This paper reports an active method for aerodynamic force control of a hypersonic spacecraft via shock wave mitigation with plasma energy deposition. The energy deposition was generated by quasi-direct current discharge at two positions in the streamwise direction on a flat plate upstream a compression surface. Wind tunnel experiments of visualizing a Mach 6 flow over a ramp with high-speed schlieren imaging were performed to verify the method's effect on diluting a shock wave. Meanwhile, the Reynolds averaged Navier-Stokes equations, with a source term of simulating plasma heating due to discharge, were solved to evaluate the method's control abilities. From the experimental results, low-density plasma layers can be formed by quasi-DC discharge, which were continuously weakening the shock wave induced by the ramp. The numerical results predicted flow topology under control well with the experimental schlieren images, with the corresponding force reduction rate as high as 58%, which mainly depends on the amount of energy injection, instead of arrangement of heating zones in this study.

本文报告了一种通过等离子体能量沉积减轻冲击波来控制高超音速航天器气动力的主动方法。能量沉积是通过在压缩表面上游平板上沿流向方向的两个位置处的准直流放电产生的。进行了使用高速纹影成像可视化斜坡上 6 马赫气流的风洞实验，以验证该方法对稀释冲击波的效果。同时，求解雷诺平均纳维-斯托克斯方程，源项模拟放电引起的等离子体加热，以评估该方法的控制能力。从实验结果来看，准直流放电可以形成低密度等离子体层，不断减弱斜坡引起的激波。