Examples with CelestialBody org.orekit.bodies.CelestialBody used on opensource projects

Example 31 with CelestialBody

use of org.orekit.bodies.CelestialBody in project Orekit by CS-SI.

the class BoxAndSolarArraySpacecraftTest method testParametersDrivers.

@Test
public void testParametersDrivers() throws OrekitException {
    CelestialBody sun = CelestialBodyFactory.getSun();
    BoxAndSolarArraySpacecraft.Facet[] facets = new BoxAndSolarArraySpacecraft.Facet[] { new BoxAndSolarArraySpacecraft.Facet(Vector3D.MINUS_I, 3.0), new BoxAndSolarArraySpacecraft.Facet(Vector3D.PLUS_I, 3.0), new BoxAndSolarArraySpacecraft.Facet(Vector3D.MINUS_J, 3.0), new BoxAndSolarArraySpacecraft.Facet(Vector3D.PLUS_J, 3.0), new BoxAndSolarArraySpacecraft.Facet(Vector3D.MINUS_K, 3.0), new BoxAndSolarArraySpacecraft.Facet(Vector3D.PLUS_K, 3.0) };
    BoxAndSolarArraySpacecraft s1 = new BoxAndSolarArraySpacecraft(1.5, 3.5, 2.5, sun, 20.0, Vector3D.PLUS_J, 2.0, 0.8, 0.1);
    Assert.assertEquals(1, s1.getDragParametersDrivers().length);
    Assert.assertEquals(DragSensitive.DRAG_COEFFICIENT, s1.getDragParametersDrivers()[0].getName());
    Assert.assertEquals(2.0, s1.getDragParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(2, s1.getRadiationParametersDrivers().length);
    Assert.assertEquals(RadiationSensitive.ABSORPTION_COEFFICIENT, s1.getRadiationParametersDrivers()[0].getName());
    Assert.assertEquals(0.8, s1.getRadiationParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(RadiationSensitive.REFLECTION_COEFFICIENT, s1.getRadiationParametersDrivers()[1].getName());
    Assert.assertEquals(0.1, s1.getRadiationParametersDrivers()[1].getValue(), 1.0e-15);
    BoxAndSolarArraySpacecraft s2 = new BoxAndSolarArraySpacecraft(1.5, 3.5, 2.5, sun, 20.0, Vector3D.PLUS_J, 2.0, 0.4, 0.8, 0.1);
    Assert.assertEquals(2, s2.getDragParametersDrivers().length);
    Assert.assertEquals(DragSensitive.DRAG_COEFFICIENT, s2.getDragParametersDrivers()[0].getName());
    Assert.assertEquals(2.0, s2.getDragParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(DragSensitive.LIFT_RATIO, s2.getDragParametersDrivers()[1].getName());
    Assert.assertEquals(0.4, s2.getDragParametersDrivers()[1].getValue(), 1.0e-15);
    Assert.assertEquals(2, s2.getRadiationParametersDrivers().length);
    Assert.assertEquals(RadiationSensitive.ABSORPTION_COEFFICIENT, s2.getRadiationParametersDrivers()[0].getName());
    Assert.assertEquals(0.8, s2.getRadiationParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(RadiationSensitive.REFLECTION_COEFFICIENT, s2.getRadiationParametersDrivers()[1].getName());
    Assert.assertEquals(0.1, s2.getRadiationParametersDrivers()[1].getValue(), 1.0e-15);
    BoxAndSolarArraySpacecraft s3 = new BoxAndSolarArraySpacecraft(facets, sun, 20.0, Vector3D.PLUS_J, 2.0, 0.8, 0.1);
    Assert.assertEquals(1, s3.getDragParametersDrivers().length);
    Assert.assertEquals(DragSensitive.DRAG_COEFFICIENT, s3.getDragParametersDrivers()[0].getName());
    Assert.assertEquals(2.0, s3.getDragParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(2, s3.getRadiationParametersDrivers().length);
    Assert.assertEquals(RadiationSensitive.ABSORPTION_COEFFICIENT, s3.getRadiationParametersDrivers()[0].getName());
    Assert.assertEquals(0.8, s3.getRadiationParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(RadiationSensitive.REFLECTION_COEFFICIENT, s3.getRadiationParametersDrivers()[1].getName());
    Assert.assertEquals(0.1, s3.getRadiationParametersDrivers()[1].getValue(), 1.0e-15);
    BoxAndSolarArraySpacecraft s4 = new BoxAndSolarArraySpacecraft(facets, sun, 20.0, Vector3D.PLUS_J, 2.0, 0.4, 0.8, 0.1);
    Assert.assertEquals(2, s4.getDragParametersDrivers().length);
    Assert.assertEquals(DragSensitive.DRAG_COEFFICIENT, s4.getDragParametersDrivers()[0].getName());
    Assert.assertEquals(2.0, s4.getDragParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(DragSensitive.LIFT_RATIO, s4.getDragParametersDrivers()[1].getName());
    Assert.assertEquals(0.4, s4.getDragParametersDrivers()[1].getValue(), 1.0e-15);
    Assert.assertEquals(2, s4.getRadiationParametersDrivers().length);
    Assert.assertEquals(RadiationSensitive.ABSORPTION_COEFFICIENT, s4.getRadiationParametersDrivers()[0].getName());
