Hi GMAT team,
My name is Anthony Gardner and I am a Senior Aerospace Engineering student
at TAMU. I am currently involved in a research project that is attempting
to use x-ray pulsars as reference points for deep space navigation. So far,
I have created a rudimentary mission to Mars and my next goal is to
populate this mission sim with astronomical bodies to represent pulsars. I
would then like to attach coordinate systems to these bodies for position
tracking purposes.
Additionally, I have been playing with the if-else loops in GMAT to
establish a constraint on position error. Ideally, I would like to define
this error as 5km off of the spacecraft's "ideal" trajectory to Mars. For
example, IF spacecraft position error exceeds 5km, apply burn; ELSE
propagate trajectory. Unfortunately, I have not had much luck with these
loops thus far.
I have looked around online and reading material on these topics is
limited. I would really appreciate any guidance/links to reference
materials related to my current work. I am also attaching my script to this
email; please let me know if you have any questions for me.
Thanks for your help,
Anthony Gardner
Aerospace Engineering '18
Texas A&M University
%General Mission Analysis Tool(GMAT) Script
%Created: 2017-08-21 14:24:26
%----------------------------------------
%---------- User-Defined Calculated Points
%----------------------------------------
Create Barycenter EarthMarsBarycenter;
GMAT EarthMarsBarycenter.OrbitColor = Gold;
GMAT EarthMarsBarycenter.TargetColor = DarkGray;
GMAT EarthMarsBarycenter.BodyNames = {Earth, Mars};
%----------------------------------------
%---------- Spacecraft
%----------------------------------------
Create Spacecraft MarsSat;
GMAT MarsSat.DateFormat = UTCGregorian;
GMAT MarsSat.Epoch = '10 May 2018 00:00:00.000';
GMAT MarsSat.CoordinateSystem = EarthMJ2000Eq;
GMAT MarsSat.DisplayStateType = Keplerian;
GMAT MarsSat.SMA = 6563.000000000009;
GMAT MarsSat.ECC = 0.001000000000000968;
GMAT MarsSat.INC = 28.69999999999998;
GMAT MarsSat.RAAN = 263;
GMAT MarsSat.AOP = 360;
GMAT MarsSat.TA = 8.537736462515939e-007;
GMAT MarsSat.DryMass = 850;
GMAT MarsSat.Cd = 2.2;
GMAT MarsSat.Cr = 1.8;
GMAT MarsSat.DragArea = 15;
GMAT MarsSat.SRPArea = 1;
GMAT MarsSat.NAIFId = -10000001;
GMAT MarsSat.NAIFIdReferenceFrame = -9000001;
GMAT MarsSat.OrbitColor = Red;
GMAT MarsSat.TargetColor = Teal;
GMAT MarsSat.EstimationStateType = 'Cartesian';
GMAT MarsSat.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 MarsSat.CdSigma = 1e+070;
GMAT MarsSat.CrSigma = 1e+070;
GMAT MarsSat.Id = 'SatId';
GMAT MarsSat.Attitude = CoordinateSystemFixed;
GMAT MarsSat.SPADSRPScaleFactor = 1;
GMAT MarsSat.ModelFile = 'aura.3ds';
GMAT MarsSat.ModelOffsetX = 0;
GMAT MarsSat.ModelOffsetY = 0;
GMAT MarsSat.ModelOffsetZ = 0;
GMAT MarsSat.ModelRotationX = 0;
GMAT MarsSat.ModelRotationY = 0;
GMAT MarsSat.ModelRotationZ = 0;
GMAT MarsSat.ModelScale = 1;
GMAT MarsSat.AttitudeDisplayStateType = 'Quaternion';
GMAT MarsSat.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT MarsSat.AttitudeCoordinateSystem = EarthMJ2000Eq;
GMAT MarsSat.EulerAngleSequence = '321';
%----------------------------------------
%---------- Mission Sequence
%----------------------------------------
Create Spacecraft InitSat;
GMAT InitSat.DateFormat = UTCGregorian;
GMAT InitSat.Epoch = '10 May 2018 00:00:00.000';
