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

Example 56 with FieldAbsoluteDate

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

the class FieldEventDetectorTest method doTestIssue108Numerical.

private <T extends RealFieldElement<T>> void doTestIssue108Numerical(Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    final TimeScale utc = TimeScalesFactory.getUTC();
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(-6142438.668), zero.add(3492467.56), zero.add(-25767.257));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(505.848), zero.add(942.781), zero.add(7435.922));
    final FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, 2003, 9, 16, utc);
    final FieldOrbit<T> orbit = new FieldCircularOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), date, mu);
    final T step = zero.add(60.0);
    final int n = 100;
    FieldNumericalPropagator<T> propagator = new FieldNumericalPropagator<>(field, new ClassicalRungeKuttaFieldIntegrator<>(field, step));
    propagator.setOrbitType(OrbitType.EQUINOCTIAL);
    propagator.resetInitialState(new FieldSpacecraftState<>(orbit));
    GCallsCounter<T> counter = new GCallsCounter<>(zero.add(100000.0), zero.add(1.0e-6), 20, new FieldStopOnEvent<GCallsCounter<T>, T>());
    propagator.addEventDetector(counter);
    propagator.propagate(date.shiftedBy(step.multiply(n)));
    Assert.assertEquals(n + 1, counter.getCount());
}

Example 57 with FieldAbsoluteDate

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

the class FieldEventDetectorTest method doTestNoisyGFunction.

private <T extends RealFieldElement<T>> void doTestNoisyGFunction(Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    // initial conditions
    Frame eme2000 = FramesFactory.getEME2000();
    TimeScale utc = TimeScalesFactory.getUTC();
    FieldAbsoluteDate<T> initialDate = new FieldAbsoluteDate<>(field, 2011, 5, 11, utc);
    FieldAbsoluteDate<T> startDate = new FieldAbsoluteDate<>(field, 2032, 10, 17, utc);
    @SuppressWarnings("unchecked") FieldAbsoluteDate<T>[] interruptDates = (FieldAbsoluteDate<T>[]) Array.newInstance(FieldAbsoluteDate.class, 1);
    interruptDates[0] = new FieldAbsoluteDate<>(field, 2032, 10, 18, utc);
    FieldAbsoluteDate<T> targetDate = new FieldAbsoluteDate<>(field, 2211, 5, 11, utc);
    FieldKeplerianPropagator<T> k1 = new FieldKeplerianPropagator<>(new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(new FieldVector3D<>(zero.add(4008462.4706055815), zero.add(-3155502.5373837613), zero.add(-5044275.9880020910)), new FieldVector3D<>(zero.add(-5012.9298276860990), zero.add(1920.3567095973078), zero.add(-5172.7403501801580))), eme2000, initialDate, Constants.WGS84_EARTH_MU));
    FieldKeplerianPropagator<T> k2 = new FieldKeplerianPropagator<>(new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(new FieldVector3D<>(zero.add(4008912.4039522274), zero.add(-3155453.3125615157), zero.add(-5044297.6484738905)), new FieldVector3D<>(zero.add(-5012.5883854112530), zero.add(1920.6332221785074), zero.add(-5172.2177085540500))), eme2000, initialDate, Constants.WGS84_EARTH_MU));
    k2.addEventDetector(new FieldCloseApproachDetector<>(zero.add(2015.243454166727), zero.add(0.0001), 100, new FieldContinueOnEvent<FieldCloseApproachDetector<T>, T>(), k1));
    k2.addEventDetector(new FieldDateDetector<>(zero.add(Constants.JULIAN_DAY), zero.add(1.0e-6), interruptDates));
    FieldSpacecraftState<T> s = k2.propagate(startDate, targetDate);
    Assert.assertEquals(0.0, interruptDates[0].durationFrom(s.getDate()).getReal(), 1.1e-6);
}

Example 58 with FieldAbsoluteDate

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

the class FieldNodeDetectorTest method doTestIssue158.

private <T extends RealFieldElement<T>> void doTestIssue158(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field);
    T a = zero.add(3.0e7);
    T e1 = zero.add(0.8);
    T e2 = zero.add(1.0e-4);
    T i = zero.add(1.0);
    T pa = zero.add(1.5 * FastMath.PI);
    T raan = zero.add(5.0);
    T m = zero.add(0);
    Frame frame = FramesFactory.getEME2000();
    double mu = Constants.EIGEN5C_EARTH_MU;
    // highly eccentric, inclined orbit
    final FieldKeplerianOrbit<T> orbit1 = new FieldKeplerianOrbit<>(a, e1, i, pa, raan, m, PositionAngle.MEAN, frame, date, mu);
    FieldEventDetector<T> detector1 = new FieldNodeDetector<>(orbit1, orbit1.getFrame());
    T t1 = orbit1.getKeplerianPeriod();
    Assert.assertEquals(t1.getReal() / 28.82, detector1.getMaxCheckInterval().getReal(), t1.getReal() / 10000);
    // nearly circular, inclined orbit
    final FieldKeplerianOrbit<T> orbit2 = new FieldKeplerianOrbit<>(a, e2, i, pa, raan, m, PositionAngle.MEAN, frame, date, mu);
    FieldEventDetector<T> detector2 = new FieldNodeDetector<>(orbit2, orbit2.getFrame());
    T t2 = orbit2.getKeplerianPeriod();
    Assert.assertEquals(t1.getReal(), t2.getReal(), t1.getReal() / 10000);
    Assert.assertEquals(t2.getReal() / 3, detector2.getMaxCheckInterval().getReal(), t2.getReal() / 10000);
}

