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

Example 96 with KeplerianOrbit

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

the class StopOnDecreasingTest method testIncreasing.

@Test
public void testIncreasing() throws OrekitException {
    SpacecraftState s = new SpacecraftState(new KeplerianOrbit(24464560.0, 0.7311, 0.122138, 3.10686, 1.00681, 0.048363, PositionAngle.MEAN, FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, Constants.EIGEN5C_EARTH_MU));
    Assert.assertSame(EventHandler.Action.CONTINUE, new StopOnDecreasing<EventDetector>().eventOccurred(s, null, true));
}

Example 97 with KeplerianOrbit

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

the class StopOnEventTest method testNoReset.

@Test
public void testNoReset() throws OrekitException {
    SpacecraftState s = new SpacecraftState(new KeplerianOrbit(24464560.0, 0.7311, 0.122138, 3.10686, 1.00681, 0.048363, PositionAngle.MEAN, FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, Constants.EIGEN5C_EARTH_MU));
    Assert.assertSame(s, new StopOnEvent<EventDetector>().resetState(null, s));
}

Example 98 with KeplerianOrbit

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

the class LofOffsetPointingTest method testTypesField.

@Test
public void testTypesField() throws OrekitException {
    AbsoluteDate date = new AbsoluteDate(new DateComponents(1970, 01, 01), new TimeComponents(3, 25, 45.6789), TimeScalesFactory.getUTC());
    KeplerianOrbit orbit = new KeplerianOrbit(7178000.0, 1.e-4, FastMath.toRadians(50.), FastMath.toRadians(10.), FastMath.toRadians(20.), FastMath.toRadians(30.), PositionAngle.MEAN, FramesFactory.getEME2000(), date, 3.986004415e14);
    for (final LOFType type : LOFType.values()) {
        RotationOrder order = RotationOrder.ZXY;
        double alpha1 = 0.123;
        double alpha2 = 0.456;
        double alpha3 = 0.789;
        LofOffset law = new LofOffset(orbit.getFrame(), type, order, alpha1, alpha2, alpha3);
        final Vector3D dir;
        switch(type) {
            case TNW:
                dir = Vector3D.PLUS_J;
                break;
            case QSW:
            case LVLH:
                dir = Vector3D.MINUS_I;
                break;
            case VVLH:
                dir = Vector3D.PLUS_K;
                break;
            default:
                // VNC
                dir = Vector3D.MINUS_K;
        }
        LofOffsetPointing lop = new LofOffsetPointing(orbit.getFrame(), earthSpheric, law, dir);
        checkField(Decimal64Field.getInstance(), lop, orbit, date, orbit.getFrame());
    }
}

Example 99 with KeplerianOrbit

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

the class NadirPointingTest method testSpin.

@Test
public void testSpin() throws OrekitException {
    // Elliptic earth shape
    OneAxisEllipsoid earthShape = new OneAxisEllipsoid(6378136.460, 1 / 298.257222101, itrf);
    // Create earth center pointing attitude provider
    NadirPointing law = new NadirPointing(FramesFactory.getEME2000(), earthShape);
    // Satellite on any position
    KeplerianOrbit orbit = new KeplerianOrbit(7178000.0, 1.e-4, FastMath.toRadians(50.), FastMath.toRadians(10.), FastMath.toRadians(20.), FastMath.toRadians(30.), PositionAngle.MEAN, FramesFactory.getEME2000(), date, mu);
    Propagator propagator = new KeplerianPropagator(orbit, law, mu, 2500.0);
    double h = 0.1;
    SpacecraftState sMinus = propagator.propagate(date.shiftedBy(-h));
    SpacecraftState s0 = propagator.propagate(date);
    SpacecraftState sPlus = propagator.propagate(date.shiftedBy(h));
    // check spin is consistent with attitude evolution
    double errorAngleMinus = Rotation.distance(sMinus.shiftedBy(h).getAttitude().getRotation(), s0.getAttitude().getRotation());
    double evolutionAngleMinus = Rotation.distance(sMinus.getAttitude().getRotation(), s0.getAttitude().getRotation());
    Assert.assertEquals(0.0, errorAngleMinus, 5.3e-9 * evolutionAngleMinus);
    double errorAnglePlus = Rotation.distance(s0.getAttitude().getRotation(), sPlus.shiftedBy(-h).getAttitude().getRotation());
    double evolutionAnglePlus = Rotation.distance(s0.getAttitude().getRotation(), sPlus.getAttitude().getRotation());
    Assert.assertEquals(0.0, errorAnglePlus, 8.1e-9 * evolutionAnglePlus);
    Vector3D spin0 = s0.getAttitude().getSpin();
    Rotation rM = sMinus.getAttitude().getRotation();
    Rotation rP = sPlus.getAttitude().getRotation();
    Vector3D reference = AngularCoordinates.estimateRate(rM, rP, 2 * h);
    Assert.assertTrue(Rotation.distance(rM, rP) > 2.0e-4);
    Assert.assertEquals(0.0, spin0.subtract(reference).getNorm(), 2.0e-6);
}

