L1 EarthMoon Near Rectilinear Orbit

Dynamics and environment models, spacecraft model, solver algorithms, etc.

L1 EarthMoon Near Rectilinear Orbit

Postby PabloPi » Fri Jul 06, 2018 9:44 am

Dear all,
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.
Code: Select all
%----------------------------------------
%---------- User-Defined Calculated Points
%----------------------------------------

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;

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

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';













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

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;

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

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;
...
%----------------------------------------
%---------- Mission Sequence
%----------------------------------------

BeginMissionSequence;
Propagate EarthMoonProp(Sat, 'STM') {Sat.ElapsedSecs = 313340};
PabloPi
 
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Joined: Fri Jul 06, 2018 9:26 am

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