Abstract
A three-dimensional finite element analysis of pin-loaded and bolted holes in (0/90) s and (90/0) s laminates has been performed. Through thickness clamping, pin-hole contact friction and laminate stiffness have been shown to contribute significantly to the resulting stress distributions. The importance of the clamping ratio, stacking sequence and clamping type are shown to have a fundamental influence on the magnitude of the interlaminar normal stress local to the bolt hole. Qualitative comparisons made with observed bearing failures in pin-loaded glass-reinforced polyester laminate specimens have given good agreement with the present finite element results.
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