基于等离子体激励的飞翼布局飞行器气动力矩控制

Aerodynamic Moment Control of Flying Wing Vehicle Using Plasma Actuators

以飞翼布局飞行器所面临的飞行控制问题为背景,采用气动力测量技术和粒子图像测速(PIV)技术,在来流风速为8.2m/s时,研究了介质阻挡放电等离子体激励器对飞翼布局飞行器气动力矩的作用。研究结果表明:在飞行器不同位置布置不同的激励器,可以实现对飞行器滚转、偏航及俯仰力矩的控制;改变激励电压,实现了对气动力矩的比例控制;通过与常规舵面的舵效进行比较,采用等离子体激励器获得的气动力矩控制,可以达到常规舵面一定偏转角度的控制效果。流场测量结果表明:等离子体激励器对飞翼布局飞行器气动力矩的控制,主要是通过控制流动分离和前缘涡破碎点位置的变化来实现的。因此,可以考虑应用等离子体流动控制技术来增强传统的舵面控制,并在提高控制效率的基础上,使其成为一种新型的飞行控制方式。

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 actu- ators 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 meas- urement 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.