Example usage for org.apache.commons.math3.ode.nonstiff DormandPrince853Integrator DormandPrince853Integrator

Introduction

In this page you can find the example usage for org.apache.commons.math3.ode.nonstiff DormandPrince853Integrator DormandPrince853Integrator.

Prototype

public DormandPrince853Integrator(final double minStep, final double maxStep,
        final double[] vecAbsoluteTolerance, final double[] vecRelativeTolerance) 

Source Link

Document

Simple constructor.

Usage

From source file:org.orekit.propagation.events.AlignmentDetectorTest.java

@Before
public void setUp() {
    try {//from   www.  j a  v  a2  s . c o m
        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());
    }
}

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From source file:org.orekit.propagation.events.EclipseDetectorTest.java

@Before
public void setUp() {
    try {/*from w w  w . j  a  v a  2s. co  m*/
        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);
    } catch (OrekitException oe) {
        Assert.fail(oe.getLocalizedMessage());
    }
}

---

From source file:org.orekit.propagation.events.EventsLoggerTest.java

@Before
public void setUp() {
    try {//from  w w w  .j  a v a2s  . com
        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.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);
        count = 0;
        umbraDetector = buildDetector(true);
        penumbraDetector = buildDetector(false);
    } catch (OrekitException oe) {
        Assert.fail(oe.getLocalizedMessage());
    }
}

---

From source file:org.orekit.propagation.events.NodeDetectorTest.java

@Test
public void testIssue138() throws OrekitException {
    double a = 800000 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS;
    double e = 0.0001;
    double i = FastMath.toRadians(98);
    double w = -90;
    double raan = 0;
    double v = 0;
    Frame inertialFrame = FramesFactory.getEME2000();
    AbsoluteDate initialDate = new AbsoluteDate(2014, 01, 01, 0, 0, 0, TimeScalesFactory.getUTC());
    AbsoluteDate finalDate = initialDate.shiftedBy(5000);
    KeplerianOrbit initialOrbit = new KeplerianOrbit(a, e, i, w, raan, v, PositionAngle.TRUE, inertialFrame,
            initialDate, Constants.WGS84_EARTH_MU);
    SpacecraftState initialState = new SpacecraftState(initialOrbit, 1000);

    double[][] tol = NumericalPropagator.tolerances(10, initialOrbit, initialOrbit.getType());
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(0.001, 1000, tol[0], tol[1]);
    NumericalPropagator propagator = new NumericalPropagator(integrator);
    propagator.setInitialState(initialState);

    // Define 2 instances of NodeDetector:
    EventDetector rawDetector = new NodeDetector(1e-6, initialState.getOrbit(), initialState.getFrame())
            .withHandler(new ContinueOnEvent<NodeDetector>());

    EventsLogger logger1 = new EventsLogger();
    EventDetector node1 = logger1.monitorDetector(rawDetector);
    EventsLogger logger2 = new EventsLogger();
    EventDetector node2 = logger2.monitorDetector(rawDetector);

    propagator.addEventDetector(node1);/*from   w w w .  j  ava2 s  .  co m*/
    propagator.addEventDetector(node2);

    // First propagation
    propagator.setEphemerisMode();
    propagator.propagate(finalDate);
    Assert.assertEquals(2, logger1.getLoggedEvents().size());
    Assert.assertEquals(2, logger2.getLoggedEvents().size());
    logger1.clearLoggedEvents();
    logger2.clearLoggedEvents();

    BoundedPropagator postpro = propagator.getGeneratedEphemeris();

    // Post-processing
    postpro.addEventDetector(node1);
    postpro.addEventDetector(node2);
    postpro.propagate(finalDate);
    Assert.assertEquals(2, logger1.getLoggedEvents().size());
    Assert.assertEquals(2, logger2.getLoggedEvents().size());

}

---

From source file:org.orekit.propagation.integration.IntegratedEphemerisTest.java

@Test
public void testSerializationDSST()
        throws PropagationException, OrekitException, IOException, ClassNotFoundException {

    AbsoluteDate finalDate = initialOrbit.getDate().shiftedBy(Constants.JULIAN_DAY);
    final double[][] tol = DSSTPropagator.tolerances(1.0, initialOrbit);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(10, Constants.JULIAN_DAY, tol[0],
            tol[1]);//from  ww  w  .j a  va 2  s . co m
    DSSTPropagator dsstProp = new DSSTPropagator(integrator);
    dsstProp.setInitialState(new SpacecraftState(initialOrbit), false);
    dsstProp.setEphemerisMode();
    dsstProp.propagate(finalDate);
    IntegratedEphemeris ephemeris = (IntegratedEphemeris) dsstProp.getGeneratedEphemeris();

