可重复使用飞行器脉动压力数值模拟研究

相对于传统火箭或导弹，可重复使用飞行器的脉动压力问题更为复杂、且相关研究较少。本文采用RANS/LES混合方法模拟了可重复使用飞行器在竖立状态、跨声速飞行、超声速飞行3类典型状态下的非定常流场，并提取了典型特征位置的脉动压力。计算结果显示，竖立状态下的脉动压力发生在背风区和分离点，声压级约115 dB，频率不超过1 Hz；跨声速飞行时的脉动压力发生在机翼和尾翼上的激波振荡区域，声压级高达140 dB，频率在10 Hz左右；超声速飞行时的脉动压力发生在飞行器机翼、副翼的下表面等迎风面上出现较强逆压梯度的区域，声压级也高达140 dB，频率约为22 Hz。此外，飞行器底部等容易发生分离的部位也是容易产生较强脉动压力的位置。

Numerical Simulation of Pressure Fluctuation on Reusable Space Vehicle

Compared with traditional rockets and missiles, pressure fluctuation problems of reusable space vehicle are more complicated and few researches were carried out. By introducing RANS/LES hybrid method, this paper simulates the unsteady flow field of reusable space vehicle under typical modes including vertical status, transonic flight and supersonic flight, and extracts fluctuating pressure data from typical characteristic positions. The computing results show that, under vertical status, pressure fluctuation occurs at leeward area and separation point, sound pressure level (SPL) is around 115 dB, and frequency is no more than 1 Hz; fluctuating pressure occurs within shock oscillation zone of wings and tails at transonic speeds, SPL is around 140 dB, and frequency is around 10 Hz; fluctuating pressure of supersonic flight happens at windward area of vehicle''s wings and ailerons, where high adverse pressure gradient is observed, SPL is also around 140 dB, and frequency is around 22 Hz. Moreover, vehicle base where separation occurs also has stronger fluctuating pressure.