Admin le 15 novembre 2022 à 08:40

2022-11-15T08:40:27Z

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	final Frame ITRF = FramesFactory.getITRF();		final Frame ITRF = FramesFactory.getITRF();
	final double AE = Constants.WGS84_EARTH_EQUATORIAL_RADIUS;		final double AE = Constants.WGS84_EARTH_EQUATORIAL_RADIUS;
	final BodyShape EARTH = new ~~ExtendedOneAxisEllipsoid~~(AE, Constants.WGS84_EARTH_FLATTENING, ITRF, "EARTH");		final BodyShape EARTH = new OneAxisEllipsoid(AE, Constants.WGS84_EARTH_FLATTENING, ITRF, "EARTH");

	// Adding atmospheric forces using MSISE2000 model		// Adding atmospheric forces using MSISE2000 model

Admin le 10 novembre 2022 à 10:39

2022-11-10T10:39:08Z

← Version précédente		Version du 10 novembre 2022 à 10:39
Ligne 80 :		Ligne 80 :
	final Frame ITRF = FramesFactory.getITRF();		final Frame ITRF = FramesFactory.getITRF();
	final double AE = Constants.WGS84_EARTH_EQUATORIAL_RADIUS;		final double AE = Constants.WGS84_EARTH_EQUATORIAL_RADIUS;
	final ~~GeometricBodyShape~~ EARTH = new ExtendedOneAxisEllipsoid(AE, Constants.WGS84_EARTH_FLATTENING, ITRF, "EARTH");		final BodyShape EARTH = new ExtendedOneAxisEllipsoid(AE, Constants.WGS84_EARTH_FLATTENING, ITRF, "EARTH");

	// Adding atmospheric forces using MSISE2000 model		// Adding atmospheric forces using MSISE2000 model

Admin : Page créée avec « public class NumericalPropagationWithLiftAndDragAndMSISE2000 { public static void main(String[] args) throws PatriusException, IOExcepti... »

2018-02-13T10:28:59Z

Page créée avec « <syntaxhighlight lang="java"> public class NumericalPropagationWithLiftAndDragAndMSISE2000 { public static void main(String[] args) throws PatriusException, IOExcepti... »

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<syntaxhighlight lang="java">
public class NumericalPropagationWithLiftAndDragAndMSISE2000 {

public static void main(String[] args) throws PatriusException, IOException, ParseException {

// Patrius Dataset initialization (needed for example to get the UTC time
PatriusDataset.addResourcesFromPatriusDataset() ;

// Recovery of the UTC time scale using a "factory" (not to duplicate such unique object)
final TimeScale TUC = TimeScalesFactory.getUTC();

// Date of the orbit given in UTC time scale)
final AbsoluteDate date = new AbsoluteDate("2010-01-01T12:00:00.000", TUC);

// Getting the frame with wich will defined the orbit parameters
// As for time scale, we will use also a "factory".
final Frame GCRF = FramesFactory.getGCRF();

// Initial orbit
final double sma = 6600.e+3;
final double exc = 0.;
final double per = sma*(1.-exc);
final double apo = sma*(1.+exc);
final double inc = FastMath.toRadians(98.);
final double pa = FastMath.toRadians(0.);
final double raan = FastMath.toRadians(0.);
final double anm = FastMath.toRadians(0.);
final double MU = Constants.WGS84_EARTH_MU;

final ApsisRadiusParameters par = new ApsisRadiusParameters(per, apo, inc, pa, raan, anm, PositionAngle.MEAN, MU);
final Orbit iniOrbit = new ApsisOrbit(par, GCRF, date);

// Mass model using an Assembly

final AssemblyBuilder builder = new AssemblyBuilder();

// Initial mass (mandatory to take into account mass for atmospheric force computation)
final double dryMass = 100.;
builder.addMainPart("MAIN");
builder.addProperty(new MassProperty(dryMass), "MAIN");

