Composites laminates are widely used in both civil and military aircraft structures and gases cylinders leading to weight saving. However, study of the behaviour of such materials has shown that they are more damage sensitive than metallic material especially to delamination due to edge effect or low velocity impact [1]. In order to improve the performance of composite structures, advances must be made in the prediction of delamination growth and the evaluation of residual strength. The aim of this paper is to extend a delamination model valid for the plate in small displacement [2] or large displacement [3] to the case of curved structures as shells. Two kinds of approach are commonly used to study delamination growth, (i) the damage mechanics approach in which the interface enclosing the delamination is modelled by a damageable material Delamination is obtained when the damage variable reaches its maximum value [4 - 6] and (ii) the fracture mechanics approach which the present work is part.When you are citing the document, use the following link http://essuir.sumdu.edu.ua/handle/123456789/25834
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