基于等离子体激励的飞翼布局飞行器气动力矩控制

doi:10.7527/S1000-6893.2013.0186

Abstract

Abstract:

To research the flight control of a flying wing vehicle, an experimental study of the effect of plasma actuators on the vehicle's aerodynamic moment is conducted at the wind speed of 8.2 m/s, using aerodynamic measurement and particle image velocimetry (PIV). The results show that aerodynamic moment control can be realized by using different plasma actuators with different configurations on the vehicle. By changing the driving voltage, the proportional control of the aerodynamic moment is realized. A comparison of the effect of plasma actuators with that of conventional control surfaces demonstrates that the plasma actuators can have the same effect as certain deflecting angles of the control surface. The flow field measurement results show that the flow structure on the wing is changed through restraining the flow separation and controlling the position of vortex breakdown point on the wing, which eventually changes the aerodynamic moment of the vehicle. Thus, the plasma flow control technology can be considered an auxiliary control technology for traditional control surfaces. If the control efficiency is improved, it may be considered a new method for flight control in the future.

Key words: flying wing, plasma, flow control, aerodynamic force, particle image velocimetry

CLC Number:

V211.7

DU Hai, SHI Zhiwei, NI Fangyuan, CHENG Ruibin, DAI Xinxi. Aerodynamic Moment Control of Flying Wing Vehicle Using Plasma Actuators[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013, 34(9): 2038-2046.

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Aerodynamic Moment Control of Flying Wing Vehicle Using Plasma Actuators

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