关键词: 平动点, 转移轨道, 中途修正, 变结构控制

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