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针对高超声速飞行器表面驻点压力较高的问题,在马赫数5的来流条件下,分别采用单脉冲和高重频激光能量注入的方式控制弓形激波。将数值模拟结果与高时空分辨率纹影照片以及驻点压力测量结果相对比,分析了单脉冲激光能量与高超声速流场弓形激波的相互作用过程,结果表明透镜效应是激光能量沉积降低钝头体驻点压力的原因。单脉冲激光能量产生的低压区不能维持,降低驻点压力效率低,因此高重频是更有效的激光能量注入方式。优化了频率为80kHz、功率为自由流焓流6.6%的激光能量沉积位置,计算结果表明当沉积位置与钝头体表面的距离等于钝头体直径的1.5倍时,驻点压力降低了40%。在优化位置提高沉积能量大小至36.9%,可将驻点压力和热流分别降低83.3%和56.9%。
In order to deal with the problem of high pressure on the surface of hypersonic vehicles, bow shocks were controlled by single-pulse and high-repetition-rate laser energy injection respectively under Mach 5 flow. The results of numerical simulation are compared with those of high spatial and temporal resolution smear images and stagnation point pressure measurements. The interaction between the single pulse laser energy and the bowed shock wave in the hypersonic flow field is analyzed. The results show that the lens effect reduces the laser energy deposition Head body pressure point in the reason. The low-pressure region created by the single-pulse laser energy is not maintained and the pressure at the stagnation point is low, so high-frequency repetition is a more effective laser energy injection method. The laser energy deposition location with the frequency of 80 kHz and the power of 6.6% of the free-flow enthalpy flow is optimized. The calculation results show that the stagnation point pressure is reduced by 40% when the deposition location is equal to 1.5 times of the blunt body surface, . Increasing the deposition energy to 36.9% at the optimized location reduced stagnation pressure and heat flow by 83.3% and 56.9% respectively.