abaqus材料子程序

各向同性材料损伤本构模型

SUBROUTINE UMAT(STRESS,STATEV,DDSDDE,SSE,SPD,SCD,

+ RPL,DDSDDT,DRPLDE,DRPLDT,

+ STRAN,DSTRAN,TIME,DTIME,TEMP,DTEMP,PREDEF,DPRED,CMNAME, + NDI,NSHR,NTENS,NSTATV,PROPS,NPROPS,COORDS,DROT,PNEWDT, + CELENT,DFGRD0,DFGRD1,NOEL,NPT,LAYER,KSPT,KSTEP,KINC)

INCLUDE 'ABA_PARAM.INC'

CHARACTER*80 CMNAME

DIMENSION STRESS(NTENS),STATEV(NSTATV),

+ DDSDDE(NTENS,NTENS),DDSDDT(NTENS),

+ DRPLDE(NTENS),STRAN(NTENS),DSTRAN(NTENS),

+ TIME(2),PREDEF(1),DPRED(1),PROPS(NPROPS),

+ COORDS(3),DROT(3,3),DFGRD0(3,3),DFGRD1(3,3)

DIMENSION STRANT(6),TSTRANT(4),PT(1)

DIMENSION OLD_STRESS(6)

DIMENSION DOLD_STRESS(6),D_STRESS(6)

DIMENSION C(6,6),CD(6,6),DSTRESS(6),BSTRESS(6),ROOT(3),

+ DFMNDE(6),DDMDE(6),DCDDM(6,6),ATEMP1(6), ATEMP2(6)

PARAMETER (ZERO=0.D0,ONE=1.D0,TWO=2.D0,FOUR=4.D0,HALF = 0.5D0) C start

C IF (NPROPS.LT.2) THEN

C WRITE(7,*) '** ERROR: UMAT REQUIRES *NPROPS=2'

C STOP

C EN

D IF

E11 =PROPS(1)

V12 =PROPS(2)

G12 =PROPS(1)/TWO/(ONE+PROPS(2))

C Critical values of stresses

XT=PROPS(3)

XC=PROPS(4)

XS=PROPS(5)

GX=PROPS(6) !Fracture energy in matrix

ETA=0.001

C Current strain

DO I = 1, NTENS

STRANT(I) = STRAN(I) + DSTRAN(I)

END DO

C Stiffness

DO I = 1, 6

DO J = 1, 6

C(I,J)=ZERO

END DO

END DO

ATEMP = (1+V12)*(1-TWO*V12)

C(1,1) = E11*(1-V12)/ATEMP

C(2,2) = E11*(1-V12)/ATEMP

C(3,3) = E11*(1-V12)/ATEMP

C(1,2) = E11*V12/ATEMP

C(1,3) = E11*V12/ATEMP

C(2,3) = E11*V12/ATEMP

C(4,4) = G12

C(5,5) = G12

C(6,6) = G12

DO I = 2, 6

DO J = 1, I-1

C(I,J) = C(J,I)

END DO

END DO

C Critical values of strains

XET=XT/(C(1,1)-2*V12*C(1,2))

XEC=XC/(C(1,1)-2*V12*C(1,2))

XES=XS/C(4,4)

DMOLD = STATEV(1)

C Strain initiation criterion

A11 = STRANT(1)**TWO+STRANT(2)**TWO+STRANT(3)**TWO

A12 = A11 / XET / XEC

A21 = STRANT(1)+STRANT(2)+STRANT(3)

A22 = (XEC - XET) / XEC / XET * A21

A31 = STRANT(4)**TWO+STRANT(5)**TWO+STRANT(6)**TWO

A32 = A31 / XES**TWO

A1= A12 + A22 + A32

C B11 = STRANT(2)**TWO

C B12 = B11 / XET / XEC

C B21 = STRANT(2)

C B22 = (XEC - XET) / XEC / XET * B21

C B31 = STRANT(5)**TWO

C B32 = B31 / XES**TWO

C B1= B12 + B22 + B32

C C11 = STRANT(3)**TWO

C C12 = C11 / XET / XEC

C C21 = STRANT(3)

C C22 = (XEC - XET) / XEC / XET * C21

C C31 = STRANT(6)**TWO

C C32 = C31 / XES**TWO

C C1= C12 + C22 + C32

STATEV(2)=A1

C STATEV(3)=B1

C STATEV(4)=C1

FMN = ZERO

IF (A1.GT.ZERO) THEN

FMN =SQRT(A1)

C IF (B1.GT.ONE) THEN

C FMN =FMN+SQRT(B1)

C IF(C1.GT.ONE) THEN

C FMN =FMN+SQRT(C1)

C EN

D IF