    Assert.assertEquals(0.8, s4.getRadiationParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(RadiationSensitive.REFLECTION_COEFFICIENT, s4.getRadiationParametersDrivers()[1].getName());
    Assert.assertEquals(0.1, s4.getRadiationParametersDrivers()[1].getValue(), 1.0e-15);
    BoxAndSolarArraySpacecraft s5 = new BoxAndSolarArraySpacecraft(1.5, 3.5, 2.5, sun, 20.0, Vector3D.PLUS_J, AbsoluteDate.J2000_EPOCH, Vector3D.PLUS_I, 7.292e-5, 2.0, 0.8, 0.1);
    Assert.assertEquals(1, s5.getDragParametersDrivers().length);
    Assert.assertEquals(DragSensitive.DRAG_COEFFICIENT, s5.getDragParametersDrivers()[0].getName());
    Assert.assertEquals(2.0, s5.getDragParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(2, s5.getRadiationParametersDrivers().length);
    Assert.assertEquals(RadiationSensitive.ABSORPTION_COEFFICIENT, s5.getRadiationParametersDrivers()[0].getName());
    Assert.assertEquals(0.8, s5.getRadiationParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(RadiationSensitive.REFLECTION_COEFFICIENT, s5.getRadiationParametersDrivers()[1].getName());
    Assert.assertEquals(0.1, s5.getRadiationParametersDrivers()[1].getValue(), 1.0e-15);
    BoxAndSolarArraySpacecraft s6 = new BoxAndSolarArraySpacecraft(1.5, 3.5, 2.5, sun, 20.0, Vector3D.PLUS_J, AbsoluteDate.J2000_EPOCH, Vector3D.PLUS_I, 7.292e-5, 2.0, 0.4, 0.8, 0.1);
    Assert.assertEquals(2, s6.getDragParametersDrivers().length);
    Assert.assertEquals(DragSensitive.DRAG_COEFFICIENT, s6.getDragParametersDrivers()[0].getName());
    Assert.assertEquals(2.0, s6.getDragParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(DragSensitive.LIFT_RATIO, s6.getDragParametersDrivers()[1].getName());
    Assert.assertEquals(0.4, s6.getDragParametersDrivers()[1].getValue(), 1.0e-15);
    Assert.assertEquals(2, s6.getRadiationParametersDrivers().length);
    Assert.assertEquals(RadiationSensitive.ABSORPTION_COEFFICIENT, s6.getRadiationParametersDrivers()[0].getName());
    Assert.assertEquals(0.8, s6.getRadiationParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(RadiationSensitive.REFLECTION_COEFFICIENT, s6.getRadiationParametersDrivers()[1].getName());
    Assert.assertEquals(0.1, s6.getRadiationParametersDrivers()[1].getValue(), 1.0e-15);
    BoxAndSolarArraySpacecraft s7 = new BoxAndSolarArraySpacecraft(facets, sun, 20.0, Vector3D.PLUS_J, AbsoluteDate.J2000_EPOCH, Vector3D.PLUS_I, 7.292e-5, 2.0, 0.8, 0.1);
    Assert.assertEquals(1, s7.getDragParametersDrivers().length);
    Assert.assertEquals(DragSensitive.DRAG_COEFFICIENT, s7.getDragParametersDrivers()[0].getName());
    Assert.assertEquals(2.0, s7.getDragParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(2, s7.getRadiationParametersDrivers().length);
    Assert.assertEquals(RadiationSensitive.ABSORPTION_COEFFICIENT, s7.getRadiationParametersDrivers()[0].getName());
    Assert.assertEquals(0.8, s7.getRadiationParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(RadiationSensitive.REFLECTION_COEFFICIENT, s7.getRadiationParametersDrivers()[1].getName());
    Assert.assertEquals(0.1, s7.getRadiationParametersDrivers()[1].getValue(), 1.0e-15);
    BoxAndSolarArraySpacecraft s8 = new BoxAndSolarArraySpacecraft(facets, sun, 20.0, Vector3D.PLUS_J, AbsoluteDate.J2000_EPOCH, Vector3D.PLUS_I, 7.292e-5, 2.0, 0.4, 0.8, 0.1);
    Assert.assertEquals(2, s8.getDragParametersDrivers().length);
    Assert.assertEquals(DragSensitive.DRAG_COEFFICIENT, s8.getDragParametersDrivers()[0].getName());
    Assert.assertEquals(2.0, s8.getDragParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(DragSensitive.LIFT_RATIO, s8.getDragParametersDrivers()[1].getName());
    Assert.assertEquals(0.4, s8.getDragParametersDrivers()[1].getValue(), 1.0e-15);
    Assert.assertEquals(2, s8.getRadiationParametersDrivers().length);
    Assert.assertEquals(RadiationSensitive.ABSORPTION_COEFFICIENT, s8.getRadiationParametersDrivers()[0].getName());
    Assert.assertEquals(0.8, s8.getRadiationParametersDrivers()[0].getValue(), 1.0e-15);
    Assert.assertEquals(RadiationSensitive.REFLECTION_COEFFICIENT, s8.getRadiationParametersDrivers()[1].getName());
    Assert.assertEquals(0.1, s8.getRadiationParametersDrivers()[1].getValue(), 1.0e-15);
}

