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.forces.gravity.CunninghamAttractionModelTest.java

private BoundedPropagator createEphemeris(double dP, SpacecraftState initialState, double duration,
        UnnormalizedSphericalHarmonicsProvider provider) throws OrekitException {
    double[][] tol = NumericalPropagator.tolerances(dP, initialState.getOrbit(), OrbitType.CARTESIAN);
    AbstractIntegrator integrator = new DormandPrince853Integrator(0.001, 120.0, tol[0], tol[1]);
    NumericalPropagator propagator = new NumericalPropagator(integrator);
    propagator.setEphemerisMode();/*w  ww.ja va  2  s.  c o  m*/
    propagator.setOrbitType(OrbitType.CARTESIAN);
    propagator.addForceModel(
            new CunninghamAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), provider));
    propagator.setInitialState(initialState);
    propagator.propagate(initialState.getDate().shiftedBy(duration));
    return propagator.getGeneratedEphemeris();
}

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From source file:org.orekit.forces.gravity.CunninghamAttractionModelTest.java

@Test
public void testStateJacobian() throws OrekitException {

    Utils.setDataRoot("regular-data:potential/grgs-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));

    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2000, 07, 01), new TimeComponents(13, 59, 27.816),
            TimeScalesFactory.getUTC());
    double i = FastMath.toRadians(98.7);
    double omega = FastMath.toRadians(93.0);
    double OMEGA = FastMath.toRadians(15.0 * 22.5);
    Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i, omega, OMEGA, 0, PositionAngle.MEAN,
            FramesFactory.getEME2000(), date, mu);
    OrbitType integrationType = OrbitType.CARTESIAN;
    double[][] tolerances = NumericalPropagator.tolerances(0.01, orbit, integrationType);

    propagator = new NumericalPropagator(
            new DormandPrince853Integrator(1.0e-3, 120, tolerances[0], tolerances[1]));
    propagator.setOrbitType(integrationType);
    CunninghamAttractionModel cuModel = new CunninghamAttractionModel(itrf2008,
            GravityFieldFactory.getUnnormalizedProvider(50, 50));
    Assert.assertEquals(TideSystem.UNKNOWN, cuModel.getTideSystem());
    propagator.addForceModel(cuModel);//from ww w .  j a va  2s.  c o m
    SpacecraftState state0 = new SpacecraftState(orbit);
    propagator.setInitialState(state0);
    try {
        DerivativeStructure one = new DerivativeStructure(7, 1, 1.0);
        cuModel.accelerationDerivatives(state0.getDate(), state0.getFrame(),
                new FieldVector3D<DerivativeStructure>(one, state0.getPVCoordinates().getPosition()),
                new FieldVector3D<DerivativeStructure>(one, state0.getPVCoordinates().getVelocity()),
                new FieldRotation<DerivativeStructure>(one.multiply(state0.getAttitude().getRotation().getQ0()),
                        one.multiply(state0.getAttitude().getRotation().getQ1()),
                        one.multiply(state0.getAttitude().getRotation().getQ2()),
                        one.multiply(state0.getAttitude().getRotation().getQ3()), false),
                one.multiply(state0.getMass()));
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.STEPS_NOT_INITIALIZED_FOR_FINITE_DIFFERENCES, oe.getSpecifier());
    }
    cuModel.setSteps(1.0, 1.0e10);

    checkStateJacobian(propagator, state0, date.shiftedBy(3.5 * 3600.0), 40000, tolerances[0], 2.0e-7);
}

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From source file:org.orekit.forces.gravity.CunninghamAttractionModelTest.java

@Before
public void setUp() {
    itrf2008 = null;//from  www.j a v a2  s.  c  o  m
    propagator = null;
    Utils.setDataRoot("regular-data");
    try {
        // Eigen c1 model truncated to degree 6
        mu = 3.986004415e+14;
        ae = 6378136.460;
        c20 = -1.08262631303e-3;
        c30 = 2.53248017972e-6;
        c40 = 1.61994537014e-6;
        c50 = 2.27888264414e-7;
        c60 = -5.40618601332e-7;

        itrf2008 = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
        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);
    } catch (OrekitException oe) {
        Assert.fail(oe.getMessage());
    }
}

---

From source file:org.orekit.forces.gravity.DrozinerAttractionModelTest.java

@Test
public void testStateJacobian() throws OrekitException {

    Utils.setDataRoot("regular-data:potential/grgs-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));

