An analytical model to predict delamination threshold loads of laminated composite plates with arbitrary stacking sequences, is presented. A laminated plate is considered as an assembly of two sub-laminates connected by a virtual elastic-brittle layer with infinitesimal thickness, representing the site for delamination. The problem is formulated and solved by the Rayleigh-Ritz method based on first-order shear deformation theory. The problem of quasi-static transverse impact (face-on), resulting in plate flexure, is analyzed as an example. The results, including elastic stiffness of deformation response, traction distributions over the potential delaminated interface, and threshold loads and initiating locations of delamination, are found to be in very good agreement in comparison with corresponding finite element simulations using cohesive elements. The modeling strategy, therefore, is useful for aerospace structural engineers at the preliminary design stage of laminated composite aerospace structures.
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