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

Example 46 with DateComponents

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

the class FieldSpacecraftStateTest method doTestDatesConsistency.

private <T extends RealFieldElement<T>> void doTestDatesConsistency(final Field<T> field) throws OrekitException {
    T zero = field.getZero();
    T a = zero.add(rOrbit.getA());
    T e = zero.add(rOrbit.getE());
    T i = zero.add(rOrbit.getI());
    T pa = zero.add(1.9674147913622104);
    T raan = zero.add(FastMath.toRadians(261));
    T lv = zero.add(0);
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(a, e, i, pa, raan, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
    BodyCenterPointing attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
    new FieldSpacecraftState<>(orbit, attitudeLaw.getAttitude(orbit.shiftedBy(zero.add(10.0)), orbit.getDate().shiftedBy(10.0), orbit.getFrame()));
}

Example 47 with DateComponents

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

the class SpacecraftStateTest method setUp.

@Before
public void setUp() {
    try {
        Utils.setDataRoot("regular-data");
        double 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;
        mass = 2500;
        double a = 7187990.1979844316;
        double e = 0.5e-4;
        double i = 1.7105407051081795;
        double omega = 1.9674147913622104;
        double OMEGA = FastMath.toRadians(261);
        double lv = 0;
        AbsoluteDate date = new AbsoluteDate(new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
        orbit = new KeplerianOrbit(a, e, i, omega, OMEGA, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
        OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
        attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
        propagator = new EcksteinHechlerPropagator(orbit, attitudeLaw, mass, ae, mu, c20, c30, c40, c50, c60);
    } catch (OrekitException oe) {
        Assert.fail(oe.getLocalizedMessage());
    }
}

Example 48 with DateComponents

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

the class PropagatorsParallelizerTest method setUp.

@Before
public void setUp() {
    try {
        Utils.setDataRoot("regular-data:potential/icgem-format");
        unnormalizedGravityField = GravityFieldFactory.getUnnormalizedProvider(6, 0);
        normalizedGravityField = GravityFieldFactory.getNormalizedProvider(6, 0);
        mass = 2500;
        double a = 7187990.1979844316;
        double e = 0.5e-4;
        double i = 1.7105407051081795;
        double omega = 1.9674147913622104;
        double OMEGA = FastMath.toRadians(261);
        double lv = 0;
        AbsoluteDate date = new AbsoluteDate(new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
        orbit = new KeplerianOrbit(a, e, i, omega, OMEGA, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, normalizedGravityField.getMu());
        OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
        attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
    } catch (OrekitException oe) {
        Assert.fail(oe.getLocalizedMessage());
    }
}

Example 49 with DateComponents

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

the class EphemerisTest method setUp.

@Before
public void setUp() throws IllegalArgumentException, OrekitException {
    Utils.setDataRoot("regular-data");
    initDate = new AbsoluteDate(new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
    finalDate = new AbsoluteDate(new DateComponents(2004, 01, 02), TimeComponents.H00, TimeScalesFactory.getUTC());
    double a = 7187990.1979844316;
    double e = 0.5e-4;
    double i = 1.7105407051081795;
    double omega = 1.9674147913622104;
    double OMEGA = FastMath.toRadians(261);
    double lv = 0;
    double mu = 3.9860047e14;
    inertialFrame = FramesFactory.getEME2000();
    Orbit initialState = new KeplerianOrbit(a, e, i, omega, OMEGA, lv, PositionAngle.TRUE, inertialFrame, initDate, mu);
    propagator = new KeplerianPropagator(initialState);
}

Example 50 with DateComponents

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

the class TLETest method testBug77TooLargeSatelliteNumber1.

@Test
public void testBug77TooLargeSatelliteNumber1() throws OrekitException {
    try {
        TLE tle = new TLE(1000000, 'U', 1971, 86, "J", 0, 908, new AbsoluteDate(new DateComponents(2012, 26), new TimeComponents(0.96078249 * Constants.JULIAN_DAY), TimeScalesFactory.getUTC()), taylorConvert(12.26882470, 1), taylorConvert(-0.00000004, 2), taylorConvert(0.00001e-9, 3), 0.0075476, FastMath.toRadians(74.0161), FastMath.toRadians(328.9888), FastMath.toRadians(228.9750), FastMath.toRadians(30.6709), 80454, 0.01234e-9);
        tle.getLine1();
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.TLE_INVALID_PARAMETER, oe.getSpecifier());
        Assert.assertEquals(1000000, ((Integer) oe.getParts()[0]).intValue());
        Assert.assertEquals("satelliteNumber-1", oe.getParts()[1]);
    }
}