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Asteroids.script.bak
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%General Mission Analysis Tool(GMAT) Script
%Created: 2015-04-12 12:19:29
%----------------------------------------
%---------- User-Defined Celestial Bodies
%----------------------------------------
Create Asteroid Vesta;
GMAT Vesta.NAIFId = 2000004;
GMAT Vesta.OrbitColor = Salmon;
GMAT Vesta.TargetColor = DarkGray;
GMAT Vesta.EquatorialRadius = 550;
GMAT Vesta.Flattening = 0.16;
GMAT Vesta.Mu = 17.288;
GMAT Vesta.PosVelSource = 'SPICE';
GMAT Vesta.CentralBody = 'Sun';
GMAT Vesta.RotationDataSource = 'IAUSimplified';
GMAT Vesta.OrientationEpoch = 21545;
GMAT Vesta.SpinAxisRAConstant = 0;
GMAT Vesta.SpinAxisRARate = 0;
GMAT Vesta.SpinAxisDECConstant = 90;
GMAT Vesta.SpinAxisDECRate = 0;
GMAT Vesta.RotationConstant = 180;
GMAT Vesta.RotationRate = 1617.37177;
GMAT Vesta.TextureMapFileName = '../data/graphics/texture/GenericCelestialBody.jpg';
Create Asteroid a228502;
GMAT a228502.NAIFId = 2228502;
GMAT a228502.OrbitColor = Salmon;
GMAT a228502.TargetColor = DarkGray;
GMAT a228502.EquatorialRadius = 0.3;
GMAT a228502.Flattening = 0;
GMAT a228502.Mu = 5;
GMAT a228502.PosVelSource = 'SPICE';
GMAT a228502.CentralBody = 'Sun';
GMAT a228502.RotationDataSource = 'IAUSimplified';
GMAT a228502.OrientationEpoch = 21545;
GMAT a228502.SpinAxisRAConstant = 0;
GMAT a228502.SpinAxisRARate = 0;
GMAT a228502.SpinAxisDECConstant = 90;
GMAT a228502.SpinAxisDECRate = 0;
GMAT a228502.RotationConstant = 180;
GMAT a228502.RotationRate = 0;
GMAT a228502.TextureMapFileName = '../data/graphics/texture/GenericCelestialBody.jpg';
%----------------------------------------
%---------- Spacecraft
%----------------------------------------
Create Spacecraft DefaultSC;
GMAT DefaultSC.DateFormat = UTCGregorian;
GMAT DefaultSC.Epoch = '01 Jun 2015 11:59:28.000';
GMAT DefaultSC.CoordinateSystem = EarthMJ2000Eq;
GMAT DefaultSC.DisplayStateType = Cartesian;
GMAT DefaultSC.X = 7100;
GMAT DefaultSC.Y = 0;
GMAT DefaultSC.Z = 1300;
GMAT DefaultSC.VX = 0;
GMAT DefaultSC.VY = 7.35;
GMAT DefaultSC.VZ = 1;
GMAT DefaultSC.DryMass = 850;
GMAT DefaultSC.Cd = 2.2;
GMAT DefaultSC.Cr = 1.8;
GMAT DefaultSC.DragArea = 15;
GMAT DefaultSC.SRPArea = 1;
GMAT DefaultSC.NAIFId = -123456789;
GMAT DefaultSC.NAIFIdReferenceFrame = -123456789;
GMAT DefaultSC.OrbitColor = Red;
GMAT DefaultSC.TargetColor = Teal;
GMAT DefaultSC.Id = 'SatId';
GMAT DefaultSC.Attitude = CoordinateSystemFixed;
GMAT DefaultSC.SPADSRPScaleFactor = 1;
GMAT DefaultSC.ModelFile = '../data/vehicle/models/aura.3ds';
GMAT DefaultSC.ModelOffsetX = 0;
GMAT DefaultSC.ModelOffsetY = 0;
GMAT DefaultSC.ModelOffsetZ = 0;
GMAT DefaultSC.ModelRotationX = 0;
GMAT DefaultSC.ModelRotationY = 0;
GMAT DefaultSC.ModelRotationZ = 0;
GMAT DefaultSC.ModelScale = 3;
GMAT DefaultSC.AttitudeDisplayStateType = 'Quaternion';
GMAT DefaultSC.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT DefaultSC.AttitudeCoordinateSystem = EarthMJ2000Eq;
GMAT DefaultSC.EulerAngleSequence = '321';
Create Spacecraft Spacecraft1;
GMAT Spacecraft1.DateFormat = TAIModJulian;
GMAT Spacecraft1.Epoch = '21545';
GMAT Spacecraft1.CoordinateSystem = EarthMJ2000Eq;
GMAT Spacecraft1.DisplayStateType = Cartesian;
GMAT Spacecraft1.X = 7100;
GMAT Spacecraft1.Y = 0;
GMAT Spacecraft1.Z = 1300;
GMAT Spacecraft1.VX = 0;
GMAT Spacecraft1.VY = 7.35;
GMAT Spacecraft1.VZ = 1;
GMAT Spacecraft1.DryMass = 850;
GMAT Spacecraft1.Cd = 2.2;
GMAT Spacecraft1.Cr = 1.8;
GMAT Spacecraft1.DragArea = 15;
GMAT Spacecraft1.SRPArea = 1;
