### Abstract

Development of optimal low-thrust transfer trajectories required between Earth and an Earth-Moon L2 halo orbit is examined. A general optimal solution method is constructed using sequential nonlinear programming to find minimum-propellant spacecraft transfers. Only a single thrust phase of the trajectory (using tangential steering) is optimized with the spacecraft traveling the remaining time on the stable manifold of the halo insertion point. The solution method is demonstrated for a number of insertion points on two different reference halos for the circular restricted three-body problem.

Original language | English (US) |
---|---|

Pages (from-to) | 1741-1756 |

Number of pages | 16 |

Journal | Advances in the Astronautical Sciences |

Volume | 97 PART 2 |

State | Published - 1997 |

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### All Science Journal Classification (ASJC) codes

- Aerospace Engineering

### Cite this

*Advances in the Astronautical Sciences*,

*97 PART 2*, 1741-1756.

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*Advances in the Astronautical Sciences*, vol. 97 PART 2, pp. 1741-1756.

**Optimal low-thrust trajectories to earth-moon L2 halo orbits (circular problem).** / Starchville, Thomas F.; Melton, Robert Graham.

Research output: Contribution to journal › Article

TY - JOUR

T1 - Optimal low-thrust trajectories to earth-moon L2 halo orbits (circular problem)

AU - Starchville, Thomas F.

AU - Melton, Robert Graham

PY - 1997

Y1 - 1997

N2 - Development of optimal low-thrust transfer trajectories required between Earth and an Earth-Moon L2 halo orbit is examined. A general optimal solution method is constructed using sequential nonlinear programming to find minimum-propellant spacecraft transfers. Only a single thrust phase of the trajectory (using tangential steering) is optimized with the spacecraft traveling the remaining time on the stable manifold of the halo insertion point. The solution method is demonstrated for a number of insertion points on two different reference halos for the circular restricted three-body problem.

AB - Development of optimal low-thrust transfer trajectories required between Earth and an Earth-Moon L2 halo orbit is examined. A general optimal solution method is constructed using sequential nonlinear programming to find minimum-propellant spacecraft transfers. Only a single thrust phase of the trajectory (using tangential steering) is optimized with the spacecraft traveling the remaining time on the stable manifold of the halo insertion point. The solution method is demonstrated for a number of insertion points on two different reference halos for the circular restricted three-body problem.

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UR - http://www.scopus.com/inward/citedby.url?scp=3342945217&partnerID=8YFLogxK

M3 - Article

AN - SCOPUS:3342945217

VL - 97 PART 2

SP - 1741

EP - 1756

JO - Advances in the Astronautical Sciences

JF - Advances in the Astronautical Sciences

SN - 1081-6003

ER -