›› 2015, Vol. 35 ›› Issue (6): 29-.doi: 10.3780/j.issn.1000-758X.2015.06.004

• 研究探讨 • 上一篇    下一篇

共面伴飞相对运动椭圆相位最省燃料控制问题

吴会英, 周美江, 齐金玲   

  1. (上海微小卫星工程中心,上海201203)
  • 收稿日期:2015-04-01 修回日期:2015-07-04 出版日期:2015-12-25 发布日期:2015-12-25
  • 作者简介:吴会英 1979年生,2004年获中国科学院紫金山天文台天体力学与天体测量专业硕士学位,副研究员。研究方向为卫星总体设计、轨道设计与轨道控制。

ResearchonMinimumFuelControlofRelativeEllipsePhaseinInPlaneCompanionFlying

WU  Hui-Ying, ZHOU  Mei-Jiang, QI  Jin-Ling   

  1. (ShanghaiEngineeringCenterForMicrosatellites,Shanghai201203)
  • Received:2015-04-01 Revised:2015-07-04 Online:2015-12-25 Published:2015-12-25

摘要: 针对伴随微纳卫星资源受限,轨控需实现最省燃料控制的现实问题,基于Hill方程和二元函数极值理论,研究了共面编队伴飞卫星的最省燃料相位控制策略。分析结果表明:当需要改变的相位为锐角、ΔV<05nb横向控制对相对运动椭圆相位改变效率最高,ΔV=05nb|cosΘ|控后相位为相对运动椭圆左右点,同时将相对运动椭圆短半轴控小;以伴随卫星绕参考卫星共面伴飞相位控制为例,应用这一理论求解了控制策略。

关键词: Hill方程, 相位改变量, 控制量, 控制时机, 控制方向, 共面编队飞行, 伴随卫星

Abstract: Itisessentialtosavefuelinorbitcontrolformicro/nanocompanionsatelliteduetothelackofresources.TheminimumfuelcontrolstrategyoftherelativeellipsephaseininplanecompanionflyingwasstudiedbasedontheHillequationandtheextremevaluetheoryofdualfunction. Whenthephaseneededtochangeisacuteangle , andthevelocityincrementislessthantheresultthatmultiplieshalfoforbit′smeanangularbytherelativeellipsesemiminoraxis(ΔV<05nb),thetheoreticalanalysisresultsshowthatthemostefficientcontrolmethodoftherelativeellipsephaseisimpulsivecontrolparalleltothelateraldirection, thevelocityincrementistheresultthatmultiplieshalfoforbit′smeanangular,therelativeellipsesemiminoraxisbytheabsoluteofphase′scosine(ΔV=05nb|cosΘ|,andthephasewillbetheleft(thephaseisπ/2)orright(thephaseis-π/2)pointofrelativeellipseaftercontrol.Therelativeellipsesemiminoraxiscanbereducedatthesametime. Whenthephaseneededtochangeisnotacuteangle, itisneededtobedividedintoseveralacuteanglesforsavingfuel. Furthermore,theorbitcontrolstrategyofacompanyingsatellite′sphasecontrolwasgainedbyapplyingthetheory.

Key words: Hillequation, Changeofphase, Controlquantity, Controltime, Controldirection, Inplanecompanionflying, Companionsatellite