/COM,ANSYS MEDIA REL. 2024R2 (05/10/2024) REF. VERIF. MANUAL: REL. 2024R2
/verify,vmr020-t2a-183
/title,vmr020-t2a-183,Edge cracked plate with uniform tensile stress
/com,
/com, Problem is taken from NAFEMS Publication
/com, "2D Test Cases in Linear Elastic Fracture Mechanics"
/com, Test case 2.1
/com,
/com, Reference: Rooke D P and Cartwright D J : Compendium
/com, of stress intensity factors, HMSO, London, England (1976)
/com,
/com, **********************************************************
/com, Stress Intensity Factor Calculation using Interaction
/com, Integral Approach
/prep7
E=207000 ! youngs modulus
NU=0.3 ! poissons ratio
sig=100 ! surface load
pi=3.141593
a=10 !crack length
et,1,plane183 ! Plane183 element
keyopt,1,3,2 ! Plane strain element
mp,ex,1,e
mp,nuxy,1,nu
k,1,-10,,
k,2,,,
k,3,10,0
k,4,10,10
k,5,-10,10
l,1,2
*rep,4,1,1
l,5,1
al,1,2,3,4,5
esize,10
kscon,2,4,1,4,0.75 ! crack tip elements
amesh,1
finish
/solu
autots,on
nsubst,10
outres,all,all
nsel,s,loc,y,0
nsel,r,loc,x,0,10
d,all,uy,0
nsel,r,loc,x,10
d,all,ux,0
nsel,all
lsel,s,line,,4
sfl,all,press,-sig
lsel,all
nsel,s,loc,y,0
nsel,r,loc,x,0
cm,crack1,node ! define the crack tip node component
nsel,all
cint,new,1
cint,type,sifs ! calculate stress intensity factors
cint,ctnc,crack1 ! crack ID
cint,ncon,3 ! number of countours
cint,symm,on ! symmetry on
cint,norm,0,2
cint,list
allsel,all
solve
fini
/out,scratch
/post1
prcint,1,,k1
*get,k_1,cint,1,ctip,node(0,0,0),,1,dtype,k1
*get,k_2,cint,1,ctip,node(0,0,0),,2,dtype,k1
*get,k_3,cint,1,ctip,node(0,0,0),,3,dtype,k1
con1 = ((pi*a)**0.5)
k1=(k_1+k_2+k_3)/3
k0=(sig*con1)
norm_sif=k1/k0
/out,
*stat,norm_sif
*DIM,LABEL,CHAR,1,5
*DIM,VALUE,,1,3
LABEL(1,1) = 'KI'
*VFILL,VALUE(1,1),DATA,3
*VFILL,VALUE(1,2),DATA,norm_sif
*VFILL,VALUE(1,3),DATA,ABS(norm_sif/3 )
SAVE,TABLE_1
FINI
/CLEAR,NOSTART
/com,*************************************************************
/com, Using J integral Calculation
/prep7
E=207000 ! youngs modulus
NU=0.3 ! poissons ratio
sig=100 ! surface load
pi=3.141593
a=10 !crack length
et,1,plane183 ! Plane183 element
keyopt,1,3,2 ! Plane strain element
mp,ex,1,e
mp,nuxy,1,nu
k,1,-10,,
k,2,,,
k,3,10,0
k,4,10,10
k,5,-10,10
l,1,2
*rep,4,1,1
l,5,1
al,1,2,3,4,5
esize,10
kscon,2,4,1,4,0.75 ! crack tip elements
amesh,1
fini
/solu
autots,on
nsubst,10
outres,all,all
nsel,s,loc,y,0
nsel,r,loc,x,0,10
d,all,uy,0
nsel,r,loc,x,10
d,all,ux,0
nsel,all
lsel,s,line,,4
sfl,all,press,-sig
lsel,all
nsel,s,loc,y,0
nsel,r,loc,x,0
cm,crack1,node ! define the crack tip node component
nsel,all
cint,new,1
cint,ctnc,crack1 ! crack ID
cint,ncon,3 ! number of countours
cint,symm,on ! symmetry on
cint,norm,0,2
cint,list
allsel,all
solve
fini
/out,scratch
/post1
prcint,1 ! Get the J1,J2,J3 values
*get,j1,cint,1,ctip,node(0,0,0),,1,,
*get,j2,cint,1,ctip,node(0,0,0),,2,,
*get,j3,cint,1,ctip,node(0,0,0),,3,,
jc1 =(abs(j1)+abs(j2)+abs(j3))/3
*stat,jc1
con1 = ((pi*a)**0.5)
con2 = E/(1-(nu*nu))
K1 = ((con2*jc1)**0.5)
k0=(sig*con1)
norm_sif = K1/k0
/out,
*status,norm_sif
*DIM,LABEL,CHAR,1,5
*DIM,VALUE,,1,3
LABEL(1,1) = 'KI'
*VFILL,VALUE(1,1),DATA,3
*VFILL,VALUE(1,2),DATA,norm_sif
*VFILL,VALUE(1,3),DATA,ABS(norm_sif/3 )
SAVE,TABLE_2
/NOPR
/COM
/OUT,vmr020-t2a-183,vrt
/COM,------------------- vmr020-t2a-183 RESULTS COMPARISON ---------------------
/COM,
/COM, | TARGET | MECHANICAL APDL | RATIO
/COM,
RESUME,TABLE_1
/COM,USING STRESS INTENSITY FACTOR CALCULATION
*VWRITE,LABEL(1,1),VALUE(1,1),VALUE(1,2),VALUE(1,3)
(1X,A8,' ',F10.3,' ',F12.3,' ',1F16.3)
/COM,
/COM,
/COM,
RESUME,TABLE_2
/COM,USING J-INTEGRAL APPROACH
/COM,
*VWRITE,LABEL(1,1),VALUE(1,1),VALUE(1,2),VALUE(1,3)
(1X,A8,' ',F10.3,' ',F12.3,' ',1F16.3)
/COM,
/COM,
/COM,
/COM,-------------------------------------------------------------------------------
/OUT
FINISH
*list,vmr020-t2a-183,vrt
