Re:ANSYS Verification Test Case Descriptions 255번, 256번을 추천합니다.

2개의 예제을 조합하여 사용하시면 될것 같습니다.. 안되시면 메일주세요. <a href="http://go.daum.net/bin/go.cgi?relative=1&url=/Mail-bin/login_f.cgi%3Ferror%3Dlogin%26lu%3D/Mail-bin/send_mail.form.cgi%3FTO%3Djutopia@hanmail.net">jutopia@hanmail.net</a> VM255 Input Listing /COM,ANSYS MEDIA REL. 11.0 (10/27/2006) REF. VERIF. MANUAL: REL. 11.0 /VERIFY,VM255 /TITLE,VM255,DELAMINATION OF DOUBLE CANTILEVER BEAM USING DEBONDING /COM, REF: ALFANO, G. AND CRISFIELD, M. A., /COM, "FINITE ELEMENT INTERFACE MODELS FOR THE DELAMINATION ANALYSIS /COM, OF LAMINATED COMPOSITES: MECHANICAL AND COMPUTATIONAL ISSUES" /COM, INT. J. NUMER. METH. ENGNG 2001, 50:1701-1736. /PREP7 ET,1,PLANE182 !* 2D 4-NODE STRUCTURAL SOLID ELEMENT KEYOPT,1,1,2 !* ENHANCE STRAIN FORMULATION KEYOPT,1,3,2 !* PLANE STRAIN ET,2,PLANE182 KEYOPT,2,1,2 KEYOPT,2,3,2 ET,3,TARGE169 !* 2D TARGET ELEMENT ET,4,CONTA171 !* 2D CONTACT ELEMENT KEYOPT,4,12,5 !* BONDED ALWAYS CONTACT MP,EX,1,1.353E5 !* E11 = 135.3 GPA MP,EY,1,9.0E3 !* E22 = 9.0 GPA MP,EZ,1,9.0E3 !* E33 = 9.0 GPA MP,GXY,1,5.2E3 !* G12 = 5.2 GPA MP,PRXY,1,0.24 MP,PRXZ,1,0.24 MP,PRYZ,1,0.46 KOPEN = 1.E6 TB,CZM,2,1,1,CBDE TBDATA,1,1.7,0.28,,,1.E-5 RECTNG,0,100,0,1.5 !* DEFINE AREAS RECTNG,0,100,0,-1.5 LSEL,S,LINE,,2,8,2 !* DEFINE LINE DIVISION LESIZE,ALL,0.75 LSEL,INVE LESIZE,ALL, , ,200 ALLSEL,ALL TYPE,1 !* MESH AREA 2 MAT,1 LOCAL,11,0,0,0,0 ESYS,11 AMESH,2 CSYS,0 TYPE,2 !* MESH AREA 1 ESYS,11 AMESH,1 CSYS,0 NSEL,S,LOC,X,30,100 TYPE,3 MAT,2 REAL,3 ESEL,S,TYPE,,2 NSLE,S NSEL,R,LOC,Y ESURF !* TARGET ELEMENTS TYPE,4 REAL,3 RMODIF,3,3,-KOPEN RMODIF,3,12,-KOPEN ESEL,S,TYPE,,1 NSLE,S NSEL,R,LOC,Y NSEL,R,LOC,X,30,100 ESURF !* CONTACT ELEMENTS ALLSEL,ALL NSEL,S,LOC,X,100 !* APPLY CONSTRAINTS D,ALL,ALL NSEL,ALL FINISH /SOLU ESEL,S,TYPE,,2 NSLE,S NSEL,R,LOC,X NSEL,R,LOC,Y,1.5 !* APPLY DISPLACEMENT LOADING ON TOP D,ALL,UY,10 NSEL,ALL ESEL,ALL ESEL,S,TYPE,,1 NSLE,S NSEL,R,LOC,X NSEL,R,LOC,Y,-1.5 !* APPLY DISPLACEMENT LOADING ON BOTTOM D,ALL,UY,-10 NSEL,ALL ESEL,ALL NLGEOM,ON AUTOTS,ON TIME,1 NSUBST,40,40,40 OUTRES,ALL,ALL SOLVE !* PERFORM SOLUTION FINISH /POST26 NSEL,S,LOC,Y,1.5 NSEL,R,LOC,X,0 *GET,NTOP,NODE,0,NUM,MAX NSEL,ALL NSOL,2,NTOP,U,Y,UY RFORCE,3,NTOP,F,Y,FY PROD,4,3, , ,RF, , ,20 /TITLE,VM255, DCB: REACTION AT TOP NODE VERSES PRESCRIBED DISPLACEMENT /AXLAB,X,DISP U (mm) /AXLAB,Y,REACTION FORCE R (N) /YRANGE,0,60 XVAR,2 PLVAR,4 PRVAR,UY,RF *GET,TMAX,VARI,4,EXTREM,TMAX !