This paper is concerned with an optimal concept design of aircraft wing from an airfoil. The airfoil itself is generated from CFD studies but there is no baseline of the wing structure. Topology optimization is recently applied for weight reduction given an operating baseline structure; here it is demonstrated that this optimization can be used to derive the concept of the wing structure directly. The optimized concept design is realized in to CAD and then a composite free-size optimization is performed to determine material distribution and ply drop regions etc. Finally a composite size and shape optimization is done and the ribs thus realized are presented.

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