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Optimum design for buckling of plain and stiffened composite axisymmetric shell panels/shells

Biswajit, Tripathy and Rao, KP (1993) Optimum design for buckling of plain and stiffened composite axisymmetric shell panels/shells. In: Seventh International Conference on Composite Structures, July 1993, Paisley, UK, pp. 459-467.

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Abstract

The buckling of plain and discretely stiffened composite axisymmetric shell panels/shells made of repeated sublaminate construction is studied using the finite element method. In repeated sublaminate construction, a full laminate is obtained by repeating a basic sublaminate, which has a smaller number of plies. The optimum design for buckling is obtained by determining the layup sequence of the plies in the sublaminate by ranking, so as to achieve maximum buckling load for a specified thickness. For this purpose, a four-noded 48-dof quadrilateral composite thin shell element, together with fully compatible two-noded 16-dof composite meridional and parallel circle stiffener elements are used.

Item Type: Conference Paper
Additional Information: Copyright of this article belongs to Elsevier Science Publishers Ltd, England.
Keywords: Buckling;Structural panels;Laminated composites;Finite element method;Optimization
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)
Date Deposited: 09 Jan 2008
Last Modified: 19 Sep 2010 04:38
URI: http://eprints.iisc.ernet.in/id/eprint/11099

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