Examples with DateComponents org.orekit.time.DateComponents used on opensource projects

Example 6 with DateComponents

use of org.orekit.time.DateComponents in project Orekit by CS-SI.

the class NRLMSISE00Test method testDensity.

@Test
public void testDensity() throws OrekitException, InstantiationException, IllegalAccessException, IllegalArgumentException, InvocationTargetException, NoSuchMethodException, SecurityException {
    // Build the input params provider
    final InputParams ip = new InputParams();
    // Get Sun
    final PVCoordinatesProvider sun = CelestialBodyFactory.getSun();
    // Get Earth body shape
    final Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, itrf);
    // Build the model
    final NRLMSISE00 atm = new NRLMSISE00(ip, sun, earth).withSwitch(9, -1);
    // Build the date
    final AbsoluteDate date = new AbsoluteDate(new DateComponents(2003, 172), new TimeComponents(29000.), TimeScalesFactory.getUT1(IERSConventions.IERS_2010, true));
    // Build the position
    final double alt = 400.;
    final double lat = 60.;
    final double lon = -70.;
    final GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(lat), FastMath.toRadians(lon), alt * 1000.);
    final Vector3D pos = earth.transform(point);
    // Run
    final double rho = atm.getDensity(date, pos, itrf);
    final double lst = 29000. / 3600. - 70. / 15.;
    final double[] ap = { 4., 100., 100., 100., 100., 100., 100. };
    Class<?> outputClass = getOutputClass();
    Constructor<?> cons = outputClass.getDeclaredConstructor(NRLMSISE00.class, Integer.TYPE, Double.TYPE, Double.TYPE, Double.TYPE, Double.TYPE, Double.TYPE, Double.TYPE, double[].class);
    cons.setAccessible(true);
    Method gtd7d = outputClass.getDeclaredMethod("gtd7d", Double.TYPE);
    gtd7d.setAccessible(true);
    Method getDensity = outputClass.getDeclaredMethod("getDensity", Integer.TYPE);
    getDensity.setAccessible(true);
    final Object out = createOutput(atm, 172, 29000., 60., -70, lst, 150., 150., ap);
    gtd7d.invoke(out, 400.0);
    Assert.assertEquals(rho, ((Double) getDensity.invoke(out, 5)).doubleValue(), rho * 1.e-3);
}

Example 7 with DateComponents

use of org.orekit.time.DateComponents in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method testStateJacobianVs80Implementation.

@Test
public void testStateJacobianVs80Implementation() 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);
    HolmesFeatherstoneAttractionModel hfModel = new HolmesFeatherstoneAttractionModel(itrf, GravityFieldFactory.getNormalizedProvider(50, 50));
    Assert.assertEquals(TideSystem.UNKNOWN, hfModel.getTideSystem());
    SpacecraftState state = new SpacecraftState(orbit);
    checkStateJacobianVs80Implementation(state, hfModel, new LofOffset(state.getFrame(), LOFType.VVLH), 2.0e-15, false);
}

Example 8 with DateComponents

use of org.orekit.time.DateComponents in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method testHelioSynchronous.

// rough test to determine if J2 alone creates heliosynchronism
@Test
public void testHelioSynchronous() throws OrekitException {
    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(1970, 07, 01), new TimeComponents(13, 59, 27.816), TimeScalesFactory.getUTC());
    Transform itrfToEME2000 = itrf.getTransformTo(FramesFactory.getEME2000(), date);
    Vector3D pole = itrfToEME2000.transformVector(Vector3D.PLUS_K);
    Frame poleAligned = new Frame(FramesFactory.getEME2000(), new Transform(date, new Rotation(pole, Vector3D.PLUS_K)), "pole aligned", true);
    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, poleAligned, date, mu);
    double[][] c = new double[3][1];
    c[0][0] = 0.0;
    c[2][0] = normalizedC20;
    double[][] s = new double[3][1];
    propagator.addForceModel(new HolmesFeatherstoneAttractionModel(itrf, GravityFieldFactory.getNormalizedProvider(6378136.460, mu, TideSystem.UNKNOWN, c, s)));
    // let the step handler perform the test
    propagator.setMasterMode(Constants.JULIAN_DAY, new SpotStepHandler(date, mu));
    propagator.setInitialState(new SpacecraftState(orbit));
    propagator.propagate(date.shiftedBy(7 * Constants.JULIAN_DAY));
    Assert.assertTrue(propagator.getCalls() < 9200);
}

Example 9 with DateComponents

use of org.orekit.time.DateComponents in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method testStateJacobian.

@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);
    SpacecraftState state0 = new SpacecraftState(orbit);
    propagator.setInitialState(state0);
    checkStateJacobian(propagator, state0, date.shiftedBy(3.5 * 3600.0), 50000, tolerances[0], 7.8e-6);
}

Example 10 with DateComponents

use of org.orekit.time.DateComponents in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method testCompleteWithCunninghamReference.

@Test
@Deprecated
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(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);
}