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Create Spacecraft ExampleSat;
GMAT ExampleSat.DateFormat = UTCGregorian;
GMAT ExampleSat.Epoch = '01 Jan 2000 11:59:28.000';
GMAT ExampleSat.CoordinateSystem = EarthMJ2000Eq;
GMAT ExampleSat.DisplayStateType = Cartesian;
GMAT ExampleSat.X = 7100;
GMAT ExampleSat.Y = 0;
GMAT ExampleSat.Z = 1300;
GMAT ExampleSat.VX = 0;
GMAT ExampleSat.VY = 7.35;
GMAT ExampleSat.VZ = 1;
GMAT ExampleSat.DryMass = 850;
GMAT ExampleSat.Cd = 2.2;
GMAT ExampleSat.Cr = 1.8;
GMAT ExampleSat.DragArea = 15;
GMAT ExampleSat.SRPArea = 1;
GMAT ExampleSat.SPADDragScaleFactor = 1;
GMAT ExampleSat.SPADSRPScaleFactor = 1;
GMAT ExampleSat.AtmosDensityScaleFactor = 1;
GMAT ExampleSat.ExtendedMassPropertiesModel = 'None';
GMAT ExampleSat.Tanks = {ChemicalTank1};
GMAT ExampleSat.Thrusters = {ChemicalThruster1};
GMAT ExampleSat.EphemerisName = '../samples/SupportFiles/Ex_R2022a_TLE_Propagation_TLE.txt';
GMAT ExampleSat.NAIFId = -10003001;
GMAT ExampleSat.NAIFIdReferenceFrame = -9003001;
GMAT ExampleSat.OrbitColor = Red;
GMAT ExampleSat.TargetColor = Teal;
GMAT ExampleSat.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 ExampleSat.CdSigma = 1e+70;
GMAT ExampleSat.CrSigma = 1e+70;
GMAT ExampleSat.Id = 'ExampleSat';
GMAT ExampleSat.Attitude = CoordinateSystemFixed;
GMAT ExampleSat.SPADSRPInterpolationMethod = Bilinear;
GMAT ExampleSat.SPADSRPScaleFactorSigma = 1e+70;
GMAT ExampleSat.SPADDragInterpolationMethod = Bilinear;
GMAT ExampleSat.SPADDragScaleFactorSigma = 1e+70;
GMAT ExampleSat.AtmosDensityScaleFactorSigma = 1e+70;
GMAT ExampleSat.ModelFile = 'aura.3ds';
GMAT ExampleSat.ModelOffsetX = 0;
GMAT ExampleSat.ModelOffsetY = 0;
GMAT ExampleSat.ModelOffsetZ = 0;
GMAT ExampleSat.ModelRotationX = 0;
GMAT ExampleSat.ModelRotationY = 0;
GMAT ExampleSat.ModelRotationZ = 0;
GMAT ExampleSat.ModelScale = 1;
GMAT ExampleSat.AttitudeDisplayStateType = 'Quaternion';
GMAT ExampleSat.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT ExampleSat.AttitudeCoordinateSystem = EarthMJ2000Eq;
GMAT ExampleSat.EulerAngleSequence = '321';

%----------------------------------------
%---------- Hardware Components
%----------------------------------------

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;

Create ChemicalThruster ChemicalThruster1;
GMAT ChemicalThruster1.CoordinateSystem = Local;
GMAT ChemicalThruster1.Origin = Earth;
GMAT ChemicalThruster1.Axes = MJ2000Eq;
GMAT ChemicalThruster1.ThrustDirection1 = 1;
GMAT ChemicalThruster1.ThrustDirection2 = 0;
GMAT ChemicalThruster1.ThrustDirection3 = 0;
GMAT ChemicalThruster1.DutyCycle = 1;
GMAT ChemicalThruster1.ThrustScaleFactor = 1;
GMAT ChemicalThruster1.DecrementMass = true;
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;

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

Create Propagator TLEProp;
GMAT TLEProp.Type = SPICESGP4;
GMAT TLEProp.InitialStepSize = 60;

%----------------------------------------
%---------- Burns
%----------------------------------------

