Aero-structural optimization of supersonic wing under thermal environment using adjoint-based optimization algorithm

For solving the problems of jig-shape design and aerodynamic shape design at the same time, based on the aero-thermo-structural (ATS) analysis model, the paper presents a coupling optimization method, in which the adjoint equations of coupling system are developed. In order to demonstrate this methodology, a supersonic wing is optimized, and its objective function is the lift-to-drag ratio considering the elastic deformation of the wing structure induced by aerodynamic load and aerodynamic heating. And independent variables are the geometric twist angles of wing sections along the span, the thickness of skin, and the cross-sectional geometrical parameters of spar and stringer. The constraint is the strength of the wing structure. When the maximum allowable mass is 700 kg, the results show that the lift-to-drag ratio is increased from 6.0505 to 6.2875, and all constraints are satisfied. Therefore, the coupling optimization method is effective. And this method can control the increment of structural mass through the maximum mass constraint.