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

Create Spacecraft Sat1 Sat1Copy;
GMAT Sat1.DateFormat = UTCGregorian;
GMAT Sat1.Epoch = '01 Jul 2005 14:59:28.000';
GMAT Sat1.CoordinateSystem = EarthMJ2000Eq;
GMAT Sat1.DisplayStateType = Keplerian;
GMAT Sat1.SMA = 8191.93881762901;
GMAT Sat1.ECC = 0.02454974900598161;
GMAT Sat1.INC = 12.85008005658097;
GMAT Sat1.RAAN = 306.6148021947984;
GMAT Sat1.AOP = 314.1905515359913;
GMAT Sat1.TA = 99.88774933204955;
GMAT Sat1.DryMass = 850;
GMAT Sat1.Cd = 2.2;
GMAT Sat1.Cr = 1.8;
GMAT Sat1.DragArea = 15;
GMAT Sat1.SRPArea = 1;

GMAT Sat1Copy.DateFormat = UTCGregorian;
GMAT Sat1Copy.Epoch = '01 Jul 2005 14:59:28.000';
GMAT Sat1Copy.CoordinateSystem = EarthMJ2000Eq;
GMAT Sat1Copy.DisplayStateType = Keplerian;
GMAT Sat1Copy.SMA = 8191.93881762901;
GMAT Sat1Copy.ECC = 0.02454974900598161;
GMAT Sat1Copy.INC = 12.85008005658097;
GMAT Sat1Copy.RAAN = 306.6148021947984;
GMAT Sat1Copy.AOP = 314.1905515359913;
GMAT Sat1Copy.TA = 99.88774933204955;
GMAT Sat1Copy.DryMass = 850;
GMAT Sat1Copy.Cd = 2.2;
GMAT Sat1Copy.Cr = 1.8;
GMAT Sat1Copy.DragArea = 15;
GMAT Sat1Copy.SRPArea = 1;

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

Create ForceModel DefaultProp_ForceModel2;
GMAT DefaultProp_ForceModel2.CentralBody = Earth;
GMAT DefaultProp_ForceModel2.PointMasses   = {Earth,Sun,Luna};
GMAT DefaultProp_ForceModel2.Drag = None;
GMAT DefaultProp_ForceModel2.SRP = On;
GMAT DefaultProp_ForceModel2.ErrorControl = RSSStep;

Create ForceModel DefaultProp_ForceModel;
GMAT DefaultProp_ForceModel.CentralBody = Earth;
GMAT DefaultProp_ForceModel.PrimaryBodies = {Earth};
GMAT DefaultProp_ForceModel.PointMasses   = {Luna, Sun};
GMAT DefaultProp_ForceModel.Drag = MSISE90;
GMAT DefaultProp_ForceModel.SRP = On;
GMAT DefaultProp_ForceModel.ErrorControl = RSSStep;
GMAT DefaultProp_ForceModel.GravityField.Earth.Degree = 4;
GMAT DefaultProp_ForceModel.GravityField.Earth.Order = 4;
GMAT DefaultProp_ForceModel.GravityField.Earth.PotentialFile = 'JGM2.cof';

Create Propagator Prop1;
GMAT Prop1.FM = DefaultProp_ForceModel;
GMAT Prop1.Type = RungeKutta89;
GMAT Prop1.InitialStepSize = 100;
GMAT Prop1.Accuracy = 1e-012;
GMAT Prop1.MinStep = 0.001;
GMAT Prop1.MaxStep = 2700;
GMAT Prop1.MaxStepAttempts = 50;

Create Variable I Case
Create ReportFile rf;

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

Sat1Copy = Sat1;

Report rf Sat1.UTCModJulian Sat1.X Sat1.Y Sat1.Z;
Report rf Sat1Copy.UTCModJulian Sat1Copy.X Sat1Copy.Y Sat1Copy.Z;
Case = 0;

If Case == 0

   Propagate Prop1(Sat1) {Sat1.ElapsedSecs = 300}; 
   Propagate Prop1(Sat1Copy) {Sat1Copy.ElapsedSecs = 300};
   Propagate Prop1(Sat1) {Sat1.ElapsedSecs = 300}; 
   Propagate Prop1(Sat1Copy) {Sat1Copy.ElapsedSecs = 300};

Else


   For I = 1:2
     Propagate Prop1(Sat1) {Sat1.ElapsedSecs = 300}; 
     Propagate Prop1(Sat1Copy) {Sat1Copy.ElapsedSecs = 300};
   EndFor;

EndIf

Report rf Sat1.UTCModJulian Sat1.X Sat1.Y Sat1.Z;
Report rf Sat1Copy.UTCModJulian Sat1Copy.X Sat1Copy.Y Sat1Copy.Z;