GMAT InitSat.CoordinateSystem = EarthMJ2000Eq;
GMAT InitSat.DisplayStateType = Keplerian;
GMAT InitSat.SMA = 6563.000000000009;
GMAT InitSat.ECC = 0.001000000000000968;
GMAT InitSat.INC = 28.69999999999998;
GMAT InitSat.RAAN = 263;
GMAT InitSat.AOP = 360;
GMAT InitSat.TA = 8.537736462515939e-007;
GMAT InitSat.DryMass = 850;
GMAT InitSat.Cd = 2.2;
GMAT InitSat.Cr = 1.8;
GMAT InitSat.DragArea = 15;
GMAT InitSat.SRPArea = 1;
GMAT InitSat.NAIFId = -10000001;
GMAT InitSat.NAIFIdReferenceFrame = -9000001;
GMAT InitSat.OrbitColor = Red;
GMAT InitSat.TargetColor = Teal;
GMAT InitSat.EstimationStateType = 'Cartesian';
GMAT InitSat.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 InitSat.CdSigma = 1e+070;
GMAT InitSat.CrSigma = 1e+070;
GMAT InitSat.Id = 'SatId';
GMAT InitSat.Attitude = CoordinateSystemFixed;
GMAT InitSat.SPADSRPScaleFactor = 1;
GMAT InitSat.ModelFile = 'aura.3ds';
GMAT InitSat.ModelOffsetX = 0;
GMAT InitSat.ModelOffsetY = 0;
GMAT InitSat.ModelOffsetZ = 0;
GMAT InitSat.ModelRotationX = 0;
GMAT InitSat.ModelRotationY = 0;
GMAT InitSat.ModelRotationZ = 0;
GMAT InitSat.ModelScale = 1;
GMAT InitSat.AttitudeDisplayStateType = 'Quaternion';
GMAT InitSat.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT InitSat.AttitudeCoordinateSystem = EarthMJ2000Eq;
GMAT InitSat.EulerAngleSequence = '321';
%----------------------------------------
%---------- ForceModels
%----------------------------------------
Create ForceModel NearEarthProp_ForceModel;
GMAT NearEarthProp_ForceModel.CentralBody = Earth;
GMAT NearEarthProp_ForceModel.PointMasses = {Earth, Mars, Sun};
GMAT NearEarthProp_ForceModel.Drag = None;
GMAT NearEarthProp_ForceModel.SRP = On;
GMAT NearEarthProp_ForceModel.RelativisticCorrection = Off;
GMAT NearEarthProp_ForceModel.ErrorControl = RSSStep;
GMAT NearEarthProp_ForceModel.SRP.Flux = 1367;
GMAT NearEarthProp_ForceModel.SRP.SRPModel = Spherical;
GMAT NearEarthProp_ForceModel.SRP.Nominal_Sun = 149597870.691;
Create ForceModel NearMarsProp_ForceModel;
GMAT NearMarsProp_ForceModel.CentralBody = Mars;
GMAT NearMarsProp_ForceModel.PointMasses = {Earth, Jupiter, Mars, Sun};
GMAT NearMarsProp_ForceModel.Drag = None;
GMAT NearMarsProp_ForceModel.SRP = On;
GMAT NearMarsProp_ForceModel.RelativisticCorrection = Off;
GMAT NearMarsProp_ForceModel.ErrorControl = RSSStep;
GMAT NearMarsProp_ForceModel.SRP.Flux = 1367;
GMAT NearMarsProp_ForceModel.SRP.SRPModel = Spherical;
GMAT NearMarsProp_ForceModel.SRP.Nominal_Sun = 149597870.691;
Create ForceModel EarthPointMass_ForceModel;
GMAT EarthPointMass_ForceModel.CentralBody = Sun;
GMAT EarthPointMass_ForceModel.PointMasses = {Earth};
GMAT EarthPointMass_ForceModel.Drag = None;
GMAT EarthPointMass_ForceModel.SRP = On;
GMAT EarthPointMass_ForceModel.RelativisticCorrection = Off;
GMAT EarthPointMass_ForceModel.ErrorControl = RSSStep;
GMAT EarthPointMass_ForceModel.SRP.Flux = 1367;
GMAT EarthPointMass_ForceModel.SRP.SRPModel = Spherical;
GMAT EarthPointMass_ForceModel.SRP.Nominal_Sun = 149597870.691;
%----------------------------------------
%---------- Propagators
%----------------------------------------
Create Propagator NearEarthProp;
GMAT NearEarthProp.FM = NearEarthProp_ForceModel;
GMAT NearEarthProp.Type = PrinceDormand78;
GMAT NearEarthProp.InitialStepSize = 60;
GMAT NearEarthProp.Accuracy = 1e-012;
GMAT NearEarthProp.MinStep = 0;
GMAT NearEarthProp.MaxStep = 160000;
