with which the solution performs data recovery and writes output to the .op2 file. The NASPRT parameter includes the following new options for topology optimization. o NASPRT = 0 (Default): Output occurs for the 0th and the best design cycle.

o NASPRT = N where N>0: Output occurs for the 0th cycle and for every Nth increment.

o NASPRT = -1: No output occurs.

o NASPRT = -2: Output occurs for every improved design cycle.

Note that for topology optimization, none of the NASPRT settings specifically requests output for the last design cycle. As a result, the NMD result for the last design cycle is only output when the last design cycle happens to coincide with one of the NASPRT requests described above. The following descriptions for NASPRT are specific to a non-topology optimization run. This behavior is the same as in previous releases.

o NASPRT = 0 (default): Output occurs for the 0th and the last design cycle.

o NASPRT = N where N>0: Output occurs for the 0th, for every Nth increment, and for the last design cycle.

o NASPRT < 0: No output occurs.

Lattice support Structurally, a lattice is a two- or three-dimensional framework consisting of a crisscrossed pattern of material strips. With modern technology, small scale lattices can be created using additive manufacturing. Each lattice type has a unique averaged out NMD to stiffness relationship. You can request that all of the elements you have designated as active with the DVTREL1 entry are made of the same type of lattice structure. The new DMRLAW bulk entry is available to select currently a single lattice type for your model. If you have selected a lattice type, the software will adjust design variable to property relations accordingly.

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You can select from the following types on the new DMRLAW bulk entry:

TYPE Field Value: Lattice Type OCTET Octet CUBIC Cubic BCC BCC FCC FCC OCTAHDRL Octahedral BCCCUBIC BCC+Cubic FCCCUBIC FCC+Cubic BCCFCC BCC+FCC BFCUBIC BCC+FCC+Cubic LINEAR NMD and Young’s modulus change at the same rate. SIMP See Penalty laws below. RAMP (Default) See Penalty laws below.

Penalty laws In addition to the lattice definitions, you also have the option to define a mass density to stiffness relationship using one of two penalty laws on the DMRLAW bulk entry. The penalty laws define the effective Young's modulus as a function of the NMD μ. • For TYPE=SIMP, the SIMP law has the form:

where p is a penalty parameter defined with the TYPEPRM field. If you define TYPE=SIMP but leave the TYPEPRM field blank, the software uses the default value of p=3.

• For TYPE=RAMP, the RAMP law has the form:

where q is a penalty parameter defined with the TYPEPRM field. If you define TYPE=RAMP but leave the TYPEPRM field blank, the software uses the default value of q=5. If you leave both TYPE and the TYPEPRM fields blank, the software uses RAMP with q = 5.0.

Manufacturing constraints Manufacturing constraints are optional restrictions that you can include in your topology optimization solution to guide the design towards meeting your production criteria. You can use the new DMNCON bulk entry to request that the software enforce the manufacturing constraints listed below. Multiple DMNCON bulk entries are supported if you would like to define a variety of manufacturing constraints. • Additive (ADDM) Additive manufacturing such as 3D printing builds material layer by layer. The previous layers in a build-up should be able to support consecutive layers. When building up overhanging geometry, if the overhang is built at an aggressive angle, there is a possibility that the structure can collapse as a result of cantilevered material. Also, practical reasons may dictate that slender

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members of an additive manufacturing built structure not be below a certain minimum size in cross-sectional dimension. For the angle requirement, you define a maximum overhang angle and the manufacturing direction which is normal to the base plate. Overhang angles are measured relative to the positive manufacturing direction vector. For the minimum size requirement, you simply enter an allowable minimum dimension. The overhang angle and the minimum dimension are separate and independent options.

• Casting die direction (CDID) Parts that are cast should not have any pockets or protrusions that would interfere with the mold or die pieces from parting, or the part coming out of the mold. You define the coordinates of a point on the casting plane, a vector normal to the casting plane, a vector along which a part of the mold travels when separating, and another optional vector along which another part of the mold, if it exists, travels when separating.

• Checker-boarding control (CHBC) Checker-boarding control is ON by default, even when a DMNCON bulk entry is not specified. Checker-boarding is a condition where topology optimizers remove material in an alternating pattern similar to a checker board, when simpler finite elements are used. It is undesirable because it does not represent an optimal distribution of material and the results are difficult to manufacture. The checker-boarding control constraint can be used to help prevent this condition from occurring. Note: If you want to disable the checker-boarding control, you must define the DMNCON bulk entry with TYPE=CHBC and a negative real number in the OFF-FLAG field (currently labeled "Radius" in the Simcenter dialogs).

• Cyclic symmetry (SYMC) This is similar to the planar symmetry scenario below, except that a full circular model is built. The mesh on each sector does not need to match. The software works to symmetrize the NMD values on each sector, based on your specification of either repeated or reflected symmetry. You define the axis of rotation, the number of sectors (NSECT) within the 360 degrees, and relative to a 0-degree symmetry plane on one side of the representative sector, you define a point on the symmetry plane and a radial vector perpendicular to the axis of rotation along one of the edges of the sector on the symmetry plane. The software sweeps the 0-degree symmetry plane counterclockwise by the angle = 360/ | NSECT | to determine the other side of the representative sector. When NSECT is a positive integer, the software treats your model as one of repeated sectors. When NSECT is a negative integer, the software treats your model as one of reflected sectors. With repeated symmetry, each sector is similar to every other sector. With reflected symmetry, each sector is the mirror image of the previous sector. You can use reflected symmetry only with an even number of sectors.

• Extrusion along a straight line (EXTC) Extruded parts must have material continuity in the extrusion direction.

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You define the extrusion direction.

• Min/Max size (MINS or MAXS) This allows you to control the minimum or maximum member size, such as the minimum or maximum dimension at a cross-section. For example, if you define the maximum member size, truss members created by the optimization process will tend to be no thicker in cross-section than the specified size. You define the size value.

• Planar symmetry (SYMP) With this constraint, your model must be meshed on both sides of the symmetry plane. The mesh does not need to match on each side of the symmetry plane. The software works to symmetrize the NMD values on both sides of a given symmetry plane, by linking design variables in an appropriate manner on two sides of the symmetry plane. More than one symmetry plane manufacturing constraint may be specified. You define a point on the symmetry plane and a vector normal to the symmetry plane.

Manufacturing constraint delay The new parameter BDMNCON, normally with a default of 10, defines the number of the design cycles at which the software will start the application of manufacturing constraints during the SOL 200 topology optimization solution, except for the SYMP type constraint. This delay has been found to improve the results when manufacturing constraints are specified. The SOL 200 maximum allowed number of design cycles, which is defined with the DESMAX parameter on the DOPTPRM bulk entry, may affect the default value of BDMNCON. As a result, the BDMNCON parameter default is the smaller of 10 cycles or of the value of the DESMAX parameter minus 3, but not less than 2. Design responses across subcases Most DRESP1 design response types are computed at the solution subcase level. Exceptions are the weight and volume response types which are computed independent of any subcases. When you define an objective or constraint above multiple subcases (globally), you cannot directly reference a DRESP1 response that is subcase dependent, such as compliance or displacement. You currently must instead define NX Nastran input syntax that exclusively assigns DRESP1 responses to relevant subcases as a precursor to formulating a global response. For this purpose, you will need to learn about the NX Nastran case control commands DRSPAN and SET, and about the bulk entries DRESP2, DRESP3, DEQATN. These inputs are not yet available through the Simcenter dialogs. Below, we give an example of how this is done for a particular popular class of problems. Let us take the MinMax problem of minimizing the value of the maximum of a particular DRESP1 response as computed in various subcases. Since an objective minimizes or maximizes a single quantity, you must resolve the responses computed in your many subcases into a single value. For example, if you have ten subcases with ANALYSIS=STATIC, each with unique load cases, and you have a single objective to minimize compliance, you likely want to minimize the largest of the compliance values from the 10 subcases. However, the code will not automatically make this association and you need to make this request in your input file by using standard NX Nastran input syntax.

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You can accomplish this by using either the DRSPAN or BETA methods which are both described below. The DRSPAN method is simpler to define than the BETA method, although, when posed properly, the BETA method achieves better convergence and results on the average. You are advised to try both to see which one will produce the better result for your particular job type. DRSPAN method • The DRESP1 bulk entry defines the response type. For example, you can define a DRESP1 bulk entry which requests that compliance be computed, but this response is not yet tied to a particular subcase, as DRESP1 responses are not associated with any subcases unless through use of DRSPAN or DCONSTR.

• You define a DRSPAN=n case control command inside the subcase you want to exclusively assign certain DRESP1 entries to, where n is the ID of a SET command. This association tells the software that this is the only subcase you want these responses to be computed at. It is important to note that once a DRESP1 is associated with a particular subcase by use of DRSPAN, it may not be associated with another subcase. This is different than the use of DRESP1 in DCONSTR, where DCONSTR for different subcases may refer to the same DRESP1, such that it is computed separately for each subcase.

• You define a SET n = ID1, ID2, ….IDi within case control, which lists the IDs of the DRESP1 entries you want to exclusively associate with a subcase.

• You can create multiple DRSPAN and SET command combinations when you want to exclusively assign different sets of DRESP1 entries to different subcases.

• Once various DRESP1 are exclusively assigned to certain subcases by way of DRSPAN/SET combinations, they can now be combined, together with other entities if needed, in one or more DRESP2 or DRESP3 type response, which can now be treated as global responses. An example would be the use of the MAX function in a DRESP2, acting on DRESP1 from more than one subcase, and pointing to the maximum of these as the DRESP2 response value. You define your design objective or DESGLB constraint globally which selects such a DRESP2 or DRESP3 entry.

DRSPAN method example The DRESP1 entries in the following input are each associated with a different subcase and are combined into a single DRESP2 entry which is selected as a global response by the design objective (DESOBJ). .... SOL 200 $ DESOBJ(MIN) = 5 DESGLB = 7 $ SET 100 = 111 SET 200 = 222 $ SUBCASE 1 LABEL = Nastopt - Statics 1 LOAD = 1 SPC = 2 ANALYSIS = STATICS DRSPAN = 100

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$ SUBCASE 2 LABEL = Nastopt - Statics 1_1 LOAD = 3 SPC = 4 ANALYSIS = STATICS DRSPAN = 200 $ BEGIN BULK .... DRESP2 5 MAXCMP MAX + DRESP1 111 222 $ DRESP1 111 SUBCAS1 CMPLNCE DRESP1 222 SUBCAS2 CMPLNCE $ .... BETA method • The BETA method requires that you first determine the order of magnitude of your subcase responses for the starting design. Currently, you will need to first run an initial analysis to get these values. If you are using a compliance response for your objective, you can request strain energy output using the ESE=ALL case control command and then multiply the total strain energy values at the tops of the tables for the various subcases by 2.0 to compute the compliance value for each. For this initial analysis, you can define DESMAX=0 on the DOPTPRM bulk entry to avoid unnecessary design cycles. After your initial solution completes, open the *.f06 file and search for the following for each subcase. The example below includes output for two subcases. .... E L E M E N T S T R A I N E N E R G I E S

ELEMENT-TYPE = TETRA * TOTAL ENERGY OF ALL ELEMENTS IN PROBLEM = 9.730185E+04 SUBCASE 1 * TOTAL ENERGY OF ALL ELEMENTS IN SET -1 = 9.730185E+04 .... E L E M E N T S T R A I N E N E R G I E S ELEMENT-TYPE = TETRA * TOTAL ENERGY OF ALL ELEMENTS IN PROBLEM = 4.452013E+04 SUBCASE 2 * TOTAL ENERGY OF ALL ELEMENTS IN SET -1 = 4.452013E+04 .... As a result: For Subcase 1: Compliance = 2.0 * 9.730185E+04 = 1.946037E+05 For Subcase 2: Compliance = 2.0 * 4.452013E+04 = 8.904026E+04 From the computed compliance values, you need to determine a reasonable normalizing value such that (compliance / normalizing value) < 1.0 (but not << 1.0) for all subcases. For the example above, a normalizing value of 1.0E+06 achieves this goal. The normalizing value is used in the following steps.

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• You will now create an artificial design variable which will act as a cap on the compliances from the associated subcases. See the Note below as to how an ID is assigned to this design variable. The artificial design variable serves the purpose of converting the discrete MAX concept to a continuous one based on a single value. For the example described here, we will assume an ID of 1000000. Note: (a) For topology optimization, which is indicated by the DVTREL1 entry, the software will offset internal design variables based on any explicit artificial variable ID, so the ID selection is arbitrary. (b) For classical SOL 200 optimization jobs, the ID of the artificial variable should not conflict with existing explicit design variable IDs. (c) For topometry optimization (indicated by DVEREL1 data), care should be taken to avoid conflict with DVEREL1 defined internal design variable numbering. Future development is planned to remove this small complication for the last two cases. The starting value for your design variable should be larger than the maximum of the normalized compliance values computed for all subcases for the initial design. For example, using the subcase 1 compliance value of 1.946037E+05, the normalized value is computed as (1.946037E+05 / 1.0E+06) = 0.194, and as 0.089 for the second subcase. So, for the example, 0.2 can be used as the starting value for the artificial design variable. This value is greater than both normalized compliance values, and is therefore a cap on the compliance values for the initial design. DESVAR 1000000 SYNTH1 0.2 1.0E-6 100.0 The upper bound for this design variable has been given high to allow the compliance values to increase as much as necessary. A small upper bound, such as 1.0, may constrain the job unnecessarily. The lower bound is taken as 1.0E-06, a sufficiently small value, which we do not expect will be breached.

• Next, you will want to make sure that the value of the artificial design variable remains a cap on the compliance values throughout the optimization process. Thus, at the optimum, the maximum of the two normalized compliance values will be no greater than the value of the artificial variable. This requires setting up constraints for each of the two subcases. Let C1 and C2 be the actual compliance values from subcases 1 and 2, respectively. Also let X be the value of the artificial design variable. Thus, our constraints should be of the form: Ci/1.0E6 ≤ X, i=1,2 and therefore, Ci/1.0E6 - X ≤ 0.0, i=1,2 Since the software may have precision problems with values very close to 0.0, you can add 10.0 (or some other reasonable number) to both sides: Ci/1.0E6 - X +10.0 ≤ 10.0, i=1, 2 You now have a constraint on the function [Ci/1.0E6 – X + 10.0] with an upper bound of 10.0. This function on the left hand side will be represented by a DRESP2 type response, but first you need to define the general compliance value Ci by a DRESP1. For example: DRESP1 111 COMPLNCE CMPLNCE Note that this DRESP1 can be used for both subcases (or, in general, multiple subcases), as we will show. This is different than for the DRSPAN case, where a separate DRESP1 had to be exclusively assigned to each subcase.

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You are now ready to define your DRESP2, which will be constrained as shown above: DRESP2 201 BCOMPL1 500 + DESVAR 1000000 + DRESP1 111 and this DRESP2 refers to an equation given by DEQATN, 500: DEQATN 500 F(B,C) = C/1.0E6 – B + 10.0 which is your function defining how the DRESP2 value should be computed. B and C are in the same order as the items in the DRESP2 response. So far, both the DRESP1 and the DRESP2 are simply templates. Only when referred to by appropriate DCONSTR will they be used to compute values for relevant subcases.

• A DCONSTR specifies a constraint in a constraint set belonging either to a particular subcase or to DESGLB (global constraint set). From a subcase, DCONSTR are referenced by the DESSUB case control command. Since you have two subcases, you will need a separate DESSUB for each subcase, for example: SUBCASE 1 … DESSUB=101 $ SUBCASE 2 … DESSUB=102

In this particular case, we have only one DCONSTR for each DESSUB: DCONSTR,101,201, ,10.0 DCONSTR,102,201, ,10.0 Note that the response referred to from each DCONSTR is DRESP2, 201, which is now computed separately at each subcase (as is the DRESP1, 111) for the evaluation of each DCONSTR. Also note the upper bound of 10.0 from our constraint expression above. For this case, it is best to leave the lower bound to default, as it is not expected to be instrumental in the process.

• You are now ready to define your objective, which is to find the minimum value of the artificial design variable that caps the compliance values as they increase. In NX Nastran, only a response can be assigned to the objective function, not a design variable. However, by employing a simple trick, the artificial design variable value can be converted to a response value: DRESP2 400 OBJ AVG + DESVAR 1000000

where AVG means compute the average of the values of the listed items (of which there is only one), after which you can define the objective function as:

DESOBJ(MIN) = 400

BETA method example The following lines of input demonstrate the BETA method for the two subcase example described above.

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... SOL 200 $ DESOBJ(MIN) = 400 .... $ SUBCASE 1 LOAD = 1 SPC = 2 ANALYSIS = STATICS DESSUB=101 $ SUBCASE 2 LOAD = 3 SPC = 4 ANALYSIS = STATICS DESSUB=102 $ BEGIN BULK $ DRESP2 400 OBJ AVG + DESVAR 1000000 $ DESVAR 1000000 SYNTH1 0.2 1.0E-6 100.0 $ DRESP1 111 COMPLNCE CMPLNCE $ DRESP2 201 BCOMPL1 500 + DESVAR 1000000 + DRESP1 111 $ DEQATN 500 F(B,C)=C/1.0e6-B+10.0 $ DCONSTR,101,201,,10.0 DCONSTR,102,201,,10.0 $ ... NX Nastran maintenance package 12.0.0 MP1 An alternative enhanced DESOBJ command will be available with the NX Nastran maintenance package 12.0.0 MP1. Since the NX Nastran 12.0.0 MP1 release will not include updated documentation, the enhanced DESOBJ command and software behavior is described below. This description does not apply to NX Nastran 12.0. The NX Nastran 12.0.0 MP1 release will be included with the release of the Simcenter maintenance package 12.0.0 MP1. The enhancement simplifies the specification of jobs involving design objectives (DESOBJ) on the minimization of a function of compliance values for multiple static subcases, with specific emphasis on the maximum of these compliance values. While this can already be done in NX Nastran 12.0 with the DRSPAN or BETA methods described in Design responses across subcases, the enhanced DESOBJ command will make it much easier to prepare input data and to run jobs through Simcenter 12.0.0 MP1 directly. It is planned to enhance the DESOBJ command further in future releases to accommodate more use cases.

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The Simcenter 12.0.0 MP1 release inputs will not change. However, when you use Simcenter 12.0.0 MP1 and you assign a compliance (CMPLNCE) response (DRESP1) to the objective function, Simcenter will automatically write the following to the NX Nastran input file: DESOBJ (MIN, SCSET=ALL, SCFUNC=MAX) = ID_of_compliance_DRESP1 In the above, SCSET=ALL refers to all static subcases, and SCFUNC=MAX specifies that the objective is to minimize the maximum of the compliance values from the multiple static subcases. You can also modify the values assigned to SCSET and SCFUNC using either the Simcenter text editor window or an external text editor to allow any of the options described below. The updated DESOBJ format for the NX Nastran 12.0.0 MP1 release will be as follows.

The MIN or MAX selection will still request that the objective is to be minimized or maximized. Also, n will still refer to a response ID, although, when using the new format (that is, SCSET and SCFUNC are defined) in NX Nastran 12.0.0 MP1, n can only refer to a compliance response defined with the DRESP1 bulk entry. SCSET=ALL will refer to all static subcases. SCSET=m will refer to specific static subcaces, where m is the ID of a SET case control command that lists the relevant subcases. SCFUNC=function will have the following function choices:

Function Description Compute the sum of the compliance values from the multiple static SUM subcases. Compute the average of the compliance values from the multiple static AVG subcases. Compute the sum of the squares of the compliance values from the SSQ multiple static subcases. Compute the square root of the sum of the squares of the compliance RSS values from the multiple static subcases. Use the maximum of the compliance values from the multiple static MAX subcases. Use the minimum of the compliance values from the multiple static MIN subcases.

As stated above, Simcenter 12.0.0 MP1 will only write the following when you assign a compliance (CMPLNCE) response (DRESP1) to the objective function:

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DESOBJ (MIN, SCSET=ALL, SCFUNC=MAX) = ID_of_compliance_DRESP1 To vary this definition, you will need to edit the input file. For example, the following input, which would apply the SSQ function to the responses from the multiple static subcases, will need to be defined manually in an input file: DESOBJ (MIN, SCSET=ALL, SCFUNC=SSQ) = ID_of_DRESP1

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DVTREL1

Element Selection for Topology Optimization

Selects the elements for the software to automatically create design variables and other related data for topology optimization.

FORMAT:

1 2 3 4 5 6 7 8 9 10 DVTREL1 ID LABEL GRPID STATE DSVFLG DVID1

EXAMPLE:

DVTREL1 200 24 30000

FIELDS:

Field Contents ID Identification number of DVTREL1 entry. (Integer>0) LABEL Optional user-defined label. (Character) GRPID ID of GROUP bulk entry that specifies a list of elements. The software associates the following types of elements with topology optimization: The 3D solid elements CHEXA, CPENTA, CPYRAM, CTETRA. and the shell elements CTRIA3, CTRIA6. CTRIAR, CQUAD4, CQUAD8, CQUADR. Any other element types or IDs for non-existent elements listed on a GROUP entry are ignored. (Integer>0) STATE Specifies that the elements referenced in the GRPID field are either ACTIVE or FROZEN. The software modifies the active elements, but not the frozen elements. (Character; Default =ACTIVE). See Remark 1 for examples demonstrating how the STATE field is used. DSVFLG Flag set by the software when you are recycling design variables from a previous solution for restart purposes. (Integer=0 or 1; Default=0) DSVFLG=0 or blank (Default): Value used in a first pass optimization solution. This value triggers the software to create new design variables and other relevant data for the elements designated as ACTIVE. DSVFLG=1: Value used in a restart solution. This value triggers the software to use already existing design variables and their values created in a previous solution. Normally, the software sets this value of 1 for DSVFLG automatically when writing the updated bulk data into the punch file. See Remark 2.

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Field Contents DVID1 Option to control the identification numbers for the auto-generated design variables. (Integer≥0; Default=0) If DVID1=0 or blank (Default), the design variable IDs will be equal to the IDs of the associated elements plus an automatically calculated offset to ensure no conflicts occur with any other design variables. If DVID1>0, see Remark 3 for the description.

REMARKS: 1. The STATE field allows you to optionally specify that the elements referenced in the GROUP field are either ACTIVE or FROZEN. The software creates a design variable for each active element, but not for frozen elements. The STATE field default is ACTIVE. The following examples demonstrate how the STATE field is used. • If you define one or multiple DVTREL1 entries and FROZEN is defined in the STATE field for all DVTREL1 entries, the topology optimizable elements that are not referenced by a DVTREL1 entry are active. This scenario is useful when you are designating most of your model as active except for a few elements. You only need to reference the few frozen elements on a DVTREL1 entry.

• If you define one or multiple DVTREL1 entries and all use the default for the STATE field (ACTIVE), only those elements designated as ACTIVE are active. Elements that are not referenced by a DVTREL1 entry are frozen.

• If you define multiple DVTREL1 entries and some use the default for the STATE field (ACTIVE) and some have FROZEN defined, the elements designated as ACTIVE are active. An exception to this is when an element is referenced by multiple DVTREL1 entries and is designated as both FROZEN and as ACTIVE. Such elements are frozen. All other elements designated as FROZEN along with any elements that are not selected in any DVTREL1 referenced GROUP data are also frozen.

Note that other elements that are not 3D solids or shell elements can be included in the model and are included in the analysis. The software simply does not create design data for these elements, so they remain constant during the topology optimization process.

2. You can optionally recycle design variable values from a previous solution to use them in a restart. The procedure is as follows. • In the original solution, your DVTREL1 entries will use the default value DSVFLG=0 and the software auto-generates new design variables with initial values of 1.0. Also, in your input file for the original optimization solution, you will request a punch file output containing the bulk data for the best design cycle, using the following command in case control: ECHO=SORT, PUNCH(BSTBULK)

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At the end of the original solution, the punch file that the software creates will include an entire BEGIN BULK section which includes everything from your original BEGIN BULK section but with some changes and additions. Specifically, your DVTREL1 entries in the punch file will now have DSVFLG=1 defined, and the punch file will include the explicit design variable values corresponding to the best design cycle found in the original solution.

• For the restart solution, you will create a new input file which uses the BEGIN BULK contents from the punch file created in original solution.

• If you wish to restart from the last design cycle instead of the best one, you will need to use the following ECHO case control command in your original input file: ECHO=SORT,PUNCH(NEWBULK) When the last design cycle is the best one, this selection does not matter. However, it is not possible to know this until the original solution is complete.

3. The DVID1 field allows you to optionally control the identification numbers for the auto-generated design variables. The software auto-generates a DESVAR and other various data for each element that is active. The software uses the DVID1 field differently for the following STATE field scenarios. • When FROZEN is defined in the STATE field for all DVTREL1 entries, the design variable ID numbering for the active elements begins with the largest DVID1 found among all DVTREL1 entries. If none of the DVTREL1 entries have the DVID1 field defined, the element IDs of the active elements become the design variable IDs with an automatic offset applied if a conflict occurs.

• When ACTIVE is defined in the STATE field for a DVTREL1 entry, the design variable ID numbering for the elements referenced by that DVTREL1 entry begins with the value defined in the DVID1 field. The numbering then continues incrementally for the remainder of the active elements referenced by that DVTREL1 entry. If DVID1 is undefined, the element IDs of the active elements become the design variable IDs with an automatic offset applied if a conflict occurs.

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DMNCON

Manufacturing Constraint for Topology Optimization

Defines a manufacturing constraint for topology optimization.

ADDITIVE MANUFACTURING (ADDM) FORMAT:

1 2 3 4 5 6 7 8 9 10 DMNCON ID ADDM ANGLE MIND X Y Z N1 N2 N3

CASTING DIE DIRECTION(S) (CDID) FORMAT:

1 2 3 4 5 6 7 8 9 10 DMNCON ID CDID X Y Z N1 N2 N3 D1 D2 D3 D21 D22 D23

CHECKER-BOARDING CONTROL (CHBC) FORMAT:

1 2 3 4 5 6 7 8 9 10 DMNCON ID CHBC OFF-FLAG

CYCLIC SYMMETRY (SYMC) FORMAT:

1 2 3 4 5 6 7 8 9 10 DMNCON ID SYMC X Y Z N1 N2 N3 M1 M2 M3 NSECT

EXTRUSION ALONG A STRAIGHT LINE (EXTC) FORMAT:

1 2 3 4 5 6 7 8 9 10 DMNCON ID EXTC N1 N2 N3

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MINIMUM SIZE (MINS) FORMAT:

1 2 3 4 5 6 7 8 9 10 DMNCON ID MINS Size

MAXIMUM SIZE (MAXS) FORMAT:

1 2 3 4 5 6 7 8 9 10 DMNCON ID MAXS Size

PLANAR SYMMETRY (SYMP) FORMAT:

1 2 3 4 5 6 7 8 9 10 DMNCON ID SYMP X Y Z N1 N2 N3

EXAMPLES:

DMNCON 500 SYMP 0.0 1.0 0.0 0.7071 0.7071 1.0

DMNCON 200 EXTC 1.0 0.0 0.0

FIELDS:

Field Contents General Fields: ID Identification number. (Integer>0) TYPE Type of manufacturing constraint. (TYPE examples: ADDM, CHBC, EXTC) See Remark 4. (Character; No default)

Fields for Additive Manufacturing (ADDM): Note that either ANGLE or MIND can be blank, indicating there is no such constraint. ANGLE Maximum angle from the normal that points away from the base plate, for overhangs, in degrees. (Real) MIND Minimum allowed size. (Real).

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Field Contents X,Y,Z Coordinates of a point on a plane for the base plate. (Real) Ni Components of a vector normal to the base plate in the direction of material addition. (Real)

Fields for Casting die direction(s) (CDID): X,Y,Z Coordinates of a point on the casting plane. (Real) Ni Components of a vector normal to the casting plane. (Real) Di Components of a vector that defines the first direction of mold removal. (Real) D2i Components of an optional vector that defines a second direction of mold removal. If these components D2i are all 0.0 or blank, then only the first direction is used. (Real: default=0.0,0.0,0.0)

Fields for Checker-boarding control (CHBC): OFF-FLAG This field is used only to turn off the default checker-boarding control, achieved by entering a negative real number in this field. (Real) The checker-boarding control manufacturing constraint is on by default, even when you have not defined the DMNCON bulk entry. To disable checker-boarding control, you must define the DMNCON bulk entry with TYPE= CHBC and a negative real number in the OFF-FLAG field. Any other choices for the OFF-FLAG field will result in the checker-boarding control remaining on by default.

Fields for Cyclic symmetry (SYMC): X,Y,Z Coordinates of a point on a selected symmetry plane, therefore defined to be at 0 degrees. (Real) Ni Components of a vector defining the axis of rotation. (Real) Mi Components of a vector perpendicular to the axis of rotation, along one of the edges of the model on the 0-degree symmetry plane. The software will sweep the 0-degree symmetry plane counter clockwise by the angle = 360/NSECT to determine each of the consecutive symmetry planes. (Real) NSECT The number of sectors which would fill the 360 degrees. (Positive or negative integer) When NSECT is a positive integer, the symmetry is that of repeated sectors. When NSECT is a negative integer, the symmetry is that of reflected sectors.

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Field Contents

Fields for Extrusion along a straight line (EXTC): Ni Components of a vector defining the extrusion direction. (Real)

Fields for Min and Max size (MINS or MAXS): Size Minimum or maximum member size. (Real)

Fields for Planar symmetry (SYMP): X,Y,Z Coordinates of a point on the symmetry plane. (Real) Ni Components of a vector normal to the symmetry plane. (Real)

REMARKS: 1. Multiple DMNCON bulk entries are supported if you would like to define a variety of manufacturing conditions. For example, you can have multiple DMNCON entries with TYPE=SYMP, and could also add another DMNCON entry with TYPE=MAXS.

2. The manufacturing conditions currently apply to all of the active elements selected for topology optimization.

3. Except for TYPE=SYMP, the parameter BDMNCON defines the design cycle at which the software will start application of the manufacturing constraints during the SOL 200 topology optimization solution. The resulting delay has been found to improve the quality of results in topology optimization with manufacturing constraints. The BDMNCON parameter default is the smaller of 10 cycles, or the value of the DESMAX parameter minus 3, but not smaller than 2. The DESMAX parameter defines the maximum number of design cycles allowed, and is defined on the DOPTPRM bulk entry. SYMP is applied from the beginning.

TYPE Description Additive manufacturing builds material layer by layer. The previous layers in a build-up must be sufficient to support consecutive layers. When building up overhanging geometry, if the overhang is built in an aggressive angle, there is a possibility that the structure can collapse as a result of Additive (ADDM) cantilevered material. You define a maximum overhang angle and/or a minimum size applicable to any slender members, as well as the manufacturing direction. Overhang angles are measured relative to the positive manufacturing direction vector.

