Affiliation:
1. Sikorsky Aircraft MS S-314A2 6900 Main Street Stratford, CT 06601
Abstract
A method to determine the complete state of stress at free edges of com posite laminates under combined loads (uniaxial tension or compression, moment, and out-of-plane shear) is presented. Based on the principle of minimum complementary en ergy, two coupled ordinary differential equations are derived with use of calculus of varia tions. The stresses are determined in closed form and are in good agreement with other solutions published in the literature for uniaxial tension and applied moment. This solu tion is applicable to general laminates with straight free edges and is computationally very efficient.
Subject
Materials Chemistry,Polymers and Plastics,Mechanical Engineering,Mechanics of Materials,Ceramics and Composites
Cited by
56 articles.
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