Abstract
An optimization strategy is presented for composite wing box structure using genetic algorithm with manufacturing constraints. Firstly, on the basis of region division and key region defined, both fiber orientation angle and covered length of each ply are treated as design variables to optimize laminate thickness and stacking sequence simultaneously while maintaining laminate ply continuity. Secondly, a parallel genetic algorithm (GA) is adopted to accelerate optimization process. Finally, a composite wing box is used to demonstrate the effectiveness of the proposed method. The result shows that the optimization method can obtain optimum design with light weight which satisfies manufacturing constraints for large composite wing structure. Keywords-composite wing box; manufacturing constraints; ply
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