L1 EarthMoon Near Rectilinear Orbit

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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
 
Posts: 1
Joined: Fri Jul 06, 2018 9:26 am

Re: L1 EarthMoon Near Rectilinear Orbit

Postby xekykejele » Tue Nov 06, 2018 5:50 pm

The assignment has been completed for the future courses. It’s been mild and do my assignment australia in the ambit of the regulation for the persons and all issues for the candidates.
xekykejele
 
Posts: 1
Joined: Tue Nov 06, 2018 5:01 pm


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