% Generated at 2019-10-10 08:13:55.768758

Create Spacecraft EstSat;

GMAT EstSat.DateFormat = UTCGregorian;
GMAT EstSat.Epoch = '01 Oct 2019 00:00:00.000';
GMAT EstSat.CoordinateSystem = EarthMJ2000Eq;
GMAT EstSat.DisplayStateType = Cartesian;
GMAT EstSat.X = 11057.8902;
GMAT EstSat.Y = -40695.4196;
GMAT EstSat.Z = -3.0934311;
GMAT EstSat.VX = 2.96672121;
GMAT EstSat.VY = 0.805879614;
GMAT EstSat.VZ = -0.000852117906;
GMAT EstSat.DryMass = 850;
GMAT EstSat.Cd = 2.2;
GMAT EstSat.Cr = 1.4;
GMAT EstSat.DragArea = 15;
GMAT EstSat.SRPArea = 15;
GMAT EstSat.Id = 'EstSat';
GMAT EstSat.AddHardware = {EstSat_Transponder, EstSat_Antenna};
GMAT EstSat.SolveFors = {'CartesianState', 'Cr'};

Create Antenna EstSat_Antenna;
Create Transponder EstSat_Transponder;
GMAT EstSat_Transponder.HardwareDelay = 5e-005;
GMAT EstSat_Transponder.PrimaryAntenna = EstSat_Antenna;
GMAT EstSat_Transponder.TurnAroundRatio = '240/221';


Create GroundStation Station1;
GMAT Station1.CentralBody = Earth;
GMAT Station1.StateType = Cartesian;
GMAT Station1.HorizonReference = Ellipsoid;
GMAT Station1.Location1 = 1113.984331943206;
GMAT Station1.Location2 = -4842.455064187911;
GMAT Station1.Location3 = 3985.458988915704;
GMAT Station1.Id = 'Station1';
GMAT Station1.AddHardware = {Station1_Transmitter, Station1_Receiver, Station1_Antenna};
GMAT Station1.IonosphereModel = 'None';
GMAT Station1.TroposphereModel = 'None';
GMAT Station1.MinimumElevationAngle = 30;
GMAT Station1.ErrorModels = {Station1_AzimuthModel, Station1_ElevationModel};

Create Transmitter Station1_Transmitter;
GMAT Station1_Transmitter.PrimaryAntenna = Station1_Antenna;
GMAT Station1_Transmitter.Frequency = 2067.5;

Create Antenna Station1_Antenna;
Create Receiver Station1_Receiver;
GMAT Station1_Receiver.PrimaryAntenna = Station1_Antenna;
GMAT Station1_Receiver.Id = '0';

Create ErrorModel Station1_AzimuthModel;
GMAT Station1_AzimuthModel.Type = 'Azimuth';
GMAT Station1_AzimuthModel.NoiseSigma = 0.0002777777777777778;
GMAT Station1_AzimuthModel.Bias = 0.0;
GMAT Station1_AzimuthModel.BiasSigma = 1e+070;

Create ErrorModel Station1_ElevationModel;
GMAT Station1_ElevationModel.Type = 'Elevation';
GMAT Station1_ElevationModel.NoiseSigma = 0.0002777777777777778;
GMAT Station1_ElevationModel.Bias = 0.0;
GMAT Station1_ElevationModel.BiasSigma = 1e+070;


Create ForceModel ODProp_ForceModel;

GMAT ODProp_ForceModel.CentralBody = Earth;
GMAT ODProp_ForceModel.PrimaryBodies = {Earth};
GMAT ODProp_ForceModel.PointMasses = {Jupiter, Luna, Sun};
GMAT ODProp_ForceModel.Drag = None;
GMAT ODProp_ForceModel.SRP = Off;
GMAT ODProp_ForceModel.RelativisticCorrection = Off;
GMAT ODProp_ForceModel.ErrorControl = None;
GMAT ODProp_ForceModel.GravityField.Earth.PotentialFile = 'JGM2.cof';
GMAT ODProp_ForceModel.GravityField.Earth.Degree = 8;
GMAT ODProp_ForceModel.GravityField.Earth.Order = 8;
GMAT ODProp_ForceModel.GravityField.Earth.StmLimit = 100;
GMAT ODProp_ForceModel.GravityField.Earth.TideModel = 'None';

Create Propagator ODProp;

GMAT ODProp.FM = ODProp_ForceModel;
GMAT ODProp.Type = RungeKutta89;
GMAT ODProp.InitialStepSize = 30;
GMAT ODProp.Accuracy = 1e-013;
GMAT ODProp.MinStep = 0;
GMAT ODProp.MaxStep = 30;
GMAT ODProp.MaxStepAttempts = 50;
GMAT ODProp.StopIfAccuracyIsViolated = true;


Create Simulator Station1_0_simulator;
GMAT Station1_0_simulator.AddData = {Station1_0_data};
GMAT Station1_0_simulator.Propagator = ODProp;
GMAT Station1_0_simulator.EpochFormat = UTCGregorian;
GMAT Station1_0_simulator.InitialEpoch = '11 Oct 2019 00:05:49.383';
GMAT Station1_0_simulator.FinalEpoch = '11 Oct 2019 00:06:49.383';
GMAT Station1_0_simulator.MeasurementTimeStep = 10;
GMAT Station1_0_simulator.AddNoise = Off;

Create TrackingFileSet Station1_0_data;
GMAT Station1_0_data.AddTrackingConfig = {{Station1,EstSat,Station1},Azimuth,Elevation};
GMAT Station1_0_data.FileName = {Station1_0_measurements.gmd};
GMAT Station1_0_data.UseLightTime = true;
GMAT Station1_0_data.UseRelativityCorrection = false;
GMAT Station1_0_data.UseETminusTAI = false;
GMAT Station1_0_data.AberrationCorrection = 'AnnualAndDiurnal';


BeginMissionSequence

Propagate BackProp ODProp(EstSat) {EstSat.ElapsedDays = -3};

RunSimulator Station1_0_simulator;