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TYPE Description Parts that are cast should not have any pockets that cannot be formed or protrusions that would interfere with the mold pieces from parting, or with the part coming out of the mold. Casting die You define the coordinates of a point on the casting plane, direction (CDID) a vector normal to the casting plane, a vector along which one part of the mold travels when separating, and another, optional, vector along which the other part of the mold, if it exists, travels when separating. Checker-boarding is a condition where topology optimizers remove material in an alternating pattern similar to a checker board, when simpler finite elements are used. It is undesirable because it does not represent an optimal distribution of material and the results are difficult to manufacture. The checker-boarding control constraint can be used to help prevent this condition from occurring. Checker-boarding control (CHBC) OFF-FLAG < 0.0, the checker-boarding control is turned off. OFF-FLAG ≥ 0.0, the checker-boarding control is left on. * Note: The software applies the checker-boarding control by default even when you have not defined a DMNCON bulk entry. If you want to disable the checker-boarding control, you must define the DMNCON bulk entry with TYPE=CHBC and a negative real number in the OFF-FLAG field. You provide a full circular model which has repeated cyclic symmetry sectors. The mesh on each sector does not need to match. The software will work to symmetrize the normalized mass density (NMD) values on each sector. You define the axis of rotation, the number of sectors (NSECT) within 360 degrees, and relative to a 0-degree symmetry plane, you define a point on that symmetry plane and a radial vector perpendicular to the axis of rotation along one of the edges of the symmetry plane. The software sweeps Cyclic symmetry the 0-degree symmetry plane counter clockwise by the angle (SYMC) = 360 / | NSECT | to determine the consecutive symmetry planes. When NSECT is a positive integer, the software treats your model as having repeated sectors. When NSECT is a negative integer, the software treats your model as having reflected sectors. With repeated symmetry, each sector is similar to every other sector. With reflected symmetry, every sector is the mirror image of the previous sector. You can use reflected symmetry only with an even number of sectors. Extrusion along a Extruded parts must have material continuity in the extrusion straight line (EXTC) direction. You define the straight line extrusion direction. This allows you to control the minimum member size for Min size (MINS) created “slender” members. You define the minimum cross-sectional "thickness" size.

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TYPE Description This allows you to control the maximum member size. For example, if you define the maximum member size, truss Max size (MAXS) members created by the optimization process will not be any "thicker" than the specified size. With this condition, your model must be meshed on both sides of the symmetry plane. The mesh on each side of the Planar symmetry symmetry plane does not need to match. The software works (SYMP) to symmetrize the NMD values on both sides of a given symmetry plane. You define a point on the symmetry plane and a vector normal to the symmetry plane.

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DMRLAW

Material relation law definition for SOL 200 topology optimization.

Defines the relation between material properties and the normalized mass density (NMD) for SOL 200 topology optimization.

FORMAT:

1 2 3 4 5 6 7 8 9 10 DMRLAW ID TYPE TYPEPRM

EXAMPLE:

DMRLAW 200 SIMP 3.5

DMRLAW 200 SIMP

DMRLAW 302 CUBIC

FIELDS:

Field Contents ID Material relation law ID. (Integer > 0) TYPE Type of law. See Remarks 2 and 3 for the supported law types. (Character; Default=RAMP, with TYPEPRM=5.0) TYPEPRM Defines p for the SIMP penalty law, and q for the RAMP penalty law. See Remark 3. (Real; Default is p=3.0 for the SIMP law and q=5.0 for the RAMP law)

REMARKS: 1. Only a single DMRLAW bulk entry is allowed.

2. A lattice in this context is a thin truss-like repeating cell structure that is manufactured, for example, using additive manufacturing. Each lattice type has a unique mass density to stiffness relationship. With the “LINEAR“ type (see below), the software auto-generates the design variables for topology optimization such that a linear relationship exists between the NMD and the Young’s Modulus. In contrast, lattices, as well as SIMP and RAMP, impose non-linear relations. Currently you can only request a single DMRLAW bulk entry for all elements you have designated as active with one or more DVTREL1 entries. The software will adjust design variable to property relations accordingly. The following types of lattice cells and penalty functions are supported: TYPE Field Lattice Type Value: OCTET Octet CUBIC Cubic

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TYPE Field Lattice Type Value: BCC BCC FCC FCC OCTAHDRL Octahedral BCCCUBIC BCC+Cubic FCCCUBIC FCC+Cubic BCCFCC BCC+FCC BFCUBIC BCC+FCC+Cubic SIMP See Remark 3 RAMP See Remark 3

3. In addition to the lattice types, you also have the option to define a mass density to stiffness relationship using one of two following penalty laws. These penalty laws define the effective Young's modulus as a function of the normalized mass density μ. • For TYPE=SIMP, the SIMP law has the form:

where p is a penalty parameter defined with the TYPEPRM field. If you leave the TYPEPRM field blank, the software uses the default value of p=3.0.

• For TYPE=RAMP, the RAMP law has the form:

where q is the penalty parameter defined with the TYPEPRM field. If you leave the TYPEPRM field blank, the software uses the default value of q=5.0.

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Chapter 11: Monitor points

Monitor points for element results and grid point forces

In previous releases, NX Nastran supports MONPNT1 for SOL 144. In this release, NX Nastran support of monitor points is expanded to include the new MONPNT2 and MONPNT3 bulk entries for SOL 101 and SOL 103. The capability of monitor points is enhanced to include element results from stress, strain, or force, and to provide summation of grid point forces at specified integrated load points in a local coordinate system. You use the new bulk entry: • MONPNT2 to output component of stress, strain, or force at a named element. The software outputs the results in a table titled STRUCTURAL INTERNAL MONITOR POINT LOADS (MONPNT2). Because MONPNT2 operates on the data block level, it can monitor an NDDL entry from the STRESS-STRAIN (contained in the oes.dll file) or FORCE (contained in the oef.dll file) output data block.

• MONPNT3 to sum select grid point forces at a chosen integrated load point. You select a set of grids to sum forces and moments about a specified point. The software outputs the results in a table titled STRUCTURAL INTEGRATED FREE BODY MONITOR POINT LOADS (MONPNT3).

Also, you can use the new MONITOR case control command to control the output of MONPNT2 and MONPNT3 results to the .f06 output file. You can place the MONITOR command above the subcase level or in individual subcases.

Note You can optionally use the OIBULK parameter to request that the software writes all case control commands, including the MONITOR3 command, to the CASECC data block in your .op2 file. For more information, see PARAM, POST ,< 0.

For an example that demonstrates the use of MONITOR, MONPNT2, and MONPNT3, see Monitor points example.

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MONPNT2

Integrated Load Monitor Point — Element Monitor Output Results Item

Defines an integrated load monitor point at a named element, and outputs component of stress, strain, or force at that element for SOL 101 and SOL 103 (SORT1 format only).

FORMAT:

1 2 3 4 5 6 7 8 9 10 MONPNT2 NAME LABEL TABLE TYPE COMP EID

EXAMPLE:

MONPNT2 MPT22 This is a MONPNT2 monitor point STRAIN CBAR EX1A 1100082 STRESS CBAR SX1A 1100234

FIELDS:

Field Contents NAME A unique character string that identifies the monitor point. (Character; 8 characters maximum; No default) LABEL A string that identifies and labels the monitor point. (Character; 56 characters maximum; Optional) TABLE Type of output to be monitored. (Character; "STRESS", "FORCE", or "STRAIN"; No default) TYPE Element type. (Character; No default) COMP Component of the element type to be monitored. This is the COMP label for the particular table and element type. For a list of supported elements and their components, see Stress monitor table and Force monitor table. (Character; No default) EID Element ID. (Integer > 0; No default)

REMARKS: 1. For a list of supported elements and their components, see Stress monitor table and Force monitor table.

2. Because of the name/descriptor field, free-field, and large field data formats are not supported for this bulk entry.

3. For shell laminates, only the homogeneous stress/strain is output. The NOCOMPS parameter allows you to control the shell laminate output. If this parameter: = 0 or -1, The homogeneous stress/strain is output.

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= 1, No homogeneous stress/strain is output.

Note Output for solid laminates and layer by layer output is not supported.

4. Output for superelements that are processed at the monitor point: • For internal and partitioned superelements, MONPNT2 results can be output for the residual or downstream superelements.

• For external superelements, MONPNT2 results are only output for the residual superelement.

Note The various elements defined for a MONPNT2 may not exist for all of the superelements in a model. When this occurs, the MONPNT2 is not processed for the superelement.

5. Invalid Table, Type, COMP, or EID generates a warning message and is ignored.

6. The software prints the results in a table titled STRUCTURAL INTERNAL MONITOR POINT LOADS (MONPNT2)

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STRESS MONITOR TABLE

Real Stresses/Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase SX1A/EX1A End A-Point C SX1AR/EX1AR End A-Point C RM SX2A/EX2A End A-Point D SX2AR/EX2AR End A-Point D RM SX3A/EX3A End A-Point E SX3AR/EX3AR End A-Point E RM SX4A/EX4A End A-Point F SX4AR/EX4AR End A-Point F RM AS/AE Axial ASR/AER Axial RM BMAXA/EBMAXA End A maximum SX1AI/EX1AI End A-Point C lP BMINA/EBMINA End A minimum SX2AI/EX2AI End A-Point D IP Safety margin in MST/MST SX3AI/EX3AI End A-Point E IP tension SX1B/EX1B End B-Point C SX4AI/EX4AI End A-Point F IP CBAR SX2B/EX2B End B-Point D ASI/AEI Axial IP 34 SX3B/EX3B End B-Point E SX1BR/EX1BR End B-Point C RM SX4B/EX4B End B-Point F SX2BR/EX2BR End B-Point D RM BMAXB/EBMAXB End B maximum SX3BR/EX3BR End B-Point E RM BMINB/EBMINB End B minimum SX4BR/EX4BR End B-Point F RM Safety margin in MSC SX1BI/EX1BI End B-Point C IP compression SX2BI/EX2BI End B-Point D IP SX3BI/EX3BI End B-Point E IP SX4BI/EX4BI End B-Point F IP

Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase Station Station SD SD RM Distance/Length Distance/Length SXC/EXC Point C SXCr/EXCr Point C RM SXD/EXD Point D SXDr/EXDr Point D RM SXE/EXE Point E SXEr/EXEr Point E RM SXF/EXF Point F SXFr/EXFr Point F RM CBAR AS/AE Axial ASr/AEr Axial RM 100 SMAX/EMAX Maximum SMAXr/EMAXr Maximum RM

Intermediate SMIN/EMIN Minimum SMINr/EMINr Minimum RM Stations Margin of Safety SXCi/EXCi Point C IP

(NDDL entitys above SXDi/EXDi Point D IP are given for End A. SXEi/EXEi Point E IP MS For codes 2 through 10 at intermediate SXFi/EXFi Point F IP stations add (K-1)*9 ASi/AEi Axial IP where K is the station number, and for SMAXi/EMAXi Maximum IP

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Minimum

(NDDL entitys above are given for End A. For codes 2 through codes at End B, 16 at intermediate K=number of stations IP SMINi/EMINi stations add (K-1)*15 plus 1.) where K is the station number, and for codes at End B, K=number of stations plus 1.) Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase GRID External grid point ID GRID External grid point ID Station Station SD SD distance/length distance/length Long. Stress/Strain Long. Stress/Strain SXC/EXC SRCR/ERCR RM at Point C at Point C Long. Stress/Strain Long. Stress/Strain SXD/EXD SXDR/EXDR RM at Point D at Point D Long. Stress/Strain Long. Stress/Strain SXE/EXE SXER/EXER RM at Point E at Point E Long. Stress/Strain Long. Stress/Strain SXF/EXF SXFR/EXFR RM at Point F at Point F Maximum Long. Stress/Strain SMAX/EMAX SXCI/EXCI IP Stress/Strain at Point C Minimum Long. Stress/Strain CBEAM SMIN/EMIN SXDI/EXDI IP Stress/Strain at Point D 2 Safety margin in Long. Stress/Strain MST SXEI/EXEI IP tension at Point E Linear Format Safety margin in Long. Stress/Strain compression at Point F

NDDL entitys are NDDL entitys are given for End A. given for End A. Addition of the Addition of the quantity (K-1)*10 quantity (K-1)*10 to the NDDL entity to the NDDL entity SXFI/EXFI IP MSC points to the same points to the same information for other information for other stations, where K is stations, where K is the station number. the station number. K=11 for End B, K=11 for End B, and K=2 through and K=2 through 10 for intermediate 10 for intermediate stations. stations. Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase

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GRID External grid point ID GRID External grid point ID Circumferential Circumferential CA CA angle angle Long. Stress/Strain Long. Stress/Strain SC/EC SCR/ECR RM at Point C at Point C Long. Stress/Strain Long. Stress/Strain SD/ED SDR/EDR RM at Point D at Point D Long. Stress/Strain Long. Stress/Strain SE/EE SER/EER RM at Point E at Point E Long. Stress/Strain Long. Stress/Strain SF/EF SFR/EFR RM at Point F at Point F CBEND Maximum Long. Stress/Strain SMAX/EMAX SCI/ECI IP Stress/Strain at Point C 69 Minimum Long. Stress/Strain SMIN/EMIN SDI/EDI IP Stress/Strain at Point D Safety margin in Long. Stress/Strain MST SEI/EEI IP tension at Point E Safety margin in Long. Stress/Strain compression at Point F

(NDDL entitys are (NDDL entitys are MSC given for End A. SFI/EFI given for End A. IP NDDL entitys 12 NDDL entitys 12 through 21 point to through 21 point to the same information the same information for end B.) for End B.) Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase TX Translation-x TXR Translation-x R TY Translation-y TYR Translation-y R TZ Translation-z TZR Translation-z R RX Rotation-x RXR Rotation-x R RY Rotation-y RYR Rotation-y R CBUSH RZ Rotation-z RZR Rotation-z R 102 TXI Translation-x I Linear Format TYI Translation-y I TZI Translation-z I RXI Rotation-x I RYI Rotation-y I RZI Rotation-z I Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase

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FE Axial force UE Axial displacement VE Axial velocity CBUSH1D AS Axial stress 40 AE Axial strain EP FAIL Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase

CELAS1 SR/ER Stress/Strain RM S/E Stress/Strain 11 SI/EI Stress/Strain IP

CELAS2 SR/ER Stress/Strain RM S/E Stress/Strain 12 SI/EI Stress/Strain IP

CELAS3 SR/ER Stress/Strain RM S/E Stress/Strain 13 SI/EI Stress/Strain IP Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CPX Normal x SHY Shear y SHZ Shear z CGAP AU Axial u Not applicable 86 SHV Shear v SHW Shear w SLV Slip v SLP Slip w Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase Stress coordinate Stress coordinate CID CID system system Coordinate type Coordinate type CTYPE CTYPE (Character) (Character) Number of active Number of active NODEF NODEF points points External grid ID External grid ID GRID GRID CHEXA (0=center) (0=center)

67 SX/EX Normal x SXR/EXR Normal x RM TXY/ETXY Shear xy SYR/EYR Normal y RM Linear Format P1/EP1 First principal SZR/EZR Normal z RM First principal x P1X/P1X TXYR/ETXYR Shear xy RM cosine Second principal x P2X/P2X TYZR/ETYZR Shear yz RM cosine Third principal x P3X/P3X TZXR/ETZXR Shear zx RM cosine

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PR/EPR Mean pressure SXI/EXI Normal x lP von Mises or OCT/EOCT octahedral shear SYI/EYI Normal y IP stress SY/EY Normal y SZI/EZI Normal z IP TYZ/ETYZ Shear yz TXYI/ETXYI Shear xy IP P2/EP2 Second principal TYZI/ETYZI Shear yz IP First principal y P1Y/P1Y TZXI/ETZXI Shear zx IP cosine Second principal y P2Y/P2Y cosine Third principal y P3Y/P3Y cosine SZ/EZ Normal z TZX/ETZX Shear zx P3/EP3 Third principal First principal z P1Z/P1Z cosine Second principal z P2Z/P2Z cosine Third principal z P3Z/P3Z cosine Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase AS/AE Axial Stress/Strain ASR/AER Axial Stress/Strain RM CONROD MSA Axial safety margin ASI/AEI Axial Stress/Strain IP Torsional Torsional 10 TS/TE TSR/TER RM Stress/Strain Stress/Strain Linear Format Torsional safety Torsional MST TSI/TEI IP margin Stress/Strain Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase Stress coordinate Stress coordinate CID CID system system Coordinate type Coordinate type CTYPE CTYPE (Character) (Character) Number of active Number of active NODEF NODEF points points GRID External grid ID GRID External grid ID CPENTA SX/EX Normal x SXR/EXR Normal x RM 68 TXY/ETXY Shear xy SYR/EYR Normal y RM

Linear Format P1/EP1 First principal SZR/EZR Normal z RM First principal x P1X/P1X TXYR/ETXYR Shear xy RM cosine Second principal x P2X/P2X TYZR/ETYZR Shear yz RM cosine Third principal x P3X/P3X TZXR/ETZXR Shear zx RM cosine PR/EPR Mean pressure SXI/EXI Normal x IP

11-8 NX Nastran 12 Release Guide Monitor points

von Mises or OCT/EOCT Octahedral shear SYI/EYI Normal y IP stress SY/EY Normal y SZI/EZI Normal z IP TYZ/ETYZ Shear yz TXYI/ETXYI Shear xy IP P2/EP2 Second principal TYZI/ETYZI Shear yz IP First principal y P1Y/P1Y TZXI/ETZXI Shear zx IP cosine Second principal y P2Y/P2Y cosine Third principal y P3Y/P3Y cosine SZ/EZ Normal z TZX/ETZX Shear zx P3/EP3 Third principal First principal z P1Z/P1Z cosine Second principal z P2Z/P2Z cosine Third principal z P3Z/P3Z cosine Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase SX Normal stress in x SXR Normal stress in x RM

CPLSTN3 SY Normal stress in y SXI Normal stress in x IP SZ Normal stress in z SYR Normal stress in y RM 271 SP In-plane shear stress SYI Normal stress in y IP Triangle plane strain SMAX Von Mises stress SZR Normal stress in z RM Linear Format SZI Normal stress in z IP (Center Only) SPR In-plane shear stress RM SPI In-plane shear stress IP Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase GRID Grid ID, 0 for centroid GRID Grid ID, 0 for centroid SX Normal stress in x SXR Normal stress in x RM CPLSTN4 SY Normal stress in y SXI Normal stress in x IP 272 SZ Normal stress in z SYR Normal stress in y RM Quadrilateral plane SP In-plane shear stress SYI Normal stress in y IP strain SMAX Von Mises stress SZR Normal stress in z RM Linear Format SZI Normal stress in z IP (Center and Corners) SPR In-plane shear stress RM SPI In-plane shear stress IP Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase

NX Nastran 12 Release Guide 11-9 ChCaphtaeprte1r1:11M: oniMtoornpiotoinrtpsoints

GRID Grid ID, 0 for centroid GRID Grid ID, 0 for centroid SX Normal stress in x SXR Normal stress in x RM CPLSTN6 SY Normal stress in y SXI Normal stress in x IP 273 SZ Normal stress in z SYR Normal stress in y RM Triangle plane strain SP In-plane shear stress SYI Normal stress in y IP

CPLSTS3 SY Normal stress in y SXI Normal stress in x IP SZ Normal stress in z SYR Normal stress in y RM 275 SP In-plane shear stress SYI Normal stress in y IP Triangle plane stress SMAX Von Mises stress SZR Normal stress in z RM Linear Format SZI Normal stress in z IP (Center Only) SPR In-plane shear stress RM SPI In-plane shear stress IP Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase GRID Grid ID, 0 for centroid GRID Grid ID, 0 for centroid Normal stress in x Normal stress in x RM CPLSTS4 SX SXR SY Normal stress in y SXI Normal stress in x IP 276 SZ Normal stress in z SYR Normal stress in y RM Quadrilateral plane SP In-plane shear stress SYI Normal stress in y IP stress SMAX Von Mises stress SZR Normal stress in z RM Linear Format SZI Normal stress in z IP (Center and Corners) SPR In-plane shear stress RM SPI In-plane shear stress IP

11-10 NX Nastran 12 Release Guide Monitor points

Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase GRID Grid ID, 0 for centroid GRID Grid ID, 0 for centroid SX Normal stress in x SXR Normal stress in x RM CPLSTS6 SY Normal stress in y SXI Normal stress in x IP 277 SZ Normal stress in z SYR Normal stress in y RM Triangle plane stress SP In-plane shear stress SYI Normal stress in y IP

Linear Format SMAX Von Mises stress SZR Normal stress in z RM SZI Normal stress in z IP (Center and Corners) SPR In-plane shear stress RM SPI In-plane shear stress IP Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase GRID Grid ID, 0 for centroid GRID Grid ID, 0 for centroid Normal stress in x Normal stress in x RM CPLSTS8 SX SXR SY Normal stress in y SXI Normal stress in x IP 278 SZ Normal stress in z SYR Normal stress in y RM Quadrilateral plane SP In-plane shear stress SYI Normal stress in y IP stress SMAX Von Mises stress SZR Normal stress in z RM Linear Format SZI Normal stress in z IP (Center and Corners) SPR In-plane shear stress RM SPI In-plane shear stress IP Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase Stress/Strain Stress coordinate CID CID coordinate system system Coordinate type Coordinate type CTYPE CTYPE (Character) (Character) Number of active Number of active NODEF NODEF points points GRID External grid ID GRID External grid ID (0=center) (0=center) CPYRAM SX/EX Normal x SXR/EXR Normal x RM 255 TXY/ETXY Shear xy SYR/EYR Normal y RM Linear Format P1/EP1 First principal SZR/EZR Normal z RM First principal x P1X/P1X TXYR/ETXYR Shear xy RM cosine Second principal x P2X/P2X TYZR/ETYZR Shear yz RM cosine Third principal x P3X/P3X TZXR/ETZXR Shear zx RM cosine PR/EPR Mean pressure SXI/EXI Normal x IP

NX Nastran 12 Release Guide 11-11 ChCaphtaeprte1r1:11M: oniMtoornpiotoinrtpsoints

von Mises or OCT/EOCT octahedral shear SYI/EYI Normal y IP stress SY/EY Normal y SZI/EZI Normal z IP TYZ/ETYZ Shear yz TXYI/ETXYI Shear xy IP P2/EP2 Second principal TYZI/ETYZI Shear yz IP First principal y P1Y TZXI/ETZXI Shear zx IP cosine Second principal y P2Y cosine Third principal y P3Y cosine SZ/EZ Normal z TZX/ETZX Shear zx P3/EP3 Third principal First principal z P1Z cosine Second principal z P2Z cosine Third principal z P3Z cosine Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase FD1 Z1=Fiber Distance 1 FD1 Z1=Fiber Distance 1 SX1/EX1 Normal x at Z1 SX1R/EX1R Normal x at Z1 RM SY1/EY1 Normal y at Z1 SX1I/EX1I Normal x at Z1 IP TXY1/EXY1 Shear xy at Z1 SY1R/EY1R Normal y at Z1 RM SA1/EA1 Shear angle at Z1 SY1I/EY1I Normal y at Z1 IP SMJRP1/ Major principal at Z1 TXY1R/EXY1R Shear xy at Z1 RM EMJRP1 SMNRP1/ Minor principal at Z1 TXY1I/EXY1I Shear xy at Z1 IP EMNRP1 CQUAD4 von Mises or SMAX1/EMAX1 maximum shear FD2/FD2 Z2=Fiber distance 2 33 at Z1 Linear Format FD2 Z2=Fiber distance 2 SX2R/EX2R Normal x at Z2 RM SX2/EX2 Normal x at Z2 SX2I/EX2I Normal x at Z2 IP Center Only SY2/EY2 Normal y at Z2 SY2R/EY2R Normal y at Z2 RM TXY2/EXY2 Shear xy at Z2 SY2I/EY2I Normal y at Z2 IP SA2/EA2 Shear angle at Z2 TXY2R/EXY2R Shear xy at Z2 RM SMJRP2/ Major principal at Z2 TXY2I/EXY2I Shear xy at Z2 IP EMJRP2 SMNRP2/ Minor principal at Z2 EMNRP2 von Mises or SMAX2/ maximum shear EMAX2 at Z2

11-12 NX Nastran 12 Release Guide Monitor points

Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase

TERM CEN/ TERM CEN/

CQUAD4 T1/ET1 Shear-12 T1/ET1 Shear-12 RM SL1/EL1 Shear-1Z SL1/EL1 Shear-1Z RM 95 SL2/EL2 Shear-2Z SL2/EL2 Shear-2Z RM Composite A1 Shear angle SX1I/EX1I Normal-1 IP Center Only MJRP1/EMJRP1 Major principal SY1I/EY1I Normal-2 IP MNRP1/EMNRP1 Minor principal T1I/ET1I Shear-12 IP TMAX1/ETMAX1 Maximum shear SL1I/EL1I Shear-1Z IP SL2I/EL2I Shear-2Z IP Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase

NX Nastran 12 Release Guide 11-13 ChCaphtaeprte1r1:11M: oniMtoornpiotoinrtpsoints

TERM CEN/ TERM CEN/

GRID 4 GRID 4 FD1 Z1-Fiber distance FD1 Z1-Fiber distance SX1/EX1 Normal x at Z1 SX1R/EX1R Normal x at Z1 RM SY1/EY1 Normal y at Z1 SX1I/EX1I Normal x at Z1 IP TXY1/ETXY1 Shear xy at Z1 SY1R/EY1R Normal y at Z1 RM A1 Shear angle at Z1 SY1I/EY1I Normal y at Z1 IP SMJRP1/ Major principal at Z1 TXY1R/ETXY1R Shear xy at Z1 RM EMJRP1 SMNRP1/ CQUAD8 Minor principal at Z1 TXY1I/ETXY1I Shear xy at Z1 IP EMNRP1 64 von Mises or TMAX1/ maximum shear FD2 Z2-Fiber distance ETMAX1 Linear Format at Z1 Center and Corners FD2 Z2-Fiber distance SX2R/EX2R Normal x at Z2 RM SX2/EX2 Normal x at Z2 SX2I/EX2I Normal x at Z2 IP SY2/EY2 Normal y at Z2 SY2R/EY2R Normal y at Z2 RM TXY2/ Shear xy at Z2 SY2I/EY2I Normal y at Z2 IP ETXY2 A2 Shear angle at Z2 TXY2R/ETXY2R Shear xy at Z2 RM SMJRP2/ Major principal at Z2 TXY2I/ETXY2I Shear xy at Z2 IP EMJRP2 SMNRP2/ Minor principal at Z2 EMNRP2 von Mises or TMAX2/ maximum shear ETMAX2 at Z2 Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CQUAD8 96 Same as Same as Same as Same as Composite CQUAD4(95) CQUAD4(95) CQUAD4(95) CQUAD4(95) Center Only Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase

TERM CEN/ TERM CEN/

GRID 4 GRID 4 FD1 Z1-Fiber distance FD1 Z1-Fiber distance CQUADR SX1/EX1 Normal x at Z1 SX1R/EX1R Normal x at Z1 RM 82 SY1/EY1 Normal y at Z1 SX1I/EX1I Normal x at Z1 IP Center and Corners TXY1/ETXY1 Shear xy at Z1 SY1R/EY1R Normal y at Z1 RM A1 Shear angle at Z1 SY1I/EY1I Normal y at Z1 IP MJRP1/EMJRP1 Major principal at Z1 TXY1R/ETXY1R Shear xy at Z1 RM MNRP1/EMNRP1 Minor principal at Z1 TXY1I/ETXY1I Shear xy at Z1 IP

11-14 NX Nastran 12 Release Guide Monitor points

von Mises or TMAX1/ETMAX1 maximum shear FD2 Z2-Fiber distance at Z1 FD2 Z2-Fiber distance SX2R/EX2R Normal x at Z2 RM SX2/EX2 Normal x at Z2 SX2I/EX2I Normal x at Z2 IP SY2/EY2 Normal y at Z2 SY2R/EY2R Normal y at Z2 RM TXY2/ETXY2 Shear xy at Z2 SY2I/EY2I Normal y at Z2 IP A2 Shear angle at Z2 TXY2R/ETXY2R Shear xy at Z2 RM MJRP2/EMJRP2 Major principal at Z2 TXY2I/ETXY2I Shear xy at Z2 IP MNRP2/EMNRP2 Minor principal at Z2 von Mises or TMAX2/ETMRP2 maximum shear at Z2 Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CQUADR 228 Same as Same as Same as Same as Center only CQUAD4(33) CQUAD4(33) CQUAD4(33) CQUAD4(33) (not supported by old formulation) Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CQUADR 232 Composite Same as Same as Same as Same as Center Only CQUAD4(95) CQUAD4(95) CQUAD4(95) CQUAD4(95) (not supported by old formulation) Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CTYPE 0 (Result at Center) CTYPE 0 (Result at Center) LOC Location LOC Location SX Radial SXR Radial RM CQUADX4 SY Azimuthal SXI Radial IP 243 SZ Axial SYR Azimuthal RM Linear Format SS Shear stress SYI Azimuthal lP Center and Corners MAXP Maximum principal SZR Axial RM

Grid and Gauss TMAX Maximum shear SZI Axial lP von Mises or OCTS SSR Shear stress RM octahedral SSI Shear stress IP Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase

NX Nastran 12 Release Guide 11-15 ChCaphtaeprte1r1:11M: oniMtoornpiotoinrtpsoints

CQUADX8 245 Same as Same as Same as Same as Linear Format CQUAD4(33) CQUAD4(33) CQUAD4(33) CQUAD4(33) Grid and Gauss Center and Corners Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CROD Same as Same as Same as Same as 1 CONROD(10) CONROD(10) CONROD(10) CONROD(10) Linear Format Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase TMAX/ETMAX Maximum shear TMAXR/ETMAXR Maximum shear RM CSHEAR TAVG/ETAVG Average shear TMAXI/ETMAXI Maximum shear lP

4 TAVGR/ETAVGR Average shear RM MS Safety margin TAVGI/ETAVGI Average shear IP Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase Stress coordinate Stress coordinate CID CID system system Coordinate type Coordinate type CTYPE CTYPE (Character) (Character) Number of active Number of active NODEF NODEF points points External grid ID External grid ID GRID GRID (0=center) (0=center) SX/EX Normal x SXR/EXR Normal x RM TXY/ETXY Shear xy SYR/EYR Normal y RM P1/EP1 First principal SZR/EZR Normal z RM First principal x P1X TXYR/ETXYR Shear xy RM cosine CTETRA Second principal x P2X TYZR/ETYZR Shear yz RM cosine 39 Third principal x P3X TZXR/ETZXR Shear zx RM Linear Format cosine PR/EPR Mean pressure SXI/EXI Normal x IP von Mises or OCT/EOCT octahedral shear SYI/EYI Normal y IP stress SY/EY Normal y SZI/EZI Normal z IP TYZ/ETYZ Shear yz TXYI/ETXYI Shear xy IP P2/EP2 Second principal TYZI/ETYZI Shear yz IP First principal y P1Y TZXI/ETZXI Shear zx IP cosine Second principal y P2Y cosine Third principal y P3Y cosine

