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

Example 56 with DateComponents

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

the class BodyCenterPointingTest method setUp.

@Before
public void setUp() {
    try {
        Utils.setDataRoot("regular-data");
        // Computation date
        date = new AbsoluteDate(new DateComponents(2008, 04, 07), TimeComponents.H00, TimeScalesFactory.getUTC());
        // Satellite position as circular parameters
        final double mu = 3.9860047e14;
        final double raan = 270.;
        circ = new CircularOrbit(7178000.0, 0.5e-4, -0.5e-4, FastMath.toRadians(50.), FastMath.toRadians(raan), FastMath.toRadians(5.300 - raan), PositionAngle.MEAN, FramesFactory.getEME2000(), date, mu);
        // WGS84 Earth model
        earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
        // Transform from EME2000 to ITRF2008
        eme2000ToItrf = FramesFactory.getEME2000().getTransformTo(earth.getBodyFrame(), date);
        // Create earth center pointing attitude provider
        earthCenterAttitudeLaw = new BodyCenterPointing(circ.getFrame(), earth);
    } catch (OrekitException oe) {
        Assert.fail(oe.getMessage());
    }
}

Example 57 with DateComponents

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

the class InertialAttitudeTest method testSpin.

@Test
public void testSpin() throws OrekitException {
    AbsoluteDate date = new AbsoluteDate(new DateComponents(1970, 01, 01), new TimeComponents(3, 25, 45.6789), TimeScalesFactory.getUTC());
    AttitudeProvider law = new InertialProvider(new Rotation(new Vector3D(-0.64, 0.6, 0.48), 0.2, RotationConvention.VECTOR_OPERATOR));
    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);
    Propagator propagator = new KeplerianPropagator(orbit, law);
    double h = 100.0;
    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, 1.0e-6 * 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, 1.0e-6 * evolutionAnglePlus);
    // compute spin axis using finite differences
    Rotation rMinus = sMinus.getAttitude().getRotation();
    Rotation rPlus = sPlus.getAttitude().getRotation();
    Rotation dr = rPlus.compose(rMinus.revert(), RotationConvention.VECTOR_OPERATOR);
    Assert.assertEquals(0, dr.getAngle(), 1.0e-10);
    Vector3D spin0 = s0.getAttitude().getSpin();
    Assert.assertEquals(0, spin0.getNorm(), 1.0e-10);
}

Example 58 with DateComponents

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

the class InertialAttitudeTest method setUp.

@Before
public void setUp() {
    try {
        Utils.setDataRoot("regular-data");
        t0 = new AbsoluteDate(new DateComponents(2008, 06, 03), TimeComponents.H12, TimeScalesFactory.getUTC());
        orbit0 = new KeplerianOrbit(12345678.9, 0.001, 2.3, 0.1, 3.04, 2.4, PositionAngle.TRUE, FramesFactory.getEME2000(), t0, 3.986004415e14);
    } catch (OrekitException oe) {
        Assert.fail(oe.getMessage());
    }
}

Example 59 with DateComponents

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

the class LofOffsetTest method testRetrieveAngles.

@Test
public void testRetrieveAngles() 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);
    RotationOrder order = RotationOrder.ZXY;
    double alpha1 = 0.123;
    double alpha2 = 0.456;
    double alpha3 = 0.789;
    LofOffset law = new LofOffset(orbit.getFrame(), LOFType.VVLH, order, alpha1, alpha2, alpha3);
    Rotation offsetAtt = law.getAttitude(orbit, date, orbit.getFrame()).getRotation();
    Rotation alignedAtt = new LofOffset(orbit.getFrame(), LOFType.VVLH).getAttitude(orbit, date, orbit.getFrame()).getRotation();
    Rotation offsetProper = offsetAtt.compose(alignedAtt.revert(), RotationConvention.VECTOR_OPERATOR);
    double[] anglesV = offsetProper.revert().getAngles(order, RotationConvention.VECTOR_OPERATOR);
    Assert.assertEquals(alpha1, anglesV[0], 1.0e-11);
    Assert.assertEquals(alpha2, anglesV[1], 1.0e-11);
    Assert.assertEquals(alpha3, anglesV[2], 1.0e-11);
    double[] anglesF = offsetProper.getAngles(order, RotationConvention.FRAME_TRANSFORM);
    Assert.assertEquals(alpha1, anglesF[0], 1.0e-11);
    Assert.assertEquals(alpha2, anglesF[1], 1.0e-11);
    Assert.assertEquals(alpha3, anglesF[2], 1.0e-11);
}

Example 60 with DateComponents

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

the class LofOffsetTest 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);
        checkField(Decimal64Field.getInstance(), law, orbit, date, orbit.getFrame());
    }
}