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

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Example 1 with TLE

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

the class OrbitDeterminationTest 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.
        Transform t = FramesFactory.getTEME().getTransformTo(FramesFactory.getEME2000(), initDate.getDate());
        return new CartesianOrbit(t.transformPVCoordinates(initialState.getPVCoordinates()), 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);
    }
}
Also used : Frame(org.orekit.frames.Frame) TopocentricFrame(org.orekit.frames.TopocentricFrame) CartesianOrbit(org.orekit.orbits.CartesianOrbit) PositionAngle(org.orekit.orbits.PositionAngle) PVCoordinates(org.orekit.utils.PVCoordinates) TimeStampedPVCoordinates(org.orekit.utils.TimeStampedPVCoordinates) TLEPropagator(org.orekit.propagation.analytical.tle.TLEPropagator) TLE(org.orekit.propagation.analytical.tle.TLE) AbsoluteDate(org.orekit.time.AbsoluteDate) SpacecraftState(org.orekit.propagation.SpacecraftState) CircularOrbit(org.orekit.orbits.CircularOrbit) Vector3D(org.hipparchus.geometry.euclidean.threed.Vector3D) EquinoctialOrbit(org.orekit.orbits.EquinoctialOrbit) KeplerianOrbit(org.orekit.orbits.KeplerianOrbit) Transform(org.orekit.frames.Transform)

Example 2 with TLE

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

the class KalmanOrbitDeterminationTest 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.
        Transform t = FramesFactory.getTEME().getTransformTo(FramesFactory.getEME2000(), initDate.getDate());
        return new CartesianOrbit(t.transformPVCoordinates(initialState.getPVCoordinates()), 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);
    }
}
Also used : Frame(org.orekit.frames.Frame) TopocentricFrame(org.orekit.frames.TopocentricFrame) CartesianOrbit(org.orekit.orbits.CartesianOrbit) PositionAngle(org.orekit.orbits.PositionAngle) TimeStampedPVCoordinates(org.orekit.utils.TimeStampedPVCoordinates) PVCoordinates(org.orekit.utils.PVCoordinates) TLEPropagator(org.orekit.propagation.analytical.tle.TLEPropagator) TLE(org.orekit.propagation.analytical.tle.TLE) AbsoluteDate(org.orekit.time.AbsoluteDate) SpacecraftState(org.orekit.propagation.SpacecraftState) CircularOrbit(org.orekit.orbits.CircularOrbit) Vector3D(org.hipparchus.geometry.euclidean.threed.Vector3D) EquinoctialOrbit(org.orekit.orbits.EquinoctialOrbit) KeplerianOrbit(org.orekit.orbits.KeplerianOrbit) Transform(org.orekit.frames.Transform)

Example 3 with TLE

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

the class TrackCorridor method createPropagator.

/**
 * Create an orbit propagator for a TLE orbit
 * @param line1 firs line of the TLE
 * @param line2 second line of the TLE
 * @return an orbit propagator
 * @exception OrekitException if the TLE lines are corrupted (wrong checksums ...)
 */
private Propagator createPropagator(final String line1, final String line2) throws OrekitException {
    // create pseudo-orbit
    TLE tle = new TLE(line1, line2);
    // create propagator
    Propagator propagator = TLEPropagator.selectExtrapolator(tle);
    return propagator;
}
Also used : TLEPropagator(org.orekit.propagation.analytical.tle.TLEPropagator) EcksteinHechlerPropagator(org.orekit.propagation.analytical.EcksteinHechlerPropagator) Propagator(org.orekit.propagation.Propagator) TLE(org.orekit.propagation.analytical.tle.TLE)

Example 4 with TLE

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

the class TLEPropagatorBuilder method buildPropagator.

