Examples with TLE org.orekit.propagation.analytical.tle.TLE used on opensource projects

Example 6 with TLE

use of org.orekit.propagation.analytical.tle.TLE in project Orekit by CS-SI.

the class TLEConverterTest method checkFit.

protected void checkFit(final TLE tle, final double duration, final double stepSize, final double threshold, final boolean positionOnly, final boolean withBStar, final double expectedRMS) throws OrekitException {
    Propagator p = TLEPropagator.selectExtrapolator(tle);
    List<SpacecraftState> sample = new ArrayList<SpacecraftState>();
    for (double dt = 0; dt < duration; dt += stepSize) {
        sample.add(p.propagate(tle.getDate().shiftedBy(dt)));
    }
    TLEPropagatorBuilder builder = new TLEPropagatorBuilder(tle, PositionAngle.TRUE, 1.0);
    List<DelegatingDriver> drivers = builder.getPropagationParametersDrivers().getDrivers();
    // there should *not* be any drivers for central attraction coefficient (see issue #313)
    Assert.assertEquals(1, drivers.size());
    Assert.assertEquals("BSTAR", drivers.get(0).getName());
    FiniteDifferencePropagatorConverter fitter = new FiniteDifferencePropagatorConverter(builder, threshold, 1000);
    if (withBStar) {
        fitter.convert(sample, positionOnly, TLEPropagatorBuilder.B_STAR);
    } else {
        fitter.convert(sample, positionOnly);
    }
    TLEPropagator prop = (TLEPropagator) fitter.getAdaptedPropagator();
    TLE fitted = prop.getTLE();
    Assert.assertEquals(expectedRMS, fitter.getRMS(), 0.001 * expectedRMS);
    Assert.assertEquals(tle.getSatelliteNumber(), fitted.getSatelliteNumber());
    Assert.assertEquals(tle.getClassification(), fitted.getClassification());
    Assert.assertEquals(tle.getLaunchYear(), fitted.getLaunchYear());
    Assert.assertEquals(tle.getLaunchNumber(), fitted.getLaunchNumber());
    Assert.assertEquals(tle.getLaunchPiece(), fitted.getLaunchPiece());
    Assert.assertEquals(tle.getElementNumber(), fitted.getElementNumber());
    Assert.assertEquals(tle.getRevolutionNumberAtEpoch(), fitted.getRevolutionNumberAtEpoch());
    final double eps = 1.0e-5;
    Assert.assertEquals(tle.getMeanMotion(), fitted.getMeanMotion(), eps * tle.getMeanMotion());
    Assert.assertEquals(tle.getE(), fitted.getE(), eps * tle.getE());
    Assert.assertEquals(tle.getI(), fitted.getI(), eps * tle.getI());
    Assert.assertEquals(tle.getPerigeeArgument(), fitted.getPerigeeArgument(), eps * tle.getPerigeeArgument());
    Assert.assertEquals(tle.getRaan(), fitted.getRaan(), eps * tle.getRaan());
    Assert.assertEquals(tle.getMeanAnomaly(), fitted.getMeanAnomaly(), eps * tle.getMeanAnomaly());
    if (withBStar) {
        Assert.assertEquals(tle.getBStar(), fitted.getBStar(), eps * tle.getBStar());
    }
}

Example 7 with TLE

use of org.orekit.propagation.analytical.tle.TLE in project Orekit by CS-SI.

the class TLEConverterTest method setUp.

@Before
public void setUp() throws OrekitException {
    Utils.setDataRoot("regular-data");
    geoTLE = new TLE("1 27508U 02040A   12021.25695307 -.00000113  00000-0  10000-3 0  7326", "2 27508   0.0571 356.7800 0005033 344.4621 218.7816  1.00271798 34501");
    leoTLE = new TLE("1 31135U 07013A   11003.00000000  .00000816  00000+0  47577-4 0    11", "2 31135   2.4656 183.9084 0021119 236.4164  60.4567 15.10546832    15");
}

Example 8 with TLE

use of org.orekit.propagation.analytical.tle.TLE in project Orekit by CS-SI.

the class IodLambertTest method testMultiRevolutions.

