This work considers a metallic aeroelastic wingbox model seeded with runout blade stiffeners along the skins. Topology optimization is conducted within the shell webs of the stiffeners in order to add cutouts and holes for mass reduction. This optimization is done with a global–local approach in order to moderate the computational cost: aeroelastic loads are computed at the wing level, but the topology and sizing optimization are conducted at the panel level. Each panel is optimized separately under stress, buckling, and adjacency constraints; and it is periodically reassembled to update the trimmed aeroelastic loads. The resulting topology is baselined against a design with standard full-depth solid stiffener blades, and it is found to weigh 7.43% less.
Aeroelastic Wingbox Stiffener Topology Optimization
Journal of Aircraft ; 55 , 3 ; 1244-1251
2018-05-01
Conference paper , Article (Journal)
Electronic Resource
English
Aeroelastic Wingbox Stiffener Topology Optimization
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