11-16 NX Nastran 12 Release Guide Monitor points

SZ/EZ Normal z TZX/ETZX Shear zx P3/EP3 Third principal First principal z P1Z cosine Second principal z P2Z cosine Third principal z P3Z cosine Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CTRAX3 242 Same As CQUADX4 Same As CQUADX4 Same As CQUADX4 Same As CQUADX4 Linear Format (243) (243) (243) (243) Center and Corners Grid or Gauss Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CTRAX6 244 Same As CQUADX4 Same As CQUADX4 Same As CQUADX4 Same As CQUADX4 Linear Format (243) (243) (243) (243) Grid and Gauss Center and Corners Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CTRIA3 74 Same as Same as Same as Same as Linear Format CQUAD4(33) CQUAD4(33) CQUAD4(33) CQUAD4(33) Center Only CTRIA3 97 Same as Same as Same as Same as Composite CQUAD4(95) CQUAD4(95) CQUAD4(95) CQUAD4(95) Center Only Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CTRIA6 75 Same as Same as Same as Same as Linear Format CQUAD8(64) CQUAD8(64) CQUAD8(64) CQUAD8(64) Center and Corners CTRIA6 98 Same as Same as Same as Same as Composite CQUAD4(95) CQUAD4(95) CQUAD4(95) CQUAD4(95) Center Only Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase

NX Nastran 12 Release Guide 11-17 ChCaphtaeprte1r1:11M: oniMtoornpiotoinrtpsoints

TERM CEN/ TERM CEN/

GRID 4 GRID 4 FD1 Z1-Fiber distance FD1 Z1-Fiber distance SX1/EX1 Normal x at Z1 SX1R/EX1R Normal x at Z1 RM SY1/EY1 Normal y at Z1 SX1I/EX1I Normal x at Z1 IP TXY1/ETXY1 Shear xy at Z1 SY1R/EY1R Normal y at Z1 RM A1 Shear angle at Z1 SY1I/EY1I Normal y at Z1 IP MJRP1/ Major principal at Z1 TXY1R/ETXY1R Shear xy at Z1 RM EMJRP1 MNRP1/ Minor principal at Z1 TXY1I/ETXY1I Shear xy at Z1 IP CTRlAR EMNRP1 von Mises or TMAX1/ 70 maximum shear FD2 Z2-Fiber distance ETMAX1 at Z1 Center and Corners FD2 Z2-Fiber distance SX2R/EX2R Normal x at Z2 RM SX2/EX2 Normal x at Z2 SX2I/EX2I Normal x at Z2 IP SY2/EY2 Normal y at Z2 SY2R/EY2R Normal y at Z2 RM TXY2/ Shear xy at Z2 SY2I/EY2I Normal y at Z2 IP ETXY2 A2 Shear angle at Z2 TXY2R/ETXY2R Shear xy at Z2 RM MJRP2/ Major principal at Z2 TXY2I/ETXY2I Shear xy at Z2 IP EMJRP2 MNRP2/ Minor principal at Z2 EMNRP2 von Mises or TMAX2/ maximum shear ETMAX2 at Z2 Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase FD1 Z1=Fiber Distance 1 FD1 Z1=Fiber Distance 1 SX1/EX1 Normal x at Z1 SX1R/EX1R Normal x at Z1 RM SY1/EY1 Normal y at Z1 SX1I/EX1I Normal x at Z1 IP TXY1/EXY1 Shear xy at Z1 SY1R/EY1R Normal y at Z1 RM SA1/EA1 Shear angle at Z1 SY1I/EY1I Normal y at Z1 IP SMJRP1/ CTRlAR Major principal at Z1 TXY1R/EXY1R Shear xy at Z1 RM EMJRP1 227 SMNRP1/ Minor principal at Z1 TXY1I/EXY1I Shear xy at Z1 IP Center Only EMNRP1 von Mises or SMAX1/ (not supported by old maximum shear FD2/FD2 Z2=Fiber distance 2 EMAX1 formulation) at Z1 FD2 Z2=Fiber distance 2 SX2R/EX2R Normal x at Z2 RM SX2/EX2 Normal x at Z2 SX2I/EX2I Normal x at Z2 IP SY2/EY2 Normal y at Z2 SY2R/EY2R Normal y at Z2 RM TXY2/EXY2 Shear xy at Z2 SY2I/EY2I Normal y at Z2 IP SA2/EA2 Shear angle at Z2 TXY2R/EXY2R Shear xy at Z2 RM

11-18 NX Nastran 12 Release Guide Monitor points

SMJRP2/ Major principal at Z2 TXY2I/EXY2I Shear xy at Z2 IP EMJRP2 SMNRP2/ Minor principal at Z2 EMNRP2 von Mises or TMAX2/ maximum shear EMAX2 at Z2 Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase CTRlAR 233 Composite Same as Same as Same as Same as Center Only CQUAD4(95) CQUAD4(95) CQUAD4(95) CQUAD4(95) (not supported by old formulation) Real Stresses or Strains Complex Stresses or Strains Element Name Real/Mag. or Imag./ (Code) NDDL entity Item NDDL entity Item Phase AS Axial Stress SE Equivalent Stress CTUBE TE Total Strain 3 EPS Eff Plastic Strain Linear Format ECS Eff Creep Strain Linear Torsional LTS Stress

NX Nastran 12 Release Guide 11-19 ChCaphtaeprte1r1:11M: oniMtoornpiotoinrtpsoints

FORCE MONITOR TABLE

Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase Bending End A plane Bending End A plane BM1A BM1AR RM 1 1 Bending End A plane Bending End A plane BM2A BM2AR RM 2 2 Bending End B plane Bending End B plane BM1B BM1BR RM 1 1 Bending End B plane Bending End B plane BM2B BM2BR RM 2 2 TS1 Shear plane 1 TS1R Shear plane 1 RM TS2 Shear plane 2 TS2R Shear plane 2 RM AF Axial force AFR Axial force RM CBAR TRQR Torque RM Bending End A plane 34 BM1AI IP 1 Bending End A plane BM2AI IP 2 Bending End B plane BM1BI IP 1 TRQ Torque Bending End B plane BM2BI IP 2 TS1I Shear plane 1 IP TS2I Shear plane 2 IP AFI Axial force lP TRQI Torque IP Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase Station Distance/ Station Distance/ SD SD RM Length Length Bending Moment Bending Moment BM1 BM1r RM Plane 1 Plane 1 Bending Moment Bending Moment BM2 BM2r RM Plane 2 Plane 2 TS1 Shear Force Plane 1 TP1r Shear Force Plane 1 RM TS2 Shear Force Plane 2 TP2r Shear Force Plane 2 RM CBAR AF Axial AFr Axial RM 100 TRQ Torque TrQR Torque RM NDDL entitys are given for End A. Addition of the quantity (K-1) * 7 Bending Moment to the NDDL entity BM1i IP Plane 1 points to the same information for other stations, where K is the station

11-20 NX Nastran 12 Release Guide Monitor points

number. K=8 for End B and 2 through 7 for intermediate stations. Bending Moment BM2i IP Plane 2 TS1i Shear Force Plane 1 IP TS2i Shear Force Plane 2 IP AFi Axial IP Torque (NDDL entitys above are given for End A. For codes 2 through 14 at intermediate TRQi stations add (K-1) IP * 13 and K is the station number, and for codes at End B, K+number of stations plus 1.) Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase GRID External grid point ID GRID External grid point ID Station Station SD SD distance/length distance/length Bending moment Bending moment BM1 BM1R RM plane 1 plane 1 Bending moment Bending moment BM2 BM2R RM plane 2 plane 2 TS1 Web shear plane 1 TS1R Web shear plane 1 RM TS2 Web shear plane 2 TS2R Web shear plane 2 RM AF Axial force AFR Axial force RM TTRQ Total torque TTRQR Total torque RM WTRQ Warping torque WTRQR Warping torque RM (NDDL entitys are CBEAM given for End A. Addition of the 2 quantity (K-1) 9 to the NDDL entity points to the same information for other Bending moment BM1I IP stations, where K is plane 1 the station number. K=11 for End B and 2 through 10 for intermediate stations.)

Bending moment BM2I IP plane 2 TS1I Web shear plane 1 lP TS2I Web shear plane 2 IP AFI Axial force IP

NX Nastran 12 Release Guide 11-21 ChCaphtaeprte1r1:11M: oniMtoornpiotoinrtpsoints

TTRQI Total torque IP WTRQI Warping torque lP (NDDL entitys are given for End A. Addition of the quantity (K-1) 16 to the NDDL entity points to the same information for other stations, where K is the station number. K=11 for End B and 2 through 10 for intermediate stations.) Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase TX Force-x TXR Force-x RM TY Force-y TYR Force-y RM TZ Force-z TZR Force-z RM RX Moment-x RXR Moment-x RM RY Moment-y RYR Moment-y RM CBEAR RZ Moment-z RZR Moment-z RM

280 TXI Force-x IP TYI Force-y IP TZI Force-z IP RXI Moment-x IP RYI Moment-y IP RZI Moment-z IP Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase GRID External grid point ID GRID External grid point ID Bending moment Bending moment BM1 BM1R RM plane 1 plane 1 Bending moment Bending moment BM2 BM2R RM plane 2 plane 2 TS1 Shear plane 1 TS1R Shear plane 1 RM TS2 Shear plane 2 TS2R Shear plane 2 RM

CBEND AF Axial force AFR Axial force RM Torque TRQR Torque RM 69 (NDDL entitys are given for End A. NDDL entitys 9 Bending moment BM1I IP through 15 point to plane 1 TRQ the same information for End B.) Bending moment BM2I IP plane 2 TS1I Shear plane 1 IP

11-22 NX Nastran 12 Release Guide Monitor points

TS2I Shear plane 2 IP AFI Axial force lP Torque (NDDL entitys are given for End A. TRQi NDDL entitys 15 IP through 27 point to the same information for End B.) Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase FX Force-x FXR Force-x RM FY Force-y FYR Force-y RM FZ Force-z FZR Force-z RM MX Moment-x MXR Moment-x RM MY Moment-y MYR Moment-y RM CBUSH MZR Moment-z RM 102 FXI Force-x IP Linear Format FYI Force-y IP MZ Moment-z FZI Force-z IP MXI Moment-x IP MYI Moment-y IP MZI Moment-z IP Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase CDAMP1 Same as Same as Same as Same as 20 CELAS1(11) CELAS1(11) CELAS1(11) CELAS1(11) Same as Same as Same as Same as CDAMP2 CELAS1(11) CELAS1(11) CELAS1(11) CELAS1(11) 21 Same as Same as Same as Same as CDAMP3 CELAS1(11) CELAS1(11) CELAS1(11) CELAS1(11) 22 Same as Same as Same as Same as CDAMP4 CELAS1(11) CELAS1(11) CELAS1(11) CELAS1(11) 23 Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase CDUM3 thru Same as Same as Same as Same as CDUM9 CELAS1(11) CELAS1(11) CELAS1(11) CELAS1(11) (55-61) Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase CELAS1 F Force FR Force RM

11 FI Force IP

NX Nastran 12 Release Guide 11-23 ChCaphtaeprte1r1:11M: oniMtoornpiotoinrtpsoints

CELAS2 Same as CELAS1 Same as CELAS1 12 CELAS3 Same as CELAS1 Same as CELAS1 13 CELAS4 Same as CELAS1 Same as CELAS1 14 Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase mz bending End A mz bending End A BM1A BM1AR RM plane 1 plane 1 my bending End A my bending End A BM2A BM2AR RM plane 2 plane 2 mz bending End B mz bending End B BM1B BM1BR RM plane 1 plane 1 my bending End B my bending End B BM2B BM2BR RM plane 2 plane 2 fy shear force plane fy shear force plane TS1 TS1R RM 1 1 fz shear force plane fz shear force plane TS2 TS2R RM 2 2 AF fx axial force AFR fx axial force RM CFAST TRQ mx torque TRQR mx torque RM mz bending End A 119 BM1AI IP plane 1 my bending End A BM2AI IP plane 2 mz bending End B BM1BI IP plane 1 my bending End B BM2BI IP plane 2 fy shear force plane TS1I IP 1 fz shear force plane TS2I IP 2 AFI fx axial force IP TRQI mx torque IP Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase AF Axial force AFR Axial force RM CONROD AFI Axial force IP

10 TRQ Torque TRQR Torque RM TRQI Torque lP Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase

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MX Membrane force x MXR Membrane force x RM MY Membrane force y MYR Membrane force y RM MXY Membrane force xy MXYR Membrane force xy RM BMX Bending moment x BMXR Bending moment x RM BMY Bending moment y BMYR Bending moment y RM BMXY Bending moment xy BMXYR Bending moment xy RM TX Shear x TXR Shear x RM CQUAD4 TY Shear y TYR Shear y RM 33 MXI Membrane force x IP Center Only MYI Membrane force y IP MXYI Membrane force xy IP BMXI Bending moment x IP BMYI Bending moment y IP BMXYI Bending moment xy IP TXI Shear x IP TYI Shear y IP Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase TERM CEN/ TERM CEN/ GRID 4 GRID 4 MX Membrane x MXR Membrane x RM MY Membrane y MYR Membrane y RM MXY Membrane xy MXYR Membrane xy RM BMX Bending x BMXR Bending x RM BMY Bending y BMYR Bending y RM BMXY Bending xy BMXYR Bending xy RM CQUAD4 TX Shear x TXR Shear x RM 144 TY Shear y TYR Shear y RM Center and Corners MXI Membrane x IP MYI Membrane y IP MXYI Membrane xy IP BMXI Bending x IP BMYI Bending y IP BMXYI Bending xy IP TXI Shear x IP TYI Shear y IP Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase CQUAD8 Same as Same as Same as Same as 64 CQUAD144(144) CQUAD144(144) CQUAD144(144) CQUAD144(144) Center and Corners

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Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase CQUADR Same as Same as Same as Same as 82 CQUAD144(144) CQUAD144(144) CQUAD144(144) CQUAD144(144) Center and Corners CQUADR 228 Same as Same as Same as Same as Center Only CQUAD4(33) CQUAD4(33) CQUAD4(33) CQUAD4(33) (not supported by old formulation) Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase CROD Same as Same as Same as Same as 1 CONROD(10) CONROD(10) CONROD(10) CONROD(10) Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase F41 Force 4 to 1 F41R Force 4 to 1 RM F21 Force 2 to 1 F21R Force 2 to 1 RM F12 Force 1 to 2 F12R Force 1 to 2 RM F32 Force 3 to 2 F32R Force 3 to 2 RM F23 Force 2 to 3 F23R Force 2 to 3 RM F43 Force 4 to 3 F43R Force 4 to 3 RM F34 Force 3 to 4 F34R Force 3 to 4 RM F14 Force 1 to 4 F14R Force 1 to 4 RM KF1 Kick force on 1 F41I Force 4 to 1 IP S12 Shear 12 F21I Force 2 to 1 lP KF2 Kick force on 2 F12I Force 1 to 2 IP S23 Shear 23 F32I Force 3 to 2 IP KF3 Kick force on 3 F23I Force 2 to 3 lP CSHEAR S34 Shear 34 F43I Force 4 to 3 IP

4 KF4 Kick force on 4 F34I Force 3 to 4 IP S41 Shear 41 F14I Force 1 to 4 IP KF1R Kick force on 1 RM S12R Shear 12 RM KF2R Kick force on 2 RM S23R Shear 23 RM KF3R Kick force on 3 RM S34R Shear 34 RM KF4R Kick force on 4 RM S41R Shear 41 RM KF1I Kick force on 1 IP S12I Shear 12 lP KF2I Kick force on 2 IP S23I Shear 23 IP

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KF3I Kick force on 3 IP S34I Shear 34 IP KF4I Kick force on 4 IP S41I Shear 41 IP Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase CTRIA3 Same as Same as Same as Same as 74 CQUAD4(33) CQUAD4(33) CQUAD4(33) CQUAD4(33) Center Only CTRlA6 Same as Same as Same as Same as 75 CQUAD144(144) CQUAD144(144) CQUAD144(144) CQUAD144(144) Center and Corners Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase CTRIAR Same as Same as Same as Same as 70 CQUAD144(144) CQUAD144(144) CQUAD144(144) CQUAD144(144) Center and Corners CTRIAR 227 Same as Same as Same as Same as Center Only CQUAD4(33) CQUAD4(33) CQUAD4(33) CQUAD4(33) (not supported by old formulation) Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase AF Axial force AFR Axial force RM CTUBE AFI Axial force IP

3 TRQ Torque TRQR Torque RM TEQI Torque lP Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase CVlSC Same as Same as Same as Same as 24 CONROD(10) CONROD(10) CONROD(10) CONROD(10) Real Element Forces Complex Element Forces Element Name Code Real/Mag. or Imag/ NDDL entity Item NDDL entity Item Phase mz bending End A mz bending End A BM1A BM1AR RM plane 1 plane 1 my bending End A my bending End A CWELDP (118) BM2A BM2AR RM plane 2 plane 2 ELPAT or PARTPAT mz bending End B mz bending End B BM1B BM1BR RM CWELDC (117) plane 1 plane 1 ELIMID or GRIDID my bending End B my bending End B with MSET=OFF BM2B BM2BR RM plane 2 plane 2 CWELD (200) fy shear force plane fy shear force plane TS1 TS1R RM ELIMID or GRIDID 1 1 with MSET=ON fz shear force plane fz shear force plane TS2 TS2R RM 2 2 AF fx axial force AFR fx axial force RM

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TRQ mx torque TRQR mx torque RM mz bending End A BM1AI IP plane 1 my bending End A BM2AI IP plane 2 mz bending End B BM1BI IP plane 1 my bending End B BM2BI IP plane 2 fy shear force plane TS1I IP 1 fz shear force plane TS2I IP 2 AFI fx axial force IP TRQI mx torque IP

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MONPNT3

Integrated Load Monitor Point — Sums Grid Point Forces

Defines an integrated load monitor point at a chosen point and sums select grid point forces for SOL 101 and SOL 103.

FORMAT:

1 2 3 4 5 6 7 8 9 10 MONPNT3 NAME LABEL AXES GRIDGRP ELEMGRP CP X Y Z XFLAG CD

EXAMPLE:

MONPNT3 MPT33 This is a MONPNT3 monitor point. 246 1001 2002 1.0 2.0 3.0 MD 1003

FIELDS:

Field Contents NAME A unique character string that identifies the monitor point. (Character; 8 characters maximum; No default) LABEL A string that identifies and labels the monitor point. (Character; 56 characters maximum; Optional) AXES Component axes about which to sum. (Integer; Any unique combination of the integers 1 through 6 with no embedded blanks; No default) GRIDGRPGROUP entry that has a list of grids to be included in the monitor point. (Integer; No default). See Remark 1. ELEMGRPGROUP entry that has a list of elements to process at the monitor point. (Integer; Optional). See Remark 2. CP The identification number of a coordinate system in which the X, Y, and Z coordinates are defined. (Integer; Default = 0; Optional). See Remark 5. X, Y, Z The coordinates in the CP coordinate system about which the forces are to be summed. (Real; Default = 0.0).

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Field Contents XFLAG Exclusion flag excludes the indicated Grid Point Force types from summation at the monitor point. (Default = blank (no type excluded)). If XFLAG = "S", SPC forces are excluded. If XFLAG = "M", MPC forces are excluded. If XFLAG = "A", "L", or "P", applied loads, which includes thermal loads, are excluded. If XFLAG = "D", DMIGs at the monitored point are excluded. CD The identification number of a coordinate system in which the results are output. (Integer ≥ 0; Default = Coordinate system specified by the CP field)

REMARKS: 1. Requirements for grids that are included in the monitor point: • You select a set of grids to sum forces and moments about the specified point.

• You must use only GRIDs in the GROUP definition. MONPNT3 does not process SPOINTs, EPOINTs, and fluid grid points when they are in the GROUP definition.

2. Requirements for elements that are processed at the monitor point: • When ELEMGRP is defined for any MONPNT3 bulk entry, you must define the GPFORCE=ALL case control command for all subcases, and the request must be for the SORT1 output format. You must either define GPFORCE=ALL in each subcase, or above the subcases (globally). When ELEMGRP is blank, no contributions are made from the set of elements attached to the grid. The elements attached to the grid are excluded.

3. Output for superelements that are processed at the monitor point: • For internal and partitioned superelements, MONPNT3 results can be output for the residual or downstream superelements.

• For external superelements, MONPNT3 results are only output for the residual superelement.

Note The various GROUPs and CPs defined for a MONPNT3 may not exist for all of the superelements in a model. When this occurs, the MONPNT3 is not processed for the superelement. A warning message indicates that the MONPNT3 is not processed.

4. Invalid grids or elements do not generate error or warning messages.

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5. A CP of zero (the default) references the basic coordinate system.

6. In a structure, you can apply MONPNT3 to determine the internal shear, moment, torque, and thermal loads.

Example A long and slender component is divided and all grids that reside on the division are placed in the GRIDGRP group. Based on the values of the ELEMGRP and XFLAG fields, the software outputs various internal load resultants. • ELEMGRP contains all elements connected to the GRIDGRP on the outer part of the split: o XFLAG is blank: The software calculates the internal load with the elements connected to the GRIDGRP that are not included in ELEMGRP. This produces resultants on the inside of the split and contains any loads applied to the GRIDGRP from any other source.

o XFLAG = SMAD: The software calculates the internal load with the elements listed in ELEMGRP. This produces resultants on the outer part of the split and does not contain loads applied to the GRIDGRP from any other source.

7. The software prints the results in a table titled STRUCTURAL INTEGRATED FREE BODY MONITOR POINT LOADS (MONPNT3). The total loads in this table include the thermal loads unless you set XFLAG = A.

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MONITOR

Print Selection for Monitor Data

Requests the type of monitor data to be output to the .f06 file in SOL 101 and SOL 103. FORMAT:

EXAMPLES: MONITOR(NOPNT2) = ALL

DESCRIBERS:

Describer Meaning NOPNT2 Do not include MONPNT2 results in the MONITOR point prints. (Default = Provide these prints) NOPNT3 Do not include MONPNT3 results in the MONITOR point prints. (Default = Provide these prints) ALL or YES Print all monitor point results except for the selected items. NONE or NO Do not print the monitor point results. (Default)

REMARKS: 1. The MONITOR command is required to obtain MONITOR results in the printed output.

Monitor points example

Test problem description In this test problem, the physical problem represents a beam model with a rectangular section. The beam starts at 1 meter long, fixed at one end or two ends, and at –50° C is heated to 25° C. The objective is to define an integrated load monitor point at a named element and output strain and stress, and to sum grid point forces around a specific point. Executive and case control Two subcase runs with different restraints (one end fixed and two ends fixed) that use the same model are used to investigate the effects of different supports. In both cases, the MONITOR case control command requests monitor points information. In both subcases, MONITOR requests to print all monitor results. Bulk data The key data in the Bulk Data section is as follows: • SPC cards are used to restrain the model at one or two ends.

• A thermal load of 25° C is applied at all grid points of the bar model.

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• MONPNT2 outputs EX1A (strain at end A at point C) and SX1A (bending stress at end A at the recovery location C).

• MONPNT3 sums the grid point forces at the first grid point around all six component axes in the basic coordinate system.

Results from NX Nastran

Partial output shows Monitor point tables

Note

REST. APPLIED stands for Resultant Applied Load. Each Resultant Applied Load value represents a sum of all the loads at the specified location in a specific direction.

Input file $* $* NX NASTRAN $* $* ANALYSIS TYPE: Structural $* SOLUTION TYPE: SOL 101 Linear Statics - Subcase Constraints $* SOLVER INPUT FILE: monitor-points.dat $* $* $* $* UNITS: SI-Meter (newton) $* ... LENGTH : meter $* ... TIME : sec $* ... MASS : kilogram (kg) $* ... FORCE : newton(N) $* ... TEMPERATURE : deg Celsius $* $*$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ $* $* EXECUTIVE CONTROL $*

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$*$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ $* SOL 101 TIME 60 CEND $* $*$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ $* $* CASE CONTROL $* $*$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ $* TITLE = monitor-points - Thermal Strain, Displacement, and Stress on Heated Beam ECHO = SORT $* TEMP(INIT) = 1 $* SUBCASE = 1 $* LABEL = One End Fixed SPC = 1 TEMP(LOAD) = 10 DISPLACEMENT(PRINT,PUNCH) = ALL SPCFORCES(PRINT,PUNCH) = ALL FORCE(PRINT,PUNCH,CORNER) = ALL STRESS = ALL STRAIN(PRINT,PUNCH,CORNER,VONMISES,STRCUR) = ALL ESE(PRINT,PUNCH) = ALL MONITOR = ALL $* SUBCASE = 2 $* LABEL = Both Ends Fixed SPC = 2 TEMP(LOAD) = 10 DISPLACEMENT(PRINT,PUNCH) = ALL SPCFORCES(PRINT,PUNCH) = ALL FORCE(PRINT,PUNCH,CORNER) = ALL STRESS = ALL STRAIN(PRINT,PUNCH,CORNER,VONMISES,STRCUR) = ALL ESE(PRINT,PUNCH) = ALL MONITOR = ALL $* $*$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ $* $* BULK DATA $* $*$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ $* BEGIN BULK $* $* PARAM CARDS $* PARAM XFLAG 0 PARAM AUTOSPC YES PARAM GRDPNT -1

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PARAM POST -2 PARAM POSTEXT YES $* $* GRID CARDS $* GRID 1 0 0.0 0.0 0.0 0 GRID 2 0 .100000 0.0 0.0 0 GRID 3 0 .200000 0.0 0.0 0 GRID 4 0 .300000 0.0 0.0 0 GRID 5 0 .400000 0.0 0.0 0 GRID 6 0 .500000 0.0 0.0 0 GRID 7 0 .600000 0.0 0.0 0 GRID 8 0 .700000 0.0 0.0 0 GRID 9 0 .800000 0.0 0.0 0 GRID 10 0 .900000 0.0 0.0 0 GRID 11 0 1.00000 0.0 0.0 0 $* $* ELEMENT CARDS $* CBAR 1 1 1 2 0.01.000000 0.0 CBAR 2 1 2 3 0.01.000000 0.0 CBAR 3 1 3 4 0.01.000000 0.0 CBAR 4 1 4 5 0.01.000000 0.0 CBAR 5 1 5 6 0.01.000000 0.0 CBAR 6 1 6 7 0.01.000000 0.0 CBAR 7 1 7 8 0.01.000000 0.0 CBAR 8 1 8 9 0.01.000000 0.0 CBAR 9 1 9 10 0.01.000000 0.0 CBAR 10 1 10 11 0.01.000000 0.0 $* $* MATERIAL CARDS $* $* Material: 1 name: MATERIAL PROPERTY TABLE1 MAT1 1206.80+9 .29000007820.0001.2000-5 0.0+ + 1.5000+91.5000+96.8000+7 $* $* PROPERTY CARDS $* $* $* Property: 1 name: PHYSICAL PROPERTY TABLE1 $* Fore Section: 2 name: RECTANGLE 0.1 X 0.1 PBAR 1 11.0000-28.3333-68.3333-61.4083-5 + + .0500000.0500000.0500000-.050000-.050000-.050000-.050000.0500000+ + .8333333.8333333 $* $* RESTRAINT CARDS $* SPC 1 1 123456 0.0 $* $* RESTRAINT CARDS $* SPC 2 1 123456 0.0 SPC 2 11 123456 0.0 $* $* TEMPERATURE CARDS $*

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TEMP 10 125.00000 225.00000 325.00000 TEMP 10 425.00000 525.00000 625.00000 TEMP 10 725.00000 825.00000 925.00000 TEMP 10 1025.00000 1125.00000 TEMPD 1 -50.000 $* $1.....12...... 23...... 34...... 45...... 56...... 67...... 78...... 89...... 9+ MONPNT2 LOCA testing1 STRAIN CBAR EX1A 1 STRESS CBAR SX1A 1 MONPNT3 A1 123456 1 0 0.0 0.0 0.0 0 $1.....12...... 23...... 34...... 45...... 56...... 67...... 78...... 89...... 9+ GROUP 1 GRID 1 ENDDATA

11-36 NX Nastran 12 Release Guide Chapter 12: Miscellaneous

HDF5 format output files You can now write results to output files in the open-source HDF5 format. The HDF5 format allows you to more easily access and use NX Nastran results in your own utilities. For example, an airframe business might have a proprietary failure criteria that needs to be evaluate with in-house software. To use its utility, the analyst needs to access the stress results from the NX Nastran run. For such a case, the HDF5 format offers the following advantages: • It uses a hierarchical data format that is specifically designed to handle large amounts of data.

• Application programming interfaces (API) are readily available to read HDF5 files.

The standard OP2 file, although widely recognized by many Pre/Post tools, is not ideally suited for such applications for the following reasons: • OP2 files use a serial file format, which may force the utility to read through the entire OP2 file to recognize the structure of the OP2 file.

• Although an API that reads OP2 files written by NX Nastran is supplied with your NX Nastran installation, this API may not be able to read OP2 files written by other solvers.

Note For information on the API supplied with your NX Nastran installation, see "Building and Using TABTST" in the NX Nastran 12 Installation and Operations Guide.

For NX Nastran 12, not all of the data blocks that the software writes to the OP2 file are written to the HDF5 file. The data blocks that are written to the HDF5 file are as follows:

Data block Description Table of displacement, velocity and acceleration in basic BOUGV1 coordinate system in SORT1 format CSTM Table of coordinate system transformation matrices EPT Table of bulk entry images related to element properties (1) GEOM1 Table of bulk entry images related to geometry Table of bulk entry images related to element connectivity and GEOM2 scalar points (2) IBULKOP2 Echo of bulk data input data ICASEOP2 Echo of case control input data MPT Table of bulk entry images related to material properties (3) OEE Output element energy (strain, kinetic, loss) OEF1 Table of element forces in SORT1 format

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Data block Description OES1 Table of element stresses or strains in SORT1 format OGF Table of grid point forces Table of single-point or multi-point constraint forces in SORT1 OQG1 format OSTR1 Table of total strain in SORT1 format OSTR1TH Table of thermal strain in SORT1 format OSTR1EL Table of elastic strain in SORT1 format Table of displacement, velocity and acceleration in global OUGV1 coordinate system in SORT1 format (1) Data from MATCID, NSM, NSML, NSML1, PBUSH1D, PCOMP, and PGPLSN is not supported. (2) Data from CFAST, CQUADRN, CTRIARN, and GENEL is not supported. (3) Data from MATCRP, MUMAT, NLARCL, NLCNTL, PLCYISO, RADBND, RADM, and RADMT is not supported.

The variable names in an HDF5 file match those in the data definition language (DDL) schema. To find descriptions of the variables, see the DMAP Programmer's Guide. To request that the software write the results to an HDF5 format output file in addition to the standard OP2 file, specify the following: • SYSTEM(653) = 1

• PARAM,POST,-2

Note For PARAM,POST,-2, OMACHPR=NO is the default. However, the software only writes data blocks in the current format to the HDF5 format output file, not the pre-MSC Nastran Version 69 or pre-MSC Nastran 2001 formats. Normally, you need to specify OMACHPR=YES to have the software write the data blocks in the current format when PARAM,POST,-2.

