Elliptic-restricted three-body problem and formation flying along an eccentric orbit

在这项工作中，我们提出了一种反馈控制系统的设计方法，用于在拉格朗日点附近的小晕轨道的产生和维持，并在晕轨道附近的地球-月球-卫星三体系统的编队飞行。本文还讨论了在连续控制、脉冲控制和脉冲控制情况下，如何设计沿着偏心轨道编队飞行的低燃料消耗反馈控制。为了使参考轨道的灵活性，我们提出了主动编队飞行的参考轨道是由一个外源系统产生的，并保持反馈控制。

In this work, we have proposed a design method of feedback control systems for the generation and maintenance of small halo orbits near a Lagrangian point and for formation flying in the vicinity of a halo orbit in the Earth-moon-satellite three-body system. We have also shown how to design feedback controls with low fuel consumption for formation flying along an eccentric orbit in the cases of continuous control, impulse control and pulse control. To allow for the flexibility of the reference orbit, we have proposed active formation flying where the reference orbit is generated by an exogenous system and is maintained by feedback controls.