/**
 * {@inheritDoc}
 */
public Propagator buildPropagator(final double[] normalizedParameters) throws OrekitException {
    // create the orbit
    setParameters(normalizedParameters);
    final Orbit orbit = createInitialOrbit();
    // we really need a Keplerian orbit type
    final KeplerianOrbit kep = (KeplerianOrbit) OrbitType.KEPLERIAN.convertType(orbit);
    final TLE tle = new TLE(satelliteNumber, classification, launchYear, launchNumber, launchPiece, TLE.DEFAULT, elementNumber, orbit.getDate(), kep.getKeplerianMeanMotion(), 0.0, 0.0, kep.getE(), MathUtils.normalizeAngle(orbit.getI(), FastMath.PI), MathUtils.normalizeAngle(kep.getPerigeeArgument(), FastMath.PI), MathUtils.normalizeAngle(kep.getRightAscensionOfAscendingNode(), FastMath.PI), MathUtils.normalizeAngle(kep.getMeanAnomaly(), FastMath.PI), revolutionNumberAtEpoch, bStar);
    return TLEPropagator.selectExtrapolator(tle);
}
Also used : KeplerianOrbit(org.orekit.orbits.KeplerianOrbit) Orbit(org.orekit.orbits.Orbit) KeplerianOrbit(org.orekit.orbits.KeplerianOrbit) TLE(org.orekit.propagation.analytical.tle.TLE)

Example 5 with TLE

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

the class GPSPropagatorTest method testTLE.

