大展弦比飞翼布局模型验证机飞行控制技术研究  

Research on flight control technology of the high-aspect-ratio flying wing model aircraft

作　　者：刘尚民[1] 孙健[1] 刘朝君[1] 

机构地区：[1]中国飞行试验研究院飞机所,陕西西安710089

出　　处：《飞行力学》2013年第6期558-560,565,共4页Flight Dynamics

摘　　要：飞翼布局飞机由于采用了翼身融合技术和无尾布局,具有隐形特性,军事和民用的应用潜力十分巨大。由于飞翼布局飞机本体静稳定性差,航向又不稳定,不易操纵,因此需要解决控制律和多操纵面的协调控制技术。以一种大展弦比飞翼布局模型验证机为研究对象,开展了大展弦比飞翼布局无人机的飞行控制技术研究。通过仿真手段,验证了所提出的飞翼布局无人机的飞行控制及多操纵面协调控制技术的合理性。Flying wings have a great potential both in civil and military for the stealth characteristics due to the use of blended wing-body and tailless configuration technology. Since the aircraft with flying wings have poor static stability,unstable heading,not easy to control,so it is necessary to master the control law and coordinated control technology of multi-effectors. Taking the high-aspect-ratio flying wing model aircraft as the research object,this paper studies the flight control technology of the high-aspect-ratio flying wing UAV through simulation so as to verify the flight control technology and coordinated control technology of multi-effectors.

关 键 词：飞翼布局 控制律 多操纵面协调控制 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程] V249.1