本文介绍一种火箭喷管入口和喉部处燃气—颗粒混合物流场的计算模型。定常状态燃气流场按长时间的渐近解计算,颗粒流场则假设为准定常流。然后,将这个模型与超音速燃气-颗粒流场特征线解方法结合。本文介绍了计算方法,说明了喷管入口角、喷管喉部曲率半径比、喉部尺寸和颗粒大小对发动机比冲的影响,并且将计算结果与少量发动机的点火试验数据作了比较。 This paper presents a computational model for the flow field of a gas-particle mixture at the rocket nozzle inlet and throat. The steady-state gas flow field is calculated as a long-term asymptotic solution, while the particle flow field is assumed to be constant. Then, this model is combined with the method of solution characteristic of supersonic gas-particle flow field. This paper introduces the calculation method, and illustrates the effects of nozzle entrance angle, nozzle radius of curvature of throat, throat size and particle size on specific impulse of the engine, and compares the calculation results with the ignition test data of a few engines.