等离子体合成射流激波-激波干扰控制数值模拟  

A Numerical Simulation in Control of Shock-Shock Interference with Hypersonic Vehicle Head by Using Plasma Synthetic Jet

作　　者：崔龙泉 周岩[2] 谢玮 罗振兵[2] 彭文强 程盼 王林[2] 邓雄[2] CUI Longquan;ZHOU Yan;XIE Wei;LUO Zhenbing;PENG Wenqiang;CHENG Pan;WANG Lin;DENG Xiong(Unit 61764,Sanya 572022,Hainan,China;College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]61764部队,海南三亚572022 [2]国防科技大学空天科学学院,长沙410073

出　　处：《空军工程大学学报》2023年第2期2-9,共8页Journal of Air Force Engineering University

基　　金：国家自然科学基金(12002377,12202488,12072352)。

摘　　要：为了减弱高超声速飞行器头激波和侧翼前缘激波的干扰,建立了等离子体合成射流对高超声速飞行器激波-激波干扰控制的仿真模型,分析了等离子体合成射流激波-激波干扰控制的流场特性,探究了等离子体合成射流进行高超声速飞行器激波-激波干扰控制的效果,开展了激励器安装位置以及激励器注入能量的参数影响研究。研究表明:等离子体合成射流产生的弓形激波能使头激波抬起一定角度,减小头激波和侧翼前缘激波干扰,达到控制激波-激波干扰区热流和压力的效果;随着出口距离的增大,对热流和压力的控制效果先增大后减小;在一定范围内,注入能量越高,控制效果越好。In order to attenuate interference with the hypersonic vehicle head shocks and flank front shocks,a simulation model on plasma high-energy synthetic jet shock-shock interference control is established.The flow field characteristics of the shock-shock interference control of plasma high-energy synthetic jet waves are analyzed,the effect of plasma high-energy synthetic jet for shock-shock interference control is explored,and the parameters of the control effect are studied for the installation position and the energy size of the actuator.The results show that the bow shock generated by the high plasma energy synthetic jet enables the head shock to lift a certain angle,reducing head shock to flank leading shock disturbance,and control the effect of heat flow and pressure in the shock-shock interference area.With increase of exit distance,the control effect of heat flow and pressure increases first and then decreases.Within a certain range,the higher the energy applies,the better the control effect.

关 键 词：等离子体 合成射流 激波-激波干扰 出口距离 降热 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]