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Lamination Parameters Applied to Reliability-Based In-Plane Strength Design of Composites
The efficiency of adopting lamination parameters as design variables for the reliability-based optimization of a laminated composite plate subject to in-plane loads is presented. The plate failure is evaluated by the first-ply failure (FPF) criterion, where the ply failure is evaluated based on the...
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Published in: | AIAA journal 2003-11, Vol.41 (11), p.2200-2207 |
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Main Authors: | , , |
Format: | Article |
Language: | English |
Subjects: | |
Citations: | Items that this one cites Items that cite this one |
Online Access: | Get full text |
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Summary: | The efficiency of adopting lamination parameters as design variables for the reliability-based optimization of a laminated composite plate subject to in-plane loads is presented. The plate failure is evaluated by the first-ply failure (FPF) criterion, where the ply failure is evaluated based on the Tsai-Wu criterion. According to the FPF criterion, the laminated plate is modeled as a series system consisting of every ply failure. The system reliability of the composite plate is evaluated by Ditlevsen's bounds. Each ply-failure probability is evaluated by the first-order reliability method, where the material properties and applied loads are treated as random variables. As numerical examples, two types of the reliability-based design are formulated in terms of lamination parameters. One is the reliability-maximized design of the constant-thickness plate. The other is the thickness-minimized design under the reliability constraint. Through numerical calculations, it is shown that the reliability has a single peak and a continuous distribution in the lamination parameter space. Consequently, numerical searching rapidly achieves the optimum solution. [PUBLICATION ABSTRACT] |
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ISSN: | 0001-1452 1533-385X |
DOI: | 10.2514/2.6812 |