how transform umat to vumat

please if somme one can help me i want to transform this umat to vumat

C 4X4 JACOBIAN THEN CONDENSATION WITH REGULARIZATION c (energy due to viscous regularization is calculated) SUBROUTINE UMAT(STRESS,STATEV,DDSDDE,SSE,SPD,SCD, 1 RPL,DDSDDT,DRPLDE,DRPLDT, 2 STRAN,DSTRAN,TIME,DTIME,TEMP,DTEMP,PREDEF,DPRED,CMNAME, 3 NDI,NSHR,NTENS,NSTATV,PROPS,NPROPS,COORDS,DROT,PNEWDT, 4 CELENT,DFGRD0,DFGRD1,NOEL,NPT,LAYER,KSPT,KSTEP,KINC)C INCLUDE 'ABA_PARAM.INC'C CHARACTER*80 CMNAME DIMENSION STRESS(NTENS),STATEV(NSTATV), 1 DDSDDE(NTENS,NTENS), 2 DDSDDT(NTENS),DRPLDE(NTENS), 3 STRAN(NTENS),DSTRAN(NTENS),TIME(2),PREDEF(1),DPRED(1), 4 PROPS(NPROPS),COORDS(3),DROT(3,3),DFGRD0(3,3),DFGRD1(3,3) DIMENSION STRANT(6),TSTRANT(4) DIMENSION CFULL(6,6),CDFULL(6,6) DIMENSION DDFDE(6), DDMDE(6), DCDDF(6,6), DCDDM(6,6) DIMENSION ATEMP1(6), ATEMP2(6), TDDSDDE(6,6) DIMENSION OLD_STRESS(6) DIMENSION DOLD_STRESS(6),D_STRESS(6) PARAMETER (ZERO = 0.D0,ONE = 1.D0,TWO = 2.D0, HALF = 0.5D0)C****************************C STRANT..... STRAIN AT THE END OF THE INCREMENTC TSTRANT.....TEMPORARY ARRAY TO HOLD THE STRAIN FOR PLANE STRESS PROBLEMC CFULL.......FULL 6X6 ELASTICITY MATRIXC CDFULL......FULL 6X6 DAMAGED ELASTICITY MATRIXC DDFDE....... D DF/D EC DDMDE....... D DM/D EC DCDDF....... D C/ D DF THE DERIVATIVE OF THE FULL MATRIX OVER DFC DCDDM........D C/ D DM THE DERIVATIVE OF THE FULL MATRIX OVER DMC ATEMP1,ATEMP2...TEMPORARY ARRAY USED IN JACOBIAN CALCULATIONC TDDSDDE.....UNCONDENSED JACOBIAN MATRIX FOR PLANE STRESS PROBLEMC OLD_STRESS...STRESS AT THE BEGINNING OF THE INCREMENT, SAVED FOR THE ENERGYC COMPUTATIONC DOLD_STRESS...STRESS AT THE BEGINNING OF THE INCREMENT, C IF THERE'S NO VISCOUS REGULARIZATIONC D_STRESS...STRESS IF THERE'S NO VISCOUS REGULARIZATION, THE ABOVE IS CALCULATEDC TO CALCULATE THE SCD, ENERGY CAUSED BY VISCOUS REGULARIZATIONC STATEV(1) damage variable dfC STATEV(2) damage variable dmC STATEV(3) regularized damage variable dfvC STATEV(4) regularizaed damage variable dmvC STATEV(5:10) TEMPORARY ARRAYS TO SAVE DOLD_STRESSC************CC GET THE MATERIAL PROPERTIES---ENGINEERING CONSTANTSC TENL = PROPS(1) !YOUNG'S MODULUS IN DIRECTION 1 (L) TENT = PROPS(2) !YOUNG'S MODULUS IN DIRECTION 2 (T) SHRLT = PROPS(3) !SHEAR MODULUS IN 12 PLANE SHRTT = PROPS(4) !SHEAR MODULUS IN 23 PLANE XNULT = PROPS(5) !POISON'S RATIO POI_12 XNUTT = PROPS(6) !POISON'S RATIO POI_23 XNUTL = XNULT / TENL * TENT !POI_21C C GET THE FAILURE PROPERTIESC SIGTL = PROPS(7) !FAILURE STRESS IN 1 DIRECTION IN TENSION SIGCL = PROPS(8) !FAILURE STRESS IN 1 DIRECTION