* TIME CORRESPONDING TO MAX RFORCE FINISH /POST1 SET, , , , ,TMAX !* RETRIEVE RESULTS AT TMAX NSEL,S,NODE, ,NTOP !* SELECT NODE NTOP *GET,RF_NTOP,NODE,NTOP,RF,FY !* FY RFORCE AT NODE NTOP *GET,UY_NTOP,NODE,NTOP,U,Y !* DISP AT NODE NTOP CORRESPONDING TO RFORCE RF_MAX = RF_NTOP*20 !* PLANE STRAIN OPTION AND WIDTH = 20 mm SET,LAST !* RETRIEVE RESULTS AT LAST SUBSTEP *GET,RF_END,NODE,NTOP,RF,FY !* FY RFORCE AT NODE NTOP AT LAST SUBSTEP *GET,UY_END,NODE,NTOP,U,Y !* DISP AT NODE NTOP CORRESPONDING TO RFORCE RF_END = RF_END*20 !* PLANE STRAIN OPTION AND WIDTH = 20 mm *DIM,LABEL,CHAR,2,2 *DIM,VALUE,,2,3 *DIM,VALUE2,,2,3 LABEL(1,1) = 'RFORCE','DISP ' LABEL(1,2) = 'FY (N)','UY (mm)' *VFILL,VALUE(1,1),DATA,50.0,1.5 *VFILL,VALUE(1,2),DATA,RF_MAX,UY_NTOP *VFILL,VALUE(1,3),DATA,ABS(RF_MAX/50.0),ABS(UY_NTOP/1.5) *VFILL,VALUE2(1,1),DATA,24.0,10.0 *VFILL,VALUE2(1,2),DATA,RF_END,UY_END *VFILL,VALUE2(1,3),DATA,ABS(RF_END/24.0),ABS(UY_END/10.0) /COM /OUT,vm255,vrt /COM,------------------- VM255 RESULTS COMPARISON -------------- /COM, /COM, | TARGET | ANSYS | RATIO /COM, /COM,MAX RFORCE AND CORRESPONDING DISP USING DEBONDING: /COM, *VWRITE,LABEL(1,1),LABEL(1,2),VALUE(1,1),VALUE(1,2),VALUE(1,3) (1X,A8,A8,' ',F10.3,' ',1F10.3,' ',1F5.3) /COM, /COM,RFORCE CORRESPONDING TO DISP U = 10.0 USING DEBONDING: /COM, *VWRITE,LABEL(1,1),LABEL(1,2),VALUE2(1,1),VALUE2(1,2),VALUE2(1,3) (1X,A8,A8,' ',F10.3,' ',1F10.3,' ',1F5.3) /COM,----------------------------------------------------------- /OUT FINISH *LIST,vm255,vrt /COM,ANSYS MEDIA REL. 11.0 (10/27/2006) REF. VERIF. MANUAL: REL. 11.0 /VERIFY,VM256 /COM, VERIFICATION MANUAL FOR FRACTURE MECHANCIS, REL 11.0 /TITLE,VM256 FRACTURE MECHANICS STRESS INTENSITY - CRACK IN A 2D PLATE /COM REFERENCE: BROWN AND SRAWLEY, ASTM SPECIAL TECHNICAL PUBLICATION NO. 410. /COM ****** CRACK IN 2-DIMENSIONS USING 2-D PLANE183 ELEMENT ****** /PREP7 ET,1,PLANE183,,,2 ! PLANE183 (PLANE STRAIN) MP,EX,1,30E6 MP,NUXY,1,0.3 K,1 ! DEFINE KEYPOINTS AND LINE SEGMENTS K,2,4 K,3,4,5 K,4,-1,5 K,5,-1 L,1,2 L,2,3 LESIZE,2,,,4 L,3,4 LESIZE,3,,,4 L,4,5, LESIZE,4,,,6,.2 L,5,1 ESIZE,,5 KSCON,1,.15,0,8 ! DEFINE CRACK TIP ELEMENT SIZE, NO SINGULAR