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http://dx.doi.org/10.7234/composres.2017.30.1.052

Optimal Design of Thick Composite Wing Structure using Laminate Sequence Database  

Jang, Jun Hwan (Helicopter Project Team, Defense Acquisition Program Administration)
Ahn, Sang Ho (Department of Automotive Engineering, Shinhan University)
Publication Information
Composites Research / v.30, no.1, 2017 , pp. 52-58 More about this Journal
Abstract
This paper presents the optimum design methodology for composite wing structure which automatically calculates the safety margin using optimization framework integrating failure modes. Particularly, its framework is possible to optimize sizing procedure to prevent failure mode which has the greatest effect on reducing the sizing time of composite structure. The main failure mode was set as the first ply failure, buckling failure mode, and bolted joint stress field, and the margin was calculated to minimize the weight. The design variable is a laminate sequence database and the responses are strain, buckling, bolted joint stress field. The objective function is the mass of the wing structure. The results of buckling analysis were compared using the finite element model to verify the robustness and reliability of Composite Optimizer.
Keywords
Wing structure; Laminate sequence design; Optimal design; Composite optimizer; Composite failure mode; Optimal algorithm;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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