IN COMPRESSION SIGTT = PROPS(9) !FAILURE STRESS IN 2 DIRECTION IN TENSION SIGCT = PROPS(10) !FAILURE STRESS IN 2 DIRECTION IN COMPRESSION SIGSLT = PROPS(11) !FAILURE STRESS IN SHEAR IN 1-2 PLANE GFMAT = PROPS(12) !FRACTURE ENERGY IN MATRIX GFFIB = PROPS(13) !FRACTURE ENERGY IN FIBER ETA = PROPS(14) ! VISCOSITY FOR REGULARIZATIONC C CALCULATE THE STRAIN AT THE END OF THE INCREMENTC DO I = 1, NTENS STRANT(I) = STRAN(I) + DSTRAN(I) END DOc C FILL THE 6X6 FULL STIFFNESS MATRIX DO I = 1, 6 DO J = 1, 6 CFULL(I,J)=ZERO END DO END DO ATEMP = ONE - TWO * XNULT * XNUTL - XNUTT ** TWO 1 - TWO * XNULT * XNUTL * XNUTT CFULL(1,1) = TENL * (ONE - XNUTT ** TWO) / ATEMP CFULL(2,2) = TENT * (ONE - XNULT * XNUTL) / ATEMP CFULL(3,3) = CFULL(2,2) CFULL(1,2) = TENT * (XNULT + XNULT * XNUTT) / ATEMP CFULL(1,3) = CFULL(1,2) CFULL(2,3) = TENT * (XNUTT + XNULT * XNUTL) / ATEMP CFULL(4,4) = SHRLT CFULL(5,5) = SHRLT CFULL(6,6) = SHRTT DO I = 2, 6 DO J = 1, I-1 CFULL(I,J) = CFULL(J,I) END DO END DOc calculate the failure strain by failure stress EPITL = SIGTL / cfull(1,1) !FAILURE STRAIN 1 DIRECTION IN TENSION EPICL = SIGCL / cfull(1,1) !FAILURE STRAIN 1 DIRECTION IN COMPRESSION EPITT = SIGTT / cfull(2,2) !TENSILE FAILURE STRAIN 2 DIRECTION EPICT = SIGCT / cfull(2,2) !COMPRESSIVE FAILURE STRAIN 2 DIRECTION EPISLT = SIGSLT/ SHRLT ! FAILURE SHEAR STRAIN ...ENGINEERING STRAINC C CHECK THE FAILURE INITIATION CONDITIONc DFOLD = STATEV(1) DMOLD = STATEV(2) DFVOLD = STATEV(3) DMVOLD = STATEV(4) CALL CheckFailureIni(EPITL,EPICL,EPITT,EPICT,EPISLT,STRANT, 1 GFMAT,GFFIB, CELENT, CFULL, DF, DM, DDFDE, DDMDE, NTENS, 2 DFOLD, DMOLD,NDI)C C ! USE VISCOUS REGULARIZATIONC DFV = ETA / (ETA + DTIME) * DFVOLD + DTIME / (ETA + DTIME) * DF DMV = ETA / (ETA + DTIME) * DMVOLD + DTIME / (ETA + DTIME) * DMC SAVE THE OLD STRESS TO OLD_STRESS DO I = 1, NTENS OLD_STRESS(I) = STRESS(I) END DOC CALL ROUTINE TO CALCULATE THE STRESSC CALCULATE THE STRESS IF THERE'S NO VISCOUS REGULARIZATION CALL GetStress(CFULL,CDFULL,DF,DM,D_STRESS,STRANT,NDI,NTENS)C CALCULATE THE STRESS IF THERE'S VISCOUS REGULARIZATION CALL GetStress(CFULL,CDFULL,DFV,DMV,STRESS,STRANT,NDI,NTENS)C GET THE OLD STRESS IF THERE'S NO VISCOUS REGULARIZATION DO I=1,NTENS DOLD_STRESS(I)=STATEV(I+4) END DOC SAVE THE CURRENT STRESS IF THERE'S NO VISCOUS REGULARIZATION DO I=1,NTENS STATEV(I+4)=D_STRESS(I) END DOC C CALCULATE THE DERIVATIVE MATRIX DC/DDM, DC/DDF OF THE DAMAGED MATRIXC CALL ElasticDerivative(CFULL,DMV,DFV, DCDDM,DCDDF)C C UPDATE THE JACOBIANC C FULL 3D CASE IF (NDI .EQ. 3) THEN DO I = 1, NTENS ATEMP1(I) = ZERO DO J = 1, NTENS