射频放电等离子体/超声速激波耦合作用的机制研究

项目名称： 射频放电等离子体/超声速激波耦合作用的机制研究

项目编号： No.11472306

项目类型： 面上项目

立项/批准年度： 2015

项目学科： 数理科学和化学

项目作者： 宋慧敏

作者单位： 中国人民解放军空军工程大学

项目金额： 75万元

中文摘要： 等离子体流动控制是基于等离子体气动激励的新概念主动流动控制技术，可以显著提升飞行器、动力装置的气动性能。射频放电等离子体气动激励具有加热效率高、放电稳定、功率调节方便等优点，在超声速激波控制方面具有广阔的应用前景。目前，国际上采用射频放电已经取得了一定的激波控制效果，但是对射频放电等离子体/超声速激波耦合作用的机制尚不清楚。本项目在已初步实验的基础上，进行射频放电等离子体/超声速激波耦合作用的机制研究：通过等离子体发射光谱诊断，流场的高速纹影、NPLS等测试手段，揭示超声速条件射频放电等离子体的转动与振动温度、电子温度与密度，等离子体气动激励的速度场和密度场等参数随时间的演化规律；结合多场耦合数值仿真和风洞实验，获得激励参数对超声速激波控制效果的影响规律；综合分析，提出提高激励强度和控制激波能力的物理机制。本项目研究可为超/高超声速飞行器激波控制等提供新的技术途径。

中文关键词： 射频放电；等离子体；超声速流动；耦合机制；激波

英文摘要： Plasma flow control, based on plasma aerodynamic actuation, is a novel active flow control technology, which could remarkably enhance the aerodynamic performance of aircrafts and earoengines. Plasma aerodynamic actuation created by RF discharge has the advantages such as high heating efficiency, stable discharge, easy to adjust power and so on, which is promising in the field of supersonic shockwave control. At present, some research has been made on shockwave control worldwide, and relevant results have been acquired. However, the mechanism of RF discharge plasma/supersonic shockwave interaction is still not clear. In this project, according to preliminary experiment results, the mechanism investigation on the interaction between RF discharge plasma and supersonic shockwave will be studied. Through time resolved emission spectrum, high speed schlieren, nano-based planar laser scattering, particle image velocimetry and other testing approaches, the evolution rules of some key parameters with RF discharge/shockwave interacion such as rotational and vibrational temperature of molecule, electronic temperature, electron density, the temperature, pressure and density of flow field can be revealed. With the multi-physics numerical simulation and wind tunnel experiments, the influence of actuation parameters on the shockwave control effect will be concluded. The physical mechanism of actuation intensity improvement and control ability enhancement will also be discussed. The work mentioned above is expected to provide new technical solutions on shockwave control for hyper/supersonic aircraft.

英文关键词： RF discharge;Plasma;Supersonic flow;Interaction mechanism;Shock wave