摘要
为了进一步推动等离子体流动控制技术工程化应用发展,以无人机机翼失速分离控制为研究对象,以压力及姿态角传感器为测试手段,搭建了飞行验证平台,开展了等离子体无人机(UAV)飞行试验,在真实大气环境下考核了对称布局等离子体激励器的控制能力,建立了从基础研究到工程应用的桥梁。结果表明:当在单侧机翼施加控制时,等离子体激励器能够较好地抑制无人机单侧机翼大迎角失速分离,使得该飞机产生较大的滚转角,从而实现对飞机姿态的控制。该结果为实现等离子体流动控制技术的工程应用积累了技术基础。
To boost the development of application of flow control technology using plasma actuator,aplatform for flight test is established and the Unmanned Aerial Vehicle（UAV）flight test is carried out to evaluate the control effect of symmetrical plasma actuators using pressure sensors and attitude angle sensor in realistic environment.The results indicate that flow separation around one wing of the UAV is suppressed by one symmetrical plasma actuator,and a large roll angle of the UAV is generated.Thus,the attitude control of aircraft is realized by using plasma actuator.The research can lay the foundation for the application of the plasma flow control technology.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2018年第2期115-122,共8页
Acta Aeronautica et Astronautica Sinica
基金
装备预先研究项目(51313010204)~~
