摘要
为了减小临近空间大展弦比无人机机翼的弯矩和挠度,采用双机身和斜拉杆两种方案,对弯矩和挠度沿展向的分布进行计算与分析;同时还对斜拉杆方案下机翼受压力时的失稳特性进行研究。结果表明:两种方案均可较大程度地减小机翼弯矩和挠度;双机身方案可使最大弯矩减小为原来的24%,斜拉杆方案可使最大弯矩减小为原来的20%;且采用斜拉杆方案,在给定参数下机翼不会发生失稳现象。
In order to reduce wing root bending moment of high aspect ratio unmanned vehicle, bi fuselage and stay bar methods are used. The bending moment and deflection along the wings are calculated and analyzed. The results show that the two methods can greatly reduce the wing＇s bending moment as well as deflection. Bifuselage＇s reduction of moment can reach 24% of the original mono-fuselage and stay bar can reduce to 20%. The deflection reductions are significant too. The instability characteristics of the compressed wings with stay bars are analyzed and the result shows that the wings will not lose stability under the assuming parameter.
出处
《航空工程进展》
2013年第4期431-437,共7页
Advances in Aeronautical Science and Engineering
关键词
大展弦比
双机身
斜拉杆
弯矩
挠度
失稳
high aspect ratio
hi-fuselage
stay bar
moment
deflection
instability
