Create Spacecraft Sat;
GMAT Sat.J2000BodyName = Earth;
GMAT Sat.DateFormat = UTCGregorian;
GMAT Sat.Epoch = 23 Jan 2010 00:00:04.033;
GMAT Sat.StateType = Cartesian;
GMAT Sat.CoordinateSystem = EarthMJ2000Eq;
GMAT Sat.X = 406326.22661319101;
GMAT Sat.Y = 177458.38761597816;
GMAT Sat.Z = 145838.58079004413;
GMAT Sat.VX = -0.51727467382287506;
GMAT Sat.VY = 0.77465036656089314;
GMAT Sat.VZ = 0.33141660265398565;

Create Spacecraft Sat2;

GMAT Sat.AnomalyType = TA;
GMAT Sat.DryMass = 850;
GMAT Sat.Cd = 2.2000000000000002;
GMAT Sat.Cr = 1.8;
GMAT Sat.DragArea = 15;
GMAT Sat.SRPArea = 1;
GMAT Sat.TotalMass = 850;

GMAT SolarSystem.UseTTForEphemeris = true;

Create ForceModel EarthMoonL2Prop_ForceModel;
GMAT EarthMoonL2Prop_ForceModel.CentralBody = Earth;
GMAT EarthMoonL2Prop_ForceModel.PointMasses = {Earth, Sun, Luna};
GMAT EarthMoonL2Prop_ForceModel.Drag = None;
GMAT EarthMoonL2Prop_ForceModel.SRP = Off;
GMAT EarthMoonL2Prop_ForceModel.ErrorControl = RSSState;


Create Propagator EarthMoonL2Prop;
GMAT EarthMoonL2Prop.FM = EarthMoonL2Prop_ForceModel;
GMAT EarthMoonL2Prop.Type = RungeKutta89;
GMAT EarthMoonL2Prop.InitialStepSize = 130;
GMAT EarthMoonL2Prop.Accuracy = 1e-012;
GMAT EarthMoonL2Prop.MinStep = 0.001;
GMAT EarthMoonL2Prop.MaxStep = 100;
GMAT EarthMoonL2Prop.MaxStepAttempts = 50;

Create ReportFile SatData;

%Create XYPlot Time;
%GMAT Time.IndVar = Sat.ElapsedDays;
%GMAT Time.Add    = Sat.ElapsedDays;

GMAT Sat2 = Sat;

Propagate EarthMoonL2Prop(Sat, {Sat.ElapsedDays = 28});
Report SatData Sat.UTCGregorian Sat.X Sat.Y Sat.Z Sat.VX Sat.VY Sat.VZ;

For i = 1:280
    Propagate EarthMoonL2Prop(Sat2, {Sat2.ElapsedDays = 0.1});
EndFor
Report SatData Sat2.UTCGregorian Sat2.X Sat2.Y Sat2.Z Sat2.VX Sat2.VY Sat2.VZ;