涡流控制在小展弦比飞翼布局飞机上的应用研究  

Vortex control in low aspect ratio flying wing

作　　者：孔轶男[1] 黄建栋[1] 王立新[1] 李林[1] 

机构地区：[1]北京航空航天大学航空工程与科学学院,北京100083

出　　处：《空气动力学学报》2008年第4期435-439,共5页Acta Aerodynamica Sinica

基　　金："973"国家安全重大基础资助项目

摘　　要：全隐身布局飞行器采用无尾飞翼布局,此种布局具有很多优点,但是在动态特性上存在一些新的问题,造成了飞行器稳定和操纵的困难。通过对小展弦比飞翼布局飞机进行涡流控制,可以产生较大的控制力矩,从而对飞机进行纵向和航向的控制,改善飞机的操纵效率。控制力矩是非线性变化的,其大小与飞机飞行状态(迎角、速度等)以及喷流的状态(喷流速度、喷孔位置、喷流方向等)有关。将喷流产生的控制力矩应用于飞机的控制,通过对增加喷流后飞机静操纵特性的分析,表明其改善了飞机静操纵特性和隐身性能,具有较好的实用性。Because the flying wing aircraft with low aspect ratio cancels the traditional stabilizers and control surfaces which are used in traditional configuration, many disadvantages of dynamic characteristic arise. The goal of this research is through vortex control over low aspect ratio flying wing to overcome some disadvantages. Vortex control could provide a large fore and moment,which could be used to manipulate airplane. The moment is nonlinear,and varies with the fly state and injection state such as attack angle, velocity,jet position and so on. The effectiveness of the vortex control improves as the injection mass flow rate is increased. Results demonstrate the ability of symmetric and asymmetric trailing edge jet injection to control the leadingedge vortex. Vortex control enhances the static control of airplane and enhances airplane＇s stealth ability.

关 键 词：小展弦比飞翼 涡流控制 喷流系数 操纵特性 

分 类 号：V212.12[航空宇航科学与技术—航空宇航推进理论与工程]