    ByteArrayOutputStream bos = new ByteArrayOutputStream();
    ObjectOutputStream oos = new ObjectOutputStream(bos);
    oos.writeObject(ephemeris);

    Assert.assertTrue(bos.size() > 8000);
    Assert.assertTrue(bos.size() < 9000);

    Assert.assertNotNull(ephemeris.getFrame());
    Assert.assertSame(ephemeris.getFrame(), dsstProp.getFrame());
    ByteArrayInputStream bis = new ByteArrayInputStream(bos.toByteArray());
    ObjectInputStream ois = new ObjectInputStream(bis);
    IntegratedEphemeris deserialized = (IntegratedEphemeris) ois.readObject();
    Assert.assertEquals(deserialized.getMinDate(), deserialized.getMinDate());
    Assert.assertEquals(deserialized.getMaxDate(), deserialized.getMaxDate());

}

---

From source file:org.orekit.propagation.integration.IntegratedEphemerisTest.java

@Test(expected = NotSerializableException.class)
public void testSerializationDSSTNotSerializableForceModel()
        throws PropagationException, OrekitException, IOException, ClassNotFoundException {

    AbsoluteDate finalDate = initialOrbit.getDate().shiftedBy(Constants.JULIAN_DAY);
    final double[][] tol = DSSTPropagator.tolerances(1.0, initialOrbit);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(10, Constants.JULIAN_DAY, tol[0],
            tol[1]);//  w  w  w  . j a va  2  s. co m
    DSSTPropagator dsstProp = new DSSTPropagator(integrator);
    dsstProp.setInitialState(new SpacecraftState(initialOrbit), false);

    // set up a dummy not serializable force model
    dsstProp.addForceModel(new DSSTForceModel() {

        public void initializeStep(AuxiliaryElements aux) {
        }

        public void initialize(AuxiliaryElements aux, boolean meanOnly) {
        }

        public double[] getShortPeriodicVariations(AbsoluteDate date, double[] meanElements) {
            return new double[6];
        }

        public double[] getMeanElementRate(SpacecraftState state) {
            return new double[6];
        }

        public EventDetector[] getEventsDetectors() {
            return null;
        }

        @Override
        public void registerAttitudeProvider(AttitudeProvider provider) {
        }

        public void computeShortPeriodicsCoefficients(SpacecraftState state) {
        }

        @Override
        public void resetShortPeriodicsCoefficients() {
        }
    });

    dsstProp.setEphemerisMode();
    dsstProp.propagate(finalDate);
    IntegratedEphemeris ephemeris = (IntegratedEphemeris) dsstProp.getGeneratedEphemeris();

    ByteArrayOutputStream bos = new ByteArrayOutputStream();
    ObjectOutputStream oos = new ObjectOutputStream(bos);
    oos.writeObject(ephemeris);

}

---

From source file:org.orekit.propagation.integration.IntegratedEphemerisTest.java

@Before
public void setUp() {
    // Definition of initial conditions with position and velocity
    Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6);
    Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);
    double mu = 3.9860047e14;

    AbsoluteDate initDate = AbsoluteDate.J2000_EPOCH.shiftedBy(584.);
    initialOrbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(),
            initDate, mu);/*  ww w .  j  av  a 2s  . c  o  m*/

    // Numerical propagator definition
    double[] absTolerance = { 0.0001, 1.0e-11, 1.0e-11, 1.0e-8, 1.0e-8, 1.0e-8, 0.001 };
    double[] relTolerance = { 1.0e-8, 1.0e-8, 1.0e-8, 1.0e-9, 1.0e-9, 1.0e-9, 1.0e-7 };
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(0.001, 500, absTolerance,
            relTolerance);
    integrator.setInitialStepSize(100);
    numericalPropagator = new NumericalPropagator(integrator);

}

---

From source file:org.orekit.propagation.numerical.NumericalPropagatorTest.java

@Test
public void testEphemerisDates() throws OrekitException {
    //setup//  w ww  . j  a v  a 2 s  .  co m
    TimeScale tai = TimeScalesFactory.getTAI();
    AbsoluteDate initialDate = new AbsoluteDate("2015-07-01", tai);
    AbsoluteDate startDate = new AbsoluteDate("2015-07-03", tai).shiftedBy(-0.1);
    AbsoluteDate endDate = new AbsoluteDate("2015-07-04", tai);
    Frame eci = FramesFactory.getGCRF();
    KeplerianOrbit orbit = new KeplerianOrbit(600e3 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS, 0, 0, 0, 0, 0,
            PositionAngle.TRUE, eci, initialDate, mu);
    double[][] tol = NumericalPropagator.tolerances(1, orbit, OrbitType.CARTESIAN);
    Propagator prop = new NumericalPropagator(new DormandPrince853Integrator(0.1, 500, tol[0], tol[1]));
    prop.resetInitialState(new SpacecraftState(new CartesianOrbit(orbit)));

