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

Example 46 with AbsoluteDate

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

the class OEMParserTest method testParseOEM2.

@Test
public void testParseOEM2() throws OrekitException, URISyntaxException {
    final String name = getClass().getResource("/ccsds/OEMExample2.txt").toURI().getPath();
    OEMParser parser = new OEMParser().withConventions(IERSConventions.IERS_2010).withSimpleEOP(true).withMu(CelestialBodyFactory.getMars().getGM()).withInternationalDesignator(1996, 2, "A").withMissionReferenceDate(new AbsoluteDate("1996-12-17T00:00:00.000", TimeScalesFactory.getUTC()));
    final OEMFile file = parser.parse(name);
    final List<String> headerComment = new ArrayList<String>();
    headerComment.add("comment");
    Assert.assertEquals(headerComment, file.getHeaderComment());
    final List<String> metadataComment = new ArrayList<String>();
    metadataComment.add("comment 1");
    metadataComment.add("comment 2");
    Assert.assertEquals(metadataComment, file.getEphemeridesBlocks().get(0).getMetaData().getComment());
    Assert.assertEquals("TOD", file.getEphemeridesBlocks().get(0).getFrameString());
    Assert.assertEquals("EME2000", file.getEphemeridesBlocks().get(1).getFrameString());
    List<EphemeridesBlock> blocks = file.getEphemeridesBlocks();
    Assert.assertEquals(2, blocks.size());
    Assert.assertTrue(blocks.get(0).getHasRefFrameEpoch());
    Assert.assertEquals(129600.331, blocks.get(0).getStartTime().durationFrom(file.getMissionReferenceDate()), 1.0e-15);
    Assert.assertEquals(941347.267, blocks.get(1).getStartTime().durationFrom(file.getMissionReferenceDate()), 1.0e-15);
}

Example 47 with AbsoluteDate

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

the class OMMParserTest method testParseOMM1.

@Test
public void testParseOMM1() throws OrekitException {
    // simple test for OMM file, contains p/v entries and other mandatory
    // data.
    final String ex = "/ccsds/OMMExample.txt";
    // initialize parser with purposely wrong international designator
    // (in order to check it is correctly overridden when parsing)
    final OMMParser parser = new OMMParser().withMu(398600e9).withInternationalDesignator(1998, 1, "a");
    final InputStream inEntry = getClass().getResourceAsStream(ex);
    final OMMFile file = parser.parse(inEntry);
    // Check Header Block;
    Assert.assertEquals(2.0, file.getFormatVersion(), 1.0e-10);
    Assert.assertEquals(new AbsoluteDate(2007, 03, 06, 16, 00, 00, TimeScalesFactory.getUTC()), file.getCreationDate());
    Assert.assertEquals("NOAA/USA", file.getOriginator());
    // Check Metadata Block;
    Assert.assertEquals("GOES 9", file.getMetaData().getObjectName());
    Assert.assertEquals("1995-025A", file.getMetaData().getObjectID());
    Assert.assertEquals("EARTH", file.getMetaData().getCenterName());
    Assert.assertTrue(file.getMetaData().getHasCreatableBody());
    Assert.assertEquals(file.getMetaData().getCenterBody(), CelestialBodyFactory.getEarth());
    Assert.assertEquals(file.getMetaData().getFrame(), FramesFactory.getTEME());
    Assert.assertEquals(file.getMetaData().getTimeSystem(), CcsdsTimeScale.UTC);
    Assert.assertEquals("SGP/SGP4", file.getMetaData().getMeanElementTheory());
    Assert.assertEquals("TEME", file.getMetaData().getFrame().toString());
    Assert.assertTrue(file.getTLERelatedParametersComment().isEmpty());
    // Check Mean Keplerian elements data block;
    Assert.assertEquals(new AbsoluteDate(2007, 03, 05, 10, 34, 41.4264, TimeScalesFactory.getUTC()), file.getEpoch());
    Assert.assertEquals(file.getMeanMotion(), 1.00273272 * FastMath.PI / 43200.0, 1e-10);
    Assert.assertEquals(file.getE(), 0.0005013, 1e-10);
    Assert.assertEquals(file.getI(), FastMath.toRadians(3.0539), 1e-10);
    Assert.assertEquals(file.getRaan(), FastMath.toRadians(81.7939), 1e-10);
    Assert.assertEquals(file.getPa(), FastMath.toRadians(249.2363), 1e-10);
    Assert.assertEquals(file.getAnomaly(), FastMath.toRadians(150.1602), 1e-10);
    Assert.assertEquals(file.getMuParsed(), 398600.8 * 1e9, 1e-10);
    Assert.assertEquals(file.getMuSet(), 398600e9, 1e-10);
    Assert.assertEquals(file.getMuCreated(), CelestialBodyFactory.getEarth().getGM(), 1e-10);
    // Check TLE Related Parameters data block;
    Assert.assertEquals(0, file.getEphemerisType());
    Assert.assertEquals('U', file.getClassificationType());
    int[] noradIDExpected = new int[23581];
    int[] noradIDActual = new int[file.getNoradID()];
    Assert.assertEquals(noradIDExpected[0], noradIDActual[0]);
    Assert.assertEquals("0925", file.getElementSetNumber());
    int[] revAtEpochExpected = new int[4316];
    int[] revAtEpochActual = new int[file.getRevAtEpoch()];
    Assert.assertEquals(1.00273272 * FastMath.PI / 43200.0, file.getMeanMotion(), 1e-10);
    Assert.assertEquals(revAtEpochExpected[0], revAtEpochActual[0]);
    Assert.assertEquals(file.getBStar(), 0.0001, 1e-10);
    Assert.assertEquals(file.getMeanMotionDot(), -0.00000113 * FastMath.PI / 1.86624e9, 1e-12);
    Assert.assertEquals(file.getMeanMotionDotDot(), 0.0 * FastMath.PI / 5.3747712e13, 1e-10);
    Assert.assertEquals(1995, file.getMetaData().getLaunchYear());
    Assert.assertEquals(25, file.getMetaData().getLaunchNumber());
    Assert.assertEquals("A", file.getMetaData().getLaunchPiece());
    file.generateCartesianOrbit();
    file.generateKeplerianOrbit();
    try {
        file.generateSpacecraftState();
    } catch (OrekitException orekitException) {
        Assert.assertEquals(OrekitMessages.CCSDS_UNKNOWN_SPACECRAFT_MASS, orekitException.getSpecifier());
    } finally {
    }
    file.generateTLE();
}

