The sensitivity analysis of static aeroelastic loads can be analytically performed by virtue of a modified stiffness matrix. However, introducing a modified stiffness matrix into the calculation will incur extra computational cost. Additionally, the intrinsic drawback of the direct method is disadvantageous for the sensitivity calculation with a large number of design variables. This paper therefore presents a novel iteration-based adjoint method for the sensitivity analysis of static aeroelastic loads acting on flexible wing, the basis of which is the static aeroelastic calculation via loosely coupled iteration between the potential-flow panel model and the structural linear finite element model. By using an iterative approach for evaluating the adjoint variable, modification to the original stiffness matrix can be obviated. Moreover, this method is more competent for the structural sensitivity analysis with a very large number of design variables, since the adjoint variable is unrelated to the designs. A rectangular wing and a swept wing are employed to demonstrate the verification of the algorithms. The design sensitivities of applied nodal forces on the structure, lift per unit span, total lift and root bending moment are calculated and analyzed. The computational cost is also discussed to further demonstrate the efficiency of the proposed method.

可以通过修改的刚度矩阵对静态气动弹性载荷进行灵敏度分析。但是，在计算中引入修改后的刚度矩阵将导致额外的计算成本。另外，直接方法的固有缺点不利于具有大量设计变量的灵敏度计算。因此，本文提出了一种新的基于迭代的伴随方法，用于对作用在柔性机翼上的静态气动弹性载荷进行敏感性分析，其基础是通过势流面板模型与结构线性有限元之间的松散耦合迭代进行的静态气动弹性计算。模型。通过使用迭代方法评估伴随变量，可以避免对原始刚度矩阵进行修改。此外，由于伴随变量与设计无关，因此该方法对于具有大量设计变量的结构敏感性分析更为有效。采用矩形翼和后掠翼来演示算法的验证。计算并分析了施加在结构上的节点力，单位跨度的升力，总升力和根部弯矩的设计灵敏度。还讨论了计算成本，以进一步证明所提出方法的效率。计算并分析了单位跨度的升力，总升力和根部弯矩。还讨论了计算成本，以进一步证明所提出方法的效率。计算并分析了单位跨度的升力，总升力和根部弯矩。还讨论了计算成本，以进一步证明所提出方法的效率。