@Test
public void testMultiRevolutions() throws OrekitException {
    Utils.setDataRoot("regular-data");
    TLE aussatB1 = new TLE("1 22087U 92054A   17084.21270512 -.00000243 +00000-0 +00000-0 0  9999", "2 22087 008.5687 046.5717 0005960 022.3650 173.1619 00.99207999101265");
    final Propagator propagator = TLEPropagator.selectExtrapolator(aussatB1);
    final Frame teme = FramesFactory.getTEME();
    final AbsoluteDate t1 = new AbsoluteDate("2017-03-25T23:48:31.282", TimeScalesFactory.getUTC());
    final Vector3D p1 = propagator.propagate(t1).getPVCoordinates(teme).getPosition();
    final AbsoluteDate t2 = t1.shiftedBy(40000);
    final Vector3D p2 = propagator.propagate(t2).getPVCoordinates(teme).getPosition();
    final AbsoluteDate t3 = t1.shiftedBy(115200.0);
    final Vector3D p3 = propagator.propagate(t3).getPVCoordinates(teme).getPosition();
    IodLambert lambert = new IodLambert(Constants.WGS84_EARTH_MU);
    KeplerianOrbit k0 = lambert.estimate(teme, true, 0, p1, t1, p2, t2);
    Assert.assertEquals(6.08e-4, k0.getE(), 1.0e-6);
    Assert.assertEquals(8.55, FastMath.toDegrees(k0.getI()), 0.01);
    Assert.assertEquals(0.0, Vector3D.distance(p1, k0.getPVCoordinates(t1, teme).getPosition()), 2.0e-8);
    Assert.assertEquals(0.0, Vector3D.distance(p2, k0.getPVCoordinates(t2, teme).getPosition()), 2.0e-7);
    KeplerianOrbit k1 = lambert.estimate(teme, false, 1, p1, t1, p3, t3);
    Assert.assertEquals(5.97e-4, k1.getE(), 1.0e-6);
    Assert.assertEquals(8.55, FastMath.toDegrees(k1.getI()), 0.01);
    Assert.assertEquals(0.0, Vector3D.distance(p1, k1.getPVCoordinates(t1, teme).getPosition()), 7.0e-9);
    Assert.assertEquals(0.0, Vector3D.distance(p3, k1.getPVCoordinates(t3, teme).getPosition()), 3.0e-7);
}

Example 9 with TLE

use of org.orekit.propagation.analytical.tle.TLE in project Orekit by CS-SI.

the class DOPComputerTest method testNotEnoughSV.

@Test(expected = OrekitException.class)
public void testNotEnoughSV() throws OrekitException {
    // Get the TLEs for 3 SV from the GPS constellation ...
    List<Propagator> gps = new ArrayList<Propagator>();
    gps.add(TLEPropagator.selectExtrapolator(new TLE("1 24876U 97035A   16084.84459975 -.00000010  00000-0  00000-0 0  9993", "2 24876  55.6874 244.8168 0043829 115.0986 245.3138  2.00562757137015")));
    gps.add(TLEPropagator.selectExtrapolator(new TLE("1 25933U 99055A   16085.52437157 -.00000002  00000-0  00000+0 0  9996", "2 25933  51.3408  97.3364 0160004  86.4308 330.0871  2.00564826120645")));
    gps.add(TLEPropagator.selectExtrapolator(new TLE("1 26360U 00025A   16085.38640501  .00000003  00000-0  00000+0 0  9993", "2 26360  53.0703 173.6078 0045232  76.6879 342.6592  2.00558759116334")));
    // Creates the computer
    final DOPComputer computer = DOPComputer.create(earth, location);
    // Defines the computation date
    final AbsoluteDate date = new AbsoluteDate(2016, 3, 27, 12, 0, 0., TimeScalesFactory.getUTC());
    // Computes the DOP with all the SV from the GPS constellation
    computer.compute(date, gps);
}

Example 10 with TLE

use of org.orekit.propagation.analytical.tle.TLE in project Orekit by CS-SI.

the class OrbitDetermination method createOrbit.

