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

Example 66 with DormandPrince853Integrator

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

the class DSSTPropagatorTest method testShortPeriodCoefficients.

@Test
public void testShortPeriodCoefficients() throws OrekitException {
    Utils.setDataRoot("regular-data:potential/icgem-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new ICGEMFormatReader("^eigen-6s-truncated$", false));
    UnnormalizedSphericalHarmonicsProvider nshp = GravityFieldFactory.getUnnormalizedProvider(4, 4);
    Orbit orbit = new KeplerianOrbit(13378000, 0.05, 0, 0, FastMath.PI, 0, PositionAngle.MEAN, FramesFactory.getTOD(false), new AbsoluteDate(2003, 5, 6, TimeScalesFactory.getUTC()), nshp.getMu());
    double period = orbit.getKeplerianPeriod();
    double[][] tolerance = DSSTPropagator.tolerances(1.0, orbit);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(period / 100, period * 100, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(10 * period);
    DSSTPropagator propagator = new DSSTPropagator(integrator, false);
    OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getGTOD(false));
    CelestialBody sun = CelestialBodyFactory.getSun();
    CelestialBody moon = CelestialBodyFactory.getMoon();
    propagator.addForceModel(new DSSTZonal(nshp, 4, 3, 9));
    propagator.addForceModel(new DSSTTesseral(earth.getBodyFrame(), Constants.WGS84_EARTH_ANGULAR_VELOCITY, nshp, 4, 4, 4, 8, 4, 4, 2));
    propagator.addForceModel(new DSSTThirdBody(sun));
    propagator.addForceModel(new DSSTThirdBody(moon));
    propagator.addForceModel(new DSSTAtmosphericDrag(new HarrisPriester(sun, earth), 2.1, 180));
    propagator.addForceModel(new DSSTSolarRadiationPressure(1.2, 180, sun, earth.getEquatorialRadius()));
    final AbsoluteDate finalDate = orbit.getDate().shiftedBy(30 * Constants.JULIAN_DAY);
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateNoConfig = propagator.propagate(finalDate);
    Assert.assertEquals(0, stateNoConfig.getAdditionalStates().size());
    propagator.setSelectedCoefficients(new HashSet<String>());
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateConfigEmpty = propagator.propagate(finalDate);
    Assert.assertEquals(234, stateConfigEmpty.getAdditionalStates().size());
    final Set<String> selected = new HashSet<String>();
    selected.add("DSST-3rd-body-Moon-s[7]");
    selected.add("DSST-central-body-tesseral-c[-2][3]");
    propagator.setSelectedCoefficients(selected);
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateConfigeSelected = propagator.propagate(finalDate);
    Assert.assertEquals(selected.size(), stateConfigeSelected.getAdditionalStates().size());
    propagator.setSelectedCoefficients(null);
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateConfigNull = propagator.propagate(finalDate);
    Assert.assertEquals(0, stateConfigNull.getAdditionalStates().size());
}

Example 67 with DormandPrince853Integrator

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

the class DSSTPropagatorTest method getLEOStatePropagatedBy30Minutes.

private SpacecraftState getLEOStatePropagatedBy30Minutes() throws IllegalArgumentException, OrekitException {
    final Vector3D position = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
    final Vector3D velocity = new Vector3D(505.8479685, 942.7809215, 7435.922231);
    // Spring equinoxe 21st mars 2003 1h00m
    final AbsoluteDate initialDate = new AbsoluteDate(new DateComponents(2003, 03, 21), new TimeComponents(1, 0, 0.), TimeScalesFactory.getUTC());
    final CartesianOrbit osculatingOrbit = new CartesianOrbit(new PVCoordinates(position, velocity), FramesFactory.getTOD(IERSConventions.IERS_1996, false), initialDate, Constants.WGS84_EARTH_MU);
    // Adaptive step integrator
    // with a minimum step of 0.001 and a maximum step of 1000
    double minStep = 0.001;
    double maxstep = 1000.0;
    double positionTolerance = 10.0;
    OrbitType propagationType = OrbitType.EQUINOCTIAL;
    double[][] tolerances = NumericalPropagator.tolerances(positionTolerance, osculatingOrbit, propagationType);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(minStep, maxstep, tolerances[0], tolerances[1]);
    NumericalPropagator propagator = new NumericalPropagator(integrator);
    propagator.setOrbitType(propagationType);
    NormalizedSphericalHarmonicsProvider provider = GravityFieldFactory.getNormalizedProvider(5, 5);
    ForceModel holmesFeatherstone = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), provider);
    propagator.addForceModel(holmesFeatherstone);
    propagator.setInitialState(new SpacecraftState(osculatingOrbit));
    return propagator.propagate(new AbsoluteDate(initialDate, 1800.));
}

