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在前期等离子体激励器基本流场特性研究的基础上,将等离子体激励器应用于微型飞行器(MAV)进行气动控制。当来流速度为9.1m/s时,在微型飞行器机翼吸力面非对称布置不同的单介质阻挡放电(SDBD)等离子体激励器,通过对未施加激励的偏航、滚转力矩曲线和施加激励的偏航、滚转力矩曲线进行对比,发现横航向气动力距发生很大的改变,可以实现对横航向气动力矩的控制。在此基础上,采用图像测速(PIV)技术,对机翼背风面的流场进行研究,分析产生横航向控制力矩的流动机理。通过改变激励器的输入电压、占空比和调制频率,实现对横航向气动力矩的比例控制。
Based on the research of the basic flow field characteristics of the plasma actuator, the plasma actuator is applied to the MAV for the pneumatic control. When the flow velocity is 9.1m / s, single-mode plasma discharge (SDBD) plasma actuators with different asymmetry arrangement on the suction side of the micro-aircraft wing are used to simulate the non-excited yawing, Excited yaw, roll torque curve comparison and found that the lateral pitch to the great change in the aerodynamic distance, you can achieve the aerodynamic torque control of the lateral. Based on this, the flow field on the leeward side of the wing was studied by using image velocity measurement (PIV) technology, and the flow mechanism for generating transverse control torque was analyzed. By changing the input voltage of the exciter, the duty cycle and the modulation frequency, the proportional control of the aerodynamic moment in the transverse direction is realized.