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L1 EarthMoon Near Rectilinear Orbit

PostPosted: Fri Jul 06, 2018 9:44 am
by PabloPi
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};

Re: L1 EarthMoon Near Rectilinear Orbit

PostPosted: Tue Nov 06, 2018 5:50 pm
by xekykejele
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.

Re: L1 EarthMoon Near Rectilinear Orbit

PostPosted: Mon Dec 17, 2018 8:23 am
by William12
I set the propagator in Three-Body Problem (point masses: Earth, Moon) Credit Card Processing 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.

Re: L1 EarthMoon Near Rectilinear Orbit

PostPosted: Sat Jan 12, 2019 6:34 am
by Richardmswanson
I am a university student and I want simulate eye doctor near me on friday a near rectilinear orbit (NRO) in Earth-Moon system.