Abstract
A progressive failure analysis approach is presented for cylindrical shells. A geometrically non-linear finite element formulation (with large rotation capability based on the total Lagrangian approach is used to predict the onset of various failure modes in laminated composite plates and shells. Some of the failure modes considered include matrix cracking, fiber breakage and delamination. Failure relations in terms of 2nd Piola Kirchhoff stresses and changes in the constitutive relations due to large strain are taken into consideration. Load-carrying capabilities of the composite cylindrical shell structures, after the first ply failure, are discussed.
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