S18-1 PAT325, Section 18, February 2004 Copyright 2004 MSC.Software Corporation SECTION 18 LAMINATE DEFINITION IN MSC.NASTRAN $1------$2------$3------$4------$5------$6------$7------$8------$9------$10----- - презентация

1 S18-1 PAT325, Section 18, February 2004 Copyright 2004 MSC.Software Corporation SECTION 18 LAMINATE DEFINITION IN MSC.NASTRAN $ $ $ $ $ $ $ $ $ $ PCOMP PID Z0 NSM SB FT TREF GE LAM +AM1 +AM1 MID1 T1 THETA1 SOUT1 MID2 T2 THETA2 SOUT2 +AM2 +AM2 MID3 T3 THETA3 SOUT3..ETC 1/2 line per ply definition

2 S18-2 PAT325, Section 18, February 2004 Copyright 2004 MSC.Software Corporation

3 S18-3 PAT325, Section 18, February 2004 Copyright 2004 MSC.Software Corporation MSC.PatranMSC.Nastran Lamina Material IsotropicMAT1 2D OrthotropicMAT8 2D AnisotropicMAT2 Laminate Material Lamina MaterialPCOMP Thickness Orientation Property Material Laminate Materialreference to PCOMP OrientationTHETA on CQUAD4/8, CTRIA3/6 record ElementsCQUAD4/8, CTRIA3/6 CoordinatesCORD2R/CORD2C/CORD2S MSC.PATRAN / MSC.NASTRAN

4 S18-4 PAT325, Section 18, February 2004 Copyright 2004 MSC.Software Corporation PCOMP PROPERTY CARD $ $ $ $ $ $ $ $ $ $ PCOMP PID Z0 NSM SB FT TREF GE LAM +AM1 +AM1 MID1 T1 THETA1 SOUT1 MID2 T2 THETA2 SOUT2 +AM2 +AM2 MID3 T3 THETA3 SOUT3..ETC 1/2 line per ply definition PIDProperty ID Z0Offset from grid points to first ply (default -1/2 element thickness) NSMNon-structural mass SBAllowable inter-laminar shear FTFailure Theory: Hill, Hoffman, Tsai-Wu, max strain TREFReference temperature. (Overrules MATi TREF) GEElement damping coefficient LAMSYM indicates only 1/2 plies defined and symmetry is used MIDi, Ti, THETAi Material, thickness, and angle of ply SOUTiYES gives stress output at this ply

5 S18-5 PAT325, Section 18, February 2004 Copyright 2004 MSC.Software Corporation 2D ORTHOTROPIC MATERIALS IN MSC.NASTRAN $ $ $ $ $ $ $ $ $ $ MAT8 MID E1 E2 NU12 G12 G1Z G2Z RHO +AM1 +AM1 A1 A2 TREF Xt Xc Yt Yc S +AM2 +AM2 GE F12 STRN MIDMaterial ID E1,E2Modulus of Elasticity along and across fibers NU12Poisson's Ratio ( 2/ 1 for load in direction 1) G12In-plane shear modulus G1ZShear modulus in 1-Z plane G2ZShear modulus in 2-Z plane RHODensity A1,A2Coefficient of thermal expansion in 1 and 2 directions TREFIgnored for pcomp entry Xt,Xc,Yt,Yc Tensile and compressive strengths in 1 and 2 directions SShear strength GEIgnored for pcomp entry F12Failure theory interaction term STRNSet to 1.0 if Xt, Xc, Yt, Yc and S are strains instead of stresses

6 S18-6 PAT325, Section 18, February 2004 Copyright 2004 MSC.Software Corporation COMPOSITE OUTPUT FROM MSC.NASTRAN n PARAM, NOCOMPS, -1 u Equivalent homogenous stresses output n PARAM, NOCOMPS, 1 u Ply stresses and failure indices output l Material allowables needed for failure index output n PARAM, NOCOMPS, 0 u Both homogeneous and ply output given