针对低空小型太阳能飞行器的设计性能要求，开展了飞行器的总体设计与仿真分析。首先，基于翼载荷确定飞行器总体设计参数，选取SD 7037为基准翼型，利用Fluent软件基于非支配排序遗传算法（non-dominated sorting genetic algorithmⅡ，NSGA Ⅱ）进行翼型优化设计。然后，使用Fluent对飞行器总体相关气动特性进行仿真分析。其次，基于Workbench通过单向流固耦合方法将气动力作用于机翼表面并进行机翼结构总应力和总变形的数值模拟分析。最后，利用拓扑优化方法对翼肋结构进行优化设计，对优化后机翼结构再次进行总应力、总变形以及模态的数值分析。研究结果发现，优化后机翼翼型的阻力系数降低约2.47%，升力系数提升约5.64%，升阻比提升约8.31%；优化后机翼结构重量减小26%，最大应力降低11.77%，最大总变形降低30.81%，前四阶模态固有频率均有所提升。

In response to the design performance requirements of the small solar-powered aircraft, the overall design and simulation analysis of the aircraft was conducted. Firstly, the overall design parameters of the aircraft was determined based on wing loads, and SD7037 was selected as the reference airfoil. The fluent software was used to optimize the airfoil design based on the NSGA-Ⅱ（non-dominated sorting genetic algorithm Ⅱ). Secondly, the fluent software was used to simulate and analyze the overall aerodynamic characteristics of the aircraft. Thirdly, based on the Workbench method, the aerodynamic force was applied to the surface of the wing through the unidirectional fluid-structure coupling method, and numerical simulation analysis of the total stress and deformation of the wing structure was carried out. Finally, the topology optimization method had been used to optimize the design of the wing rib structure, and the stress, total deformation, and modal values of the optimized wing structure was analyzed again. The research results had shown that the drag coefficient of the optimized wing profile had decreased by about 2.47%, the lift coefficient had increased by about 5.64%, and the lift-to-drag ratio had increased by about 8.31%. The weight of the wing structure had decreased by 26%, the maximum stress had decreased by 11.77%, the maximum total deformation had decreased by 30.81%, and the natural frequencies of the first four modes had all increased.