GMAT Spacecraft1.NAIFId = -123456789;
GMAT Spacecraft1.NAIFIdReferenceFrame = -123456789;
GMAT Spacecraft1.OrbitColor = Green;
GMAT Spacecraft1.TargetColor = LightGray;
GMAT Spacecraft1.Id = 'SatId';
GMAT Spacecraft1.Attitude = CoordinateSystemFixed;
GMAT Spacecraft1.SPADSRPScaleFactor = 1;
GMAT Spacecraft1.ModelFile = '../data/vehicle/models/aura.3ds';
GMAT Spacecraft1.ModelOffsetX = 0;
GMAT Spacecraft1.ModelOffsetY = 0;
GMAT Spacecraft1.ModelOffsetZ = 0;
GMAT Spacecraft1.ModelRotationX = 0;
GMAT Spacecraft1.ModelRotationY = 0;
GMAT Spacecraft1.ModelRotationZ = 0;
GMAT Spacecraft1.ModelScale = 3;
GMAT Spacecraft1.AttitudeDisplayStateType = 'Quaternion';
GMAT Spacecraft1.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT Spacecraft1.AttitudeCoordinateSystem = EarthMJ2000Eq;
GMAT Spacecraft1.EulerAngleSequence = '321';
%----------------------------------------
%---------- ForceModels
%----------------------------------------
Create ForceModel DefaultProp_ForceModel;
GMAT DefaultProp_ForceModel.CentralBody = Sun;
GMAT DefaultProp_ForceModel.PointMasses = {Earth, Vesta};
GMAT DefaultProp_ForceModel.Drag = None;
GMAT DefaultProp_ForceModel.SRP = On;
GMAT DefaultProp_ForceModel.RelativisticCorrection = On;
GMAT DefaultProp_ForceModel.ErrorControl = RSSStep;
GMAT DefaultProp_ForceModel.SRP.Flux = 1367;
GMAT DefaultProp_ForceModel.SRP.SRPModel = Spherical;
GMAT DefaultProp_ForceModel.SRP.Nominal_Sun = 149597870.691;
%----------------------------------------
%---------- 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 = 2700;
GMAT DefaultProp.MaxStepAttempts = 50;
GMAT DefaultProp.StopIfAccuracyIsViolated = true;
%----------------------------------------
%---------- Burns
%----------------------------------------
Create ImpulsiveBurn DefaultIB;
GMAT DefaultIB.CoordinateSystem = Local;
GMAT DefaultIB.Origin = Earth;
GMAT DefaultIB.Axes = VNB;
GMAT DefaultIB.Element1 = 0;
GMAT DefaultIB.Element2 = 0;
GMAT DefaultIB.Element3 = 0;
GMAT DefaultIB.DecrementMass = false;
GMAT DefaultIB.Isp = 300;
GMAT DefaultIB.GravitationalAccel = 9.810000000000001;
%----------------------------------------
%---------- Subscribers
%----------------------------------------
Create OrbitView DefaultOrbitView;
GMAT DefaultOrbitView.SolverIterations = Current;
GMAT DefaultOrbitView.UpperLeft = [ 0.003654080389768575 0.004166666666666667 ];
GMAT DefaultOrbitView.Size = [ 0.5042630937880633 0.45 ];
GMAT DefaultOrbitView.RelativeZOrder = 272;
GMAT DefaultOrbitView.Maximized = false;
GMAT DefaultOrbitView.Add = {DefaultSC, 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.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 GroundTrackPlot DefaultGroundTrackPlot;
GMAT DefaultGroundTrackPlot.SolverIterations = Current;
GMAT DefaultGroundTrackPlot.UpperLeft = [ 0 0.45625 ];
GMAT DefaultGroundTrackPlot.Size = [ 0.5006090133982948 0.45 ];
GMAT DefaultGroundTrackPlot.RelativeZOrder = 268;
GMAT DefaultGroundTrackPlot.Maximized = false;
GMAT DefaultGroundTrackPlot.Add = {DefaultSC};
GMAT DefaultGroundTrackPlot.DataCollectFrequency = 1;
GMAT DefaultGroundTrackPlot.UpdatePlotFrequency = 50;
GMAT DefaultGroundTrackPlot.NumPointsToRedraw = 0;
GMAT DefaultGroundTrackPlot.ShowPlot = true;
GMAT DefaultGroundTrackPlot.CentralBody = Earth;
GMAT DefaultGroundTrackPlot.TextureMap = '../data/graphics/texture/ModifiedBlueMarble.jpg';
%----------------------------------------
%---------- Mission Sequence
%----------------------------------------
BeginMissionSequence;
Propagate DefaultProp(DefaultSC) {DefaultSC.ElapsedSecs = 12000.0};