The file extension for HDF5 format output files is .hdf.

Visualization elements You can now use eight new shell and solid visualization elements to model geometry without adding physical effects such as mass, stiffness, and damping to the FE model. In earlier versions of NX Nastran, the one-dimensional PLOTEL element is the only visualization element. The new visualization elements are as follows:

Visualization Element Description PLOTEL3 Triangular visualization element with three grid points PLOTEL4 Quadrilateral visualization element with four grid points PLOTEL6 Triangular visualization element with six grid points PLOTEL8 Quadrilateral visualization element with eight grid points

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Visualization Element Description Six-sided hexahedron visualization element with eight to twenty PLOTHEX grid points Five-sided pentahedron visualization element with six to fifteen PLOTPEN grid points Five-sided pyramid visualization element with five to thirteen grid PLOTPYR points Four-sided tetrahedron visualization element with four to ten grid PLOTTET points

Typically, you use visualization elements in substructuring applications where the underlying FE mesh of the substructure is unavailable. For such situations, you can create a mesh of visualization elements from the grid points associated with the substructure. Because the mesh is a geometric representation of the substructure, you can display the analysis results across the entire model in post-processing.

As an example, consider the following application where you also use the new direct-input, frequency-dependent component capability.

Suppose you want to perform a frequency response analysis on an airframe and you want to:

• Use frequency response test results to define the dynamic stiffness of the wings.

• Use FE to model the remainder of the airframe.

• Visualize the analysis results over the entire airframe.

You can use the new direct-input, frequency-dependent component capability to define the dynamic stiffness matrix of the wings from the test results. To do so, include an FRFSTIF bulk entry for each wing. Each FRFSTIF bulk entry defines the dynamic stiffness matrix of a wing as seen by the DOF that connect the wing to the fuselage.

You can define an output transformation matrix that relates the response at other points on the wing where test data is collected to the DOF that connect the wing to the fuselage. To do so, define grid points at these locations on the wings and include an FRFOTM bulk entry for each wing. Each FRFOTM bulk entry relates the response at these grid points to the response of the DOF that connect the wing to the fuselage.

During the frequency response analysis solve, the software computes the response at the DOF that connect the wings to the fuselage. During results recovery, the software uses the response at these DOF and the FRFOTM bulk entries to calculate the response at the other grid points on the wing.

To view the response of the entire airframe, the post-processor requires a geometric representation of the wing. You can use the new visualization elements and the grid points on the wings to create meshes of the wings over which the post-processor can display results.

For more information on direct-input, frequency-dependent components, see Direct-input, frequency-dependent components.

For more information on output transformation matrices, see Output transformation matrices for frequency response analysis.

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PLOTEL3

Triangular Visualization Element

Defines the connectivity of a triangular visualization element with three grid points for use in post-processing.

FORMAT:

1 2 3 4 5 6 7 8 9 10 PLOTEL3 EID G1 G2 G3

EXAMPLE:

PLOTEL3 29 35 16 42

FIELDS:

Field Contents EID Element identification number. (Integer > 0) Gi Grid point identification numbers of connection points. (Integer > 0; All Gi must be unique)

REMARKS: 1. The element connectivity is the same as a CTRIA3 element.

2. Element identification numbers should be unique with respect to all other PLOTi bulk entries.

3. Grid point IDs G1 through G3 are mandatory.

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PLOTEL4

Quadrilateral Visualization Element

Defines the connectivity of a quadrilateral visualization element with four grid points for use in post-processing.

FORMAT:

1 2 3 4 5 6 7 8 9 10 PLOTEL4 EID G1 G2 G3 G4

EXAMPLE:

PLOTEL4 29 35 16 42 23

FIELDS:

Field Contents EID Element identification number. (Integer > 0) Gi Grid point identification numbers of connection points. (Integer > 0; All Gi must be unique)

REMARKS: 1. The element connectivity is the same as a CQUAD4 element.

2. Element identification numbers should be unique with respect to all other PLOTi bulk entries.

3. Grid point IDs G1 through G4 are mandatory.

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PLOTEL6

Triangular Visualization Element

Defines the connectivity of a triangular visualization element with three to six grid points for use in post-processing.

FORMAT:

1 2 3 4 5 6 7 8 9 10 PLOTEL6 EID G1 G2 G3 G4 G5 G6

EXAMPLE:

PLOTEL6 29 35 16 42 23 57 39

FIELDS:

Field Contents EID Element identification number. (Integer > 0) Gi Grid point identification numbers of connection points. (Integer > 0; All Gi must be unique)

REMARKS: 1. The element connectivity is the same as a CTRIA6 element.

2. Element identification numbers should be unique with respect to all other PLOTi bulk entries.

3. Grid point IDs G1 through G3 are mandatory. Grid point IDs G4 through G6 are optional.

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PLOTEL8

Quadrilateral Visualization Element

Defines the connectivity of a quadrilateral visualization element with five to eight grid points for use in post-processing.

FORMAT:

1 2 3 4 5 6 7 8 9 10 PLOTEL8 EID G1 G2 G3 G4 G5 G6 G7 G8

EXAMPLE:

PLOTEL6 29 35 16 42 23 57 39 45 48

FIELDS:

Field Contents EID Element identification number. (Integer > 0) Gi Grid point identification numbers of connection points. (Integer > 0; All Gi must be unique)

REMARKS: 1. The element connectivity is the same as a CQUAD8 element.

2. Element identification numbers should be unique with respect to all other PLOTi bulk entries.

3. Grid point IDs G1 through G4 are mandatory. Grid point IDs G5 through G8 are optional.

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PLOTHEX

Six-Sided Hexahedron Visualization Element

Defines the connectivity of a six-sided hexahedron visualization element with eight to twenty grid points for use in post-processing.

FORMAT:

1 2 3 4 5 6 7 8 9 10 PLOTHEX EID G1 G2 G3 G4 G5 G6 G7 G8 G9 G10 G11 G12 G13 G14 G15 G16 G17 G18 G19 G20

EXAMPLE:

PLOTHEX 29 35 16 42 23 57 39 44 73 65 61 47 33 64 32 49 36 51 19 12 45

FIELDS:

Field Contents EID Element identification number. (Integer > 0) Gi Grid point identification numbers of connection points. (Integer > 0; All Gi must be unique)

REMARKS: 1. The element connectivity is the same as a CHEXA element.

2. Element identification numbers should be unique with respect to all other PLOTi bulk entries.

3. Grid point IDs G1 through G8 are mandatory. Grid point IDs G9 through G20 are optional.

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PLOTPEN

Five-Sided Pentahedron Visualization Element

Defines the connectivity of a five-sided pentahedron visualization element with six to fifteen grid points for use in post-processing.

FORMAT:

1 2 3 4 5 6 7 8 9 10 PLOTPEN EID G1 G2 G3 G4 G5 G6 G7 G8 G9 G10 G11 G12 G13 G14 G15

EXAMPLE:

PLOTPEN 29 35 16 42 23 57 39 44 73 65 61 47 33 64 32 49

FIELDS:

Field Contents EID Element identification number. (Integer > 0) Gi Grid point identification numbers of connection points. (Integer > 0; All Gi must be unique)

REMARKS: 1. The element connectivity is the same as a CPENTA element.

2. Element identification numbers should be unique with respect to all other PLOTi bulk entries.

3. Grid point IDs G1 through G6 are mandatory. Grid point IDs G7 through G15 are optional.

NX Nastran 12 Release Guide 12-9 ChCaphtaeprte1r2:12M: isceMlliasnceollaunseous

PLOTPYR

Five-Sided Pyramid Visualization Element

Defines the connectivity of a five-sided pyramid visualization element with five to thirteen grid points for use in post-processing.

FORMAT:

1 2 3 4 5 6 7 8 9 10 PLOTPEN EID G1 G2 G3 G4 G5 G6 G7 G8 G9 G10 G11 G12 G13

EXAMPLE:

PLOTPEN 29 35 16 42 23 57 39 44 73 65 61 47 33 64

FIELDS:

Field Contents EID Element identification number. (Integer > 0) Gi Grid point identification numbers of connection points. (Integer > 0; All Gi must be unique)

REMARKS: 1. The element connectivity is the same as a CPYRAM element.

2. Element identification numbers should be unique with respect to all other PLOTi bulk entries.

3. Grid point IDs G1 through G5 are mandatory. Grid point IDs G6 through G13 are optional.

12-10 NX Nastran 12 Release Guide Miscellaneous

PLOTTET

Four-Sided Tetrahedron Visualization Element

Defines the connectivity of a four-sided tetrahedron visualization element with four to ten grid points for use in post-processing. FORMAT:

1 2 3 4 5 6 7 8 9 10 PLOTTET EID G1 G2 G3 G4 G5 G6 G7 G8 G9 G10

EXAMPLE:

PLOTTET 29 35 16 42 23 57 39 44 73 65 61

FIELDS:

Field Contents EID Element identification number. (Integer > 0) Gi Grid point identification numbers of connection points. (Integer > 0; All Gi must be unique)

REMARKS: 1. The element connectivity is the same as a CTETRA element.

2. Element identification numbers should be unique with respect to all other PLOTi bulk entries.

3. Grid point IDs G1 through G4 are mandatory. Grid point IDs G5 through G10 are optional.

Separate mechanical and thermal strain When you use the STRAIN command in the linear solutions 101, 103, 105, 107-112, you are requesting the total strain which includes both mechanical and thermal strain. You can now request the mechanical and thermal strains separately for the shell and solid elements listed below. • ELSTRN case control command - requests the mechanical strain only.

• THSTRN case control command - requests the thermal strain only.

• STRAIN case control command - requests the total strain which includes both the mechanical and thermal strain.

ELSTRN and THSTRN element support for linear solutions

NX Nastran 12 Release Guide 12-11 ChCaphtaeprte1r2:12M: isceMlliasnceollaunseous

• For SOL 101, ELSTRN and THSTRN are supported for the shell elements CQUAD4, CTRIA3 , CQUAD8, CTRIA6, CTRIAR, and CQUADR that reference a PSHELL, PCOMP or PCOMPG entry, and the 3D solid elements CTETRA, CHEXA, CPENTA and CPYRAM that reference a PSOLID entry.

• For a static subcase in SOLs 103, 105, 107-112, ELSTRN and THSTRN are supported for the shell elements CQUAD4, CTRIA3 , CQUAD8, CTRIA6, CTRIAR, and CQUADR that reference a PSHELL entry, and the 3D solid elements CTETRA, CHEXA, CPENTA and CPYRAM that reference a PSOLID entry. ELSTRN and THSTRN are ignored in a non-static subcase.

Modal stress calculation when TEMPERATURE(LOAD) is specified

In SOL 103, 110, 111, and 112 when TEMPERATURE(LOAD) is specified, the software now calculates modal stresses from the total strain for all elements. Thus, Remark 10 on the TEMPERATURE case control command is removed. In earlier versions, the software calculates modal stresses from the elastic strain for CBEAM, CPLSTSi, CPLSTNi, CPYRAM, and, when used to model a composite solid, CHEXA and CPENTA elements.

P-elements in SOL 200

Beginning in NX Nastran 12, the p-element method has been removed from SOL 200. Attempting to run SOL 200 with p-elements will now cause a fatal error. The p-element method is still available in the software, except for SOL 200. The p-element documentation was removed in NX Nastran 11.

12-12 NX Nastran 12 Release Guide Chapter 13: Documentation changes

Removing documentation for legacy acoustic absorber and barrier elements

The following bulk entries are removed from the documentation: • CHACAB acoustic absorber element

• CHACBR acoustic barrier element

• PACABS acoustic absorber property

• PACBAR acoustic barrier property

Although these bulk entries are still supported in the software, you cannot use them with the new acoustics implementation that began in NX Nastran 11.

Removing documentation for the legacy VECTOR case control command

The VECTOR case control command is now removed from the documentation. If you run a legacy input file that contains the VECTOR case control command, the software treats the VECTOR case control command specification the same as it treats an equivalent DISPLACEMENT case control command specification. For example, suppose a legacy input file contains the following VECTOR specification: VECTOR(SORT2,PUNCH,REAL)=ALL When you run the legacy input file in NX Nastran 12, the software treats the VECTOR specification the same as the following DISPLACEMENT specification: DISPLACEMENT(SORT2,PUNCH,REAL)=ALL

NX Nastran 12 Release Guide 13-1

Chapter 14: Upward compatibility

Updated data blocks

CASECC

Updated Record - REPEAT

Word Name Type Description

......

309 GCTOPG I Grid contributions TOPG (GRDCON)

......

312 GCGRID I Grid contributions GRID (GRDCON)

......

421 PRSSET I Pressure output set (PRESSURE)

422 PRSMEDIA I Pressure output media (PRESSURE)

423 PRSFMT I Pressure output format (PRESSURE)

424 FRFIN I FRFIN set number

425 PRSTOTAL I Pressure output: total bit(0)=0, scatter bit(0)=0

......

433 ACTLDSET I Acoustic load set (ALOAD)

......

509 ATVFSID I SID of ATVF

510 ATVUNIT I ATVOUT OP2 unit

511 ATVSETNO I ATVOUT microphone set identification number

512 ATVFLAGS I ATVOUT bits for flags = 1 if ATVOUT specified

513 ACPANEL I PANEL in ACPOWER: 0 for none, -1 for all, >0 for panel identification number

......

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Word Name Type Description

561 INITSSET I Initial stress/strain: INITS=n where n=0 for none, n>0 for INITS or INITADD bulk entry SID, n<0 for invalid value

......

573 MPINTSET I Microphone point intensity, output set (ACINTENSITY)

574 MPINTDIA I Microphone point intensity, output media (ACINTENSITY)

575 MPINTFMT I Microphone point intensity, output format (ACINTENSITY)

576 OTMFORC I Output set (OTMFORC)

577 OTMFORCM I Output media (OTMFORC)

578 OTMFORCF I Output format (OTMFORC)

......

599 GRDCON I Grid contributions set

600 GCMEDIA I Grid contributions media

601 GCFMT I Grid contributions format

602 GCFORM I Grid contributions FORM

603 GCSOL I Grid contributions SOLUTION

604 INITSOFF I Initial strain offset for balanced initial stress/strain: INITS(OFFSET)=n where n=0 for none, n>0 for INITS or INITADD bulk entry SID, n<0 for invalid value

605 INPWRGST I Incident acoustic power, GROUP output set (INPOWER)

606 INPWRFST I Incident acoustic power, FACES output set (INPOWER)

607 INPWRDIA I Incident acoustic power, output media (INPOWER)

608 INPWRFMT I Incident acoustic power, output format (INPOWER)

14-2 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

609 TRPWRGST I Transmitted acoustic power, GROUP output set (TRPOWER)

610 TRPWRAST I Transmitted acoustic power, AMLREG output set (TRPOWER)

611 TRPWRDIA I Transmitted acoustic power, output media (TRPOWER)

612 TRPWRFMT I Transmitted acoustic power, output format (TRPOWER)

613 TRLOSFLG I Acoustic transmission loss, YES/NO flag (1=yes, 0=no) (TRLOSS)

614 TRLOSDIA I Acoustic transmission loss, output media (TRLOSS)

615 TRLOSFMT I Acoustic transmission loss, output format (TRLOSS)

616 NLARCST I SOL 401 nonlinear arc-length solution flag set IF (NLARCL)

617 IMPRFST I SOL 401 imperfection set flag, SET IF (IMPERF)

618 MONPNT I MONPNTn output bit flag(s)

619 FRFOUT I Frequency-dependent component output flag (FRFOUT)

620 FRFOPT I Frequency-dependent component output options (FRFOUT)

621 FRFSEID I SEID for frequency-dependent component output (FRFOUT)

622 FRFOP2 I Unit for frequency-dependent component output (FRFOUT)

623 UNDEF(577) None

LCC LSEM(C) I Number of symmetry subcase coefficients from item SYMFLG

The value for LCC is set by word 166

LCC+1 COEF RS Symmetry subcase coefficients (SUBSEQ or SYMSEQ)

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Word Name Type Description

Word LCC+1 repeats LSEM times

LCC+2 SETID I Set identification number

LCC+3 SETLEN(C) I Length of this set

LCC+4 SETMEM I Set member identification number

Word LCC+4 repeats SETLEN times

Words LCC+2 through LCC+4 repeat NSETS times

LCC+5 PARA CHAR4 Hard-coded to "PARA"

LCC+6 PARLEN(C) I Length of this parameter value specification

LCC+7 CHTYPE(C) I Character type flag: 3 means character, 2 otherwise

LCC+8 PARAM(2) CHAR4 Hard-coded to "PARA" and "M "

LCC+10 PNAME(2) CHAR4 Name of parameter

PARLEN =8 Length

LCC+12 INTEGER I Integer value

PARLEN =9 Real-double parameter value

LCC+12 TYPE I Real type - hard-coded to -4

LCC+13 REAL RD Real-double value

PARLEN =10 Complex-single parameter value

LCC+12 RTYPE I Real part type - hard-coded to -2

LCC+13 REAL RS Real part value

LCC+14 ITYPE I Imaginary part type - hard-coded to -2

LCC+15 IMAG RS Imaginary part value

PARLEN =12 Complex-double parameter value

LCC+12 RTYPE I Real part type - hard-coded to -4

LCC+13 REAL RD Real part value

LCC+14 ITYPE I Imaginary part type - hard-coded to -4

LCC+15 IMAG RD Imaginary part value

14-4 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

End PARLEN

Words LCC+5 through max repeat until NANQ occurs

Words LCC+5 through LCC+15 repeat until End of Record

Updated Record - NOTES

Note 13 is removed.

CONTACT

New Record – ATVFS(6571,65,657)

Word Name Type Description

1 OPTION I 0 = set, 1 = ALL

2 BID I BSURFS identification number

3 -1 I Delimiter

New Record – ACTRAD(5907,60,654)

Word Name Type Description

1 SID I Identification number

2 PID I Identification number of PACTRAD bulk entry

3 BIDS I Source BSURFS bulk entry identification number

4 BIDT I Target BSURFS bulk entry identification number

5 AREA RS Area correction factor

6 SDIST RS Search distance

7 ANGLE RS Tolerance angle

8 UNDEF(3) None

New Record – BCTPAR2(6621,66,662)

Same as BCTPARA(7610,76,593)

NX Nastran 12 Release Guide 14-5 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

New Record – PACTRAD(6581,61,658)

Word Name Type Description

1 PID I Parameter identification number

2 METHOD I Method to define the parameters: 0 for six, 1 for four

3 A1R RS Real part of parameter 1

4 TIDA1R I TABLEDi ID of real part of parameter 1

5 A1I RS Imaginary part of parameter 1

6 TIDA1I RS TABLEDi ID of imaginary part of parameter 1

7 A2R RS Real part of parameter 2

8 TIDA2R I TABLEDi ID of real part of parameter 2

9 A2I RS Imaginary part of parameter 2

10 TIDA2I RS TABLEDi ID of imaginary part of parameter 2

11 A3R RS Real part of parameter 3

12 TIDA3R I TABLEDi ID of real part of parameter 3

13 A3I RS Imaginary part of parameter 3

14 TIDA3I RS TABLEDi ID of imaginary part of parameter 3

15 A4R RS Real part of parameter 4

16 TIDA4R I TABLEDi ID of real part of parameter 4

17 A4I RS Imaginary part of parameter 4

18 TIDA4I RS TABLEDi ID of imaginary part of parameter 4

19 A5R RS Real part of parameter 5

20 TIDA5R I TABLEDi ID of real part of parameter 5

21 A5I RS Imaginary part of parameter 5

22 TIDA5I RS TABLEDi ID of imaginary part of parameter 5

23 A6R RS Real part of parameter 6

24 TIDA6R I TABLEDi ID of real part of parameter 6

25 A6I RS Imaginary part of parameter 6

26 TIDA6I RS TABLEDi ID of imaginary part of parameter 6

14-6 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

27 UNDEF(4) None

DIT

New Record - TABLED6(1605,16,117)

Word Name Type Description

1 ID I Table identification number

2 TYPE I Type of table data: =0 for real/imaginary; =1 for magnitude/phase

3 FLAG I Extrapolation on/off flag

4 UNDEF(5) None

9 X RS X value (frequency in Hz)

10 YR RS Y real or magnitude value

11 YI RS Y imaginary or phase value (phase in degrees)

Words 9 through 11 repeat until (-1,-1,-1) occurs

New Record – TABLEM5(505,5,644)

Word Name Type Description

1 ID I Table identification number

2 UNDEF(2) None

4 FLAG I Extrapolation on/off flag

5 UNDEF(4) None

9 X RS X tabular value

10 Y RS Y tabular value

Words 9 through 10 repeat until (-1,-1) occurs

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DSCMCOL

New RTYPE=17

Word Name Type Description

RTYPE =17 Compliance

4 UNDEF(2) None

6 SUBCASE I Subcase identification number

7 UNDEF(3) None

DYNAMIC

New Record – ACADAPT(9407,94,659) Adaptation rule for FEM Adaptive Order solution

Word Name Type Description

1 RULE(2) CHAR4 STANDARD, COARSE, or FINE

3 E1 I Element identification number (for future use)

Word 3 repeats until -1 occurs

New Record – ACNVEL(5507,55,650) Acoustic normal velocity on surface

Word Name Type Description

1 SID I Load set identification number

2 FORM I Complex format: 0 for real/imaginary, 1 for magnitude/phase

3 A RS Scale factor

4 TRTM RS Real part or magnitude

5 TIDTRTM I TABLEDi bulk entry identification number for real part or magnitude

6 TITP RS Imaginary part or phase (in degrees)

7 TIDTITP I TABLEDi bulk entry identification number for imaginary part or phase (in degrees)

8 BID I BSURF identification number

14-8 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

9 UNDEF(3) None

New Record – ACORDER(9607,96,660)

Adaptivity order for FEM Adaptive Order solution

Word Name Type Description

1 ORDER(2) CHAR4 Maximum or minimum

3 NUMBER I Order number

4 E1 I Element identification number (for future use)

Word 4 repeats until -1 occurs

New Record – ACPLNW(5807,59,653)

Acoustic plane wave source

Word Name Type Description

1 SID I Load set identification number

2 FORM I Complex format: 0 for real/imaginary, 1 for magnitude/phase

3 A1 RS Scale factor 1

4 TRTM RS Real part or magnitude of plane wave

5 TIDTRTM I TABLEDi bulk entry identification number for real part or magnitude of plane wave

6 TITP RS Imaginary part or phase (in degrees) of plane wave

7 TIDTITP I TABLEDi bulk entry identification number for imaginary part or phase (in degrees) of plane wave

8 CID1 I Coordinate system identification number for location of plane wave source

9 X RS X-coordinate of plane wave source

10 Y RS Y-coordinate of plane wave source

11 Z RS Z-coordinate of plane wave source

12 CID2 I Coordinate system identification number for direction of plane wave

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Word Name Type Description

13 NX RS Direction cosine between plane wave direction and X-axis

14 NY RS Direction cosine between plane wave direction and Y-axis

15 NZ RS Direction cosine between plane wave direction and Z-axis

16 UNDEF(3) None

New Record – ACPOLE1(5607,56,651)

Acoustic monopole source

Word Name Type Description

1 SID I Load set identification number

2 TYPE I 0 for amplitude, 1 for power

3 FORM I Complex format: 0 for real/imaginary, 1 for magnitude/phase

4 A RS Scale factor

5 TRTM RS Real part or magnitude of monopole source

6 TIDTRTM I TABLEDi bulk entry identification number for real part or magnitude of monopole source

7 TITP RS Imaginary part or phase (in degrees) of monopole source

8 TIDTITP I TABLEDi bulk entry identification number for imaginary part or phase (in degrees) of monopole source

9 CID I Coordinate system identification number for monopole source location

10 X RS X-direction coordinate of monopole source

11 Y RS Y-direction coordinate of monopole source

12 Z RS Z-direction coordinate of monopole source

13 UNDEF(3) None

14-10 NX Nastran 12 Release Guide Upward compatibility

New Record – ACPOLE2(5707,58,652)

Acoustic dipole source

Word Name Type Description

1 SID I Load set identification number

2 FORM I Complex format: 0 for real/imaginary, 1 for magnitude/phase

3 CID1 I Coordinate system identification number for dipole source location

4 X RS X-direction coordinate of dipole source

5 Y RS Y-direction coordinate of dipole source

6 Z RS Z-direction coordinate of dipole source

7 CID2 I Coordinate system identification number for dipole moment

8 A1 RS Scale factor 1

9 TRTM1 RS Real part or magnitude of dipole moment in X-direction

10 TIDTRTM1 I TABLEDi bulk entry identification number for real part or magnitude of dipole moment in X-direction

11 TITP1 RS Imaginary part or phase (in degrees) of dipole moment in X-direction

12 TIDTITP1 I TABLEDi bulk entry identification number for imaginary part or phase (in degrees) of dipole moment in X-direction

13 A2 RS Scale factor 2

14 TRTM2 RS Real part or magnitude of dipole moment in Y-direction

15 TIDTRTM2 I TABLEDi bulk entry identification number for real part or magnitude of dipole moment in Y-direction

16 TITP2 RS Imaginary part or phase (in degrees) of dipole moment in Y-direction

17 TIDTITP2 I TABLEDi bulk entry identification number for imaginary part or phase (in degrees) of dipole moment in Y-direction

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Word Name Type Description

18 A3 RS Scale factor 3

19 TRTM3 RS Real part or magnitude of dipole moment in Z-direction

20 TIDTRTM3 I TABLEDi bulk entry identification number for real part or magnitude of dipole moment in Z-direction

21 TITP3 RS Imaginary part or phase (in degrees) of dipole moment in Z-direction

22 TIDTITP3 I TABLEDi bulk entry identification number for imaginary part or phase (in degrees) of dipole moment in Z-direction

23 UNDEF(3) None

New Record – ALOAD(5407,54,649)

Combination of acoustic loads

Word Name Type Description

1 SID I Load set identification number

2 UNDEF(3) None

5 LI I Load set identification number i

Word 5 repeats until -1 occurs

New Record – FRFFLEX(2601,26,58)

Word Name Type Description

1 ID I Identification number for FRF component

2 IDUM I Dummy word (always 0)

3 TYPE I Data type: =1 for displacement per unit force; =2 for velocity per unit force; =3 for acceleration per unit force

4 SYMFLG I Symmetry flag: =0 for symmetric; =1 for unsymmetric

5 LSCALE RS Length scaling factor

6 FSCALE RS Force scaling factor

14-12 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

7 PSCALE RS Pressure scaling factor

8 QSCALE RS Acoustic source strength scaling factor

9 UNDEF(8) None

17 GJ I Grid identification number of excited location (column)

18 CJ I Component (0-6) of excited location (column)

19 GI I Grid identification number of response location (row)

20 CI I Component (0-6) of response location (row)

21 TIDI I Identification number of TABLED6 for dynamic flexibility value

Words 19 through 21 repeat for each row until (-1,-1) occurs

Words 17 and 18 along with 19 through 21 repeat for each column until (-1,-1) occurs

New Record – FRFOMAP(2807,28,79)

Word Name Type Description

1 ID I Identification number for FRF component

2 UNDEF(7) None

9 TYPE I Output data type: 1=displacement, 2=velocity, 3=acceleration

10 GI I Grid identification number of response location (row)

11 CI I Component (0-6) of response location (row)

Words 10 and 11 repeat for each response location i until (-1,-1) occurs

Words 9 through 11 repeat for each response type until (-1,-1) occurs

New Record – FRFOTM(2701,27,62 )

Word Name Type Description

1 ID I Identification number for FRF component

2 IDUM I Dummy word (always 0)

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Word Name Type Description

3 LSCALE RS Length scaling factor

4 FSCALE RS Force scaling factor

5 PSCALE RS Pressure scaling factor

6 QSCALE RS Acoustic source strength scaling factor

7 UNDEF(2) None

9 GIN I Grid identification number of input location

10 CIN I Component (0-6) of input location

11 TYPEIN I Input type: =0 for force/moment; =1 for displacement; =2 for velocity; =3 for acceleration

12 UNDEF(4) None

16 GOUT I Grid identification number of output i

17 COUT I Component (0-6) of output i

18 TIDI I Identification number of TABLED6 for dynamic/flexibility value

Words 16 through 18 repeat for each output i until (-1,-1) occurs

Words 9 through 15 along with 16 through 18 repeat for each input location until (-1,-1) occurs

New Record – FRFSTIF(2501,25,57)

Word Name Type Description

1 ID I Identification number for FRF component

2 IDUM I Dummy word (always 0)

3 TYPE I Data type: =1 for force per unit displacement; =2 for force per unit velocity; =3 for force per unit acceleration

4 SYMFLG I Symmetry flag: =0 for symmetric; =1 for unsymmetric

5 LSCALE RS Length scaling factor

6 FSCALE RS Force scaling factor

7 PSCALE RS Pressure scaling factor

14-14 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

8 QSCALE RS Acoustic source strength scaling factor

9 UNDEF(8) None

17 GJ I Grid identification number of excited location (column)

18 CJ I Component (0-6) of excited location (column)

19 GI I Grid identification number of response location (row)

20 CI I Component (0-6) of response location (row)

21 TIDI I Identification number of TABLED6 for dynamic stiffness value

Words 19 and 21 repeat for each row until (-1,-1) occurs

Words 17 and 18 along with 19 through 21 repeat for each column until (-1,-1) occurs

New Record – TLOAD3(7307,73,647)

Word Name Type Description

1 SID I Load set identification number

2 EXCITID I SID of FORCDST entry

3 DELAYR RS Constant value for tau if DELAYI=0

4 TIDF(3) I Identification numbers of TABLEDi entries for three force components: F(t)

7 TIDM(3) I Identification numbers of TABLEDi entries for three moment components: M(t)

EDOM

Updated Record – DRESP1(3806,38,359)

Word Name Type Description

......

FLAG = 1 WEIGHT

5 UNDEF(2) None

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Word Name Type Description

7 REGION I Region identifier for constraint screening

8 ATTA I Response attribute (-10 for DWEIGHT which is the topology optimization design weight

9 ATTB I Response attribute

10 MONE I Entry is -1

FLAG = 2 VOLUME

......

FLAG = 17 Compliance

5 UNDEF(2) None

7 UNDEF I Reserved for SEID for compliance DRESP1

8 UNDEF(2) None

10 MONE I Entry is -1

FLAG = 19 ERP

......

