Effectiveness of direct current discharge on hypersonic aerodynamic control for a conical model with ramps
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摘要: 本文基于直流放电激波重构气动力控制原理，开展了带斜坡锥体模型的高超声速（Ma = 6）气动力控制风洞试验，采用光纤天平技术考察了模型在两种放电功率（284 W和517 W）下的气动力/力矩变化情况，并采用纹影成像研究了放电对流动拓扑的影响。纹影图像揭示了由于放电热阻塞和马赫数降低引起的波系重构现象，表现为放电诱导压缩波和再附激波弱化、角度减小。天平信号验证了放电使得模型的轴向力、法向力和俯仰力矩减小，放电功率较大时控制效果明显。通过求解带功率密度源项的Navier-Stokes方程模拟放电的加热效应，数值研究了模型气动力随功率密度的变化规律及加热位置对控制能力的影响。研究表明，模型气动力变化率与功率密度呈正相关；当以激励器的上游位置为参考点时，俯仰力矩变化显著；当加热位置靠近斜坡时，控制能力降低。Abstract: Based on the aerodynamic control principle of the direct current discharge that reconstructs a shock wave, the wind tunnel experiments at Mach 6 of hypersonic aerodynamic control for a conical model with ramps were conducted. The aerodynamic force/torque variations of the model at two discharge powers (284 W and 517 W) were acquired using fiber optic balance, and the corresponding changes of flow topology was studied using schlieren imaging. The schlieren images reveal the shock wave reconstruction caused by the discharge, which chokes the flow and reduces the local Mach number. Specifically, the discharge induces a compression wave and causes the attachment shock weakened with its angle reduction. The balance signal shows the axial force, normal force and pitching moment of the model decrease while discharging, and their changes are prominent with a larger power output. Further, the heating effects of discharge were simulated by solving the Navier-Stokes equations with an energy source, and the aerodynamic force variation with power density, as well as the effect of heating position on control ability were studied. The results show the aerodynamic changes are positively correlated with the power density; Taking the position upstream of the actuator as the reference point, the pitching moment of the model changes significantly; When the heating zone is located closer to the ramp, the control efficiency decreases.
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图 2 试验模型及风洞试验设置示意图
Figure 2. Schematic diagram of the test model and the wind tunnel experimental setup
图 5 天平轴向力校准结果
Figure 5. Change in output value by load in the direction of the axial component of the balance
图 7 有无放电情形下的流场纹影图
Figure 7. Schlieren images of the flow fields with and without discharge
图 12 模型壁面压力云图和z = 0截面密度云图
Figure 12. The pressure contour on the wall and the density contour at plane of z = 0
图 13 不同功率密度下轴向力和法向力及其变化率的计算结果
Figure 13. Numerical results of the axial force and the normal force and their change rates at different heating powers
图 14 不同功率密度下俯仰力矩及其变化率的计算结果
Figure 14. Numerical results of the pitch moments and their change rates at different heating powers
图 15 不同功率密度下轴向力和法向力及其变化率的计算结果
Figure 15. Numerical results of the axial force and the normal force and their change rates at different heating powers
图 16 不同功率密度下俯仰力矩及其变化率的计算结果
Figure 16. Numerical results of the pitch moments and their change rates at different heating powers
表 1 试验来流参数
Table 1. The parameters of the freestream
参数 数值 马赫数 M∞ 6.1 总压 p0 0.7 MPa 总温 T0 300 K 速度 u∞ 729 m/s 静压 p∞ 400.3 Pa 静温 T∞ 35.53 K 
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表 2 基于放电参数的试验设置
Table 2. The experimental setup based on discharge parameters
输入电流I/A 输出功率P/W 标记 5 A 284 Case5A 10 A 517 Case10A
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