Abstract
An isoparametric axisymmetrical finite element is developed for the analysis of multilayer composite structures wound by wide plies. This element takes into account the variation of angle along the width of a layer for a given parallel of a revolution structure. Evaluation of strain and stress tensors is performed in mean and extreme fibre directions of a ply. Moreover, this model can represent geometrical nonlinear behaviour and material nonlinearities. The extended possibilities of this model are illustrated for two aerospace structures: a spherical wound satellite tank and the composite head of a rocket motor.
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