ABSTRACT
I. INTRODUCTION Stress analysis for the design of composite laminates is commonly implemented by the use of computer programs based on laminated plate theory (LPT). This provides the basis for determining the elastic properties of the laminate, its response to applied membrane stresses, bending and/or twisting moments, the distribution of stress and strain in the constituent plies and also allows for a ply-by-ply failure analysis, using one or more of the standard failure criteria. The available software is convenient, efficient and user-friendly but over elaborate for the preliminary stages of design. One of the principal disadvantages of simple LPT programs is that they do not assist in determining the optimum laminate configuration or in choosing the best material system.