ELEMENTS AL,1,2,3,4,5 DL,1,1,SYMM ! APPLY SOLID MODEL BOUNDARY CONDITIONS DL,4,1,SYMM SFL,3,PRES,-.5641895 AMESH,1 OUTPR,ALL FINISH /SOLU ANTYPE,STATIC OUTRES,ALL,ALL NSEL,S,LOC,X,0,10 NSEL,R,LOC,Y,0 D,ALL,UY,0 ALLSEL,ALL NSEL,S,LOC,X,0 NSEL,R,LOC,Y,0 D,ALL,UX,0 ALLSEL,ALL NSEL,S,LOC,X,0 NSEL,R,LOC,Y,0 CM,CRACKTIP,NODE ! DEFINE CRACK TIP NODE COMPONENT ALLSEL,ALL CINT,NEW,1 ! DEFINE CRACK ID CINT,CTNC,CRACKTIP ! DEFINE CRACK TIP NODE COMPONENT CINT,SYMM,ON ! SYMMETRY ON CINT,NCON,6 ! NUMBER OF COUNTOURS CINT,NORM,0,2 ! DEFINE CRACK PLANE NORMAL CINT,LIST ALLSEL,ALL /OUT,SCRATCH SOLVE FINI /POST1 /OUT, PRCINT,1 ! PRINT THE J INTEGRAL VALUES FOR ALL PATHS *GET,J,CINT,1,,1,,6 ! GET THE J INTEGRAL VALUE FOR CRACK TIP NODE 1, COUNTOUR NUMBER 6 *STATUS,J CON1=30E6/(1-(0.3*0.3)) ! WHERE E=30E6; NU=0.3 K =(CON1*ABS(J))**0.5 *STATUS,K /OUT,SCRATCH *DIM,LABEL,CHAR,1, *DIM,VALUE,,1,3 LABEL(1,1) = 'KI ', *VFILL,VALUE(1,1),DATA,1.0249 ! STRESS INTENSITY VALUE OBTAINED FROM REFERENCE *VFILL,VALUE(1,2),DATA,K *VFILL,VALUE(1,3),DATA,ABS(K/1.0249) SAVE,TABLE_1 FINISH /CLEAR, NOSTART ! CLEAR DATABASE FOR 2ND SOLUTION /OUT, /COM ************* CRACK IN 3D PLATE USING SOLID 185 ELEMENT ******************* C /PREP7 SMRT,OFF /TITLE, VM256, FRACTURE MECHANICS STRESS INTENSITY - CRACK IN A FINITE WIDTH PLATE /COM, ****** CRACK IN 3-DIMENSIONS USING SOLID185 /COM, ET,1,SOLID185 ! SOLID 185 ELEMENT ET,2,SOLID185 ! ELEMENTS AROUND THE CRACK TIP MP,EX,1,3E7 MP,NUXY,1,0.3 CSYS,1 ! CYLINDRICAL COORDINATE SYSTEM N,1 NGEN,9,20,1 N,11,0.8 N,171,0.8,180 FILL,11,171,7,31,20 CSYS,0 ! CARTESIAN COORDINATE SYSTEM FILL,1,11,9,2,1,9,20,3 N,15,4 N,75,4,5 FILL,15,75,2,35,20 N,155,-1,5 FILL,75,155,3,95,20 N,172,-1 FILL,155,172,5,177,-1,,,.15 FILL,11,15,3,,,7,20,3 NGEN,2,200,1,177,,,,.25 /OUT,SCRATCH E,2,22,1,1,202,222,201,201 EGEN,8,20,-1 E,2,3,23,22,202,203,223,222 EGEN,8,20,-1 EGEN,9,1,-8 EGEN,5,1,73,78 E,171,151,173,172,371,351,373,372 E,151,131,174,173,351,331,374,373 E,131,132,175,174,331,332,375,374 EGEN,3,1,-1 E,134,135,155,177,334,335,355,377 TYPE,2 EMODIF,1 ! MODIFY ELEMENTS 1 TO 8 FROM TYPE,1 TO TYPE,2 *REPEAT,8,1 NUMMRG,NODE ! MERGE COINCIDENT NODES ALLSEL,ALL /OUT, NSEL,S,LOC,X,0 NSEL,R,LOC,Y,0 NLIST CM,CRACKTIP,NODE ! CRACK TIP NODE COMPONENT ALLSEL,ALL NSEL,S,LOC,X,-1 DSYM,SYMM,X ! SYMMETRY