@Test
public void testTLE() throws OrekitException {
    List<GPSPropagator> gpsPropagators = new ArrayList<GPSPropagator>();
    for (final GPSAlmanac almanac : almanacs) {
        gpsPropagators.add(new GPSPropagator.Builder(almanac).build());
    }
    // the following map corresponds to the GPS constellation status in early 2016
    final Map<Integer, TLE> prnToTLE = new HashMap<Integer, TLE>();
    prnToTLE.put(1, new TLE("1 37753U 11036A   16059.51505483 -.00000016  00000-0  00000+0 0  9995", "2 37753  55.2230 119.7200 0049958  23.9363 306.3749  2.00566105 33828"));
    prnToTLE.put(2, new TLE("1 28474U 04045A   16059.68518942 -.00000018 +00000-0 +00000-0 0  9992", "2 28474 054.0048 117.2153 0156693 236.8152 092.4773 02.00556694082981"));
    prnToTLE.put(3, new TLE("1 40294U 14068A   16059.64183862 +.00000012 +00000-0 +00000-0 0  9990", "2 40294 054.9632 179.3690 0003634 223.4011 136.5596 02.00553679009768"));
    prnToTLE.put(4, new TLE("1 34661U 09014A   16059.51658765 -.00000072  00000-0  00000+0 0  9997", "2 34661  56.3471   0.6400 0080177  48.0430 129.2467  2.00572451 50844"));
    prnToTLE.put(5, new TLE("1 35752U 09043A   16059.39819238  .00000011  00000-0  00000+0 0  9993", "2 35752  54.2243 178.7652 0044753  24.8598  29.4422  2.00555538 47893"));
    prnToTLE.put(6, new TLE("1 39741U 14026A   16059.18044747 -.00000016  00000-0  00000+0 0  9990", "2 39741  55.2140 119.2493 0005660 259.2190 100.7882  2.00566982 13061"));
    prnToTLE.put(7, new TLE("1 32711U 08012A   16059.36304856 -.00000033 +00000-0 +00000-0 0  9998", "2 32711 055.4269 300.7399 0091867 207.6311 151.9340 02.00564257058321"));
    prnToTLE.put(8, new TLE("1 40730U 15033A   16059.44106931 -.00000026 +00000-0 +00000-0 0  9994", "2 40730 055.1388 059.0069 0020452 282.1769 077.6168 02.00566073004562"));
    prnToTLE.put(9, new TLE("1 40105U 14045A   16059.27451329  .00000045  00000-0  00000+0 0  9996", "2 40105  54.7529 238.9873 0004485 121.4766 238.5557  2.00568637 11512"));
    prnToTLE.put(10, new TLE("1 41019U 15062A   16059.49433942  .00000013  00000-0  00000+0 0  9991", "2 41019  54.9785 179.1399 0012328 204.9013 155.0292  2.00561967  2382"));
    prnToTLE.put(11, new TLE("1 25933U 99055A   16059.51073770 -.00000024  00000-0  00000+0 0  9997", "2 25933  51.3239  98.4815 0159812  86.1576 266.7718  2.00565163120122"));
    prnToTLE.put(12, new TLE("1 29601U 06052A   16059.62966898 -.00000070 +00000-0 +00000-0 0  9994", "2 29601 056.7445 002.2755 0057667 037.0706 323.3313 02.00552237067968"));
    prnToTLE.put(13, new TLE("1 24876U 97035A   16059.41696335  .00000046  00000-0  00000+0 0  9998", "2 24876  55.6966 245.8203 0044339 114.8899 245.5712  2.00562657136305"));
    prnToTLE.put(14, new TLE("1 26605U 00071A   16059.56211888  .00000047  00000-0  00000+0 0  9997", "2 26605  55.2663 243.7251 0085518 248.7231  95.5323  2.00557009112094"));
    prnToTLE.put(15, new TLE("1 32260U 07047A   16059.45678257 +.00000044 +00000-0 +00000-0 0  9994", "2 32260 053.3641 236.0940 0079746 026.4105 333.9774 02.00547771061402"));
    prnToTLE.put(16, new TLE("1 27663U 03005A   16059.14440417 -.00000071  00000-0  00000+0 0  9996", "2 27663  56.7743   3.3691 0085346  17.6322 214.4333  2.00559487 95843"));
    prnToTLE.put(17, new TLE("1 28874U 05038A   16059.21070933 -.00000024  00000-0  00000+0 0  9997", "2 28874  55.8916  61.9596 0112077 248.9647 205.7384  2.00567116 76379"));
    prnToTLE.put(18, new TLE("1 26690U 01004A   16059.51332910  .00000008  00000-0  00000+0 0  9990", "2 26690  52.9999 177.6630 0169501 250.8579 153.6293  2.00563995110499"));
    prnToTLE.put(19, new TLE("1 28190U 04009A   16058.12363503 -.00000030  00000-0  00000+0 0  9999", "2 28190  55.7230  64.8110 0105865  40.0254 321.4519  2.00572212 87500"));
    prnToTLE.put(20, new TLE("1 26360U 00025A   16059.44770263  .00000005  00000-0  00000+0 0  9992", "2 26360  53.0712 174.6895 0046205  76.0615 334.4302  2.00559931115818"));
    prnToTLE.put(21, new TLE("1 27704U 03010A   16059.50719524 -.00000019  00000-0  00000+0 0  9998", "2 27704  53.6134 117.9454 0234081 255.6874 199.2128  2.00564673 94659"));
    prnToTLE.put(22, new TLE("1 28129U 03058A   16059.06680941  .00000008  00000-0  00000+0 0  9990", "2 28129  52.8771 177.7253 0079127 245.1376 114.0279  2.00398763 89357"));
    prnToTLE.put(23, new TLE("1 28361U 04023A   16059.54310021  .00000046  00000-0  00000+0 0  9995", "2 28361  54.2347 239.3240 0106509 211.5355  11.7648  2.00557932 85613"));
    prnToTLE.put(24, new TLE("1 38833U 12053A   16059.04618549 -.00000032  00000-0  00000+0 0  9999", "2 38833  54.4591 298.1383 0042253  18.7074 341.5041  2.00568407 24895"));
    prnToTLE.put(25, new TLE("1 36585U 10022A   16059.29300735 -.00000074  00000-0  00000+0 0  9993", "2 36585  56.0738 359.4320 0050768  38.3425  49.1794  2.00578535 42134"));
    prnToTLE.put(26, new TLE("1 40534U 15013A   16059.28299301 -.00000076  00000-0  00000+0 0  9994", "2 40534  55.0430 359.0082 0009349 342.4081  17.5685  2.00558853  6801"));
    prnToTLE.put(27, new TLE("1 39166U 13023A   16059.40401153 -.00000025  00000-0  00000+0 0  9990", "2 39166  55.6020  59.1224 0032420   7.7969 352.2759  2.00568484 20414"));
    prnToTLE.put(28, new TLE("1 26407U 00040A   16059.80383354 -.00000069 +00000-0 +00000-0 0  9994", "2 26407 056.6988 003.6328 0201499 267.0948 317.6209 02.00569902114508"));
    prnToTLE.put(29, new TLE("1 32384U 07062A   16059.44770263 -.00000021  00000-0  00000+0 0  9992", "2 32384  55.9456  62.5022 0011922 319.9531 172.6730  2.00571577 60128"));
    prnToTLE.put(30, new TLE("1 39533U 14008A   16059.40267873 -.00000038 +00000-0 +00000-0 0  9996", "2 39533 054.6126 303.3404 0017140 179.4267 180.6311 02.00568364014251"));
    prnToTLE.put(31, new TLE("1 29486U 06042A   16059.50651990 -.00000032  00000-0  00000+0 0  9992", "2 29486  55.7041 301.2472 0084115 334.2804 254.9897  2.00560606 69098"));
    prnToTLE.put(32, new TLE("1 41328U 16007A   16059.56873502  .00000049  00000-0  00000+0 0  9991", "2 41328  55.0137 239.0304 0002157 298.9074  61.0768  1.99172830   453"));
    for (final GPSPropagator gpsPropagator : gpsPropagators) {
        final int prn = gpsPropagator.getGPSOrbitalElements().getPRN();
        TLE tle = prnToTLE.get(prn);
        TLEPropagator tlePropagator = TLEPropagator.selectExtrapolator(tle);
        for (double dt = 0; dt < Constants.JULIAN_DAY; dt += 600) {
            final AbsoluteDate date = tlePropagator.getInitialState().getDate().shiftedBy(dt);
            final PVCoordinates gpsPV = gpsPropagator.getPVCoordinates(date, gpsPropagator.getECI());
            final PVCoordinates tlePV = tlePropagator.getPVCoordinates(date, gpsPropagator.getECI());
            Assert.assertEquals(0.0, Vector3D.distance(gpsPV.getPosition(), tlePV.getPosition()), 8400.0);
        }
    }
}
Also used : HashMap(java.util.HashMap) ArrayList(java.util.ArrayList) TimeStampedPVCoordinates(org.orekit.utils.TimeStampedPVCoordinates) PVCoordinates(org.orekit.utils.PVCoordinates) TLEPropagator(org.orekit.propagation.analytical.tle.TLEPropagator) TLE(org.orekit.propagation.analytical.tle.TLE) AbsoluteDate(org.orekit.time.AbsoluteDate) GPSAlmanac(org.orekit.gnss.GPSAlmanac) Test(org.junit.Test)

