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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2018, Vol. 39 ›› Issue (2): 121587-121587.doi: 10.7527/S1000-6893.2017.121587

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Flight test of flow separation control using plasma UAV

ZHANG Xin1, HUANG Yong2, YANG Pengyu2, ZHANG Peng2, HUANG Zhiyuan2, WANG Dawei2, LI Huaxing1   

  1. 1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
    2. Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2017-07-05 Revised:2017-08-14 Online:2018-02-15 Published:2018-02-11
  • Supported by:
    Program of Equipment Investigation in Advance (51313010204)

Abstract: To boost the development of application of flow control technology using plasma actuator, a platform 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.

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

CLC Number: