### Abstract

This paper considers halo orbit control for the Earth-moon elliptic restricted threebody problem. Expressing equations of motion with true anomaly, Lagrangian points are defined and a halo orbit control problem at the L _{2} point is discussed. By the change of control variables, constant feedback controllers are designed which maintain a halo orbit of the circular restricted problem. Considering equations of motion relative to the moon, and letting the mass of the moon go to zero, the equations of relative motion along an eccentric orbit are derived. Then formation and reconfiguration problems are formulated, and feedback controllers, based on the Hill-Clohessy-Wiltshire systems, are designed from the point of view of L_{1}-norm minimization.

Original language | English |
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Title of host publication | Astrodynamics 2009 - Advances in the Astronautical Sciences |

Subtitle of host publication | Proceedings of the AAS/AIAA Astrodynamics Specialist Conference |

Pages | 301-313 |

Number of pages | 13 |

Publication status | Published - Dec 1 2010 |

Externally published | Yes |

Event | AAS/AIAA Astrodynamics Specialist Conference - Pittsburgh, PA, United States Duration: Aug 9 2009 → Aug 13 2009 |

### Publication series

Name | Advances in the Astronautical Sciences |
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Volume | 135 |

ISSN (Print) | 0065-3438 |

### Other

Other | AAS/AIAA Astrodynamics Specialist Conference |
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Country | United States |

City | Pittsburgh, PA |

Period | 8/9/09 → 8/13/09 |

### All Science Journal Classification (ASJC) codes

- Aerospace Engineering
- Space and Planetary Science

## Fingerprint Dive into the research topics of 'From elliptic restricted three-body problem to Tschauner-Hempel equations: A control strategy based on circular problems'. Together they form a unique fingerprint.

## Cite this

*Astrodynamics 2009 - Advances in the Astronautical Sciences: Proceedings of the AAS/AIAA Astrodynamics Specialist Conference*(pp. 301-313). (Advances in the Astronautical Sciences; Vol. 135).