New Record – DMNCON(6903,69,637)

Word Name Type Description

1 ID I Unique entry identifier

2 GID I GROUP identification number

3 IOPTION I Number of element layers to consider or for CYCLIC_SYMMETRY, REPREF=1 indicates repeated sector; 2 indicates reflected sector

4 FLAG I

FLAG = 1 Type of constraint = PLANE_SYMMETRY

5 X RS X axis of point on plane

6 Y RS Y axis of point on plane

7 Z RS Z axis of point on plane

14-16 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

8 N1 RS X component of vector normal to plane

9 N2 RS Y component of vector normal to plane

10 N3 RS Z component of vector normal to plane

11 UNDEF(5) None

FLAG = 2 Type of constraint = CYCLIC_SYMMETRY

5 X RS X component of point on axis

6 Y RS Y component of point on axis

7 Z RS Z component of point on axis

8 N1 RS X component of vector defining the rotational axis

9 N2 RS Y component of vector defining the rotational axis

10 N3 RS Z component of vector defining the rotational axis

11 M1 RS X component of vector defining symmetry plane

12 M2 RS Y component of vector defining symmetry plane

13 M3 RS Z component of vector defining symmetry plane

14 NSECT I Number of sectors

15 UNDEF(5) None

FLAG = 3 Type of constraint = EXTRUSION

5 N1 RS X component of vector to define extrusion

6 N2 RS Y component of vector to define extrusion

7 N3 RS Z component of vector to define extrusion

8 UNDEF(5) None

FLAG = 4 Type of constraint = CASTING

5 X RS X component of point on casting plane

6 Y RS Y component of point on casting plane

7 Z RS Z component of point on casting plane

8 N1 RS X component of a vector normal to the casting plane

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Word Name Type Description

9 N2 RS Y component of a vector normal to the casting plane

10 N3 RS Z component of a vector normal to the casting plane

11 D11 RS X component of a vector which defines the mold removal direction 1 of casting

12 D12 RS Y component of a vector which defines the mold removal direction 1 of casting

13 D13 RS Z component of a vector which defines the mold removal direction 1 of casting

14 D21 RS X component of a vector which defines the mold removal direction 2 of casting

15 D22 RS Y component of a vector which defines the mold removal direction 2 of casting

16 D23 RS Z component of a vector which defines the mold removal direction 2 of casting

17 UNDEF(5) None

FLAG = 5 Type of constraint = MAX_SIZE

5 MSIZE RS Maximum size

6 UNDEF(5) None

FLAG = 6 Type of constraint = MIN_SIZE

5 MSIZE RS Minimum size

6 UNDEF(5) None

FLAG = 7 Type of constraint = ADDITIVE

5 ANGLE RS Maximum angle measured from the vector N

6 MIND RS Minimum allowed dimension

7 X RS X coordinate of point on base plate

8 Y RS Y coordinate of point on base plate

9 Z RS Z coordinate of point on base plate

14-18 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

10 N1 RS X component of a vector normal to the casting plate in the direction of material addition

11 N2 RS Y component of a vector normal to the casting plate in the direction of material addition

12 N3 RS Z component of a vector normal to the casting plate in the direction of material addition

13 UNDEF(5) None

FLAG = 8 Type of constraint = CHECKERBOARDING

5 RADIUS RS Minimum radius to be considered

6 UNDEF(5) None

New Record – DMRLAW(7102,71,645)

Word Name Type Description

1 ID I Material relation law identification number

2 FLAG I

FLAG = -1 Lattice octet cell law

3 PARAM I Equation parameter, currently unused

FLAG = -2 Lattice cubic cell law

3 PARAM I Equation parameter, currently unused

FLAG = -3 Lattice BCC cell law

3 PARAM I Equation parameter, currently unused

FLAG = -4 Lattice FCC cell law

3 PARAM I Equation parameter, currently unused

FLAG = -5 Lattice octahedral cell law

3 PARAM I Equation parameter, currently unused

FLAG = -6 Lattice BCC+cubic cell law

3 PARAM I Equation parameter, currently unused

FLAG = -7 Lattice FCC+cubic cell law

NX Nastran 12 Release Guide 14-19 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

3 PARAM I Equation parameter, currently unused

FLAG = -8 Lattice BCC+FCC cell law

3 PARAM I Equation parameter, currently unused

FLAG = -9 Lattice BCC+FCC+cubic cell law

3 PARAM I Equation parameter, currently unused

FLAG = -1000 SIMP penalty exponent

3 PARAM RS SIMP penalty exponent

FLAG = -1001 RAMP penalty law

3 PARAM RS RAMP penalty exponent

FLAG = 0 LINEAR penalty law

3 PARAM I Equation parameter, currently unused

4 RESERV I Reserved for future use

New Record – DVTREL1(6803,68,636)

Word Name Type Description

1 ID I Identification number

2 LABEL(2) CHAR4 Label

4 GID I Referenced GROUP bulk entry identification number

5 STATE I 0=ACTIVE, 1=FROZEN

6 DSVFLG I Flag normally to be added by way of the punch file bulk output

7 UNDEF(3) None

10 DVID I Blank or identification number for the 1st auto-generated DESVAR entry

11 COEF RS Coefficient in the expression P=COEF*DV (currently inactive)

12 UNDEF(6) None

14-20 NX Nastran 12 Release Guide Upward compatibility

EDT

New Record – MONPNT2(1247,12,667)

Word Name Type Description

1 NAME(2) CHAR4 Character string identifying the monitor point

3 LABEL(14) CHAR4 Character string identifying and labeling the monitor point

17 TABLE(2) CHAR4 Stress, strain, or force

19 ELTYP(2) CHAR4 Element type

21 ITEM(2) CHAR4 NDDL item

23 EID I Element identification number

Words 17 thru 23 repeat until -1 occurs

Words 1 thru 23 repeat until (-2,-2) occurs

New Record – MONPNT3(1448,14,668)

Word Name Type Description

1 NAME(2) CHAR4 Parameter name

3 LABEL(14) CHAR4 Parameter name

17 AXES I Component axes about which to sum

18 GSET1 I Grid set group

19 ESET2 I Element set group

20 CID I Input coordinate system

21 X RS X-coordinate

22 Y RS Y-coordinate

23 Z RS Z-coordinate

24 XFLAG(2) CHAR4 Exclude flag

26 CD I Output coordinate system

NX Nastran 12 Release Guide 14-21 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

ELRSCALV

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach Code

2 TCODE(C) I Table code

3 DATCOD I Modal contribution code: 1/11=abs st/fl, 2/12=norm st/fl

4 SUBCASE I Subcase identification number

TCODE,1 =1 Sort 1

ACODE,4 =01 Statics (static and modal results are both designated as static)

5 LSDVMN I Load set number (always 1)

6 UNDEF(2 ) None

End TCODE,1

8 RCODE I Random code identification number (always 0)

9 FCODE I Format code (always 1)

10 NUMWDE I Number of words per entry in DATA record (always 2)

11 UNDEF(2) None

13 ACFLG(C) I Acoustic pressure flag (always 0)

14 UNDEF(9) None

23 THERMAL I 1 for heat transfer, 0 otherwise

24 UNDEF(27)

51 TITLE(32) CHAR4 Title “Topology Optimization”

83 SUBTITL(32) CHAR4 Subtitle “NAMEKEY Normalized Material Density”

115 LABEL(32) CHAR4 Label

14-22 NX Nastran 12 Release Guide Upward compatibility

EPT

Updated RECORDS – NSM(3201,32,991), NSM1(3301,33,992), NSML(3501,35,994), NSML1(3701,37,995)

Word Name Type Description

1 SID I Set identification number

2 PROP CHAR4 Set of properties

3 TYPE CHAR4 Set of elements

......

New RECORD – PAABSF1(6551,71,655)

Defines the properties of a frequency-dependent acoustic impedance/admittance

Word Name Type Description

1 PID I Property identification number

2 PTYPE I Property type: 0 for impedance, 1 for admittance

3 FORM I Complex format: 0 for real/imaginary, 1 for magnitude/phase (in degrees)

4 ZR RS Real part/magnitude of impedance/admittance

5 TIDZR I TABLEDi bulk entry identification number for ZR

6 ZI RS Imaginary part/phase (in degrees) of impedance/admittance

7 TIDZI I TABLEDi bulk entry identification number for ZI

8 UNDEF(3) None

New RECORD – PCOMPG1(15106,151,953)

Word Name Type Description

1 PID I Property identification number

2 Z0 RS Distance from the reference plane to the bottom surface

3 NSM RS Nonstructural mass per unit area

4 SB RS Allowable shear stress of the bonding material

NX Nastran 12 Release Guide 14-23 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

5 UNDEF None

6 TREF RS Reference temperature

7 GE RS Damping coefficient

8 UNDEF None

9 GPLYIDi I Global ply identification number

10 MID I Material identification number

11 T RS Thicknesses of the ply

12 THETA RS Orientation angle of the longitudinal direction of the ply

13 FT I Failure theory

14 SOUT I Stress or strain output request of the ply

15 UNDEF None

Words 9 through 15 repeat until (-1,-1,-1,-1,-1,-1,-1,-1) occurs

New RECORD – PSHELL1(8601,86,954)

Word Name Type Description

1 PID I Property identification number

2 MID1 I Material identification number for the membrane

3 T RS Default membrane thickness for Ti on the connection entry

4 MID2 I Material identification number for bending

5 INTEG I Integration number through the thickness

6 UNDEF None

7 MID4 I Material identification number for membrane-bending coupling

8 NSM RS Nonstructural mass per unit area

9 UNDEF(3) None

14-24 NX Nastran 12 Release Guide Upward compatibility

EPT705

New RECORD – PCOMPG1(15106,151,953)

Word Name Type Description

1 PID I Property identification number

2 Z0 RS Distance from the reference plane to the bottom surface

3 NSM RS Nonstructural mass per unit area

4 SB RS Allowable shear stress of the bonding material

5 UNDEF None

6 TREF RS Reference temperature

7 GE RS Damping coefficient

8 UNDEF None

9 GPLYIDi I Global ply identification number

10 MID I Material identification number

11 T RS Thicknesses of the ply

12 THETA RS Orientation angle of the longitudinal direction of the ply

13 FT I Failure theory

14 SOUT I Stress or strain output request of the ply

15 UNDEF None

Words 9 through 15 repeat N times

New RECORD – PSHELL1(8601,86,954)

Word Name Type Description

1 PID I Property identification number

2 MID1 I Material identification number for the membrane

3 T RS Default membrane thickness for Ti on the connection entry

4 MID2 I Material identification number for bending

NX Nastran 12 Release Guide 14-25 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

5 INTEG I Integration number through the thickness

6 UNDEF None

7 MID4 I Material identification number for membrane-bending coupling

8 NSM RS Nonstructural mass per unit area

9 UNDEF(3) None

GEOM1

New Record – ATVBULK(6591,65,659)

Word Name Type Description

1 UNIT I FORTRAN unit identification number for ATV OP2 file

2 EOFFSET I Element identification number offset

3 GOFFSET I Grid identification number offset

4 POFFSET I Property identification number offset

5 UNDEF(6) None

New Record – IMPERF(1209,96,665)

Word Name Type Description

1 ID I Imperfection identification number

2 CP I Imperfection coordinate system identification number

3 GID I Grid point identification number

4 X1 RX Imperfection at the point in coordinate 1 of CP

5 X2 RX Imperfection at the point in coordinate 2 of CP

6 X3 RX Imperfection at the point in coordinate 3 of CP

Words 3 through 6 repeat until (-1,-1) occurs

14-26 NX Nastran 12 Release Guide Upward compatibility

New Record – IMPRADD(1208,84,664)

Word Name Type Description

1 SID I Imperfection set identification number

2 S RS Overall scale factor

3 SI RS Scale factor i

4 LI I Imperfection set identification number

Words 3 and 4 repeat until (-1,-1) occurs

Removed Records CSUPER1(5701,57,323) CSUPUP(5801,58,324) GMCORD(6401,64,402) GMCURV(6601,66,392)

GEOM2

New RECORD – ACFACE3(15200,152,9912)

Word Name Type Description

1 EID I Element identification number

2 G(3) I Grid point identification numbers of connection points

3 UNDEF(2) None

New RECORD – ACFACE4(15500,155,9913)

Word Name Type Description

1 EID I Element identification number

2 G(4) I Grid point identification numbers of connection points

3 UNDEF(2) None

New RECORD – ACFACE6(15600,156,9914)

Word Name Type Description

1 EID I Element identification number

NX Nastran 12 Release Guide 14-27 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

2 G(6) I Grid point identification numbers of connection points

3 UNDEF(2) None

New RECORD – ACFACE8(15700,157,9915)

Word Name Type Description

1 EID I Element identification number

2 G(8) I Grid point identification numbers of connection points

3 UNDEF(2) None

New RECORD – CBUSH1DNL(5609,60,9899)

Word Name Type Description

1 EID I Element identification number

2 PID I Property identification number

3 G(2) I Grid point identification numbers

5 CID I Coordinate system identification number

6 UNDEF(3 ) None

New RECORD – CELAS1NL(6010,53,9900)

Same as record CELAS1 description.

New RECORD – CELAS2NL(7010,20,9898)

Same as record CELAS2 description.

New RECORD – CQUAD8L(3302,33,1694)

Same as record CQUAD8 description.

New RECORD – CQUAD8N(15901,159,9956)

Same as record CQUAD8 description.

New RECORD - CQUADRN(15401,154,9954)

Same as record CQUAD4 description.

14-28 NX Nastran 12 Release Guide Upward compatibility

New RECORD - CTRIA6L(3202,32,1693) Same as record CTRIA6 description.

New RECORD - CTRIA6N(15801,158,9955) Same as record CTRIA6 description.

New RECORD - CTRIARL(12902,129,1691) Same as record CTRIA3 description.

New RECORD - CTRIARN(15301,153,9953) Same as record CTRIA3 description.

New RECORD - PLOTEL3(5202,52,669)

Word Name Type Description

1 EID I Element identification number

2 G(3) I Grid point identification numbers of connection points

New RECORD – PLOTEL4(5203,52,670)

Word Name Type Description

1 EID I Element identification number

2 G(4) I Grid point identification numbers of connection points

New RECORD – PLOTEL6(5204,52,671

Word Name Type Description

1 EID I Element identification number

2 G(6) I Grid point identification numbers of connection points

New RECORD – PLOTEL8(5205,52,672)

Word Name Type Description

1 EID I Element identification number

2 G(8) I Grid point identification numbers of connection points

NX Nastran 12 Release Guide 14-29 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

New RECORD - PLOTHEX(5206,52,673)

Word Name Type Description

1 EID I Element identification number

2 G(20) I Grid point identification numbers of connection points

New RECORD – PLOTPEN(5208,52,675)

Word Name Type Description

1 EID I Element identification number

2 G(15) I Grid point identification numbers of connection points

New RECORD – PLOTPYR(5209,52,676)

Word Name Type Description

1 EID I Element identification number

2 G(13) I Grid point identification numbers of connection points

New RECORD – PLOTTET(5207,52,674)

Word Name Type Description

1 EID I Element identification number

2 G(10) I Grid point identification numbers of connection points

GEOM3

New Record – FORCDST(5001,50,646)

Word Name Type Description

1 SID I Load set identification number

2 GEOM I SID of BSURF/BSURFS/BEDGE

3 PLOC(2) CHAR4 Coordinate system identification number

5 GRID I Grid point identification numbers

14-30 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

6 OFFST(3) RS Offsets in x, y, and z-directions

9 F RS Force scale factor

10 FN(3) RS Vector for force direction such that Force = F x FN

13 M RS Moment scale factor

14 MN(3) RS Vector for moment direction such that Moment = M x MN

New Record – INITS(8701,87,625)

Word Name Type Description

1 SID I INITS set identification number

2 TYPE I Type of data: 1=stress, 2=strain

3 LOC(C) I The location on the element where the stresses/strains are defined.

4 SYSTEM I Reference coordinate system used to define the stress/strain orientation coordinate system. Values: -1 for MATCID, 0 for BASIC, >0 for CSYS ID

5 UNDEF(4) None

LOC=0 Stress/strain defined at element centroid (unsupported)

9 EID I Element identification number

10 EXX RS Stress/strain xx

11 EYY RS Stress/strain yy

12 EZZ RS Stress/strain zz

13 EXY RS Stress/strain xy

14 EYZ RS Stress/strain yz

15 EXZ RS Stress/strain zx

Words 9 through 15 repeat until -1 occurs

LOC=1 Stress/strain defined at grids on element

9 EID I Element identification number

NX Nastran 12 Release Guide 14-31 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

10 GID I Grid identification number

11 EXX RS Stress/strain xx

12 EYY RS Stress/strain yy

13 EZZ RS Stress/strain zz

14 EXY RS Stress/strain xy

15 EYZ RS Stress/strain yz

16 EXZ RS Stress/strain zx

Words 9 through 16 repeat until -1 occurs

LOC=2 Stress/strain defined at grid points

9 GID I Grid identification number

10 EXX RS Stress/strain xx

11 EYY RS Stress/strain yy

12 EZZ RS Stress/strain zz

13 EXY RS Stress/strain xy

14 EYZ RS Stress/strain yz

15 EXZ RS Stress/strain zx

Words 9 through 15 repeat until -1 occurs

LOC=3 Stress/strain defined at element Gauss points (unsupported)

9 EID I Element identification number of grid or element

10 GID I Gauss point identification number

11 EXX RS Stress/strain xx

12 EYY RS Stress/strain yy

13 EZZ RS Stress/strain zz

14 EXY RS Stress/strain xy

15 EYZ RS Stress/strain yz

16 EXZ RS Stress/strain zx

Words 9 through 16 repeat until -1 occurs

14-32 NX Nastran 12 Release Guide Upward compatibility

New Record – INITSO(2901,29,638)

Word Name Type Description

1 SID I INITSO set identification number

2 TYPE I Type of data (only STRAIN is allowed): 2=strain

3 LOC(C) I The location on the element where the stresses/strains are defined.

4 SYSTEM I Reference coordinate system used to define the stress/strain orientation coordinate system. Values: -1 for MATCID, 0 for BASIC, >0 for CSYS ID

5 UNDEF(4) None

LOC=0 Initial strain offset at element centroid (unsupported)

9 EID I Element identification number

10 EXX RS Stress/strain xx

11 EYY RS Stress/strain yy

12 EZZ RS Stress/strain zz

13 EXY RS Stress/strain xy

14 EYZ RS Stress/strain yz

15 EXZ RS Stress/strain zx

Words 9 through 15 repeat until -1 occurs

LOC=1 Initial strain offset at grids on elements

9 EID I Element identification number

10 GID I Grid identification number

11 EXX RS Stress/strain xx

12 EYY RS Stress/strain yy

13 EZZ RS Stress/strain zz

14 EXY RS Stress/strain xy

15 EYZ RS Stress/strain yz

16 EXZ RS Stress/strain zx

NX Nastran 12 Release Guide 14-33 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

Words 9 through 16 repeat until -1 occurs

LOC=2 Initial strain offset at grid points

9 GID I Grid identification number

10 EXX RS Stress/strain xx

11 EYY RS Stress/strain yy

12 EZZ RS Stress/strain zz

13 EXY RS Stress/strain xy

14 EYZ RS Stress/strain yz

15 EXZ RS Stress/strain zx

Words 9 through 15 repeat until -1 occurs

LOC=3 Initial strain offset at element Gauss points (unsupported)

9 EID I Element identification number of grid or element

10 GID I Gauss point identification number

11 EXX RS Stress/strain xx

12 EYY RS Stress/strain yy

13 EZZ RS Stress/strain zz

14 EXY RS Stress/strain xy

15 EYZ RS Stress/strain yz

16 EXZ RS Stress/strain zx

Words 9 through 16 repeat until -1 occurs

New Record – INITADD(1101,11,626)

Word Name Type Description

1 SID I Load set identification number

2 UNDEF(8) None

10 LI I INITS or INITSO set identification number

Word 10 repeats until -1 occurs

14-34 NX Nastran 12 Release Guide Upward compatibility

GEOM4

New Record – ACPRESS(5656,57,656)

Word Name Type Description

1 SID I Load set identification number

2 FORM I Real/imaginary = 0, magnitude/phase = 1

3 A RS Scale factor

4 TRTM RS TR/RM

5 TIDTRTM I Table identification number of TR/RM

6 TITP RS TI/TP

7 TIDTRTM I Table identification number of TI/TP

8 UNDEF(3) None

11 ID I For GID, ID > 0; for "THRU", ID = 0; for "BY", ID = -6

Word 11 repeats until -1 occurs

LAMA

Updated Record 1 – OFPID

Word Name Type Description

......

3 UNDEF None

4 SCID I Subcase ID

5 UNDEF(5) None

......

12 UNDEF(11) None

23 FLAG I Default = 0; SOL 401 Axi-Fourier = 2, SOL 401 Cyclic = 3

24 UNDEF(2) None

26 HINDEX I Harmonic index for SOL 401 Axi-Fourier or SOL 401 Cyclic solutions. Default = -1 if not SOL 401 Axi-Fourier or Cyclic.

NX Nastran 12 Release Guide 14-35 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

27 UNDEF(24) None

......

MPT

Updated Record – MATCZ(5303,53,906)

Word Name Type Description

......

DLAW = 5 UMAT

3 UNDEF(6) None

9 K03S RS Transverse stiffness

10 K02 RS Shear stiffness

11 K01 RS Second shear stiffness

12 UNDEF(13) None

Updated Record – MATDMG(5101,51,642)

Word Name Type Description

PPFMOD=1 UD damage model

......

26 TID I Identification number of a TABLEM5 entry for nonlinear shear damage

......

PPFMOD=2 EUD damage model

3 UNDEF(6) None

9 Y012 RS Fiber/matrix de-bonding threshold

10 YC12 RS Critical thermodynamic force

11 K RS Coupling coefficient to account for the contribution of thermodynamic force Yd to fiber damage in compression

14-36 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

12 ALPHA RS Parameter given by the user to define the relationship for three crack modes in rupture envelope

13 Y11LIMT RS Breaking thresholds in tension

14 Y11LIMC RS Breaking thresholds in compression

15 KSIT RS Non-linearity coefficients in tension

16 KSIC RS Non-linearity coefficients in compression

17 B2 RS Coupling coefficient

18 B3 RS Coupling coefficient between the damage variables

19 A RS Coupling coefficient (plasticity)

20 LITK RS Initial plastic threshold

21 BIGK RS Parameter of plastic law

22 EXPN RS Exponent of plastic law

23 TAU RS Time for delay

24 ADEL RS Parameter for delay

25 USER I Indicator whether static damage w is limited to the maximum damage before taking into account time delay effect

26 RO1 RS Maximum transverse micro-cracking density

27 HBAR RS Transition thickness

28 DMAX RS Maximum value of damage

29 DS RS Maximum diffuse damage

30 GIC RS Critical mode I crack energy release rates for the ply

31 GIIC RS Critical mode II crack energy release rates for the ply

32 GIIIC RS Critical mode III crack energy release rates for the ply

NX Nastran 12 Release Guide 14-37 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

New Record – MAT10C(4701,50,965)

Word Name Type Description

1 MID I Material identification number

2 FORM I Format of data: real/imaginary=0, magnitude/phase=1

3 RHOR RS Mass density real part or magnitude

4 UNDEF None

5 RHOI RS Mass density imaginary part or phase (in degrees)

6 UNDEF None

7 CR RS Speed of sound real part or magnitude

8 UNDEF None

9 CI RS Speed of sound imaginary part or phase (in degrees)

10 UNDEF(3) None

New Record – MATF10C(6610,52,661)

Word Name Type Description

1 MID I Material identification number

2 TIDRHOR I TABLEDi identification number that defines frequency-dependent real part or magnitude of mass density

3 TIDRHOI I TABLEDi identification number that defines frequency-dependent imaginary part or phase (in degrees) of mass density

4 TIDCR I TABLEDi identification number that defines frequency-dependent real part or magnitude of speed of sound

5 TIDCI I TABLEDi identification number that defines frequency-dependent imaginary part or phase (in degrees) of speed of sound

6 UNDEF(5) None

14-38 NX Nastran 12 Release Guide Upward compatibility

New Record – MATT10(4901,49,960)

Word Name Type Description

1 MID I Material identification number

2 TBULK I TABLEMi ID for bulk modulus

3 TRHO I TABLEMi ID for mass density

4 TC I TABLEMi ID for speed of sound

5 TGE I TABLEMi ID for structural damping coefficient

6 ALPHA I TABLEMi ID for temporal damping coefficient

7 UNDEF(4) None

New Record – NLARCL(1308,13,663)

Word Name Type Description

1 ID I NLARCL identification number

2 PARAM(i)1 CHAR4 First 4 characters in PARAM(i) name

3 PARAM(i)2 CHAR4 Second 4 characters in PARAM(i) name

4 PMLIST I Parameter value type

PMLIST=1 Parameter value is integer

5 IVAL I Integer value of PARAMi

PMLIST=2 Parameter value is real

5 RVAL RS Real parameter value

PMLIST=3 Parameter value is character

5 CVAL1 CHAR4 First 4 characters in PARAM(i) value

6 CVAL2 CHAR4 Second 4 characters in PARAM(i) value

If in previous loop PMLIST=1 or 2, words 3 through 5 repeat until (-1,-1) occurs If in previous loop PMLIST=3, words 3 through 6 repeat until (-1,-1) occurs

New Record – NLCNTL(1203,12,617)

Word Name Type Description

1 ID I NLCNTL identification number

NX Nastran 12 Release Guide 14-39 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

2 PARAM(i)1 CHAR4 First 4 characters in PARAM(i) name

3 PARAM(i)2 CHAR4 Second 4 characters in PARAM(i) name

4 PMLIST I Parameter value type

PMLIST=1 Parameter value is integer

5 IVAL I Integer value of PARAMi

PMLIST=2 Parameter value is real

5 RVAL RS Real parameter value

PMLIST=3 Parameter value is character

5 CVAL1 CHAR4 First 4 characters in PARAM(i) value

6 CVAL2 CHAR4 Second 4 characters in PARAM(i) value

If in previous loop PMLIST=1 or 2, words 3 through 5 repeat until (-1,-1) occurs If in previous loop PMLIST=3, words 3 through 6 repeat until (-1,-1) occurs

OACCQ

Updated Record – IDENT

Word Name Type Description

3 DATCOD I Data code: • 0 = coupled fluid faces; normal projection distance in absolute units

• 1 = uncoupled fluid faces; outward and inward normal search distance in absolute units

• 2 = coupled and uncoupled fluid faces; for coupled faces, normal projection distance in absolute units; for uncoupled faces, outward and inward normal search distance in absolute units

• 3 = coupled and uncoupled structural faces; for coupled faces, distance = 0.0; for uncoupled faces, distance = 1.0

14-40 NX Nastran 12 Release Guide Upward compatibility

OACINT

Acoustic intensity at fluid grids in SORT1 and SORT2 format

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach code

2 TCODE(C) I Table code = 54

3 UNDEF None

4 SUBCASE I Subcase identification number.

TCODE,1 = 01 Sort 1

5 FREQ RS Frequency (Hz)

TCODE,1 = 02 Sort 2

5 GID I Fluid grid ID

End TCODE,1

6 UNDEF(3) None

9 FCODE(C) I Format code

10 NUMWDE(C) I Number of words per entry in DATA record = 7

11 UNDEF(40) None

51 TITLE(32) CHAR4 Title character string (TITLE)

83 SUBTITL(32) CHAR4 Subtitle character string (SUBTITLE)

115 LABEL(32) CHAR4 LABEL character string (LABEL)

Updated Record – DATA

Word Name Type Description

TCODE,1 = 01 Sort 1

1 GID I Fluid grid ID

TCODE,1 = 02 Sort 2

1 FREQ RS Frequency (Hz)

End TCODE,1

NX Nastran 12 Release Guide 14-41 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

2 INTR(3) RS Intensity components - real part

5 INTI(3) RS Intensity components - imaginary part

OACPWR

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach code

2 TCODE(C) I Table code = 55

3 DATCOD I Data code; 10*SID for AMLREG, 10*SID+1 for GROUP

4 SUBCAS I Subcase identification number

TCODE,1 = 01 SORT1 format

5 FREQ RS Frequency (Hz)

TCODE,1 = 02 SORT2 format

5 SID I AMLREG / GROUP ID

End TCODE,1

6 UNDEF(1) None

7 RCODE I Random ID

8 UNDEF(1) None

9 FCODE(C) I Format type code

10 NUMWDE(C) I Number of words per entry in DATA record = 2 or 3

11 DESCR(12) CHAR4 AMLREG / GROUP description

23 UNDEF(28) None

51 TITLE(32) CHAR4 Title character string (TITLE)

83 SUBTITL(32) CHAR4 Subtitle character string (SUBTITLE)

115 LABEL(32) CHAR4 LABEL character string (LABEL)

14-42 NX Nastran 12 Release Guide Upward compatibility

Updated Record – DATA

Word Name Type Description

TCODE,1 = 01 SORT1 Format

1 SID I AMLREG/GROUP ID

TCODE,1 = 02 SORT2 Format

1 FREQ RS Frequency (Hz)

End TCODE,1

TCODE,7 = 01 Real or imaginary

2 POWERR RS Power - real part

3 POWERI RS Power - imaginary part

TCODE,7 = 0 or 2 Real or random response

2 POWER RS Power

End TCODE,7

Updated Record – TRAILER

Word Name Type Description

1 NUMRF I Number of record pairs * number of frequencies

2 UNDEF(5) None

OACVELO

Acoustic velocity at fluid grids in SORT1 and SORT2 format

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach code

2 TCODE(C) I Table code = 53

3 UNDEF

4 SUBCAS I Subcase identification number

TCODE,1 = 01 Sort 1

NX Nastran 12 Release Guide 14-43 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

5 FREQ RS Frequency (Hz)

TCODE,1 = 02 Sort 2

5 GID I Fluid grid ID

End TCODE,1

6 UNDEF(3)

9 FCODE(C) I Format code

10 NUMWDE(C) I Number of words per entry in DATA record = 7

11 UNDEF(40)

51 TITLE(32) CHAR4 Title character string (TITLE)

83 SUBTITL(32) CHAR4 Subtitle character string (SUBTITLE)

115 LABEL(32) CHAR4 LABEL character string (LABEL)

Updated Record – DATA

Word Name Type Description

TCODE,1 = 01 Sort 1

1 GID I Fluid grid ID

TCODE,1 = 02 Sort 2

1 FREQ RS Frequency (Hz)

End TCODE,1

2 VELR(3) RS Velocity components - real part

5 VELI(3) RS Velocity components - imaginary part

OBC

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10* Approach Code

2 TCODE(C) I Table code, 62

14-44 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

3 UNDEF None

4 SUBCASE I Subcase identification number

TCODE=1 SORT1

ACODE=01 SOL 101 linear statics

5 LSDVMN I Load set number

6 UNDEF(2) None

ACODE=06 401 non arc-length

5 TIME RS Time step

6 UNDEF(2) None

ACODE=10 401, 601, and 701 nonlinear statics

5 LFTSFQ RS Load factor for SOL 401 arc-length only

6 TIME RS Time for SOL 401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL 401 arc-length only

End ACODE

TCODE=2 SORT2

5 LSDVMN I Load set, mode number

6 UNDEF(2) None

End TCODE

8 LSDVMN I Load set number

9 FCODE I Format code

10 NUMWDE I Number of words per entry in DATA record

11 UNDEF None

12 PID I Physical property

13 UNDEF(38) None

51 TITLE(32) CHAR4 Title

83 SUBTITL(32) CHAR4 Subtitle

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Word Name Type Description

115 LABEL(32) CHAR4 Label

OBOLT

Updated Record – IDENT

Word Name Type Description

......