/**
 * Create an orbit from input parameters
 * @param parser input file parser
 * @param mu     central attraction coefficient
 * @throws NoSuchElementException if input parameters are missing
 * @throws OrekitException if inertial frame cannot be created
 */
private Orbit createOrbit(final KeyValueFileParser<ParameterKey> parser, final double mu) throws NoSuchElementException, OrekitException {
    final Frame frame;
    if (!parser.containsKey(ParameterKey.INERTIAL_FRAME)) {
        frame = FramesFactory.getEME2000();
    } else {
        frame = parser.getInertialFrame(ParameterKey.INERTIAL_FRAME);
    }
    // Orbit definition
    PositionAngle angleType = PositionAngle.MEAN;
    if (parser.containsKey(ParameterKey.ORBIT_ANGLE_TYPE)) {
        angleType = PositionAngle.valueOf(parser.getString(ParameterKey.ORBIT_ANGLE_TYPE).toUpperCase());
    }
    if (parser.containsKey(ParameterKey.ORBIT_KEPLERIAN_A)) {
        return new KeplerianOrbit(parser.getDouble(ParameterKey.ORBIT_KEPLERIAN_A), parser.getDouble(ParameterKey.ORBIT_KEPLERIAN_E), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_I), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_PA), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_RAAN), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_ANOMALY), angleType, frame, parser.getDate(ParameterKey.ORBIT_DATE, TimeScalesFactory.getUTC()), mu);
    } else if (parser.containsKey(ParameterKey.ORBIT_EQUINOCTIAL_A)) {
        return new EquinoctialOrbit(parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_A), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_EX), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_EY), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_HX), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_HY), parser.getAngle(ParameterKey.ORBIT_EQUINOCTIAL_LAMBDA), angleType, frame, parser.getDate(ParameterKey.ORBIT_DATE, TimeScalesFactory.getUTC()), mu);
    } else if (parser.containsKey(ParameterKey.ORBIT_CIRCULAR_A)) {
        return new CircularOrbit(parser.getDouble(ParameterKey.ORBIT_CIRCULAR_A), parser.getDouble(ParameterKey.ORBIT_CIRCULAR_EX), parser.getDouble(ParameterKey.ORBIT_CIRCULAR_EY), parser.getAngle(ParameterKey.ORBIT_CIRCULAR_I), parser.getAngle(ParameterKey.ORBIT_CIRCULAR_RAAN), parser.getAngle(ParameterKey.ORBIT_CIRCULAR_ALPHA), angleType, frame, parser.getDate(ParameterKey.ORBIT_DATE, TimeScalesFactory.getUTC()), mu);
    } else if (parser.containsKey(ParameterKey.ORBIT_TLE_LINE_1)) {
        final String line1 = parser.getString(ParameterKey.ORBIT_TLE_LINE_1);
        final String line2 = parser.getString(ParameterKey.ORBIT_TLE_LINE_2);
        final TLE tle = new TLE(line1, line2);
        TLEPropagator propagator = TLEPropagator.selectExtrapolator(tle);
        // propagator.setEphemerisMode();
        AbsoluteDate initDate = tle.getDate();
        SpacecraftState initialState = propagator.getInitialState();
        // Transformation from TEME to frame.
        return new CartesianOrbit(initialState.getPVCoordinates(FramesFactory.getEME2000()), frame, initDate, mu);
    } else {
        final double[] pos = { parser.getDouble(ParameterKey.ORBIT_CARTESIAN_PX), parser.getDouble(ParameterKey.ORBIT_CARTESIAN_PY), parser.getDouble(ParameterKey.ORBIT_CARTESIAN_PZ) };
        final double[] vel = { parser.getDouble(ParameterKey.ORBIT_CARTESIAN_VX), parser.getDouble(ParameterKey.ORBIT_CARTESIAN_VY), parser.getDouble(ParameterKey.ORBIT_CARTESIAN_VZ) };
        return new CartesianOrbit(new PVCoordinates(new Vector3D(pos), new Vector3D(vel)), frame, parser.getDate(ParameterKey.ORBIT_DATE, TimeScalesFactory.getUTC()), mu);
    }
}