Create FiniteBurn FiniteBurn1;
GMAT FiniteBurn1.Thrusters = {ChemicalThruster1};
GMAT FiniteBurn1.ThrottleLogicAlgorithm = 'MaxNumberOfThrusters';

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

Create ReportFile rf;
GMAT rf.SolverIterations = Current;
GMAT rf.UpperLeft = [ 0 0 ];
GMAT rf.Size = [ 0 0 ];
GMAT rf.RelativeZOrder = 0;
GMAT rf.Maximized = false;
GMAT rf.Filename = 'Ex_R2022a_TLE_Propagation.txt';
GMAT rf.Precision = 16;
GMAT rf.Add = {ExampleSat.UTCGregorian, ExampleSat.X, ExampleSat.Y, ExampleSat.Z, ExampleSat.VX, ExampleSat.VY, ExampleSat.VZ};
GMAT rf.WriteHeaders = true;
GMAT rf.LeftJustify = On;
GMAT rf.ZeroFill = Off;
GMAT rf.FixedWidth = true;
GMAT rf.Delimiter = ' ';
GMAT rf.ColumnWidth = 23;
GMAT rf.WriteReport = true;

Create OrbitView OrbitView1;
GMAT OrbitView1.SolverIterations = Current;
GMAT OrbitView1.UpperLeft = [ 0 0 ];
GMAT OrbitView1.Size = [ 0.8 0.8497109826589595 ];
GMAT OrbitView1.RelativeZOrder = 828;
GMAT OrbitView1.Maximized = false;
GMAT OrbitView1.Add = {ExampleSat, Earth};
GMAT OrbitView1.CoordinateSystem = EarthMJ2000Eq;
GMAT OrbitView1.DrawObject = [ true true ];
GMAT OrbitView1.DataCollectFrequency = 1;
GMAT OrbitView1.UpdatePlotFrequency = 50;
GMAT OrbitView1.NumPointsToRedraw = 0;
GMAT OrbitView1.ShowPlot = true;
GMAT OrbitView1.MaxPlotPoints = 20000;
GMAT OrbitView1.ShowLabels = true;
GMAT OrbitView1.ViewPointReference = Earth;
GMAT OrbitView1.ViewPointVector = [ 0 0 30000 ];
GMAT OrbitView1.ViewDirection = Earth;
GMAT OrbitView1.ViewScaleFactor = 1;
GMAT OrbitView1.ViewUpCoordinateSystem = EarthMJ2000Eq;
GMAT OrbitView1.ViewUpAxis = Z;
GMAT OrbitView1.EclipticPlane = Off;
GMAT OrbitView1.XYPlane = On;
GMAT OrbitView1.WireFrame = Off;
GMAT OrbitView1.Axes = On;
GMAT OrbitView1.Grid = Off;
GMAT OrbitView1.SunLine = Off;
GMAT OrbitView1.UseInitialView = On;
GMAT OrbitView1.StarCount = 7000;
GMAT OrbitView1.EnableStars = On;
GMAT OrbitView1.EnableConstellations = On;

Create XYPlot XYPlot1;
GMAT XYPlot1.SolverIterations = Current;
GMAT XYPlot1.UpperLeft = [ 0.1411764705882353 0.3132947976878613 ];
GMAT XYPlot1.Size = [ 0.5 0.4497109826589595 ];
GMAT XYPlot1.RelativeZOrder = 836;
GMAT XYPlot1.Maximized = false;
GMAT XYPlot1.XVariable = ExampleSat.A1ModJulian;
GMAT XYPlot1.YVariables = {ExampleSat.Earth.Altitude};
GMAT XYPlot1.ShowGrid = true;
GMAT XYPlot1.ShowPlot = true;

%----------------------------------------
%---------- Arrays, Variables, Strings
%----------------------------------------
Create Variable I;







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

BeginMissionSequence;
BeginFiniteBurn FiniteBurn1(ExampleSat);
Propagate TLEProp(ExampleSat) {ExampleSat.ElapsedSecs = 36000};
EndFiniteBurn FiniteBurn1(ExampleSat);
Propagate TLEProp(ExampleSat) {ExampleSat.ElapsedDays = 1};
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