nastran nonlinear elements

S5-1

NAS400, Section 5, April 2011

Copyright 2011 MSC.Software Corporation

SECTION 5

Advanced Nonlinear Elements

S5-2

NAS400, Section 5, August 2011


S5-3



Overview

Advanced Conventional Elements

1D Elements: ROD, BAR, BEAM

2D and 3D Solid Elements

Shell Element

Advanced Composite Elements

2D and 3D Solid Composites

Composite Shell Element

Nonlinear Connector Elements

BUSH

WELD and FAST

S5-4



Overview (cont.)

Nonlinear Kinematic Elements

RBE1, RBE2, RBE3

RBAR, RBAR1

RJOINT

Additional Results Output for the Advanced Nonlinear Elements

S5-5



Overview 1D Elements

Membrane ROD

Name Connectivity Properties BEH INT

Truss (9)1)

CROD PROD & PRODN1 ROD L

1)Marc Type

2)underlined for default

Membrane & Bending BAR

Name Connectivity Properties BEH INT SECT

Thin elastic beam (52)1)

CBAR PBAR(L) & PBARN1 BAR LC2)

S/N

Thin elastic beam (98)1)

CBAR PBAR(L) & PBARN1 BAR LS S/N

Closed Section beam (78)1)

CBAR PBARL & PBARN1 BAR LCC N

S5-6



Overview 1D Elements (cont.)

Membrane & Bending BEAM

Name Connectivity Properties BEH INT SECT

Bernoulli beam (52)1)

CBEAM PBEAM(L) & PBEMN1 BEAM LC S/N

Shear flexible beam (98)1)

CBEAM PBEAM(L) & PBEMN1 BEAM LS S/N

Closed Section beam (78)1)

CBEAM PBEAML & PBEMN1 BEAM LCC N

Open Section beam (79)1)

CBEAM PBEAML & PBEMN1 BEAM LCO N

Legend for INT:

L linear; C cubic; S shearLCC linear/cubic/closed sectionLCO linear/cubic/open section

Legend for SECT:

S smeared cross sectionN numerically integrated

with warping

1)Marc Type

2)underlined for default

S5-7



Overview 2D Solid Elements

Plane Stress


4 node quad (3)1)

CQUAD4 PLPLANE & PSHLN2 PSTRS L

4 node quad red. int. (114)1)

CQUAD4 PLPLANE & PSHLN2 PSTRS LRIH

8 node quad (26)1)

CQUAD8 PLPLANE & PSHLN2 PSTRS Q

8 node quad red. int. (53)1)

CQUAD8 PLPLANE & PSHLN2 PSTRS QRI

6 node triangle(124)1)

CTRIA6 PLPLANE & PSHLN2 PSTRS Q

Plane StrainName Connectivity Properties BEH INT

4 node quad (11) CQUAD4 PLPLANE & PSHLN2 PLSTRN L

4 node quad red. int. (115) CQUAD4 PLPLANE & PSHLN2 PLSTRN LRIH

3 node triangle (6) CTRIA3 PLPLANE & PSHLN2 PLSTRN L

S5-8



Overview 2D Solids (cont.)

Plane Strain (cont.)


8 node quad (27) CQUAD8 PLPLANE & PSHLN2 PLSTRN Q

8 node quad red. int. (54) CQUAD8 PLPLANE & PSHLN2 PLSTRN QRI

6 node triangle (125) CTRIA6 PLPLANE & PSHLN2 PLSTRN Q

4 node gasket (151) CQUAD4 PLPLANE & PSHLN2 COMPS L

4 node composite (151) CQUAD4 PLCOMP COMPS L

8 node composite (153) CQUAD8 PLCOMP COMPS Q

cohesive zone (186/187) CIFQUAD PCOHE G or N

Axisymmetric


4 node quad (10) CQUADX PLPLANE & PSHLN2 AXSOLID L

S5-9



Overview 2D Solids (cont.) Axisymmetric (cont.)


4 node quad w. twist (20) CQUADX PLPLANE & PSHLN2 AXSOLID LT

4 node quad red. int. (116) CQUADX PLPLANE & PSHLN2 AXSOLID LRIH

3 node triangle (2) CTRIAX PLPLANE & PSHLN2 AXSOLID L

8 node quad (28) CQUADX PLPLANE & PSHLN2 AXSOLID Q

8 node quad w. twist (67) CQUADX PLPLANE & PSHLN2 AXSOLID QT

8 node quad red. int. (55) CQUADX PLPLANE & PSHLN2 AXSOLID QRI

6 node triangle (126) CTRIAX PLPLANE & PSHLN2 AXSOLID Q

4 node gasket (152) CQUADX PLPLANE & PSHLN2 AXCOMP L

4 node composite (152) CQUADX PLCOMP AXCOMP L

8 node composite (154) CQUADX PLCOMP AXCOMP Q

cohesive zone (190/191) CIFQDX PCOHE G or N

S5-10



Overview 3D Solid Elements Solids


hex8 (7) CHEXA PSOLID & PSLDN1 SOLID L

hex8 (117) CHEXA PSOLID & PSLDN1 SOLID LRIH

6 node penta (136) CPENTA PSOLID & PSLDN1 SOLID L

tet4 (134) CTETRA PSOLID & PSLDN1 SOLID L

hex20 (21) CHEXA PSOLID & PSLDN1 SOLID Q

hex20 (57) CHEXA PSOLID & PSLDN1 SOLID QRI

15 node penta (21) CPENTA PSOLID & PSLDN1 SOLID Q

tet10 (127) CTETRA PSOLID & PSLDN1 SOLID Q

tet10 (184) CTETRA PSOLID & PSLDN1 SOLID LRIH

hex8 gasket (149) CHEXA PSOLID & PSLDN1 SLCOMP L

hex8 solid shell (185) CHEXA PSOLID & PSLDN1 SLCOMP ASTN

S5-11



Overview 3D Solids (cont.)

Solids (cont.)


hex8 composite (149) CHEXA PCOMPLS SLCOMP L

hx8 comp. solid shell (185) CHEXA PCOMPLS SLCOMP ASTN

hex20 composite (150) CHEXA PCOMPLS SLCOMP Q

cohesive zone (188/189) CIFHEX PCOHE G or N

cohesive zone (192/193) CIFPENT PCOHE G or N

Legend for INT:

L linearQ quadraticRI reducedH hourglass controlG GaussN Newton-Coates/LobattoASTN assumed strain solid shell

S5-12



Overview Shell Elements Shells ( for composite, use PCOMP or PCOMPG )


4 node quad (18) CQUAD4 PSHELL & PSHLN1 MB L

3 node triangle (158) CTRIA3 PSHELL & PSHLN1 MB L

8 node quad (30) CQUAD8 PSHELL & PSHLN1 MB Q

6 node triangle (200) CTRIA6 PSHELL & PSHLN1 MB Q

4 node shear (18) CSHEAR PSHEAR & PSHEARN MB L

4 node thick quad*)(75) CQUAD4 PSHELL & PSHLN1 DCT L

4 node thick quad*)(140) CQUAD4 PSHELL & PSHLN1 DCT LRIH

4 node thin quad (139) CQUAD4 PSHELL & PSHLN1 DCTN LDK

3 node triangle (138) CTRIA3 PSHELL & PSHLN1 DCTN LDK

8 node thick quad*)(22) CQUAD8 PSHELL & PSHLN1 DCT QRI

*) with transverse shear effect

LDK linear discrete Kirchhoff

S5-13



Advanced Conventional Elements

S5-14



PBEAM(L)PBAR(L)

MATS1

MAT1

PRODN1

from previous Enhanced

Enhanced Input for 1D

+

MAT1

MATS1

MATEP

MATVE

MATVP

MATF

or

PBEAM(plastic hinge)

PBARN1orPROD or PBEMN1or

PBAR(not effective)

PROD(nlelast + plastic)

S5-15



Enhanced Input for Rods

PRODN1 nonlinear property extension for PROD

S5-16



Enhanced Input for Rods (cont.)

