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

Example 16 with EquinoctialOrbit

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

the class ElevationDetectorTest method testEventForMask.

@Test
public void testEventForMask() 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");
    double[][] maskValues = { { FastMath.toRadians(0), FastMath.toRadians(5) }, { FastMath.toRadians(30), FastMath.toRadians(4) }, { FastMath.toRadians(60), FastMath.toRadians(3) }, { FastMath.toRadians(90), FastMath.toRadians(2) }, { FastMath.toRadians(120), FastMath.toRadians(3) }, { FastMath.toRadians(150), FastMath.toRadians(4) }, { FastMath.toRadians(180), FastMath.toRadians(5) }, { FastMath.toRadians(210), FastMath.toRadians(6) }, { FastMath.toRadians(240), FastMath.toRadians(5) }, { FastMath.toRadians(270), FastMath.toRadians(4) }, { FastMath.toRadians(300), FastMath.toRadians(3) }, { FastMath.toRadians(330), FastMath.toRadians(4) } };
    ElevationMask mask = new ElevationMask(maskValues);
    ElevationDetector detector = new ElevationDetector(topo).withElevationMask(mask).withHandler(new StopOnIncreasing<ElevationDetector>());
    Assert.assertSame(mask, detector.getElevationMask());
    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(0.065, elevation, 2.0e-5);
}

Example 17 with EquinoctialOrbit

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

the class EventDetectorTest method testWrappedException.

@Test
public void testWrappedException() throws OrekitException {
    final Throwable dummyCause = new RuntimeException();
    try {
        // initial conditions
        Frame eme2000 = FramesFactory.getEME2000();
        TimeScale utc = TimeScalesFactory.getUTC();
        final AbsoluteDate initialDate = new AbsoluteDate(2011, 5, 11, utc);
        final AbsoluteDate exceptionDate = initialDate.shiftedBy(3600.0);
        KeplerianPropagator k = new KeplerianPropagator(new EquinoctialOrbit(new PVCoordinates(new Vector3D(4008462.4706055815, -3155502.5373837613, -5044275.9880020910), new Vector3D(-5012.9298276860990, 1920.3567095973078, -5172.7403501801580)), eme2000, initialDate, Constants.WGS84_EARTH_MU));
        k.addEventDetector(new DateDetector(initialDate.shiftedBy(Constants.JULIAN_DAY)) {

            private static final long serialVersionUID = 1L;

            @Override
            public double g(final SpacecraftState s) throws OrekitException {
                final double dt = s.getDate().durationFrom(exceptionDate);
                if (FastMath.abs(dt) < 1.0) {
                    throw new OrekitException(dummyCause, LocalizedCoreFormats.SIMPLE_MESSAGE, "dummy");
                }
                return dt;
            }
        });
        k.propagate(initialDate.shiftedBy(Constants.JULIAN_YEAR));
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertSame(dummyCause, oe.getCause());
    }
}

Example 18 with EquinoctialOrbit

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

the class EventShifterTest method setUp.

@Before
public void setUp() {
    try {
        Utils.setDataRoot("regular-data");
        mu = 3.9860047e14;
        double ae = 6.378137e6;
        double c20 = -1.08263e-3;
        double c30 = 2.54e-6;
        double c40 = 1.62e-6;
        double c50 = 2.3e-7;
        double c60 = -5.5e-7;
        final Vector3D position = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
        final Vector3D velocity = new Vector3D(505.8479685, 942.7809215, 7435.922231);
        iniDate = new AbsoluteDate(1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
        final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getGCRF(), iniDate, mu);
        propagator = new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
        log = new ArrayList<EventEntry>();
    } catch (OrekitException oe) {
        Assert.fail(oe.getLocalizedMessage());
    }
}

Example 19 with EquinoctialOrbit

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

the class AlignmentDetectorTest method setUp.

@Before
public void setUp() {
    try {
        Utils.setDataRoot("regular-data");
        double mu = 3.9860047e14;
        final Vector3D position = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
        final Vector3D velocity = new Vector3D(505.8479685, 942.7809215, 7435.922231);
        iniDate = new AbsoluteDate(1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
        final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), iniDate, mu);
        initialState = new SpacecraftState(orbit);
        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);
        propagator.setInitialState(initialState);
    } catch (OrekitException oe) {
        Assert.fail(oe.getLocalizedMessage());
    }
}

Example 20 with EquinoctialOrbit

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

the class JacobianPropagatorConverterTest method setUp.

@Before
public void setUp() throws OrekitException, IOException, ParseException {
    Utils.setDataRoot("regular-data:potential/shm-format");
    gravity = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), GravityFieldFactory.getNormalizedProvider(2, 0));
    mu = gravity.getParameterDriver(NewtonianAttraction.CENTRAL_ATTRACTION_COEFFICIENT).getValue();
    dP = 1.0;
    // use a orbit that comes close to Earth so the drag coefficient has an effect
    final Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6).normalize().scalarMultiply(Constants.WGS84_EARTH_EQUATORIAL_RADIUS + 300e3);
    final Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);
    final AbsoluteDate initDate = new AbsoluteDate(2010, 10, 10, 10, 10, 10.0, TimeScalesFactory.getUTC());
    orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    earth.setAngularThreshold(1.e-7);
    atmosphere = new SimpleExponentialAtmosphere(earth, 0.0004, 42000.0, 7500.0);
    final double dragCoef = 2.0;
    crossSection = 25.0;
    drag = new DragForce(atmosphere, new IsotropicDrag(crossSection, dragCoef));
}