I tried associating a nuclear power system with the spacecraft in
R2020a. Seems to work fine. I am on Ubuntu 18.04. I have attached the
script file for you. Try testing it on your system.
Regards,
Debdeep Roychowdhury
On 03.06.22 23:02, James Gilland wrote:
I have the latest GMAT, GMAT-R2020a_Beta, and am trying to learn how
to do a low thrust mission analysis. I’m just trying to configure the
resources, but when I try and associate a power system with the
spacecraft, it doesn't register. The spacecraft never recognizes the
power system – I can select it, but the “Apply” button is grayed out,
and selecting “Okay” leaves the window but the power system is not in
the spacecraft configuration when I go back. Is this a bug? An older
version seemed to do this part fine.
Also, changing the epoch in the power system definition, even for a
nuclear power system, crashes the program.
I’m on a NASA issue MacBook Pro, macOS 11.6.6.
Thanks,
Jim Gilland
Dr. James H. Gilland
Ohio Aerospace Institute
22800 Cedar Point Rd.
Brook Park, OH 44142
(440) 962 - 3142 (ofc.)
(440) 364 - 3589 (cell)
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Technische Universität Berlin
Institut für Luft- und Raumfahrt | Institute of Aeronautics and Astronautics
Fachgebiet Raumfahrttechnik (F6)| Chair of Space Technology (F6)
Room 411, Marchstraße 12, 10587 Berlin
Ph: +49 30 314-22345 | Fax: +49 30 314-21306 | LinkedIn:https://www.linkedin.com/in/debdeeprc/ | Email:roychowdh...@tu-berlin.de
%General Mission Analysis Tool(GMAT) Script
%Created: 2022-06-04 08:16:36
%----------------------------------------
%---------- 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.PowerSystem = NuclearPowerSystem1;
GMAT DefaultSC.NAIFId = -10000001;
GMAT DefaultSC.NAIFIdReferenceFrame = -9000001;
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.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';
%----------------------------------------
%---------- Hardware Components
%----------------------------------------
Create NuclearPowerSystem NuclearPowerSystem1;
GMAT NuclearPowerSystem1.EpochFormat = 'UTCGregorian';
GMAT NuclearPowerSystem1.InitialEpoch = '01 Jan 2000 11:59:28.000';
GMAT NuclearPowerSystem1.InitialMaxPower = 1.2;
GMAT NuclearPowerSystem1.AnnualDecayRate = 5;
GMAT NuclearPowerSystem1.Margin = 5;
GMAT NuclearPowerSystem1.BusCoeff1 = 0.3;
GMAT NuclearPowerSystem1.BusCoeff2 = 0;
GMAT NuclearPowerSystem1.BusCoeff3 = 0;
%----------------------------------------
%---------- 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;
%----------------------------------------
%---------- Subscribers
%----------------------------------------
Create OrbitView DefaultOrbitView;
GMAT DefaultOrbitView.SolverIterations = Current;
GMAT DefaultOrbitView.UpperLeft = [ 0 0 ];
GMAT DefaultOrbitView.Size = [ 0 0 ];
GMAT DefaultOrbitView.RelativeZOrder = 0;
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 0 ];
GMAT DefaultGroundTrackPlot.Size = [ 0 0 ];
GMAT DefaultGroundTrackPlot.RelativeZOrder = 0;
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';
%----------------------------------------
%---------- Mission Sequence
%----------------------------------------
BeginMissionSequence;
Propagate DefaultProp(DefaultSC) {DefaultSC.ElapsedSecs = 12000.0};
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