This paper presents a method for simultaneous optimization of the outer shape and internal topology of aircraft wings, with the objective of minimizing drag subject to lift and compliance constraints for multiple load cases. The physics are evaluated by the means of a source-doublet panel method for the aerodynamic response and linear elastic finite elements for the structural response, which are one-way coupled. At each design iteration, a mapping procedure is applied to map the current wing shape and corresponding pressure loads to the unfitted finite element mesh covering the design domain. Wings of small fixed-wing airplanes both with and without a stiffening strut are optimized. The resulting wings show internal topologies with struts and wall-truss combinations, depending on the design freedom of the shape optimization. The lift distributions of the optimized wings show patterns like the ones obtained when performing optimization of wing shapes with constraints on the bending moment at the root.

翻译：本文提出一种针对飞机机翼外形与内部拓扑的同步优化方法，以多工况条件下满足升力与柔度约束为目标实现阻力最小化。物理场评估采用源-偶极面元法计算气动响应，结合线弹性有限元法分析结构响应，两者构成单向耦合。在每个设计迭代步中，应用映射程序将当前机翼形状及对应压力载荷映射至覆盖设计域的非拟合有限元网格。针对有无加强支柱的小型固定翼飞机机翼进行优化，优化结果显示：基于形状优化设计自由度的差异，机翼内部拓扑呈现出支柱与壁-桁架组合结构。优化后的机翼升力分布显现出与根部弯矩约束下机翼外形优化结果相似的分布模式。