飞翼布局飞行器结构拓扑优化设计

Structural topology optimization of flying wing aircraft

飞翼布局飞行器由于具有气动效率高的优势,将成为未来航空飞行器发展的主流方向,然而结构质量限制了其性能的进一步提升,结构优化是实现结构减重的重要技术。以飞翼布局飞行器内部结构为研究对象,建立拓扑优化模型,以柔顺度作为目标函数,探究飞翼布局飞行器全机内部结构的最优布置方式,分析弯曲梁构件在飞翼布局飞行器结构优化中的作用和减重机制,根据拓扑优化结果建立重构模型,同时依据Boeing第二代结构设计建立标准模型,使用尺寸优化评估重构模型相较于标准模型的减重效果。结果表明:在等柔顺度时,重构模型相比标准模型质量减少14.53%;在等质量时,重构模型相比标准模型全机柔顺度降低47.90%,并减少了44.87%的z向最大位移,拓扑优化减重和增加刚度效果显著,验证了弯曲梁构件的减重作用。研究结果可为飞翼布局飞行器结构减重优化奠定基础,建立的优化评估机制可为飞翼布局飞行器的内部结构设计提供参考。

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.