中文摘要：

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 K coefficient，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。

英文摘要：

Based on small deviation theory, the no-perturbation 3-body dynamic equations were linearized and the error linear model was deduced. Based on the pole assignment theory of linear system, station-keeping for perturbed halo orbit near L1 point in Earth-Moon system was achieved through designing the closed-loop pole assignment state feedback matrix K by choosing standard orbit state vector as closed-loop target pole. Aimed at the control error caused by single control level of three axis inK, a design method of variable feedback matrix Kcoefficient （VKC） considering the scale of orbit injection was proposed. The experiments show that the VKC method which improved control effect of original control method and decreased tracking variance sum under different error levels is available.