GMAT NearEarthProp.MaxStepAttempts = 50;
GMAT NearEarthProp.StopIfAccuracyIsViolated = true;
Create Propagator NearMarsProp;
GMAT NearMarsProp.FM = NearMarsProp_ForceModel;
GMAT NearMarsProp.Type = PrinceDormand78;
GMAT NearMarsProp.InitialStepSize = 60;
GMAT NearMarsProp.Accuracy = 1e-012;
GMAT NearMarsProp.MinStep = 0;
GMAT NearMarsProp.MaxStep = 160000;
GMAT NearMarsProp.MaxStepAttempts = 50;
GMAT NearMarsProp.StopIfAccuracyIsViolated = true;
Create Propagator EarthPointMass;
GMAT EarthPointMass.FM = EarthPointMass_ForceModel;
GMAT EarthPointMass.Type = PrinceDormand78;
GMAT EarthPointMass.InitialStepSize = 600;
GMAT EarthPointMass.Accuracy = 1e-012;
GMAT EarthPointMass.MinStep = 0.001;
GMAT EarthPointMass.MaxStep = 86400;
GMAT EarthPointMass.MaxStepAttempts = 50;
GMAT EarthPointMass.StopIfAccuracyIsViolated = true;
%----------------------------------------
%---------- Burns
%----------------------------------------
Create ImpulsiveBurn TOI;
GMAT TOI.CoordinateSystem = Local;
GMAT TOI.Origin = Earth;
GMAT TOI.Axes = VNB;
GMAT TOI.Element1 = 3.65;
GMAT TOI.Element2 = 0;
GMAT TOI.Element3 = 0;
GMAT TOI.DecrementMass = false;
GMAT TOI.Isp = 300;
GMAT TOI.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 = false;
GMAT MOI.Isp = 300;
GMAT MOI.GravitationalAccel = 9.810000000000001;
%----------------------------------------
%---------- Coordinate Systems
%----------------------------------------
Create CoordinateSystem SunEcliptic;
GMAT SunEcliptic.Origin = Sun;
GMAT SunEcliptic.Axes = MJ2000Ec;
Create CoordinateSystem EarthSunRotCS;
GMAT EarthSunRotCS.Origin = Sun;
GMAT EarthSunRotCS.Axes = ObjectReferenced;
GMAT EarthSunRotCS.XAxis = R;
GMAT EarthSunRotCS.ZAxis = N;
GMAT EarthSunRotCS.Primary = Sun;
GMAT EarthSunRotCS.Secondary = Earth;
Create CoordinateSystem MarsInertial;
GMAT MarsInertial.Origin = Mars;
GMAT MarsInertial.Axes = BodyInertial;
Create CoordinateSystem EarthMarsRot;
GMAT EarthMarsRot.Origin = Earth;
GMAT EarthMarsRot.Axes = ObjectReferenced;
GMAT EarthMarsRot.XAxis = R;
GMAT EarthMarsRot.ZAxis = N;
GMAT EarthMarsRot.Primary = Earth;
GMAT EarthMarsRot.Secondary = Mars;
Create CoordinateSystem MarsMJ2000Eq;
GMAT MarsMJ2000Eq.Origin = Mars;
GMAT MarsMJ2000Eq.Axes = MJ2000Eq;
Create CoordinateSystem SunCentered;
GMAT SunCentered.Origin = Sun;
GMAT SunCentered.Axes = ICRF;
%----------------------------------------
%---------- Solvers
%----------------------------------------
Create DifferentialCorrector DC1;
GMAT DC1.ShowProgress = true;
GMAT DC1.ReportStyle = Normal;
GMAT DC1.ReportFile = 'DifferentialCorrectorDefaultDC.data';
GMAT DC1.MaximumIterations = 45;
GMAT DC1.DerivativeMethod = ForwardDifference;
GMAT DC1.Algorithm = NewtonRaphson;
%----------------------------------------
%---------- Subscribers
%----------------------------------------
Create OrbitView EarthView;
GMAT EarthView.SolverIterations = Current;
GMAT EarthView.UpperLeft = [ 0.4990825688073395 0.6420664206642066 ];
GMAT EarthView.Size = [ 0.4990825688073395 0.3210332103321033 ];
GMAT EarthView.RelativeZOrder = 1281;
GMAT EarthView.Maximized = false;
GMAT EarthView.Add = {MarsSat, Earth, Mars};
GMAT EarthView.CoordinateSystem = EarthMJ2000Eq;
GMAT EarthView.DrawObject = [ true true true ];
GMAT EarthView.DataCollectFrequency = 1;
GMAT EarthView.UpdatePlotFrequency = 50;
GMAT EarthView.NumPointsToRedraw = 0;
GMAT EarthView.ShowPlot = true;
