For deep-space missions that remain in the vicinity of a target body, solar eclipses might become a source of major concern due to thermal and power constraints. This paper presents a method for minimizing the eclipse duration of periodic trajectories in three-body systems using synodic resonant periodic orbits. The proposed methodology successfully captures the global eclipse structure of synodic resonant periodic orbits in terms of driving parameters such as elongation and phase angles. Two-dimensional Eclipse maps are introduced to identify optimal orbit insertion conditions that avoid or minimize eclipse intervals. The validity and applicability of the proposed method is tested in the full-ephemeris model (DE430) of the Earth–Moon and Mars–Phobos systems, respectively. As a result of these investigations, we propose new science minimum-eclipse trajectories that are under consideration for the upcoming JAXA missions EQUULEUS and MMX.

对于停留在目标物体附近的深空任务，由于热量和功率的限制，日食可能成为人们关注的主要问题。本文提出了一种利用同步共振周期轨道来最小化三体系统中周期轨迹的食道持续时间的方法。所提出的方法成功地捕获了驱动参数（如伸长率和相角）方面的共鸣共振周期轨道的整体日食结构。引入了二维Eclipse映射，以识别最佳的轨道插入条件，以避免或最小化日食间隔。分别在Earth-Moon和Mars-Phobos系统的全星历模型（DE430）中测试了该方法的有效性和适用性。这些调查的结果是，