Abstract: With diversiform needs of space missions, not only minimizing fuel is required for the spacecrafts interception and orbit transformation, but minimizing time is also required. The optimization of near range orbit maneuver time-energy is studied. By means of linear C-W equations, the characteristic velocity is derived for the on-orbit servicing spacecraft using two-impulse orbit. By analyzing the impact of single and mixed index on the system, the relations between time and energy under the mixed index are obtained. The goal is to minimize the weighted sum of energy and time. Based on EDA, the optimal energy and the time are found. As a result, accurate numerical simulation of optimal index in near range is realized. From the numerical results and comparison between these results, some conclusions of significance are drawn, which can provide reference for the following research.

Key words: spacecraft orbit maneuver, time and energy, two impulses orbit maneuver, Estimation of Distribution Algorithm（EDA）

摘要： 随着航天任务需求的多样化，对航天器轨道转移问题不但提出了最省燃料要求，还提出了最小时间要求。主要研究了航天器近距离双脉冲变轨燃料和时间最优问题，基于线性化C-W方程，推导了在轨服务器在双冲量变轨时的特征速度，以时间-燃料为指标构造了加权模型，分析单一和混合指标情况下对系统的影响后，得到了混合指标下时间和能量关系，通过设计分布估计算法，找到最优能量和相应的转移时间，使得燃料和时间的加权和最小，实现近距离变轨最优指标的精确数值模拟。从数值结果的对比分析中得出了一些有意义的结论，可供下一步研究参考。

关键词: 航天器轨道转移, 燃料时间, 双冲量变轨, 分布估计算法