S5-1NAS400, Section 5, April 2011 Copyright 2011 MSC.Software Corporation SECTION 5 Advanced Nonlinear Elements S5-2 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation S5-3 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Overview (cont.) ● Nonlinear Kinematic Elements ● RBE1, RBE2, RBE3 ● RBAR, RBAR1 ● RJOINT ● Additional Results Output for the Advanced Nonlinear Elements S5-5 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 LC 2) 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 – shear LCC – linear/cubic/closed section LCO – linear/cubic/open section Legend for SECT: S – smeared cross section N – numerically integrated with warping 1) Marc Type 2) underlined for default S5-7 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Overview – 2D Solid Elements ● Plane Stress Name Connectivity Properties BEH INT 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 Strain Name 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Overview – 2D Solids (cont.) ● Plane Strain (cont.) Name Connectivity Properties BEH INT 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 Name Connectivity Properties BEH INT 4 node quad (10) CQUADX PLPLANE & PSHLN2 AXSOLID L S5-9 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Overview – 2D Solids (cont.) ● Axisymmetric (cont.) Name Connectivity Properties BEH INT 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Overview – 3D Solid Elements ● Solids Name Connectivity Properties BEH INT 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Overview – 3D Solids (cont.) ● Solids (cont.) Name Connectivity Properties BEH INT 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 – linear Q – quadratic RI – reduced H – hourglass control G – Gauss N – Newton-Coates/Lobatto ASTN – assumed strain solid shell S5-12 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Overview – Shell Elements ● Shells ( for composite, use PCOMP or PCOMPG ) Name Connectivity Properties BEH INT 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 NAS400, Section 5, April 2011 Copyright 2011 MSC.Software Corporation Advanced Conventional Elements S5-14 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation PBEAM(L) PBAR(L) MATS1 MAT1 PRODN1 from previous Enhanced Enhanced Input for 1D + MAT1 MATS1 MATEP MATVE MATVP MATF or PBEAM (plastic hinge) PBARN1 or PROD or PBEMN1 or PBAR (not effective) PROD (nlelast + plastic) S5-15 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for Rods ● PRODN1 – nonlinear property extension for PROD S5-16 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 ; e nom(eng) would be s y / 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 e finite(large strain) 100. U nom(eng) =10.3 H s y S5-17 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for BARs ● PBARN1 – nonlinear property extension for PBAR(L) SECT: S – smeared cross section N – numercally integrated R: curved pipe (not available yet) S5-18 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 NLPARM 1 1 FNT 15 PV YES + 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 e nom(eng) no finite strain available PBAR will always be SECT=S and linear elastic S5-19 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for BEAMs ● PBEMN1 – nonlinear property extension for PBEAM(L) same as for BAR S5-20 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 NLPARM 1 1 FNT 15 PV YES + 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation PLPLANE PSHLN2 from previous Enhanced 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 MATS8 MATSort S5-22 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● PSHLN2 – nonlinear property extension for PLPLANE Enhanced Input for 2D Solids (cont.) S5-23 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for 2D Solids (cont.) S5-24 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● MID (materials) and DIRECT (layer orientation) for COMPS and AXCOMP: Enhanced Input for 2D Solids (cont.) will be shown later with PLCOMP S5-25 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● Small Test Case to show the Results Formats Enhanced Input for 2D Solids (cont.) QUAD4, 10x10x10 mm E=100 GPa n=0.3 y b 1 2, 12 3, 1 4 x b 1.5E4 1.5E4 ● Test Case applied to Plane Stress BEGIN 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 s y m . a x i s f o r A X S O S5-26 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for 2D Solids (cont.) ● 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for 2D Solids (cont.) ● 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 ) ELEMENT GRID/ POINT CAUCHY STRESSES/ LOG STRAINS PRESSURE VOL. STRAIN 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 ) 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 -2.870081E+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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for 2D Solids (cont.) ● 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) ELEMENT GRID/ POINT CAUCHY STRESSES/ LOG STRAINS PRESSURE VOL. STRAIN 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) ELEMENT GRID/ POINT ---------CAUCHY STRESSES-------- PRINCIPAL STRESSES (ZERO SHEAR) 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation PSOLID MAT1 MAT9 MATS1 PSLDN1 from previous Enhanced + MAT1 MAT9 MATHE MATS1 MATEP MATVE MATVP MATF MATEP MATVE MATVP MATF MATVE MATG MATort MATSort MATEP MATVE MATVP MATF Enhanced Input for 3D Solids S5-30 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for 3D Solids (cont.) ● PSLDN1 – nonlinear property extension for PSOLID S5-31 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● BEHi (behavior) and INTi (integration type) Enhanced Input for 3D Solids (cont.) S5-32 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● MID (materials) and DIRECT (layer orientation) for BEH8=SLCOMP, INT8=L: Enhanced Input for 3D Solids (cont.) will be shown later with PCOMPLS S5-33 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 Enhanced Input for 3D Solids (cont.) ● 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 y 1 2,123 3,1 4 5 6,12 7,1 8 Cube 10x10x10 mm E=100 GPa, n=0.3 S5-34 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 Enhanced Input for 3D Solids (cont.) S5-35 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation PSHELL PCOMP(G) MAT1 MAT1 MAT2 MAT8 MATS1 PSHLN1 from previous Enhanced Enhanced Input for Shells + MAT1 MAT2 MAT8 MATHE MATS1 MATEP MATVE MATVP MATF MATEP MATVE MATVP MATF MATEP MATVE MATF MATVE or S5-36 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for Shells (cont.) ● PSHLN1 – nonlinear property extension for PSHELL or PCOMP(G) S5-37 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for Shells (cont.) ● BEHi (behavior) and INTi (integration type) S5-38 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for Shells (cont.) ● 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for Shells (cont.) 