Affiliation:
1. Department of Mechanical Engineering and Applied Mechanics The University of Michigan, Ann Arbor, Michigan 48109
2. Department of Aeronautics and Astronautics Stanford University, Stanford, California 94305
Abstract
Methods are presented for sizing composite laminates containing one, two, or several pin loaded holes, the holes being arranged either in a single row or in two parallel rows. It is shown how the design parameters (number of holes, hole diameter, hole positions) can be found, which result in the maximum failure load and in the max imum failure load per unit weight.
Subject
Materials Chemistry,Mechanical Engineering,Mechanics of Materials,Ceramics and Composites
Cited by
25 articles.
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