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Stiffened composite cylindrical panels�Optimum lay-up for buckling by ranking

Tripathy, B and Rao, KP (1992) Stiffened composite cylindrical panels�Optimum lay-up for buckling by ranking. In: Computers & Structures, 42 (4). pp. 481-488.

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Official URL: http://dx.doi.org/10.1016/0045-7949(92)90115-G

Abstract

Buckling of discretely stiffened composite cylindrical panels made of repeated sublaminate construction is studied using a finite element method. In repeated sublaminate construction, a full laminate is obtained by repeating a basic sublaminate, which has a smaller number of plies. This paper deals with the determination of the optimum lay-up for buckling by ranking of such stiffened (longitudinal and hoop) composite cylindrical panels. For this purpose we use the particularized form of a four-noded, 48 degrees of freedom doubly curved quadrilateral thin shell finite element together with a fully compatible two-noded, 16 degrees of freedom composite stiffener element. The computer program developed has been used, after extensive checking for correctness, to obtain an optimum orientation scheme of the plies in the sublaminate so as to achieve maximum buckling load for a specified thickness of typical stiffened 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: 30 May 2011 08:39
Last Modified: 30 May 2011 08:39
URI: http://eprints.iisc.ernet.in/id/eprint/37647

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