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建立了火箭弹道仿真模型。用蒙特卡洛法对简控火箭在无控条件下进行了模拟打靶。从其所有成功子样中统计出了火箭运动参数在主动段一系列时间点上的容许偏差。分别以上述时间点为起点，综合考虑运动参数偏差及其它随机偏差的影响，对落点散布进行了仿真分析。找出了合适的简控时间终点及其运动参数容许的偏差范围，为简控系统的设计提供了直接依据。
Established a rocket trajectory simulation model. The Monte Carlo method was used to simulate the launch of a simple control rocket under uncontrolled conditions. From all of its successful subsamples, the allowable deviation of the rocket motion parameters at a series of time points in the active segment is calculated. Taking these time points as the starting points respectively, considering the influence of the deviation of motion parameters and other random deviations, the simulation of the falling scatter is carried out. Finding out the suitable end point of simple control and the allowable deviation range of its motion parameters provide a direct basis for the design of simple control system.