## Abstract

This paper develops a systematic procedure for generating optimal low-thrust transfers from one of the primaries in the elliptic restricted three-body problem (ER3BP) to a halo orbit in the three-body system. The examples all involve transfers from Earth to halo orbits about the L2 point in the Earth-Moon system. Using a transformation to the pulsating coordinate system (distances scaled by the time-varying range between primaries), it is possible to employ the method of stable manifolds to determine low-thrust trajectories that correctly inject into a specified halo orbit. The paper includes examples of both circular and elliptical halo orbits.

Original language | English (US) |
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Pages (from-to) | 1489-1505 |

Number of pages | 17 |

Journal | Advances in the Astronautical Sciences |

Volume | 99 |

Issue number | 2 |

State | Published - Dec 1 1998 |

## All Science Journal Classification (ASJC) codes

- Aerospace Engineering
- Space and Planetary Science