ACODE,4=06 Transient

5 TIME RS Current time step

6 UNDEF(4) None

ACODE,4=10 Nonlinear statics

5 LFTSFQ RS Load factor for SOL 401 arc-length only

6 TIME RS Time for SOL 401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL 401 arc-length only

8 UNDEF(2) None

End ACODE

10 NUMWDE(C) I Number of words per entry in DATA record

11 CSID I Bolt coordinate system ID

12 IDIR I Bolt direction vector

13 EULER1(3) RS Euler angles between basic and bolt CSYS in undeformed configuration

16 EULER2(3) RS Euler angles between basic and bolt CSYS in deformed configuration

19 UNDEF(32) None

......

14-46 NX Nastran 12 Release Guide Upward compatibility

OBG

Updated Record – IDENT

Word Name Type Description

......

ACODE=10 Nonlinear statics

5 LFTSFQ RS Load factor for SOL 401 arc-length only

6 TIME RS Time for SOL 401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL 401 arc-length only

......

OCKGAP1

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10* Approach Code

2 TCODE(C) I Table code, 81

3 ELTYPE(C) I Element type number

4 SUBCASE I Subcase identification number

ACODE=06 Transient

5 TIME RS Current time step

6 UNDEF(4) None

ACODE=10 Nonlinear statics

5 LFTSFQ RS Load factor for SOL 401 arc-length only

6 TIME RS Time for SOL 401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL 401 arc-length only

8 UNDEF(2) None

End ACODE

10 NUMWPE I Number of words per entry element

NX Nastran 12 Release Guide 14-47 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

11 UNDEF(40) None

51 TITLE(32) CHAR4 Title

83 SUBTITL(32) CHAR4 Subtitle

115 LABEL(32) CHAR4 Label

ODAMGCZD

Updated Record - IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach code = 60 + iand (print, plot)

2 TCODE I Table code

3 ELTYPE(C) I Element type number

4 SUBCASE I Subcase number

TCODE,1 = 01 Sort 1

ACODE,4 = 06 Transient

5 TIME RS Current time step

6 UNDEF(45) None

ACODE,4 = 10 Nonlinear statics

5 LFTSFQ RS Load step for SOL 401 arc-length only

6 TIME RS Time for SOL 401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL 401 arc-length only

8 UNDEF(43) None

End ACODE,4

TCODE,1 = 02 Sort 2

End TCODE,1

51 TITLE(32) CHAR4 Title character string (TITLE)

83 SUBTITL(32) CHAR4 Subtitle character string (SUBTITLE)

14-48 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

115 LABEL(32) CHAR4 LABEL character string (LABEL)

ODAMGCZR

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach code = 60 + iand (print, plot)

2 TCODE I Table code

3 ELTYPE(C) I Element type number

4 SUBCASE I Subcase number

TCODE,1 = 01 Sort 1

ACODE,4 = 06 Transient

5 TIME RS Current time step

6 UNDEF(4) None

ACODE,4 = 10 Nonlinear statics

5 LFTSFQ RS Load step for SOL401 arc-length only

6 TIME RS Time for SOL401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL401 arc-length only

8 UNDEF(2) None

End ACODE,4

TCODE,1 = 02 Sort 2

End TCODE,1

10 NWDSPE I Number of words per element E335=41, E336=31, E353=34, E354=26

11 UNDEF(40) None

51 TITLE(32) CHAR4 Title character string (TITLE)

83 SUBTITL(32) CHAR4 Subtitle character string (SUBTITLE)

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Word Name Type Description

115 LABEL(32) CHAR4 LABEL character string (LABEL)

Updated Record – DATA

Word Name Type Description

ELTYPE=335 or 336 ELTYPE=335 - Cohesive HEXA element (CHEXCZ) ELTYPE=336 - Cohesive PENTA element (CPENTCZ)

1 EID I Element ID * 10 + device code

2 GRID I External identification number of grid

3 RDN RS Normal relative separation

4 RD1 RS In-plane relative motion in X direction (basic coordinate system)

5 RD2 RS In-plane relative motion in Y direction (basic coordinate system)

6 RD3 RS In-plane relative motion in Z direction (basic coordinate system)

ELTYPE=353 or 354 ELTYPE=353 - Cohesive HEXA element (CHEXCZ) output in material coordinate system ELTYPE=354 - Cohesive PENTA element (CPENTCZ) output in material coordinate system

1 EID I Element ID * 10 + device code

2 CID I Material coordinate system identification number

3 GRID I External identification number of grid

4 RD1 RS Relative motion in X direction (material coordinate system)

5 RD2 RS Relative motion in Y direction (material coordinate system)

6 RD3 RS Relative motion in Z direction (material coordinate system)

Repeat words 2-6 for each corner grid point. (8 corners for cohesive CHEXA (CHEXCZ) and 6 corners for cohesive PENTA element (CPENTCZ).)

14-50 NX Nastran 12 Release Guide Upward compatibility

ODAMGCZT

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach code = 60 + iand (print, plot)

2 TCODE I Table code

3 ELTYPE(C) I Element type number

4 SUBCASE I Subcase number

TCODE,1 = 01 Sort 1

ACODE,4 = 06 Transient

5 TIME RS Current time step

6 UNDEF(4) None

ACODE,4 = 10 Nonlinear statics

5 LFTSFQ RS Load step for SOL401 arc-length only

6 TIME RS Time for SOL401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL401 arc-length only

8 UNDEF(2) None

End ACODE,4

TCODE,1 = 02 Sort 2

End TCODE,1

10 NWDSPE I Number of words per element, E335=41, E336=31, E353=34, E354=26

11 UNDEF(40) None

51 TITLE(32) CHAR4 Title character string (TITLE)

83 SUBTITL(32) CHAR4 Subtitle character string (SUBTITLE)

115 LABEL(32) CHAR4 LABEL character string (LABEL)

NX Nastran 12 Release Guide 14-51 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Updated Record – DATA

Word Name Type Description

ELTYPE=335 or 336 ELTYPE=335 - Cohesive HEXA element (CHEXCZ) ELTYPE=336 - Cohesive PENTA element (CPENTCZ)

1 ELID I Element ID * 10 + device code

2 GRID I External identification number of grid

3 TN RS Normal stress on face

4 T1 RS Shear stress on face in X direction (basic coordinate system)

5 T2 RS Shear stress on face in Y direction (basic coordinate system)

6 T3 RS Shear stress on face in Z direction (basic coordinate system)

ELTYPE=353 or 354 ELTYPE=353 - Cohesive HEXA element (CHEXCZ) output in material coordinate system ELTYPE=354 - Cohesive PENTA element (CPENTCZ) output in material coordinate system

1 ELID I Element ID * 10 + device code

2 CID I Material coordinate system ID

3 GRID I External identification number of grid

4 T1 RS Stress in direction X (material coordinate system)

5 T2 RS Stress in direction Y (material coordinate system)

6 T3 RS Stress in direction Z (material coordinate system)

Repeat words 2-6 for each corner grid point. (8 corners for cohesive CHEXA (CHEXCZ) and 6 corners for cohesive PENTA element (CPENTCZ).)

ODAMGPFD

Table of damage values for ply failure for SOL 401 Damage values at corner grids on middle, and the values are unitless.

14-52 NX Nastran 12 Release Guide Upward compatibility

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach code = 60 + iand (print, plot)

2 TCODE I Table code

3 ELTYPE(C) I Element type number

4 SUBCASE I Subcase number

TCODE,1 = 01 Sort 1

ACODE,4 = 06 Transient

5 TIME RS Current time step

6 UNDEF(4) None

ACODE,4 = 10 Nonlinear statics

5 LFTSFQ RS Load step for SOL401 arc-length only

6 TIME RS Time for SOL401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL401 arc-length only

8 UNDEF(2) None

End ACODE,4

TCODE,1 = 02 Sort 2

End TCODE,1

10 NUMWDE I Number of words per entry in DATA record

11 UNDEF(40) None

51 TITLE(32) CHAR4 Title character string (TITLE)

83 SUBTITL(32) CHAR4 Subtitle character string (SUBTITLE)

115 LABEL(32) CHAR4 LABEL character string (LABEL)

NX Nastran 12 Release Guide 14-53 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Updated Record – DATA

Word Name Type Description

ELTYPE=267, 268, 355, ELTYPE=267 - Composite HEXA element (CHEXAL) 356, 357, or 358 ELTYPE=268 - Composite PENTA element (CPENTAL) ELTYPE=355 - Composite triangular shell element (CTRIA6) ELTYPE=356 - Composite quadrilateral shell element (CQUAD8) ELTYPE=357 - Composite triangular shell element (CTRIAR) ELTYPE=358 - Composite quadrilateral shell element (CQUADR)

1 ELID I Element ID * 10 + device code

2 PLY I Lamina number

3 DMID I Damage model identification number

DMID=1 UD damage model

4 NVPG I Number of active damage values, =6 for UD model

5 GRID I External grid ID

6 DV1 RS Damage value d11

7 DV2 RS Damage value d22

8 DV3 RS Damage value d33

9 DV4 RS Damage value d12

10 DV5 RS Damage value d23

11 DV6 RS Damage value d13

DMID=2 EUD damage model

4 NVPG I Number of active damage values, =6 for EUD model

5 GRID I External grid ID

6 DV1 RS Damage value d11

7 DV2 RS Damage value d22

8 DV3 RS Damage value d33

9 DV4 RS Damage value d12

10 DV5 RS Damage value d23

14-54 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

11 DV6 RS Damage value d13

On each ply, words 5 thru 11 repeat for each corner grid point. (4 corners for composite HEXA and CQUADi elements, 3 corners for composite PENTA and CTRIAi elements.)

ODAMGPFE

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach code = 60 + iand (print, plot)

2 TCODE I Table code

3 ELTYPE I Element type number

4 SUBCASE I Subcase number

TCODE,1 = 01 Sort 1

ACODE,4 = 06 Transient

5 TIME RS Current time step

6 UNDEF(4) None

ACODE,4 = 10 Nonlinear statics

5 LFTSFQ RS Load step for SOL401 arc-length only

6 TIME RS Time for SOL401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL401 arc-length only

8 UNDEF(2) None

End ACODE,4

TCODE,1 = 02 Sort 2

End TCODE,1

10 NWDSPE I Number of words per element = 2

11 UNDEF(40) None

51 TITLE(32) CHAR4 Title character string (TITLE)

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Word Name Type Description

83 SUBTITL(32) CHAR4 Subtitle character string (SUBTITLE)

115 LABEL(32) CHAR4 LABEL character string (LABEL)

ODAMGPFS

Updated Record – IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach code = 60 + iand (print, plot)

2 TCODE I Table code

3 ELTYPE I Element type number

4 SUBCASE I Subcase number

TCODE,1 = 01 Sort 1

ACODE,4 = 06 Transient

5 TIME RS Current time step

6 UNDEF(4) None

ACODE,4 = 10 Nonlinear statics

5 LFTSFQ RS Load step for SOL401 arc-length only

6 TIME RS Time for SOL401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL401 arc-length only

8 UNDEF(2) None

End ACODE,4

TCODE,1 = 02 Sort 2

End TCODE,1

10 NWDSPE I Number of words per element = 2

11 UNDEF(40) None

51 TITLE(32) CHAR4 Title character string (TITLE)

83 SUBTITL(32) CHAR4 Subtitle character string (SUBTITLE)

14-56 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

115 LABEL(32) CHAR4 LABEL character string (LABEL)

OEE

Updated Record - DATA

Word Name Type Description

......

CVALRES=01 Complex value resolution: Average

2 ENERGYR RS Element Energy Average (real/mag part)

3 ENERGYI RS Element Energy Average (imag/phase part)

4 PCT RS Percent of Total Energy

5 DEN RS Element Energy Density, or '-1' after all elements

CVALRES=02 Complex value resolution: Amplitude

2 ENERGYR RS Element Energy Amplitude (real/mag part)

3 ENERGYI RS Element Energy Amplitude (imag/phase part)

4 PCT RS Percent of Total Energy

5 DEN RS Element Energy Density, or '-1' after all elements

CVALRES=03 Complex value resolution: Peak

2 ENERGYR RS Element Energy Peak (real/mag part)

3 ENERGYI RS Element Energy Peak (imag/phase part)

4 PCT RS Percent of Total Energy

5 DEN RS Element Energy Density, or '-1' after all elements

CVALRES=04 Complex value resolution: AVGAMP

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Word Name Type Description

2 ENERGRAV RS Element Energy Average (real/mag part)

3 ENERGIAV RS Element Energy Average (imag/phase part)

4 ENERGRAM RS Element Energy Amplitude (real/mag part)

5 ENERGIAM RS Element Energy Amplitude (imag/phase part)

6 PCT RS Percent of Total Energy

7 DEN RS Element Energy Density, or '-1' after all elements

End CVALRES

End TCODE,7

OEF

Updated Record – IDENT

Word Name Type Description

......

ACODE,4 =10 Nonlinear Statics

5 LFTSFQ RS Load factor for SOL 401 arc-length only

6 TIME RS Time for SOL 401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL 401 arc-length only

......

24 UNDEF(2) None

26 HINDEX I Harmonic index

27 SCFLAG I Sine/cosine flag: 0=0th harmonic, 1=cosine component, 2=sine component, -1 (default) for other solution type output

28 UNDEF(23) None

......

14-58 NX Nastran 12 Release Guide Upward compatibility

Updated Record – DATA

Word Name Type Description

TCODE,1 =1 SORT1 Format

1 EKEY I Device code + 10*Element identification number

TCODE,1 =02 SORT2 Format

ACODE,4 =01 Statics

......

Word Name Type Description

......

ELTYPE =02 Beam element (CBEAM)

TCODE,7 =0 or 2 Real or Random Response

2 GRID I Grid point identification number

3 SD RS Station Distance divided by element's length

4 BM1 RS Bending moment plane 1

5 BM2 RS Bending moment plane 2

6 TS1 RS Shear Plane 1

7 TS2 RS Shear Plane 2

8 AF RS Axial Force

9 TTRQ RS Total Torque

10 WTRQ RS Warping Torque

TCODE,7 =1 Real/imaginary or magnitude/phase

2 GRID I Grid point identification number

3 SD RS Station Distance divided by element's length

4 BM1R RS Bending moment plane 1 - real/mag. part

5 BM2R RS Bending moment plane 2 - real/mag. part

6 TS1R RS Shear plane 1 - real/mag. part

7 TS2R RS Shear plane 2 - real/mag. part

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Word Name Type Description

8 AFR RS Axial force - real/mag. part

9 TTRQR RS Total torque - real/mag. part

10 WTRQR RS Warping torque - real/mag. part

11 BM1I RS Bending moment plane 1 - imag./phase part

12 BM2I RS Bending moment plane 2 - imag./phase part

13 TS1I RS Shear plane 1 - imag./phase part

14 TS2I RS Shear plane 2 - imag./phase part

15 AFI RS Axial force - imag./phase part

16 TTRQI RS Total torque - imag./phase part

17 WTRQI RS Warping torque - imag./phase part

End TCODE,7

Words 2 through max repeat 011 times

......

Word Name Type Description

......

ELTYPE =64 Curved quadrilateral shell element (CQUAD8)

TCODE,7 =0 or 2 Real or Random Response

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids or corner grid ID

4 MX RS Membrane force in x

5 MY RS Membrane force in y

6 MXY RS Membrane force in xy

7 BMX RS Bending moment in x

8 BMY RS Bending moment in y

9 BMXY RS Bending moment in xy

10 TX RS Shear force in x

14-60 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

11 TY RS Shear force in y

TCODE,7 =1 Real/imaginary or magnitude/phase

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids or corner grid ID

4 MXR RS Membrane force in x - real/mag. part

5 MYR RS Membrane force in y - real/mag. part

6 MXYR RS Membrane force in xy - real/mag. part

7 BMXR RS Bending moment in x - real/mag. part

8 BMYR RS Bending moment in y - real/mag. part

9 BMXYR RS Bending moment in xy - real/mag. part

10 TXR RS Shear force in x - real/mag. part

11 TYR RS Shear force in y - real/mag. part

12 MXI RS Membrane force in x - imag./phase part

13 MYI RS Membrane force in y - imag./phase part

14 MXYI RS Membrane force in xy - imag./phase part

15 BMXI RS Bending moment in x - imag./phase part

16 BMYI RS Bending moment in y - imag./phase part

17 BMXYI RS Bending moment in xy - imag./phase part

18 TXI RS Shear force in x - imag./phase part

19 TYI RS Shear force in y - imag./phase part

End TCODE,7

Words 3 through max repeat 005 times

......

ELTYPE =69 Curved beam or pipe element (CBEND - see note)

TCODE,7 =0 or 2 Real or Random Response

2 GRID I Grid point identification number

3 BM1 RS Bending moment plane 1

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Word Name Type Description

4 BM2 RS Bending moment plane 1

5 TS1 RS Shear plane 1

6 TS2 RS Shear plane 2

7 AF RS Axial force

8 TRQ RS Torque

TCODE,7 =1 Real/imaginary or magnitude/phase

2 GRID I Grid point identification number - real/mag. part

3 BM1R RS Bending moment plane 1 - real/mag. part

4 BM2R RS Bending moment plane 1 - real/mag. part

5 TS1R RS Shear plane 1 - real/mag. part

6 TS2R RS Shear plane 2 - real/mag. part

7 AFR RS Axial force - real/mag. part

8 TRQR RS Torque - real/mag. part

9 BM1I RS Bending moment plane 1 - imag./phase part

10 BM2I RS Bending moment plane 1 - imag./phase part

11 TS1I RS Shear plane 1 - imag./phase part

12 TS2I RS Shear plane 2 - imag./phase part

13 AFI RS Axial force - imag./phase part

14 TRQI RS Torque - imag./phase part

End TCODE,7

Words 2 through max repeat 002 times

Word Name Type Description

ELTYPE =70 Triangular plate element (CTRIAR)

TCODE,7 =0 or 2 Real or Random Response

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids or corner grid ID

14-62 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

4 MX RS Membrane force in x

5 MY RS Membrane force in y

6 MXY RS Membrane force in xy

7 BMX RS Bending moment in x

8 BMY RS Bending moment in y

9 BMXY RS Bending moment in xy

10 TX RS Shear force in x

11 TY RS Shear force in y

TCODE,7 =1 Real/imaginary or magnitude/phase

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids or corner grid ID

4 MXR RS Membrane force in x - real/mag. part

5 MYR RS Membrane force in y - real/mag. part

6 MXYR RS Membrane force in xy - real/mag. part

7 BMXR RS Bending moment in x - real/mag. part

8 BMYR RS Bending moment in y - real/mag. part

9 BMXYR RS Bending moment in xy - real/mag. part

10 TXR RS Shear force in x - real/mag. part

11 TYR RS Shear force in y - real/mag. part

12 MXI RS Membrane force in x - imag./phase part

13 MYI RS Membrane force in y - imag./phase part

14 MXYI RS Membrane force in xy - imag./phase part

15 BMXI RS Bending moment in x - imag./phase part

16 BMYI RS Bending moment in y - imag./phase part

17 BMXYI RS Bending moment in xy - imag./phase part

18 TXI RS Shear force in x - imag./phase part

19 TYI RS Shear force in y - imag./phase part

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Word Name Type Description

End TCODE,7

Words 3 through max repeat 004 times

......

ELTYPE =75 Curved triangular shell element (CTRIA6)

TCODE,7 =0 or 2 Real or Random Response

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids or corner grid ID

4 MX RS Membrane force in x

5 MY RS Membrane force in y

6 MXY RS Membrane force in xy

7 BMX RS Bending moment in x

8 BMY RS Bending moment in y

9 BMXY RS Bending moment in xy

10 TX RS Shear force in x

11 TY RS Shear force in y

TCODE,7 =1 Real/imaginary or magnitude/phase

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids or corner grid ID

4 MXR RS Membrane force in x - real/mag. part

5 MYR RS Membrane force in y - real/mag. part

6 MXYR RS Membrane force in xy - real/mag. part

7 BMXR RS Bending moment in x - real/mag. part

8 BMYR RS Bending moment in y - real/mag. part

9 BMXYR RS Bending moment in xy - real/mag. part

10 TXR RS Shear force in x - real/mag. part

11 TYR RS Shear force in y - real/mag. part

12 MXI RS Membrane force in x - imag./phase part

14-64 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

13 MYI RS Membrane force in y - imag./phase part

14 MXYI RS Membrane force in xy - imag./phase part

15 BMXI RS Bending moment in x - imag./phase part

16 BMYI RS Bending moment in y - imag./phase part

17 BMXYI RS Bending moment in xy - imag./phase part

18 TXI RS Shear force in x - imag./phase part

19 TYI RS Shear force in y - imag./phase part

End TCODE,7

Words 3 through max repeat 004 times

ELTYPE =76 Acoustic velocity/pressures in six-sided solid element (CHEXA)

TCODE,7 = 1 Real/imaginary or magnitude/phase

2 ELNAME(2) CHAR4 Element name: "HEXPR"

4 AXR RS Acceleration in x - real/mag. part

5 AYR RS Acceleration in y - real/mag. part

6 AZR RS Acceleration in z - real/mag. part

7 VXR RS Velocity in x - real/mag. part

8 VYR RS Velocity in y - real/mag. part

9 VZR RS Velocity in z - real/mag. part

10 PRESSURE RS Pressure in dB

11 AXI RS Acceleration in x - imag./phase part

12 AYI RS Acceleration in y - imag./phase part

13 AZI RS Acceleration in z - imag./phase part

14 VXI RS Velocity in x - imag./phase part

15 VYI RS Velocity in y - imag./phase part

16 VZI RS Velocity in z - imag./phase part

TCODE,7 =0 or 2 Real or Random Response

2 ELNAME(2) CHAR4 Element name: "HEXPR"

NX Nastran 12 Release Guide 14-65 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

4 AX RS Acceleration in x - real/mag. part

5 AY RS Acceleration in y - real/mag. part

6 AZ RS Acceleration in z - real/mag. part

7 VX RS Velocity in x - real/mag. part

8 VY RS Velocity in y - real/mag. part

9 VZ RS Velocity in z - real/mag. part

10 PRESSURE RS Pressure in dB

ELTYPE =77 Acoustic velocity/pressures in five-sided solid element (CPENTA)

TCODE,7 =0 or 2 Real or Random Response

2 ELNAME(2) CHAR4 Element name: "PENPR"

4 AX RS Acceleration in x

5 AY RS Acceleration in y

6 AZ RS Acceleration in z

7 VX RS Velocity in x

8 VY RS Velocity in y

9 VZ RS Velocity in z

10 PRESSURE RS Pressure in dB

TCODE,7 =1 Complex

2 ELNAME(2) CHAR4 Element name: "PENPR"

4 AXR RS Acceleration in x - real/mag. part

5 AYR RS Acceleration in y - real/mag. part

6 AZR RS Acceleration in z - real/mag. part

7 VXR RS Velocity in x - real/mag. part

8 VYR RS Velocity in y - real/mag. part

9 VZR RS Velocity in z - real/mag. part

10 PRESSURE RS Pressure in dB

11 AXI RS Acceleration in x - imag./phase part

14-66 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

12 AYI RS Acceleration in y - imag./phase part

13 AZI RS Acceleration in z - imag./phase part

14 VXI RS Velocity in x - imag./phase part

15 VYI RS Velocity in y - imag./phase part

16 VZI RS Velocity in z - imag./phase part

End TCODE,7

ELTYPE =78 Acoustic velocity/pressures in four-sided solid element (CTETRA)

TCODE,7 =0 or 2 Real or Random Response

2 ELNAME(2) CHAR4 Element name: "TETPR"

4 AX RS Acceleration in x

5 AY RS Acceleration in y

6 AZ RS Acceleration in z

7 VX RS Velocity in x

8 VY RS Velocity in y

9 VZ RS Velocity in z

10 PRESSURE RS Pressure in dB

TCODE,7 =1

2 ELNAME(2) CHAR4 Element name: "TETPR"

4 AXR RS Acceleration in x - real/mag. part

5 AYR RS Acceleration in y - real/mag. part

6 AZR RS Acceleration in z - real/mag. part

7 VXR RS Velocity in x - real/mag. part

8 VYR RS Velocity in y - real/mag. part

9 VZR RS Velocity in z - real/mag. part

10 PRESSURE RS Pressure in dB

11 AXI RS Acceleration in x - imag./phase part

12 AYI RS Acceleration in y - imag./phase part

NX Nastran 12 Release Guide 14-67 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

13 AZI RS Acceleration in z - imag./phase part

14 VXI RS Velocity in x - imag./phase part

15 VYI RS Velocity in y - imag./phase part

16 VZI RS Velocity in z - imag./phase part

End TCODE,7

ELTYPE =79 Acoustic velocity/pressures in five-sided solid element (CPYRAM)

TCODE,7 = 0 or 2 Real or Random Response

2 ELNAME(2) CHAR4 Element name: “PYRAMPR”

4 AX RS Acceleration in x

5 AY RS Acceleration in y

6 AZ RS Acceleration in z

7 VX RS Velocity in x

8 VY RS Velocity in y

9 VZ RS Velocity in z

10 PRESSURE RS Pressure in dB

TCODE,7 = 1

2 ELNAME(2) CHAR4 Element name: “PYRAMPR”

4 AXR RS Acceleration in x – real/mag. part

5 AYR RS Acceleration in y – real/mag. part

6 AZR RS Acceleration in z – real/mag. part

7 VXR RS Velocity in x – real/mag. part

8 VYR RS Velocity in y– real/mag. part

9 VZR RS Velocity in z– real/mag. part

10 PRESSURE RS Pressure in dB

11 AXI RS Acceleration in x – imag./phase part

12 AYI RS Acceleration in y – imag./phase part

14-68 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

13 AZI RS Acceleration in z – imag./phase part

14 VXI RS Velocity in x – imag./phase part

15 VYI RS Velocity in y – imag./phase part

16 VZI RS Velocity in z – imag./phase part

End TCODE,7

Word Name Type Description

......

ELTYPE =82 Quadrilateral plate element (CQUADR)

TCODE,7 =0 or 2 Real or Random Response

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids (4) or corner grid identification number

4 MX RS Membrane force in x

5 MY RS Membrane force in y

6 MXY RS Membrane force in xy

7 BMX RS Bending moment in x

8 BMY RS Bending moment in y

9 BMXY RS Bending moment in xy

10 TX RS Shear force in x

11 TY RS Shear force in y

TCODE,7 =1 Real/imaginary or magnitude/phase

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids (4) or corner grid identification number

4 MXR RS Membrane force in x - real/mag. part

5 MYR RS Membrane force in y - real/mag. part

6 MXYR RS Membrane force in xy - real/mag. part

NX Nastran 12 Release Guide 14-69 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

7 BMXR RS Bending moment in x - real/mag. part

8 BMYR RS Bending moment in y - real/mag. part

9 BMXYR RS Bending moment in xy - real/mag. part

10 TXR RS Shear force in x - real/mag. part

11 TYR RS Shear force in y - real/mag. part

12 MXI RS Membrane force in x - imag./phase part

13 MYI RS Membrane force in y - imag./phase part

14 MXYI RS Membrane force in xy - imag./phase part

15 BMXI RS Bending moment in x - imag./phase part

16 BMYI RS Bending moment in y - imag./phase part

17 BMXYI RS Bending moment in xy - imag./phase part

18 TXI RS Shear force in x - imag./phase part

19 TYI RS Shear force in y - imag./phase part

End TCODE,7

Words 3 through max repeat 005 times

......

Word Name Type Description

......

ELTYPE =144 Quadrilateral plate element for corner stresses (QUAD144)

TCODE,7 =0 or 2 Real or Random Response

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids (4) or corner grid ID

4 MX RS Membrane x

5 MY RS Membrane y

6 MXY RS Membrane xy

7 BMX RS Bending x

14-70 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

8 BMY RS Bending y

9 BMXY RS Bending xy

10 TX RS Shear x

11 TY RS Shear y

TCODE,7 =1 Real/imaginary or magnitude/phase

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids (4) or corner grid ID

4 MXR RS Membrane x - real/mag. part

5 MYR RS Membrane y - real/mag. part

6 MXYR RS Membrane xy - real/mag. part

7 BMXR RS Bending x - real/mag. part

8 BMYR RS Bending y - real/mag. part

9 BMXYR RS Bending xy - real/mag. part

10 TXR RS Shear x - real/mag. part

11 TYR RS Shear y - real/mag. part

12 MXI RS Membrane x - imag./phase part

13 MYI RS Membrane y - imag./phase part

14 MXYI RS Membrane xy - imag./phase part

15 BMXI RS Bending x - imag./phase part

16 BMYI RS Bending y - imag./phase part

17 BMXYI RS Bending xy - imag./phase part

18 TXI RS Shear x - imag./phase part

19 TYI RS Shear y - imag./phase part

End TCODE,7

Words 3 through max repeat 005 times

......

NX Nastran 12 Release Guide 14-71 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

......

