### Abstract

The magnitude and direction of the required acceleration creating the artificial equilibrium point (AEP) in the low-thrust restricted three-dimensional space problem are investigated. A nonequilibrium point is turned into AEP by applying the appropriate continuous control acceleration. The nondimensional magnitude of acceleration is found in terms of the sun-earth system and the required acceleration is obtained by assuming that other planets such as Mars and Venus are not near the spacecraft with negligible effect. The stability of each AEP is found by linearizing the equations of motion and carrying out a linear stability analysis. The results show that for a small mass-ratio system such as the Sun-Earth system, there are stable regions of AEPs with very small control acceleration that are defined in space missions.

Original language | English |
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Pages (from-to) | 1563-1568 |

Number of pages | 6 |

Journal | Journal of Guidance, Control, and Dynamics |

Volume | 30 |

Issue number | 5 |

DOIs | |

Publication status | Published - 2007 Sep 1 |

Externally published | Yes |

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### ASJC Scopus subject areas

- Control and Systems Engineering
- Aerospace Engineering
- Space and Planetary Science
- Applied Mathematics
- Electrical and Electronic Engineering

### Cite this

*Journal of Guidance, Control, and Dynamics*,

*30*(5), 1563-1568. https://doi.org/10.2514/1.26771

**Artificial equilibrium points in the low-thrust restricted three-body problem.** / Morimoto, Mutsuko; Yamakawa, Hiroshi; Uesugi, Kuninori.

Research output: Contribution to journal › Article

*Journal of Guidance, Control, and Dynamics*, vol. 30, no. 5, pp. 1563-1568. https://doi.org/10.2514/1.26771

}

TY - JOUR

T1 - Artificial equilibrium points in the low-thrust restricted three-body problem

AU - Morimoto, Mutsuko

AU - Yamakawa, Hiroshi

AU - Uesugi, Kuninori

PY - 2007/9/1

Y1 - 2007/9/1

N2 - The magnitude and direction of the required acceleration creating the artificial equilibrium point (AEP) in the low-thrust restricted three-dimensional space problem are investigated. A nonequilibrium point is turned into AEP by applying the appropriate continuous control acceleration. The nondimensional magnitude of acceleration is found in terms of the sun-earth system and the required acceleration is obtained by assuming that other planets such as Mars and Venus are not near the spacecraft with negligible effect. The stability of each AEP is found by linearizing the equations of motion and carrying out a linear stability analysis. The results show that for a small mass-ratio system such as the Sun-Earth system, there are stable regions of AEPs with very small control acceleration that are defined in space missions.

AB - The magnitude and direction of the required acceleration creating the artificial equilibrium point (AEP) in the low-thrust restricted three-dimensional space problem are investigated. A nonequilibrium point is turned into AEP by applying the appropriate continuous control acceleration. The nondimensional magnitude of acceleration is found in terms of the sun-earth system and the required acceleration is obtained by assuming that other planets such as Mars and Venus are not near the spacecraft with negligible effect. The stability of each AEP is found by linearizing the equations of motion and carrying out a linear stability analysis. The results show that for a small mass-ratio system such as the Sun-Earth system, there are stable regions of AEPs with very small control acceleration that are defined in space missions.

UR - http://www.scopus.com/inward/record.url?scp=35348964743&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=35348964743&partnerID=8YFLogxK

U2 - 10.2514/1.26771

DO - 10.2514/1.26771

M3 - Article

VL - 30

SP - 1563

EP - 1568

JO - Journal of Guidance, Control, and Dynamics

JF - Journal of Guidance, Control, and Dynamics

SN - 0731-5090

IS - 5

ER -