ATEMP1(I) = ATEMP1(I) + DCDDM(I,J) * STRANT(J) END DO END DO DO I = 1, NTENS ATEMP2(I) = ZERO DO J = 1, NTENS ATEMP2(I) = ATEMP2(I) + DCDDF(I,J) * STRANT(J) END DO END DO DO I = 1, NTENS DO J = 1, NTENS DDSDDE(I,J)=CDFULL(I,J) + ( ATEMP1(I) * DDMDE(J) 1 + ATEMP2(I) * DDFDE(J) ) * DTIME / (DTIME + ETA) END DO END DOC C ! PLANE STRESS CASEC ELSE IF (NDI .EQ.2) THEN TSTRANT(1) = STRANT(1) TSTRANT(2) = STRANT(2) TSTRANT(3) = -CDFULL(1,3) / CDFULL(3,3) * STRANT(1) 1 - CDFULL(2,3) / CDFULL(3,3) * STRANT(2) TSTRANT(4) = STRANT(3) DO I = 1, 4 ATEMP1(I) = ZERO DO J = 1, 4 ATEMP1(I) = ATEMP1(I) + DCDDM(I,J) * TSTRANT(J) END DO END DO DO I = 1, 4 ATEMP2(I) = ZERO DO J = 1, 4 ATEMP2(I) = ATEMP2(I) + DCDDF(I,J) * TSTRANT(J) END DO END DO DO I = 1,6 DO J = 1,6 TDDSDDE(I,J) = ZERO END DO END DOC TO GET THE UNCONDENSED JACOBIAN FOR PLANE STRESS CASE DO I = 1, NTENS DO J = 1, NTENS DDSDDE(I,J) = ZERO END DO END DO DO I = 1, 4 DO J = 1, 4 TDDSDDE(I,J)=CDFULL(I,J) + ( ATEMP1(I) * DDMDE(J) 1 + ATEMP2(I) * DDFDE(J) ) * DTIME / (DTIME + ETA) END DO END DOC C CONDENSE THE JACOBIAN MATRIX FOR PLANE STRESS PROBLEMC CALL MatrixCondense(TDDSDDE,DDSDDE) END IF C C TO UPDATE THE STATE VARIABLEC STATEV(1) = DF STATEV(2) = DM STATEV(3) = DFV STATEV(4) = DMVC C TO COMPUTE THE ENERGYC DO I = 1, NDI SSE = SSE + HALF * (STRESS(I) + OLD_STRESS(I)) * DSTRAN(I) END DO DO I = NDI+1, NTENS SSE = SSE + (STRESS(I) + OLD_STRESS(I)) * DSTRAN(I) END DOC TO COMPUTE THE INTERNAL ENERGY WITHOUT VISCOUS REGULARIZATION DO I = 1, NDI SCD = SCD + HALF * (STRESS(I) + OLD_STRESS(I) 1 -D_STRESS(I)-DOLD_STRESS(I)) * DSTRAN(I) END DO DO I = NDI+1, NTENS SCD = SCD + (STRESS(I) + OLD_STRESS(I) 1 -D_STRESS(I)-DOLD_STRESS(I)) * DSTRAN(I) END DO RETURN END C******************************************************************************C CALCULATE THE STRESS BASED ON THE DAMAGE VARAIBLES***************************C****************************************************************************** SUBROUTINE GetStress(CFULL,CDFULL,DFV,DMV,STRESS,STRANT,NDI,NTENS) INCLUDE 'ABA_PARAM.INC' DIMENSION CFULL(6,6),CDFULL(6,6),STRESS(NTENS), 1 STRANT(6),CDTHREE(3,3) PARAMETER (ZERO=0.D0, ONE=1.D0)C CDTHREE.....DAMAGED CONDENSED-ELASTICITY MATRIX FOR PLANE STRESS PROBLEM DO I = 1, 6 DO J = 1, 6 CDFULL(I,J)=CFULL(I,J) END DO END DO IF ( (DFV .NE. ZERO) .OR. (DMV .NE. ZERO)) THEN CDFULL(1,1) = (ONE - DFV) * CFULL(1,1) CDFULL(1,2) = (ONE - DFV) * (ONE - DMV) * CFULL(1,2) CDFULL(2,1) = CDFULL(1,2) CDFULL(2,2) = (ONE - DMV) * CFULL(2,2) CDFULL(1,3) = (ONE - DFV) * CFULL(1,3) CDFULL(3,1) = CDFULL(1,3) CDFULL(2,3) = (ONE- DMV) * CFULL(2,3) CDFULL(3,2) = CDFULL(2,3) CDFULL(4,4) = (ONE - DMV) * (ONE - DFV) * CFULL(4,4) END IFC UPDATE THE STRESS STATE IF 3D CASEC IF (NDI .EQ. 3) THEN DO I = 1, NTENS STRESS(I)=ZERO DO J = 1, NTENS STRESS(I)=STRESS(I)+CDFULL(I,J) * STRANT(J) END DO END DO C C INITIALIZE THE 3X3 CONDENSED STIFFNESS MATRIX IF PLANE STRESS CASEC ELSE IF ( NDI .EQ. 2) THEN DO I = 1, NTENS DO J = 1, NTENS CDTHREE(I,J)=ZERO END DO END DOC C C CONDENSE THE UNDAMAGED STIFFNESS MATRIXC CALL MatrixCondense(CDFULL,CDTHREE)C C UPDATE THE STRESSC DO I = 1, NTENS STRESS(I)=ZERO DO J = 1, NTENS STRESS(I)=STRESS(I)+CDTHREE(I,J) * STRANT(J) END DO END DO END IF RETURN ENDC******************************************************************************C TO CHECK THE FAILURE INITIATION AND THE CORRESPONDING DERIVATIVE*********C****************************************************************************** SUBROUTINE CheckFailureIni(EPITL,EPICL,EPITT,EPICT,EPISLT,STRANT, 1 GFMAT,GFFIB, CELENT, CFULL, DF, DM, DDFDE, DDMDE, NTENS, 2 DFOLD,DMOLD, NDI ) INCLUDE 'ABA_PARAM.INC' DIMENSION DDFDE(6), DDMDE(6), STRANT(6), CFULL(6,6) DIMENSION DFMNDE(6), DFFNDE(6) PARAMETER (ZERO = 0.D0, ONE = 1.D0, TWO = 2.D0, HALF = 0.5D0)C C CHECK THE INITIATION CONDITION FOR MATRIXC FMN=FM/EPITT > 1 THEN EVALUATE THE DAMAGE VARIABLE AND DERIVATIVEC TERM1 = STRANT(2)**TWO / EPICT / EPITT TERM2 = (EPICT - EPITT) / EPICT / EPITT * STRANT(2) IF (NDI .EQ. 3) THEN TERM3 = (STRANT(4))**TWO / EPISLT**TWO ELSE IF (NDI .EQ. 2) THEN TERM3 = (STRANT(3))**TWO / EPISLT**TWO END IF TERM = TERM1 + TERM2 + TERM3 IF (TERM .GT. ZERO) THEN FMN = SQRT(TERM) ELSE FMN = ZERO END IFCC INITIALIZE THE ARRAY AND VARIABLEC DM = ZERO DDMDFMN = ZERO DO I = 1, 6 DFMNDE(I) = ZERO DDMDE(I) = ZERO END DO IF (FMN .GT. ONE) THENC CALCULATE DM, DDMDFMN CALL DamageEvaluation( CFULL(2,2), FMN, GFMAT, CELENT, 1 EPITT, DM, DDMDFMN)C CALCULATE DFMNDE IF (DM .GT. DMOLD) THEN DFMNDE(2) = HALF / FMN * (TWO * STRANT(2) + EPICT - EPITT) 1 / EPICT / EPITT IF (NDI .EQ. 3) THEN DFMNDE(4) = ONE / FMN * STRANT(4) / EPISLT**TWO ELSE IF (NDI .EQ. 2) THEN DFMNDE(4) = ONE / FMN * STRANT(3) / EPISLT**TWO END IF DO I = 1, 6 DDMDE(I) = DFMNDE(I) * DDMDFMN END DO END IF END IF DM = MAX (DM, DMOLD)C C CHECK THE INITIATION CONDITION FOR FIBERC FFN=FF/EPITL>1 THEN CALCULATE THE DAMAGE VARIABLE AND DERIVATIVEC TERM1 = STRANT(1)**TWO / EPICL / EPITL TERM2 = (EPICL - EPITL) / EPICL / EPITL *STRANT(1) TERM = TERM1 + TERM2 IF (TERM .GT. ZERO) THEN FFN = SQRT(TERM) ELSE FFN = ZERO END IF DF = ZERO DDFDFFN = ZERO DO I = 1, 6 DFFNDE(I) = ZERO DDFDE(I) = ZERO