火花型合成射流的自耦合特性及其对喷管流动的激励机制

The fluid mechanic and aeronautical and astronautical discipline always focus on the work of the active flow control and higher performance fluidic vector nozzle technology. The synthetic characteristics of the sparkjet activated by sparkjet actuator and the thermodynamic properties of the gas in the actuator cavity are important to the performances of synthetic jet for active flow control. The interaction mechanisms of the sparkjet and the high-speed flow are related to the achievements of the thrust-vectoring for the exhaust nozzle. This project put the emphasis on the theoretical analysis model, the thermodynamic properties for the sparkjet in the procedure of the electrical discharge for the thermal heating of air inside of a cavity, the evolution of the synthetic jet in the supersonic flow and the collaborative operation pattern of the multi-sparkjets. The flow characteristics of the sparkjet and the mechanism of vector control interacted between the supersonic sparkjet and the supersonic nozzle flow will be revealed in this program. These researches are challenges technologically and supply the theoretical fundaments of using the parkjet to control the vector thrust for the vector nozzle.

流动主动控制和高性能气动矢量喷管技术是目前国际流体力学和航空宇航科学关注的研究热点之一。本项目围绕火花型合成射流的自耦合特性及激发腔体内气流热力学状态影响机制、火花型合成射流和高速气流之间的相互作用机制及其对喷管推力矢量的影响规律这两个科学问题，重点开展火花型合成射流激励过程理论分析模型、激励器火花放电过程热力学状态和合成射流在高速气流中的演化特征、以及多股合成射流的协同工作模式等内容的研究。其研究意义不仅在于探究火花型合成射流的自耦合特性及其对喷管流动的激励机制，也为探索合成射流在矢量喷管中实现有效的推力矢量流动主动控制提供技术创新的理论支撑。

流动主动控制和高性能气动矢量喷管技术是目前国际流体力学和航空宇航科学关注的研究热点之一。本项目围绕火花型合成射流的自耦合特性及激发腔体内气流热力学状态影响机制、火花型合成射流和高速气流之间的相互作用机制及其对喷管推力矢量的影响规律这两个科学问题，完善了火花型合成射流激励过程理论分析模型和数值计算方法，揭示了火花放电过程热力学状态和激励器参数对其性能的影响，设计制作了火花型合成射流激励器并开展了参数化的实验测试，实现了以合成射流控制双喉道喷管最大到达9.8°的矢量偏转。其研究意义不仅在于探究了火花型合成射流的自耦合特性及其对喷管流动的激励机制，也为探索合成射流在矢量喷管中实现有效的推力矢量流动主动控制提供技术创新的理论支撑。