Examples with OneAxisEllipsoid org.orekit.bodies.OneAxisEllipsoid used on opensource projects

Example 91 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class ElevationDetectorTest method testHorizon.

@Test
public void testHorizon() throws OrekitException {
    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, mu);
    Propagator propagator = new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
    // Earth and frame
    // equatorial radius in meter
    double ae = 6378137.0;
    // flattening
    double f = 1.0 / 298.257223563;
    // terrestrial frame at an arbitrary date
    Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
    GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(48.833), FastMath.toRadians(2.333), 0.0);
    TopocentricFrame topo = new TopocentricFrame(earth, point, "Gstation");
    AtmosphericRefractionModel refractionModel = new EarthStandardAtmosphereRefraction();
    ElevationDetector detector = new ElevationDetector(topo).withRefraction(refractionModel).withHandler(new StopOnIncreasing<ElevationDetector>());
    Assert.assertSame(refractionModel, detector.getRefractionModel());
    AbsoluteDate startDate = new AbsoluteDate(2003, 9, 15, 20, 0, 0, utc);
    propagator.resetInitialState(propagator.propagate(startDate));
    propagator.addEventDetector(detector);
    final SpacecraftState fs = propagator.propagate(startDate.shiftedBy(Constants.JULIAN_DAY));
    double elevation = topo.getElevation(fs.getPVCoordinates().getPosition(), fs.getFrame(), fs.getDate());
    Assert.assertEquals(FastMath.toRadians(-0.5746255623877098), elevation, 2.0e-5);
}

Example 92 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class KeplerianPropagatorTest method setting.

@Test
public void setting() throws OrekitException {
    final KeplerianOrbit orbit = new KeplerianOrbit(7.8e6, 0.032, 0.4, 0.1, 0.2, 0.3, PositionAngle.TRUE, FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, 3.986004415e14);
    KeplerianPropagator propagator = new KeplerianPropagator(orbit);
    final OneAxisEllipsoid earthShape = new OneAxisEllipsoid(6378136.460, 1 / 298.257222101, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final TopocentricFrame topo = new TopocentricFrame(earthShape, new GeodeticPoint(0.389, -2.962, 0), null);
    propagator.addEventDetector(new ElevationDetector(60, AbstractDetector.DEFAULT_THRESHOLD, topo).withConstantElevation(0.09));
    AbsoluteDate farTarget = AbsoluteDate.J2000_EPOCH.shiftedBy(10000.0);
    SpacecraftState propagated = propagator.propagate(farTarget);
    final double elevation = topo.getElevation(propagated.getPVCoordinates().getPosition(), propagated.getFrame(), propagated.getDate());
    final double zVelocity = propagated.getPVCoordinates(topo).getVelocity().getZ();
    Assert.assertTrue(farTarget.durationFrom(propagated.getDate()) > 7800.0);
    Assert.assertTrue(farTarget.durationFrom(propagated.getDate()) < 7900.0);
    Assert.assertEquals(0.09, elevation, 1.0e-9);
    Assert.assertTrue(zVelocity < 0);
}

Example 93 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class KeplerianPropagatorTest method altitude.

@Test
public void altitude() throws OrekitException {
    final KeplerianOrbit orbit = new KeplerianOrbit(7.8e6, 0.032, 0.4, 0.1, 0.2, 0.3, PositionAngle.TRUE, FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, 3.986004415e14);
    KeplerianPropagator propagator = new KeplerianPropagator(orbit);
    BodyShape bodyShape = new OneAxisEllipsoid(6378137.0, 1.0 / 298.257222101, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    AltitudeDetector detector = new AltitudeDetector(0.05 * orbit.getKeplerianPeriod(), 1500000, bodyShape);
    Assert.assertEquals(1500000, detector.getAltitude(), 1.0e-12);
    propagator.addEventDetector(detector);
    AbsoluteDate farTarget = AbsoluteDate.J2000_EPOCH.shiftedBy(10000.0);
    SpacecraftState propagated = propagator.propagate(farTarget);
    Assert.assertTrue(farTarget.durationFrom(propagated.getDate()) > 5400.0);
    Assert.assertTrue(farTarget.durationFrom(propagated.getDate()) < 5500.0);
    GeodeticPoint gp = bodyShape.transform(propagated.getPVCoordinates().getPosition(), propagated.getFrame(), propagated.getDate());
    Assert.assertEquals(1500000, gp.getAltitude(), 0.1);
}

Example 94 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class TLEPropagatorTest method testBodyCenterInPointingDirection.

/**
 * Test if body center belongs to the direction pointed by the satellite
 */
@Test
public void testBodyCenterInPointingDirection() throws OrekitException {
    final Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, itrf);
    DistanceChecker checker = new DistanceChecker(itrf);
    // with Earth pointing attitude, distance should be small
    TLEPropagator propagator = TLEPropagator.selectExtrapolator(tle, new BodyCenterPointing(FramesFactory.getTEME(), earth), Propagator.DEFAULT_MASS);
    propagator.setMasterMode(900.0, checker);
    propagator.propagate(tle.getDate().shiftedBy(period));
    Assert.assertEquals(0.0, checker.getMaxDistance(), 2.0e-7);
    // with default attitude mode, distance should be large
    propagator = TLEPropagator.selectExtrapolator(tle);
    propagator.setMasterMode(900.0, checker);
    propagator.propagate(tle.getDate().shiftedBy(period));
    Assert.assertEquals(1.5219e7, checker.getMinDistance(), 1000.0);
    Assert.assertEquals(2.6572e7, checker.getMaxDistance(), 1000.0);
}

Example 95 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class FieldOfViewDetectorTest method testStopOnExit.

/**
 * check the default behavior to stop propagation on FoV exit.
 */
@Test
public void testStopOnExit() throws OrekitException {
    // setup
    double pi = FastMath.PI;
    // arbitrary date
    AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
    AbsoluteDate endDate = date.shiftedBy(Constants.JULIAN_DAY);
    Frame eci = FramesFactory.getGCRF();
    Frame ecef = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    BodyShape earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, ecef);
    GeodeticPoint gp = new GeodeticPoint(FastMath.toRadians(39), FastMath.toRadians(77), 0);
    TopocentricFrame topo = new TopocentricFrame(earth, gp, "topo");
    // iss like orbit
    KeplerianOrbit orbit = new KeplerianOrbit(6378137 + 400e3, 0, FastMath.toRadians(51.65), 0, 0, 0, PositionAngle.TRUE, eci, date, Constants.EGM96_EARTH_MU);
    AttitudeProvider attitude = new NadirPointing(eci, earth);
    // action
    FieldOfView fov = new FieldOfView(Vector3D.PLUS_K, Vector3D.PLUS_I, pi / 3, 16, 0);
    FieldOfViewDetector fovDetector = new FieldOfViewDetector(topo, fov).withMaxCheck(5.0);
    EventsLogger logger = new EventsLogger();
    Propagator prop = new KeplerianPropagator(orbit, attitude);
    prop.addEventDetector(logger.monitorDetector(fovDetector));
    prop.propagate(endDate);
    List<LoggedEvent> actual = logger.getLoggedEvents();
    // verify
    // check we have an entry and an exit event.
    Assert.assertEquals(2, actual.size());
}