Example 32 with CelestialBody

use of org.orekit.bodies.CelestialBody in project Orekit by CS-SI.

the class OrekitEphemerisFileTest method testWritingToOEM.

@Test
public void testWritingToOEM() throws OrekitException, IOException {
    final double muTolerance = 1e-12;
    final double positionTolerance = 1e-8;
    final double velocityTolerance = 1e-8;
    final String satId = "SATELLITE1";
    final double sma = 10000000;
    final double inc = Math.toRadians(45.0);
    final double ecc = 0.001;
    final double raan = 0.0;
    final double pa = 0.0;
    final double ta = 0.0;
    final AbsoluteDate date = new AbsoluteDate();
    final Frame frame = FramesFactory.getGCRF();
    final CelestialBody body = CelestialBodyFactory.getEarth();
    final double mu = body.getGM();
    KeplerianOrbit initialOrbit = new KeplerianOrbit(sma, ecc, inc, pa, raan, ta, PositionAngle.TRUE, frame, date, mu);
    KeplerianPropagator propagator = new KeplerianPropagator(initialOrbit);
    final double propagationDurationSeconds = 86400.0;
    final double stepSizeSeconds = 60.0;
    List<SpacecraftState> states = new ArrayList<SpacecraftState>();
    for (double dt = 0.0; dt < propagationDurationSeconds; dt += stepSizeSeconds) {
        states.add(propagator.propagate(date.shiftedBy(dt)));
    }
    OrekitEphemerisFile ephemerisFile = new OrekitEphemerisFile();
    OrekitSatelliteEphemeris satellite = ephemerisFile.addSatellite(satId);
    satellite.addNewSegment(states);
    String tempOemFile = Files.createTempFile("OrekitEphemerisFileTest", ".oem").toString();
    new OEMWriter().write(tempOemFile, ephemerisFile);
    EphemerisFile ephemerisFromFile = new OEMParser().parse(tempOemFile);
    Files.delete(Paths.get(tempOemFile));
    EphemerisSegment segment = ephemerisFromFile.getSatellites().get(satId).getSegments().get(0);
    assertEquals(states.get(0).getDate(), segment.getStart());
    assertEquals(states.get(states.size() - 1).getDate(), segment.getStop());
    assertEquals(states.size(), segment.getCoordinates().size());
    assertEquals(frame, segment.getFrame());
    assertEquals(body.getName().toUpperCase(), segment.getFrameCenterString());
    assertEquals(body.getGM(), segment.getMu(), muTolerance);
    for (int i = 0; i < states.size(); i++) {
        TimeStampedPVCoordinates expected = states.get(i).getPVCoordinates();
        TimeStampedPVCoordinates actual = segment.getCoordinates().get(i);
        assertEquals(expected.getDate(), actual.getDate());
        assertEquals(0.0, Vector3D.distance(expected.getPosition(), actual.getPosition()), positionTolerance);
        assertEquals(0.0, Vector3D.distance(expected.getVelocity(), actual.getVelocity()), velocityTolerance);
    }
    // test ingested ephemeris generates access intervals
    final OneAxisEllipsoid parentShape = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final double latitude = 0.0;
    final double longitude = 0.0;
    final double altitude = 0.0;
    final GeodeticPoint point = new GeodeticPoint(latitude, longitude, altitude);
    final TopocentricFrame topo = new TopocentricFrame(parentShape, point, "testPoint1");
    final ElevationDetector elevationDetector = new ElevationDetector(topo);
