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.

为了同时解决夹具形状设计和空气动力学形状设计的问题，在空气热结构分析模型的基础上，提出了一种耦合优化方法，建立了耦合系统的伴随方程。 。为了证明这种方法，对超音速机翼进行了优化，其目标功能是考虑气动载荷和气动加热引起的机翼结构弹性变形的升力/阻力比。自变量是沿翼展的机翼截面的几何扭曲角，蒙皮的厚度以及翼梁和桁条的横截面几何参数。约束条件是机翼结构的强度。当最大允许质量为700 kg时，结果显示举升/拖动比从6.0505增加到6。2875，并且满足所有约束条件。因此，耦合优化方法是有效的。并且该方法可以通过最大质量约束来控制结构质量的增加。