%
%   Solar system properties.
%

SolarSystem.EphemerisSource  = 'DE421';
% Earth.EopFileName            = '/common/eopc04';

%
%   Spacecraft
%

Create Spacecraft Sat;

Sat.DateFormat       = 'UTCGregorian';
Sat.Epoch            = '03 Jan 2020 00:00:00.000';
Sat.CoordinateSystem = EarthMJ2000Eq;
Sat.DisplayStateType = Cartesian;
Sat.X                = 36.011
Sat.Y                = 6151.799
Sat.Z                = 3143.840
Sat.VX               = -7.50436
Sat.VY               = 0.587104
Sat.VZ               = -1.05874
Sat.DryMass          = 123.0;
Sat.Cd               = 1.33;
Sat.Cr               = 1.5;
Sat.DragArea         = 40.;
Sat.SRPArea          = 40.;
Sat.Id               = 9003702;

%
%   Force model and propagator
%

Create ForceModel Fm;
Create Propagator Prop;

Fm.CentralBody                       = Earth;
Fm.PrimaryBodies                     = {Earth};
Fm.GravityField.Earth.Degree         = 30;
Fm.GravityField.Earth.Order          = 30;
Fm.GravityField.Earth.PotentialFile  = 'JGM2.cof';
Fm.GravityField.Earth.TideModel      = 'None';
Fm.PointMasses                       = {Luna, Sun};
Fm.SRP                               = On;
Fm.Drag.AtmosphereModel              = 'JacchiaRoberts';
Fm.Drag.HistoricWeatherSource        = 'CSSISpaceWeatherFile';
Fm.Drag.PredictedWeatherSource       = 'SchattenFile'
Fm.Drag.SchattenTimingModel          = 'NominalCycle'
Fm.Drag.SchattenErrorModel           = 'PlusTwoSigma'
Fm.ErrorControl                      = 'None';

Prop.FM                              = Fm;
Prop.Type                            = RungeKutta89;
Prop.InitialStepSize                 = 60;
Prop.Accuracy                        = 1e-13;
Prop.MinStep                         = 0;
Prop.MaxStep                         = 60;
Prop.MaxStepAttempts                 = 50;

%
%   Report file
%

Create ReportFile DensityReport

%DensityReport.Add      = {Sat.UTCGregorian, Sat.BrouwerLongSMA, Sat.AtmosDensity}
%DensityReport.Add      = {Sat.UTCGregorian, Sat.BrouwerLongSMA}
DensityReport.Filename = 'PlusTwoSigma_NominalCycle.txt'

%
%   Ephemeris file
%

Create EphemerisFile Ephem

Ephem.Spacecraft       = Sat
Ephem.Filename         = 'PlusTwoSigma_NominalCycle.ephem'
Ephem.FileFormat       = 'Code-500'
Ephem.StepSize         = 60
Ephem.OutputFormat     = BigEndian
Ephem.CoordinateSystem = EarthMJ2000Eq

%
%   Mission sequence
%

BeginMissionSequence

While Sat.ElapsedDays < 1

    Propagate Prop(Sat) {Sat.ElapsedDays = 1}
    Report DensityReport Sat.UTCGregorian Sat.BrouwerLongSMA Sat.AtmosDensity

EndWhile