Abstract
An initial stress iteration method using a quasi-three-dimensional finite element has been developed for the nonlinear analysis of Carbon Fibre Reinforced Plastic (CFRP) laminates subjected to a uniform inplane load. Linear and nonlinear analyses of the free edge problem were carried out for the [0/90] s, and [ ± 45] s laminates with and without resin layers included between plies of laminae. The nonlinear results show that the peak shear stress in the [0/90] s laminate and all the stress components in the [±45], laminates are reduced. A maximum strain failure criterion was used and failure modes were predicted.
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