Abstract
A semi-analytical finite strip method is described for the analysis of the overall, geometrically non-linear, elastic behaviour of diaphragm-supported prismatic plate structures which may be made of composite laminated material and may have initial geometric imperfections. Both the large-deflection problem and the post-overall-buckling (under progressive end shortening) problem are considered. Enhanced strain-displacement relationships are used in the development of the properties of a range of finite strip models, and particular attention is paid to the appropriate representation of the longitudinal displacement. The development is made in the contexts of both first-order shear deformation and classical plate theories. A description is given of a small number of applications, most of which concern blade-stiffened panels. A comparison is made between the predictions of the developed finite strip method and those of a commercial finite element package, and such comparison is shown to be close.
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