›› 2015, Vol. 35 ›› Issue (6): 82-.doi: 10.3780/j.issn.1000-758X.2015.06.010

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OptimalEntryTrajectoryDesignofWingedMarsProbe

 LIU  Tao, NAN Ying , HU  Hai-Long   

  1. (1SchoolofAstronautics,NanjingUniversityofAeronauticsandAstronautics,Nanjing210016) (2The8thInstituteofShanghaiAcademyofSpaceFlightTechnology,Shanghai210000)
  • Received:2015-03-20 Revised:2015-08-20 Online:2015-12-25 Published:2015-12-25

Abstract: ThispaperprovidesanoptimalentrytrajectoryofthewingedMarsprobe,rightafteritchangedtheorbitintotheMartianatmospherebrakedbyreversethrustengine.ThispaperestablishesMartianatmospheremodelandgravitationalfieldmodelcorrespondingonthedensityoftheMartianatmosphereandgravitationalfieldparameters,anddeterminedthedynamicequationsoftheMarsprobe.Withinalltheconstraintconditionsintheenteringprocess,thispaperdesignsanoptimalentrytrajectorybasedonthegeneticalgorithm.Inaddition,thispaperprovidesdifferentthrustengineschemethroughcomparingthem.Theresultsshowthatthesecondschemecanachievetheoptimalperformanceindexandthelandingspeedis136m/s,ultimatelyrealizingtheminimumconsumptionofenergyandaerodynamicheatemissionstructurequalityintheprocessofenteringandsoftlanding.

Key words: Trajectoryoptimization, Atmosphericmodel, Gravitationalfieldmodel, Geneticalgorithm, Marsprobe