为了掌握高超声速飞行器盲腔流场的激波振荡机理,采用“双时间步”方法对轴对称吸气式高超声速飞行器内流道盲腔流场进行了非定常数值模拟。结果表明,飞行器内流道出现了非定常激波振荡现象,内流道壁面压力出现了低频高幅的周期性变化。为了消除高超声速飞行器内流道的激波振荡现象,设计了级间段泄流方案,对飞行器进行了内外流一体化定常和非定常的数值模拟。结果表明,级间段泄流方案可以有效地消除内流道的激波振荡现象。 In order to grasp the shock oscillation mechanism of the blind cavity flow field of hypersonic vehicle, the unsteady numerical simulation of the blind cavity flow field in the axial symmetric aspirated hypersonic vehicle is performed using the “double time step” method. The results show that the unsteady shock wave appears in the flow path of the aircraft, and the pressure in the inner flow channel changes cyclically with low frequency and amplitude. In order to eliminate the shock oscillation of the runner in the hypersonic vehicle, a scheme of interstage discharge was designed to simulate the steady and unsteady flow of the aircraft. The results show that the interstage discharge can effectively eliminate the shock wave in the inner flow channel.