Abstract
A finite strip method is described for the analysis of the geometrically non-linear elastic response of composite laminated, orthotropic prismatic plate structures subjected to progressive uniform end shortening. Attention is restricted to local buckling/post-buckling behaviour so that certain simplifying assumptions related to the insignificance of movements of plate junctions can be invoked. Analyses are based on the use of both classical plate theory and first-order shear deformation plate theory and a range of finite strip models is available for use in the contexts of each of these plate theories. A description is given of a number of applications involving the post-local-buckling behaviour of box sections and top-hat-stiffened and blade-stiffened panels. In one application considering a laminated box section, results are generated using a commercial finite element package and these are seen to compare closely with the predictions of the presented finite strip method.
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