Aggregations

TLE (org.orekit.propagation.analytical.tle.TLE)10 TLEPropagator (org.orekit.propagation.analytical.tle.TLEPropagator)8 AbsoluteDate (org.orekit.time.AbsoluteDate)6 KeplerianOrbit (org.orekit.orbits.KeplerianOrbit)5 Vector3D (org.hipparchus.geometry.euclidean.threed.Vector3D)4 Frame (org.orekit.frames.Frame)4 Propagator (org.orekit.propagation.Propagator)4 SpacecraftState (org.orekit.propagation.SpacecraftState)4 PVCoordinates (org.orekit.utils.PVCoordinates)4 ArrayList (java.util.ArrayList)3 Test (org.junit.Test)3 TopocentricFrame (org.orekit.frames.TopocentricFrame)3 CartesianOrbit (org.orekit.orbits.CartesianOrbit)3 CircularOrbit (org.orekit.orbits.CircularOrbit)3 EquinoctialOrbit (org.orekit.orbits.EquinoctialOrbit)3 PositionAngle (org.orekit.orbits.PositionAngle)3 TimeStampedPVCoordinates (org.orekit.utils.TimeStampedPVCoordinates)3 Transform (org.orekit.frames.Transform)2 HashMap (java.util.HashMap)1 Before (org.junit.Before)1
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