The attention to the periodic orbit in the Earth-Moon restricted three-body system continues to grow due to its special environment and locations. This research investigates the feasibility of constructing fuel-optimal single and multiple impulse transfers between unstable periodic orbits at L₁ and L₂ points. Invariant manifolds, which could provide the appropriate initial trajectories for optimization, are analyzed deeply to enable previously unknown orbit options and potentially to reduce mission cost. A global search strategy based on comparing the orbital state of the unstable and stable manifolds, incorporated with low-thrust techniques, is performed to seek a suitable matching point for maneuver application. Then the sequential quadratic programming (SQP) is adopted to further optimize the velocity increment and obtain the single/multiple impulse optimal transfers. The associated constraint gradients are derived to achieve higher accuracy and rapidity of the algorithm. To highlight the effectivity of the transfer scheme, three-dimensional low-energy transfers between different types and spatial regions of performing single and multiple impulses are explored. The total Delta-V required varies between a few meters per second and tens of meters per second, and the related flight time is about several weeks, mainly depending on the energy of periodic orbits and the invariant manifold structure. The results obtained in this paper can provide a useful reference for the selection of escape and capture site along the manifolds, maneuver magnitude and transfer time.

由于其特殊的环境和位置，对月球受限三体系统中的周期性轨道的关注持续增长。这项研究调查了在L ₁和L _2的不稳定周期轨道之间构造燃料最佳单脉冲和多脉冲传输的可行性点。可以为优化提供合适的初始轨迹的不变流形经过深入分析，以实现以前未知的轨道选择，并有可能降低任务成本。执行基于全局比较策略的不稳定和稳定流形的轨道状态，并结合低推力技术，以寻找适合机动应用的匹配点。然后采用顺序二次规划（SQP）进一步优化速度增量并获得单次/多次脉冲最优传递。导出相关的约束梯度以实现算法的更高准确性和更快性。为了突出转移方案的有效性，探索了在执行单个和多个脉冲的不同类型和空间区域之间的三维低能传递。所需的总Delta-V在每秒几米和每秒几十米之间变化，并且相关的飞行时间大约为几周，这主要取决于周期轨道的能量和不变的流形结构。本文获得的结果可为选择沿歧管的​​逃生和俘获地点，操纵幅度和转移时间提供有用的参考。