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等离子体无人机失速分离控制飞行实验

张鑫   

  1. 西北工业大学
  • 收稿日期:2017-07-06 修回日期:2017-08-07 发布日期:2017-08-14
  • 通讯作者: 张鑫
  • 基金资助:
    装备预先研究项目“等离子体和脉冲吹吸气对机翼的流动控制”

Flight testing of flow separation control using plasma actuator

Xin ZHANG   

  • Received:2017-07-06 Revised:2017-08-07 Published:2017-08-14
  • Contact: Xin ZHANG
  • Supported by:
    the fund of equipment investigation in advance “ Flow control on a wing using plasma actuator and unsteady blowing and suction”

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飞行实验,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角的控制。

关键词: 等离子体激励器, 流动控制, 流动分离, 无人机, 飞行实验

Abstract: In order to boost the application development of flow control technology using plasma actuator, the platform of flight testing was established and the Unmanned Aerial Vehicle (UAV) flight testing was carried out to evaluate the control effect of symmetrical plasma actuators using pressure sensors and attitude angle sensor under realistic environment. The results indicated that flow separation around one wing of UAV is suppressed by one symmetrical plasma actuator and the large roll angle of UAV is generated. These researches could lay the foundation for the application of plasma flow control technology.

Key words: plasma actuator, flow control, flow separation, UAV, flight testing