摘要:
基于介质阻挡与准直流电弧放电的物理过程,分析了它们的气动激励机理,建立了各自的气动激励模型,并分别研究了它们对低速和超声速流动的激励效果.结果显示：介质挡板放电等离子体气动激励机理是改变了连续流体中的三种力,即由牛顿内摩擦引起的剪切应力、由电动力学引起的体积力及由压力突变引起的冲击力,其中基于电动力学的体积力效应占主导地位;临近空间环境中体积力的作用效果更强,诱导速度更大;超声速来流下准直流电弧放电气动激励机理主要是等离子体的热阻塞效应,本文所建立的爆炸丝传热模型可以用于仿真其控制激波的过程;热电弧对于超声速来流而言就像一个具有一定斜坡角度的虚拟突起,可用于高超声速飞行器前体激波的控制.
Abstract:
Based on the physical processes of dielectric barrier discharge（DBD） and quasi-direct-current（quasi-DC） discharge,the plasma aerodynamic actuation mechanism is analyzed,then the numerical model of plasma aerodynamic actuation is founded,finally the DBD and the quasi-DC discharge plasma flow control processes are simulated in the cases of low velocity and high velocity.The results show that the aerodynamic actuation mechanism of DBD plasma is that the discharge changes three kinds of forces in continuum fluent medium,these being shear stress caused by Newton friction,body force caused by electro hydrodynamic and impulsive active force caused by pressure change,and the main aerodynamic actuation mechanism of DBD plasma is body force caused by electro hydrodynamic.The effect of body force is stronger in near space than in the sea level,plasma induced flow velocity increases in near space.The main aerodynamic actuation mechanism of quasi-DC discharge plasma in supersonic air flow is the thermal mechanism of heat plasma,the exploding wires diathermanous model found in this paper is good for the simulation of the process of surface quasi-DC discharge plasma incident shock.The effect of quasi-DC discharge plasma on the supersonic flow field is conform with the effect of protuberance with a bevel to the supersonic flow field,so it can be used to control the shock wave in supersonic aircraft.
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