    final EphemerisSegmentPropagator ephemerisSegmentPropagator = new EphemerisSegmentPropagator(segment);
    final EventsLogger lookupLogger = new EventsLogger();
    ephemerisSegmentPropagator.addEventDetector(lookupLogger.monitorDetector(elevationDetector));
    final EventsLogger referenceLogger = new EventsLogger();
    propagator.clearEventsDetectors();
    propagator.addEventDetector(referenceLogger.monitorDetector(elevationDetector));
    propagator.propagate(segment.getStart(), segment.getStop());
    ephemerisSegmentPropagator.propagate(segment.getStart(), segment.getStop());
    final double dateEpsilon = 1.0e-9;
    assertTrue(referenceLogger.getLoggedEvents().size() > 0);
    assertEquals(referenceLogger.getLoggedEvents().size(), lookupLogger.getLoggedEvents().size());
    for (int i = 0; i < referenceLogger.getLoggedEvents().size(); i++) {
        LoggedEvent reference = referenceLogger.getLoggedEvents().get(i);
        LoggedEvent actual = lookupLogger.getLoggedEvents().get(i);
        assertEquals(0.0, FastMath.abs(reference.getState().getDate().durationFrom(actual.getState().getDate())), dateEpsilon);
    }
    final Propagator embeddedPropagator = segment.getPropagator();
    final EventsLogger embeddedPropLogger = new EventsLogger();
    embeddedPropagator.addEventDetector(embeddedPropLogger.monitorDetector(elevationDetector));
    embeddedPropagator.propagate(segment.getStart(), segment.getStop());
    assertEquals(referenceLogger.getLoggedEvents().size(), embeddedPropLogger.getLoggedEvents().size());
    for (int i = 0; i < referenceLogger.getLoggedEvents().size(); i++) {
        LoggedEvent reference = referenceLogger.getLoggedEvents().get(i);
        LoggedEvent actual = embeddedPropLogger.getLoggedEvents().get(i);
        assertEquals(0.0, FastMath.abs(reference.getState().getDate().durationFrom(actual.getState().getDate())), dateEpsilon);
    }
    final List<SpacecraftState> readInStates = new ArrayList<SpacecraftState>();
    segment.getCoordinates().forEach(c -> {
        try {
            readInStates.add(new SpacecraftState(new CartesianOrbit(c, frame, mu)));
        } catch (IllegalArgumentException | OrekitException e) {
            fail(e.getLocalizedMessage());
        }
    });
    final int interpolationPoints = 5;
    Ephemeris directEphemProp = new Ephemeris(readInStates, interpolationPoints);
    final EventsLogger directEphemPropLogger = new EventsLogger();
    directEphemProp.addEventDetector(directEphemPropLogger.monitorDetector(elevationDetector));
    directEphemProp.propagate(segment.getStart(), segment.getStop());
    assertEquals(referenceLogger.getLoggedEvents().size(), directEphemPropLogger.getLoggedEvents().size());
    for (int i = 0; i < referenceLogger.getLoggedEvents().size(); i++) {
        LoggedEvent reference = referenceLogger.getLoggedEvents().get(i);
        LoggedEvent actual = directEphemPropLogger.getLoggedEvents().get(i);
        assertEquals(0.0, FastMath.abs(reference.getState().getDate().durationFrom(actual.getState().getDate())), dateEpsilon);
    }
}

Example 33 with CelestialBody

use of org.orekit.bodies.CelestialBody in project Orekit by CS-SI.

the class BoxAndSolarArraySpacecraftTest method testNormalFixedRateField.