    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2000, 07, 01), new TimeComponents(13, 59, 27.816),
            TimeScalesFactory.getUTC());
    double i = FastMath.toRadians(98.7);
    double omega = FastMath.toRadians(93.0);
    double OMEGA = FastMath.toRadians(15.0 * 22.5);
    Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i, omega, OMEGA, 0, PositionAngle.MEAN,
            FramesFactory.getEME2000(), date, mu);
    OrbitType integrationType = OrbitType.CARTESIAN;
    double[][] tolerances = NumericalPropagator.tolerances(0.01, orbit, integrationType);

    propagator = new NumericalPropagator(
            new DormandPrince853Integrator(1.0e-3, 120, tolerances[0], tolerances[1]));
    propagator.setOrbitType(integrationType);
    DrozinerAttractionModel drModel = new DrozinerAttractionModel(itrf2008,
            GravityFieldFactory.getUnnormalizedProvider(50, 50));
    Assert.assertEquals(TideSystem.UNKNOWN, drModel.getTideSystem());
    propagator.addForceModel(drModel);/*from  w  w  w. j a v  a  2 s . c  o  m*/
    SpacecraftState state0 = new SpacecraftState(orbit);
    propagator.setInitialState(state0);
    try {
        DerivativeStructure one = new DerivativeStructure(7, 1, 1.0);
        drModel.accelerationDerivatives(state0.getDate(), state0.getFrame(),
                new FieldVector3D<DerivativeStructure>(one, state0.getPVCoordinates().getPosition()),
                new FieldVector3D<DerivativeStructure>(one, state0.getPVCoordinates().getVelocity()),
                new FieldRotation<DerivativeStructure>(one.multiply(state0.getAttitude().getRotation().getQ0()),
                        one.multiply(state0.getAttitude().getRotation().getQ1()),
                        one.multiply(state0.getAttitude().getRotation().getQ2()),
                        one.multiply(state0.getAttitude().getRotation().getQ3()), false),
                one.multiply(state0.getMass()));
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.STEPS_NOT_INITIALIZED_FOR_FINITE_DIFFERENCES, oe.getSpecifier());
    }
    drModel.setSteps(1.0, 1.0e10);

    checkStateJacobian(propagator, state0, date.shiftedBy(3.5 * 3600.0), 40000, tolerances[0], 2.0e-7);

}

---

From source file:org.orekit.forces.gravity.DrozinerAttractionModelTest.java

@Before
public void setUp() {
    itrf2008 = null;//from  ww w. j av a 2 s.  c o m
    propagator = null;
    Utils.setDataRoot("regular-data");
    try {
        mu = 3.986004415e+14;
        ae = 6378136.460;
        c20 = -1.08262631303e-3;
        c30 = 2.53248017972e-6;
        c40 = 1.61994537014e-6;
        c50 = 2.27888264414e-7;
        c60 = -5.40618601332e-7;
        itrf2008 = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
        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);

    } catch (OrekitException oe) {
        Assert.fail(oe.getMessage());
    }
}

---

From source file:org.orekit.forces.gravity.HolmesFeatherstoneAttractionModelTest.java

@Test
public void testCompleteWithCunninghamReference() throws OrekitException {

    Utils.setDataRoot("regular-data:potential/grgs-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));

    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2000, 07, 01), new TimeComponents(13, 59, 27.816),
            TimeScalesFactory.getUTC());
    double i = FastMath.toRadians(98.7);
    double omega = FastMath.toRadians(93.0);
    double OMEGA = FastMath.toRadians(15.0 * 22.5);
    Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i, omega, OMEGA, 0, PositionAngle.MEAN,
            FramesFactory.getEME2000(), date, mu);
    double[][] tolerances = NumericalPropagator.tolerances(0.01, orbit, OrbitType.CARTESIAN);
    AbsoluteDate targetDate = date.shiftedBy(3 * Constants.JULIAN_DAY);

    propagator = new NumericalPropagator(
            new DormandPrince853Integrator(1.0e-3, 120, tolerances[0], tolerances[1]));
    propagator.setOrbitType(OrbitType.CARTESIAN);
    propagator.addForceModel(/*from ww  w  .  j a  v a  2  s  .  c  om*/
            new HolmesFeatherstoneAttractionModel(itrf, GravityFieldFactory.getNormalizedProvider(69, 69)));

    propagator.setInitialState(new SpacecraftState(orbit));
    SpacecraftState hfOrb = propagator.propagate(targetDate);

    propagator.removeForceModels();

    propagator.addForceModel(
            new CunninghamAttractionModel(itrf, GravityFieldFactory.getUnnormalizedProvider(69, 69)));

    propagator.setInitialState(new SpacecraftState(orbit));
    SpacecraftState cOrb = propagator.propagate(targetDate);

    Vector3D dif = hfOrb.getPVCoordinates().getPosition().subtract(cOrb.getPVCoordinates().getPosition());
    Assert.assertEquals(0, dif.getNorm(), 4e-5);
}

