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

Mutsuko Y. Morimoto, Hiroshi Yamakawa, Kuninori Uesugi

Research output: Contribution to journalArticlepeer-review

40 Citations (Scopus)


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 languageEnglish
Pages (from-to)1563-1568
Number of pages6
JournalJournal of Guidance, Control, and Dynamics
Issue number5
Publication statusPublished - 2007
Externally publishedYes

ASJC Scopus subject areas

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


Dive into the research topics of 'Artificial equilibrium points in the low-thrust restricted three-body problem'. Together they form a unique fingerprint.

Cite this