### Abstract

Minimum-time escape trajectories using a solar sail for propulsion are presented. Results are obtained from a direct collocation with nonlinear programming optimization algorithm which indicate that previous assumptions of the near-optimality for minimum time escape by maximizing the instantaneous rate of increase in total orbital energy may not always be correct. Under some circumstances, reduced escape times can be achieved by temporarily decreasing orbital energy at opportune points along the escape trajectory. These unanticipated results have motivated the development of a feasible trajectory generator using a search technique known as a rapidly-exploring random tree that is capable of negotiating multi-modal search spaces to find counter-intuitive escape trajectories - i.e., trajectories that move inward towards the central body before escaping. These feasible trajectories can then be used as initial guesses for gradient-based optimization techniques.

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

Article number | AAS 04-279 |

Pages (from-to) | 2809-2828 |

Number of pages | 20 |

Journal | Advances in the Astronautical Sciences |

Volume | 119 |

Issue number | SUPPL. |

State | Published - Aug 26 2005 |

Externally published | Yes |

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### ASJC Scopus subject areas

- Aerospace Engineering
- Space and Planetary Science

### Cite this

*Advances in the Astronautical Sciences*,

*119*(SUPPL.), 2809-2828. [AAS 04-279].

**Optimal counter-intuitive solar sail escape trajectories.** / Hartmann, John W.; Coverstone, Victoria; Prussing, John E.

Research output: Contribution to journal › Article

*Advances in the Astronautical Sciences*, vol. 119, no. SUPPL., AAS 04-279, pp. 2809-2828.

}

TY - JOUR

T1 - Optimal counter-intuitive solar sail escape trajectories

AU - Hartmann, John W.

AU - Coverstone, Victoria

AU - Prussing, John E.

PY - 2005/8/26

Y1 - 2005/8/26

N2 - Minimum-time escape trajectories using a solar sail for propulsion are presented. Results are obtained from a direct collocation with nonlinear programming optimization algorithm which indicate that previous assumptions of the near-optimality for minimum time escape by maximizing the instantaneous rate of increase in total orbital energy may not always be correct. Under some circumstances, reduced escape times can be achieved by temporarily decreasing orbital energy at opportune points along the escape trajectory. These unanticipated results have motivated the development of a feasible trajectory generator using a search technique known as a rapidly-exploring random tree that is capable of negotiating multi-modal search spaces to find counter-intuitive escape trajectories - i.e., trajectories that move inward towards the central body before escaping. These feasible trajectories can then be used as initial guesses for gradient-based optimization techniques.

AB - Minimum-time escape trajectories using a solar sail for propulsion are presented. Results are obtained from a direct collocation with nonlinear programming optimization algorithm which indicate that previous assumptions of the near-optimality for minimum time escape by maximizing the instantaneous rate of increase in total orbital energy may not always be correct. Under some circumstances, reduced escape times can be achieved by temporarily decreasing orbital energy at opportune points along the escape trajectory. These unanticipated results have motivated the development of a feasible trajectory generator using a search technique known as a rapidly-exploring random tree that is capable of negotiating multi-modal search spaces to find counter-intuitive escape trajectories - i.e., trajectories that move inward towards the central body before escaping. These feasible trajectories can then be used as initial guesses for gradient-based optimization techniques.

UR - http://www.scopus.com/inward/record.url?scp=23844542042&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=23844542042&partnerID=8YFLogxK

M3 - Article

AN - SCOPUS:23844542042

VL - 119

SP - 2809

EP - 2828

JO - Advances in the Astronautical Sciences

JF - Advances in the Astronautical Sciences

SN - 1081-6003

IS - SUPPL.

M1 - AAS 04-279

ER -