GMAT EarthView.ShowLabels = true;
GMAT EarthView.ViewPointReference = Earth;
GMAT EarthView.ViewPointVector = [ 0 0 30000 ];
GMAT EarthView.ViewDirection = Earth;
GMAT EarthView.ViewScaleFactor = 1;
GMAT EarthView.ViewUpCoordinateSystem = EarthMJ2000Eq;
GMAT EarthView.ViewUpAxis = Z;
GMAT EarthView.EclipticPlane = Off;
GMAT EarthView.XYPlane = Off;
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 = Off;
Create OrbitView MarsView;
GMAT MarsView.SolverIterations = Current;
GMAT MarsView.UpperLeft = [ 0.4990825688073395 0 ];
GMAT MarsView.Size = [ 0.4990825688073395 0.3210332103321033 ];
GMAT MarsView.RelativeZOrder = 1292;
GMAT MarsView.Maximized = false;
GMAT MarsView.Add = {MarsSat, Earth, Mars};
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.ShowLabels = true;
GMAT MarsView.ViewPointReference = Mars;
GMAT MarsView.ViewPointVector = [ 22000 22000 0 ];
GMAT MarsView.ViewDirection = Mars;
GMAT MarsView.ViewScaleFactor = 1;
GMAT MarsView.ViewUpCoordinateSystem = EarthMJ2000Eq;
GMAT MarsView.ViewUpAxis = Z;
GMAT MarsView.EclipticPlane = Off;
GMAT MarsView.XYPlane = Off;
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 = Off;
Create OrbitView SolarSystemView;
GMAT SolarSystemView.SolverIterations = Current;
GMAT SolarSystemView.UpperLeft = [ 0.4990825688073395 0.3210332103321033 ];
GMAT SolarSystemView.Size = [ 0.4990825688073395 0.3210332103321033 ];
GMAT SolarSystemView.RelativeZOrder = 1286;
GMAT SolarSystemView.Maximized = false;
GMAT SolarSystemView.Add = {MarsSat, 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.ShowLabels = true;
GMAT SolarSystemView.ViewPointReference = Sun;
GMAT SolarSystemView.ViewPointVector = [ 0 0 500000000 ];
GMAT SolarSystemView.ViewDirection = Sun;
GMAT SolarSystemView.ViewScaleFactor = 4;
GMAT SolarSystemView.ViewUpCoordinateSystem = SunEcliptic;
GMAT SolarSystemView.ViewUpAxis = Z;
GMAT SolarSystemView.EclipticPlane = Off;
GMAT SolarSystemView.XYPlane = Off;
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 = Off;
Create OrbitView EarthMarsRotView;
GMAT EarthMarsRotView.SolverIterations = Current;
GMAT EarthMarsRotView.UpperLeft = [ 0 0 ];
GMAT EarthMarsRotView.Size = [ 0.4990825688073395 0.4824723247232473 ];
GMAT EarthMarsRotView.RelativeZOrder = 1510;
GMAT EarthMarsRotView.Maximized = false;
GMAT EarthMarsRotView.Add = {MarsSat, Earth, Mars};
GMAT EarthMarsRotView.CoordinateSystem = EarthMarsRot;
GMAT EarthMarsRotView.DrawObject = [ true true true ];
GMAT EarthMarsRotView.DataCollectFrequency = 1;
GMAT EarthMarsRotView.UpdatePlotFrequency = 50;
GMAT EarthMarsRotView.NumPointsToRedraw = 0;
GMAT EarthMarsRotView.ShowPlot = true;
GMAT EarthMarsRotView.ShowLabels = true;
GMAT EarthMarsRotView.ViewPointReference = Earth;
GMAT EarthMarsRotView.ViewPointVector = [ -30000 0 0 ];
GMAT EarthMarsRotView.ViewDirection = Earth;
GMAT EarthMarsRotView.ViewScaleFactor = 20;
GMAT EarthMarsRotView.ViewUpCoordinateSystem = EarthMarsRot;
GMAT EarthMarsRotView.ViewUpAxis = -X;
GMAT EarthMarsRotView.EclipticPlane = Off;
GMAT EarthMarsRotView.XYPlane = Off;
GMAT EarthMarsRotView.WireFrame = Off;
GMAT EarthMarsRotView.Axes = On;
GMAT EarthMarsRotView.Grid = Off;
GMAT EarthMarsRotView.SunLine = Off;
GMAT EarthMarsRotView.UseInitialView = On;
GMAT EarthMarsRotView.StarCount = 7000;
GMAT EarthMarsRotView.EnableStars = On;
GMAT EarthMarsRotView.EnableConstellations = Off;
Create XYPlot PositionPlot;
