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Composite cylindrical panels-optimum lay-up for buckling by ranking

Rao, KP and Tripathy, Biswajit (1991) Composite cylindrical panels-optimum lay-up for buckling by ranking. In: Computers & Structures, 38 (2). pp. 217-225.

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Official URL: http://dx.doi.org/10.1016/0045-7949(91)90098-7

Abstract

Fibre-reinforced composite cylindrical panels are a typical subcomponent used in various aerospace structures. Buckling is one of the important modes of failure of such a panel. Repeated sublaminate construction is often used in practice to reduce manufacturing errors and to produce more damage-tolerant laminates. In this type of construction, the full laminate is obtained by repeating the basic sublaminate, which has a smaller number of plies. This paper deals with the determination of optimum lay-up for buckling by ranking of such fibre-reinforced plastic composite cylindrical panels (which may be solid, sandwich or stiffened) using the finite element method. The particularized form of a four-noded, 48-dof doubly curved quadrilateral laminated anisotropic thin shell finite element is used. The core/stiffener can be a corrugated composite sheet or a regular grid. The computer program developed has been used, after extensive checking for correctness, to obtain the optimum orientation scheme of the plies in the sublaminate so as to achieve maximum buckling load for typical composite cylindrical panels.

Item Type: Journal Article
Additional Information: Copyright of this article belongs to Elsevier Science.
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)
Date Deposited: 28 Jun 2007
Last Modified: 17 Jan 2012 07:05
URI: http://eprints.iisc.ernet.in/id/eprint/11295

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