satkit 0.21.2

Satellite Toolkit
Documentation 
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%General Mission Analysis Tool(GMAT) Script
%Created: 2024-03-27 09:34:03

%----------------------------------------
%---------- Spacecraft
%----------------------------------------

Create Spacecraft TESS;
TESS.DateFormat = UTCGregorian;
TESS.Epoch = '16 May 2023 20:00:00.00';
TESS.CoordinateSystem = EarthMJ2000Eq;
TESS.DisplayStateType = Cartesian;
TESS.X = -130142.3736645361
TESS.Y = 120626.1878655891
TESS.Z = 126520.4971633258
TESS.VX = -0.308744045658656
TESS.VY = -1.40299418814228
TESS.VZ = -0.0616245044905574416
% SRP parameters
% TESS.DryMass = 450;
% TESS.Cr = 1.8;
% TESS.SRPArea = 1;

% 
%----------------------------------------
%---------- ForceModels
%----------------------------------------

Create ForceModel DefaultProp_ForceModel;
DefaultProp_ForceModel.CentralBody = Earth;
DefaultProp_ForceModel.PrimaryBodies = {Earth};
DefaultProp_ForceModel.PointMasses = {Luna, Sun};
DefaultProp_ForceModel.Drag = None;
DefaultProp_ForceModel.SRP = Off;
%DefaultProp_ForceModel.SRP = Off
DefaultProp_ForceModel.RelativisticCorrection = On;
DefaultProp_ForceModel.ErrorControl = RSSStep;
DefaultProp_ForceModel.GravityField.Earth.Degree = 36;
DefaultProp_ForceModel.GravityField.Earth.Order = 36;
DefaultProp_ForceModel.GravityField.Earth.StmLimit = 100;
DefaultProp_ForceModel.GravityField.Earth.PotentialFile = 'EGM96.cof';
DefaultProp_ForceModel.GravityField.Earth.TideModel = 'Solid';
% DefaultProp_ForceModel.SRP.Flux = 1367;
% DefaultProp_ForceModel.SRP.SRPModel = Spherical;
% DefaultProp_ForceModel.SRP.Nominal_Sun = 149597870.691;

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

Create Propagator DefaultProp;
DefaultProp.FM = DefaultProp_ForceModel;
DefaultProp.Type = RungeKutta89;
DefaultProp.InitialStepSize = 60;
DefaultProp.Accuracy = 1e-14;
DefaultProp.MinStep = 0.001;
DefaultProp.MaxStep = 2700
DefaultProp.MaxStepAttempts = 50;
DefaultProp.StopIfAccuracyIsViolated = true;

%----------------------------------------
%---------- Coordinate Systems
%----------------------------------------

Create CoordinateSystem EarthMoonBBR;
EarthMoonBBR.Origin = Earth;
EarthMoonBBR.Axes = ObjectReferenced;
EarthMoonBBR.XAxis = R;
EarthMoonBBR.ZAxis = N;
EarthMoonBBR.Primary = Earth;
EarthMoonBBR.Secondary = Luna;

%----------------------------------------
%---------- Solvers
%----------------------------------------

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

Create OrbitView EMBBR;
EMBBR.SolverIterations = Current;
EMBBR.UpperLeft = [ 0.04411764705882353 0.2179656538969617 ];
EMBBR.Size = [ 1.142352941176471 0.809775429326288 ];
EMBBR.RelativeZOrder = 12106;
EMBBR.Maximized = false;
EMBBR.Add = {TESS, Earth, Luna};
EMBBR.CoordinateSystem = EarthMoonBBR;
EMBBR.DrawObject = [ true true true ];
EMBBR.DataCollectFrequency = 1;
EMBBR.UpdatePlotFrequency = 50;
EMBBR.NumPointsToRedraw = 0;
EMBBR.ShowPlot = true;
EMBBR.MaxPlotPoints = 1000000;
EMBBR.ShowLabels = true;
EMBBR.ViewPointReference = Earth;
EMBBR.ViewPointVector = [ 0 0 1500000 ];
EMBBR.ViewDirection = Earth;
EMBBR.ViewScaleFactor = 1;
EMBBR.ViewUpCoordinateSystem = EarthMoonBBR;
EMBBR.ViewUpAxis = Z;
EMBBR.EclipticPlane = Off;
EMBBR.XYPlane = Off;
EMBBR.WireFrame = Off;
EMBBR.Axes = Off;
EMBBR.Grid = Off;
EMBBR.SunLine = Off;
EMBBR.UseInitialView = On;
EMBBR.StarCount = 7000;
EMBBR.EnableStars = Off;
EMBBR.EnableConstellations = On;

%----------------------------------------
%---------- Arrays, Variables, Strings
%----------------------------------------

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

% Just propagate
BeginMissionSequence
Propagate DefaultProp(TESS) {TESS.ElapsedDays=7}
Write TESS.UTCGregorian TESS.X TESS.Y TESS.Z TESS.VX TESS.VY TESS.VZ