Chinese Space Science and Technology ›› 2020, Vol. 40 ›› Issue (4): 69-77.doi: 10.16708/j.cnki.1000-758X.2020.0047

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Study on maneuver methods of satellites constellation with continual small-thrust propulsion

  

  1. 1 Shanghai Institute of Spaceflight Control Technology,Shanghai201109,China
    2 Shanghai Key Laboratory of Aerospace Intelligent Control Technology,Shanghai201109,China
  • Online:2020-08-25 Published:2020-07-20

Abstract: Based on the orbit dynamic characteristics, orbit maneuver methods of satellites constellation with continual small-thrust propulsion are studied in this paper. Because of the huge scales of constellations, orbit maneuver of constellation in near-earth orbit can hardly be managed by traditional method as trajectory planning. Orbit insertion for constellation configuration is considered as a relative semimajor axis control problem in timedelay maneuver sequence. Meanwhile, offset control of inclination is considered for drift of right ascension of ascending node(RAAN) during arisingorbit maneuver. For consideration of orbit discarded problem, a unitedcontrol for combination of semimajor axis and eccentricity is designed for a rapid orbit decay with energy-saving. Because of the curveeffect for continual smallthrust propulsion, curvilinear integral of orbit control should be investigated for all the strategy optimizations.

Key words: constellation, continual smallthrust propulsion, orbit maneuver, orbit insertion, orbit discarded, curveeffect, curvilinear integral