Example 68 with DormandPrince853Integrator

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

the class DSSTPropagatorTest method testGetInitialOsculatingState.

@Test
public void testGetInitialOsculatingState() throws IllegalArgumentException, OrekitException {
    final SpacecraftState initialState = getGEOState();
    // build integrator
    final double minStep = initialState.getKeplerianPeriod() * 0.1;
    final double maxStep = initialState.getKeplerianPeriod() * 10.0;
    final double[][] tol = DSSTPropagator.tolerances(0.1, initialState.getOrbit());
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(minStep, maxStep, tol[0], tol[1]);
    // build the propagator for the propagation of the mean elements
    DSSTPropagator prop = new DSSTPropagator(integrator, true);
    final UnnormalizedSphericalHarmonicsProvider provider = GravityFieldFactory.getUnnormalizedProvider(4, 0);
    final Frame earthFrame = CelestialBodyFactory.getEarth().getBodyOrientedFrame();
    DSSTForceModel zonal = new DSSTZonal(provider, 4, 3, 9);
    DSSTForceModel tesseral = new DSSTTesseral(earthFrame, Constants.WGS84_EARTH_ANGULAR_VELOCITY, provider, 4, 0, 4, 8, 4, 0, 2);
    prop.addForceModel(zonal);
    prop.addForceModel(tesseral);
    // Set the initial state as osculating
    prop.setInitialState(initialState, false);
    // Check the stored initial state is the osculating one
    Assert.assertEquals(initialState, prop.getInitialState());
    // Check that no propagation, i.e. propagation to the initial date, provides the initial
    // osculating state although the propagator is configured to propagate mean elements !!!
    Assert.assertEquals(initialState, prop.propagate(initialState.getDate()));
}

Example 69 with DormandPrince853Integrator

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

the class AdditionalEquationsTest method testInitNumerical.

/**
 * Test for issue #401
 *  with a numerical propagator
 */
@Test
public void testInitNumerical() throws OrekitException {
    // setup
    final double reference = 1.25;
    InitCheckerEquations checker = new InitCheckerEquations(reference);
    Assert.assertFalse(checker.wasCalled());
    // action
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(60);
    NumericalPropagator propagatorNumerical = new NumericalPropagator(integrator);
    propagatorNumerical.setInitialState(initialState.addAdditionalState(checker.getName(), reference));
    propagatorNumerical.addAdditionalEquations(checker);
    propagatorNumerical.propagate(initDate.shiftedBy(600));
    // verify
    Assert.assertTrue(checker.wasCalled());
}

Example 70 with DormandPrince853Integrator

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

the class AdditionalEquationsTest method testInitDSST.

/**
 * Test for issue #401
 *  with a DSST propagator
 */
@Test
public void testInitDSST() throws OrekitException {
    // setup
    final double reference = 3.5;
    InitCheckerEquations checker = new InitCheckerEquations(reference);
    Assert.assertFalse(checker.wasCalled());
    // action
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(60);
    DSSTPropagator propagatorDSST = new DSSTPropagator(integrator);
    propagatorDSST.setInitialState(initialState.addAdditionalState(checker.getName(), reference));
    propagatorDSST.addAdditionalEquations(checker);
    propagatorDSST.propagate(initDate.shiftedBy(600));
    // verify
    Assert.assertTrue(checker.wasCalled());
}