在制动火箭推力幅值满足连续可变的前提下,研究了月球探测器软着陆末端的垂直下落过程中的控制问题。基于线性系统跟踪控制理论,利用线性系统中的模型参考跟踪控制的方法设计了一种对指定轨迹进行跟踪的制动方案。同时为了满足耗燃最优性和安全性,根据最优化理论,对控制律中的参数进行优化,最终确定系统的控制律。仿真结果表明该设计方法是简单、有效的。 Under the condition that the thrust rocket thrust amplitude is continuously variable, the control problem of the vertical drop of the lunar probe at the soft landing end is studied. Based on the theory of linear system tracking control, a method of tracking the specified trajectory is designed by using the model reference tracking control method in linear system. At the same time, in order to meet the optimality and safety of the combustion, according to the optimization theory, the parameters in the control law are optimized and finally the control law of the system is determined. Simulation results show that the design method is simple and effective.