@Test
public void testNormalFixedRateField() throws OrekitException {
    AbsoluteDate initialDate = propagator.getInitialState().getDate();
    CelestialBody sun = CelestialBodyFactory.getSun();
    BoxAndSolarArraySpacecraft s = new BoxAndSolarArraySpacecraft(0, 0, 0, sun, 20.0, Vector3D.PLUS_J, initialDate, Vector3D.PLUS_K, 1.0e-3, 0.0, 1.0, 0.0);
    Field<Decimal64> field = Decimal64Field.getInstance();
    for (double dt = 0; dt < 4000; dt += 60) {
        AbsoluteDate date = initialDate.shiftedBy(dt);
        SpacecraftState state = propagator.propagate(date);
        FieldVector3D<Decimal64> normal = s.getNormal(new FieldAbsoluteDate<>(field, state.getDate()), state.getFrame(), new FieldVector3D<>(field, state.getPVCoordinates().getPosition()), new FieldRotation<>(field, state.getAttitude().getRotation()));
        Assert.assertEquals(0, FieldVector3D.dotProduct(normal, Vector3D.PLUS_J).getReal(), 1.0e-16);
    }
}

Example 34 with CelestialBody

use of org.orekit.bodies.CelestialBody in project Orekit by CS-SI.

the class BoxAndSolarArraySpacecraftTest method testPlaneSpecularReflection.

@Test
public void testPlaneSpecularReflection() throws OrekitException {
    AbsoluteDate initialDate = propagator.getInitialState().getDate();
    CelestialBody sun = CelestialBodyFactory.getSun();
    BoxAndSolarArraySpacecraft s = new BoxAndSolarArraySpacecraft(0, 0, 0, sun, 20.0, Vector3D.PLUS_J, 0.0, 0.0, 1.0);
    for (double dt = 0; dt < 4000; dt += 60) {
        AbsoluteDate date = initialDate.shiftedBy(dt);
        SpacecraftState state = propagator.propagate(date);
        Vector3D sunDirection = sun.getPVCoordinates(date, state.getFrame()).getPosition().normalize();
        Vector3D flux = new Vector3D(-4.56e-6, sunDirection);
        Vector3D acceleration = s.radiationPressureAcceleration(state.getDate(), state.getFrame(), state.getPVCoordinates().getPosition(), state.getAttitude().getRotation(), state.getMass(), flux, getRadiationParameters(s));
        Vector3D normal = state.getAttitude().getRotation().applyInverseTo(s.getNormal(state.getDate(), state.getFrame(), state.getPVCoordinates().getPosition(), state.getAttitude().getRotation()));
        // solar array normal is slightly misaligned with Sun direction due to Sun being out of orbital plane
        Assert.assertEquals(15.1, FastMath.toDegrees(Vector3D.angle(sunDirection, normal)), 0.11);
        // radiation pressure is exactly opposed to solar array normal as there is only specular reflection
        Assert.assertEquals(180.0, FastMath.toDegrees(Vector3D.angle(acceleration, normal)), 1.0e-3);
    }
}

Example 35 with CelestialBody

use of org.orekit.bodies.CelestialBody in project Orekit by CS-SI.

the class BoxAndSolarArraySpacecraftTest method testNormalOptimalRotationDouble.

@Test
public void testNormalOptimalRotationDouble() throws OrekitException {
    AbsoluteDate initialDate = propagator.getInitialState().getDate();
    CelestialBody sun = CelestialBodyFactory.getSun();
    BoxAndSolarArraySpacecraft s = new BoxAndSolarArraySpacecraft(0, 0, 0, sun, 20.0, Vector3D.PLUS_J, 0.0, 1.0, 0.0);
    for (double dt = 0; dt < 4000; dt += 60) {
        AbsoluteDate date = initialDate.shiftedBy(dt);
        SpacecraftState state = propagator.propagate(date);
        Vector3D normal = s.getNormal(state.getDate(), state.getFrame(), state.getPVCoordinates().getPosition(), state.getAttitude().getRotation());
        Assert.assertEquals(0, Vector3D.dotProduct(normal, Vector3D.PLUS_J), 1.0e-16);
    }
}