Example 100 with KeplerianOrbit

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

the class NadirPointingTest method testNonSphericEarth.

/**
 * Test in the case of an elliptic earth : nadir pointing shall be :
 *   - the same as earth center pointing in case of equatorial or polar position
 *   - different from earth center pointing in any other case
 */
@Test
public void testNonSphericEarth() throws OrekitException {
    // Elliptic earth shape
    OneAxisEllipsoid earthShape = new OneAxisEllipsoid(6378136.460, 1 / 298.257222101, itrf);
    // Create nadir pointing attitude provider
    NadirPointing nadirAttitudeLaw = new NadirPointing(FramesFactory.getEME2000(), earthShape);
    // Create earth center pointing attitude provider
    BodyCenterPointing earthCenterAttitudeLaw = new BodyCenterPointing(FramesFactory.getEME2000(), earthShape);
    // Satellite on equatorial position
    // **********************************
    KeplerianOrbit kep = new KeplerianOrbit(7178000.0, 1.e-8, FastMath.toRadians(50.), 0., 0., 0., PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
    // Get nadir attitude
    Rotation rotNadir = nadirAttitudeLaw.getAttitude(kep, date, kep.getFrame()).getRotation();
    checkField(Decimal64Field.getInstance(), nadirAttitudeLaw, kep, kep.getDate(), kep.getFrame());
    // Get earth center attitude
    Rotation rotCenter = earthCenterAttitudeLaw.getAttitude(kep, date, kep.getFrame()).getRotation();
    // For a satellite at equatorial position, earth center pointing attitude and nadir pointing
    // attitude shall be the same, i.e the composition of inverse earth pointing rotation
    // with nadir pointing rotation shall be identity.
    Rotation rotCompo = rotCenter.composeInverse(rotNadir, RotationConvention.VECTOR_OPERATOR);
    double angle = rotCompo.getAngle();
    Assert.assertEquals(0.0, angle, 5.e-6);
    // Satellite on polar position
    // *****************************
    CircularOrbit circ = new CircularOrbit(7178000.0, 1.e-5, 0., FastMath.toRadians(90.), 0., FastMath.toRadians(90.), PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
    // Get nadir attitude
    rotNadir = nadirAttitudeLaw.getAttitude(circ, date, circ.getFrame()).getRotation();
    // Get earth center attitude
    rotCenter = earthCenterAttitudeLaw.getAttitude(circ, date, circ.getFrame()).getRotation();
    // For a satellite at polar position, earth center pointing attitude and nadir pointing
    // attitude shall be the same, i.e the composition of inverse earth pointing rotation
    // with nadir pointing rotation shall be identity.
    rotCompo = rotCenter.composeInverse(rotNadir, RotationConvention.VECTOR_OPERATOR);
    angle = rotCompo.getAngle();
    Assert.assertEquals(angle, 0.0, 5.e-6);
    // Satellite on any position
    // ***************************
    circ = new CircularOrbit(7178000.0, 1.e-5, 0., FastMath.toRadians(50.), 0., FastMath.toRadians(90.), PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
    // Get nadir attitude
    rotNadir = nadirAttitudeLaw.getAttitude(circ, date, circ.getFrame()).getRotation();
    // Get earth center attitude
    rotCenter = earthCenterAttitudeLaw.getAttitude(circ, date, circ.getFrame()).getRotation();
    // For a satellite at any position, earth center pointing attitude and nadir pointing
    // and nadir pointing attitude shall not be the same, i.e the composition of inverse earth
    // pointing rotation with nadir pointing rotation shall be different from identity.
    rotCompo = rotCenter.composeInverse(rotNadir, RotationConvention.VECTOR_OPERATOR);
    angle = rotCompo.getAngle();
    Assert.assertEquals(angle, FastMath.toRadians(0.16797386586252272), Utils.epsilonAngle);
}