中国空间科学技术

中国空间科学技术 ›› 2020, Vol. 40 ›› Issue (4): 69-77.doi: 10.16708/j.cnki.1000-758X.2020.0047

• 研究探讨 • 上一篇    下一篇

连续小推力条件下星座轨道机动方法研究

  

  1. 1 上海航天控制技术研究所，上海201109
    2 上海市空间智能控制技术重点实验室，上海201109
  • 出版日期:2020-08-25 发布日期:2020-07-20

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
  • Published:2020-08-25 Online:2020-07-20

PDF (PC)

603

摘要： 基于连续小推力条件下星座轨道机动的动力学特性分析，研究了其入轨的布局置入和离轨机动方法。地球轨道上的大型星座数量巨大，传统的轨迹优化方法较难应用。针对多星入轨的星座布局置入任务，求解了分时序抬轨的相位调整问题，并在轨道抬升过程中，利用轨道倾角偏置补偿升交点赤经漂移。针对星座中卫星的离轨任务，设计了半长轴和偏心率的联合调整方法。在保证卫星快速离轨的同时，能够有效减少燃料的消耗。考虑到连续小推力机动的弧段效应，控制策略需要围绕控制效应的曲线积分进行优化。

关键词: 星座, 连续小推力, 轨道机动, 轨道布局置入, 离轨, 弧段效应, 曲线积分

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