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用辨识方法确定了带反喷固体火箭发动机推力终止过程中的瞬变参数，视这些参数是服从正态分布的随机变量，用Montecarlo方法分析了推力终止过程内弹道的散布。结果显示，推力终止过程中不同时刻压力散布服从正态分布，据此求出了弹道散布的数字特征和分布函数，研究结果对带反喷管的固体火箭发动机设计有参考价值。
The transient parameters in the process of thrust termination with anti-jet solid rocket motor were determined by the identification method. The Monte Carlo method was used to analyze the distribution of the internal ballistics during the thrust termination process, considering these parameters as random variables subject to normal distribution. The results show that the pressure distribution obeys normal distribution at different time during the process of thrust termination, and the digital character and distribution function of trajectory dispersion are obtained. The research results are of reference value for the design of solid rocket motor with anti-nozzle.