ELTYPE =189 Quadrilateral plate view element (VUQUAD)

TCODE,7 =0 Real

2 PARENT I Parent p-element identification number

3 COORD I Coordinate system identification number

4 ICORD CHAR4 Flat/curved and so on

5 THETA I Material angle

6 UNDEF None

7 VUID I VU-grid identification number ID for corner

8 MFX RS Membrane force x

9 MFY RS Membrane force y

10 MFXY RS Membrane force xy

11 UNDEF(3 ) None

14 BMX RS Bending moment x

15 BMY RS Bending moment y

16 BMXY RS Bending moment xy

17 SYZ RS Shear yz

18 SZX RS Shear zx

19 UNDEF None

TCODE,7 =1 Real/imaginary or magnitude/phase

2 PARENT I Parent p-element identification number

3 COORD I Coordinate system identification number

4 ICORD CHAR4 Flat/curved and so on

5 THETA I Material angle

6 UNDEF None

7 VUID I VU-grid identification number for corner

8 MFXR RS Membrane force x real/mag.

14-72 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

9 MFYR RS Membrane force y real/mag.

10 MFXYR RS Membrane force xy real/mag.

11 UNDEF(3 ) None

14 BMXR RS Bending moment x real/mag.

15 BMYR RS Bending moment y real/mag.

16 BMXYR RS Bending moment xy real/mag.

17 SYZR RS Shear yz real/mag.

18 SZXR RS Shear zx real/mag.

19 UNDEF None

20 MFXI RS Membrane force x imag./phase

21 MFYI RS Membrane force y imag./phase

22 MFXYI RS Membrane force xy imag./phase

23 UNDEF(3 ) None

26 BMXI RS Bending moment x imag./phase

27 BMYI RS Bending moment y imag./phase

28 BMXYI RS Bending moment xy imag./phase

29 SYZI RS Shear yz imag./phase

30 SZXI RS Shear zx imag./phase

31 UNDEF None

Words 7 through max repeat 004 times

End TCODE,7

Word Name Type Description

ELTYPE =190 Triangular shell view element (VUTRIA)

TCODE,7 =0 Real

2 PARENT I Parent p-element identification number

3 COORD I Coordinate system identification number

NX Nastran 12 Release Guide 14-73 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

4 ICORD CHAR4 Flat/curved and so on

5 THETA I Material angle

6 UNDEF None

7 VUID I VU grid ID for this corner

8 MFX RS Membrane force x

9 MFY RS Membrane force y

10 MFXY RS Membrane force xy

11 UNDEF(3 ) None

14 BMX RS Bending moment x

15 BMY RS Bending moment y

16 BMXY RS Bending moment xy

17 SYZ RS Shear yz

18 SZX RS Shear zx

19 UNDEF None

TCODE,7 =1 Real/imaginary or magnitude/phase

2 PARENT I Parent p-element identification number

3 COORD I Coordinate system identification number

4 ICORD CHAR4 Flat/curved and so on

5 THETA I Material angle

6 UNDEF None

7 VUID I VU grid ID this corner

8 MFXR RS Membrane force x real/mag.

9 MFYR RS Membrane force y real/mag.

10 MFXYR RS Membrane force xy real/mag.

11 UNDEF(3 ) None

14 BMXR RS Bending moment x real/mag.

15 BMYR RS Bending moment y real/mag.

14-74 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

16 BMXYR RS Bending moment xy real/mag.

17 SYZR RS Shear yz real/mag.

18 SZXR RS Shear zx real/mag.

19 UNDEF None

20 MFXI RS Membrane force x imag./phase

21 MFYI RS Membrane force y imag./phase

22 MFXYI RS Membrane force xy imag./phase

23 UNDEF(3 ) None

26 BMXI RS Bending moment x imag./phase

27 BMYI RS Bending moment y imag./phase

28 BMXYI RS Bending moment xy imag./phase

29 SYZI RS Shear yz imag./phase

30 SZXI RS Shear zx imag./phase

31 UNDEF None

Words 7 through max repeat 003 times

End TCODE,7

ELTYPE =191 Beam view element (VUBEAM)

TCODE,7 =0 Real

2 PARENT I Parent p-element identification number

3 COORD I Coordinate system identification number

4 ICORD CHAR4 Flat/curved and so on

5 VUGRID I VU grid ID for output grid

6 POSIT RS x/L position of VU grid identification number

7 FORCEX RS Force x

8 SHEARY RS Shear force y

9 SHEARZ RS Shear force z

10 TORSION RS Torsional moment x

NX Nastran 12 Release Guide 14-75 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

11 BENDY RS Bending moment y

12 BENDZ RS Bending moment z

TCODE,7 =1 Real/imaginary or magnitude/phase

2 PARENT I Parent p-element identification number

3 COORD I Coordinate system identification number

4 ICORD CHAR4 Flat/curved and so on

5 VUGRID I VU grid identification number for output grid

6 POSIT RS x/L position of VU grid identification number

7 FORCEXR RS Force x real/mag.

8 SHEARYR RS Shear force y real/mag.

9 SHEARZR RS Shear force z real/mag.

10 TORSINR RS Torsional moment x real/mag.

11 BENDYR RS Bending moment y real/mag.

12 BENDZR RS Bending moment z real/mag.

13 FORCEXI RS Force x imag./phase

14 SHEARYI RS Shear force y imag./phase

15 SHEARZI RS Shear force z imag./phase

16 TORSINI RS Torsional moment x imag./phase

17 BENDYI RS Bending moment y imag./phase

18 BENDZI RS Bending moment z imag./phase

Words 5 through max repeat 2 times

End TCODE,7

......

Word Name Type Description

......

ELTYPE =229 Triangular plate element (CTRIA3)

14-76 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

TCODE,7 =0 or 2 Real

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids or corner grid ID

4 MX RS Membrane force in x

5 MY RS Membrane force in y

6 MXY RS Membrane force in xy

7 BMX RS Bending moment in x

8 BMY RS Bending moment in y

9 BMXY RS Bending moment in xy

10 TX RS Shear force in x

11 TY RS Shear force in y

TCODE,7 =1 Real/imaginary or magnitude/phase

2 TERM CHAR4 Character string "CEN/"

3 GRID I Number of active grids or corner grid ID

4 MXR RS Membrane in x - real/mag. part

5 MYR RS Membrane in y - real/mag. part

6 MXYR RS Membrane in xy - real/mag. part

7 BMXR RS Bending in x - real/mag. part

8 BMYR RS Bending in y - real/mag. part

9 BMXYR RS Bending in xy - real/mag. part

10 TXR RS Shear in x - real/mag. part

11 TYR RS Shear in y - real/mag. part

12 MXI RS Membrane in x - imag./phase part

13 MYI RS Membrane in y - imag./phase part

14 MXYI RS Membrane in xy - imag./phase part

15 BMXI RS Bending in x - imag./phase part

16 BMYI RS Bending in y - imag./phase part

NX Nastran 12 Release Guide 14-77 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

17 BMXYI RS Bending in xy - imag./phase part

18 TXI RS Shear in x - imag./phase part

19 TYI RS Shear in y - imag./phase part

Words 3 through max repeat 4 times

End TCODE,7

Word Name Type Description

ELTYPE =341 Triangular shell element (CTRIA3) for SOL 401

TCODE,7 =0 Real

2 THETA RS Material property orientation angle in degrees

3 GRID I Grid point identification number

4 MX RS Membrane in x

5 MY RS Membrane in y

6 MXY RS Membrane in xy

7 BMX RS Bending in x

8 BMY RS Bending in y

9 BMXY RS Bending in xy

10 TX RS Transverse shear in x

11 TY RS Transverse shear in y

Words 3 thru 11 repeat 3 times

Word Name Type Description

ELTYPE =342 Quadrilateral shell element (CQUAD4) for SOL 401

TCODE,7 =0 Real

2 THETA RS Material property orientation angle in degrees

3 GRID I Grid point identification number

4 MX RS Membrane in x

5 MY RS Membrane in y

14-78 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

6 MXY RS Membrane in xy

7 BMX RS Bending in x

8 BMY RS Bending in y

9 BMXY RS Bending in xy

10 TX RS Transverse shear in x

11 TY RS Transverse shear in y

Words 3 thru 11 repeat 4 times

Word Name Type Description

ELTYPE =343 Triangular shell element (CTRIA6) for SOL 401

TCODE,7 =0 Real

2 THETA RS Material property orientation angle in degrees

3 GRID I Grid point identification number

4 MX RS Membrane in x

5 MY RS Membrane in y

6 MXY RS Membrane in xy

7 BMX RS Bending in x

8 BMY RS Bending in y

9 BMXY RS Bending in xy

10 TX RS Transverse shear in x

11 TY RS Transverse shear in y

Words 3 thru 11 repeat 3 times

Word Name Type Description

ELTYPE =344 Quadrilateral shell element (CQUAD8) for SOL 401

TCODE,7 =0 Real

2 THETA RS Material property orientation angle in degrees

3 GRID I Grid point identification number

NX Nastran 12 Release Guide 14-79 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

4 MX RS Membrane in x

5 MY RS Membrane in y

6 MXY RS Membrane in xy

7 BMX RS Bending in x

8 BMY RS Bending in y

9 BMXY RS Bending in xy

10 TX RS Transverse shear in x

11 TY RS Transverse shear in y

Words 3 thru 11 repeat 4 times

Word Name Type Description

ELTYPE =345 Triangular shell element (CTRIAR) for SOL 401

TCODE,7 =0 Real

2 THETA RS Material property orientation angle in degrees

3 GRID I Grid point identification number

4 MX RS Membrane in x

5 MY RS Membrane in y

6 MXY RS Membrane in xy

7 BMX RS Bending in x

8 BMY RS Bending in y

9 BMXY RS Bending in xy

10 TX RS Transverse shear in x

11 TY RS Transverse shear in y

Words 3 thru 11 repeat 3 times

Word Name Type Description

ELTYPE =346 Quadrilateral shell element (CQUADR) for SOL 401

TCODE,7 =0 Real

14-80 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

2 THETA RS Material property orientation angle in degrees

3 GRID I Grid point identification number

4 MX RS Membrane in x

5 MY RS Membrane in y

6 MXY RS Membrane in xy

7 BMX RS Bending in x

8 BMY RS Bending in y

9 BMXY RS Bending in xy

10 TX RS Transverse shear in x

11 TY RS Transverse shear in y

Words 3 thru 11 repeat 4 times

Word Name Type Description

ELTYPE =347 Bar element (CBAR) for SOL 401

TCODE,7 =0 Real

2 GRID I Grid point identification number

3 BM1 RS Bending moment plane 1

4 BM2 RS Bending moment plane 2

5 TS1 RS Shear plane 1

6 TS2 RS Shear plane 2

7 AF RS Axial force

8 TTRQ RS Total torque

9 WTRQ RS Warping torque

Words 2 thru 9 repeat 2 times

Word Name Type Description

ELTYPE =348 Beam element (CBEAM) for SOL 401

TCODE,7 =0 Real

NX Nastran 12 Release Guide 14-81 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

2 GRID I Grid point identification number

3 BM1 RS Bending moment plane 1

4 BM2 RS Bending moment plane 2

5 TS1 RS Shear plane 1

6 TS2 RS Shear plane 2

7 AF RS Axial force

8 TTRQ RS Total torque

9 WTRQ RS Warping torque

Words 2 thru 9 repeat 2 times

Word Name Type Description

ELTYPE =349 Bushing element (CBUSH1D) for SOL 401

TCODE,7 =0 Real

2 FX RS Axial force

Word Name Type Description

ELTYPE =350 Spring element (CELAS1) for SOL 401

TCODE,7 =0 Real

2 FX RS Axial force

Word Name Type Description

ELTYPE =351 Spring element (CELAS2) for SOL 401

TCODE,7 =0 Real

2 FX RS Axial force

Word Name Type Description

ELTYPE =352 Bushing element (CBUSH) for SOL 401

TCODE,7 =0 Real

14-82 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

2 FX I Force in x

3 FY RS Force in y

4 FZ RS Force in z

5 RX RS Moment in YZ

6 RY RS Moment in ZX

7 RZ RS Moment in XY

Word Name Type Description

ELTYPE =353 Reserved for CHEXCZ ELTYPE =354 Reserved for CPENTCZ ELTYPE =359 Reserved for PLOTEL3 ELTYPE =360 Reserved for PLOTEL4 ELTYPE =361 Reserved for PLOTEL6 ELTYPE =362 Reserved for PLOTEL8

Word Name Type Description

ELTYPE =363 Rod element (CROD) for SOL 402

TCODE,7 =0 Real

2 GRID I Grid point identification number

3 AF RS Axial force

4 TF RS Torsional force

Words 2 thru 4 repeat 2 times

Word Name Type Description

ELTYPE =364 Reserved for PLOTHEX ELTYPE =365 Reserved for PLOTTET ELTYPE =366 Reserved for PLOTPEN ELTYPE =367 Reserved for PLOTPYR ELTYPE =368 Reserved for ACFACE3 ELTYPE =369 Reserved for ACFACE4 ELTYPE =370 Reserved for ACFACE6 ELTYPE =371 Reserved for ACFACE8

NX Nastran 12 Release Guide 14-83 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Updated Notes

1. The RECORD=IDENT and DATA pair is repeated for each subcase.

2. For composite elements, ELTYPEs 95-98 and 355-358, OEF contains composite failure indices and the DATA record is repeated for each ply as well as each element. Also, the first EID of each element is Element ID, the subsequent EID=-1, then OFP module prints a blank line.

OERR

Updated Record - IDENT

Word Name Type Description

......

ACODE,4=06 Transient

5 TIME RS Current time step

6 UNDEF(4) None

ACODE,4=10 Nonlinear statics

5 LFTSFQ RS Load factor for SOL 401 arc-length only

6 TIME RS Time for SOL 401 arc-length only

7 AL_TOTAL RS Accumulated arc-length for SOL 401 arc-length only

8 UNDEF(2) None

End ACODE

......

OES

Updated Record - IDENT

Word Name Type Description

......

ACODE,4 = 10 Nonlinear statics

5 LFTSFQ RS Load factor for SOL 401 arc-length only

6 TIME RS Time for SOL 401 arc-length only

14-84 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

7 AL_TOTAL RS Accumulated arc-length for SOL 401 arc-length only

......

5 LSDVMN I Load set, mode number, time step, and so on. For composites this is 10*element_id+0 (do not output) or +1 (do output)

......

22 BDFIXCS I Body-fixed coordinate system flag for SOL 401 only: 0=in basic CS; 1=in body-fixed material CS

......

24 STRMEAS I Strain/stress measurement for SOL 401/402 only: 0=Engineering; 1=Green/PK2; 2=Log/Cauchy; 3=Biot; 4=Log/Kirchhoff

25 UNDEF None

......

Updated Record - DATA

Word Name Type Description

ELTYPE =189 Quadrilateral plate view element (VUQUAD)

SCODE,6 =0 Strain

TCODE,7 =0 Real

2 PARENT I Parent p-element identification number

3 COORD I CID coordinate system identification number

4 ICORD CHAR4 ICORD flat/curved and so on

5 THETA I THETA angle

6 ITYPE I ITYPE strcur =0, fiber=1

7 VUID I VU grid identification number for this corner

8 UNDEF(2) None

10 MSX RS Membrane stain x

NX Nastran 12 Release Guide 14-85 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

11 MSY RS Membrane strain y

12 MXY RS Membrane strain xy

13 UNDEF(3) None

16 BCX RS Bending curvature x

17 BCY RS Bending curvature y

18 BCXY RS Bending curvature xy

19 TYZ RS Shear yz

20 TZX RS Shear zx

21 UNDEF(3 ) None

Words 7 through 23 repeat 004 times

TCODE,7 =1 Real / Imaginary

2 PARENT I Parent p-element identification number

3 COORD I CID coordinate system identification number

4 ICORD CHAR4 ICORD flat/curved and so on

5 THETA I THETA angle

6 ITYPE I ITYPE strcur =0, fiber=1

7 VUID I VU grid identification number this corner

8 UNDEF(2 ) None

10 MSXR RS Membrane strain x RM

11 MSYR RS Membrane strain y RM

12 MXYR RS Membrane strain xy RM

13 UNDEF(3 ) None

16 BCXR RS Bending curvature x RM

17 BCYR RS Bending curvature y RM

18 BCXYR RS Bending curvature xy RM

19 TYZR RS Shear yz RM

20 TZXR RS Shear zx RM

14-86 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

21 UNDEF None

22 MSXI RS Membrane strain x IP

23 MSYI RS Membrane strain y IP

24 MXYI RS Membrane strain xy IP

25 UNDEF(3 ) None

28 BCXI RS Bending curvature x IP

29 BCYI RS Bending curvature y IP

30 BCXYI RS Bending curvature xy IP

31 TYZI RS Shear yz IP

32 TZXI RS Shear zx IP

33 UNDEF None

Words 7 through 33 repeat 004 times

TCODE,7 =2 Random Response

2 UNDEF None

End TCODE,7

SCODE,6 =01 Stress

TCODE,7 =0 Real

2 PARENT I Parent p-element identification number

3 COORD I CID coordinate system identification number

4 ICORD CHAR4 ICORD flat/curved and so on

5 THETA I THETA angle

6 ITYPE I ITYPE strcur =0, fiber=1

7 VUID I VU grid identification number for this corner

8 Z1 RS Z1 fiber distance

9 Z2 RS Z2 fiber distance

10 NX1 RS Normal x at Z1

11 NY1 RS Normal y at Z1

NX Nastran 12 Release Guide 14-87 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

12 TXY1 RS Shear xy at Z1

13 ANGLE1 RS Shear Angle at Z1 or n/a

14 MJRP1 RS Major principal at Z1 or n/a

15 MNRP1 RS Minor principal at Z1 or n/a

16 MAXSV1 RS vonMises/Max.Shear at Z1 or n/a

17 NX2 RS Normal x at Z2

18 NY2 RS Normal y at Z2

19 TXY2 RS Shear xy at Z2

20 ANGLE2 RS Shear Angle at Z2 or n/a

21 MJRP2 RS Major principal at Z2 or n/a

22 MNRP2 RS Minor principal at Z2 or n/a

23 MAXSV2 RS vonMises/Max.Shear at Z2 or n/a

Words 7 through 23 repeat 004 times

TCODE,7 =1 Real / Imaginary

2 PARENT I Parent p-element identification number

3 COORD I CID coordinate system identification number

4 ICORD CHAR4 ICORD flat/curved and so on

5 THETA I THETA angle

6 ITYPE I ITYPE strcur =0, fiber=1

7 VUID I VU grid identification number for this corner

8 Z1 RS Z1 fiber distance

9 Z2 RS Z2 fiber distance

10 NX1R RS Normal x rm at Z1

11 NX1I RS Normal x ip at Z1

12 NY1R RS Normal y rm at Z1

13 NY1I RS Normal y ip at Z1

14 TXY1R RS Shear xy rm at Z1

14-88 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

15 TXY1I RS Shear xy ip at Z1

16 NZ1R RS Normal z rm at Z1 or n/a

17 NZ1I RS Normal z ip at Z1 or n/a

18 TYZ1R RS Shear yz rm at Z1 or n/a

19 TYZ1I RS Shear yz ip at Z1 or n/a

20 TZX1R RS Shear zx rm at Z1 or n/a

21 TZX1I RS Shear zx ip at Z1 or n/a

22 NX2R RS Normal x rm at Z2

23 NX2I RS Normal x ip at Z2

24 NY2R RS Normal y rm at Z2

25 NY2I RS Normal y ip at Z2

26 TXY2R RS Shear xy rm at Z2

27 TXY2I RS Shear xy ip at Z2

28 NZ2R RS Normal z rm at Z2 or n/a

29 NZ2I RS Normal z ip at Z2 or n/a

30 TYZ2R RS Shear yz rm at Z2 or n/a

31 TYZ2I RS Shear yz ip at Z2 or n/a

32 TZX2R RS Shear zx rm at Z2 or n/a

33 TZX2I RS Shear zx ip at Z2 or n/a

Words 7 through 33 repeat 004 times

TCODE,7 =2 Random Response

2 UNDEF None

End TCODE,7

End SCODE,6

Word Name Type Description

ELTYPE =190 Triangular shell view element (VUTRIA)

NX Nastran 12 Release Guide 14-89 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

SCODE,6 =0 Strain

TCODE,7 =0 Real

2 PARENT I Parent p-element identification number

3 COORD I CID coordinate system identification number

4 ICORD CHAR4 ICORD flat/curved and so on

5 THETA I THETA angle

6 ITYPE I ITYPE strcur =0, fiber=1

7 VUID I VU grid identification number for this corner

8 NONE(2) I Nothing

10 MSX RS Membrane stain x

11 MSY RS Membrane strain y

12 MXY RS Membrane strain xy

13 NONE(3) RS Nothing

16 BCX RS bending curvature x

17 BCY RS Bending curvature y

18 BCXY RS Bending curvature xy

19 TYZ RS Shear yz

20 TZX RS Shear zx

21 NONE(3) RS Nothing

Words 7 through 23 repeat 003 times

TCODE,7 =1 Real / Imaginary

2 PARENT I Parent p-element identification number

3 COORD I CID coordinate system identification number

4 ICORD CHAR4 ICORD flat/curved and so on

5 THETA I THETA angle

6 ITYPE I ITYPE strcur =0, fiber=1

7 VUID I VU grid identification number this corner

14-90 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

8 UNDEF(2 ) None

10 MSXR RS Membrane strain x RM

11 MSYR RS Membrane strain y RM

12 MXYR RS Membrane strain xy RM

13 UNDEF(3 ) None

16 BCXR RS Bending curvature x RM

17 BCYR RS Bending curvature y RM

18 BCXYR RS Bending curvature xy RM

19 TYZR RS Shear yz RM

20 TZXR RS Shear zx RM

21 UNDEF None

22 MSXI RS Membrane strain x IP

23 MSYI RS Membrane strain y IP

24 MXYI RS Membrane strain xy IP

25 UNDEF(3 ) None

28 BCXI RS Bending curvature x IP

29 BCYI RS Bending curvature y IP

30 BCXYI RS Bending curvature xy IP

31 TYZI RS Shear yz IP

32 TZXI RS Shear zx IP

33 UNDEF None

Words 7 through 33 repeat 003 times

TCODE,7 =2 Random Response

2 UNDEF None

End TCODE,7

SCODE,6 =01 Stress

TCODE,7 =0 Real

NX Nastran 12 Release Guide 14-91 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

2 PARENT I Parent p-element identification number

3 COORD I CID coordinate system identification number

4 ICORD CHAR4 ICORD flat/curved and so on

5 THETA I THETA angle

6 ITYPE I ITYPE strcur =0, fiber=1

7 VUID I VU grid identification number for this corner

8 Z1 RS Z1 fiber distance

9 Z2 RS Z2 fiber distance

10 NX1 RS Normal x at Z1

11 NY1 RS Normal y at Z1

12 TXY1 RS Shear xy at Z1

13 ANGLE1 RS Shear Angle at Z1 or n/a

14 MJRP1 RS Major principal at Z1 or n/a

15 MNRP1 RS Minor principal at Z1 or n/a

16 MAXSV1 RS vonMises/Max.Shear at Z1 or n/a

17 NX2 RS Normal x at Z2

18 NY2 RS Normal y at Z2

19 TXY2 RS Shear xy at Z2

20 ANGLE2 RS Shear Angle at Z2 or n/a

21 MJRP2 RS Major principal at Z2 or n/a

22 MNRP2 RS Minor principal at Z2 or n/a

23 MAXSV2 RS vonMises/Max.Shear at Z2 or n/a

Words 7 through 23 repeat 003 times

TCODE,7 =1 Real / Imaginary

2 PARENT I Parent p-element identification number

3 COORD I CID coordinate system identification number

4 ICORD CHAR4 ICORD flat/curved and so on

14-92 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

5 THETA I THETA angle

6 ITYPE I ITYPE strcur =0, fiber=1

7 VUID I VU grid identification number for this corner

8 Z1 RS Z1 fiber distance

9 Z2 RS Z2 fiber distance

10 NX1R RS Normal x rm at Z1

11 NX1I RS Normal x ip at Z1

12 NY1R RS Normal y rm at Z1

13 NY1I RS Normal y ip at Z1

14 TXY1R RS Shear xy rm at Z1

15 TXY1I RS Shear xy ip at Z1

16 NZ1R RS Normal z rm at Z1 or n/a

17 NZ1I RS Normal z ip at Z1 or n/a

18 TYZ1R RS Shear yz rm at Z1 or n/a

19 TYZ1I RS Shear yz ip at Z1 or n/a

20 TZX1R RS Shear zx rm at Z1 or n/a

21 TZX1I RS Shear zx ip at Z1 or n/a

22 NX2R RS Normal x rm at Z2

23 NX2I RS Normal x ip at Z2

24 NY2R RS Normal y rm at Z2

25 NY2I RS Normal y ip at Z2

26 TXY2R RS Shear xy rm at Z2

27 TXY2I RS Shear xy ip at Z2

28 NZ2R RS Normal z rm at Z2 or n/a

29 NZ2I RS Normal z ip at Z2 or n/a

30 TYZ2R RS Shear yz rm at Z2 or n/a

31 TYZ2I RS Shear yz ip at Z2 or n/a

NX Nastran 12 Release Guide 14-93 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

32 TZX2R RS Shear zx rm at Z2 or n/a

33 TZX2I RS Shear zx ip at Z2 or n/a

Words 7 through 33 repeat 003 times

TCODE,7 =2 Random Response

2 UNDEF None

End TCODE,7

End SCODE,6

......

ELTYPE =269 Composite HEXA element (CHEXAL)

SCODE,6=0 Strain

TCODE,7 =0 Real

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 E11 RS Normal strain in the 1-direction

6 E22 RS Normal strain in the 2-direction

7 E33 RS Normal strain in the 3-direction

8 E12 RS Shear strain in the 12-plane

9 E23 RS Shear strain in the 23-plane

10 E13 RS Shear strain in the 13-plane

11 ETMAX1 RS von Mises strain

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

14-94 NX Nastran 12 Release Guide Upward compatibility

5 E11 RS Normal strain in the 1-direction

6 E22 RS Normal strain in the 2-direction

7 E33 RS Normal strain in the 3-direction

8 E12 RS Shear strain in the 12-plane

9 E23 RS Shear strain in the 23-plane

10 E13 RS Shear strain in the 13-plane

11 ETMAX1 RS Von Mises strain

For each fiber location requested (PLSLOC), words 4 through 11 repeat 5 times.

TCODE,7 =1 Real/imaginary

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (Center = 0)

5 E11r RS Normal strain in the 1-direction, real part

6 E22r RS Normal strain in the 2-direction, real part

7 E33r RS Normal strain in the 3-direction, real part

8 E12r RS Shear strain in the 12-plane, real part

9 E23r RS Shear strain in the 23-plane, real part

10 E13r RS Shear strain in the 13-plane, real part

11 E11i RS Normal strain in the 1-direction, imaginary part

12 E22i RS Normal strain in the 2-direction, imaginary part

13 E33i RS Normal strain in the 3-direction, imaginary part

14 E12i RS Shear strain in the 12-plane, imaginary part

15 EL23i RS Shear strain in the 23-plane, imaginary part

16 EL13i RS Shear strain in the 13-plane, imaginary part

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

NX Nastran 12 Release Guide 14-95 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

4 GRID I Edge grid ID (Center = 0)

5 E11r RS Normal strain in the 1-direction, real part

6 E22r RS Normal strain in the 2-direction, real part

7 E33r RS Normal strain in the 3-direction, real part

8 E12r RS Shear strain in the 12-plane, real part

9 E23r RS Shear strain in the 23-plane, real part

10 E13r RS Shear strain in the 13-plane, real part

11 E11i RS Normal strain in the 1-direction, imaginary part

12 E22i RS Normal strain in the 2-direction, imaginary part

13 E33i RS Normal strain in the 3-direction, imaginary part

14 E12i RS Shear strain in the 12-plane, imaginary part

15 E23i RS Shear strain in the 23-plane, imaginary part

16 E13i RS Shear strain in the 13-plane, imaginary part

For each fiber location requested (PLSLOC), words 4 through 16 repeat 5 times.

TCODE,7 =2 Random Response

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 E11 RS Normal strain in the 1-direction

6 E22 RS Normal strain in the 2-direction

7 E33 RS Normal strain in the 3-direction

8 E12 RS Shear strain in the 12-plane

9 E23 RS Shear strain in the 23-plane

10 E13 RS Shear strain in the 13-plane

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

14-96 NX Nastran 12 Release Guide Upward compatibility

4 GRID I Edge grid ID (center=0)

5 E11 RS Normal strain in the 1-direction

6 E22 RS Normal strain in the 2-direction

7 E33 RS Normal strain in the 3-direction

8 E12 RS Shear strain in the 12-plane

9 E23 RS Shear strain in the 23-plane

10 E13 RS Shear strain in the 13-plane

For each fiber location requested (PLSLOC), words 4 through 10 repeat 5 times.

End TCODE,7

SCODE,6=1 Stress

TCODE,7 =0 Real

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 S11 RS Normal stress in the 1-direction

6 S22 RS Normal stress in the 2-direction

7 S33 RS Normal stress in the 3-direction

8 S12 RS Shear stress in the 12-plane

9 S23 RS Shear stress in the 23-plane

10 S13 RS Shear stress in the 13-plane

11 STMAX1 RS Von Mises stress

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 S11 RS Normal stress in the 1-direction

6 S22 RS Normal stress in the 2-direction

NX Nastran 12 Release Guide 14-97 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

7 S33 RS Normal stress in the 3-direction

8 S12 RS Shear stress in the 12-plane

9 S23 RS Shear stress in the 23-plane

10 S13 RS Shear stress in the 13-plane

11 STMAX1 RS Von Mises stress

For each fiber location requested (PLSLOC), words 4 through 11 repeat 5 times.

TCODE,7 =1 Real/imaginary

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (Center = 0)

5 S11r RS Normal stress in the 1-direction, real part

6 S22r RS Normal stress in the 2-direction, real part

7 S33r RS Normal stress in the 3-direction, real part

8 S12r RS Shear stress in the 12-plane, real part

9 S23r RS Shear stress in the 23-plane, real part

10 S13r RS Shear stress in the 13-plane, real part

11 S11i RS Normal stress in the 1-direction, imaginary part

12 S22i RS Normal stress in the 2-direction, imaginary part

13 S33i RS Normal stress in the 3-direction, imaginary part

14 S12i RS Shear stress in the 12-plane, imaginary part

15 S23i RS Shear stress in the 23-plane, imaginary part

16 S13i RS Shear stress in the 13-plane, imaginary part

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (Center = 0)

5 S11r RS Normal stress in the 1-direction, real part

14-98 NX Nastran 12 Release Guide Upward compatibility

6 S22r RS Normal stress in the 2-direction, real part

7 S33r RS Normal stress in the 3-direction, real part

8 S12r RS Shear stress in the 12-plane, real part

9 S23r RS Shear stress in the 23-plane, real part

10 S13r RS Shear stress in the 13-plane, real part

11 S11i RS Normal stress in the 1-direction, imaginary part

12 S22i RS Normal stress in the 2-direction, imaginary part

13 S33i RS Normal stress in the 3-direction, imaginary part

14 S12i RS Shear stress in the 12-plane, imaginary part

15 S23i RS Shear stress in the 23-plane, imaginary part

16 S13i RS Shear stress in the 13-plane, imaginary part

For each fiber location requested (PLSLOC), words 4 through 16 repeat 5 times.

TCODE,7 =2 Random Response

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 S11 RS Normal stress in the 1-direction

6 S22 RS Normal stress in the 2-direction

7 S33 RS Normal stress in the 3-direction

8 S12 RS Shear stress in the 12-plane

9 S23 RS Shear stress in the 23-plane

10 S13 RS Shear stress in the 13-plane

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 S11 RS Normal stress in the 1-direction

NX Nastran 12 Release Guide 14-99 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

6 S22 RS Normal stress in the 2-direction

7 S33 RS Normal stress in the 3-direction

8 S12 RS Shear stress in the 12-plane

9 S23 RS Shear stress in the 23-plane

10 S13 RS Shear stress in the 13-plane

For each fiber location requested (PLSLOC), words 4 through 10 repeat 5 times.

End TCODE,7

End SCODE,6

ELTYPE =270 Composite PENTA element (CPENTAL)

SCODE,6=0 Strain

TCODE,7 =0 Real

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 E11 RS Normal strain in the 1-direction

6 E22 RS Normal strain in the 2-direction

7 E33 RS Normal strain in the 3-direction

8 E12 RS Shear strain in the 12-plane

9 E23 RS Shear strain in the 23-plane

10 E13 RS Shear strain in the 13-plane

11 ETMAX1 RS Von Mises strain

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 E11 RS Normal strain in the 1-direction

14-100 NX Nastran 12 Release Guide Upward compatibility

6 E22 RS Normal strain in the 2-direction

7 E33 RS Normal strain in the 3-direction

8 E12 RS Shear strain in the 12-plane

9 E23 RS Shear strain in the 23-plane

10 E13 RS Shear strain in the 13-plane

11 ETMAX1 RS Von Mises strain

For each fiber location requested (PLSLOC), words 4 through 11 repeat 4 times.

