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

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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

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