Interfacial Ply Crack Singularity (Stroh's Method): NPIB

Submit batch job to compute singularities at an interface seperating two
dissimilar anisotropic materials with a ply crack acting normal to the interface.

Instructions for using this form:

    1. Enter appropriate numbers in the boxes,
    2. enter your email address,
    3. click on submit, and
    4. wait for results to be returned to your email. (this will take about 10-seconds)
  1. Web location of results: strohplycrack.html will be sent to your email address.
  2. If your email does not provide direct email links, copy and paste the web address: http://www.jwave.vt.edu/output/strohplycrack_"unique date-time"/strohplycrack.html from the email into your web browser Location: window and look at this file to see if the job ran correctly.
  3. If the job ran correctly you can now download files from your web browser to your computer for archiving (a 4.6Gbyte read/write optical disk is available for each student to use in the SMVC for archiving large simulation files).
  4. If you submit the form "as-is", a sample of results has been archived in the directory: http://www.jwave.vt.edu/output/ARCHIVE_Examples_SAVE/strohplycrack_12-24-2000-9:52:12:764/
    Select strohplycrack.html to see a summary of the results.

Below is a brief description of a method to calculate singuariltes that exists at an interface seperating two dissimilar anisotropic materials where a ply crack terminates normal to this interface. A more complete description is give in Section 7. "Cracks Near Interfaces Between Dissimilar Anisotropic Materials"


Figure 1. Coordinates defined for stress free edge singularity Ref.[25]

It is important to note that singularities coincide with the coordinate system origin. Hence each interface singularity has a unique coordinate system. Since the objective here is to reproduce published results the same coordinate system established by Ting et al. will be used. For this module we have expanded on the solution introduced by Ting et al. and developed the numerical approach to solve for these singularities. The solution is organized into three parts: 1) transformation of fourth order stiffness tensor, Cijkl, for arbitrary rotation in the 1-3 plane, see eqn 35 Ref.[25], 2) calcuate eigenvalues, pk, and eigen vectors, νi and τij, from equations (9) and (10) Ref.[25], and 3) calcuate exponent, k (singularity) on radius, r, from the determinate of equations (21) and (22) of Ref.[26] using appropriate boundary conditions equation (36) of Ref.[26]. From these boundary conditions 18 homogeneous equations are generated. Equation coefficients are functions of elastic properties and exponent, k, on the radius vector whose origin is located at the crack tip where the singularity exists. With the elastic properties prescribed inthe NPIB form the determinate of the coefficient matrix is only a function of the exponent, k. For comparison results from Ting et al. Ref.[26] are listed below in Table 1 using the Pipes-Pagano approximation which are the default elastic properties in the NPIB form.

E1=E2=+2.100E+06,    E1=+2.000E+07
G12=G13=G23=+0.850E+06
ν21= ν31= ν32=+0.210E+00

Table 1. Stress singularity at an interface with a ply crack acting normal to the interface
Exponent
of r-k
θ=0 θ=15 θ=30 θ=45 θ=60 θ=75 θ=90
θ'=90 .676635
.500212
.5
.676012
.502156
.500222
.672441
.505068
.500236
.660488
.504813
.500227
.630471
.502297
.500314
.567537
.500314
.500048
.5
θ'=75 .675051
.500189
.433918
.665411
.500305
.446234
.646234
.500401
.466560
.616354
.500401
.485037
.571159
.500269
.496300
.5 .499859
.499688
.4322561
θ'=60 .665263
.499839
.379767
.642118
.500352
.404849
.606628
.500735
.441810
.557636
.500673
.477316
.5 .503704
.499085
.430024
.498608
.497668
.371402
θ'=45 .643963
.499012
.369508
.606474
.500092
.407075
.556388
.500639
.456342
.5 .522801
.498293
.443947
.515052
.496531
.388842
.495691
.495008
.345965
θ'=30 .609394
.498562
.391694
.557954
.499986
.442491
.5 .543655
.498192
.445399
.558434
.495380
.400299
.533668
.493226
.364378
.494600
.492252
.339747
θ'=15 .560499
.499279
.438704
.5 .557552
.498554
.444039
.592813
.495627
.400073
.595139
.492603
.369244
.553905
.490548
.349787
.497659
.489828
.340358
θ'=0 .5 .562178
.498904
.441309
.609785
.496201
.397243
.631434
.493110
.367864
.620457
.490626
.350305
.566078
.489298
.342401
.5
.489038
.341108