AI 中文总结
研究地月系航天器的防御机动规划难题，将其建模为地月圆型限制性三体问题下的零和微分博弈，提出带约束的离散时间微分动态规划方法与共享时间正则化，验证了相位控制的优势及参考轨道几何的重要性。
AI 中文摘要
地月系航天器工作在非线性且不稳定的环境中，这使得防御机动规划变得困难。我们在地月圆型限制性三体问题框架下，将地月系航天器的追逐与规避问题建模为零和微分博弈。每艘航天器可控制其推力与参考轨道相位，从而能沿周期轨道运动并跨越准周期环面，同时保持在参考轨道附近。我们采用带约束的离散时间微分动态规划方法求解该博弈，该方法可强制执行严格的输入约束。我们提出一种共享时间正则化方法，用于在近月 passages 附近细化离散化过程中同步两艘航天器。针对周期轨道与准周期轨道的数值结果表明，相位控制可提升机动灵活性，同时限制航天器偏离参考轨道；与连续时间形式相比，该离散时间方法具有显著的计算优势。准晕轨道与准近直线晕轨道的对比显示，近月 passages 会创造更大的逃逸机会，但也会提升交会的敏感性。这些结果表明，参考轨道几何是地月系防御任务设计的重要组成部分。
英文摘要
Cislunar spacecraft operate in nonlinear and unstable environments that make defensive maneuver planning difficult. We formulate cislunar spacecraft pursuit and evasion as a zero-sum differential game in the circular restricted three-body problem. Each spacecraft controls its thrust and reference orbit phase, enabling motion along periodic orbits and across quasi-periodic tori while remaining near the reference. We solve the game using a constrained discrete-time differential dynamic programming method that enforces hard input constraints. We propose a shared time regularization to synchronize both spacecraft while refining the discretization near close lunar passages. Numerical results on periodic and quasi-periodic orbits show that phase control improves maneuvering flexibility while limiting departure from the reference orbit. The discrete-time method also provides a large computational advantage over a continuous-time formulation. Comparisons between quasi-halo and quasi-near-rectilinear halo orbits show that close lunar passages create larger escape opportunities but also increase the sensitivity of the encounter. These results show that reference orbit geometry is an important part of defensive cislunar mission design.
CommentsInitial submission to JCGD
