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A Simple Elasticity Solution for Predicting Interlaminar Stresses in Laminated Composites

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A simple iterative method for the approximate solution of boundary value prohlems is presented. The method is applied to the prediction of interlaminar stresses in composite laminates subjected to axial tension and torsion loads. One‐ and two‐term closed‐form approximations for the stress functions are obtained. The model predictions are compared with results of a finite difference solution, another analytical solution, and a finite element cross‐sectional analysis of flexbeam laminates under torsion.
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Document Type: Research Article

Affiliations: School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, Georgia 30332-0150

Publication date: 1999-04-01

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