Example 59 with FieldAbsoluteDate

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

the class FieldNodeDetectorTest method doTestIssue138.

private <T extends RealFieldElement<T>> void doTestIssue138(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    T a = zero.add(800000 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS);
    T e = zero.add(0.0001);
    T i = zero.add(FastMath.toRadians(98));
    T w = zero.add(-90);
    T raan = zero;
    T v = zero;
    Frame inertialFrame = FramesFactory.getEME2000();
    FieldAbsoluteDate<T> initialDate = new FieldAbsoluteDate<>(field, 2014, 01, 01, 0, 0, 0, TimeScalesFactory.getUTC());
    FieldAbsoluteDate<T> finalDate = initialDate.shiftedBy(5000);
    FieldKeplerianOrbit<T> initialOrbit = new FieldKeplerianOrbit<>(a, e, i, w, raan, v, PositionAngle.TRUE, inertialFrame, initialDate, Constants.WGS84_EARTH_MU);
    FieldSpacecraftState<T> initialState = new FieldSpacecraftState<>(initialOrbit, zero.add(1000));
    FieldKeplerianPropagator<T> propagator = new FieldKeplerianPropagator<>(initialOrbit);
    // Define 2 instances of NodeDetector:
    FieldEventDetector<T> rawDetector = new FieldNodeDetector<>(zero.add(1e-6), initialState.getOrbit(), initialState.getFrame()).withHandler(new FieldContinueOnEvent<FieldNodeDetector<T>, T>());
    FieldEventsLogger<T> logger1 = new FieldEventsLogger<>();
    FieldEventDetector<T> node1 = logger1.monitorDetector(rawDetector);
    FieldEventsLogger<T> logger2 = new FieldEventsLogger<>();
    FieldEventDetector<T> node2 = logger2.monitorDetector(rawDetector);
    propagator.addEventDetector(node1);
    propagator.addEventDetector(node2);
    // First propagation
    propagator.setEphemerisMode();
    propagator.propagate(finalDate);
    Assert.assertEquals(2, logger1.getLoggedEvents().size());
    Assert.assertEquals(2, logger2.getLoggedEvents().size());
    logger1.clearLoggedEvents();
    logger2.clearLoggedEvents();
    FieldBoundedPropagator<T> postpro = propagator.getGeneratedEphemeris();
    // Post-processing
    postpro.addEventDetector(node1);
    postpro.addEventDetector(node2);
    postpro.propagate(finalDate);
    Assert.assertEquals(2, logger1.getLoggedEvents().size());
    Assert.assertEquals(2, logger2.getLoggedEvents().size());
}

Example 60 with FieldAbsoluteDate

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

the class FieldEclipseDetectorTest method doTestInsideOcculted.

private <T extends RealFieldElement<T>> void doTestInsideOcculted(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(-6142438.668), zero.add(3492467.560), zero.add(-25767.25680));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(505.8479685), zero.add(942.7809215), zero.add(7435.922231));
    FieldAbsoluteDate<T> iniDate = new FieldAbsoluteDate<>(field, 1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
    final FieldOrbit<T> orbit = new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getGCRF(), iniDate, mu);
    FieldSpacecraftState<T> initialState = new FieldSpacecraftState<>(orbit);
    double[] absTolerance = { 0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001 };
    double[] relTolerance = { 1.0e-7, 1.0e-4, 1.0e-4, 1.0e-7, 1.0e-7, 1.0e-7, 1.0e-7 };
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 1000, absTolerance, relTolerance);
    integrator.setInitialStepSize(field.getZero().add(60));
    FieldNumericalPropagator<T> propagator = new FieldNumericalPropagator<>(field, integrator);
    propagator.setOrbitType(OrbitType.EQUINOCTIAL);
    propagator.setInitialState(initialState);
    sun = CelestialBodyFactory.getSun();
    earth = CelestialBodyFactory.getEarth();
    sunRadius = 696000000.;
    earthRadius = 6400000.;
    FieldEclipseDetector<T> e = new FieldEclipseDetector<>(field.getZero().add(60.), field.getZero().add(1.e-3), sun, sunRadius, earth, earthRadius);
    Vector3D p = sun.getPVCoordinates(AbsoluteDate.J2000_EPOCH, FramesFactory.getGCRF()).getPosition();
    FieldSpacecraftState<T> s = new FieldSpacecraftState<>(new FieldCartesianOrbit<>(new TimeStampedFieldPVCoordinates<>(FieldAbsoluteDate.getJ2000Epoch(field), new FieldPVCoordinates<>(new FieldVector3D<>(field.getOne(), field.getZero(), field.getZero()).add(p), new FieldVector3D<>(field.getZero(), field.getZero(), field.getOne()))), FramesFactory.getGCRF(), mu));
    Assert.assertEquals(FastMath.PI, e.g(s).getReal(), 1.0e-15);
}