飞翼布局飞行器结构拓扑优化设计

Flying wing aircraft will become the mainstream of future aircraft due to its high aerodynamic efficiency; however, its performance improvement is limited by structural weight. Structural optimization is an important technique to reduce structural weight. A topology optimization model is thus established based on the internal structure of flying wing aircraft with the compliance of the aircraft skin as the objective function. The optimal arrangement of this structure is studied, and the effect and weight reduction mechanism of curvilinear spars are investigated in the structural optimization of the aircraft. The rebuilt model and the standard model are developed according to the topology optimization results and the Boeing second generation structure design respectively, using sizing optimization to evaluate the effect of topology optimization. Results show that compared with the standard model, the rebuilt model decreases the mass by 14.53% with the same compliance. The compliance of the reconstructed model is decreased by 47.90% and the maximum z-displacement is reduced by 44.87% with the same quality, showing significant decrease in weight reduction and increase in stiffness for topology optimization. The weight reduction effect of curvilinear spars is also validated. The results of this study can lay a foundation for weight reduction optimization of flying wing aircraft, and the optimization-evaluation mechanism can provide insight into the internal structural design of flying wing aircraft.