% ---- Spacecraft A Earth Baseline
 
Create Spacecraft Sc;
GMAT Sc.DateFormat = TAIModJulian;
GMAT Sc.Epoch = '21545.000000000';
GMAT Sc.CoordinateSystem = EarthMJ2000Eq;
GMAT Sc.DryMass = 850;
GMAT Sc.Cd = 2.2;
GMAT Sc.Cr = 1.8;
GMAT Sc.DragArea = 15;
GMAT Sc.SRPArea = 1;
GMAT Sc.Tanks = {TankL};
GMAT Sc.Thrusters = {ThrusterB};
GMAT Sc.Attitude = CoordinateSystemFixed;
GMAT Sc.AttitudeDisplayStateType = 'EulerAngles';
GMAT Sc.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT Sc.AttitudeCoordinateSystem = 'EarthMJ2000Eq';
GMAT Sc.EulerAngleSequence = '312';
GMAT Sc.EulerAngle1 = 35.2643896827547;
GMAT Sc.EulerAngle2 = 0;
GMAT Sc.EulerAngle3 = -45;
GMAT Sc.AngularVelocityX = 0;
GMAT Sc.AngularVelocityY = 0;
GMAT Sc.AngularVelocityZ = 0;
% --- Planet Specific Coords
GMAT Sc.X = 7653.768;
GMAT Sc.Y = 0;
GMAT Sc.Z = 0;
GMAT Sc.VX = 0;
GMAT Sc.VY = 7.2166;
GMAT Sc.VZ = 0;
GMAT Earth.Mu = 398600.4415;
 
% Tank L Baseline Blowdown Tank
Create FuelTank TankL;
GMAT TankL.FuelMass = 725;
GMAT TankL.Pressure = 1200;
GMAT TankL.Temperature = 20;
GMAT TankL.RefTemperature = 12;
GMAT TankL.Volume = 0.8;
GMAT TankL.FuelDensity = 1029;
GMAT TankL.PressureModel = BlowDown;
 
 
% Thruster B Off Direction
Create Thruster ThrusterB;
GMAT ThrusterB.CoordinateSystem = Local;
GMAT ThrusterB.Origin = Earth;
GMAT ThrusterB.Axes = SpacecraftBody;
GMAT ThrusterB.ThrustDirection1 = 1;
GMAT ThrusterB.ThrustDirection2 = 0;
GMAT ThrusterB.ThrustDirection3 = 0;
GMAT ThrusterB.DutyCycle = 1;
GMAT ThrusterB.ThrustScaleFactor = 1;
GMAT ThrusterB.DecrementMass = true;
GMAT ThrusterB.Tank = {TankL};
GMAT ThrusterB.GravitationalAccel = 9.81;
GMAT ThrusterB.C1 = 10;
GMAT ThrusterB.C2 = 0.25;
GMAT ThrusterB.C3 = 0.25;
GMAT ThrusterB.C4 = 0;
GMAT ThrusterB.C5 = 0;
GMAT ThrusterB.C6 = 0;
GMAT ThrusterB.C7 = 0;
GMAT ThrusterB.C8 = 0;
GMAT ThrusterB.C9 = 0;
GMAT ThrusterB.C10 = 0;
GMAT ThrusterB.C11 = 0;
GMAT ThrusterB.C12 = 0;
GMAT ThrusterB.C13 = 0;
GMAT ThrusterB.C14 = 0;
GMAT ThrusterB.C15 = 0;
GMAT ThrusterB.C16 = 0;
GMAT ThrusterB.K1 = 300;
GMAT ThrusterB.K2 = 0.25;
GMAT ThrusterB.K3 = 0.25;
GMAT ThrusterB.K4 = 0;
GMAT ThrusterB.K5 = 0;
GMAT ThrusterB.K6 = 0;
GMAT ThrusterB.K7 = 0;
GMAT ThrusterB.K8 = 0;
GMAT ThrusterB.K9 = 0;
GMAT ThrusterB.K10 = 0;
GMAT ThrusterB.K11 = 0;
GMAT ThrusterB.K12 = 0;
GMAT ThrusterB.K13 = 0;
GMAT ThrusterB.K14 = 0;
GMAT ThrusterB.K15 = 0;
GMAT ThrusterB.K16 = 0;
 
 
%--------------------
% Create Finite Burn 
% -------------------
Create FiniteBurn fb1;
GMAT fb1.Thrusters = {ThrusterB};
 
 
 %--- Alternate Coord System Not needed for Earth
 
Create ForceModel fm;
GMAT fm.CentralBody = Earth;
GMAT fm.PointMasses = {Earth};
GMAT fm.Drag = None;
GMAT fm.SRP = Off;
GMAT fm.ErrorControl = RSSStep;
 
 
%  Create a propagator
Create Propagator prop;
GMAT prop.FM = fm;
GMAT prop.Type = RungeKutta56;
GMAT prop.InitialStepSize = 0.001;
GMAT prop.Accuracy = 1e-012;
GMAT prop.MinStep = 0.001;    %0.001;
GMAT prop.MaxStep = 432000;  %was 60
GMAT prop.MaxStepAttempts = 50;
 

 
Create Variable loop;

%% test for ReportFile FRR-30
%%  Create a report file
Create ReportFile rf1;
GMAT rf1.Filename = 'Thruster_FBurn_Earth_ScA_ThrusterB_CS3_TankL_RK56.report';
GMAT rf1.Precision = 16;
GMAT rf1.Add = {Sc.TAIModJulian, Sc.EarthMJ2000Eq.X, Sc.EarthMJ2000Eq.Y, Sc.EarthMJ2000Eq.Z, Sc.EarthMJ2000Eq.VX, Sc.EarthMJ2000Eq.VY, Sc.EarthMJ2000Eq.VZ, Sc.TotalMass, Sc.TankL.FuelMass};

GMAT rf1.WriteHeaders = On;
GMAT rf1.ZeroFill = On;
GMAT rf1.ColumnWidth = 27;
GMAT rf1.LeftJustify = On;



Create XYPlot XYPlot1;
GMAT XYPlot1.SolverIterations = Current;
GMAT XYPlot1.UpperLeft = [ 0.2830188679245283 0 ];
GMAT XYPlot1.Size = [ 0.5783018867924529 0.8508771929824561 ];
GMAT XYPlot1.RelativeZOrder = 284;
GMAT XYPlot1.XVariable = Sc.ElapsedSecs; %Sc.ElapsedDays;
GMAT XYPlot1.YVariables = {Sc.EarthMJ2000Eq.X};
GMAT XYPlot1.ShowGrid = true;
GMAT XYPlot1.ShowPlot = true;




%%%----------------------------------------
%%%---------- Mission Sequence
%%%----------------------------------------
%%%
%%%
%%%-----------Begin Propagation and Report Generation--------
%%% Propagate based on preset propagation parameters
%%% and current stop conditions.
BeginMissionSequence;
%
%% Output Report file data for each propagation set in the FOR loop

BeginFiniteBurn fb1(Sc);
Propagate prop(Sc,{Sc.ElapsedSecs = 7200})
ClearPlot XYPlot1;
Propagate BackProp prop(Sc,{Sc.ElapsedSecs = -7200})
EndFiniteBurn fb1(Sc);
%