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

Mutsuko Y. Morimoto, Hiroshi Yamakawa, Kuninori Uesugi

研究成果: Article査読

33 被引用数 (Scopus)

抄録

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.

本文言語English
ページ(範囲)1563-1568
ページ数6
ジャーナルJournal of Guidance, Control, and Dynamics
30
5
DOI
出版ステータスPublished - 2007
外部発表はい

ASJC Scopus subject areas

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

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