%General Mission Analysis Tool(GMAT) Script %---------------------------------------- %----------LightSail #9 %---------------------------------------- Create Spacecraft DefaultSC; GMAT DefaultSC.DateFormat = UTCModJulian; GMAT DefaultSC.Epoch = '27187.4844212963'; GMAT DefaultSC.CoordinateSystem = EarthMJ2000Eq; GMAT DefaultSC.DisplayStateType = Keplerian; GMAT DefaultSC.SMA = 6745.96820546937; GMAT DefaultSC.ECC = 0.00753594184577265; GMAT DefaultSC.INC = 55.0129815394915; GMAT DefaultSC.RAAN = 233.787099960804; GMAT DefaultSC.AOP = 263.667033616011; GMAT DefaultSC.TA = 96.3329194288332; GMAT DefaultSC.DryMass = 4.93; GMAT DefaultSC.Cd = 2.2; GMAT DefaultSC.Cr = 1.8; GMAT DefaultSC.DragArea = 6.965; GMAT DefaultSC.SRPArea = 6.965; GMAT DefaultSC.NAIFId = -123456789; GMAT DefaultSC.NAIFIdReferenceFrame = -123456789; GMAT DefaultSC.Id = 'SatId'; GMAT DefaultSC.Attitude = CoordinateSystemFixed; 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'; %---------------------------------------- %---------- ForceModels %---------------------------------------- Create ForceModel DefaultProp_ForceModel; GMAT DefaultProp_ForceModel.CentralBody = Earth; GMAT DefaultProp_ForceModel.PrimaryBodies = {Earth}; GMAT DefaultProp_ForceModel.SRP = On; GMAT DefaultProp_ForceModel.RelativisticCorrection = Off; GMAT DefaultProp_ForceModel.ErrorControl = RSSStep; GMAT DefaultProp_ForceModel.GravityField.Earth.Degree = 90; GMAT DefaultProp_ForceModel.GravityField.Earth.Order = 90; GMAT DefaultProp_ForceModel.GravityField.Earth.PotentialFile = 'EGM96.cof'; GMAT DefaultProp_ForceModel.GravityField.Earth.EarthTideModel = 'None'; GMAT DefaultProp_ForceModel.Drag.AtmosphereModel = MSISE90; GMAT DefaultProp_ForceModel.Drag.F107 = 136.1; GMAT DefaultProp_ForceModel.Drag.F107A = 118.8; GMAT DefaultProp_ForceModel.Drag.MagneticIndex = 3.4; %---------------------------------------- %---------- Propagators %---------------------------------------- Create Propagator DefaultProp; GMAT DefaultProp.FM = DefaultProp_ForceModel; GMAT DefaultProp.Type = PrinceDormand78; GMAT DefaultProp.InitialStepSize = 60; GMAT DefaultProp.Accuracy = 1e-009; GMAT DefaultProp.MinStep = 0; 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 = [ 0.00410958904109589 0 ]; GMAT DefaultOrbitView.Size = [ 0.5006849315068493 0.4497041420118343 ]; GMAT DefaultOrbitView.RelativeZOrder = 310; GMAT DefaultOrbitView.Maximized = false; GMAT DefaultOrbitView.Add = {DefaultSC, Earth, Sun}; GMAT DefaultOrbitView.CoordinateSystem = EarthMJ2000Eq; GMAT DefaultOrbitView.DrawObject = [ true true true ]; GMAT DefaultOrbitView.OrbitColor = [ 255 32768 4227327 ]; GMAT DefaultOrbitView.TargetColor = [ 8421440 0 0 ]; GMAT DefaultOrbitView.DataCollectFrequency = 1; GMAT DefaultOrbitView.UpdatePlotFrequency = 50; GMAT DefaultOrbitView.NumPointsToRedraw = 0; GMAT DefaultOrbitView.ShowPlot = 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 = Off; GMAT DefaultOrbitView.WireFrame = Off; GMAT DefaultOrbitView.Axes = On; GMAT DefaultOrbitView.Grid = Off; GMAT DefaultOrbitView.SunLine = On; GMAT DefaultOrbitView.UseInitialView = On; GMAT DefaultOrbitView.StarCount = 7000; GMAT DefaultOrbitView.EnableStars = On; GMAT DefaultOrbitView.EnableConstellations = Off; Create GroundTrackPlot DefaultGroundTrackPlot; GMAT DefaultGroundTrackPlot.SolverIterations = Current; GMAT DefaultGroundTrackPlot.UpperLeft = [ 0.00410958904109589 0.4544378698224852 ]; GMAT DefaultGroundTrackPlot.Size = [ 0.5006849315068493 0.4497041420118343 ]; GMAT DefaultGroundTrackPlot.RelativeZOrder = 269; GMAT DefaultGroundTrackPlot.Maximized = false; GMAT DefaultGroundTrackPlot.Add = {DefaultSC, Earth}; 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'; 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.UTCGregorian, DefaultSC.Earth.Latitude, DefaultSC.Earth.Longitude, DefaultSC.Earth.Altitude, DefaultSC.EarthMJ2000Eq.X, DefaultSC.EarthMJ2000Eq.Y, DefaultSC.EarthMJ2000Eq.Z, DefaultSC.EarthMJ2000Eq.VX, DefaultSC.EarthMJ2000Eq.VY, DefaultSC.EarthMJ2000Eq.VZ, DefaultSC.EarthMJ2000Eq.INC, DefaultSC.EarthMJ2000Eq.RAAN, DefaultSC.Earth.ECC, DefaultSC.Earth.MA, DefaultSC.EarthMJ2000Eq.AOP, DefaultSC.Earth.MM, DefaultSC.Earth.SMA}; GMAT ReportFile1.WriteHeaders = true; GMAT ReportFile1.LeftJustify = On; GMAT ReportFile1.ZeroFill = Off; GMAT ReportFile1.ColumnWidth = 20; GMAT ReportFile1.WriteReport = true; %---------------------------------------- %---------- Mission Sequence %---------------------------------------- BeginMissionSequence; Propagate DefaultProp(DefaultSC) {DefaultSC.ElapsedSecs = 100000};