大展弦比机翼翼段气动弹性效应下拓扑优化分析

Topology optimization was used to reduce the weight of aircraft structure according to the aerodynamic loads of high-aspect-ratio wing. Aerodynamic loads were obtained by using CFD/CSD numerical simulation method. Redistributions of aerodynamic loads caused by aeroelastic deformation were considered. The SIMP method was used in topology optimization. The constraint condition of the optimization is the reduction of structure weight, and the optimization objective is to minimize the flexibility of the structure. Topology optimization model was fabricated by using 3D print technique, and the feasibility of the combination topology optimization with the 3D print was proved.