等离子体激励器对微型飞行器横航向气动力矩控制的实验研究

Abstract

Abstract: Base on the existing research of flow field characteristics of plasma actuators, a study is made to apply these actuators to micro air vehicle(MAV) for aerodynamic control. The single dielectric barrier discharge (SDBD) plasma actuators asymmetrically placed on the leeward of the wings of MAVs are found to generate rolling and yawing moments when the flow speed is 9.1 m/s. In addition to force measurement experiment, a flow visualization experiment using particle image velocimetry(PIV)technology is carried out, and the flow control result on leeward is discussed. Base on the above work,the directional-lateral aerodynamic moment control mechanism is analyzed. The ratio control of the rolling and yawing moment is realized through changing the input voltage, duty cycle and frequency of the plasma actuators.

Key words: micro air vehicle, plasma actuator, flow control, directional-lateral aerodynamic moment, particle image velocimetry

CLC Number:

V211.7

DU Hai, SHI Zhiwei, GENG Xi, WEI Dechen. Experimental Study of Directional-lateral Aerodynamic Moment Control of Micro Air Vehicle by Plasma Actuators[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(10): 1781-1790.

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Experimental Study of Directional-lateral Aerodynamic Moment Control of Micro Air Vehicle by Plasma Actuators

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