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%General Mission Analysis Tool(GMAT) Script
%Created: 2023-10-17 16:56:24
%----------------------------------------
%---------- Spacecraft
%----------------------------------------
Create Spacecraft DefaultSC;
GMAT DefaultSC.DateFormat = TAIModJulian;
GMAT DefaultSC.Epoch = '21545';
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.SPADDragScaleFactor = 1;
GMAT DefaultSC.SPADSRPScaleFactor = 1;
GMAT DefaultSC.AtmosDensityScaleFactor = 1;
GMAT DefaultSC.ExtendedMassPropertiesModel = 'None';
GMAT DefaultSC.Tanks = {ChemicalTank1};
GMAT DefaultSC.Thrusters = {ChemicalThruster1};
GMAT DefaultSC.NAIFId = -10005001;
GMAT DefaultSC.NAIFIdReferenceFrame = -9005001;
GMAT DefaultSC.OrbitColor = Red;
GMAT DefaultSC.TargetColor = Teal;
GMAT DefaultSC.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 DefaultSC.CdSigma = 1e+70;
GMAT DefaultSC.CrSigma = 1e+70;
GMAT DefaultSC.Id = 'SatId';
GMAT DefaultSC.Attitude = CoordinateSystemFixed;
GMAT DefaultSC.SPADSRPInterpolationMethod = Bilinear;
GMAT DefaultSC.SPADSRPScaleFactorSigma = 1e+70;
GMAT DefaultSC.SPADDragInterpolationMethod = Bilinear;
GMAT DefaultSC.SPADDragScaleFactorSigma = 1e+70;
GMAT DefaultSC.AtmosDensityScaleFactorSigma = 1e+70;
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 = EarthFixed;
GMAT DefaultSC.EulerAngleSequence = '321';
%----------------------------------------
%---------- Hardware Components
%----------------------------------------
Create ChemicalThruster ChemicalThruster1;
GMAT ChemicalThruster1.CoordinateSystem = Local;
GMAT ChemicalThruster1.Origin = Earth;
GMAT ChemicalThruster1.Axes = SpacecraftBody;
GMAT ChemicalThruster1.ThrustDirection1 = 1;
GMAT ChemicalThruster1.ThrustDirection2 = 0;
GMAT ChemicalThruster1.ThrustDirection3 = 0;
GMAT ChemicalThruster1.DutyCycle = 1;
GMAT ChemicalThruster1.ThrustScaleFactor = 10;
GMAT ChemicalThruster1.DecrementMass = false;
GMAT ChemicalThruster1.Tank = {ChemicalTank1};
GMAT ChemicalThruster1.MixRatio = [ 1 ];
GMAT ChemicalThruster1.GravitationalAccel = 9.81;
GMAT ChemicalThruster1.C1 = 10;
GMAT ChemicalThruster1.C2 = 0;
GMAT ChemicalThruster1.C3 = 0;
GMAT ChemicalThruster1.C4 = 0;
GMAT ChemicalThruster1.C5 = 0;
GMAT ChemicalThruster1.C6 = 0;
GMAT ChemicalThruster1.C7 = 0;
GMAT ChemicalThruster1.C8 = 0;
GMAT ChemicalThruster1.C9 = 0;
GMAT ChemicalThruster1.C10 = 0;
GMAT ChemicalThruster1.C11 = 0;
GMAT ChemicalThruster1.C12 = 0;
GMAT ChemicalThruster1.C13 = 0;
GMAT ChemicalThruster1.C14 = 0;
GMAT ChemicalThruster1.C15 = 0;
GMAT ChemicalThruster1.C16 = 0;
GMAT ChemicalThruster1.K1 = 300;
GMAT ChemicalThruster1.K2 = 0;
GMAT ChemicalThruster1.K3 = 0;
GMAT ChemicalThruster1.K4 = 0;
GMAT ChemicalThruster1.K5 = 0;
GMAT ChemicalThruster1.K6 = 0;
GMAT ChemicalThruster1.K7 = 0;
GMAT ChemicalThruster1.K8 = 0;
GMAT ChemicalThruster1.K9 = 0;
GMAT ChemicalThruster1.K10 = 0;
GMAT ChemicalThruster1.K11 = 0;
GMAT ChemicalThruster1.K12 = 0;
GMAT ChemicalThruster1.K13 = 0;
GMAT ChemicalThruster1.K14 = 0;
GMAT ChemicalThruster1.K15 = 0;
GMAT ChemicalThruster1.K16 = 0;
Create ChemicalTank ChemicalTank1;
GMAT ChemicalTank1.AllowNegativeFuelMass = false;
GMAT ChemicalTank1.FuelMass = 756;
GMAT ChemicalTank1.Pressure = 1500;
GMAT ChemicalTank1.Temperature = 20;
GMAT ChemicalTank1.RefTemperature = 20;
GMAT ChemicalTank1.Volume = 0.75;
GMAT ChemicalTank1.FuelDensity = 1260;