Example for PRODN1 ( MATEP used )

BEGIN BULK

NLMOPTS LRGSTRN 1

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

NLPARM 1 1 FNT 15 PV YES

+ 1.-5 -3

FORCE 1 2 3.+4 1.

GRID 1 0.0 123456

GRID 2 100.0 23456

MAT1 1 100000. 0.3

MATEP 1 200. 1000.

PROD 10 1 100. 2000.

PRODN1 10 1

CROD 101 10 1 2

ENDDATA

; enom(eng) would be sy / E + Ds / H = 0.103

N O N L I N E A R S T R E S S E S I N R O D E L E M E N T S ( C R O D )

ELEMENT AXIAL STRESS EQUIVALENT TOTAL STRAIN EFF. STRAIN EFF. CREEP LIN. TORSIONAL

ID STRESS PLASTIC/NLELAST STRAIN STRESS

1 3.604114E+02 3.604114E+02 1.640155E-01 0.0 0.0

D I S P L A C E M E N T V E C T O R

POINT ID. TYPE T1 T2 T3 R1 R2 R3

1 G 0.0 0.0 0.0 0.0 0.0 0.0

2 G 1.528253E+01 0.0 0.0 0.0 0.0 0.0

efinite(large strain)

100.

Unom(eng)=10.3

H

sy

S5-17



Enhanced Input for BARs

PBARN1 nonlinear property extension for PBAR(L)

SECT:S smeared cross sectionN numercally integrated

R:curved pipe

(not available yet)

S5-18



Enhanced Input for BARs (cont.)

Example for PBARN1 (same model as before)

BEGIN BULK

NLMOPTS LRGST 1

$.......2.......3.......4.......5.......6.......7.......8.......9.......0


+ 1.-7 -3

.

.

PBARL 10 1 BAR

+ 10. 10.

PBARN1 10 1 N

CBAR 101 10 1 2 0. 1. 0.

N O N L I N E A R S T R E S S E S I N B A R E L E M E N T S ( C B A R )

ELEMENT GRID POINT STRESS EQUIVALENT TOTAL STRAIN EFF. STRAIN EFF. CREEP

ID ID STRESS PLASTIC/NLELAST STRAIN

0 1 1 C 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

D 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

E 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

F 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

2 C 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

D 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

E 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

F 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

enom(eng) no finite strain available

PBAR will always be

SECT=S and linear elastic

S5-19



Enhanced Input for BEAMs

PBEMN1 nonlinear property extension for PBEAM(L)

same as for BAR

S5-20



Enhanced Input for BEAMs (cont.)

Example for PBEMN1 (same model as before)

BEGIN BULK

NLMOPTS LRGST 1

$.......2.......3.......4.......5.......6.......7.......8.......9.......0


+ 1.-7 -3

.

.

PBEAML 10 1 BAR

+ 10. 10.

PBEMN1 10 1 N

CBEAM 101 10 1 2 0. 1. 0.PBEAM will always be

SECT=S and linear elastic

N O N L I N E A R S T R E S S E S I N B E A M E L E M E N T S ( C B E A M )

ELEMENT GRID POINT STRESS EQUIVALENT TOTAL STRAIN EFF. STRAIN EFF. CREEP

ID ID STRESS PLASTIC/NLELAST STRAIN

0 1 1 C 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

D 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

E 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

F 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

2 C 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

D 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

E 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

F 3.000000E+02 3.000000E+02 1.030000E-01 9.999997E-02 0.0

same results as for BAR

S5-21



PLPLANE PSHLN2


Enhanced Input for 2D Solids

+

MAT1 MAT2 MAT8 MATHE

MATS1

MATEP

MATVE

MATVP

MATF

MATEP

MATVE

MATVP

MATF

MATEP

MATVE

MATF

MATVE

MAT3 MATort

MATVE

MATVP

MATF

MATEP

MATVE

MATVP

MATF

MATG

MATHP

MATS3

MATEP

MATS8MATSort

S5-22



PSHLN2 nonlinear property extension for PLPLANE

Enhanced Input for 2D Solids (cont.)

S5-23




S5-24



MID (materials) and DIRECT (layer orientation)

for COMPS and AXCOMP:


will be shown later with PLCOMP

S5-25



Small Test Case to show the Results Formats


QUAD4, 10x10x10 mm

E=100 GPa

n=0.3yb

1 2, 12

3, 14

xb

1.5E4

1.5E4

Test Case applied to Plane StressBEGIN BULK

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

MAT1 1 100000. 0.3

MATEP 1 200. 1000.

PLPLANE 1 1

PSHLN2 1 1 10.

+ C4 PSTR

CQUAD4 101 1 1 2 3 4

sym

. a

xis

fo

r A

XS

O

S5-26




Results for Plane Stress

N O N L I N E A R S T R E S S E S I N P L A N A R Q U A D R I L A T E R A L E L E M E N T S ( QUAD4FD )

ELEMENT GRID/ POINT CAUCHY STRESSES/ LOG STRAINS PRESSURE VOL. STRAIN

ID GAUSS ID X Y Z XY

0 1 GRID 1 -2.772397E+02 -1.459266E-03 0.0 4.303163E-14 -9.241373E+01 -4.055405E-02

-8.001141E-02 3.945735E-02 0.0 -6.114626E-18

2 -2.772397E+02 -1.459266E-03 0.0 -4.980505E-14 -9.241373E+01 -4.055405E-02

-8.001141E-02 3.945735E-02 0.0 3.866429E-18

3 -2.772397E+02 -1.459266E-03 0.0 -4.544615E-14 -9.241373E+01 -4.055405E-02

-8.001141E-02 3.945735E-02 0.0 5.076220E-18

4 -2.772397E+02 -1.459266E-03 0.0 6.207892E-14 -9.241373E+01 -4.055405E-02

-8.001141E-02 3.945735E-02 0.0 -4.885475E-18

S T R E S S E S I N P L A N A R Q U A D R I L A T E R A L E L E M E N T S ( QUAD4FD )

ELEMENT GRID/ POINT ---------CAUCHY STRESSES-------- PRINCIPAL STRESSES (ZERO SHEAR)

