/COM,ANSYS MEDIA REL. 2024R2 (05/10/2024) REF. VERIF. MANUAL: REL. 2024R2 /VERIFY,VM279 /COM, VERIFICATION MANUAL FOR FRACTURE MECHANCIS, /TITLE,VM279, T-STRESS FOR A CRACK IN A 2D PLATE /COM REFERENCE: STRESS INTENSITY FACTORS, T-STRESSES, WEIGHT /COM FUNCTIONS BY THEO FETT,INSTITUTE OF CERAMICS IN /COM MECHANICAL ENGINEERING (IKM),UNIVERSITY OF KARLSRUHE(TH) /COM ****CRACK IN 2-DIMENSIONS USING 2-D PLANE183 ELEMENT*** /OUT,SCRATCH /PREP7 E=207000 ! YOUNGS MODULUS NU=0.3 ! POISSONS RATIO SIG=100 ! SURFACE LOAD ! DIMENSIONS. A = 10 ! HALF CRACK LENGTH ALPHA = 0.2 ! ALPHA = A / W HEIGHT_WIDTH_RATIO = 0.75 ! H / W W = A / ALPHA ! HALF PLATE WIDTH H = HEIGHT_WIDTH_RATIO*W ! HALF PLATE HEIGHT TSTRESS_REFERENCE_NORMALIZED = -0.88 ! TSTRESS TARGET VALUE ! NORMALIZED AS: T/SIG*(1-ALPHA) ! TSTRESS TARGET VALUE CORRESPONDING TO THE GIVEN DIMENSIONS: TSTRESS_REFERENCE = (TSTRESS_REFERENCE_NORMALIZED*SIG) / (1 - ALPHA) ET,1,PLANE183 ! PLANE 183 ELEMENT KEYOPT,1,3,2 ! PLANE STRAIN MP,EX,1,E MP,NUXY,1,NU K,1,0,0 ! DEFINE KEYPOINTS AND LINE SEGMENTS K,2,A,0 ! CRACK TIP K,3,W,0 K,4,W,H/2 K,5,W,H K,6,0,H K,7,0,H/2 L,1,2 *REP,6,1,1 L,7,1 L,4,7 AL,1,2,3,8,7 AL,4,5,6,8 ESIZE,1 KSCON,2,1,1,4,0.75 !CRACK TIP ELEMENTS AMESH,1 ESIZE,2 AMESH,2 FINI /SOLU OUTRES,ALL,ALL NSEL,S,LOC,Y,0 NSEL,R,LOC,X,A,W D,ALL,UY,0 ! APPLY MODEL BOUNDARY CONDITIONS NSEL,S,LOC,X,0 NSEL,R,LOC,Y,0,H D,ALL,UX,0 NSEL,ALL LSEL,S,LINE,,5 SFL,ALL,PRESS,-SIG LSEL,ALL NSEL,S,LOC,Y,0 NSEL,R,LOC,X,A CM,CRACK1,NODE ! DEFINE THE CRACK TIP NODE COMPONENT NSEL,ALL CINT,NEW,1 CINT,TYPE,TSTR ! CALCULATE T-STRESS CINT,CTNC,CRACK1 ! CRACK ID CINT,NCON,4 ! NUMBER OF COUNTOURS CINT,SYMM,ON ! SYMMETRY ON CINT,NORM,0,2 CINT,LIST ALLSEL,ALL SOLVE FINISH /POST1 /OUT, PRCINT,1,,TSTR ! GET THE T-STRESS VALUES TIP_NODE_NUMBER = NODE(A,0,0) *GET,TSTRESS_1,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,1,DTYPE,TSTR *GET,TSTRESS_2,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,2,DTYPE,TSTR *GET,TSTRESS_3,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,3,DTYPE,TSTR *GET,TSTRESS_4,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,4,DTYPE,TSTR TSTRESS = (TSTRESS_2+ TSTRESS_3 + TSTRESS_4) / 3 *STAT,TSTRESS /OUT,SCRATCH TSTRESS_RATIO = ABS(TSTRESS/TSTRESS_REFERENCE) ! STORE DATA *DIM,LABEL,CHAR,1,5 *DIM,VALUE,,1,3 LABEL(1,1) = 'T-STRESS' *VFILL,VALUE(1,1),DATA,TSTRESS_REFERENCE *VFILL,VALUE(1,2),DATA,TSTRESS *VFILL,VALUE(1,3),DATA,TSTRESS_RATIO SAVE,TABLE_1 FINISH /CLEAR, NOSTART ! CLEAR DATABASE FOR 2ND SOLUTION /OUT, /COM ***** CRACK IN 3D PLATE USING SOLID 185 ELEMENT ******** /OUT,SCRATCH /PREP7 E=207000 ! YOUNGS MODULUS NU=0.3 ! POISSONS RATIO SIG=100 ! SURFACE