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基于小偏差理论,对无摄动三体动力学方程沿标称轨道线性化,推导了其误差线性模型。在线性系统极点配置原理的的基础上,利用标准轨道状态向量选择闭环目标极点,通过设计闭环极点配置状态反馈增益阵K,实现了对地月系L1点附近受摄晕轨道的保持控制。针对K中三通道使用单一控制量级带来的控制误差,提出了利用入轨误差比例设计的可变反馈阵系数(Variable feedback matrix Kcoefficient,VKC)设计方法。VKC方法改善了原有控制方法的控制效果,在不同等级误差下减小跟踪方差和并获得了闭合周期轨道,试验证明了方法的有效性。
Based on the theory of small deviations, the linear model of the kinetic equation without perturbation along the nominal orbit is deduced, and its error linear model is deduced. Based on the pole assignment principle of linear system, the closed-loop target pole is selected by using the standard orbit state vector, and the state feedback gain matrix K is used to design the closed-loop pole. Aiming at the control error caused by the single control order of three channels in K, a variable feedback matrix Kcoefficient (VKC) design method is proposed. The VKC method improves the control effect of the original control method, reduces the tracking variance under different levels of error and obtains the closed periodic orbit, and the experiment proves the effectiveness of the method.