ID GAUSS ID NORMAL-X NORMAL-Y SHEAR-XY ANGLE MAJOR MINOR

0 1 GAUS 1 -2.772397E+02 -1.459266E-03 2.591385E-14 90.0000 -1.459266E-03 -2.772397E+02

2 -2.772397E+02 -1.459266E-03 -2.774897E-14 -90.0000 -1.459266E-03 -2.772397E+02

3 -2.772397E+02 -1.459266E-03 3.692384E-14 90.0000 -1.459266E-03 -2.772397E+02

4 -2.772397E+02 -1.459266E-03 -2.522938E-14 -90.0000 -1.459266E-03 -2.772397E+02

NLSTRESS = ALL

STRESS = ALL

This is a limitation right now that 2D results

are always in the format of hyperelastic material

S5-27




Test Case applied to Plane Strain

BEGIN BULK

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

MAT1 1 100000. 0.3

PLPLANE 10 1

PSHLN2 10 1

+ C4 PLSTRN

CQUAD4 101 10 1 2 3 4

N O N L I N E A R S T R E S S E S I N P L A N A R Q U A D R I L A T E R A L E L E M E N T S ( QUAD4FD )


ID GAUSS ID X Y Z XY

0 1 GRID 1 -2.870081E+02 -1.924351E-03 -1.667499E+02 8.993561E-14 -1.512533E+02 -1.815040E-03

-4.607959E-02 4.426455E-02 0.0 3.228621E-17

2 -2.870081E+02 -1.924351E-03 -1.667499E+02 3.974964E-15 -1.512533E+02 -1.815040E-03

-4.607959E-02 4.426455E-02 0.0 2.744412E-18

3 -2.870081E+02 -1.924351E-03 -1.667499E+02 -8.923872E-14 -1.512533E+02 -1.815040E-03

-4.607959E-02 4.426455E-02 0.0 -3.622263E-17

4 -2.870081E+02 -1.924351E-03 -1.667499E+02 -1.429180E-14 -1.512533E+02 -1.815040E-03

-4.607959E-02 4.426455E-02 0.0 -1.277675E-17

S T R E S S E S I N P L A N A R Q U A D R I L A T E R A L E L E M E N T S ( QUAD4FD )


ID GAUSS ID NORMAL-X NORMAL-Y SHEAR-XY ANGLE MAJOR MINOR

0 1 GAUS 1 -2.870081E+02 -1.924351E-03 5.097109E-14 90.0000 -1.924351E-03 -2.870081E+02

2 -2.870081E+02 -1.924351E-03 1.282847E-15 90.0000 -1.924351E-03 -2.870081E+02

3 -2.870081E+02 -1.924351E-03 -9.275978E-15 -90.0000 -1.924351E-03 -2.870081E+02

4 -2.870081E+02 -1.924351E-03 -5.259789E-14 -90.0000 -1.924351E-03 -2.870081E+02

NLSTRESS

STRESS

S5-28




Test Case applied to Axisymmetric

BEGIN BULK

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

MAT1 1 100000. 0.3

PLPLANE 10 1

PSHLN2 10 1

+ C4 AXSO

CQUADX 101 10 1 2 3 4

N O N L I N E A R S T R E S S E S IN A X I S Y M M E T R I C Q U A D R I L A T E R A L ELEMENTS (QUADX4FD)


ID GAUSS ID RADIAL(X) AXIAL(Y) THETA(Z) XY

0 1 GRID 1 -3.395956E-01 -3.411921E-02 4.789650E+01 3.406230E-02 1.584093E+01 1.900911E-04

-1.469831E-04 -1.430119E-04 4.800861E-04 8.856200E-07

2 -1.352211E-01 3.400619E-02 4.762400E+01 3.406232E-02 1.584093E+01 1.900911E-04

-1.443262E-04 -1.421263E-04 4.765436E-04 8.856204E-07

3 -1.352211E-01 3.400619E-02 4.762400E+01 -3.406232E-02 1.584093E+01 1.900911E-04

-1.443262E-04 -1.421263E-04 4.765436E-04 -8.856204E-07

4 -3.395956E-01 -3.411921E-02 4.789650E+01 -3.406230E-02 1.584093E+01 1.900911E-04

-1.469831E-04 -1.430119E-04 4.800861E-04 -8.856200E-07

Modifications to Model

inner radius 1000 mm SPC at grid 1 in y only

S T R E S S E S I N A X I S Y M M E T R I C Q U A D R I L A T E R A L E L E M E N T S (QUADX4FD)


ID GAUSS ID RADIAL(X) AXIAL(Y) SHEAR-XY ANGLE MAJOR MINOR

0 1 GAUS 1 -2.964761E-01 -1.974593E-02 1.968919E-02 85.9506 -1.835208E-02 -2.978700E-01

2 -1.783406E-01 1.963291E-02 1.968920E-02 84.3751 2.157208E-02 -1.802797E-01

3 -2.964761E-01 -1.974593E-02 -1.968919E-02 -85.9506 -1.835208E-02 -2.978700E-01

4 -1.783406E-01 1.963291E-02 -1.968920E-02 -84.3751 2.157208E-02 -1.802797E-01

NLSTRESS

STRESS

below yield

S5-29



PSOLID

MAT1 MAT9

MATS1

PSLDN1


+

MAT1 MAT9 MATHE

MATS1

MATEP

MATVE

MATVP

MATF

MATEP

MATVE

MATVP

MATF

MATVE

MATGMATort

MATSort

MATEP

MATVE

MATVP

MATF

Enhanced Input for 3D Solids

S5-30




PSLDN1 nonlinear property extension for PSOLID

S5-31



BEHi (behavior) and INTi (integration type)


S5-32




for BEH8=SLCOMP, INT8=L:


will be shown later with PCOMPLS

S5-33



BEGIN BULK

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

MAT1 1 100000. 0.3

MATEP 1 200. 1000.

PSOLID 10 1

PSLDN1 10 1

CHEXA 101 10 1 2 3 4 5 6

+ 7 8


Example for PSLDN1

similar to model before

will give the same results as for plane

stress

plane strain different since

deformation in z is free here

z

x

y1

2,123

3,1

4

5

6,12

7,1

8

Cube

10x10x10 mm

E=100 GPa, n=0.3

S5-34



Results for PSLDN1

N O N L I N E A R S T R E S S E S I N H E X A H E D R O N S O L I D E L E M E N T S ( H E X A )

