Abstract
This work presents a rigorous study on the free-edge stress singularity for general composite laminates (except the angle-ply and cross-ply laminates) under uniform axial strain. Based on the general solutions derived for the plies with 0°, 90° and arbitrary fiber orientations, the corresponding transcendental characteristic equations of general [θ1/θ2], [θ/0°] and [θ/90°] laminates are established by using appropriate near-field boundary conditions, respectively. To avoid numerical errors, the transcendental characteristic equations are expanded by a symbolic operation technique analytically and solved graphically. Hence, once the ply material properties and stacking sequence are known, the accurate characteristics of the free-edge stress singularity of examined composite laminates can be obtained. These will be helpful for the failure analysis of composite materials and structures.
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