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应用数值模拟分析方法对液体火箭发动机径向不稳定燃烧完成了初步分析，并分析了声腔的阻尼特性。数值方法采用一步隐式预测、两步显式校正进行非定常流动计算的PISO算法。建立了不稳定燃烧声腔分析模型及压力挑动模型，通过模拟计算压力扰动波的传播过程考察发动机的燃烧稳定性。
The radial instability combustion of the liquid propellant rocket engine is analyzed by numerical simulation. The damping characteristics of the acoustic cavity are analyzed. The numerical method adopts one-step implicit prediction and PISO algorithm with two-step explicit correction for unsteady flow calculation. The unsteady combustion chamber analysis model and pressure provoking model were established. The combustion stability of the engine was investigated by simulating the propagation of pressure disturbance wave.