Abstract
The buckling behavior of composite laminated square plates is analyzed with the aid of the finite-element method in which a modified isoparametric linear shell element is used. The in-plane and bending displacements are used together in the formulation of the finite-element method in the case of asymmetric laminates. A new method of modifying the constitutive law of composite materials to circumvent the shear-lock effect is also proposed. This new method has the useful property of removing the shear-lock effect in the case of very thin plates. Composite laminates of symmetric and asymmetric stacking sequences, with and without a central circular hole are analyzed. Using the developed program, various laminated cases are analyzed and discussed. The present results show an improvement over those found analytically when compared with experimental results for asymmetric laminates.
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