Quasi-satellite or distant retrograde orbits are stable orbits in the restricted three-body problem will be used in remote planetary satellite missions like JAXA’s Martian Moons eXploration (MMX). Due to Phobos’ irregular gravity field, the proximity operations of the MMX mission require sophisticated techniques for transfers and maintenance between different quasi-satellite orbits. This paper focuses on the design of transfer trajectories between Quasi-Satellite Orbits (QSO) around Phobos. We utilize horizontal bifurcated Multi-Revolution Periodic QSOs (MP-QSOs) that are found in the vicinity of an ellipsoidal Phobos under the assumptions of the circular Hill Problem. Transfer strategy via MP-QSOs is explored through transfer maps that illustrate transfer design space between different altitudes QSOs. It is found that transfers via MP-QSOs provide insights on minimum $\Delta$V transfers and the parameters determining the transfer cost. The proposed transfer method is explicitly applied to MMX baseline QSOs. This research has identified that transfers between high(100 × 200 km)-to-mid(50 × 100 km), mid-to-low(30 × 50 km), and lower altitude($<30$ km) QSOs via MP-QSOs can be achieved with as low as 11.63 m/s, 3.99 m/s, 1.74 m/s, and 0.97 m/s, respectively.

受限制的三体问题中的准卫星或远距离逆行轨道是稳定轨道，将用于JAXA的火星卫星飞行（MMX）等远程行星卫星任务。由于火卫一的不规则重力场，MMX任务的近距离作战需要复杂的技术来在不同的准卫星轨道之间进行转移和维护。本文重点研究火卫一附近准卫星轨道（QSO）之间的转移轨迹设计。我们利用圆形希尔问题的假设，在椭圆形火卫兵附近发现水平分叉的多周期周期性QSO（MP-QSO）。通过传输图探索了通过MP-QSO的传输策略，该图说明了不同高度的QSO之间的传输设计空间。$\Delta$V转移和确定转移成本的参数。提议的传输方法已明确应用于MMX基线QSO。本研究确定了高（100×200 km）至中（50×100 km），中至低（30×50 km）和低海拔（$<30$ km）通过MP-QSO分别实现的QSO分别低至11.63 m / s，3.99 m / s，1.74 m / s和0.97 m / s。