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 Spaceship trajectory simulator

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Rang: Administrateur
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Nombre de messages : 6681
Date d'inscription : 31/08/2006
Localisation : Wezembeek - Bruxelles

MessageSujet: Spaceship trajectory simulator   Mar 10 Nov 2015 - 18:12

Pour ceux qui sont passionné par le calcul (réel) des trajectoires de vol, avec tous les
vrais arguments... 

Un joli outil : 

http://gmat.gsfc.nasa.gov



Evidemment, je vous raconte pas l'épaisseur du "introduction guide"...  cool-blue cool-blue cool-blue

Un exemple de script...  scratch

Code:
%General Mission Analysis Tool(GMAT) Script
%Created: 2012-05-16 04:37:14


%----------------------------------------
%---------- 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 = Cartesian;
GMAT MAVEN.X = 3728.345810006184;
GMAT MAVEN.Y = 4697.943961035268;
GMAT MAVEN.Z = -2784.040094879185;
GMAT MAVEN.VX = -9.502477543864449;
GMAT MAVEN.VY = 5.935188001372066;
GMAT MAVEN.VZ = -2.696272103530009;
GMAT MAVEN.DryMass = 904;
GMAT MAVEN.Cd = 2.2;
GMAT MAVEN.Cr = 1;
GMAT MAVEN.DragArea = 20;
GMAT MAVEN.SRPArea = 20;
GMAT MAVEN.Tanks = {MainTank};
GMAT MAVEN.NAIFId = -123456789;
GMAT MAVEN.NAIFIdReferenceFrame = -123456789;
GMAT MAVEN.OrbitColor = Red;
GMAT MAVEN.TargetColor = Teal;
GMAT MAVEN.Id = 'SatId';
GMAT MAVEN.Attitude = CoordinateSystemFixed;
GMAT MAVEN.SPADSRPScaleFactor = 1;
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 = 1;
GMAT MAVEN.AttitudeDisplayStateType = 'Quaternion';
GMAT MAVEN.AttitudeRateDisplayStateType = 'AngularVelocity';
GMAT MAVEN.AttitudeCoordinateSystem = EarthMJ2000Eq;
GMAT MAVEN.EulerAngleSequence = '321';

%----------------------------------------
%---------- Hardware Components
%----------------------------------------
Create ChemicalTank 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.PrimaryBodies = {Earth};
GMAT NearEarth_ForceModel.PointMasses = {Luna, Sun};
GMAT NearEarth_ForceModel.Drag = None;
GMAT NearEarth_ForceModel.SRP = On;
GMAT NearEarth_ForceModel.RelativisticCorrection = Off;
GMAT NearEarth_ForceModel.ErrorControl = RSSStep;
GMAT NearEarth_ForceModel.GravityField.Earth.Degree = 8;
GMAT NearEarth_ForceModel.GravityField.Earth.Order = 8;
GMAT NearEarth_ForceModel.GravityField.Earth.PotentialFile = 'JGM2.cof';
GMAT NearEarth_ForceModel.GravityField.Earth.EarthTideModel = 'None';
GMAT NearEarth_ForceModel.SRP.Flux = 1358;
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, Luna, Mars, Sun, Venus, Jupiter, Saturn, Uranus, Neptune};
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 = 1358;
GMAT DeepSpace_ForceModel.SRP.SRPModel = Spherical;
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 = {Sun};
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 = 1358;
GMAT NearMars_ForceModel.SRP.SRPModel = Spherical;
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 TCM1;
GMAT TCM1.CoordinateSystem = Local;
GMAT TCM1.Origin = Earth;
GMAT TCM1.Axes = VNB;
GMAT TCM1.Element1 = 0;
GMAT TCM1.Element2 = 0;
GMAT TCM1.Element3 = 0;
GMAT TCM1.DecrementMass = false;
GMAT TCM1.Isp = 300;
GMAT TCM1.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 MarsFK5;
GMAT MarsFK5.Origin = Mars;
GMAT MarsFK5.Axes = MJ2000Eq;

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 DC;
GMAT DC.ShowProgress = true;
GMAT DC.ReportStyle = Normal;
GMAT DC.ReportFile = 'DifferentialCorrectorDC1.data';
GMAT DC.MaximumIterations = 25;
GMAT DC.DerivativeMethod = ForwardDifference;
GMAT DC.Algorithm = NewtonRaphson;

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

Create OrbitView EarthView;
GMAT EarthView.SolverIterations = Current;
GMAT EarthView.UpperLeft = [ 0.3258823529411765 0 ];
GMAT EarthView.Size = [ 0.5529411764705883 0.6870026525198939 ];
GMAT EarthView.RelativeZOrder = 778;
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.ShowLabels = true;
GMAT EarthView.ViewPointReference = Earth;
GMAT EarthView.ViewPointVector = [ -30000 20000 -5000 ];
GMAT EarthView.ViewDirection = Earth;
GMAT EarthView.ViewScaleFactor = 1;
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 = 3000;
GMAT EarthView.EnableStars = On;
GMAT EarthView.EnableConstellations = On;