END DO IF (FFN .GT. ONE) THENC CALCULATE DF, DDFDFFN CALL DamageEvaluation( CFULL(1,1), FFN, GFFIB, CELENT, 1 EPITL, DF, DDFDFFN)C CALCULATE DFFNDE IF (DF .GT. DFOLD) THEN DFFNDE(1) = HALF / FFN * (TWO * STRANT(1) + EPICL - EPITL) 1 / EPICL / EPITL DDFDE(1) = DFFNDE(1) * DDFDFFN END IF END IF DF = MAX (DF, DFOLD) RETURN ENDC******************************************************************************C SUBROUTINE TO EVALUATE THE DAMAGE AND THEc DERIVATIVE************************C****************************************************************************** SUBROUTINE DamageEvaluation(STIFF, FN, GF, CELENT, EPIT, D, 1 DDDFN)C CALCULATE DAMAGE VARIABLE INCLUDE 'ABA_PARAM.INC' PARAMETER (ONE = 1.D0,tol=1d-3, zero = 0.d0) TERM1 = STIFF * EPIT**2 * CELENT / GF TERM2 = (ONE - FN) * TERM1 D = ONE - EXP(TERM2) / FNC CALCULATE THE DERIVATIVE OF DAMAGE VARIABLE WITH RESPECT TO FAILUREC RITERION DDDFN = (ONE / FN + TERM1) * (ONE - D) RETURN ENDC******************************************************************************C SUBROUTINE TO CONDENSE THE 4X4 MATRIX INTO 3X3 MATRIX********************C****************************************************************************** SUBROUTINE MatrixCondense(CFULL,CTHREE) INCLUDE 'ABA_PARAM.INC' DIMENSION CFULL(6,6),CTHREE(3,3)C CTHREE(1,1) = CFULL(1,1) - CFULL(1,3) * CFULL(3,1) / CFULL(3,3) CTHREE(1,2) = CFULL(1,2) - CFULL(1,3) * CFULL(3,2) / CFULL(3,3) CTHREE(2,1) = CFULL(2,1) - CFULL(2,3) * CFULL(3,1) / CFULL(3,3) CTHREE(2,2) = CFULL(2,2) - CFULL(2,3) * CFULL(3,2) / CFULL(3,3) CTHREE(3,3) = CFULL(4,4) RETURN ENDC*******************************************************************************C SUBROUTINE TO GET THE DERIVATIVE MATRIX OF CONDENSE DAMAGED MATRIX OVERC**** THE DAMAGE VARIABLE******************************************************C******************************************************************************* SUBROUTINE ElasticDerivative(CFULL,DMV,DFV, DCDDM,DCDDF) INCLUDE 'ABA_PARAM.INC' DIMENSION CFULL(6,6), DCDDM(6,6), 1 DCDDF(6,6) PARAMETER (ZERO = 0.D0, ONE = 1.D0, HALF = 0.5D0)C initialize the data to zero DO I = 1, 6 DO J = 1, 6 DCDDM(I,J) = ZERO DCDDF(I,J) = ZERO END DO END DOC C CALCULATE DC/DDFC DCDDF(1,1) = - CFULL(1,1) DCDDF(1,2) = - (ONE - DMV) * CFULL(1,2) DCDDF(2,1) = DCDDF(1,2) DCDDF(1,3) = -CFULL(1,3) DCDDF(3,1) = DCDDF(1,3) DCDDF(4,4) = -(ONE - DMV) * CFULL(4,4)C C CALCULATE DC/DDMC DCDDM(1,2) = - (ONE - DFV) * CFULL(1,2) DCDDM(2,1) = DCDDM(1,2) DCDDM(2,2) = -CFULL(2,2) DCDDM(2,3) = -CFULL(2,3) DCDDM(3,2) = DCDDM(2,3) DCDDM(4,4) = -(ONE - DFV) * CFULL(4,4) RETURN END

thanks