%General Mission Analysis Tool(GMAT) Script
%Created: 2012-09-13 06:34:31


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

Create Spacecraft MAVEN;
GMAT MAVEN.DateFormat = UTCGregorian;
GMAT MAVEN.Epoch = '18 Nov 2013 20:26:24.315';
GMAT MAVEN.CoordinateSystem = EarthMJ2000Eq;
GMAT MAVEN.DisplayStateType = Keplerian;
GMAT MAVEN.SMA = -32593.21599272777;
GMAT MAVEN.ECC = 1.202872548116186;
GMAT MAVEN.INC = 28.80241266404144;
GMAT MAVEN.RAAN = 173.9693759331483;
GMAT MAVEN.AOP = 240.9696529532762;
GMAT MAVEN.TA = 359.9465533778342;
GMAT MAVEN.DryMass = 850;
GMAT MAVEN.Cd = 2.2;
GMAT MAVEN.Cr = 1.8;
GMAT MAVEN.DragArea = 15;
GMAT MAVEN.SRPArea = 1;
GMAT MAVEN.Tanks = {MainTank};
GMAT MAVEN.NAIFId = -123456789;
GMAT MAVEN.NAIFIdReferenceFrame = -123456789;
GMAT MAVEN.Id = 'SatId';
GMAT MAVEN.Attitude = CoordinateSystemFixed;
GMAT MAVEN.ModelFile = '../data/vehicle/models/aura.3ds';
GMAT MAVEN.ModelOffsetX = 0;
GMAT MAVEN.ModelOffsetY = 0;
GMAT MAVEN.ModelOffsetZ = 0;
GMAT MAVEN.ModelRotationX = 0;
GMAT MAVEN.ModelRotationY = 0;
GMAT MAVEN.ModelRotationZ = 0;
GMAT MAVEN.ModelScale = 3;
GMAT MAVEN.AttitudeDisplayStateType = 'Quaternion';
GMAT MAVEN.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT MAVEN.AttitudeCoordinateSystem = EarthMJ2000Eq;
GMAT MAVEN.EulerAngleSequence = '321';


%----------------------------------------
%---------- Hardware Components
%----------------------------------------
Create FuelTank MainTank;
GMAT MainTank.AllowNegativeFuelMass = false;
GMAT MainTank.FuelMass = 1718;
GMAT MainTank.Pressure = 5000;
GMAT MainTank.Temperature = 20;
GMAT MainTank.RefTemperature = 20;
GMAT MainTank.Volume = 2;
GMAT MainTank.FuelDensity = 1000;
GMAT MainTank.PressureModel = PressureRegulated;

%----------------------------------------
%---------- ForceModels
%----------------------------------------

Create ForceModel NearEarth_ForceModel;
GMAT NearEarth_ForceModel.CentralBody = Earth;
GMAT NearEarth_ForceModel.PointMasses = {Earth};
GMAT NearEarth_ForceModel.Drag = None;
GMAT NearEarth_ForceModel.SRP = On;
GMAT NearEarth_ForceModel.RelativisticCorrection = Off;
GMAT NearEarth_ForceModel.ErrorControl = RSSStep;
GMAT NearEarth_ForceModel.SRP.Flux = 1367;
GMAT NearEarth_ForceModel.SRP.SRPModel = Spherical;
GMAT NearEarth_ForceModel.SRP.Nominal_Sun = 149597870.691;

Create ForceModel DeepSpace_ForceModel;
GMAT DeepSpace_ForceModel.CentralBody = Sun;
GMAT DeepSpace_ForceModel.PointMasses = {Earth, Jupiter, Luna, Mars, Neptune, Saturn, Sun, Uranus, Venus};
GMAT DeepSpace_ForceModel.Drag = None;
GMAT DeepSpace_ForceModel.SRP = On;
GMAT DeepSpace_ForceModel.RelativisticCorrection = Off;
GMAT DeepSpace_ForceModel.ErrorControl = RSSStep;
GMAT DeepSpace_ForceModel.SRP.Flux = 1367;
GMAT DeepSpace_ForceModel.SRP.Nominal_Sun = 149597870.691;

Create ForceModel NearMars_ForceModel;
GMAT NearMars_ForceModel.CentralBody = Mars;
%GMAT NearMars_ForceModel.PrimaryBodies = {Mars};
GMAT NearMars_ForceModel.PointMasses = {Mars};
GMAT NearMars_ForceModel.Drag = None;
GMAT NearMars_ForceModel.SRP = On;
GMAT NearMars_ForceModel.RelativisticCorrection = Off;
GMAT NearMars_ForceModel.ErrorControl = RSSStep;
% GMAT NearMars_ForceModel.GravityField.Mars.Degree = 8;
% GMAT NearMars_ForceModel.GravityField.Mars.Order = 8;
% GMAT NearMars_ForceModel.GravityField.Mars.PotentialFile = 'Mars50c.cof';
GMAT NearMars_ForceModel.SRP.Flux = 1367;
GMAT NearMars_ForceModel.SRP.Nominal_Sun = 149597870.691;