TCODE,7 =1 Real/imaginary

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (Center = 0)

5 E11r RS Normal strain in the 1-direction, real part

6 E22r RS Normal strain in the 2-direction, real part

7 E33r RS Normal strain in the 3-direction, real part

8 E12r RS Shear strain in the 12-plane, real part

9 E23r RS Shear strain in the 23-plane, real part

10 E13r RS Shear strain in the 13-plane, real part

11 E11i RS Normal strain in the 1-direction, imaginary part

12 E22i RS Normal strain in the 2-direction, imaginary part

13 E33i RS Normal strain in the 3-direction, imaginary part

14 E12i RS Shear strain in the 12-plane, imaginary part

15 E23i RS Shear strain in the 23-plane, imaginary part

16 E13i RS Shear strain in the 13-plane, imaginary part

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (Center = 0)

NX Nastran 12 Release Guide 14-101 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

5 E11r RS Normal strain in the 1-direction, real part

6 E22r RS Normal strain in the 2-direction, real part

7 E33r RS Normal strain in the 3-direction, real part

8 E12r RS Shear strain in the 12-plane, real part

9 E23r RS Shear strain in the 23-plane, real part

10 E13r RS Shear strain in the 13-plane, real part

11 E11i RS Normal strain in the 1-direction, imaginary part

12 E22i RS Normal strain in the 2-direction, imaginary part

13 E33i RS Normal strain in the 3-direction, imaginary part

14 E12i RS Shear strain in the 12-plane, imaginary part

15 E23i RS Shear strain in the 23-plane, imaginary part

16 E13i RS Shear strain in the 13-plane, imaginary part

For each fiber location requested (PLSLOC), words 4 through 16 repeat 4 times.

TCODE,7 =2 Random Response

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 E11 RS Normal strain in the 1-direction

6 E22 RS Normal strain in the 2-direction

7 E33 RS Normal strain in the 3-direction

8 E12 RS Shear strain in the 12-plane

9 E23 RS Shear strain in the 23-plane

10 E13 RS Shear strain in the 13-plane

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

14-102 NX Nastran 12 Release Guide Upward compatibility

5 E11 RS Normal strain in the 1-direction

6 E22 RS Normal strain in the 2-direction

7 E33 RS Normal strain in the 3-direction

8 E12 RS Shear strain in the 12-plane

9 E23 RS Shear strain in the 23-plane

10 E13 RS Shear strain in the 13-plane

For each fiber location requested (PLSLOC), words 4 through 10 repeat 4 times.

End TCODE,7

SCODE,6=1 Stress

TCODE,7 =0 Real

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 S11 RS Normal stress in the 1-direction

6 S22 RS Normal stress in the 2-direction

7 S33 RS Normal stress in the 3-direction

8 S12 RS Shear stress in the 12-plane

9 S23 RS Shear stress in the 23-plane

10 S13 RS Shear stress in the 13-plane

11 STMAX1 RS Von Mises stress

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 S11 RS Normal stress in the 1-direction

6 S22 RS Normal stress in the 2-direction

7 S33 RS Normal stress in the 3-direction

NX Nastran 12 Release Guide 14-103 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

8 S12 RS Shear stress in the 12-plane

9 S23 RS Shear stress in the 23-plane

10 S13 RS Shear stress in the 13-plane

11 STMAX1 RS Von Mises stress

For each fiber location requested (PLSLOC), words 4 through 11 repeat 4 times.

TCODE,7 =1 Real/imaginary

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (Center = 0)

5 S11r RS Normal stress in the 1-direction, real part

6 S22r RS Normal stress in the 2-direction, real part

7 S33r RS Normal stress in the 3-direction, real part

8 S12r RS Shear stress in the 12-plane, real part

9 S23r RS Shear stress in the 23-plane, real part

10 S13r RS Shear stress in the 13-plane, real part

11 S11i RS Normal stress in the 1-direction, imaginary part

12 S22i RS Normal stress in the 2-direction, imaginary part

13 S33i RS Normal stress in the 3-direction, imaginary part

14 S12i RS Shear stress in the 12-plane, imaginary part

15 S23i RS Shear stress in the 23-plane, imaginary part

16 S13i RS Shear stress in the 13-plane, imaginary part

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (Center = 0)

5 S11r RS Normal stress in the 1-direction, real part

6 S22r RS Normal stress in the 2-direction, real part

14-104 NX Nastran 12 Release Guide Upward compatibility

7 S33r RS Normal stress in the 3-direction, real part

8 S12r RS Shear stress in the 12-plane, real part

9 S23r RS Shear stress in the 23-plane, real part

10 S13r RS Shear stress in the 13-plane, real part

11 S11i RS Normal stress in the 1-direction, imaginary part

12 S22i RS Normal stress in the 2-direction, imaginary part

13 S33i RS Normal stress in the 3-direction, imaginary part

14 S12i RS Shear stress in the 12-plane, imaginary part

15 S23i RS Shear stress in the 23-plane, imaginary part

16 S13i RS Shear stress in the 13-plane, imaginary part

For each fiber location requested (PLSLOC), words 4 through 16 repeat 4 times.

TCODE,7 =2 Random Response

Q4CSTR=0 Center option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 S11 RS Normal stress in the 1-direction

6 S22 RS Normal stress in the 2-direction

7 S33 RS Normal stress in the 3-direction

8 S12 RS Shear stress in the 12-plane

9 S23 RS Shear stress in the 23-plane

10 S13 RS Shear stress in the 13-plane

Q4CSTR=1 Center and Corner option

2 PLY I Lamina number

3 FLOC CHAR4 Fiber location (BOT, MID, TOP)

4 GRID I Edge grid ID (center=0)

5 S11 RS Normal stress in the 1-direction

6 S22 RS Normal stress in the 2-direction

NX Nastran 12 Release Guide 14-105 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

7 S33 RS Normal stress in the 3-direction

8 S12 RS Shear stress in the 12-plane

9 S23 RS Shear stress in the 23-plane

10 S13 RS Shear stress in the 13-plane

For each fiber location requested (PLSLOC), words 4 through 10 repeat 4 times.

End TCODE,7

End SCODE,6

ELTYPE =304 Linear composite HEXA element (CHEXAL)

SCODE,6=0 Strain

1 PLY I Lamina number

2 FLOC CHAR4 Fiber location (BOT, MID, TOP)

3 GRID I Edge grid ID (center=0)

4 EX1 RS Normal strain in the 1-direction

5 EY1 RS Normal strain in the 2-direction

6 EZ1 RS Normal strain in the 3-direction

7 ET1 RS Shear strain in the 12-plane

8 EL2 RS Shear strain in the 23-plane

9 EL1 RS Shear strain in the 13-plane

10 ETMAX1 RS von Mises strain

For each fiber location requested (PLSLOC), words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

1 PLY I Lamina number

2 FLOC CHAR4 Fiber location (BOT, MID, TOP)

3 GRID I Edge grid ID (center=0)

4 SX1 RS Normal stress in the 1-direction

5 SY1 RS Normal stress in the 2-direction

14-106 NX Nastran 12 Release Guide Upward compatibility

6 SZ1 RS Normal stress in the 3-direction

7 ST1 RS Shear stress in the 12-plane

8 SL2 RS Shear stress in the 23-plane

9 SL1 RS Shear stress in the 13-plane

10 STMAX1 RS von Mises stress

For each fiber location requested (PLSLOC), words 3 through 10 repeat 4 times.

End SCODE,6

ELTYPE =305 Linear composite PENTA element (CPENTAL)

SCODE,6=0 Strain

1 PLY I Lamina number

2 FLOC CHAR4 Fiber location (BOT, MID, TOP)

3 GRID I Edge grid ID (center=0)

4 EX1 RS Normal strain in the 1-direction

5 EY1 RS Normal strain in the 2-direction

6 EZ1 RS Normal strain in the 3-direction

7 ET1 RS Shear strain in the 12-plane

8 EL2 RS Shear strain in the 23-plane

9 EL1 RS Shear strain in the 13-plane

10 ETMAX1 RS von Mises strain

For each fiber location requested (PLSLOC), words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

1 PLY I Lamina number

2 FLOC CHAR4 Fiber location (BOT, MID, TOP)

3 GRID I Edge grid ID (center=0)

4 SX1 RS Normal stress in the 1-direction

NX Nastran 12 Release Guide 14-107 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

5 SY1 RS Normal stress in the 2-direction

6 SZ1 RS Normal stress in the 3-direction

7 ST1 RS Shear stress in the 12-plane

8 SL2 RS Shear stress in the 23-plane

9 SL1 RS Shear stress in the 13-plane

10 STMAX1 RS von Mises stress

For each fiber location requested (PLSLOC), words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =306 Nonlinear composite HEXA element (CHEXALN)

SCODE,6=0 Strain

1 PLY I Lamina number

2 FLOC CHAR4 Fiber location (BOT, MID, TOP)

3 GRID I Edge grid ID (center=0)

4 EX1 RS Normal strain in the 1-direction

5 EY1 RS Normal strain in the 2-direction

6 EZ1 RS Normal strain in the 3-direction

7 ET1 RS Shear strain in the 12-plane

8 EL2 RS Shear strain in the 23-plane

9 EL1 RS Shear strain in the 13-plane

10 ETMAX1 RS von Mises strain

For each fiber location requested (PLSLOC), words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

1 PLY I Lamina number

2 FLOC CHAR4 Fiber location (BOT, MID, TOP)

3 GRID I Edge grid ID (center=0)

4 SX1 RS Normal stress in the 1-direction

14-108 NX Nastran 12 Release Guide Upward compatibility

5 SY1 RS Normal stress in the 2-direction

6 SZ1 RS Normal stress in the 3-direction

7 ST1 RS Shear stress in the 12-plane

8 SL2 RS Shear stress in the 23-plane

9 SL1 RS Shear stress in the 13-plane

10 STMAX1 RS von Mises stress

For each fiber location requested (PLSLOC), words 3 through 10 repeat 4 times.

End SCODE,6

ELTYPE =307 Nonlinear composite PENTA element (CPENTALN)

SCODE,6=0 Strain

1 PLY I Lamina number

2 FLOC CHAR4 Fiber location (BOT, MID, TOP)

3 GRID I Edge grid ID (center=0)

4 EX1 RS Normal strain in the 1-direction

5 EY1 RS Normal strain in the 2-direction

6 EZ1 RS Normal strain in the 3-direction

7 ET1 RS Shear strain in the 12-plane

8 EL2 RS Shear strain in the 23-plane

9 EL1 RS Shear strain in the 13-plane

10 ETMAX1 RS von Mises strain

For each fiber location requested (PLSLOC), words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

1 PLY I Lamina number

2 FLOC CHAR4 Fiber location (BOT, MID, TOP)

3 GRID I Edge grid ID (center=0)

4 SX1 RS Normal stress in the 1-direction

NX Nastran 12 Release Guide 14-109 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

5 SY1 RS Normal stress in the 2-direction

6 SZ1 RS Normal stress in the 3-direction

7 ST1 RS Shear stress in the 12-plane

8 SL2 RS Shear stress in the 23-plane

9 SL1 RS Shear stress in the 13-plane

10 STMAX1 RS von Mises stress

For each fiber location requested (PLSLOC), words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =312 Axisymmetric tria element (TRAX3)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

14-110 NX Nastran 12 Release Guide Upward compatibility

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =313 Axisymmetric quad element (QUADX4)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

TCODE,7=0 Real

NX Nastran 12 Release Guide 14-111 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 4 times.

End SCODE,6

ELTYPE =314 Axisymmetric tria element (TRAX6)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 3 times.

14-112 NX Nastran 12 Release Guide Upward compatibility

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =315 Axisymmetric quad element (QUADX8)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

NX Nastran 12 Release Guide 14-113 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

10 EVM RS von Mises strain

Words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 4 times.

End SCODE,6

ELTYPE =316 Plane strain tria element (PLSTN3)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

14-114 NX Nastran 12 Release Guide Upward compatibility

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =317 Plane strain quad element (PLSTN4)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

NX Nastran 12 Release Guide 14-115 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 4 times.

End SCODE,6

ELTYPE =318 Plane strain tria element (PLSTN6)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

14-116 NX Nastran 12 Release Guide Upward compatibility

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =319 Plane strain quad element (PLSTN8)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

NX Nastran 12 Release Guide 14-117 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 4 times.

End SCODE,6

ELTYPE =320 Plane stress tria element (PLSTS3)

SCODE,6=0 Strain

14-118 NX Nastran 12 Release Guide Upward compatibility

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =321 Plane stress quad element (PLSTS4)

NX Nastran 12 Release Guide 14-119 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 4 times.

End SCODE,6

14-120 NX Nastran 12 Release Guide Upward compatibility

ELTYPE =322 Plane stress tria element (PLSTS6)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 3 times.

NX Nastran 12 Release Guide 14-121 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

End SCODE,6

ELTYPE =323 Plane stress quad element (PLSTS8)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

14-122 NX Nastran 12 Release Guide Upward compatibility

10 SVM RS von Mises stress

Words 3 through 10 repeat 4 times.

End SCODE,6

ELTYPE =328 Generalized plane strain tria element (GPLSTN3)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

NX Nastran 12 Release Guide 14-123 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =329 Generalized plane strain quad element (GPLSTN4)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

14-124 NX Nastran 12 Release Guide Upward compatibility

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 4 times.

End SCODE,6

ELTYPE =330 Generalized plane strain tria element (GPLSTN6)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

NX Nastran 12 Release Guide 14-125 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =331 Generalized plane strain quad element (GPLSTN8)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

14-126 NX Nastran 12 Release Guide Upward compatibility

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 4 times.

End SCODE,6

ELTYPE =337 Chocking triangular element (CHOCK3)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

NX Nastran 12 Release Guide 14-127 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =338 Chocking quad element (CHOCK4)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

14-128 NX Nastran 12 Release Guide Upward compatibility

Words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 4 times.

End SCODE,6

ELTYPE =339 Chocking triangular element (CHOCK6)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

NX Nastran 12 Release Guide 14-129 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 3 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 3 times.

End SCODE,6

ELTYPE =340 Chocking quad element (CHOCK8)

SCODE,6=0 Strain

TODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 EX RS Normal strain in the X-direction

5 EY RS Normal strain in the Y-direction

6 EZ RS Normal strain in the Z-direction

14-130 NX Nastran 12 Release Guide Upward compatibility

7 EXY RS Shear strain in the XY-plane

8 EYZ RS Shear strain in the YZ-plane

9 EZX RS Shear strain in the ZX-plane

10 EVM RS von Mises strain

Words 3 through 10 repeat 4 times.

SCODE,6=1 Stress

TCODE,7=0 Real

1 THETA RS Material orientation angle

2 CTYPE CHAR4 Grid or Gauss

3 GRID I External grid ID

4 SX RS Normal stress in the X-direction

5 SY RS Normal stress in the Y-direction

6 SZ RS Normal stress in the Z-direction

7 SXY RS Shear stress in the XY-plane

8 SYZ RS Shear stress in the YZ-plane

9 SZX RS Shear stress in the ZX-plane

10 SVM RS von Mises stress

Words 3 through 10 repeat 4 times.

End SCODE,6

Word Name Type Description

ELTYPE =347 Bar element for SOL 401 (CBAR)

SCODE,6=0 Strain

TCODE,7 =0 Real

2 GRID I External grid point ID

3 EXC RS Longitudinal strain at Point C

4 EXD RS Longitudinal strain at Point D

5 EXE RS Longitudinal strain at Point E

NX Nastran 12 Release Guide 14-131 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

6 EXF RS Longitudinal strain at Point F

Words 2 through 6 repeat 2 times

SCODE,6=1 Stress

TCODE,7 =0 Real

2 GRID I External grid point ID

3 SXC RS Longitudinal stress at Point C

4 SXD RS Longitudinal stress at Point D

5 SXE RS Longitudinal stress at Point E

6 SXF RS Longitudinal stress at Point F

Words 2 through 6 repeat 2 times

End SCODE,6

Word Name Type Description

ELTYPE =348 Beam element for SOL 401 (CBEAM)

SCODE,6=0 Strain

TCODE,7 =0 Real

2 GRID I External grid point ID

3 EXC RS Longitudinal strain at Point C

4 EXD RS Longitudinal strain at Point D

5 EXE RS Longitudinal strain at Point E

6 EXF RS Longitudinal strain at Point F

Words 2 through 6 repeat 2 times

SCODE,6=1 Stress

TCODE,7 =0 Real

2 GRID I External grid point ID

3 SXC RS Longitudinal stress at Point C

4 SXD RS Longitudinal stress at Point D

14-132 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

5 SXE RS Longitudinal stress at Point E

6 SXF RS Longitudinal stress at Point F

Words 2 through 6 repeat 2 times

End SCODE,6

Word Name Type Description

ELTYPE =349 Bushing element for SOL 401 (CBUSH1D)

SCODE,6=0 Strain

TCODE,7 =0 Real

2 ST RS Axial strain

SCODE,6=1 Stress

TCODE,7 =0 Real

2 ST RS Axial stress

End SCODE,6

Word Name Type Description

ELTYPE =350 Spring element for SOL 401 (CELAS1)

SCODE,6=0 Strain

TCODE,7 =0 Real

2 ST RS Axial strain

SCODE,6=1 Stress

TCODE,7 =0 Real

2 ST RS Axial stress

End SCODE,6

Word Name Type Description

ELTYPE =351 Spring element for SOL 401 (CELAS2)

SCODE,6=0 Strain

NX Nastran 12 Release Guide 14-133 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

TCODE,7 =0 Real

2 ST RS Axial strain

SCODE,6=1 Stress

TCODE,7 =0 Real

2 ST RS Axial stress

End SCODE,6

Word Name Type Description

ELTYPE =352 Bushing element for SOL 401 (CBUSH)

SCODE,6=0 Strain

TCODE,7 =0 Real

2 SXX RS Strain in x

3 SYY RS Strain in y

4 SZZ RS Strain in z

5 SXY RS Strain in xy

6 SYZ RS Strain in yz

7 SZX RS Strain in zx

SCODE,6=1 Stress

TCODE,7 =0 Real

2 SXX RS Stress in x

3 SYY RS Stress in y

4 SZZ RS Stress in z

5 SXY RS Stress in xy

6 SYZ RS Stress in yz

7 SZX RS Stress in zx

End SCODE,6

14-134 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

ELTYPE =355 Composite triangular shell element (CTRIA6)

SCODE,6=0 Strain

TCODE,7 =0 Real

2 PLY I Lamina number

3 THETA RS Material orientation angle

4 GRID I External grid ID

5 EX1 RS Normal -1

6 EY1 RS Normal -2

7 EZ1 RS Normal -3

8 ET1 RS Shear-12

9 EL2 RS Shear-2Z

10 EL1 RS Shear-1Z

11 ETMAX1 RS von Mises

Words 4 through 11 repeat 3 times

SCODE,6=1 Stress

TCODE,7 =0 Real

2 PLY I Lamina number

3 THETA RS Material orientation angle

4 GRID I External grid ID

5 SX1 RS Normal -1

6 SY1 RS Normal -2

7 SZ1 RS Normal -3

8 ST1 RS Shear-12

9 SL2 RS Shear-2Z

10 SL1 RS Shear-1Z

11 TMAX1 RS von Mises

Words 4 through 11 repeat 3 times

NX Nastran 12 Release Guide 14-135 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

End SCODE,6

Word Name Type Description

ELTYPE =356 Composite quadrilateral shell element (CQUAD8)

SCODE,6=0 Strain

TCODE,7 =0 Real

2 PLY I Lamina number

3 THETA RS Material orientation angle

4 GRID I External grid ID

5 EX1 RS Normal -1

6 EY1 RS Normal -2

7 EZ1 RS Normal -3

8 ET1 RS Shear-12

9 EL2 RS Shear-2Z

10 EL1 RS Shear-1Z

11 ETMAX1 RS von Mises

Words 4 through 11 repeat 4 times

SCODE,6=1 Stress

TCODE,7 =0 Real

2 PLY I Lamina number

3 THETA RS Material orientation angle

4 GRID I External grid ID

5 SX1 RS Normal -1

6 SY1 RS Normal -2

7 SZ1 RS Normal -3

8 ST1 RS Shear-12

9 SL2 RS Shear-2Z

14-136 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

10 SL1 RS Shear-1Z

11 TMAX1 RS von Mises

Words 4 through 11 repeat 4 times

End SCODE,6

Word Name Type Description

ELTYPE =357 Composite triangular shell element (CTRIAR)

SCODE,6=0 Strain

TCODE,7 =0 Real

2 PLY I Lamina number

3 THETA RS Material orientation angle

4 GRID I External grid ID

5 EX1 RS Normal -1

6 EY1 RS Normal -2

7 EZ1 RS Normal -3

8 ET1 RS Shear-12

9 EL2 RS Shear-2Z

10 EL1 RS Shear-1Z

11 ETMAX1 RS von Mises

Words 4 through 11 repeat 3 times

SCODE,6=1 Stress

TCODE,7 =0 Real

2 PLY I Lamina number

3 THETA RS Material orientation angle

4 GRID I External grid ID

5 SX1 RS Normal -1

6 SY1 RS Normal -2

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Word Name Type Description

7 SZ1 RS Normal -3

8 ST1 RS Shear-12

9 SL2 RS Shear-2Z

10 SL1 RS Shear-1Z

11 TMAX1 RS von Mises

Words 4 through 11 repeat 3 times

End SCODE,6

Word Name Type Description

ELTYPE =358 Composite quadrilateral shell element (CQUADR)

SCODE,6=0 Strain

TCODE,7 =0 Real

2 PLY I Lamina number

3 THETA RS Material orientation angle

4 GRID I External grid ID

5 EX1 RS Normal -1

6 EY1 RS Normal -2

7 EZ1 RS Normal -3

8 ET1 RS Shear-12

9 EL2 RS Shear-2Z

10 EL1 RS Shear-1Z

11 ETMAX1 RS von Mises

Words 4 through 11 repeat 4 times

SCODE,6=1 Stress

TCODE,7 =0 Real

2 PLY I Lamina number

3 THETA RS Material orientation angle

14-138 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

4 GRID I External grid ID

5 SX1 RS Normal -1

6 SY1 RS Normal -2

7 SZ1 RS Normal -3

8 ST1 RS Shear-12

9 SL2 RS Shear-2Z

10 SL1 RS Shear-1Z

11 TMAX1 RS von Mises

Words 4 through 11 repeat 4 times

End SCODE,6

Word Name Type Description

ELTYPE =363 Rod element for SOL 402 (CROD)

SCODE,6=0 Strain

TCODE,7 =0 Real

2 GRID I External grid point ID

3 AE RS Axial strain

4 TE RS Torsional strain

Words 2 through 4 repeat 2 times

SCODE,6=1 Stress

TCODE,7 =0 Real

2 GRID I External grid point ID

3 AE RS Axial stress

4 TE RS Torsional stress

Words 2 through 4 repeat 2 times

End SCODE,6

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OGF

Updated Record - IDENT

Word Name Type Description

1 ACODE(C) I Device code + 10*Approach code

2 TCODE(C) I Table code; always 19

3 UNDEF None

4 SUBCASE I Subcase identification number

TCODE,1=01

ACODE,4=0

5 UNDEF(2) None Not defined

ACODE,4=01 Statics

5 UNDEF None See word 8

6 UNDEF None

ACODE,4=02 Real Eigenvalues

5 MODE I Mode Number

6 UNDEF None

ACODE,4=03 Differential Stiffness 0

5 UNDEF None See word 8

6 UNDEF None

ACODE,4=04 Differential Stiffness 1

5 UNDEF None See word 8

6 UNDEF None

ACODE,4=05 Frequency

5 FREQ RS Frequency

6 UNDEF None

ACODE,4=06 Transient

5 TIME RS Time step

6 UNDEF None

14-140 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

ACODE,4=07 Buckling 0 (Pre-buckling)

5 UNDEF None See word 8

6 UNDEF None

ACODE,4=08 Buckling 1 (Post-buckling)

5 MODE I Mode number

6 UNDEF None

ACODE,4=09 Complex Eigenvalues

5 MODE I Mode number

6 UNDEF None

ACODE,4=10 Nonlinear Statics (Sol 106)

5 LFTSFQ RS Load factor

6 UNDEF None

ACODE,4=11 Geometric Nonlinear Statics

5 UNDEF None See word 8

6 UNDEF None

ACODE,4=12 CONTRAN

5 TIME RS Time step

6 UNDEF None

End ACODE,4

TCODE,1=02

5 EKEY I Device code + 10*Point ID

6 EID I Element identification number if element force, otherwise zero

End TCODE,1

7 UNDEF None

8 LOADSET I Load set or zero

9 FCODE I Format Code

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Word Name Type Description

10 NUMWDE(C) I Number of words per entry in DATA record

11 ELNAME(2) CHAR4 UNDEF(2) if SORT1. Element name if SORT2: APP-LOAD, F-OF-SPC, F-OF-MPC, or *TOTALS*

13 SETID I Set identification number

14 EIGENR RS Natural eigenvalue – real part

15 EIGENI RS Natural eigenvalue – imaginary part

16 FREQ RS Natural frequency

17 UNDEF(6) None

23 THERMAL I THERMAL = 1 for heat transfer; = 2 for axisymmetric Fourier; = 3 for cyclic symmetric; = 0 otherwise

24 UNDEF(2) None

26 HINDEX I Harmonic index

27 SCFLAG I Sine/cosine flag. SCFLAG = 0 for 0th harmonic; = 1 for cosine component; = 2 for sine component; = -1 (default) for other solution type output

28 TIME RS Time for SOL401 arc-length only

29 AL_TOTAL RS Accumulated arc-length for SOL401 arc-length only

30 UNDEF(21) None

51 TITLE(32) CHAR4 Title

83 SUBTITL(32) CHAR4 Subtitle

115 LABEL(32) CHAR4 Label

Updated Record - DATA

Word Name Type Description

......

NUMWDE =8 Real - SORT2

TCODE,1 =1 SORT1

14-142 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

2 EID I Element identification number if element force; otherwise zero

3 ELNAME(2) CHAR4 Element name, APP-LOAD, F-OF-SPC, F-OF-MPC, or *TOTALS*

5 F1 RS Force in displacement coordinate system direction 1

6 F2 RS Force in displacement coordinate system direction 2

7 F3 RS Force in displacement coordinate system direction 3

8 M1 RS Moment in displacement coordinate system direction 1

9 M2 RS Moment in displacement coordinate system direction 2

10 M3 RS Moment in displacement coordinate system direction 3

TCODE,1 =02 SORT2 - Swap with word 5 of IDENT

2 GCHAR CHAR4 G

3 F1 RS Force in displacement coordinate system direction 1

4 F2 RS Force in displacement coordinate system direction 2

5 F3 RS Force in displacement coordinate system direction 3

6 M1 RS Moment in displacement coordinate system direction 1

7 M2 RS Moment in displacement coordinate system direction 2

8 M3 RS Moment in displacement coordinate system direction 3

End TCODE,1

NUMWDE =10 Real - SORT1

TCODE,1 =1 SORT1

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Word Name Type Description

2 EID I Element identification number if element force; otherwise zero

3 ELNAME(2) CHAR4 Element name, APP-LOAD, F-OF-SPC, F-OF-MPC, or *TOTALS*

5 F1 RS Force in displacement coordinate system direction 1

6 F2 RS Force in displacement coordinate system direction 2

7 F3 RS Force in displacement coordinate system direction 3

8 M1 RS Moment in displacement coordinate system direction 1

9 M2 RS Moment in displacement coordinate system direction 2

10 M3 RS Moment in displacement coordinate system direction 3

TCODE,1 =02 SORT2 - Swap with word 5 of IDENT

2 GCHAR CHAR4 G

3 F1 RS Force in displacement coordinate system direction 1

4 F2 RS Force in displacement coordinate system direction 2

5 F3 RS Force in displacement coordinate system direction 3

6 M1 RS Moment in displacement coordinate system direction 1

7 M2 RS Moment in displacement coordinate system direction 2

8 M3 RS Moment in displacement coordinate system direction 3

End TCODE,1

NUMWDE =14 Complex - SORT2

TCODE,1 =1 SORT1

14-144 NX Nastran 12 Release Guide Upward compatibility

Word Name Type Description

2 EID I Element identification number if element force; otherwise zero

3 ELNAME(2) CHAR4 Element name, APP-LOAD, F-OF-SPC, F-OF-MPC, or *TOTALS*

5 F1R RS Force in displacement coordinate system direction 1 - real part

6 F2R RS Force in displacement coordinate system direction 2 - real part

7 F3R RS Force in displacement coordinate system direction 3 - real part

8 M1R RS Moment in displacement coordinate system direction 1 - real part

9 M2R RS Moment in displacement coordinate system direction 2 - real part

10 M3R RS Moment in displacement coordinate system direction 3 - real part

11 F1I RS Force in displacement coordinate system direction 1 - imaginary part

12 F2I RS Force in displacement coordinate system direction 2 - imaginary part

13 F3I RS Force in displacement coordinate system direction 3 - imaginary part

14 M1I RS Moment in displacement coordinate system direction 1 - imaginary part

15 M2I RS Moment in displacement coordinate system direction 2 - imaginary part

16 M3I RS Moment in displacement coordinate system direction 3 - imaginary part

TCODE,1 =02 SORT2 - Swap with word 5 of IDENT

2 GCHAR CHAR4 G

3 F1R RS Force in displacement coordinate system direction 1 - real part

4 F2R RS Force in displacement coordinate system direction 2 - real part

NX Nastran 12 Release Guide 14-145 ChCaphtaeprte1r4:14U: pwaUrpdwcaormdpcaotmibpilaittyibility

Word Name Type Description

5 F3R RS Force in displacement coordinate system direction 3 - real part

6 M1R RS Moment in displacement coordinate system direction 1 - real part

7 M2R RS Moment in displacement coordinate system direction 2 - real part

8 M3R RS Moment in displacement coordinate system direction 3 - real part

9 F1I RS Force in displacement coordinate system direction 1 - imaginary part

10 F2I RS Force in displacement coordinate system direction 2 - imaginary part

11 F3I RS Force in displacement coordinate system direction 3 - imaginary part

12 M1I RS Moment in displacement coordinate system direction 1 - imaginary part

13 M2I RS Moment in displacement coordinate system direction 2 - imaginary part

14 M3I RS Moment in displacement coordinate system direction 3 - imaginary part

End TCODE,1

NUMWDE =16 Complex - SORT1

TCODE,1 =1 SORT1

2 EID I Element identification number if element force; otherwise zero

3 ELNAME(2) CHAR4 Element name, APP-LOAD, F-OF-SPC, F-OF-MPC, or *TOTALS*

5 F1R RS Force in displacement coordinate system direction 1 - real part

6 F2R RS Force in displacement coordinate system direction 2 - real part

7 F3R RS Force in displacement coordinate system direction 3 - real part

14-146 NX Nastran 12 Release Guide Upward compatibility