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for Shells (cont.) ● 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 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 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; s e = 1.1E4 MPa S5-41 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Enhanced Input for Shells (cont.) ● 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 MID3≠0 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 Nonlinear QUADR / TRIAR (cont.) S5-45 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 Nonlinear QUADR / TRIAR (cont.) S5-46 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Nonlinear QUADR / TRIAR (cont.) ● 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 NAS400, Section 5, April 2011 Copyright 2011 MSC.Software Corporation Advanced Composite Elements S5-48 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Input for 2D Composites ● PLCOMP – property for 2D composite -etc- S5-49 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● BEHi (behavior) and INTi (integration type) Input for 2D Composites (cont.) S5-50 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● MID (materials) and DIRECT (layer orientation) Input for 2D Composites (cont.) S5-51 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation l a y e r 1 l a y e r 2 l a y e r 3 layer 3 layer 2 1 3 4 2 layer 1 Input for 2D Composites (cont.) ● Meaning of DIRECT (layer orientation) DIRECT = +1 or -1 1 3 4 2 DIRECT = +2 or -2 x m x m DIRECT >0 – fractional layer thickness <0 – absolute layer thickness S5-52 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 Input for 2D Composites (cont.) - 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation NLSTRESS(NLOUT=1) = ALL . BEGIN BULK NLOUT 1 CTOTSTRN ● Additional Results Output Input for 2D Composites (cont.) 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Input for 3D Composites ● PCOMPLS – property for 3D Composite S5-55 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● BEHi (behavior) and INTi (integration type) Input for 3D Composites (cont.) S5-56 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● MID (materials) and DIRECT (layer orientation) Input for 3D Composites (cont.) S5-57 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation l a y e r 1 l a y e r 2 l a y e r 3 layer 3 layer 2 layer 1 1 2 6 5 Input for 3D Composites (cont.) ● Meaning of DIRECT (layer orientation) DIRECT = 1 1 6 5 2 DIRECT = 2 3 T 8 7 8 3 l a y e r 1 l a y e r 2 l a y e r 3 DIRECT = 3 1 2 6 5 3 7 8 + – + – + – x m y m 7 R S z m CORDm S5-58 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 Input for 3D Composites (cont.) ● Example for PCOMPLS – solid HEX8 same model as for PSLDN1 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 -2.772E+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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Input for 3D Composites (cont.) ● Example for PCOMPLS – solid HEX8 (cont.) ● total strains ( NLOUT request ) ● interlaminar shear stresses 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 -0.800E-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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 Input for 3D Composites (cont.) ● Example for PCOMPLS – solid shell HEX8 same model as for PSLDN1 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 -2.772E+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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Input for 3D Composites (cont.) ● Example for PCOMPLS – solid shell HEX8 (cont.) ● total strains ( NLOUT request ) ● interlaminar shear stresses 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 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 ) 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 -0.800E-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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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: u max = 36.8 against 36.7 mm weight = 12 against 13.5 kg for quadratic shear calculation S5-64 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● Results for PCOMP(G) & PSHLN1 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 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 Composite Shell Elements (cont.) S5-65 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● Results for PCOMP(G) & PSHLN1 (cont.) 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 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 Composite Shell Elements (cont.) S5-66 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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.) Composite Shell Elements (cont.) S5-67 NAS400, Section 5, April 2011 Copyright 2011 MSC.Software Corporation Nonlinear Connector Elements S5-68 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 S5-69 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Connector Element – BUSH (cont.) + + S5-70 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● Large Rotation Option ● Controlled using LRGR flag on the PBUSHT entry ● For the axial BUSH element 1) 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 Connector Element – BUSH (cont.) 1) grids A and B are non-coincident and vector v nor CID are specified S5-71 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 u x and u y times K1. ● TS: spherical dependence. The force results from the length of u x + u y + u z 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 Connector Element – BUSH (cont.) S5-72 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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) Connector Element – BUSH (cont.) S5-73 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 S5-74 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 y grid 5030 2.5x2.0x0.1 E=3E7 n=0.3 connector diameter S5-75 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● Results for WELD Example WELD / FAST Elements (cont.) 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 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 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 S5-76 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● Results for WELD Example (cont.) WELD / FAST Elements (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 S5-77 NAS400, Section 5, April 2011 Copyright 2011 MSC.Software Corporation Nonlinear Kinematic Elements S5-78 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Nonlinear Kinematic Elements ● 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 S5-79 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation 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 S5-80 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 Nonlinear Kinematic Elements (cont.) S5-81 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 Nonlinear Kinematic Elements (cont.) S5-82 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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 Nonlinear Kinematic Elements (cont.) S5-83 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● Example for RJOINT Nonlinear Kinematic Elements (cont.) S5-84 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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. Nonlinear Kinematic Elements (cont.) S5-85 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation ● 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. Nonlinear Kinematic Elements (cont.) S5-86 NAS400, Section 5, April 2011 Copyright 2011 MSC.Software Corporation Additional Results Output S5-87 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Additional Results Output 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 S5-88 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation Additional Results Output (cont.) back 5-53 S5-89 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation EXERCISE ● Perform Workshop 4: Buckling of a Composite Plate. S5-90 NAS400, Section 5, August 2011 Copyright 2011 MSC.Software Corporation