求复合材料非线性屈曲例子？？
如题，谢谢[ 本帖最后由 ynn1980 于 2008-7-28 22:14 编辑 ] 我也想要，能给我一份吗？
hdm106@hotmail.com 我也比较关心，请高人指点！ my qq:15834362 我也想要 kaochao@tom.com 我也想要，谢谢renhongpeng2006@126.com] 5# kaochao /TITLE,Orthotropic plate with edge load, Bifurcation Analysis, SHELL91
/UNITS,MPA ! Units are in mm, MPa, and Newtons
/PREP7 ! Pre-processor module
! Material properties for lamina
uimp,1,ex,ey,ez,145880,13312,13312
uimp,1,gxy,gyz,gxz,4386,4529,4386
uimp,1,prxy,pryz,prxz,0.263,0.470,0.263
ET,1,SHELL91,,1 ! Chooses Shell91 element for analysis
! Set KEYOPT(2)=1, then supply 12+(6*NL) const.
KEYOPT,1,1,12 ! Set KEYOPT(1)=12, Max number of layers = 12
KEYOPT,1,5,1 ! Set KEYOPT(5)=1, Element output: Middle layer
! Real constant set #1, [(0/90)3]s, NL=12, lamina thick=0.85 mm
R,1,12,1, ! 12 layers symmetrical
RMORE,,,,,,,
RMORE,1,0,0.85 ! 1st layer: mat. #1, 0 deg, Th=0.85 mm
RMORE,1,90,0.85 ! 2nd layer: mat. #1,90 deg, Th=0.85 mm
RMORE,1,0,0.85 ! 3nd layer: mat. #1, 0 deg, Th=0.85 mm
RMORE,1,90,0.85 ! 4th layer: mat. #1,90 deg, Th=0.85 mm
RMORE,1,0,0.85 ! 5th layer: mat. #1, 0 deg, Th=0.85 mm
RMORE,1,90,0.85 ! 6th layer: mat. #1,90 deg, Th=0.85 mm
! Geometry and mesh
RECTNG,0,500,0,250 ! Creates a rectangle with x=1 m and y=1 m
ESIZE,,25 ! 25 divisions for edge
AMESH,all ! Mesh the area
FINISH ! Exit pre-processor module
/SOLU ! Solution module, (i) STATIC ANALYSIS
ANTYPE,STATIC ! Set static analysis
PSTRESS,ON ! Calculate the stress stiffness matrix
DL,2,1,uz,0 ! Impose Simple Supported BC
DL,3,1,uz,0
DL,1,1,symm ! Impose Symmetry BC
DL,4,1,symm
!d,all,rotz ! Constraint rotations about z axes (optional)
!Load application
SFL,2,PRES,1 ! Apply uniform pressure in x=500 mm
SFL,3,PRES,1 ! Apply uniform pressure in y=250 mm
SOLVE ! Solve current load state
FINISH ! Exit solution module
/SOLU ! Solution module, (ii) find the BIFURCATION LOADS
ANTYPE,BUCK
BUCOPT,SUBSP,10 ! Find the first 10 bifurcations loads
SOLVE ! Solve
FINISH ! Exit solution module
/SOLU ! Solution module, (ii) find the BUCKLING MODES
EXPASS
MXPAND
SOLVE ! Solve
FINISH ! Exit solution module
/POST1 ! Post-processor module
SET,LIST ! List the critical loads
SET,1,2 ! Set mode number 2 shape
PLDISP,1 ! Display the mode 2 shape displacements
FINISH ! Exit post-processor module /TITLE,Orthotropic plate with edge load, Bifurcation Analysis, SHELL91
/UNITS,MPA ! Units are in mm, MPa, and Newtons
/PREP7 ! Pre-processor module
! Material properties for lamina
uimp,1,ex,ey,ez,145880,13312,13312
uimp,1,gxy,gyz,gxz,4386,4529,4386
uimp,1,prxy,pryz,prxz,0.263,0.470,0.263
ET,1,SHELL91,,1 ! Chooses Shell91 element for analysis
! Set KEYOPT(2)=1, then supply 12+(6*NL) const.
