Optimal Design of Laminated-Composite Circular-Cylindrical Shells Subjected to Combined Loads

[+] Author and Article Information
G. Sun

Shanghai Jiao Tong University, Shanghai, People’s Republic of China

J. S. Hansen

Institute for Aerospace Studies, University of Toronto, Downsview, Ontario, Canada M3H 5T6

J. Appl. Mech 55(1), 136-142 (Mar 01, 1988) (7 pages) doi:10.1115/1.3173619 History: Received June 18, 1987; Revised October 07, 1987; Online July 21, 2009


Optimization of the buckling load of a laminated-composite, circular-cylindrical shell subjected to axial compression, external pressure, torsion, or a combination thereof is undertaken. In the optimization procedure it is assumed that the shell has a fixed weight (length, radius and thickness); the buckling load is taken as the objective function which is maximized by adopting the lamina fiber orientations as the optimizing parameters. For the shell analysis a perturbation approach is used and the boundary conditions and nonlinear prebuckling effects are included; the analysis yields both the buckling load and the post-buckling character of the shell. The procedure developed is demonstrated for eight loading configurations. In addition, selected laminates were chosen for an experimental programme involving a series of graphite/epoxy shells. The predicted analytical and the measured experimental buckling loads are in very good agreement.

Copyright © 1988 by ASME
Your Session has timed out. Please sign back in to continue.





Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In