Examples with FieldKeplerianPropagator org.orekit.propagation.analytical.FieldKeplerianPropagator used on opensource projects

Example 1 with FieldKeplerianPropagator

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

the class FieldSpacecraftStateTest method doTestTransform.

private <T extends RealFieldElement<T>> void doTestTransform(final Field<T> field) throws OrekitException {
    T zero = field.getZero();
    T a = zero.add(rOrbit.getA());
    T e = zero.add(rOrbit.getE());
    T i = zero.add(rOrbit.getI());
    T pa = zero.add(1.9674147913622104);
    T raan = zero.add(FastMath.toRadians(261));
    T lv = zero.add(0);
    T mass = zero.add(2500);
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(a, e, i, pa, raan, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
    BodyCenterPointing attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
    FieldKeplerianPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit, attitudeLaw, mu, mass);
    double maxDP = 0;
    double maxDV = 0;
    double maxDA = 0;
    for (double t = 0; t < orbit.getKeplerianPeriod().getReal(); t += 60) {
        final FieldSpacecraftState<T> state = propagator.propagate(orbit.getDate().shiftedBy(zero.add(t)));
        final Transform transform = state.toSpacecraftState().toTransform().getInverse();
        PVCoordinates pv = transform.transformPVCoordinates(PVCoordinates.ZERO);
        PVCoordinates dPV = new PVCoordinates(pv, state.getPVCoordinates().toPVCoordinates());
        Vector3D mZDirection = transform.transformVector(Vector3D.MINUS_K);
        double alpha = Vector3D.angle(mZDirection, state.getPVCoordinates().toPVCoordinates().getPosition());
        maxDP = FastMath.max(maxDP, dPV.getPosition().getNorm());
        maxDV = FastMath.max(maxDV, dPV.getVelocity().getNorm());
        maxDA = FastMath.max(maxDA, FastMath.toDegrees(alpha));
    }
    Assert.assertEquals(0.0, maxDP, 1.0e-6);
    Assert.assertEquals(0.0, maxDV, 1.0e-9);
    Assert.assertEquals(0.0, maxDA, 1.0e-12);
}

Example 2 with FieldKeplerianPropagator

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

the class FieldSpacecraftStateTest method doTestAdditionalStates.

private <T extends RealFieldElement<T>> void doTestAdditionalStates(final Field<T> field) throws OrekitException {
    T zero = field.getZero();
    T a = zero.add(rOrbit.getA());
    T e = zero.add(rOrbit.getE());
    T i = zero.add(rOrbit.getI());
    T pa = zero.add(1.9674147913622104);
    T raan = zero.add(FastMath.toRadians(261));
    T lv = zero.add(0);
    T mass = zero.add(2500);
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(a, e, i, pa, raan, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
    BodyCenterPointing attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
    FieldKeplerianPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit, attitudeLaw, mu, mass);
    final FieldSpacecraftState<T> state = propagator.propagate(orbit.getDate().shiftedBy(60));
    T[] add = MathArrays.buildArray(field, 2);
    add[0] = zero.add(1.);
    add[1] = zero.add(2.);
    final FieldSpacecraftState<T> extended = state.addAdditionalState("test-1", add).addAdditionalState("test-2", zero.add(42.0));
    Assert.assertEquals(0, state.getAdditionalStates().size());
    Assert.assertFalse(state.hasAdditionalState("test-1"));
    try {
        state.getAdditionalState("test-1");
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(oe.getSpecifier(), OrekitMessages.UNKNOWN_ADDITIONAL_STATE);
        Assert.assertEquals(oe.getParts()[0], "test-1");
    }
    try {
        state.ensureCompatibleAdditionalStates(extended);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(oe.getSpecifier(), OrekitMessages.UNKNOWN_ADDITIONAL_STATE);
        Assert.assertTrue(oe.getParts()[0].toString().startsWith("test-"));
    }
    try {
        extended.ensureCompatibleAdditionalStates(state);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(oe.getSpecifier(), OrekitMessages.UNKNOWN_ADDITIONAL_STATE);
        Assert.assertTrue(oe.getParts()[0].toString().startsWith("test-"));
    }
    try {
        T[] kk = MathArrays.buildArray(field, 7);
        extended.ensureCompatibleAdditionalStates(extended.addAdditionalState("test-2", kk));
        Assert.fail("an exception should have been thrown");
    } catch (MathIllegalStateException mise) {
        Assert.assertEquals(LocalizedCoreFormats.DIMENSIONS_MISMATCH, mise.getSpecifier());
        Assert.assertEquals(7, ((Integer) mise.getParts()[0]).intValue());
    }
    Assert.assertEquals(2, extended.getAdditionalStates().size());
    Assert.assertTrue(extended.hasAdditionalState("test-1"));
    Assert.assertTrue(extended.hasAdditionalState("test-2"));
    Assert.assertEquals(1.0, extended.getAdditionalState("test-1")[0].getReal(), 1.0e-15);
    Assert.assertEquals(2.0, extended.getAdditionalState("test-1")[1].getReal(), 1.0e-15);
    Assert.assertEquals(42.0, extended.getAdditionalState("test-2")[0].getReal(), 1.0e-15);
    // test various constructors
    T[] dd = MathArrays.buildArray(field, 1);
    dd[0] = zero.add(-6.0);
    Map<String, T[]> map = new HashMap<String, T[]>();
    map.put("test-3", dd);
    FieldSpacecraftState<T> sO = new FieldSpacecraftState<>(state.getOrbit(), map);
    Assert.assertEquals(-6.0, sO.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
    FieldSpacecraftState<T> sOA = new FieldSpacecraftState<>(state.getOrbit(), state.getAttitude(), map);
    Assert.assertEquals(-6.0, sOA.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
    FieldSpacecraftState<T> sOM = new FieldSpacecraftState<>(state.getOrbit(), state.getMass(), map);
    Assert.assertEquals(-6.0, sOM.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
    FieldSpacecraftState<T> sOAM = new FieldSpacecraftState<>(state.getOrbit(), state.getAttitude(), state.getMass(), map);
    Assert.assertEquals(-6.0, sOAM.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
    FieldSpacecraftState<T> sFromDouble = new FieldSpacecraftState<>(field, sOAM.toSpacecraftState());
    Assert.assertEquals(-6.0, sFromDouble.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
}

