### Abstract

Language | English |
---|---|

Pages | 847-859 |

Number of pages | 13 |

Journal | Journal of Guidance, Control and Dynamics |

Volume | 34 |

Issue number | 3 |

DOIs | |

Publication status | Published - May 2011 |

### Fingerprint

### Keywords

- pole-sitter orbit
- hybrid propulsion
- trajectory optimisation
- earth observation

### Cite this

*Journal of Guidance, Control and Dynamics*,

*34*(3), 847-859. https://doi.org/10.2514/1.50935

}

*Journal of Guidance, Control and Dynamics*, vol. 34, no. 3, pp. 847-859. https://doi.org/10.2514/1.50935

**Generation of optimal trajectories for Earth hybrid pole sitters.** / Ceriotti, Matteo; McInnes, Colin.

Research output: Contribution to journal › Article

TY - JOUR

T1 - Generation of optimal trajectories for Earth hybrid pole sitters

AU - Ceriotti, Matteo

AU - McInnes, Colin

N1 - Impact Factor: 1.031, Half-Life: >10.0

PY - 2011/5

Y1 - 2011/5

N2 - A pole-sitter orbit is a closed path that is constantly above one of the Earth's poles, by means of continuous low thrust. This work proposes to hybridize solar sail propulsion and solar electric propulsion (SEP) on the same spacecraft, to enable such a pole-sitter orbit. Locally-optimal control laws are found with a semi-analytical inverse method, starting from a trajectory that satisfies the pole-sitter condition in the Sun-Earth circular restricted three-body problem. These solutions are subsequently used as first guess to find optimal orbits, using a direct method based on pseudospectral transcription. The orbital dynamics of both the pure SEP case and the hybrid case are investigated and compared. It is found that the hybrid spacecraft allows savings on propellant mass fraction. Finally, it is shown that for sufficiently long missions, a hybrid pole-sitter, based on mid-term technology, enables a consistent reduction in the launch mass for a given payload, with respect to a pure SEP spacecraft.

AB - A pole-sitter orbit is a closed path that is constantly above one of the Earth's poles, by means of continuous low thrust. This work proposes to hybridize solar sail propulsion and solar electric propulsion (SEP) on the same spacecraft, to enable such a pole-sitter orbit. Locally-optimal control laws are found with a semi-analytical inverse method, starting from a trajectory that satisfies the pole-sitter condition in the Sun-Earth circular restricted three-body problem. These solutions are subsequently used as first guess to find optimal orbits, using a direct method based on pseudospectral transcription. The orbital dynamics of both the pure SEP case and the hybrid case are investigated and compared. It is found that the hybrid spacecraft allows savings on propellant mass fraction. Finally, it is shown that for sufficiently long missions, a hybrid pole-sitter, based on mid-term technology, enables a consistent reduction in the launch mass for a given payload, with respect to a pure SEP spacecraft.

KW - pole-sitter orbit

KW - hybrid propulsion

KW - trajectory optimisation

KW - earth observation

UR - http://pdf.aiaa.org/jaPreview/JGCD/2011/PVJA50935.pdf

U2 - 10.2514/1.50935

DO - 10.2514/1.50935

M3 - Article

VL - 34

SP - 847

EP - 859

JO - Journal of Guidance, Control and Dynamics

T2 - Journal of Guidance, Control and Dynamics

JF - Journal of Guidance, Control and Dynamics

SN - 0731-5090

IS - 3

ER -