## Abstract

The space mission planning process is considered as a hybrid optimal control problem. Hybrid optimal control problems are problems that include categorical variables in the problem formulation. For example, an interplanetary trajectory may consist of a sequence of low thrust arcs, impulses and planetary flybys. However, for each choice of the structure of the mission, for example, for a particular choice of the number of planetary flybys to be used, there is a corresponding optimal trajectory. It is not a priori clear which structure will yield the most efficient mission. In this work we present a mathematical framework for describing such problems and solution methods for the hybrid optimal control problem based on evolutionary principles that have the potential for being a robust solver of such problems. As an example, the methods are used to find the optimal choice of three asteroids to visit in sequence, out of a set of eight candidate asteroids, in order to minimize the fuel required.

Original language | English (US) |
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Pages (from-to) | 73-86 |

Number of pages | 14 |

Journal | CELESTIAL MECHANICS AND DYNAMICAL ASTRONOMY |

Volume | 97 |

Issue number | 2 |

DOIs | |

State | Published - Feb 1 2007 |

## Keywords

- Evolutionary methods
- Genetic algorithms
- Mission planning
- Trajectory optimization

## ASJC Scopus subject areas

- Modeling and Simulation
- Mathematical Physics
- Astronomy and Astrophysics
- Space and Planetary Science
- Computational Mathematics
- Applied Mathematics