GMAT PositionPlot.SolverIterations = Current;
GMAT PositionPlot.UpperLeft = [ 0 0.4824723247232473 ];
GMAT PositionPlot.Size = [ 0.4990825688073395 0.4824723247232473 ];
GMAT PositionPlot.RelativeZOrder = 1304;
GMAT PositionPlot.Maximized = false;
GMAT PositionPlot.XVariable = MarsSat.ElapsedDays;
GMAT PositionPlot.YVariables = {MarsSat.SunCentered.X, MarsSat.SunCentered.Y,
MarsSat.SunCentered.Z};
GMAT PositionPlot.ShowGrid = true;
GMAT PositionPlot.ShowPlot = true;
%----------------------------------------
%---------- Arrays, Variables, Strings
%----------------------------------------
Create Variable RAAN AOP;
GMAT RAAN = 0;
GMAT AOP = 0;
%----------------------------------------
%---------- Mission Sequence
%----------------------------------------
BeginMissionSequence;
Toggle PositionPlot Off;
Target 'Initial Mars Target' DC1 {SolveMode = Solve, ExitMode =
DiscardAndContinue, ShowProgressWindow = true};
Vary 'Vary RAAN' DC1(MarsSat.RAAN = 265.519738727431, {Perturbation =
0.00001, Lower = -360, Upper = 360, MaxStep = 5, AdditiveScaleFactor = 0.0,
MultiplicativeScaleFactor = 1.0});
Vary 'Vary AOP' DC1(MarsSat.AOP = 257.2744780874672, {Perturbation =
0.00001, Lower = -360, Upper = 360, MaxStep = 5, AdditiveScaleFactor = 0.0,
MultiplicativeScaleFactor = 1.0});
Maneuver 'Apply TOI burn' TOI(MarsSat);
GMAT 'Save RAAN' RAAN = MarsSat.RAAN;
GMAT 'Save AOP' AOP = MarsSat.AOP;
Propagate 'Prop to Mars' NearEarthProp(MarsSat) {MarsSat.Mars.Periapsis,
OrbitColor = [255 128 0]};
Achieve 'Achieve RA = 0' DC1(MarsSat.EarthMarsRot.RA = 0, {Tolerance = 1});
Achieve 'Achieve DEC = 0' DC1(MarsSat.EarthMarsRot.DEC = 0, {Tolerance = 1});
EndTarget; % For targeter DC1
GMAT 'Initialize MarsSat' MarsSat = InitSat;
Toggle EarthMarsRotView EarthView MarsView PositionPlot SolarSystemView On;
Target 'Refined Mars Target' DC1 {SolveMode = Solve, ExitMode =
DiscardAndContinue, ShowProgressWindow = true};
Vary 'Vary RAAN' DC1(MarsSat.RAAN = RAAN, {Perturbation = 0.1, Lower = -360,
Upper = 360, MaxStep = 15, AdditiveScaleFactor = 0.0, MultiplicativeScaleFactor
= 1.0});
Vary 'Vary AOP' DC1(MarsSat.AOP = AOP, {Perturbation = 0.1, Lower = -360,
Upper = 360, MaxStep = 15, AdditiveScaleFactor = 0.0, MultiplicativeScaleFactor
= 1.0});
Vary 'Vary TOI deltaV' DC1(TOI.Element1 = TOI.Element1, {Perturbation =
0.0000001, Lower = -10e300, Upper = 10e300, MaxStep = 0.01, AdditiveScaleFactor
= 0.0, MultiplicativeScaleFactor = 1.0});
Maneuver 'Apply TOI burn' TOI(MarsSat);
Propagate 'Prop to Mars' NearEarthProp(MarsSat) {MarsSat.Mars.Periapsis,
MarsSat.Mars.RMAG = 1000, OrbitColor = [255 128 255]};
Achieve 'Achieve Mars RMAG = 20000' DC1(MarsSat.Mars.RMAG = 20000,
{Tolerance = 1});
Achieve 'Achieve Mars Bvecangle = 75' DC1(MarsSat.MarsInertial.BVectorAngle
= 75, {Tolerance = 0.1});
Vary 'Vary MOI deltaV' DC1(MOI.Element1 = -2.987010526770675, {Perturbation
= 0.00001, Lower = -10e300, Upper = 10e300, MaxStep = 0.2, AdditiveScaleFactor
= 0.0, MultiplicativeScaleFactor = 1.0});
Maneuver 'Apply MOI burn' MOI(MarsSat);
Achieve 'Achieve Mars ECC = 0.093' DC1(MarsSat.Mars.ECC = 0.093, {Tolerance
= 0.01});
EndTarget; % For targeter DC1
Propagate 'Prop Mars Orbit' NearMarsProp(MarsSat) {MarsSat.ElapsedDays = 3,
OrbitColor = [255 0 128]};
------------------------------------------------------------------------------
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