环月飞行器返回轨道设计与优化

针对传统月地返回轨道设计方法在从初始轨道直接转移的局限性，提出一种基于Lambert问题的月地转移轨道设计方法。该方法重新选取了轨道约束参数，并在笛卡尔坐标系下建立了返回轨道动力学模型，并基于该模型全面分析了返回轨道关于约束参数的变化特性。此外，针对带有约束条件的返回轨道优化设计问题，提出了快速收敛的函数构造法，并给出了有效的目标函数形式。以某一在轨环月飞行器的轨道参数作为初始轨道进行返回轨道计算，结果验证了所提出返回轨道设计方法以及函数构造法的有效性。

Design and Optimization of Return Orbit of Circumlunar Spacecraft

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.