Abstract
An approximate solution in the form of a polynomial is developed for the in-plane stresses near a circular hole in an orthotropic composite laminate under biaxial loading. The derived stresses are found to be in good agreement with the exact anisotropic solution for a series of laminates investigated. However, the degree of accuracy of the approximate stress distribution is strongly influenced by the laminate layup and the biaxiality ratio. The resultant stresses are then employed in a fracture mechanics model to estimate the damage initiation, growth, and final fracture of carbon fiber-epoxy plates with an open hole subjected to biaxial compression-tension static loading. Using the independently measured laminate parameters of unnotched strength and in-plane fracture toughness, the model successfully predicts the notched strength of multidirectional laminates under various biaxiality ratios.
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