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

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

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

// 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 = 7200.e+3;
final double exc = 0.01;
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);

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

// 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);

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

//SPECIFIC
// Adding gravity field (8x8)
final ForceModel potentiel = EarthGravitationalModelFactory.getDroziner(GravityFieldNames.GRGS, "grim4s4_gr", 8, 8, true);

propagator.addForceModel(potentiel);
//SPECIFIC

// Propagating 1000s
final double dt = 1000.;
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");

}

}
</syntaxhighlight>

NumericalPropagationWithPotential 4.5.1 - Historique des versions

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

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