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Abstract

The buckling of composite laminates subjected to in-plane partial edge compression is studied using a refined plate theory. In this theory, transverse shear stresses are continuous at the layer interfaces along with stress-free conditions at the top and bottom surfaces of the plate. It is quite interesting to note that the plate model having all these refined features requires unknowns only at the reference plane. However, this theory demands C¹ continuity of transverse displacement at the element edges, which is difficult to accommodate in any existing finite element. The present study is made by a new triangular element developed for the purpose.

Keywords

laminates buckling partial edge load finite element analysis

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Buckling of Composite Laminates Subjected to In-plane Partial Edge Compression using a Refined Plate Theory

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