CORNER STRESSES/ TOTAL STRAINS EQUIVALENT EFF. STRAIN EFF. CREEP

ELEMENT-ID GRID-ID X Y Z XY YZ ZX STRESS PLAS/NLELAS STRAIN

0 1 0GRID CS 8 GP

CENTER -2.7724E+02 -3.7915E-04 -3.7915E-04 3.0712E-15 -1.2232E-14 -3.3034E-15 2.7724E+02 7.7235E-02 0.0

-8.0008E-02 3.9449E-02 3.9449E-02 -2.8888E-17 -7.8482E-18 -1.4705E-18

1 -2.7724E+02 -3.7915E-04 -3.7915E-04 2.2495E-13 -8.2312E-14 -7.0250E-14 2.7724E+02 7.7235E-02 0.0

-8.0008E-02 3.9449E-02 3.9449E-02 8.9886E-17 -4.0506E-17 -7.3093E-17

2 -2.7724E+02 -3.7915E-04 -3.7915E-04 -4.0129E-13 -2.3197E-14 -3.2889E-14 2.7724E+02 7.7235E-02 0.0

-8.0008E-02 3.9449E-02 3.9449E-02 -2.5580E-16 -3.1180E-17 5.0519E-18

3 -2.7724E+02 -3.7915E-04 -3.7915E-04 -2.4887E-13 -1.5915E-13 -2.3530E-14 2.7724E+02 7.7235E-02 0.0

-8.0008E-02 3.9449E-02 3.9449E-02 -1.7271E-16 -9.8195E-17 8.3285E-18

4 -2.7724E+02 -3.7915E-04 -3.7915E-04 3.5860E-13 -7.3002E-14 2.1225E-14 2.7724E+02 7.7235E-02 0.0

-8.0008E-02 3.9449E-02 3.9449E-02 1.6761E-16 -3.7622E-17 8.6098E-18

5 -2.7724E+02 -3.7915E-04 -3.7915E-04 3.5170E-13 9.0636E-14 2.6746E-14 2.7724E+02 7.7235E-02 0.0

-8.0008E-02 3.9449E-02 3.9449E-02 1.7727E-16 6.0124E-17 -1.8353E-17

6 -2.7724E+02 -3.7915E-04 -3.7915E-04 -3.0811E-13 1.0989E-13 6.5281E-14 2.7724E+02 7.7235E-02 0.0

-8.0008E-02 3.9449E-02 3.9449E-02 -2.1672E-16 5.1683E-17 5.4634E-17

7 -2.7724E+02 -3.7915E-04 -3.7915E-04 -3.1198E-13 -5.8632E-14 -2.1511E-14 2.7724E+02 7.7235E-02 0.0

-8.0008E-02 3.9449E-02 3.9449E-02 -2.0872E-16 -3.3308E-17 1.1423E-17

8 -2.7724E+02 -3.7915E-04 -3.7915E-04 3.5957E-13 9.7914E-14 8.5002E-15 2.7724E+02 7.7235E-02 0.0

-8.0008E-02 3.9449E-02 3.9449E-02 1.8808E-16 6.6220E-17 -8.3650E-18

NLSTRESS = ALL


S5-35



PSHELL PCOMP(G)

MAT1

MAT1

MAT2

MAT8

MATS1

PSHLN1


Enhanced Input for Shells

+

MAT1 MAT2 MAT8 MATHE

MATS1

MATEP

MATVE

MATVP

MATF

MATEP

MATVE

MATVP

MATF

MATEP

MATVE

MATF

MATVE

or

S5-36



Enhanced Input for Shells (cont.)

PSHLN1 nonlinear property extension for PSHELL or PCOMP(G)

S5-37





S5-38




MID1 (membrane) and MID2 (bending)

except for MAT1, MAT2 and MAT8 only available with PSHLN1 !

NSM not available at this time (no message indicating this in f06)

S5-39




BEGIN BULK

PARAM LGDISP 1

NLMOPTS LRGST 1

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

MAT1 1 100000. 0.3 2.7-9

MATEP 1 500. 1.-10

PSHELL 1 1 5.0 1 1

PSHLN1 1 1 1

$

CQUAD4 1 1 1 2 13 12

Example for PSHELL & PSHLN1

Plate 1000x1000 mm

E=100 GPa; n=0.3

5 mm thick

simply supported

constant pressure of 1 MPa

z

x

y

grid 61

quad 46

S5-40




Results for PSHELL & PSHLN1

1 QUAD4_10X10 - PSHLN1 - MATEP JUNE 2, 2008 MD NASTRAN 5/ 8/08 PAGE 13

0 SUBCASE 1 STEP 1

LOAD STEP = 1.00000E+00

N O N L I N E A R S T R E S S E S I N Q U A D R I L A T E R A L E L E M E N T S ( Q U A D 4 )

ELEMENT FIBER STRESSES/ TOTAL STRAINS EQUIVALENT EFF. STRAIN EFF. CREEP

ID DISTANCE X Y Z XY STRESS PLASTIC/NLELAST STRAIN

0 46 -2.493541E+00 4.999142E+02 4.999142E+02 0.000000E+00 3.810283E+00 5.000000E+02 1.674281E-04 0.0

3.582057E-03 3.582057E-03 -2.587031E-03 1.024309E-04

2.493541E+00 3.478169E+02 3.478169E+02 0.000000E+00 8.907989E-01 3.478508E+02 0.0 0.0

2.435762E-03 2.435762E-03 -2.587031E-03 2.323268E-05

0 SUBCASE 1 STEP 1

LOAD STEP = 1.00000E+00



61 G -1.258384E-16 2.782326E-15 -3.666331E+01 -3.251228E-17 -1.437026E-16 1.186709E-12

For comparison with full linear:

u = 3.5 m; se = 1.1E4 MPa

S5-41




PSHEARN nonlinear property extension for PSHEAR

+

BEGIN BULK

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

MAT1 1 210000. 0.3 7.85-9

MATEP 1 500. 1000.

PSHEAR 10 1 1.2

PSHEARN 10 1

CQUAD4 101 10 1 2 3 4

CTRIA3 102 10 4 3 5

S5-42



QUADR/TRIAR elements have been extended to nonlinear static and

transient analysis for SOL 400 only

Benefits:

No K6ROT necessary

MOMENTs and SPC normal to plane rotations can be applied

The membrane performance of QUADR/TRIAR is superior to that of

QUAD4/TRIA3

For material nonlinear analysis, 4 (QUADR) or 3 (TRIAR) in-plane integration

points are used. This will give better results.

Nonlinear QUADR / TRIAR

S5-43



Benefits (cont.):

Green strains are implemented

The stress output location can be either corner or integration points

Type of analyses:

Material nonlinear analysis the material models are elastoplastic and nonlinear elastic

Geometric nonlinear analysis PARAM, LGDISP,1

Geometric nonlinear analysis for temperature dependent composites

PARAM, COMPMATT, YES

PARAM, EPSILONT, SECANT or INTEGRAL

Nonlinear QUADR / TRIAR (cont.)

S5-44



There are two methods to compute the out of plane shear stiffness:

The stiffness method new method implemented for QUADR

The flexibility method the method used in QUAD4

These methods can be selected by the user with MDLPRM,

QRSHEAR, n

n=0, use the stiffness method if MID30 on PSHELL entry and use the flexibility method if MID3=0. This is Default.

n=1, use the flexibility method

n=2, use the stiffness method


S5-45



Green strain

Green strain is implemented for QUADR/TRIAR. It can be requested by

MDLPRM, GNLSTN, n

n=0, Small strain. Default

n=1, Green strain

Stress output locations

For QUADR/TRIAR, the stress/force output locations can be either at the

corner points or at the integration points. User can select the output location

by MDLPRM, INTOUT, n

n=0, corner point output. Default

n=1, integration point output


S5-46




An option is provided not to compute the differential stiffness by

MDLPRM, NLDIFF, n

n=0, compute the differential stiffness / follower force stiffness (default)

n=1, do not compute the differential stiffness

Please note, the differential stiffness / follower force stiffness can be

deactivated and the solution will still be correct

Limitations:

No CREEP, creep material

No MATHP, hyperelastic material like rubber

S5-47



Advanced Composite Elements

S5-48



Input for 2D Composites

PLCOMP property for 2D composite

-etc-

S5-49




Input for 2D Composites (cont.)

