一种翼身融合布局飞行器的偏离特性分析

为研究某翼身融合布局飞行器的偏离特性，在南京航空航天大学回流式低湍流度开口风洞中进行了飞机模型的大迎角静态测力试验。通过对试验结果的充分挖掘，利用横航向静稳定性判据、侧滑偏离判据、横向控制偏离参数以及Weissman组合判据进行分析，获得了飞机的大致初始偏离迎角和偏离区域，并对飞机的尾旋敏感区进行了预测。同时，利用风洞虚拟飞行试验技术进行三自由度释放验证。结果表明:该翼身融合布局飞行器的横向静稳定性较差，在很小的迎角下就可能出现非指令滚转运动，这也是造成偏离发散的主要原因；而虚拟飞行试验对偏离现象有较好的复现，与通过稳定性判据得到的偏离特性具有较好的对应关系，验证了虚拟飞行试验在偏离特性研究上的可靠性。

Departure characteristics of blended-wing-body aircraft

Static force measurements of blended-wing-body aircraft at high angles of attack were carried out in the 1 m low speed wind tunnel of Nanjing University of Aeronautics and Astronautics. By fully mining and analyzing the experimental results, the approximate initial departure angle of attack and departure region of BWB aircraft are obtained by using multiple criteria, including the static stability derivative, the dynamic directional stability parameter, the lateral control departure parameter and the Weissman chart. Besides, the spin sensitive region of BWB aircraft is predicted. At the same time, the departure is simulated by the virtual flight test in wind tunnel. The results show that the lateral stability of BWB aircraft is poor, and the non-command roll motion may occur at a very small angle of attack, which is also the main reason for the divergence of the departure. And the departure characteristics obtained from the virtual flight test and these stability criteria are in good consistency, which verifies the reliability of the virtual flight test in departure characteristics research.