    //action
    prop.setEphemerisMode();
    prop.propagate(startDate, endDate);
    BoundedPropagator ephemeris = prop.getGeneratedEphemeris();

    //verify
    TimeStampedPVCoordinates actualPV = ephemeris.getPVCoordinates(startDate, eci);
    TimeStampedPVCoordinates expectedPV = orbit.getPVCoordinates(startDate, eci);
    MatcherAssert.assertThat(actualPV.getPosition(),
            OrekitMatchers.vectorCloseTo(expectedPV.getPosition(), 1.0));
    MatcherAssert.assertThat(actualPV.getVelocity(),
            OrekitMatchers.vectorCloseTo(expectedPV.getVelocity(), 1.0));
    MatcherAssert.assertThat(ephemeris.getMinDate().durationFrom(startDate), OrekitMatchers.closeTo(0, 0));
    MatcherAssert.assertThat(ephemeris.getMaxDate().durationFrom(endDate), OrekitMatchers.closeTo(0, 0));
    //test date
    AbsoluteDate date = endDate.shiftedBy(-0.11);
    Assert.assertEquals(ephemeris.propagate(date).getDate().durationFrom(date), 0, 0);
}

---

From source file:org.orekit.propagation.numerical.NumericalPropagatorTest.java

@Test
public void testEphemerisDatesBackward() throws OrekitException {
    //setup/* w w w.  j a  v  a 2  s .c  o  m*/
    TimeScale tai = TimeScalesFactory.getTAI();
    AbsoluteDate initialDate = new AbsoluteDate("2015-07-05", tai);
    AbsoluteDate startDate = new AbsoluteDate("2015-07-03", tai).shiftedBy(-0.1);
    AbsoluteDate endDate = new AbsoluteDate("2015-07-04", tai);
    Frame eci = FramesFactory.getGCRF();
    KeplerianOrbit orbit = new KeplerianOrbit(600e3 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS, 0, 0, 0, 0, 0,
            PositionAngle.TRUE, eci, initialDate, mu);
    double[][] tol = NumericalPropagator.tolerances(1, orbit, OrbitType.CARTESIAN);
    Propagator prop = new NumericalPropagator(new DormandPrince853Integrator(0.1, 500, tol[0], tol[1]));
    prop.resetInitialState(new SpacecraftState(new CartesianOrbit(orbit)));

    //action
    prop.setEphemerisMode();
    prop.propagate(endDate, startDate);
    BoundedPropagator ephemeris = prop.getGeneratedEphemeris();

    //verify
    TimeStampedPVCoordinates actualPV = ephemeris.getPVCoordinates(startDate, eci);
    TimeStampedPVCoordinates expectedPV = orbit.getPVCoordinates(startDate, eci);
    MatcherAssert.assertThat(actualPV.getPosition(),
            OrekitMatchers.vectorCloseTo(expectedPV.getPosition(), 1.0));
    MatcherAssert.assertThat(actualPV.getVelocity(),
            OrekitMatchers.vectorCloseTo(expectedPV.getVelocity(), 1.0));
    MatcherAssert.assertThat(ephemeris.getMinDate().durationFrom(startDate), OrekitMatchers.closeTo(0, 0));
    MatcherAssert.assertThat(ephemeris.getMaxDate().durationFrom(endDate), OrekitMatchers.closeTo(0, 0));
    //test date
    AbsoluteDate date = endDate.shiftedBy(-0.11);
    Assert.assertEquals(ephemeris.propagate(date).getDate().durationFrom(date), 0, 0);
}

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From source file:org.orekit.propagation.numerical.NumericalPropagatorTest.java

private PVCoordinates propagateInType(SpacecraftState state, double dP, OrbitType type, PositionAngle angle)
        throws PropagationException {

    final double dt = 3200;
    final double minStep = 0.001;
    final double maxStep = 1000;

    double[][] tol = NumericalPropagator.tolerances(dP, state.getOrbit(), type);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(minStep, maxStep, tol[0], tol[1]);
    NumericalPropagator newPropagator = new NumericalPropagator(integrator);
    newPropagator.setOrbitType(type);//from   www  .  jav a2 s .  c o m
    newPropagator.setPositionAngleType(angle);
    newPropagator.setInitialState(state);
    for (ForceModel force : propagator.getForceModels()) {
        newPropagator.addForceModel(force);
    }
    return newPropagator.propagate(state.getDate().shiftedBy(dt)).getPVCoordinates();

}

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