S5-50





S5-51



layer

1

layer

2

layer

3

layer 3

layer 2

1

34

2

layer 1


Meaning of DIRECT (layer orientation)

DIRECT = +1 or -1

1

34

2

DIRECT = +2 or -2

xm

xm

DIRECT >0 fractional layer thickness

S5-52



BEGIN BULK

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

MATORT 1 100000. 100000. 100000. 0.3 0.3 0.3

+ 38461.5 38461.5 38461.5

MATEP 1 200. 1000.

PLCOMP 10 1 10.

+ C4 COMPS

+ 1 1 0.5 0.0

+ 2 1 0.5 0.0

CQUAD4 101 10 1 2 3 4

Former 2D Test Case also applied here


- plane strain

- 2 plies for same number

of integration

points

- MATORT for demo

S T R E S S E S A N D S T R A I N S F O R L A Y E R E D C O M P O S I T E E L E M E N T S

ELEMENT INTEG. --------------- S T R E S S E S & S T R A I N S --------------

ID PLY ID POINT ID S11 S22 S33 S12 S23 S31

1 1 1 -2.870E+02 -1.924E-03 -1.667E+02 -5.145E-14 0.000E+00 0.000E+00

-2.370E-03 1.361E-03 -8.065E-04 -1.338E-18 0.000E+00 0.000E+00

2 -2.870E+02 -1.924E-03 -1.667E+02 1.111E-13 0.000E+00 0.000E+00

-2.370E-03 1.361E-03 -8.065E-04 2.889E-18 0.000E+00 0.000E+00

2 1 -2.870E+02 -1.924E-03 -1.667E+02 -8.686E-14 0.000E+00 0.000E+00

-2.370E-03 1.361E-03 -8.065E-04 -2.258E-18 0.000E+00 0.000E+00

2 -2.870E+02 -1.924E-03 -1.667E+02 7.393E-14 0.000E+00 0.000E+00

-2.370E-03 1.361E-03 -8.065E-04 1.922E-18 0.000E+00 0.000E+00

stresses the same,

strains are the

elastic strains.

to request the total strains NLOUT has to be used

S5-53



NLSTRESS(NLOUT=1) = ALL

.

BEGIN BULK

NLOUT 1 CTOTSTRN

Additional Results Output


LOAD STEP = 1.00000E+00

TENSOR OUTPUT QUANTITIES

element output ply-id CID gaus tensor components

id quantity point X Y Z XY YZ XZ

1 CTOTSTRN 1 0 1 -0.461E-01 0.443E-01 0.000E+00 0.342E-16 0.000E+00 0.000E+00

2 -0.461E-01 0.443E-01 0.000E+00 -0.490E-17 0.000E+00 0.000E+00

2 0 1 -0.461E-01 0.443E-01 0.000E+00 0.459E-17 0.000E+00 0.000E+00

2 -0.461E-01 0.443E-01 0.000E+00 -0.310E-16 0.000E+00 0.000E+00

Further information on NLOUT

are in a separate section

these are the same strains as before

5-85

S5-54



Input for 3D Composites

PCOMPLS property for 3D Composite

S5-55





S5-56





S5-57



layer

1

layer

2

layer

3

layer 3

layer 2

layer 1

1 2

65


Meaning of DIRECT (layer orientation)

DIRECT = 1

1

65

2

DIRECT = 2

3

T

8 78

3

layer

1

layer

2

layer

3

DIRECT = 31 2

65

3

78

+

+

+

xm

ym

7

R

S

zm

CORDm

S5-58



BEGIN BULK

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

MATORT 1 100000. 100000. 100000. 0.3 0.3 0.3

+ 38461.5 38461.5 38461.5

MATEP 1 200. 1000.

PCOMPLS 1 1

+ C8 SLCOMP L

+ 1 1 0.5 0.0

+ 2 1 0.5 0.0

CHEXA 101 1 1 2 3 4 5 6

+ 7 8


Example for PCOMPLS solid HEX8

same model as for PSLDN1




1 1 1 -2.772E+02 -3.792E-04 -3.792E-04 7.837E-14 -3.707E-14 7.723E-14

-2.772E-03 8.317E-04 8.317E-04 2.038E-18 -9.637E-19 2.008E-18

2 -2.772E+02 -3.792E-04 -3.792E-04 -9.877E-14 -3.631E-15 -3.535E-14

-2.772E-03 8.317E-04 8.317E-04 -2.568E-18 -9.440E-20 -9.190E-19

3 -2.772E+02 -3.792E-04 -3.792E-04 1.247E-13 -8.523E-14 -5.593E-14

-2.772E-03 8.317E-04 8.317E-04 3.242E-18 -2.216E-18 -1.454E-18

4 -2.772E+02 -3.792E-04 -3.792E-04 -5.422E-14 -4.472E-14 -9.106E-14

-2.772E-03 8.317E-04 8.317E-04 -1.410E-18 -1.163E-18 -2.367E-18

2 1 -2.772E+02 -3.792E-04 -3.792E-04 6.552E-14 4.256E-14 8.577E-14

-2.772E-03 8.317E-04 8.317E-04 1.703E-18 1.107E-18 2.230E-18

2 -2.772E+02 -3.792E-04 -3.792E-04 -4.464E-14 1.240E-13 -1.435E-14

-2.772E-03 8.317E-04 8.317E-04 -1.161E-18 3.225E-18 -3.732E-19

3 -2.772E+02 -3.792E-04 -3.792E-04 9.989E-14 1.732E-14 -1.898E-14

-2.772E-03 8.317E-04 8.317E-04 2.597E-18 4.503E-19 -4.935E-19

4 -2.772E+02 -3.792E-04 -3.792E-04 -1.330E-14 5.600E-14 -4.757E-14

-2.772E-03 8.317E-04 8.317E-04 -3.457E-19 1.456E-18 -1.237E-18

stresses the same,

strains are the

elastic strains.