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

Create Propagator NearEarth;
GMAT NearEarth.FM = NearEarth_ForceModel;
GMAT NearEarth.Type = RungeKutta89;
GMAT NearEarth.InitialStepSize = 600;
GMAT NearEarth.Accuracy = 1e-013;
GMAT NearEarth.MinStep = 0;
GMAT NearEarth.MaxStep = 600;
GMAT NearEarth.MaxStepAttempts = 50;
GMAT NearEarth.StopIfAccuracyIsViolated = true;

Create Propagator DeepSpace;
GMAT DeepSpace.FM = DeepSpace_ForceModel;
GMAT DeepSpace.Type = PrinceDormand78;
GMAT DeepSpace.InitialStepSize = 600;
GMAT DeepSpace.Accuracy = 1e-012;
GMAT DeepSpace.MinStep = 0;
GMAT DeepSpace.MaxStep = 864000;
GMAT DeepSpace.MaxStepAttempts = 50;
GMAT DeepSpace.StopIfAccuracyIsViolated = true;

Create Propagator NearMars;
GMAT NearMars.FM = NearMars_ForceModel;
GMAT NearMars.Type = PrinceDormand78;
GMAT NearMars.InitialStepSize = 600;
GMAT NearMars.Accuracy = 1e-012;
GMAT NearMars.MinStep = 0;
GMAT NearMars.MaxStep = 86400;
GMAT NearMars.MaxStepAttempts = 50;
GMAT NearMars.StopIfAccuracyIsViolated = true;

%----------------------------------------
%---------- Burns
%----------------------------------------

Create ImpulsiveBurn TCM;
GMAT TCM.CoordinateSystem = Local;
GMAT TCM.Origin = Earth;
GMAT TCM.Axes = VNB;
GMAT TCM.Element1 = 0;
GMAT TCM.Element2 = 0;
GMAT TCM.Element3 = 0;
GMAT TCM.DecrementMass = true;
GMAT TCM.Tank = {MainTank};
GMAT TCM.Isp = 300;
GMAT TCM.GravitationalAccel = 9.810000000000001;

Create ImpulsiveBurn MOI;
GMAT MOI.CoordinateSystem = Local;
GMAT MOI.Origin = Mars;
GMAT MOI.Axes = VNB;
GMAT MOI.Element1 = 0;
GMAT MOI.Element2 = 0;
GMAT MOI.Element3 = 0;
GMAT MOI.DecrementMass = true;
GMAT MOI.Tank = {MainTank};
GMAT MOI.Isp = 300;
GMAT MOI.GravitationalAccel = 9.810000000000001;

%----------------------------------------
%---------- Coordinate Systems
%----------------------------------------

Create CoordinateSystem SunEcliptic;
GMAT SunEcliptic.Origin = Sun;
GMAT SunEcliptic.Axes = MJ2000Ec;

Create CoordinateSystem MarsInertial;
GMAT MarsInertial.Origin = Mars;
GMAT MarsInertial.Axes = BodyInertial;

%----------------------------------------
%---------- Solvers
%----------------------------------------

Create DifferentialCorrector DefaultDC;
GMAT DefaultDC.ShowProgress = true;
GMAT DefaultDC.ReportStyle = Normal;
GMAT DefaultDC.ReportFile = 'DifferentialCorrectorDC1.data';
GMAT DefaultDC.MaximumIterations = 25;
GMAT DefaultDC.DerivativeMethod = ForwardDifference;

%----------------------------------------
%---------- Subscribers
%----------------------------------------

Create OrbitView EarthView;
GMAT EarthView.SolverIterations = Current;
GMAT EarthView.UpperLeft = [ 0.002941176470588235 0.03195876288659794 ];
GMAT EarthView.Size = [ 0.3047058823529412 0.9092783505154639 ];
GMAT EarthView.RelativeZOrder = 56;
GMAT EarthView.Maximized = false;
GMAT EarthView.Add = {MAVEN, Earth};
GMAT EarthView.CoordinateSystem = EarthMJ2000Eq;
GMAT EarthView.DrawObject = [ true true ];
GMAT EarthView.DataCollectFrequency = 1;
GMAT EarthView.UpdatePlotFrequency = 50;
GMAT EarthView.NumPointsToRedraw = 0;
GMAT EarthView.ShowPlot = true;
GMAT EarthView.ViewPointReference = Earth;
GMAT EarthView.ViewPointVector = [ 0 0 30000 ];
GMAT EarthView.ViewDirection = Earth;
GMAT EarthView.ViewScaleFactor = 4;
GMAT EarthView.ViewUpCoordinateSystem = EarthMJ2000Eq;
GMAT EarthView.ViewUpAxis = Z;
GMAT EarthView.EclipticPlane = Off;
GMAT EarthView.XYPlane = On;
GMAT EarthView.WireFrame = Off;
GMAT EarthView.Axes = On;
GMAT EarthView.Grid = Off;
GMAT EarthView.SunLine = Off;
GMAT EarthView.UseInitialView = On;
GMAT EarthView.StarCount = 7000;
GMAT EarthView.EnableStars = On;
GMAT EarthView.EnableConstellations = On;

