Optimization of Laminated Shells with Multiple Loading Conditions and Fabrication Constraints*

Abstract

A methodology for design of laminated conical shells subject to multiple loading conditions is described. The most significant feature of the technique is the ability to tailor the composite structure to specific envelope specifications and loading conditions within the framework of restrictive fabrication constraints. The methodology combines conventional field analysis, a field analysis sampling scheme, and a dynamic program. The methodology is general with respect to loading conditions, geometry, and field theory. Application of the method yields a laminated composite shell with equivalent strength and stiffness to a baseline design with a significant reduction in weight.

This work was sponsored by the US Air Force Materials Laboratory, Wright Patterson AFB, Ohio, USA.