Create OrbitView MarsView;
GMAT MarsView.SolverIterations = Current;
GMAT MarsView.UpperLeft = [ 0.3258823529411765 0.4549071618037135 ];
GMAT MarsView.Size = [ 0.3423529411764706 0.4549071618037135 ];
GMAT MarsView.RelativeZOrder = 784;
GMAT MarsView.Maximized = false;
GMAT MarsView.Add = {MAVEN, Mars};
GMAT MarsView.CoordinateSystem = MarsFK5;
GMAT MarsView.DrawObject = [ 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 = [ -10000 10000 10000 ];
GMAT MarsView.ViewDirection = Mars;
GMAT MarsView.ViewScaleFactor = 1.5;
GMAT MarsView.ViewUpCoordinateSystem = MarsFK5;
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 = 3000;
GMAT MarsView.EnableStars = On;
GMAT MarsView.EnableConstellations = On;

Create OrbitView SolarSystemView;
GMAT SolarSystemView.SolverIterations = Current;
GMAT SolarSystemView.UpperLeft = [ 0 0 ];
GMAT SolarSystemView.Size = [ 0 0 ];
GMAT SolarSystemView.RelativeZOrder = 0;
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 = false;
GMAT SolarSystemView.ShowLabels = true;
GMAT SolarSystemView.ViewPointReference = Luna;
GMAT SolarSystemView.ViewPointVector = [ 0 0 500000000 ];
GMAT SolarSystemView.ViewDirection = Sun;
GMAT SolarSystemView.ViewScaleFactor = 1;
GMAT SolarSystemView.ViewUpCoordinateSystem = SunEcliptic;
GMAT SolarSystemView.ViewUpAxis = X;
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 = 1000;
GMAT SolarSystemView.EnableStars = On;
GMAT SolarSystemView.EnableConstellations = On;

%----------------------------------------
%---------- Arrays, Variables, Strings
%----------------------------------------
Create Variable EarthSOI MarsSOI BdotT BdotR deltaV;
GMAT EarthSOI = 1000000;
GMAT MarsSOI = 577204;



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

BeginMissionSequence;

%  Target desired B-plane coordinates
Target DC {SolveMode = Solve, ExitMode = DiscardAndContinue, ShowProgressWindow = true};
  Vary 'Vary TOI.V' DC(TCM1.Element1 = 1e-005, {Perturbation = .00001, Lower = -9.999999e300, Upper = 9.999999e300, MaxStep = .002, AdditiveScaleFactor = 0.0, MultiplicativeScaleFactor = 1.0});
  Vary 'Vary TOI.N' DC(TCM1.Element2 = 1e-005, {Perturbation = .00001, Lower = -9.999999e300, Upper = 9.999999e300, MaxStep = .002, AdditiveScaleFactor = 0.0, MultiplicativeScaleFactor = 1.0});
  Vary 'Vary TOI.B' DC(TCM1.Element3 = 1e-005, {Perturbation = .00001, Lower = -9.999999e300, Upper = 9.999999e300, MaxStep = .002, AdditiveScaleFactor = 0.0, MultiplicativeScaleFactor = 1.0});
  Propagate 'Prop 3 Days' NearEarth(MAVEN) {MAVEN.ElapsedDays = 3, StopTolerance = 1e-005};
  Propagate 'Prop to TCM1' DeepSpace(MAVEN) {MAVEN.ElapsedDays = 12, StopTolerance = 1e-005};
  Maneuver 'Apply TCM1' TCM1(MAVEN);
  Propagate 'Prop 280 Days' DeepSpace(MAVEN) {MAVEN.ElapsedDays = 280};
  Propagate 'Prop to Mars Periapsis' NearMars(MAVEN) {MAVEN.Mars.Periapsis, MAVEN.ElapsedDays = 20};
  Achieve 'Achieve BdotT' DC(MAVEN.MarsInertial.BdotT = 2700, {Tolerance = .1});
  Achieve 'Achieve BdotR' DC(MAVEN.MarsInertial.BdotR = -7000, {Tolerance = .1});
EndTarget;  % For targeter DC

Target DC {SolveMode = Solve, ExitMode = DiscardAndContinue, ShowProgressWindow = true};
  Vary 'Vary MOI.V' DC(MOI.Element1 = -2, {Perturbation = .00001, Lower = -9.999999e300, Upper = 9.999999e300, MaxStep = .1, AdditiveScaleFactor = 0.0, MultiplicativeScaleFactor = 1.0});
  Maneuver 'Apply MOI' MOI(MAVEN);
  Propagate 'Prop to Mars Apoapsis' NearMars(MAVEN) {MAVEN.Mars.Apoapsis};
  Achieve 'Achieve RMAG' DC(MAVEN.Mars.RMAG = 12000, {Tolerance = .1});
EndTarget;  % For targeter DC

Propagate 'Prop 1 Day' NearMars(MAVEN) {MAVEN.ElapsedDays = 1};

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