基于流场增压三电极等离子体合成射流阵列的高超声速流场激波非定常性控制机理研究

高超声速飞行器发展面临诸多关键基础问题，激波/边界层干扰引起的分离激波非定常振荡便是其中之一，它会带来飞行器气动力振荡、进气道工作不稳定、结构疲劳失效、热载荷不可预测和局部严重烧蚀等问题。等离子体合成射流激励器具有控制力强、响应迅速、无需气源等优势，其高能高重频工作模式对于激波非定常性控制极具应用潜力。本项目拟在课题组发明的三电极等离子体合成射流激励器基础上，发展适用于高超声速稀薄流场环境的流场增压式激励器，获得高温高速增压气流与三电极火花/电弧放电的耦合作用规律；开展流场增压式三电极激励器高频大电流串并联工作机理研究，分析同步/异步射流阵列流场演化规律；开展流场增压式三电极激励器阵列高超声速流场激波非定常性控制研究，分析激励器阵列冲击波、热射流及诱导涡对激波与边界层的作用特征，揭示激励器阵列控制分离激波非定常振荡的作用机理和控制规律，为高超声速飞行器大范围激波非定常性控制提供新方法。

The development of hypersonic flight vehicle faces some critical foundation problems. Separation shock low-frequency oscillation caused by shock wave/boundary layer interaction is one of the problems. It will lead to aircraft buffeting, inlet instability, aerostructure fatigue, unpredictable thermal loading and severe local ablation et al. Plasma synthetic jet (PSJ) exhibits the advantages of strong control authority, fast response and lack of external air supply, and its inherent high-energy and high-frequency working characteristics are particularly suitable for shock unsteadiness control. On the basis of three-electrode PSJ actuator invented by our group, this project intends to develop a novel actuator suitable for the rarefied air environment in the hypersonic flow application through the flowfield-pressurized design method. The interaction characteristic between the high-temperature and high-speed pressurizing airflow and the spark/arc discharge of three-electrode actuator will be acquired. The high frequency and high current series and parallel operating mechanism of flowfield-pressurized three-electrode PSJ actuator will be investigated, and the flowfield evolution of the synchronous/asynchronous jet array will be analyzed. Finally, the research on the control of shock wave unsteadiness in a hypersonic flow by using flowfield-pressurized three-electrode PSJ actuator will be carried out. The effect of the blast shock, vortices and hot jets generated by actuator array on shock and boundary layer in the hypersonic flow will be analyzed. The mechanism of separation shock unsteadiness control will be acquired. A novel flow control method of large-scale shock unsteadiness for hypersonic flight vehicle will be developed.