I am a university student and I want simulate a near rectilinear orbit (NRO) in Earth-Moon system. I set the propagator in Three-Body Problem (point masses: Earth, Moon) and then I put the initial conditions. I'm sure about initial condition, but I think there is wrong something in mission set up. Can someone help me? Below you can see the code.

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%---------- User-Defined Calculated Points

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Create LibrationPoint EarthMoonL1;

GMAT EarthMoonL1.OrbitColor = GreenYellow;

GMAT EarthMoonL1.TargetColor = [32 254 254];

GMAT EarthMoonL1.Primary = Earth;

GMAT EarthMoonL1.Secondary = Luna;

GMAT EarthMoonL1.Point = L1;

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%---------- Spacecraft

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Create Spacecraft Sat;

GMAT Sat.DateFormat = TTGregorian;

GMAT Sat.Epoch = '01 Jul 2020 00:01:09.184';

GMAT Sat.CoordinateSystem = MoonRotFrame;

GMAT Sat.DisplayStateType = Cartesian;

GMAT Sat.X = 16003.9582;

GMAT Sat.Y = 0.008493173987517366;

GMAT Sat.Z = 71821.86109999999;

GMAT Sat.VX = -0.001143739999999956;

GMAT Sat.VY = 0.1202071119999999;

GMAT Sat.VZ = 0.01182962700000003;

GMAT Sat.DryMass = 850;

GMAT Sat.Cd = 2.2;

GMAT Sat.Cr = 1.8;

GMAT Sat.DragArea = 15;

GMAT Sat.SRPArea = 1;

GMAT Sat.NAIFId = -10000001;

GMAT Sat.NAIFIdReferenceFrame = -9000001;

GMAT Sat.OrbitColor = [251 2 254];

GMAT Sat.TargetColor = Teal;

GMAT Sat.OrbitErrorCovariance = [ 1e+70 0 0 0 0 0 ; 0 1e+70 0 0 0 0 ; 0 0 1e+70 0 0 0 ; 0 0 0 1e+70 0 0 ; 0 0 0 0 1e+70 0 ; 0 0 0 0 0 1e+70 ];

GMAT Sat.CdSigma = 1e+70;

GMAT Sat.CrSigma = 1e+70;

GMAT Sat.Id = 'SatId';

GMAT Sat.Attitude = CoordinateSystemFixed;

GMAT Sat.SPADSRPScaleFactor = 1;

GMAT Sat.ModelFile = 'aura.3ds';

GMAT Sat.ModelOffsetX = 0;

GMAT Sat.ModelOffsetY = 0;

GMAT Sat.ModelOffsetZ = 0;

GMAT Sat.ModelRotationX = 0;

GMAT Sat.ModelRotationY = 0;

GMAT Sat.ModelRotationZ = 0;

GMAT Sat.ModelScale = 1;

GMAT Sat.AttitudeDisplayStateType = 'Quaternion';

GMAT Sat.AttitudeRateDisplayStateType = 'AngularVelocity';

GMAT Sat.AttitudeCoordinateSystem = EarthMJ2000Eq;

GMAT Sat.EulerAngleSequence = '321';

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%---------- ForceModels

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Create ForceModel EarthMoonProp_ForceModel;

GMAT EarthMoonProp_ForceModel.CentralBody = Earth;

GMAT EarthMoonProp_ForceModel.PointMasses = {Earth, Luna};

GMAT EarthMoonProp_ForceModel.Drag = None;

GMAT EarthMoonProp_ForceModel.SRP = On;

GMAT EarthMoonProp_ForceModel.RelativisticCorrection = Off;

GMAT EarthMoonProp_ForceModel.ErrorControl = RSSStep;

GMAT EarthMoonProp_ForceModel.SRP.Flux = 1367;

GMAT EarthMoonProp_ForceModel.SRP.SRPModel = Spherical;

GMAT EarthMoonProp_ForceModel.SRP.Nominal_Sun = 149597870.691;

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%---------- Propagators

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Create Propagator EarthMoonProp;

GMAT EarthMoonProp.FM = EarthMoonProp_ForceModel;

GMAT EarthMoonProp.Type = RungeKutta89;

GMAT EarthMoonProp.InitialStepSize = 60;

GMAT EarthMoonProp.Accuracy = 9.999999999999999e-12;

GMAT EarthMoonProp.MinStep = 0.001;

GMAT EarthMoonProp.MaxStep = 2700;

GMAT EarthMoonProp.MaxStepAttempts = 50;

GMAT EarthMoonProp.StopIfAccuracyIsViolated = true;

...

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%---------- Mission Sequence

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BeginMissionSequence;

Propagate EarthMoonProp(Sat, 'STM') {Sat.ElapsedSecs = 313340};