BOUNDARY CONDITIONS NSEL,S,LOC,X,0,4 NSEL,R,LOC,Y,0 DSYM,SYMM,Y ! SYMMETRY BOUNDARY CONDITIONS ALLSEL,ALL D,ALL,UZ,0 ALLSEL,ALL NSEL,S,LOC,Y,5 SF,ALL,PRES,-0.5641895 ! SURFACE PRESSURE ALLSEL,ALL FINI /SOLU AUTOTS,ON NSUBST,10 OUTRES,ALL,ALL CINT,NEW,1 ! CRACK ID CINT,NAME,CRACKTIP ! CRACK COMPONENT CINT,NCON,6 ! NO OF CONTOURS CINT,SYMM,ON ! SYMMETRY ON CINT,NORM,0,2 ! CRACK PLANE NORMAL CINT,LIST ALLSEL,ALL SAVE /NERR,0,,,, /OUT,SCRATCH SOLVE FINI /POST1 /OUT, *GET,J,CINT,1,,1,,6 ! GET J INTEGRAL VALUE FOR CRACK ID 1, CRACK TIP NODE 1, COUNTOUR 6 *STATUS,J CON1=3E7/(1-(0.3*0.3)) ! WHERE E=3E7; NU=0.3 K =(CON1*ABS(J))**0.5 *STATUS,K *DIM,LABEL,CHAR,1, *DIM,VALUE,,1,3 LABEL(1,1) = 'KI ', *VFILL,VALUE(1,1),DATA,1.0249 ! STRESS INTENSITY VALUE OBTAINED FROM REFERENCE *VFILL,VALUE(1,2),DATA,K *VFILL,VALUE(1,3),DATA,ABS(K/1.0249) SAVE,TABLE_2 FINISH /CLEAR, NOSTART ! CLEAR DATABASE FOR 3RD SOLUTION /OUT, /COM ************* SEMI CIRCULAR SURFACE CRACK IN 3D PLATE USING SOLID 186 ELEMENT ******************* C /PREP7 /TITLE,VM256 FRACTURE MECHANICS STRESS INTENSITY - SEMI CIRCULAR SURFACE CRACK IN A 3D PLATE /COM REFERENCE: RAJU, I.S.,NEWMAN, J.C., " STRESS INTENSITY FACTORS FOR A WIDE RANGE OF /COM, SEMI ELLIPTICAL SURFACE CRACK IN FINITE-THICKNESS PLATES", ENGINEERING /COM, FRACTURE MECHANICS, VOL 11, 1979, PP 817-829 /COM, ET,1,186 ! SOLID ELEMENT 186 ET,11,200,7 ! MESH 200 ELEMENT SIGM = -100 ! LOAD MP,EX,1,30E6 MP,NUXY,1,0.3 A=6 ! CRACK LENGTH B=6 ! CRACK RADIUS BW=15 ! THICKNESS BB=A+B BB2=30 ! HALF WIDTH BH=1.5 BH2=30 ! HALF HEIGHT A1=1 B1=1 LOCAL,11,1,0,0,0, 0,0,0,1,1 X1=0 Y1=0 Z1=0 X2=a Y2=0 Z2=0 X3=bb Y3=0 Z3=0 X4=bb Y4=0 Z4=bh X5=0 Y5=bw Z5=0 X6=bb Y6=bw Z6=0 X7=bb Y7=0 Z7=bh2 X8=bb2 Y8=0 Z8=0 CSYS,11 K,1,A K,2,A,90 L,1,2 K,3,A1 K,4,A1,90 L,3,4 CSYS,0 K,14,X4,Y4,Z4 ! KEYPOINTS K,11,X1,Y1,Z1 K,13,X3,Y3,Z3 K,15,X5,Y5,Z5 K,16,X6,Y6,Z6 K,17,X7,Y7,Z7 K,18,X8,Y8,Z8 L,13,14 L,14,17 L,13,18 A,11,3,4 A,3,1,2,4 A,1,13,16,15,2 VEXT,ALL,,,,,1.5 ALLSEL,ALL ESIZE,0.25 KSEL,S,,,1 KESIZE,1,0.2 KSCON,1,0.2,0,4,1.0 /OUT,SCRATCH TYPE,11 AMESH,5 ! BASE AREA AMESH,9 ! BASE AREA AMESH,13 ! BASE AREA ALLSEL,ALL EXTOPT,ACLEAR,1 TYPE,1 VSWEEP,2,9,11 VSWEEP,3,13,16 VSWEEP,1,5,7 ASEL,S,,,4 ASEL,A,,,8 ASEL,A,,,12 LESIZE,4,,,4,4 ! LINE ALONG Z DIRECTION VDRAG,ALL,,,,,,4 LESIZE,5,,,4,4 ! LINE ALONG X AXIS ASEL,S,LOC,X,BB VDRAG,ALL,,,,,,5 CSYS,11 NSEL,S,LOC,Z,0 AA = A-0.01 NSEL,R,LOC,X,AA,100000 D,ALL,UZ CSYS,0 NSEL,S,LOC,X, D,ALL,UX,0 NSEL,R,LOC,Y, NSEL,R,LOC,Z, D,ALL,UY ALLSEL,ALL NSEL,S,LOC,Z,BH2-0.001,100000 SF,ALL,PRES,SIGM ALLSEL,ALL FINI /SOLU ANTYPE,STATIC EQSLV,PCG LSEL,S,LINE,,1 /OUT, NSLL,S,1 CM,CRACKTIP,NODE ALLSEL,ALL CINT,NEW,1 ! CRACK ID CINT,CTNC,CRACKTIP ! CRACK TIP NODE COMPONENT CINT,NCON,5 ! NUMBER OF COUNTOUR CINT,NORM,0,3 ! CRACK PLANE NORMAL CINT,SYMM,ON ! SYMMETRY ON CINT,LIST ALLSEL,ALL /OUT,SCRATCH SOLVE SAVE FINI /POST1 SET,LAST PRCINT,1 ! J INTEGRAL VALUES /OUT, /COM, /COM, ********** CALCULATING STRESS INTENSITY USING CINT COMMAND ************** C *GET,J1,CINT,1,,94,,5 ! GET THE J VALUE FOR CRACK TIP NODE 94 ( 0 DEGREE) *STAT,J1 CON1 = 30E6 / (1-(0.3*0.3)) K1 = SQRT(ABS(J1)*CON1) KI1 = K1 / (100*SQRT(A)) ! STRESS INTENSITY VALUE OBTAINED FROM CINT COMMAND *STATUS,KI1 /COM, /COM, ********** CALCULATING STRESS INTENSITY USING KCALC COMMAND **************** C CS,14,0,94,680,140 ! DEFINE A LOCAL COORDINATE SYSTEM ( CRACK TIP NODE AT 0 DEGREE) CSYS,14 RSYS,14 PATH,PATH1,3,,48 ! DEFINE PATH WITH NAME = "PATH1" PPATH,1,94 ! DEFINE PATH POINTS BY NODE PPATH,2,137 PPATH,3,136 KCALC,0,1,0,1 *GET,K2,KCALC,,K,1 *STATUS,K2 KI2 = K2 / (100*SQRT(A)) *STATUS,KI2 /COM, *DIM,LABEL,CHAR,1, *DIM,VALUE,,1,3 LABEL(1,1) = 'KI ', *VFILL,VALUE(1,1),DATA,1.40 ! STRESS INTENSITY VALUE OBTAINED FROM REFERENCE FOR 0 DEGREE *VFILL,VALUE(1,2),DATA,KI1 ! STRESS INTENSITY VALUE OBTAINED FROM CINT COMMAND *VFILL,VALUE(1,3),DATA,ABS(KI1/1.40) SAVE,TABLE_3 FINISH RESUME,TABLE_1 /COM /OUT,vm256,vrt /COM,------------------- VM256 RESULTS COMPARISON -------------- /COM, /COM, | TARGET | ANSYS | 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,' ',F10.4,' ',F5.3) /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,' ',F10.4,' ',F5.3) /NOPR RESUME,TABLE_3 /GOPR /COM, /COM, ******************************************************** /COM, USING SOLID 186 ELEMENT - SURFACE CRACK (3-D ANALYSIS) /COM, ******************************************************** /COM, *VWRITE,LABEL(1,1),VALUE(1,1),VALUE(1,2),VALUE(1,3) (1X,A8,' ',F10.4,' ',F10.4,' ',F5.3) /NOPR /COM, /COM,----------------------------------------------------------- /OUT FINISH *LIST,vm256,vrt