Examples with DormandPrince853Integrator org.hipparchus.ode.nonstiff.DormandPrince853Integrator used on opensource projects

Example 36 with DormandPrince853Integrator

use of org.hipparchus.ode.nonstiff.DormandPrince853Integrator in project Orekit by CS-SI.

the class CloseEventsNumericalDP853Test method getPropagator.

/**
 * Create a propagator using the {@link #initialOrbit}.
 *
 * @param stepSize   of integrator.
 * @return a usable propagator.
 * @throws OrekitException
 */
public Propagator getPropagator(double stepSize) throws OrekitException {
    double[][] tol = NumericalPropagator.tolerances(1e-3, initialOrbit, OrbitType.CARTESIAN);
    final NumericalPropagator propagator = new NumericalPropagator(new DormandPrince853Integrator(stepSize, stepSize, tol[0], tol[1]));
    propagator.setInitialState(new SpacecraftState(initialOrbit));
    propagator.setOrbitType(OrbitType.CARTESIAN);
    return propagator;
}

Example 37 with DormandPrince853Integrator

use of org.hipparchus.ode.nonstiff.DormandPrince853Integrator in project Orekit by CS-SI.

the class DateDetectorTest method setUp.

@Before
public void setUp() {
    try {
        Utils.setDataRoot("regular-data");
        final double mu = 3.9860047e14;
        final Vector3D position = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
        final Vector3D velocity = new Vector3D(505.8479685, 942.7809215, 7435.922231);
        iniDate = new AbsoluteDate(1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
        iniOrbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), iniDate, mu);
        SpacecraftState initialState = new SpacecraftState(iniOrbit);
        double[] absTolerance = { 0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001 };
        double[] relTolerance = { 1.0e-7, 1.0e-4, 1.0e-4, 1.0e-7, 1.0e-7, 1.0e-7, 1.0e-7 };
        AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(0.001, 1000, absTolerance, relTolerance);
        integrator.setInitialStepSize(60);
        propagator = new NumericalPropagator(integrator);
        propagator.setInitialState(initialState);
        dt = 60.;
        maxCheck = 10.;
        threshold = 10.e-10;
        evtno = 0;
    } catch (OrekitException oe) {
        Assert.fail(oe.getLocalizedMessage());
    }
}

Example 38 with DormandPrince853Integrator

use of org.hipparchus.ode.nonstiff.DormandPrince853Integrator in project Orekit by CS-SI.

the class AlignmentDetectorTest method setUp.

@Before
public void setUp() {
    try {
        Utils.setDataRoot("regular-data");
        double mu = 3.9860047e14;
        final Vector3D position = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
        final Vector3D velocity = new Vector3D(505.8479685, 942.7809215, 7435.922231);
        iniDate = new AbsoluteDate(1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
        final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), iniDate, mu);
        initialState = new SpacecraftState(orbit);
        double[] absTolerance = { 0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001 };
        double[] relTolerance = { 1.0e-7, 1.0e-4, 1.0e-4, 1.0e-7, 1.0e-7, 1.0e-7, 1.0e-7 };
        AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(0.001, 1000, absTolerance, relTolerance);
        integrator.setInitialStepSize(60);
        propagator = new NumericalPropagator(integrator);
        propagator.setInitialState(initialState);
    } catch (OrekitException oe) {
        Assert.fail(oe.getLocalizedMessage());
    }
}

Example 39 with DormandPrince853Integrator

use of org.hipparchus.ode.nonstiff.DormandPrince853Integrator in project Orekit by CS-SI.

the class CloseEventsNumericalAMTest method getPropagator.

/**
 * Create a propagator using the {@link #initialOrbit}.
 *
 * @param stepSize   of integrator.
 * @return a usable propagator.
 * @throws OrekitException
 */
public Propagator getPropagator(double stepSize) throws OrekitException {
    double[][] tol = NumericalPropagator.tolerances(1, initialOrbit, OrbitType.CARTESIAN);
    final AdamsMoultonIntegrator integrator = new AdamsMoultonIntegrator(4, stepSize, stepSize, tol[0], tol[1]);
    final DormandPrince853Integrator starter = new DormandPrince853Integrator(stepSize / 100, stepSize / 10, tol[0], tol[1]);
    starter.setInitialStepSize(stepSize / 20);
    integrator.setStarterIntegrator(starter);
    final NumericalPropagator propagator = new NumericalPropagator(integrator);
    propagator.setInitialState(new SpacecraftState(initialOrbit));
    propagator.setOrbitType(OrbitType.CARTESIAN);
    return propagator;
}

Example 40 with DormandPrince853Integrator

use of org.hipparchus.ode.nonstiff.DormandPrince853Integrator in project Orekit by CS-SI.

the class EclipseDetectorTest method setUp.

@Before
public void setUp() {
    try {
        Utils.setDataRoot("regular-data");
        mu = 3.9860047e14;
        final Vector3D position = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
        final Vector3D velocity = new Vector3D(505.8479685, 942.7809215, 7435.922231);
        iniDate = new AbsoluteDate(1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
        final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getGCRF(), iniDate, mu);
        initialState = new SpacecraftState(orbit);
        double[] absTolerance = { 0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001 };
        double[] relTolerance = { 1.0e-7, 1.0e-4, 1.0e-4, 1.0e-7, 1.0e-7, 1.0e-7, 1.0e-7 };
        AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(0.001, 1000, absTolerance, relTolerance);
        integrator.setInitialStepSize(60);
        propagator = new NumericalPropagator(integrator);
        propagator.setInitialState(initialState);
        sun = CelestialBodyFactory.getSun();
        earth = CelestialBodyFactory.getEarth();
        sunRadius = 696000000.;
        earthRadius = 6400000.;
    } catch (OrekitException oe) {
        Assert.fail(oe.getLocalizedMessage());
    }
}