S5-59




Example for PCOMPLS solid HEX8 (cont.)

total strains ( NLOUT request )

interlaminar shear stresses




1 CTOTSTRN 1 0 1 -0.800E-01 0.394E-01 0.394E-01 -0.314E-16 -0.322E-16 0.161E-16

2 -0.800E-01 0.394E-01 0.394E-01 -0.147E-17 0.118E-15 -0.636E-16

3 -0.800E-01 0.394E-01 0.394E-01 0.212E-16 -0.514E-16 -0.621E-17

4 -0.800E-01 0.394E-01 0.394E-01 0.474E-16 -0.283E-16 -0.487E-16

2 0 1 -0.800E-01 0.394E-01 0.394E-01 0.428E-16 0.278E-16 0.496E-16

2 -0.800E-01 0.394E-01 0.394E-01 0.102E-15 0.127E-15 -0.469E-16

3 -0.800E-01 0.394E-01 0.394E-01 -0.222E-16 0.688E-17 -0.324E-16

4 -0.800E-01 0.394E-01 0.394E-01 0.370E-16 -0.225E-16 -0.730E-16

I N T E R L A M I N A R S T R E S S E S F O R L A Y E R E D C O M P O S I T E E L E M E N T S

ELEMENT INTEG. N O R M A L S T R E S S S H E A R S T R E S S BOND

ID PLY ID POINT ID 1 2 3 1 2 3 INDEX

1 1 1 -5.436E-28 9.836E-20 -3.792E-04 8.703E-14 2.748E-15 0.000E+00 0.000E+00

2 -5.436E-28 6.475E-20 -3.792E-04 -1.932E-14 6.021E-14 0.000E+00 0.000E+00

3 -7.296E-20 9.836E-20 -3.792E-04 -8.528E-14 -3.396E-14 0.000E+00 0.000E+00

4 -7.296E-20 6.475E-20 -3.792E-04 -1.171E-13 5.637E-15 0.000E+00 0.000E+00

2 1 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00

2 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00

3 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00

4 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00

S5-60



BEGIN BULK

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

MATORT 1 100000. 100000. 100000. 0.3 0.3 0.3

+ 38461.5 38461.5 38461.5

MATEP 1 200. 1000.

PCOMPLS 1 1

+ C8 SLCOMP ASTN

+ 1 1 0.5 0.0

+ 2 1 0.5 0.0

CHEXA 101 1 1 2 3 4 5 6

+ 7 8


Example for PCOMPLS solid shell HEX8

same model as for PSLDN1




1 1 1 -2.772E+02 -3.792E-04 -3.792E-04 1.828E-14 -1.426E-14 -8.839E-14

-2.772E-03 8.317E-04 8.317E-04 4.753E-19 -3.709E-19 -2.298E-18

2 1 -2.772E+02 -3.792E-04 -3.792E-04 2.960E-14 -2.105E-14 -9.214E-14

-2.772E-03 8.317E-04 8.317E-04 7.697E-19 -5.473E-19 -2.396E-18

stresses the same,

strains are the

elastic strains.

S5-61




Example for PCOMPLS solid shell HEX8 (cont.)

total strains ( NLOUT request )

interlaminar shear stresses




1 1 1 6.384E-19 3.237E-19 -3.792E-04 -1.006E-13 -1.730E-14 1.841E-28 0.000E+00

2 1 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00

N O N L I N E A R O U T P U T I N H E X A H E D R O N E L E M E N T S ( H E X A )




1 CTOTSTRN 1 0 1 -0.800E-01 0.394E-01 0.394E-01 0.774E-17 -0.105E-16 -0.595E-15

2 0 1 -0.800E-01 0.394E-01 0.394E-01 0.393E-18 -0.157E-16 -0.590E-15

S5-62



In addition to PCOMP(G): Integration Control

INT=1 (Default), conventional through the thickness integration of each layer, allows all available material behavior

through the thickness.

INT=2, linear elastic material, fast-integrated through the thickness - thermal strains and temperature dependent

material properties are not allowed.

INT=3, linear elastic material, fast integrated through the thickness.

Composite Shell Elements

S5-63



Composite Shell Elements (cont.)

BEGIN BULK

PARAM LGDISP 1

NLMOPTS LRGSTRN 1

+ TSHEAR TSHEAR

$.......2.......3.......4.......5.......6.......7.......8.......9.......0

MAT8 1 140000. 12000. 0.26 5800. 5400. 5400. 1.5-9

MATF 1 0 100.

+ CRI 1 2000. 1500. 70. 230.

+ 90.

$

PCOMP 1 100. STRN SYM

+ 1 0.5 90. YES

+ 1 0.5 0. YES

+ 1 0.5 90. YES

+ 1 0.5 0. YES

+ 1 0.5 90. YES

+ 1 0.5 0. YES

+ 1 0.5 90. YES

+ 1 0.5 0. YES

PCOMPF 2 1

PSHLN1 1 1 1

Example for PCOMP(G) & PSHLN1

maximum stress criterion

Same model as for PSHELL:

umax = 36.8 against 36.7 mm

weight = 12 against 13.5 kg

for quadratic shear calculation

S5-64



Results for PCOMP(G) & PSHLN1




46 1 1 6.446E+02 6.648E+01 0.000E+00 -6.764E-01 3.271E-03 3.272E-02

4.481E-03 4.343E-03 0.000E+00 -1.166E-04 6.057E-07 6.060E-06

2 6.242E+02 6.603E+01 0.000E+00 -9.326E-01 3.271E-03 4.170E-02

4.336E-03 4.343E-03 0.000E+00 -1.608E-04 6.058E-07 7.721E-06

3 6.450E+02 6.825E+01 0.000E+00 -4.217E-01 2.722E-03 3.272E-02

4.481E-03 4.489E-03 0.000E+00 -7.270E-05 5.041E-07 6.060E-06

4 6.246E+02 6.779E+01 0.000E+00 -6.778E-01 2.722E-03 4.170E-02

4.336E-03 4.489E-03 0.000E+00 -1.169E-04 5.041E-07 7.721E-06

2 1 6.101E+02 6.598E+01 0.000E+00 6.175E-01 6.935E-02 -3.965E-02

4.235E-03 4.365E-03 0.000E+00 1.065E-04 1.284E-05 -7.342E-06

2 6.097E+02 6.430E+01 0.000E+00 8.395E-01 8.837E-02 -3.965E-02

4.235E-03 4.226E-03 0.000E+00 1.447E-04 1.637E-05 -7.342E-06

3 6.299E+02 6.642E+01 0.000E+00 3.967E-01 6.935E-02 -3.300E-02

4.376E-03 4.365E-03 0.000E+00 6.840E-05 1.284E-05 -6.110E-06

4 6.295E+02 6.474E+01 0.000E+00 6.187E-01 8.837E-02 -3.300E-02

4.376E-03 4.226E-03 0.000E+00 1.067E-04 1.637E-05 -6.110E-06

16 1 3.953E+02 4.157E+01 0.000E+00 2.071E-01 3.271E-03 3.272E-02

2.746E-03 2.730E-03 0.000E+00 3.571E-05 6.057E-07 6.060E-06

2 3.872E+02 4.139E+01 0.000E+00 4.633E-01 3.271E-03 4.170E-02

2.689E-03 2.730E-03 0.000E+00 7.987E-05 6.058E-07 7.721E-06

3 3.955E+02 4.227E+01 0.000E+00 -4.767E-02 2.722E-03 3.272E-02

2.746E-03 2.788E-03 0.000E+00 -8.219E-06 5.041E-07 6.060E-06

4 3.874E+02 4.209E+01 0.000E+00 2.085E-01 2.722E-03 4.170E-02

2.689E-03 2.788E-03 0.000E+00 3.594E-05 5.041E-07 7.721E-06


S5-65



Results for PCOMP(G) & PSHLN1 (cont.)




