环月飞行器返回轨道设计与优化

A method for designing a lunar return orbit based on the Lambert problem is proposed according to the limitation of the traditional orbit design method. An orbital dynamic model is presented in three-dimensional space using new constrained parameters. The characteristics of the lunar return orbits based on this model are well studied. A function construction method is presented to deal with the optimal design with constraint conditions and an effective objective function is proposed. The orbital parameters of a certain circumlunar spacecraft are used as the initial values to design the return orbit. The results verify the effectiveness of the proposed return orbit design method and function construction method.