KEYOPT,1,1,12 ! Set KEYOPT(1)=12, Max number of layers = 12
KEYOPT,1,5,1 ! Set KEYOPT(5)=1, Element output: Middle layer
! Real constant set #1, [(0/90)3]s, NL=12, lamina thick=0.85 mm
R,1,12,1, ! 12 layers symmetrical
RMORE,,,,,,,
RMORE,1,0,0.85 ! 1st layer: mat. #1, 0 deg, Th=0.85 mm
RMORE,1,90,0.85 ! 2nd layer: mat. #1,90 deg, Th=0.85 mm
RMORE,1,0,0.85 ! 3nd layer: mat. #1, 0 deg, Th=0.85 mm
RMORE,1,90,0.85 ! 4th layer: mat. #1,90 deg, Th=0.85 mm
RMORE,1,0,0.85 ! 5th layer: mat. #1, 0 deg, Th=0.85 mm
RMORE,1,90,0.85 ! 6th layer: mat. #1,90 deg, Th=0.85 mm
! Geometry and mesh
RECTNG,0,500,0,250 ! Creates a rectangle with x=1 m and y=1 m
ESIZE,50 ! 50 size element edge
AMESH,all ! Mesh the area
FINISH ! Exit pre-processor module
/SOLU ! Solution module, (i) STATIC ANALYSIS
ANTYPE,STATIC ! Set static analysis
PSTRESS,ON ! Calculate the stress stiffness matrix
DL,2,1,uz,0 ! Impose Simple Supported BC
DL,3,1,uz,0
DL,1,1,symm ! Impose Symmetry BC
DL,4,1,symm
!d,all,rotz ! Constraint rotations about z axes (optional)
!Load application
SFL,2,PRES,1 ! Apply uniform pressure in x=500 mm
SFL,3,PRES,1 ! Apply uniform pressure in y=250 mm
SOLVE ! Solve current load state
FINISH ! Exit solution module
/SOLU ! Solution module, (ii) find the BIFURCATION LOADS
ANTYPE,BUCK
BUCOPT,SUBSP,10 ! Find the first 10 bifurcations loads
SOLVE ! Solve
FINISH ! Exit solution module
/SOLU ! Solution module, (ii) find the BUCKLING MODES
EXPASS
MXPAND
SOLVE ! Solve
FINISH ! Exit solution module
/PREP7 ! Pre-processor module
ftr=(10.8/10) ! Multiplicator shape factor (Th/10)
UPGEOM,ftr,1,1,file,rst
! ftr: Multiplier for displacements added to coordinates
! 1,1 : Load step 1, substep=1, equivalent to mode =1
! file,rst: results file to obtain displacements
FINISH ! Exit pre-processor module
/SOLU ! Solution module, Continuation loads
ANTYPE,STATIC ! Set static analysis
NLGEOM,1 ! Use large displacements analysis
OUTRES,ALL,ALL ! Keep results of each substep
mult=225 ! Apply loads until N = 225 N/mm
SFL,2,PRES,1*mult ! Apply uniform pressure in x=500 mm
SFL,3,PRES,1*mult ! Apply uniform pressure in y=250 mm
ARCLEN,1,10,0.1 ! Use ARCLENG method to obtain solution
NSUBST,50,0,0 ! #Substeps
SOLVE ! Solve current load state
FINISH ! Exit solution module
/POST26 ! Post-processor module
LINES,1000 ! List without breaks between pages
NSOL,2,1,U,Z,UZ_node1 ! Load deflexion in central plate node
PLVAR,2 ! DISPLAY VARIABLES evolution
PRVAR,2 ! PRINT VARIABLES evolution
FINISH 做复合材料屈曲分析 用Midas-NastranFX 定义求解方便快捷 无需命令流
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