Example 48 with AbsoluteDate

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

the class OPMParserTest method testParseOPM1.

@Test
public void testParseOPM1() throws OrekitException {
    // simple test for OPM file, contains p/v entries and other mandatory
    // data.
    final String ex = "/ccsds/OPMExample.txt";
    final OPMParser parser = new OPMParser().withMu(398600e9).withConventions(IERSConventions.IERS_2010).withSimpleEOP(true);
    final InputStream inEntry = getClass().getResourceAsStream(ex);
    final OPMFile file = parser.parse(inEntry, "OPMExample.txt");
    Assert.assertEquals(IERSConventions.IERS_2010, file.getConventions());
    // Check Header Block;
    Assert.assertEquals(2.0, file.getFormatVersion(), 1.0e-10);
    Assert.assertEquals(new AbsoluteDate(1998, 11, 06, 9, 23, 57, TimeScalesFactory.getUTC()), file.getCreationDate());
    Assert.assertEquals("JAXA", file.getOriginator());
    // Check Metadata Block;
    Assert.assertEquals("GODZILLA 5", file.getMetaData().getObjectName());
    Assert.assertEquals("1998-057A", file.getMetaData().getObjectID());
    Assert.assertEquals(1998, file.getMetaData().getLaunchYear());
    Assert.assertEquals(57, file.getMetaData().getLaunchNumber());
    Assert.assertEquals("A", file.getMetaData().getLaunchPiece());
    Assert.assertEquals("EARTH", file.getMetaData().getCenterName());
    Assert.assertTrue(file.getMetaData().getHasCreatableBody());
    Assert.assertEquals(CelestialBodyFactory.getEarth(), file.getMetaData().getCenterBody());
    Assert.assertEquals(CCSDSFrame.ITRF97.toString(), file.getMetaData().getFrame().getName());
    Assert.assertEquals(CcsdsTimeScale.TAI, file.getMetaData().getTimeSystem());
    Assert.assertFalse(file.hasCovarianceMatrix());
    // Check State Vector data Block;
    Assert.assertEquals(new AbsoluteDate(1998, 12, 18, 14, 28, 15.1172, TimeScalesFactory.getTAI()), file.getEpoch());
    checkPVEntry(new PVCoordinates(new Vector3D(6503514.000, 1239647.000, -717490.000), new Vector3D(-873.160, 8740.420, -4191.076)), file.getPVCoordinates());
    try {
        file.generateCartesianOrbit();
        Assert.fail("an exception should have been thrown");
    } catch (OrekitIllegalArgumentException oiae) {
        Assert.assertEquals(OrekitMessages.NON_PSEUDO_INERTIAL_FRAME, oiae.getSpecifier());
        Assert.assertEquals("ITRF97", oiae.getParts()[0]);
    }
    try {
        file.generateKeplerianOrbit();
        Assert.fail("an exception should have been thrown");
    } catch (OrekitIllegalArgumentException oiae) {
        Assert.assertEquals(OrekitMessages.NON_PSEUDO_INERTIAL_FRAME, oiae.getSpecifier());
        Assert.assertEquals("ITRF97", oiae.getParts()[0]);
    }
    try {
        file.generateSpacecraftState();
        Assert.fail("an exception should have been thrown");
    } catch (OrekitIllegalArgumentException oiae) {
        Assert.assertEquals(OrekitMessages.NON_PSEUDO_INERTIAL_FRAME, oiae.getSpecifier());
        Assert.assertEquals("ITRF97", oiae.getParts()[0]);
    }
}