LOAD PI=3.141593 TK=1 ! DIMENSIONS. A = 10 ! HALF CRACK LENGTH ALPHA = 0.2 ! ALPHA = A / W HEIGHT_WIDTH_RATIO = 0.75 ! H / W W = A / ALPHA ! HALF PLATE WIDTH H = HEIGHT_WIDTH_RATIO*W ! HALF PLATE HEIGHT TSTRESS_REFERENCE_NORMALIZED = -0.88 ! TSTRESS TARGET VALUE ! NORMALIZED AS: T/SIG*(1-ALPHA) ! TSTRESS TARGET VALUE CORRESPONDING TO THE GIVEN DIMENSIONS: TSTRESS_REFERENCE = (TSTRESS_REFERENCE_NORMALIZED*SIG) / (1 - ALPHA) ET,1,PLANE182 ! PLANE 182 ELEMENT ET,2,SOLID185 ! SOLID185 ELEMENT MP,EX,1,E MP,NUXY,1,NU K,1,0,0 ! DEFINE KEYPOINTS AND LINE SEGMENTS K,2,A,0 K,3,W,0 K,4,W,H/2 K,5,W,H K,6,0,H K,7,0,H/2 L,1,2 *REP,6,1,1 L,7,1 L,4,7 AL,1,2,3,8,7 AL,4,5,6,8 ESIZE,1 KSCON,2,1,0,4,0.75 !CRACK TIP ELEMENTS AMESH,1 ESIZE,2 AMESH,2 ALLSEL,ALL TYPE,2 ESIZE,,5 VEXT,ALL,,,0,0,TK ALLSEL,ALL ESEL,S,ENAME,,182 ACLEAR,1,2,,, ALLSEL FINI /SOLU OUTRES,ALL,ALL NSEL,S,LOC,Y,0 NSEL,R,LOC,X,A,W D,ALL,UY,0 NSEL,S,LOC,X,0 NSEL,R,LOC,Y,0,H D,ALL,UX,0 NSEL,ALL ASEL,S,,,11 SFA,ALL,,PRESS,-SIG ALLSEL,ALL D,ALL,UZ,0 ALLSEL NSEL,S,LOC,Y,0 NSEL,R,LOC,X,A CM,CRACK1,NODE ! DEFINE THE CRACK FRONT NODES COMPONENT NSEL,ALL CINT,NEW,1 CINT,TYPE,TSTR ! CALCULATE T-STRESS CINT,CTNC,CRACK1 ! CRACK ID CINT,NCON,4 ! NUMBER OF COUNTOURS CINT,SYMM,ON ! SYMMETRY ON CINT,NORM,0,2 CINT,LIST ALLSEL,ALL SOLVE FINISH /POST1 /OUT, PRCINT,1,,TSTR ! GET THE T-STRESS VALUES TIP_NODE_NUMBER = NODE(A,0,0) *GET,TSTRESS_1,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,1,DTYPE,TSTR *GET,TSTRESS_2,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,2,DTYPE,TSTR *GET,TSTRESS_3,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,3,DTYPE,TSTR *GET,TSTRESS_4,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,4,DTYPE,TSTR TSTRESS = (TSTRESS_2+ TSTRESS_3 + TSTRESS_4) / 3 *STAT,TSTRESS /OUT,SCRATCH TSTRESS_RATIO = ABS(TSTRESS/TSTRESS_REFERENCE) ! STORE DATA *DIM,LABEL,CHAR,1,5 *DIM,VALUE,,1,3 LABEL(1,1) = 'T-STRESS' *VFILL,VALUE(1,1),DATA,TSTRESS_REFERENCE *VFILL,VALUE(1,2),DATA,TSTRESS *VFILL,VALUE(1,3),DATA,TSTRESS_RATIO SAVE,TABLE_2 FINISH /CLEAR, NOSTART ! CLEAR DATABASE FOR 2ND SOLUTION /OUT, /COM ***** CRACK IN 3D PLATE USING SOLID 186 ELEMENT ******** /OUT,SCRATCH /PREP7 E=207000 ! YOUNGS MODULUS NU=0.3 ! POISSONS RATIO SIG=100 ! SURFACE LOAD PI=3.141593 TK=1 ! DIMENSIONS. A = 10 ! HALF CRACK LENGTH ALPHA = 0.2 ! ALPHA = A / W HEIGHT_WIDTH_RATIO = 0.75 ! H / W W = A / ALPHA ! HALF PLATE WIDTH H = HEIGHT_WIDTH_RATIO*W ! HALF PLATE HEIGHT TSTRESS_REFERENCE_NORMALIZED = -0.88 ! TSTRESS TARGET VALUE ! NORMALIZED AS: T/SIG*(1-ALPHA) ! TSTRESS TARGET VALUE CORRESPONDING TO THE GIVEN DIMENSIONS: TSTRESS_REFERENCE = (TSTRESS_REFERENCE_NORMALIZED*SIG) / (1 - ALPHA) ET,1,PLANE183 ! PLANE 182 ELEMENT ET,2,SOLID186 ! SOLID185 ELEMENT MP,EX,1,E MP,NUXY,1,NU K,1,0,0 ! DEFINE KEYPOINTS AND LINE SEGMENTS K,2,A,0 K,3,W,0 K,4,W,H/2 K,5,W,H K,6,0,H K,7,0,H/2 L,1,2 *REP,6,1,1 L,7,1 L,4,7 AL,1,2,3,8,7 AL,4,5,6,8 ESIZE,1 KSCON,2,1,0,4,0.75 !CRACK TIP ELEMENTS AMESH,1 ESIZE,2 AMESH,2 ALLSEL,ALL TYPE,2 ESIZE,,5 VEXT,ALL,,,0,0,TK ALLSEL,ALL ESEL,S,ENAME,,183 ACLEAR,1,2,,, ALLSEL FINI /SOLU OUTRES,ALL,ALL NSEL,S,LOC,Y,0 NSEL,R,LOC,X,A,W D,ALL,UY,0 NSEL,S,LOC,X,0 NSEL,R,LOC,Y,0,H D,ALL,UX,0 NSEL,ALL ASEL,S,,,11 SFA,ALL,,PRESS,-SIG ALLSEL,ALL D,ALL,UZ,0 ALLSEL NSEL,S,LOC,Y,0 NSEL,R,LOC,X,A CM,CRACK1,NODE ! DEFINE THE CRACK FRONT NODES COMPONENT NSEL,ALL CINT,NEW,1 CINT,TYPE,TSTR ! CALCULATE T-STRESS CINT,CTNC,CRACK1 ! CRACK ID CINT,NCON,4 ! NUMBER OF COUNTOURS CINT,SYMM,ON ! SYMMETRY ON CINT,NORM,0,2 CINT,LIST ALLSEL,ALL SOLVE FINISH /POST1 /OUT, PRCINT,1,,TSTR ! GET THE T-STRESS VALUES TIP_NODE_NUMBER = NODE(A,0,0) *GET,TSTRESS_1,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,1,DTYPE,TSTR *GET,TSTRESS_2,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,2,DTYPE,TSTR *GET,TSTRESS_3,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,3,DTYPE,TSTR *GET,TSTRESS_4,CINT,1,CTIP,TIP_NODE_NUMBER,CONTOUR,4,DTYPE,TSTR TSTRESS = (TSTRESS_2+ TSTRESS_3 + TSTRESS_4) / 3 *STAT,TSTRESS /OUT,SCRATCH TSTRESS_RATIO = ABS(TSTRESS/TSTRESS_REFERENCE) ! STORE DATA *DIM,LABEL,CHAR,1,5 *DIM,VALUE,,1,3 LABEL(1,1) = 'T-STRESS' *VFILL,VALUE(1,1),DATA,TSTRESS_REFERENCE *VFILL,VALUE(1,2),DATA,TSTRESS *VFILL,VALUE(1,3),DATA,TSTRESS_RATIO SAVE,TABLE_3 /OUT, FINISH RESUME,TABLE_1 /COM /OUT,vm279,vrt /COM,------------------- VM279 RESULTS COMPARISON -------------- /COM, /COM, | TARGET | Mechanical APDL | RATIO /COM, /COM, **************************************** /COM, USING PLANE 183 ELEMENT (2-D ANALYSIS) /COM, ***************************************** /COM, *VWRITE,LABEL(1,1),VALUE(1,1),VALUE(1,2),VALUE(1,3) (1X,A8,' ',F10.4,' ',F14.4,' ',F15.3) /NOPR RESUME,TABLE_2 /GOPR /COM, /COM, ***************************************** /COM, USING SOLID 185 ELEMENT (3-D ANALYSIS) /COM, ***************************************** /COM, *VWRITE,LABEL(1,1),VALUE(1,1),VALUE(1,2),VALUE(1,3) (1X,A8,' ',F10.4,' ',F14.4,' ',F15.3) /NOPR RESUME,TABLE_3 /GOPR /COM, /COM, ******************************************************** /COM, USING SOLID 186 ELEMENT (3-D ANALYSIS) /COM, ******************************************************** /COM, *VWRITE,LABEL(1,1),VALUE(1,1),VALUE(1,2),VALUE(1,3) (1X,A8,' ',F10.4,' ',F14.4,' ',F15.3) /NOPR /COM, /COM,----------------------------------------------------------- /OUT, FINISH *LIST,vm279,vrt