46 1 1 0.000E+00 0.000E+00 0.000E+00 6.693E-02 -6.691E-03 0.000E+00 6.693E-04

2 0.000E+00 0.000E+00 0.000E+00 8.529E-02 -6.691E-03 0.000E+00 8.529E-04

3 0.000E+00 0.000E+00 0.000E+00 6.693E-02 -5.568E-03 0.000E+00 6.693E-04

4 0.000E+00 0.000E+00 0.000E+00 8.529E-02 -5.568E-03 0.000E+00 8.529E-04

2 1 0.000E+00 0.000E+00 0.000E+00 7.190E-02 -7.434E-02 0.000E+00 7.434E-04

2 0.000E+00 0.000E+00 0.000E+00 9.162E-02 -7.434E-02 0.000E+00 9.162E-04

3 0.000E+00 0.000E+00 0.000E+00 7.190E-02 -6.187E-02 0.000E+00 7.190E-04

4 0.000E+00 0.000E+00 0.000E+00 9.162E-02 -6.187E-02 0.000E+00 9.162E-04

3 1 0.000E+00 0.000E+00 0.000E+00 1.210E-01 -7.925E-02 0.000E+00 1.210E-03

2 0.000E+00 0.000E+00 0.000E+00 1.542E-01 -7.925E-02 0.000E+00 1.542E-03

3 0.000E+00 0.000E+00 0.000E+00 1.210E-01 -6.595E-02 0.000E+00 1.210E-03

4 0.000E+00 0.000E+00 0.000E+00 1.542E-01 -6.595E-02 0.000E+00 1.542E-03

16 1 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00

2 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00

3 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00

4 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00


S5-66



F A I L U R E R E S U L T S F O R L A Y E R E D C O M P O S I T E E L E M E N T S

ELEMENT INTEG. FAILURE MAXIMUM STRENGTH FAILURE TOTAL FIBER MATRIX

ID PLY ID POINT ID THEORY FAIL.INDEX RATIO MODE DAMAGE DAMAGE DAMAGE

46 1 1 MAXSTRES 9.497E-01 1.053E+00 2 0.000E+00 0.000E+00 0.000E+00

2 MAXSTRES 9.432E-01 1.060E+00 2 0.000E+00 0.000E+00 0.000E+00

3 MAXSTRES 9.750E-01 1.026E+00 2 0.000E+00 0.000E+00 0.000E+00

4 MAXSTRES 9.685E-01 1.033E+00 2 0.000E+00 0.000E+00 0.000E+00

2 1 MAXSTRES 9.425E-01 1.061E+00 2 0.000E+00 0.000E+00 0.000E+00

2 MAXSTRES 9.185E-01 1.089E+00 2 0.000E+00 0.000E+00 0.000E+00

3 MAXSTRES 9.488E-01 1.054E+00 2 0.000E+00 0.000E+00 0.000E+00

4 MAXSTRES 9.248E-01 1.081E+00 2 0.000E+00 0.000E+00 0.000E+00

3 1 MAXSTRES 9.023E-01 1.108E+00 2 0.000E+00 0.000E+00 0.000E+00

2 MAXSTRES 8.963E-01 1.116E+00 2 0.000E+00 0.000E+00 0.000E+00

3 MAXSTRES 9.255E-01 1.081E+00 2 0.000E+00 0.000E+00 0.000E+00

4 MAXSTRES 9.195E-01 1.088E+00 2 0.000E+00 0.000E+00 0.000E+00

16 1 MAXSTRES 5.938E-01 1.684E+00 2 0.000E+00 0.000E+00 0.000E+00

2 MAXSTRES 5.913E-01 1.691E+00 2 0.000E+00 0.000E+00 0.000E+00

3 MAXSTRES 6.039E-01 1.656E+00 2 0.000E+00 0.000E+00 0.000E+00

4 MAXSTRES 6.013E-01 1.663E+00 2 0.000E+00 0.000E+00 0.000E+00

M A X / M I N F A I L U R E O U T P U T F O R L A Y E R E D C O M P O S I T E E L E M E N T S

ELEMENT ------ FMAX ------ ----- SRMIN ------ FAIL ------ DAMAGE ------

ID max(FIi) PLY ID min(SRi) PLY ID FLAG max PLY ID

46 9.750E-01 1 1.026E+00 1 0.000E+00 0

Results for PCOMP(G) & PSHLN1 (cont.)


S5-67



Nonlinear Connector Elements

S5-68



General Description

The BUSH element is a generalized spring-damper element used to model

everything from special connectors to gap elements

large rotations are included ( MD R3+ )

FUSE capability can be used to model bearing failure in rotor dynamics

(MD R3+)

Input Description

Changes have been made to the PBUSHT Bulk Data Entry

Output Description

No changes

Connector Element BUSH

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Connector Element BUSH (cont.)

+

+

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Large Rotation Option

Controlled using LRGR flag on the PBUSHT entry

For the axial BUSH element1)

LRGR is ignored

For BUSH defined using a coordinate system CID or an orientation vector v

LRGR=0 (Default): the element coordinate system is rotated with the rotation of

grid A for both the CID and the v vector

LRGR=1: will suppress large rotation at end A. The initial CID and the v vector

will remain unchanged

LRGR=2: a mid-increment method is used to rotate the element system for the v

vector


1)grids A and B are non-coincident and vector v nor CID are specified

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Fuse option, with following entries on PBUSHT

FDC, force-deflection curve rule

NR: all directions are independent (default)

TRXY, TRXZ or TRYZ: radial dependence, useful for radial bearings. For example,

the force results from the length of ux and uy times K1.

TS: spherical dependence. The force results from the length of ux+ uy+ uz times

K1.

FUSE

0: no fuse (default)

1: associated elements are deactivated if failure criterion is met, elements remain

for post processing only

2: associated elements are deactivated if failure criterion is met, elements are

removed from post processing


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Fuse option (cont.)

DIR, fuse direction

0: any direction can fuse, same as 123456

1-6: directions which can fuse (like SPC input)

OPTION, failure mode

ULTLD for load

RELDIS for displacement

UPPER/LOWER, failure limits

depending on OPTION a load or displacement limit

FRATE, fraction for stiffness scaling to avoid sudden zero (default=1.-5)


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WELDs and FASTs are elements designed for the connection of shells

Applications are spot welds

and fasteners

WELD is a BEAM element

FAST is a BUSH element

Both elements are connected to the shells by internally created RBE3

elements

Both elements can undergo large rotations

The WELD element can have all nonlinear materials allowed for

BEAM(PBEAM) elements

Connector Elements WELD / FAST

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Example for the WELD Element

weld element 1 is connecting 4 elements

on each side in this case

pressure on upper

plate (1.+3)

WELD / FAST Elements (cont.)

BEGIN BULK

PARAM LGDISP 1

CWELD 1 11 100 PARTPAT

+ 100 200

PWELD 11 10 0.8

$

PSHELL 100 10 .1 10 1. .833333

CQUAD4 1000 100 1000 1001 2001 2000 0. 0.