Example 49 with AbsoluteDate

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

the class OPMParserTest method testParseOPM4.

@Test
public void testParseOPM4() throws OrekitException {
    // 
    final String ex = "/ccsds/OPMExample4.txt";
    OPMParser parser = new OPMParser().withMissionReferenceDate(new AbsoluteDate()).withConventions(IERSConventions.IERS_2010);
    final InputStream inEntry = getClass().getResourceAsStream(ex);
    final OPMFile file = parser.parse(inEntry, "OPMExample4.txt");
    file.getMetaData().getFrame().toString();
    file.getMetaData().getObjectID();
    file.getEpoch();
    file.getPVCoordinates();
    file.getMetaData().getFrame();
}

Example 50 with AbsoluteDate

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

the class OPMParserTest method testParseOPM2.

@Test
public void testParseOPM2() throws OrekitException {
    // simple test for OPM file, contains all mandatory information plus
    // Keplerian elements, Spacecraft parameters and 2 maneuvers.
    final String ex = "/ccsds/OPMExample2.txt";
    final OPMParser parser = new OPMParser();
    final InputStream inEntry = getClass().getResourceAsStream(ex);
    final OPMFile file = parser.parse(inEntry, "OPMExample2.txt");
    try {
        file.getConventions();
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.CCSDS_UNKNOWN_CONVENTIONS, oe.getSpecifier());
    }
    // Check Header Block;
    Assert.assertEquals(2.0, file.getFormatVersion(), 1.0e-10);
    ArrayList<String> headerComment = new ArrayList<String>();
    headerComment.add("Generated by GSOC, R. Kiehling");
    headerComment.add("Current intermediate orbit IO2 and maneuver planning data");
    Assert.assertEquals(headerComment, file.getHeaderComment());
    Assert.assertEquals(new AbsoluteDate(2000, 06, 03, 05, 33, 00, TimeScalesFactory.getUTC()), file.getCreationDate());
    Assert.assertEquals(file.getOriginator(), "GSOC");
    // Check Metadata Block;
    Assert.assertEquals("EUTELSAT W4", file.getMetaData().getObjectName());
    Assert.assertEquals("2000-028A", file.getMetaData().getObjectID());
    Assert.assertEquals("EARTH", file.getMetaData().getCenterName());
    Assert.assertTrue(file.getMetaData().getHasCreatableBody());
    Assert.assertEquals(CelestialBodyFactory.getEarth(), file.getMetaData().getCenterBody());
    Assert.assertEquals(FramesFactory.getGCRF(), file.getMetaData().getFrame());
    Assert.assertEquals(CcsdsTimeScale.GPS, file.getMetaData().getTimeSystem());
    Assert.assertEquals(0, file.getMetaDataComment().size());
    // Check Data State Vector block
    ArrayList<String> epochComment = new ArrayList<String>();
    epochComment.add("State Vector");
    Assert.assertEquals(epochComment, file.getEpochComment());
    Assert.assertEquals(new AbsoluteDate(2006, 06, 03, 00, 00, 00, TimeScalesFactory.getGPS()), file.getEpoch());
    checkPVEntry(new PVCoordinates(new Vector3D(6655994.2, -40218575.1, -82917.7), new Vector3D(3115.48208, 470.42605, -1.01495)), file.getPVCoordinates());
    // Check Data Keplerian Elements block
    Assert.assertTrue(file.hasKeplerianElements());
    ArrayList<String> keplerianElementsComment = new ArrayList<String>();
    keplerianElementsComment.add("Keplerian elements");
    Assert.assertEquals(keplerianElementsComment, file.getKeplerianElementsComment());
    Assert.assertEquals(41399512.3, file.getA(), 1e-6);
    Assert.assertEquals(0.020842611, file.getE(), 1e-10);
    Assert.assertEquals(FastMath.toRadians(0.117746), file.getI(), 1e-10);
