Abstract
A plane stress solution for an anisotropic plate with a circular hole, developed by Savin, is extended to derive the interlaminar stresses in a centrally notched composite laminate under uniform tension. Based upon Lekhnitskii's stress potentials, theory of anisotropic elastic body and boundary layer effect, stress shapes are chosen such that the zeroth order equilibrium equations, interface continuity and boundary conditions are satisfied. The unknown parameters in the stress expressions are then determined by the requirement of stress integral equilibrium. The merit of our model is highlighted by obtaining the interlaminar stresses and the order of boundary layer stress singularity simultaneously. Several examples of [0/90]s, [±45]s and [0/90/±45]s graphite/epoxy composite laminates containing centrally circular holes are analysed.
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