---

From source file:org.orekit.forces.gravity.HolmesFeatherstoneAttractionModelTest.java

private BoundedPropagator createEphemeris(double dP, SpacecraftState initialState, double duration,
        NormalizedSphericalHarmonicsProvider provider) throws OrekitException {
    double[][] tol = NumericalPropagator.tolerances(dP, initialState.getOrbit(), OrbitType.CARTESIAN);
    AbstractIntegrator integrator = new DormandPrince853Integrator(0.001, 120.0, tol[0], tol[1]);
    NumericalPropagator propagator = new NumericalPropagator(integrator);
    propagator.setEphemerisMode();/*  www  . java  2  s  . com*/
    propagator.setOrbitType(OrbitType.CARTESIAN);
    propagator.addForceModel(new HolmesFeatherstoneAttractionModel(
            FramesFactory.getITRF(IERSConventions.IERS_2010, true), provider));
    propagator.setInitialState(initialState);
    propagator.propagate(initialState.getDate().shiftedBy(duration));
    return propagator.getGeneratedEphemeris();
}

---

From source file:org.orekit.forces.gravity.HolmesFeatherstoneAttractionModelTest.java

@Test
public void testStateJacobian() throws OrekitException {

    Utils.setDataRoot("regular-data:potential/grgs-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));

    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2000, 07, 01), new TimeComponents(13, 59, 27.816),
            TimeScalesFactory.getUTC());
    double i = FastMath.toRadians(98.7);
    double omega = FastMath.toRadians(93.0);
    double OMEGA = FastMath.toRadians(15.0 * 22.5);
    Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i, omega, OMEGA, 0, PositionAngle.MEAN,
            FramesFactory.getEME2000(), date, mu);
    OrbitType integrationType = OrbitType.CARTESIAN;
    double[][] tolerances = NumericalPropagator.tolerances(0.01, orbit, integrationType);

    propagator = new NumericalPropagator(
            new DormandPrince853Integrator(1.0e-3, 120, tolerances[0], tolerances[1]));
    propagator.setOrbitType(integrationType);
    HolmesFeatherstoneAttractionModel hfModel = new HolmesFeatherstoneAttractionModel(itrf,
            GravityFieldFactory.getNormalizedProvider(50, 50));
    Assert.assertEquals(TideSystem.UNKNOWN, hfModel.getTideSystem());
    propagator.addForceModel(hfModel);/*from  w w  w.  j a  va 2 s .  c  o m*/
    SpacecraftState state0 = new SpacecraftState(orbit);
    propagator.setInitialState(state0);

    checkStateJacobian(propagator, state0, date.shiftedBy(3.5 * 3600.0), 50000, tolerances[0], 7.0e-10);
}

---

From source file:org.orekit.forces.gravity.HolmesFeatherstoneAttractionModelTest.java

@Before
public void setUp() {
    itrf = null;/*from w w  w.j a  v a2 s . c  om*/
    propagator = null;
    Utils.setDataRoot("regular-data");
    try {
        // Eigen 6s model truncated to degree 6
        mu = 3.986004415e+14;
        ae = 6378136.460;
        normalizedC20 = -4.84165299820e-04;
        normalizedC30 = 9.57211326674e-07;
        normalizedC40 = 5.39990167207e-07;
        normalizedC50 = 6.86846073356e-08;
        normalizedC60 = -1.49953256913e-07;
        unnormalizedC20 = FastMath.sqrt(5) * normalizedC20;
        unnormalizedC30 = FastMath.sqrt(7) * normalizedC30;
        unnormalizedC40 = FastMath.sqrt(9) * normalizedC40;
        unnormalizedC50 = FastMath.sqrt(11) * normalizedC50;
        unnormalizedC60 = FastMath.sqrt(13) * normalizedC60;

        itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
        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);
    } catch (OrekitException oe) {
        Assert.fail(oe.getMessage());
    }
}

---

From source file:org.orekit.forces.gravity.OceanTidesTest.java

private SpacecraftState propagate(Orbit orbit, AbsoluteDate target, ForceModel... forceModels)
        throws OrekitException {
    double[][] tolerances = NumericalPropagator.tolerances(10, orbit, OrbitType.KEPLERIAN);
    AbstractIntegrator integrator = new DormandPrince853Integrator(1.0e-3, 300, tolerances[0], tolerances[1]);
    NumericalPropagator propagator = new NumericalPropagator(integrator);
    for (ForceModel forceModel : forceModels) {
        propagator.addForceModel(forceModel);
    }//  w  ww .  ja  v a2 s  . c  o m
    propagator.setInitialState(new SpacecraftState(orbit));
    return propagator.propagate(target);
}

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