APPENDIX
STRESS SINGULARITY USING STROH'S METHOD
Stress singularity at a ply crack tip acting normal to an interface of composite
laminates can be obtained using Stroh's method. The displacements ui (i=1,2,3) are in the
xi-x2 plane as shown in Figure A. 1.
Figure A. 1.Geometry of an angle-ply laminated composite and a crack normal to an
interface between two anisotropic materials.
The strains and the stresses are described as a function of x2 and x3. The
displacement, stress-strain and equilibrium equations can be written as
E, = (0u, x + a uj ax)/2 (Al)
Cl = Cijkp.- (A2)
A1-A3 can be obtained by letting
A1-A3 can be obtained by letting