In this work, end-to-end low-thrust transfers from a GTO orbit to a low-altitude lunar orbit by exploiting the manifolds of a chosen Earth–Moon ${\text{L}}_1$ halo orbit has been studied. The practicality of piece-wise, minimum-time transfers that exploit halo orbit manifolds is demonstrated, which offers more flexibility to meet mission objectives. It is known that the structure of the manifolds varies substantially due to the presence of the Sun and its contribution has to be considered to obtain more realistic trajectories. To incorporate Sun’s perturbation, we study (1) manifolds’ behavior within a Bi-Circular Problem (BCP) dynamics and (2) Sun’s impact on the previously converged trajectories obtained using the standard Circular Restricted Three-Body Problem (CR3BP). Comparisons of the resulting trajectories using the CR3BP and BCP are presented.

在这项工作中，通过利用选定的地球-月球的流形，从GTO轨道到低空月球轨道的端到端低推力转换 ${\text{大号}}_{\mathrm{1个}}$已经研究了晕圈轨道。演示了利用光环轨道流形的分段，最短时间转移的实用性，这为实现任务目标提供了更大的灵活性。众所周知，由于太阳的存在，歧管的结构发生很大变化，必须考虑其贡献以获得更真实的轨迹。为了结合Sun的摄动，我们研究（1）双圆问题（BCP）动力学中的流形行为，以及（2）Sun对使用标准的圆受限三体问题（CR3BP）获得的先前收敛轨迹的影响。给出了使用CR3BP和BCP对所得轨迹进行的比较。