    Assert.assertEquals(FastMath.toRadians(17.604721), file.getRaan(), 1e-10);
    Assert.assertEquals(FastMath.toRadians(218.242943), file.getPa(), 1e-10);
    Assert.assertEquals(PositionAngle.TRUE, file.getAnomalyType());
    Assert.assertEquals(FastMath.toRadians(41.922339), file.getAnomaly(), 1e-10);
    Assert.assertEquals(398600.4415 * 1e9, file.getMuParsed(), 1e-10);
    // Check Data Spacecraft block
    ArrayList<String> spacecraftComment = new ArrayList<String>();
    spacecraftComment.add("Spacecraft parameters");
    Assert.assertEquals(spacecraftComment, file.getSpacecraftComment());
    Assert.assertEquals(1913.000, file.getMass(), 1e-10);
    Assert.assertEquals(10.000, file.getSolarRadArea(), 1e-10);
    Assert.assertEquals(1.300, file.getSolarRadCoeff(), 1e-10);
    Assert.assertEquals(10.000, file.getDragArea(), 1e-10);
    Assert.assertEquals(2.300, file.getDragCoeff(), 1e-10);
    // Check Data Maneuvers block
    Assert.assertTrue(file.getHasManeuver());
    Assert.assertEquals(3, file.getNbManeuvers());
    ArrayList<String> stateManeuverComment0 = new ArrayList<String>();
    stateManeuverComment0.add("2 planned maneuvers");
    stateManeuverComment0.add("First maneuver: AMF-3");
    stateManeuverComment0.add("Non-impulsive, thrust direction fixed in inertial frame");
    Assert.assertEquals(stateManeuverComment0, file.getManeuver(0).getComment());
    Assert.assertEquals(new AbsoluteDate(2000, 06, 03, 9, 00, 34.1, TimeScalesFactory.getGPS()), file.getManeuvers().get(0).getEpochIgnition());
    Assert.assertEquals(132.6, file.getManeuver(0).getDuration(), 1e-10);
    Assert.assertEquals(-18.418, file.getManeuver(0).getDeltaMass(), 1e-10);
    Assert.assertNull(file.getManeuver(0).getRefLofType());
    Assert.assertEquals(FramesFactory.getEME2000(), file.getManeuver(0).getRefFrame());
    Assert.assertEquals(0.0, new Vector3D(-23.25700, 16.83160, -8.93444).distance(file.getManeuver(0).getDV()), 1.0e-10);
    ArrayList<String> stateManeuverComment1 = new ArrayList<String>();
    stateManeuverComment1.add("Second maneuver: first station acquisition maneuver");
    stateManeuverComment1.add("impulsive, thrust direction fixed in RTN frame");
    Assert.assertEquals(stateManeuverComment1, file.getManeuver(1).getComment());
    Assert.assertEquals(new AbsoluteDate(2000, 06, 05, 18, 59, 21, TimeScalesFactory.getGPS()), file.getManeuvers().get(1).getEpochIgnition());
    Assert.assertEquals(0.0, file.getManeuver(1).getDuration(), 1e-10);
    Assert.assertEquals(-1.469, file.getManeuver(1).getDeltaMass(), 1e-10);
    Assert.assertEquals(LOFType.QSW, file.getManeuver(1).getRefLofType());
    Assert.assertNull(file.getManeuver(1).getRefFrame());
    Assert.assertEquals(0.0, new Vector3D(1.015, -1.873, 0.0).distance(file.getManeuver(1).getDV()), 1.0e-10);
    Assert.assertTrue(file.getManeuver(2).getComment().isEmpty());
    Assert.assertEquals(new AbsoluteDate(2000, 06, 05, 18, 59, 51, TimeScalesFactory.getGPS()), file.getManeuvers().get(2).getEpochIgnition());
    Assert.assertEquals(0.0, file.getManeuver(2).getDuration(), 1e-10);
    Assert.assertEquals(-1.469, file.getManeuver(2).getDeltaMass(), 1e-10);
    Assert.assertEquals(LOFType.QSW, file.getManeuver(2).getRefLofType());
    Assert.assertNull(file.getManeuver(2).getRefFrame());
    Assert.assertEquals(0.0, new Vector3D(1.015, -1.873, 0.0).distance(file.getManeuver(2).getDV()), 1.0e-10);
    file.generateCartesianOrbit();
    file.generateKeplerianOrbit();
    file.generateSpacecraftState();
}