Create Spacecraft wind;
GMAT wind.DateFormat = UTCGregorian;
GMAT wind.Epoch = '28 Jun 2019 12:26:24.248';
GMAT wind.CoordinateSystem = EarthMJ2000Eq;
GMAT wind.DisplayStateType = Cartesian;
GMAT wind.X = -773695.05056;
GMAT wind.Y = 1212282.71475;
GMAT wind.Z = 480068.14193;
GMAT wind.VX = -0.339605;
GMAT wind.VY = -0.078260;
GMAT wind.VZ = -0.021361;
GMAT wind.DryMass = 886.102672;
GMAT wind.Cd = 2.2;
GMAT wind.Cr = 1.688801632554336;
GMAT wind.DragArea = 1;
GMAT wind.SRPArea = 4.514;
GMAT wind.Tanks = {FuelTank1};
GMAT wind.NAIFId = -123456789;
GMAT wind.NAIFIdReferenceFrame = -123456789;
GMAT wind.OrbitColor = Red;
GMAT wind.TargetColor = Teal;
GMAT wind.EstimationStateType = 'Cartesian';
GMAT wind.OrbitErrorCovariance = [ 1e+070 0 0 0 0 0 ; 0 1e+070 0 0 0 0 ; 0 0 1e+070 0 0 0 ; 0 0 0 1e+070 0 0 ; 0 0 0 0 1e+070 0 ; 0 0 0 0 0 1e+070 ];
GMAT wind.CdSigma = 1e+070;
GMAT wind.CrSigma = 0.02;
GMAT wind.Id = '8';
GMAT wind.Attitude = Spinner;
GMAT wind.SPADSRPScaleFactor = 1;
GMAT wind.AddHardware = {HGA, scTransponder};
GMAT wind.SolveFors = {'CartesianState', 'Cr'};
GMAT wind.ModelFile = '../../../global_workspace/data/vehicle/models/aura.3ds';
GMAT wind.ModelOffsetX = 0;
GMAT wind.ModelOffsetY = 0;
GMAT wind.ModelOffsetZ = 0;
GMAT wind.ModelRotationX = 0;
GMAT wind.ModelRotationY = 0;
GMAT wind.ModelRotationZ = 0;
GMAT wind.ModelScale = 3;
GMAT wind.AttitudeDisplayStateType = 'Quaternion';
GMAT wind.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT wind.Q1 = -0.6872238392592825;
GMAT wind.Q2 = 0.6975921746300752;
GMAT wind.Q3 = 0.1422556048473538;
GMAT wind.Q4 = 0.144401854344493;
GMAT wind.EulerAngleSequence = '323';
GMAT wind.AngularVelocityX = 0;
GMAT wind.AngularVelocityY = 0;
GMAT wind.AngularVelocityZ = 0;