大展弦比太阳能无人机气动载荷计算方法研究

Aerodynamic Load Calculation of High-aspect-ratio Solar Unmanned Aerial Vehicle

从工程实用角度出发计算了某型大展弦比太阳能无人机不同设计阶段的主结构设计载荷。在初始设计阶段,通过求解平衡方程和采用涡格法计算了气动载荷分布和刚性飞机的结构载荷;在详细设计阶段,通过叠加弹性模态,采用全机配平法计算了弹性飞机的载荷。对关键的设计工况还采用了精细方法进行校核,校核结果与计算结果吻合较好,表明该计算可用于工程实践。

The main structural design loads of a solar unmanned aerial vehicle with high aspect ratio at different design stages are calculated from the perspective of practical engineering.In the initial design stage,the aerodynamic load distribution and the structural load of rigid aircraft are calculated by solving the balance equation and the vortex lattice method.In the detailed design stage,the load of the elastic aircraft is calculated by superimposing the elastic modes and using the whole aircraft balance method.The key design conditions are also checked by a fine method,and the results are in good agreement with the calculated results,which shows that the calculation can be used in engineering practice.