PowerCubeSat/OrbitScript.script at master · dhrumiltailor10/PowerCubeSat · GitHub

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%General Mission Analysis Tool(GMAT) Script
%Created: 2017-03-16 01:55:06


%----------------------------------------
%---------- Spacecraft
%----------------------------------------
Create Spacecraft DefaultSC;
GMAT DefaultSC.DateFormat = UTCGregorian;
GMAT DefaultSC.Epoch = '01 Jan 2000 12:00:00.000';
GMAT DefaultSC.CoordinateSystem = EarthMJ2000Eq;
GMAT DefaultSC.DisplayStateType = Keplerian;
GMAT DefaultSC.SMA = 6771;
GMAT DefaultSC.ECC = 0;
GMAT DefaultSC.INC = 50;
GMAT DefaultSC.RAAN = 0;
GMAT DefaultSC.AOP = 0;
GMAT DefaultSC.TA = 0;
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 = -10000001;
GMAT DefaultSC.NAIFIdReferenceFrame = -9000001;
GMAT DefaultSC.OrbitColor = Red;
GMAT DefaultSC.TargetColor = Teal;
GMAT DefaultSC.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 DefaultSC.CdSigma = 1e+070;
GMAT DefaultSC.CrSigma = 1e+070;
GMAT DefaultSC.Id = 'SatId';
GMAT DefaultSC.Attitude = CoordinateSystemFixed;
GMAT DefaultSC.SPADSRPScaleFactor = 1;
GMAT DefaultSC.ModelFile = '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 = 1;
GMAT DefaultSC.AttitudeDisplayStateType = 'Quaternion';
GMAT DefaultSC.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT DefaultSC.AttitudeCoordinateSystem = EarthMJ2000Eq;
GMAT DefaultSC.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 = 0;
GMAT DefaultProp_ForceModel.GravityField.Earth.Order = 0;
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 = 2700;
GMAT DefaultProp.MaxStepAttempts = 50;
GMAT DefaultProp.StopIfAccuracyIsViolated = true;


%----------------------------------------
%---------- Subscribers
%----------------------------------------
Create OrbitView DefaultOrbitView;
GMAT DefaultOrbitView.SolverIterations = Current;
GMAT DefaultOrbitView.UpperLeft = [ 0 0 ];
GMAT DefaultOrbitView.Size = [ 0.4994117647058823 1.082954545454546 ];
GMAT DefaultOrbitView.RelativeZOrder = 41;
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.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 ReportFile ReportFile;
GMAT ReportFile.SolverIterations = Current;
GMAT ReportFile.UpperLeft = [ 0.0111764705882353 0.025 ];
GMAT ReportFile.Size = [ 0.5952941176470589 0.79 ];
GMAT ReportFile.RelativeZOrder = 232;
GMAT ReportFile.Maximized = false;
GMAT ReportFile.Filename = './GMAT_Report.txt';
GMAT ReportFile.Precision = 16;
GMAT ReportFile.Add = {DefaultSC.A1Gregorian, DefaultSC.EarthMJ2000Eq.X, DefaultSC.EarthMJ2000Eq.Y, DefaultSC.EarthMJ2000Eq.Z, DefaultSC.EarthMJ2000Eq.VX, DefaultSC.EarthMJ2000Eq.VY, DefaultSC.EarthMJ2000Eq.VZ, Sun.EarthMJ2000Eq.X, Sun.EarthMJ2000Eq.Y, Sun.EarthMJ2000Eq.Z};
GMAT ReportFile.WriteHeaders = true;
GMAT ReportFile.LeftJustify = On;
GMAT ReportFile.ZeroFill = Off;
GMAT ReportFile.FixedWidth = true;
GMAT ReportFile.Delimiter = ' ';
GMAT ReportFile.ColumnWidth = 23;
GMAT ReportFile.WriteReport = true;

Create GroundTrackPlot GroundTrackPlot1;
GMAT GroundTrackPlot1.SolverIterations = Current;
GMAT GroundTrackPlot1.UpperLeft = [ 0.4852941176470588 0 ];
GMAT GroundTrackPlot1.Size = [ 0.4994117647058823 1.082954545454546 ];
GMAT GroundTrackPlot1.RelativeZOrder = 33;
GMAT GroundTrackPlot1.Maximized = false;
GMAT GroundTrackPlot1.Add = {DefaultSC};
GMAT GroundTrackPlot1.DataCollectFrequency = 1;
GMAT GroundTrackPlot1.UpdatePlotFrequency = 50;
GMAT GroundTrackPlot1.NumPointsToRedraw = 0;
GMAT GroundTrackPlot1.ShowPlot = true;
GMAT GroundTrackPlot1.MaxPlotPoints = 20000;
GMAT GroundTrackPlot1.CentralBody = Earth;
GMAT GroundTrackPlot1.TextureMap = 'ModifiedBlueMarble.jpg';


%----------------------------------------
%---------- Mission Sequence
%----------------------------------------
BeginMissionSequence;
Report 'ReportOrbitalPeriod' ReportFile DefaultSC.Earth.OrbitPeriod;
Propagate 'Propagate' DefaultProp(DefaultSC) {DefaultSC.ElapsedDays = 1};