Examples with Propagator org.orekit.propagation.Propagator used on opensource projects

Example 71 with Propagator

use of org.orekit.propagation.Propagator in project Orekit by CS-SI.

the class CloseEventsAbstractTest method testEventChangesGFunctionDefinitionReverse.

/**
 * test when one event detector changes the definition of another's g function before
 * the end of the step as a result of a continue action. Not sure if this should be
 * officially supported, but it is used in Orekit's DateDetector, it's useful, and not
 * too hard to implement.
 */
@Test
public void testEventChangesGFunctionDefinitionReverse() throws OrekitException {
    // setup
    double maxCheck = 5;
    double tolerance = 1e-6;
    double t1 = -11, t2 = -19;
    // shared event list so we know the order in which they occurred
    List<Event<EventDetector>> events = new ArrayList<>();
    // mutable boolean
    boolean[] swap = new boolean[1];
    ContinuousDetector detectorA = new ContinuousDetector(t1).withMaxCheck(maxCheck).withThreshold(tolerance).withHandler(new RecordAndContinue<EventDetector>(events) {

        @Override
        public Action eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing) {
            swap[0] = true;
            return super.eventOccurred(s, detector, increasing);
        }
    });
    ContinuousDetector detectorB = new ContinuousDetector(t2);
    EventDetector detectorC = new AbstractDetector<EventDetector>(maxCheck, tolerance, 100, new RecordAndContinue<>(events)) {

        private static final long serialVersionUID = 1L;

        @Override
        public double g(SpacecraftState state) throws OrekitException {
            if (swap[0]) {
                return detectorB.g(state);
            } else {
                return 1;
            }
        }

        @Override
        protected EventDetector create(double newMaxCheck, double newThreshold, int newMaxIter, EventHandler<? super EventDetector> newHandler) {
            return null;
        }
    };
    Propagator propagator = getPropagator(10);
    propagator.addEventDetector(detectorA);
    propagator.addEventDetector(detectorC);
    // action
    propagator.propagate(epoch.shiftedBy(-30.0));
    // verify
    Assert.assertEquals(2, events.size());
    Assert.assertEquals(t1, events.get(0).getState().getDate().durationFrom(epoch), tolerance);
    Assert.assertEquals(true, events.get(0).isIncreasing());
    Assert.assertSame(detectorA, events.get(0).getDetector());
    Assert.assertEquals(t2, events.get(1).getState().getDate().durationFrom(epoch), tolerance);
    Assert.assertEquals(true, events.get(1).isIncreasing());
    Assert.assertSame(detectorC, events.get(1).getDetector());
}

Example 72 with Propagator

use of org.orekit.propagation.Propagator in project Orekit by CS-SI.

the class ElevationDetectorTest method testIssue136.

@Test
public void testIssue136() throws OrekitException {
    // Initial state definition : date, orbit
    AbsoluteDate initialDate = new AbsoluteDate(2004, 01, 01, 23, 30, 00.000, TimeScalesFactory.getUTC());
    // inertial frame for orbit definition
    Frame inertialFrame = FramesFactory.getEME2000();
    Orbit initialOrbit = new KeplerianOrbit(6828137.005, 7.322641382145889e-10, 1.6967079057368113, 0.0, 1.658054062748353, 0.0001223149429077902, PositionAngle.MEAN, inertialFrame, initialDate, Constants.EIGEN5C_EARTH_MU);
    // Propagator : consider a simple Keplerian motion (could be more elaborate)
    Propagator kepler = new EcksteinHechlerPropagator(initialOrbit, Constants.EGM96_EARTH_EQUATORIAL_RADIUS, Constants.EGM96_EARTH_MU, Constants.EGM96_EARTH_C20, 0.0, 0.0, 0.0, 0.0);
    // Earth and frame
    // equatorial radius in meter
    double ae = 6378137.0;
    // flattening
    double f = 1.0 / 298.257223563;
    // terrestrial frame at an arbitrary date
    Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
    // Station
    final double longitude = FastMath.toRadians(-147.5);
    final double latitude = FastMath.toRadians(64);
    final double altitude = 160;
    final GeodeticPoint station1 = new GeodeticPoint(latitude, longitude, altitude);
    final TopocentricFrame sta1Frame = new TopocentricFrame(earth, station1, "station1");
    // Event definition
    final double maxcheck = 120.0;
    final double elevation = FastMath.toRadians(5.);
    final double threshold = 10.0;
    final EventDetector rawEvent = new ElevationDetector(maxcheck, threshold, sta1Frame).withConstantElevation(elevation).withHandler(new ContinueOnEvent<ElevationDetector>());
    final EventsLogger logger = new EventsLogger();
    kepler.addEventDetector(logger.monitorDetector(rawEvent));
    // Propagate from the initial date to the first raising or for the fixed duration
    kepler.propagate(initialDate.shiftedBy(60 * 60 * 24.0 * 40));
    int countIncreasing = 0;
    int countDecreasing = 0;
    for (LoggedEvent le : logger.getLoggedEvents()) {
        if (le.isIncreasing()) {
            ++countIncreasing;
        } else {
            ++countDecreasing;
        }
    }
    Assert.assertEquals(314, countIncreasing);
    Assert.assertEquals(314, countDecreasing);
}

Example 73 with Propagator

use of org.orekit.propagation.Propagator in project Orekit by CS-SI.

the class ElevationDetectorTest method testEventForMask.

