等离子推进无人机的电空气动力学研究

针对一种新兴的等离子推进无人机概念开展其电空气动力学研究，并通过数值仿真论证等离子推进系统作为无人机主推力系统的可行性。等离子推进无人机的飞行原理是利用一种非对称高压电极组电晕放电实现空气电离，并通过高压电场实现离子加速，从而产生推力推动无人机飞行。相比于传统无人机，等离子推进无人机具有较低机械疲劳、飞行噪音小和能量利用效率高的优点。本文完成了等离子推进无人机组成设计，并对单等离子推进器和等离子推进无人机整体电空气动力学进行了理论研究和数值仿真。单等离子推进器数值仿真结果表明，随着工作电压的升高，单位长度推进器所能产生的推力单调递增。且在相同施加电压情况下，等离子推进器电极间隙越小，所能产生的推力越大。等离子推进无人机飞行仿真结果表明，通过优化等离子推进器结构，施加足够高的电极组电压，等离子推进无人机能够实现稳定飞行。

Electroaerodynamics Study of the Plasma-Propelled Unmanned Aerial Vehicle

The electroaerodynamics of a novel unmanned aerial vehicle (UAV), which is named as plasma-propelled UAV, is studied in this paper. Through numerical simulations, the feasibility of plasma propulsion system as the main thrust system of UAV is demonstrated. The flight principle of plasma-propelled UAV is that the air ionization and ion acceleration are achieved by corona discharge of an asymmetric high-voltage electrode group. Compared with traditional UAVs, the plasma-propelled UAVs have the advantages of low mechanical fatigue, low flight noise and high energy efficiency. The composition design of plasma-propelled UAV is completed, and the theoretical research and numerical simulations of the single plasma thruster and plasma-propelled UAV are implemented. The numerical simulation results of single plasma thruster show that the thrust per unit length of thruster increases monotonously with the increase of working voltage. Under the same voltage, the smaller the gap between the plasma thruster electrodes, the greater the thrust generated. The flight simulation results of the plasma-propelled UAV show that the stable flight of the UAV can be achieved by optimizing the structure of the plasma thruster and applying a sufficiently high voltage of the electrodes.