Sun–Earth/Moon $L_4$ and $L_5$ axial orbits provide ideal locations to monitor and search for near Earth asteroids. In this paper, an unstable $L_5$ axial orbit is selected as the target orbit, and then we first investigate transfers from the Earth to the target axial orbit in the ephemeris model. Based on the dynamical structure, we employ stable manifolds associated with the target axial orbit and lunar flyby technique in the preliminary design process. Then, we implement the multiple-shooting differential correction to refine the lunar flyby transfer orbit in the ephemeris model based on the preliminary design. Through a refinement strategy we proposed, a four-impulse lunar flyby transfer orbit from the initial low Earth orbit to the target axial orbit is obtained in the ephemeris model. Finally, we apply the optimal control method to design a low-thrust transfer for a small satellite to the target axial orbit based on the four-impulse transfer orbit. We obtain a low-thrust end-to-end transfer orbit with three thrust arcs via the optimization piece by piece. Numerical results indicate that the lunar flyby plays an important role in the low-thrust transfer orbit, and helps us efficiently decrease the fuel consumption.

太阳地球/月亮 ${\mathrm{大号}}_4$ 和 ${\mathrm{大号}}_5$轴向轨道为监视和搜索近地小行星提供了理想的位置。在本文中，一个不稳定的${\mathrm{大号}}_5$选择轴向轨道作为目标轨道，然后我们首先研究星历模型中从地球到目标轴向轨道的转移。基于动力学结构，我们在初步设计过程中采用了与目标轴向轨道和月球飞越技术相关的稳定歧管。然后，在初步设计的基础上，我们实施了多次射击差分校正，以细化星历模型中的月球飞越转移轨道。通过提出的改进策略，在星历模型中获得了从初始低地球轨道到目标轴向轨道的四脉冲月球飞越转移轨道。最后，我们采用最优控制方法，设计了基于四脉冲转移轨道的小卫星低推力转移到目标轴向轨道。通过逐段优化，我们获得了具有三个推力弧的低推力端到端传输轨道。数值结果表明，月球掠过在低推力转移轨道中起着重要作用，有助于我们有效地降低油耗。