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Failure analysis; delaminated composite; bending; impact.

The present work aims at the first ply failure analysis of laminated composite plates with arbitrarily located multiple delaminations subjected to transverse static load as well as impact. The theoretical formulation is based on a simple multiple delamination model. Conventional first order shear deformation is assumed using eight-noded isoparametric quadratic elements to develop the finite element analysis procedure. Composite plates are assumed to contain both single and multiple delaminations. For the case of impact, Newmark time integration algorithm is employed for solving the time dependent multiple equations of the plate and the impactor. Tsai-Wu failure criterion is used to check for failure of the laminate for both the cases. To investigate the first ply failure, parametric studies are made for different cases by varying the size and number of delaminations as well as the stacking sequences and boundary conditions.

P K Parhi¹ S K Bhattacharyya² P K Sinha¹

1. Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur 721 302, India
2. Department of Civil Engineering, Indian Institute of Technology, Kharagpur 721 302, India

Published

April 2001