@Test
public void testEventForMask() throws OrekitException {
    final TimeScale utc = TimeScalesFactory.getUTC();
    final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
    final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
    final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
    final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), date, mu);
    Propagator propagator = new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
    // Earth and frame
    // equatorial radius in meter
    double ae = 6378137.0;
    // flattening
    double f = 1.0 / 298.257223563;
    // terrestrial frame at an arbitrary date
    Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
    GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(48.833), FastMath.toRadians(2.333), 0.0);
    TopocentricFrame topo = new TopocentricFrame(earth, point, "Gstation");
    double[][] maskValues = { { FastMath.toRadians(0), FastMath.toRadians(5) }, { FastMath.toRadians(30), FastMath.toRadians(4) }, { FastMath.toRadians(60), FastMath.toRadians(3) }, { FastMath.toRadians(90), FastMath.toRadians(2) }, { FastMath.toRadians(120), FastMath.toRadians(3) }, { FastMath.toRadians(150), FastMath.toRadians(4) }, { FastMath.toRadians(180), FastMath.toRadians(5) }, { FastMath.toRadians(210), FastMath.toRadians(6) }, { FastMath.toRadians(240), FastMath.toRadians(5) }, { FastMath.toRadians(270), FastMath.toRadians(4) }, { FastMath.toRadians(300), FastMath.toRadians(3) }, { FastMath.toRadians(330), FastMath.toRadians(4) } };
    ElevationMask mask = new ElevationMask(maskValues);
    ElevationDetector detector = new ElevationDetector(topo).withElevationMask(mask).withHandler(new StopOnIncreasing<ElevationDetector>());
    Assert.assertSame(mask, detector.getElevationMask());
    AbsoluteDate startDate = new AbsoluteDate(2003, 9, 15, 20, 0, 0, utc);
    propagator.resetInitialState(propagator.propagate(startDate));
    propagator.addEventDetector(detector);
    final SpacecraftState fs = propagator.propagate(startDate.shiftedBy(Constants.JULIAN_DAY));
    double elevation = topo.getElevation(fs.getPVCoordinates().getPosition(), fs.getFrame(), fs.getDate());
    Assert.assertEquals(0.065, elevation, 2.0e-5);
}

Example 74 with Propagator

use of org.orekit.propagation.Propagator in project Orekit by CS-SI.

the class EventDetectorTest method testBasicScheduling.

@Test
public void testBasicScheduling() throws OrekitException {
    final TimeScale utc = TimeScalesFactory.getUTC();
    final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
    final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
    final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
    final Orbit orbit = new CircularOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), date, mu);
    Propagator propagator = new KeplerianPropagator(orbit);
    double stepSize = 60.0;
    OutOfOrderChecker checker = new OutOfOrderChecker(stepSize);
    propagator.addEventDetector(new DateDetector(date.shiftedBy(5.25 * stepSize)).withHandler(checker));
    propagator.setMasterMode(stepSize, checker);
    propagator.propagate(date.shiftedBy(10 * stepSize));
    Assert.assertTrue(checker.outOfOrderCallDetected());
}

Example 75 with Propagator

use of org.orekit.propagation.Propagator in project Orekit by CS-SI.

the class FieldOfViewTest method testRollPitchYawHexagonalFootprint.

@Test
public void testRollPitchYawHexagonalFootprint() throws OrekitException {
    Utils.setDataRoot("regular-data");
    FieldOfView fov = new FieldOfView(Vector3D.PLUS_K, Vector3D.PLUS_I, FastMath.toRadians(3.0), 6, 0.0);
    OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    KeplerianOrbit orbit = new KeplerianOrbit(new PVCoordinates(new Vector3D(7.0e6, 1.0e6, 4.0e6), new Vector3D(-500.0, 8000.0, 1000.0)), FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, Constants.EIGEN5C_EARTH_MU);
    Propagator propagator = new KeplerianPropagator(orbit);
    propagator.setAttitudeProvider(new LofOffset(orbit.getFrame(), LOFType.VVLH, RotationOrder.XYZ, FastMath.toRadians(10), FastMath.toRadians(20), FastMath.toRadians(5)));
    SpacecraftState state = propagator.propagate(orbit.getDate().shiftedBy(1000.0));
    Transform inertToBody = state.getFrame().getTransformTo(earth.getBodyFrame(), state.getDate());
    Transform fovToBody = new Transform(state.getDate(), state.toTransform().getInverse(), inertToBody);
    List<List<GeodeticPoint>> footprint = fov.getFootprint(fovToBody, earth, FastMath.toRadians(0.1));
    Vector3D subSat = earth.projectToGround(state.getPVCoordinates(earth.getBodyFrame()).getPosition(), state.getDate(), earth.getBodyFrame());
    Assert.assertEquals(1, footprint.size());
    List<GeodeticPoint> loop = footprint.get(0);
    Assert.assertEquals(210, loop.size());
    double minEl = Double.POSITIVE_INFINITY;
    double maxEl = 0;
    double minDist = Double.POSITIVE_INFINITY;
    double maxDist = 0;
    for (int i = 0; i < loop.size(); ++i) {
        Assert.assertEquals(0.0, loop.get(i).getAltitude(), 1.0e-15);
        TopocentricFrame topo = new TopocentricFrame(earth, loop.get(i), "atLimb");
        final double elevation = topo.getElevation(state.getPVCoordinates().getPosition(), state.getFrame(), state.getDate());
        minEl = FastMath.min(minEl, elevation);
        maxEl = FastMath.max(maxEl, elevation);
        final double dist = Vector3D.distance(subSat, earth.transform(loop.get(i)));
        minDist = FastMath.min(minDist, dist);
        maxDist = FastMath.max(maxDist, dist);
    }
    Assert.assertEquals(48.0026, FastMath.toDegrees(minEl), 0.001);
    Assert.assertEquals(60.1975, FastMath.toDegrees(maxEl), 0.001);
    Assert.assertEquals(1221543.6, minDist, 1.0);
    Assert.assertEquals(1804921.6, maxDist, 1.0);
}