ePrints@IIScePrints@IISc Home | About | Browse | Latest Additions | Advanced Search | Contact | Help

Stiffened composite axisymmetric shells-optimum lay-up for buckling by ranking

Tripathy, Biswajit and Rao, KP (1993) Stiffened composite axisymmetric shells-optimum lay-up for buckling by ranking. In: Computers and Structures, 46 (2). pp. 299-309.

[img] PDF
STIFFENED_COMPOSITE-387.pdf
Restricted to Registered users only

Download (976Kb) | Request a copy

Abstract

Linear bifurcation buckling of FRP axisymmetric shells with fully compatible FRP meridional and hoop stiffeners is studied using the finite element method. Eccentricity of the stiffeners is taken into account. The composite shell and the stiffener are assumed to be made of a repeated sublaminate construction. This type of construction is used in industry to reduce manufacturing errors and to produce more damage-tolerant laminates. In this type of construction, the sublaminate consists of smaller number of plies and the required thickness of the laminate is obtained by repeating the sublaminate many times. This paper deals with the determination of the optimum lay-up scheme in the sublaminate of a composite axisymmetric shell with composite stiffener elements so as to achieve maximum buckling load for a given geometry, loading and boundary conditions using the finite element method. A four-noded, 48-DOF doubly curved quadrilateral laminated anisotropic thin shell finite element with fully compatible two-noded, 16-DOF meridional stiffener elements (MSE) and parallel circle stiffener elements (PCSE) is used. The buckling loads computed for several cases of shells (solid/stiffened) of positive and negative Gaussian curvatures with different applied loads and boundary conditions compare well with existing results in the literature. Subsequently the computer program has been used to find the optimum lay-up scheme of the plies in the sublaminate so as to achieve maximum buckling load for typical composite solid/stiffened shells.

Item Type: Journal Article
Additional Information: The copyright of this article belongs to Elsevier.
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)
Date Deposited: 26 Sep 2006
Last Modified: 19 Sep 2010 04:31
URI: http://eprints.iisc.ernet.in/id/eprint/8461

Actions (login required)

View Item View Item