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