Create OrbitView SolarSystemView;
GMAT SolarSystemView.SolverIterations = Current;
GMAT SolarSystemView.UpperLeft = [ 0.3088235294117647 0.03298969072164949 ];
GMAT SolarSystemView.Size = [ 0.3135294117647059 0.9061855670103093 ];
GMAT SolarSystemView.RelativeZOrder = 75;
GMAT SolarSystemView.Maximized = false;
GMAT SolarSystemView.Add = {MAVEN, Earth, Mars, Sun};
GMAT SolarSystemView.CoordinateSystem = SunEcliptic;
GMAT SolarSystemView.DrawObject = [ true true true true ];
GMAT SolarSystemView.DataCollectFrequency = 1;
GMAT SolarSystemView.UpdatePlotFrequency = 50;
GMAT SolarSystemView.NumPointsToRedraw = 0;
GMAT SolarSystemView.ShowPlot = true;
GMAT SolarSystemView.ViewPointReference = Sun;
GMAT SolarSystemView.ViewPointVector = [ 0 0 500000000 ];
GMAT SolarSystemView.ViewDirection = Sun;
GMAT SolarSystemView.ViewScaleFactor = 1;
GMAT SolarSystemView.ViewUpCoordinateSystem = SunEcliptic;
GMAT SolarSystemView.ViewUpAxis = Z;
GMAT SolarSystemView.EclipticPlane = Off;
GMAT SolarSystemView.XYPlane = On;
GMAT SolarSystemView.WireFrame = Off;
GMAT SolarSystemView.Axes = On;
GMAT SolarSystemView.Grid = Off;
GMAT SolarSystemView.SunLine = Off;
GMAT SolarSystemView.UseInitialView = On;
GMAT SolarSystemView.StarCount = 7000;
GMAT SolarSystemView.EnableStars = On;
GMAT SolarSystemView.EnableConstellations = On;

Create OrbitView MarsView;
GMAT MarsView.SolverIterations = Current;
GMAT MarsView.UpperLeft = [ 0.6241176470588236 0.03195876288659794 ];
GMAT MarsView.Size = [ 0.3541176470588235 0.9010309278350516 ];
GMAT MarsView.RelativeZOrder = 73;
GMAT MarsView.Maximized = false;
GMAT MarsView.Add = {MAVEN, Mars, Earth};
GMAT MarsView.CoordinateSystem = MarsInertial;
GMAT MarsView.DrawObject = [ true true true ];
GMAT MarsView.DataCollectFrequency = 1;
GMAT MarsView.UpdatePlotFrequency = 50;
GMAT MarsView.NumPointsToRedraw = 0;
GMAT MarsView.ShowPlot = true;
GMAT MarsView.ViewPointReference = Mars;
GMAT MarsView.ViewPointVector = [ 22000 22000 0 ];
GMAT MarsView.ViewDirection = Mars;
GMAT MarsView.ViewScaleFactor = 1;
GMAT MarsView.ViewUpCoordinateSystem = MarsInertial;
GMAT MarsView.ViewUpAxis = Z;
GMAT MarsView.EclipticPlane = Off;
GMAT MarsView.XYPlane = On;
GMAT MarsView.WireFrame = Off;
GMAT MarsView.Axes = On;
GMAT MarsView.Grid = Off;
GMAT MarsView.SunLine = Off;
GMAT MarsView.UseInitialView = On;
GMAT MarsView.StarCount = 7000;
GMAT MarsView.EnableStars = On;
GMAT MarsView.EnableConstellations = On;

Create ReportFile rf
rf.SolverIterations = None;
GMAT rf.Filename = 'rf.txt';

Create ReportFile rf2
rf2.SolverIterations = Current;
rf2.Filename = 'rf2.txt'

Create ReportFile rf3
rf3.Filename = 'Mars_B_Plane_Targeting_output_2.report'
rf3.WriteHeaders = false


Create GmatFunction Case_2;



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



BeginMissionSequence;

% Test 2: 
Global 'make All subscirbers Global' MAVEN DeepSpace_ForceModel DefaultDC EarthView MainTank MarsView MOI NearEarth_ForceModel NearMars_ForceModel rf rf2 rf3 SolarSystemView TCM;
Case_2();


Report rf3 MAVEN.UTCModJulian MAVEN.MarsInertial.X MAVEN.MarsInertial.Y MAVEN.MarsInertial.Z MAVEN.MarsInertial.VX MAVEN.MarsInertial.VY MAVEN.MarsInertial.VZ

Propagate 'Prop for 1 more day' NearMars(MAVEN) {MAVEN.ElapsedDays = 1};

Report rf3 MAVEN.UTCModJulian MAVEN.MarsInertial.X MAVEN.MarsInertial.Y MAVEN.MarsInertial.Z MAVEN.MarsInertial.VX MAVEN.MarsInertial.VY MAVEN.MarsInertial.VZ