//SPECIFIC
// Adding the AeroGSphere property for drag only
final double cd = 2.0;
final double cl = 0.2;
final double sref = 10.;
//builder.addProperty(new AeroGlobalProperty(cd, cl, new ConstantFunction(sref)), "MAIN");
builder.addProperty(new AeroGlobalProperty(cd, cl, new Sphere(Vector3D.ZERO, FastMath.sqrt(sref/FastMath.PI))), "MAIN");

final UpdatableFrame mainFrame = new UpdatableFrame(GCRF, Transform.IDENTITY, "mainPartFrame");
builder.initMainPartFrame(mainFrame);
//SPECIFIC

final Assembly assembly = builder.returnAssembly();
final MassProvider mm = new MassModel(assembly);

// We create a spacecratftstate
final SpacecraftState iniState = new SpacecraftState(iniOrbit, mm);

// Initialization of the Runge Kutta integrator with a 2 s step
final double pasRk = 2.;
final FirstOrderIntegrator integrator = new ClassicalRungeKuttaIntegrator(pasRk);

// Initialization of the propagator
final NumericalPropagator propagator = new NumericalPropagator(integrator);
propagator.resetInitialState(iniState);

// Adding additional state (change name add to set for V3.3)
propagator.setMassProviderEquation(mm);

// Forcing integration using cartesian equations
propagator.setOrbitType(OrbitType.CARTESIAN);

//SPECIFIC
// Adding an attitude law
final AttitudeLaw attitudeLaw = new LofOffset(LOFType.LVLH, RotationOrder.ZYX, 0., 0., 0.);
propagator.setAttitudeProvider(attitudeLaw);

// Definition of the Earth ellipsoid for later atmospheric density computation
final Frame ITRF = FramesFactory.getITRF();
final double AE = Constants.WGS84_EARTH_EQUATORIAL_RADIUS;
final GeometricBodyShape EARTH = new ExtendedOneAxisEllipsoid(AE, Constants.WGS84_EARTH_FLATTENING, ITRF, "EARTH");

// Adding atmospheric forces using MSISE2000 model
SolarActivityDataProvider solarProvider = new ConstantSolarActivity(100, 15);
final MSISE2000InputParameters data = new ClassicalMSISE2000SolarData(solarProvider);
CelestialBody sunBody = CelestialBodyFactory.getSun();
final Atmosphere atmosphere = new MSISE2000(data, EARTH, sunBody);

final DragLiftModel dragLiftModel = new DragLiftModel(assembly);
final ForceModel atm = new DragForce(atmosphere, dragLiftModel);
propagator.addForceModel(atm);
//SPECIFIC

// Propagating 5 periods
final double dt = 5.*iniOrbit.getKeplerianPeriod();
final AbsoluteDate finalDate = date.shiftedBy(dt);
final SpacecraftState finalState = propagator.propagate(finalDate);
final Orbit finalOrbit = finalState.getOrbit();

// Printing new date and semi major axis
System.out.println();
System.out.println("Initial semi major axis = "+iniOrbit.getA()/1000.+" km");
System.out.println("New date = "+finalOrbit.getDate().toString(TUC)+" deg");
System.out.println("Final semi major axis = "+finalOrbit.getA()/1000.+" km");
// Printing mass
System.out.println();
System.out.println("Mass = "+finalState.getMass("MAIN")+" kg");

}

}
</syntaxhighlight>

NumericalPropagationWithLiftAndDragAndMSISE2000 - Historique des versions

Admin le 15 novembre 2022 à 08:40

Admin le 10 novembre 2022 à 10:39

Admin : Page créée avec « public class NumericalPropagationWithLiftAndDragAndMSISE2000 { public static void main(String[] args) throws PatriusException, IOExcepti... »

Admin : Page créée avec « public class NumericalPropagationWithLiftAndDragAndMSISE2000 { public static void main(String[] args) throws PatriusException, IOExcepti... »