.

PSHELL 200 10 .1 10 1. .833333

CQUAD4 4005 200 5006 5007 5013 5012 0. 0.

.

MAT1 10 3.+7 1.153+7 0.3 .0074

z

x

ygrid 5030

2.5x2.0x0.1

E=3E7

n=0.3

connector diameter

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Results for WELD Example


0 SUBCASE 1 STEP 1

LOAD STEP = 1.00000E+00

F O R C E S I N W E L D E L E M E N T S ( C W E L D )

STAT DIST/ - BENDING MOMENTS - - WEB SHEARS - AXIAL TOTAL WARPING

ELEMENT-ID GRID LENGTH PLANE 1 PLANE 2 PLANE 1 PLANE 2 FORCE TORQUE TORQUE

0 1

101000001 0.000 -8.839650E+02 2.412787E+03 3.064666E+02 -3.020579E+02 -4.963424E+03 -6.540462E+02 0.0

101000002 1.000 -9.605817E+02 2.488301E+03 3.064666E+02 -3.020579E+02 -4.963424E+03 -6.540462E+02 0.0

0 SUBCASE 1 STEP 1

LOAD STEP = 1.00000E+00



5030 G 1.445504E-02 -1.584998E+00 -2.640457E+00 -1.381116E+00 -1.278003E-01 9.589864E-02

without GNL WELD (MD R2.1)

this value would be -2.44

This value meets top plate area

(2.5x2.0) times pressure (1E3).

Without GNL WELD it would be far

off (-1502.2).

these grid points are the grids A and B

of an internally created BEAM

for the WELD

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Results for WELD Example (cont.)


0 SUBCASE 1 STEP 1

LOAD STEP = 1.00000E+00

G R I D P O I N T F O R C E B A L A N C E

0 3002 2001 QUAD4 1.084012E+03 1.374482E+03 -8.756651E+02 4.998597E+02 -1.588867E+02 1.458691E+02

3002 2002 QUAD4 -9.773187E+02 1.014899E+03 -1.177605E+02 4.968433E+02 1.249129E+02 -1.175040E+02

3002 3001 QUAD4 1.340506E+03 -1.484548E+03 6.786337E+02 -4.930043E+02 -1.708182E+01 7.086414E+01

3002 3002 QUAD4 -1.472552E+03 -7.252704E+02 3.445563E+02 -5.036438E+02 5.055989E+01 -9.921779E+01

3002 100001004 RBE3 2.550272E+01 -1.790153E+02 -3.152349E+01 0.0 0.0 0.0

3002 *TOTALS* 1.497325E-01 5.466715E-01 -1.759053E+00 5.487696E-02 -4.957646E-01 1.150136E-02

0 SUBCASE 1 STEP 1

LOAD STEP = 1.00000E+00

S T R E S S E S I N W E L D E L E M E N T S ( C W E L D )

STAT DIST/

ELEMENT-ID GRID LENGTH SXC SXD SXE SXF S-MAX S-MIN M.S.-T M.S.-C

0 1

101000001 0.000 7.711506E+03 -5.787528E+04 -2.746034E+04 3.812645E+04 3.812645E+04 -5.787528E+04

101000002 1.000 9.235746E+03 -5.937759E+04 -2.898458E+04 3.962876E+04 3.962876E+04 -5.937759E+04

0 SUBCASE 1 STEP 1

LOAD STEP = 1.00000E+00

S T R A I N S I N W E L D E L E M E N T S ( C W E L D )

STAT DIST/

ELEMENT-ID GRID LENGTH SXC SXD SXE SXF S-MAX S-MIN M.S.-T M.S.-C

0 1

101000001 0.000 -5.445103E-04 -1.928071E-03 -1.137843E-04 1.269777E-03 1.269777E-03 -1.928071E-03

101000002 1.000 2.348792E-04 -1.978735E-03 -8.931737E-04 1.320440E-03 1.320440E-03 -1.978735E-03

this is one of 8 newly created grid points which not directly belong to WELD

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Nonlinear Kinematic Elements are the rigid elements with Lagrange

formulation used in geometric nonlinear analysis of large rotation

These include RBAR, RBAR1, RJOINT, RBE1, RBE2, RBE3, RTRPLT, and

RTRPL1

Type of elements that can be combined with the kinematic elements:

CBEAM, CQUAD4, CQUADR, CTRIA3, and CTRIAR

CHEXA, CPENTA, CTETRA (4 and 10 nodes)

CBAR and CSHEAR, which are converted into CBEAM and CQUAD4 by

new bulk card:

MDLPRM, BRTOBM, 1, SHRTOQ4, 1

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Nonlinear Kinematic Elements (cont.)

Implemented in SOL 400 only. User fatal error issued if used in SOL 106

or 129

Implemented in both nonlinear static and transient analyses

This type of element becomes linkage if any dof is released

Appropriate constraints must be supplied, otherwise the structure model will

be singular and the solution diverges

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Benefits:

The kinematic elements can be combined with shell, beam, and solid

elements

Differential stiffness are computed to facilitate convergence of the solution

Appropriate scale factors for Lagrange multipliers and penalty functions are

computed automatically

Allow thermal load to be used with the kinematic elements

Both force and GPFORCE outputs available for output


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Thermal effects are computed if thermal load is requested

ALPHA field on the Bulk Data entry must be supplied

Outputs:

Element force is requested by the Case Control command MPCFO

The GPFORCE output is requested by the GPFO Case Control command


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The scale factors for Lagrange multipliers and penalty functions are

computed automatically based on:

the geometry of the kinematic elements

the average magnitude of the stiffness matrix

PARAM, LMFACT and PENFN will overwrite the computed default

values for the stiffness portion

Case Control command RIGID=LINEAR can be used to request the

corresponding linear rigid elements instead of the NL kinematic

elements


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Example for RJOINT


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An RJOINT can be:

Spherical joint - A spherical joint is a mechanical joint that rotates freely

about all three axes. All rotational degrees of freedom released,

i.e. CB = 123.

Hinge - A hinge is a mechanical joint that rotates freely about one axis of the

local coordinate system. One rotational degree of freedom released,

i.e., CB = 12356, 12346, or 12345.

Universal joint - A universal joint is a mechanical joint that rotates freely in

two axes. Two rotational degrees for freedom released,

i.e., CB = 1234, 1235, or 1236.


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An RJOINT can be (cont.):

Prismatic joint - A prismatic joint is a mechanical system with two blocks that

are constrained to have the same rotations, but translate relatively with each

other along a local axis,

i.e., CB = 23456, 13456, 12456.

Cylindrical joint - A cylindrical joint is a mechanical system that allows two

grid points have relative translation along a moving axis and relative rotation

about the same axis,

i.e. CB = 2356, 1346, 1245.


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1)applies only to the nonlinear property extension elements ( PSHLN1, PSLDN1, )

Extended NLSTRESS Command 1)

which refers to an NLOUT Bulk Data Card

with the following results quantities

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Additional Results Output (cont.)

back5-53

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EXERCISE

Perform Workshop 4: Buckling of a Composite Plate.

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nastran nonlinear elements

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