Abstract
Two aeroelastic design approaches are applied to a supersonic lambda wing configuration with the goal of improving the wing’s aeroelastic performance. Aeroelastic tailoring and active aeroelastic wing technologies are investigated in a sequential manner to quantify their benefits. Industry-standard tools are used to perform these design studies. First, a finite element model of a lambda wing is developed. Second, eight structural variants of the finite element model are created to study variations in wing stiffness. Finally, two sizing optimization processes are applied. The first is an aeroelastic sizing approach standard to MSC NASTRAN, and the second is an active aeroelastic wing design process, which is presented in this paper. The latter process integrates control and structural sizing design variables together. Both of these processes are used to size all eight structural variants. The optimized variants are compared based on weight and control surface effectiveness. Additionally, the optimal variations in percent ply utilization over the wing for the lightest weight concept are explored. It is found that applying aeroelastic tailoring simultaneously with active aeroelastic wing has the potential to reduce the aircraft gross takeoff weight by 7% in lambda wing configurations.
Published Version
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