%General Mission Analysis Tool(GMAT) Script
%Created: 2018-04-24 15:37:33


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

Create Spacecraft ELE;
GMAT ELE.DateFormat = TAIModJulian;
GMAT ELE.Epoch = '21545';
GMAT ELE.CoordinateSystem = EarthMJ2000Eq;
GMAT ELE.DisplayStateType = Cartesian;
GMAT ELE.X = 8616.168315301933;
GMAT ELE.Y = -4.86244745572458e-013;
GMAT ELE.Z = 1577.608283083451;
GMAT ELE.VX = 1.416784487553298;
GMAT ELE.VY = 6.54930519811212;
GMAT ELE.VZ = 1.150473175915834;
GMAT ELE.DryMass = 850;
GMAT ELE.Cd = 2.2;
GMAT ELE.Cr = 1.8;
GMAT ELE.DragArea = 15;
GMAT ELE.SRPArea = 1;
GMAT ELE.NAIFId = -10000001;
GMAT ELE.NAIFIdReferenceFrame = -9000001;
GMAT ELE.OrbitColor = Red;
GMAT ELE.TargetColor = Teal;
GMAT ELE.OrbitErrorCovariance = [ 1e+070 0 0 0 0 0 ; 0 1e+070 0 0 0 0 ; 0 0 1e+070 0 0 0 ; 0 0 0 1e+070 0 0 ; 0 0 0 0 1e+070 0 ; 0 0 0 0 0 1e+070 ];
GMAT ELE.CdSigma = 1e+070;
GMAT ELE.CrSigma = 1e+070;
GMAT ELE.Id = 'SatId';
GMAT ELE.Attitude = CoordinateSystemFixed;
GMAT ELE.SPADSRPScaleFactor = 1;
GMAT ELE.ModelFile = 'aura.3ds';
GMAT ELE.ModelOffsetX = 0;
GMAT ELE.ModelOffsetY = 0;
GMAT ELE.ModelOffsetZ = 0;
GMAT ELE.ModelRotationX = 0;
GMAT ELE.ModelRotationY = 0;
GMAT ELE.ModelRotationZ = 0;
GMAT ELE.ModelScale = 1;
GMAT ELE.AttitudeDisplayStateType = 'Quaternion';
GMAT ELE.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT ELE.AttitudeCoordinateSystem = EarthMJ2000Eq;
GMAT ELE.EulerAngleSequence = '321';









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

Create ForceModel DefaultProp_ForceModel;
GMAT DefaultProp_ForceModel.CentralBody = Earth;
GMAT DefaultProp_ForceModel.PrimaryBodies = {Earth};
GMAT DefaultProp_ForceModel.Drag = None;
GMAT DefaultProp_ForceModel.SRP = Off;
GMAT DefaultProp_ForceModel.RelativisticCorrection = Off;
GMAT DefaultProp_ForceModel.ErrorControl = RSSStep;
GMAT DefaultProp_ForceModel.GravityField.Earth.Degree = 4;
GMAT DefaultProp_ForceModel.GravityField.Earth.Order = 4;
GMAT DefaultProp_ForceModel.GravityField.Earth.StmLimit = 100;
GMAT DefaultProp_ForceModel.GravityField.Earth.PotentialFile = 'JGM2.cof';
GMAT DefaultProp_ForceModel.GravityField.Earth.TideModel = 'None';

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

Create Propagator DefaultProp;
GMAT DefaultProp.FM = DefaultProp_ForceModel;
GMAT DefaultProp.Type = RungeKutta89;
GMAT DefaultProp.InitialStepSize = 60;
GMAT DefaultProp.Accuracy = 9.999999999999999e-012;
GMAT DefaultProp.MinStep = 0.001;
GMAT DefaultProp.MaxStep = 600;
GMAT DefaultProp.MaxStepAttempts = 50;
GMAT DefaultProp.StopIfAccuracyIsViolated = true;

%----------------------------------------
%---------- Subscribers
%----------------------------------------

Create OrbitView DefaultOrbitView;
GMAT DefaultOrbitView.SolverIterations = Current;
GMAT DefaultOrbitView.UpperLeft = [ 0.1153305203938115 0.3099547511312217 ];
GMAT DefaultOrbitView.Size = [ 0.5949367088607594 0.5690045248868778 ];
GMAT DefaultOrbitView.RelativeZOrder = 17;
GMAT DefaultOrbitView.Maximized = false;
GMAT DefaultOrbitView.Add = {ELE, Earth};
GMAT DefaultOrbitView.CoordinateSystem = EarthMJ2000Eq;
GMAT DefaultOrbitView.DrawObject = [ true true ];
GMAT DefaultOrbitView.DataCollectFrequency = 1;
GMAT DefaultOrbitView.UpdatePlotFrequency = 50;
GMAT DefaultOrbitView.NumPointsToRedraw = 0;
GMAT DefaultOrbitView.ShowPlot = true;
GMAT DefaultOrbitView.MaxPlotPoints = 20000;
GMAT DefaultOrbitView.ShowLabels = true;
GMAT DefaultOrbitView.ViewPointReference = Earth;
GMAT DefaultOrbitView.ViewPointVector = [ 30000 0 0 ];
GMAT DefaultOrbitView.ViewDirection = Earth;
GMAT DefaultOrbitView.ViewScaleFactor = 1;
GMAT DefaultOrbitView.ViewUpCoordinateSystem = EarthMJ2000Eq;
GMAT DefaultOrbitView.ViewUpAxis = Z;
GMAT DefaultOrbitView.EclipticPlane = Off;
GMAT DefaultOrbitView.XYPlane = On;
GMAT DefaultOrbitView.WireFrame = Off;
GMAT DefaultOrbitView.Axes = On;
GMAT DefaultOrbitView.Grid = Off;
GMAT DefaultOrbitView.SunLine = Off;
GMAT DefaultOrbitView.UseInitialView = On;
GMAT DefaultOrbitView.StarCount = 7000;
GMAT DefaultOrbitView.EnableStars = On;
GMAT DefaultOrbitView.EnableConstellations = On;

Create DynamicDataDisplay DDD;
GMAT DDD.UpperLeft = [ 0.04219409282700422 0.04638009049773756 ];
GMAT DDD.Size = [ 0.8185654008438819 0.1085972850678733 ];
GMAT DDD.RelativeZOrder = 19;
GMAT DDD.Maximized = false;
GMAT DDD.AddParameters = {1, ELE.TAIGregorian, ELE.Earth.RMAG, ELE.Earth.Altitude, ELE.RAAN};
GMAT DDD.RowTextColors = {1, [0 0 0], [0 0 0], [0 0 0], [0 0 0]};
GMAT DDD.WarnBounds = {ELE.Earth.RMAG, [7500 9000] };
GMAT DDD.WarnBounds = {ELE.Earth.Altitude, [500 4000] };
GMAT DDD.CritBounds = {ELE.Earth.RMAG, [6800 9900] };
GMAT DDD.CritBounds = {ELE.Earth.Altitude, [350 4500] };
GMAT DDD.WarnColor = [218 165 32];
GMAT DDD.CritColor = [255 0 0];


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

BeginMissionSequence;
While ELE.ElapsedDays < 1.0
   Propagate DefaultProp(ELE);
   UpdateDynamicData DDD;
EndWhile;