›› 2017, Vol. 37 ›› Issue (4): 18-27.doi: 10.16708/j.cnki.1000-758X.2017.0047

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TransferorbitinitialdesignandanalysisforMarsexplorationmission

 YANG  Bin1,2, LI  Shuang1,2,*   

  1. 1CollegeofAstronautics,NanjingUniversityofAeronauticsandAstronautics,Nanjing210016,China
    2LaboratoryofSpaceNewTechnology,NanjingUniversityofAeronauticsandAstronautics,Nanjing210016,China
  • Received:2016-12-08 Revised:2017-03-31 Online:2017-08-25 Published:2017-06-29

Abstract: AccordingtothepropulsionmodeandwhethertouseVenusgravity-assist,Marstransferorbitisdividedintofourtypes:theimpulsedirecttransferorbit,theimpulseVenus′gravity-assisttransferorbit,thelowthrustdirecttransferorbit,andthelow-thrust Venus′gravity-assisttransferorbit.InordertocomprehensivelyanalyzetheorbitcharacteristicsofthefourMarstransferstrategies,theenergyoptimaltransferorbitsforeverytransferorbitstrategyrespectivelyweredesigned.Inaddition,theorbitalcharacteristicsofdifferentMarstransferstrategieswereobtainedbynumericalsimulationandcomputation.Thebeneficialconclusionsweredrawnbasedonthecomparativeanalysisofthesimulationresults.Thelow-thrustMarstransfertrajectorydesignisnotrestrictedbylaunchwindows.ThelaunchwindowsopenalternatelyforimpulsedirecttransferandimpulseVenus′gravity-assisttransfer.Theenergyconsumptionoflow-thrustprobe,whichadoptsVenus′gravityassisttransferstrategy,isreducedby10%comparedwithdirecttransfer.TheeffectofVenusgravityassisttransferinenergyconsumptionisveryobvious.

Key words: Marsexploration, transfertrajectory, preliminarydesign, lowthrust, impulsepropulsion