Abstract: Combining with characteristic of small midcourse correction level of transfer orbit, approximate error linear model of restricted 3-body dynamic problem in the earth-moon system is established. On this foundation, variable structure adjuster theory and model reference variable structure control theory of linear system are used to deduce midcourse control law separately. The optimal choosing method for control sub matrix b2 under different orbit injection error level and calculating method for input vector of reference model under different state are proposed. Simulation experiments compare the performance of standard orbit and re-designed correcting orbit under two kinds of variable structure theories, and analyze affection on control effect brought by r corresponding to orbit state under different characteristic points. The experimental results show validity of proposed methods.

Key words: libration point, transfer orbit, midcourse correction, variable structure control

摘要： 结合转移轨道中途修正量级较小的特点，建立了地月系限制性三体动力学问题的近似误差线性模型。在此基础上，分别利用线性系统的变结构调节器理论与模型参考变结构控制器理论推导了对应的中途修正控制律。提出了控制子矩阵b2在不同入轨误差等级下的最优选择方法和不同状态下参考模型输入向量r的计算方法。仿真实验对比了分别利用两种变结构理论进行控制时，重新规划出的修正轨道与理论轨道的性能指标，并分析了选择不同特征点处轨道状态对应的r对控制效果的影响情况。实验结果验证了所提方法的有效性。

关键词: 平动点, 转移轨道, 中途修正, 变结构控制