GMAT ChemicalTank1.PressureModel = PressureRegulated;
%----------------------------------------
%---------- 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-12;
GMAT DefaultProp.MinStep = 0.001;
GMAT DefaultProp.MaxStep = 2700;
GMAT DefaultProp.MaxStepAttempts = 50;
GMAT DefaultProp.StopIfAccuracyIsViolated = true;
%----------------------------------------
%---------- Burns
%----------------------------------------
Create FiniteBurn DefaultFB;
GMAT DefaultFB.Thrusters = {ChemicalThruster1};
GMAT DefaultFB.ThrottleLogicAlgorithm = 'MaxNumberOfThrusters';
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 = 9.81;
%----------------------------------------
%---------- Solvers
%----------------------------------------
Create DifferentialCorrector DC1;
GMAT DC1.ShowProgress = true;
GMAT DC1.ReportStyle = Normal;
GMAT DC1.ReportFile = 'DifferentialCorrectorDC1.data';
GMAT DC1.MaximumIterations = 25;
GMAT DC1.DerivativeMethod = ForwardDifference;
GMAT DC1.Algorithm = NewtonRaphson;
%----------------------------------------
%---------- Subscribers
%----------------------------------------
Create OrbitView DefaultOrbitView;
GMAT DefaultOrbitView.SolverIterations = Current;
GMAT DefaultOrbitView.UpperLeft = [ 0.4405882352941177 0 ];
GMAT DefaultOrbitView.Size = [ 0.5 0.509829619921363 ];
GMAT DefaultOrbitView.RelativeZOrder = 1961;
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 GroundTrackPlot DefaultGroundTrackPlot;
GMAT DefaultGroundTrackPlot.SolverIterations = Current;
GMAT DefaultGroundTrackPlot.UpperLeft = [ 0.000588235294117647 0.509829619921363 ];
GMAT DefaultGroundTrackPlot.Size = [ 0.5 0.509829619921363 ];
GMAT DefaultGroundTrackPlot.RelativeZOrder = 1937;
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.MaxPlotPoints = 20000;
GMAT DefaultGroundTrackPlot.CentralBody = Earth;
GMAT DefaultGroundTrackPlot.TextureMap = 'ModifiedBlueMarble.jpg';
Create XYPlot XYPlot1;
GMAT XYPlot1.SolverIterations = Current;
GMAT XYPlot1.UpperLeft = [ 0.09 0.3525557011795544 ];
GMAT XYPlot1.Size = [ 0.7105882352941176 0.6068152031454783 ];
GMAT XYPlot1.RelativeZOrder = 1942;
GMAT XYPlot1.Maximized = false;
GMAT XYPlot1.XVariable = DefaultSC.A1ModJulian;
GMAT XYPlot1.YVariables = {DefaultSC.Earth.TA};
GMAT XYPlot1.ShowGrid = true;
GMAT XYPlot1.ShowPlot = true;
Create ReportFile ReportFile1;
GMAT ReportFile1.SolverIterations = Current;
GMAT ReportFile1.UpperLeft = [ 0 0 ];
GMAT ReportFile1.Size = [ 0 0 ];
GMAT ReportFile1.RelativeZOrder = 0;
GMAT ReportFile1.Maximized = false;
GMAT ReportFile1.Filename = 'ReportFile1.txt';
GMAT ReportFile1.Precision = 16;
GMAT ReportFile1.Add = {DefaultSC.Earth.Altitude};
GMAT ReportFile1.WriteHeaders = true;
GMAT ReportFile1.LeftJustify = On;
GMAT ReportFile1.ZeroFill = Off;
GMAT ReportFile1.FixedWidth = true;
GMAT ReportFile1.Delimiter = ' ';
GMAT ReportFile1.ColumnWidth = 23;
GMAT ReportFile1.WriteReport = true;
%----------------------------------------
%---------- Arrays, Variables, Strings
%----------------------------------------
Create Variable bruntime;
GMAT bruntime = 0;
%----------------------------------------
%---------- Mission Sequence
%----------------------------------------
BeginMissionSequence;
Propagate DefaultProp(DefaultSC) {DefaultSC.ElapsedSecs = 12000.0};
BeginFiniteBurn DefaultFB(DefaultSC);
Propagate DefaultProp(DefaultSC) {DefaultSC.ElapsedSecs = 12000.0};
EndFiniteBurn DefaultFB(DefaultSC);