Examples with EquinoctialOrbit org.orekit.orbits.EquinoctialOrbit used on opensource projects

Example 46 with EquinoctialOrbit

use of org.orekit.orbits.EquinoctialOrbit in project Orekit by CS-SI.

the class LatitudeCrossingDetectorTest method testNoCrossing.

@Test
public void testNoCrossing() throws OrekitException {
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    LatitudeCrossingDetector d = new LatitudeCrossingDetector(10.0, 1.e-6, earth, FastMath.toRadians(82.0)).withHandler(new ContinueOnEvent<LatitudeCrossingDetector>());
    Assert.assertEquals(10.0, d.getMaxCheckInterval(), 1.0e-15);
    Assert.assertEquals(1.0e-6, d.getThreshold(), 1.0e-15);
    Assert.assertEquals(82.0, FastMath.toDegrees(d.getLatitude()), 1.0e-14);
    Assert.assertEquals(AbstractDetector.DEFAULT_MAX_ITER, d.getMaxIterationCount());
    final TimeScale utc = TimeScalesFactory.getUTC();
    final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
    final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
    final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
    final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), date, Constants.EIGEN5C_EARTH_MU);
    Propagator propagator = new EcksteinHechlerPropagator(orbit, Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS, Constants.EIGEN5C_EARTH_MU, Constants.EIGEN5C_EARTH_C20, Constants.EIGEN5C_EARTH_C30, Constants.EIGEN5C_EARTH_C40, Constants.EIGEN5C_EARTH_C50, Constants.EIGEN5C_EARTH_C60);
    EventsLogger logger = new EventsLogger();
    propagator.addEventDetector(logger.monitorDetector(d));
    propagator.propagate(date.shiftedBy(Constants.JULIAN_DAY));
    Assert.assertEquals(0, logger.getLoggedEvents().size());
}

Example 47 with EquinoctialOrbit

use of org.orekit.orbits.EquinoctialOrbit in project Orekit by CS-SI.

the class LatitudeCrossingDetectorTest method testRegularCrossing.

@Test
public void testRegularCrossing() throws OrekitException {
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    LatitudeCrossingDetector d = new LatitudeCrossingDetector(60.0, 1.e-6, earth, FastMath.toRadians(60.0)).withHandler(new ContinueOnEvent<LatitudeCrossingDetector>());
    Assert.assertEquals(60.0, d.getMaxCheckInterval(), 1.0e-15);
    Assert.assertEquals(1.0e-6, d.getThreshold(), 1.0e-15);
    Assert.assertEquals(60.0, FastMath.toDegrees(d.getLatitude()), 1.0e-14);
    Assert.assertEquals(AbstractDetector.DEFAULT_MAX_ITER, d.getMaxIterationCount());
    final TimeScale utc = TimeScalesFactory.getUTC();
    final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
    final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
    final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
    final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), date, Constants.EIGEN5C_EARTH_MU);
    Propagator propagator = new EcksteinHechlerPropagator(orbit, Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS, Constants.EIGEN5C_EARTH_MU, Constants.EIGEN5C_EARTH_C20, Constants.EIGEN5C_EARTH_C30, Constants.EIGEN5C_EARTH_C40, Constants.EIGEN5C_EARTH_C50, Constants.EIGEN5C_EARTH_C60);
    EventsLogger logger = new EventsLogger();
    propagator.addEventDetector(logger.monitorDetector(d));
    propagator.propagate(date.shiftedBy(Constants.JULIAN_DAY));
    AbsoluteDate previous = null;
    for (LoggedEvent e : logger.getLoggedEvents()) {
        SpacecraftState state = e.getState();
        double latitude = earth.transform(state.getPVCoordinates(earth.getBodyFrame()).getPosition(), earth.getBodyFrame(), null).getLatitude();
        Assert.assertEquals(60.0, FastMath.toDegrees(latitude), 3.0e-10);
        if (previous != null) {
            if (e.isIncreasing()) {
                // crossing northward
                Assert.assertTrue(state.getPVCoordinates().getVelocity().getZ() > 3611.0);
                Assert.assertEquals(4954.70, state.getDate().durationFrom(previous), 0.01);
            } else {
                // crossing southward
                Assert.assertTrue(state.getPVCoordinates().getVelocity().getZ() < -3615.0);
                Assert.assertEquals(956.17, state.getDate().durationFrom(previous), 0.01);
            }
        }
        previous = state.getDate();
    }
    Assert.assertEquals(30, logger.getLoggedEvents().size());
}

Example 48 with EquinoctialOrbit

use of org.orekit.orbits.EquinoctialOrbit in project Orekit by CS-SI.

the class ElevationExtremumDetectorTest method testLEO.

@Test
public void testLEO() throws OrekitException {
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final GeodeticPoint gp = new GeodeticPoint(FastMath.toRadians(51.0), FastMath.toRadians(66.6), 300.0);
    final ElevationExtremumDetector raw = new ElevationExtremumDetector(new TopocentricFrame(earth, gp, "test")).withMaxCheck(60).withThreshold(1.e-6).withHandler(new ContinueOnEvent<ElevationExtremumDetector>());
    final EventSlopeFilter<ElevationExtremumDetector> maxElevationDetector = new EventSlopeFilter<ElevationExtremumDetector>(raw, FilterType.TRIGGER_ONLY_DECREASING_EVENTS);
    Assert.assertEquals(60.0, raw.getMaxCheckInterval(), 1.0e-15);
    Assert.assertEquals(1.0e-6, raw.getThreshold(), 1.0e-15);
    Assert.assertEquals(AbstractDetector.DEFAULT_MAX_ITER, raw.getMaxIterationCount());
    Assert.assertEquals("test", raw.getTopocentricFrame().getName());
    final TimeScale utc = TimeScalesFactory.getUTC();
    final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
    final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
    final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
    final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), date, Constants.EIGEN5C_EARTH_MU);
    Propagator propagator = new EcksteinHechlerPropagator(orbit, Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS, Constants.EIGEN5C_EARTH_MU, Constants.EIGEN5C_EARTH_C20, Constants.EIGEN5C_EARTH_C30, Constants.EIGEN5C_EARTH_C40, Constants.EIGEN5C_EARTH_C50, Constants.EIGEN5C_EARTH_C60);
    EventsLogger logger = new EventsLogger();
    propagator.addEventDetector(logger.monitorDetector(maxElevationDetector));
    propagator.propagate(date.shiftedBy(Constants.JULIAN_DAY));
    int visibleEvents = 0;
    for (LoggedEvent e : logger.getLoggedEvents()) {
        final double eMinus = raw.getElevation(e.getState().shiftedBy(-10.0));
        final double e0 = raw.getElevation(e.getState());
        final double ePlus = raw.getElevation(e.getState().shiftedBy(+10.0));
        if (e0 > FastMath.toRadians(5.0)) {
            ++visibleEvents;
        }
        Assert.assertTrue(e0 > eMinus);
        Assert.assertTrue(e0 > ePlus);
    }
    Assert.assertEquals(15, logger.getLoggedEvents().size());
    Assert.assertEquals(6, visibleEvents);
}

Example 49 with EquinoctialOrbit

use of org.orekit.orbits.EquinoctialOrbit in project Orekit by CS-SI.

the class EventEnablingPredicateFilterTest method setUp.

@Before
public void setUp() throws OrekitException {
    Utils.setDataRoot("regular-data");
    earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    gp = new GeodeticPoint(FastMath.toRadians(51.0), FastMath.toRadians(66.6), 300.0);
    final TimeScale utc = TimeScalesFactory.getUTC();
    final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
    final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
    final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
    orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), date, Constants.EIGEN5C_EARTH_MU);
}

Example 50 with EquinoctialOrbit

use of org.orekit.orbits.EquinoctialOrbit in project Orekit by CS-SI.

the class EcksteinHechlerConverterTest method setUp.

@Before
public void setUp() throws OrekitException {
    Utils.setDataRoot("regular-data");
    AbsoluteDate initDate = AbsoluteDate.J2000_EPOCH.shiftedBy(584.);
    double mu = 3.9860047e14;
    double ae = 6.378137e6;
    double[][] cnm = new double[][] { { 0 }, { 0 }, { -1.08263e-3 }, { 2.54e-6 }, { 1.62e-6 }, { 2.3e-7 }, { -5.5e-7 } };
    double[][] snm = new double[][] { { 0 }, { 0 }, { 0 }, { 0 }, { 0 }, { 0 }, { 0 } };
    provider = GravityFieldFactory.getUnnormalizedProvider(ae, mu, TideSystem.UNKNOWN, cnm, snm);
    orbit = new EquinoctialOrbit(new PVCoordinates(new Vector3D(3220103., 69623., 6449822.), new Vector3D(6414.7, -2006., -3180.)), FramesFactory.getEME2000(), initDate, mu);
}