Example 3 with FieldKeplerianPropagator

use of org.orekit.propagation.analytical.FieldKeplerianPropagator 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 4 with FieldKeplerianPropagator

use of org.orekit.propagation.analytical.FieldKeplerianPropagator 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 5 with FieldKeplerianPropagator

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

the class FixedRateTest method doTestSpin.

private <T extends RealFieldElement<T>> void doTestSpin(final Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(1970, 01, 01), new TimeComponents(3, 25, 45.6789), TimeScalesFactory.getUTC());
    final T rate = zero.add(2 * FastMath.PI / (12 * 60));
    AttitudeProvider law = new FixedRate(new Attitude(date.toAbsoluteDate(), FramesFactory.getEME2000(), new Rotation(0.48, 0.64, 0.36, 0.48, false), new Vector3D(rate.getReal(), Vector3D.PLUS_K), Vector3D.ZERO));
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(zero.add(7178000.0), zero.add(1.e-4), zero.add(FastMath.toRadians(50.)), zero.add(FastMath.toRadians(10.)), zero.add(FastMath.toRadians(20.)), zero.add(FastMath.toRadians(30.)), PositionAngle.MEAN, FramesFactory.getEME2000(), date, 3.986004415e14);
    FieldPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit, law);
    T h = zero.add(0.01);
    FieldSpacecraftState<T> sMinus = propagator.propagate(date.shiftedBy(h.negate()));
    FieldSpacecraftState<T> s0 = propagator.propagate(date);
    FieldSpacecraftState<T> sPlus = propagator.propagate(date.shiftedBy(h));
    // check spin is consistent with attitude evolution
    double errorAngleMinus = FieldRotation.distance(sMinus.shiftedBy(h).getAttitude().getRotation(), s0.getAttitude().getRotation()).getReal();
    double evolutionAngleMinus = FieldRotation.distance(sMinus.getAttitude().getRotation(), s0.getAttitude().getRotation()).getReal();
    Assert.assertEquals(0.0, errorAngleMinus, 1.0e-6 * evolutionAngleMinus);
    double errorAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.shiftedBy(h.negate()).getAttitude().getRotation()).getReal();
    double evolutionAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.getAttitude().getRotation()).getReal();
    Assert.assertEquals(0.0, errorAnglePlus, 1.0e-6 * evolutionAnglePlus);
    FieldVector3D<T> spin0 = s0.getAttitude().getSpin();
    FieldVector3D<T> reference = FieldAngularCoordinates.estimateRate(sMinus.getAttitude().getRotation(), sPlus.getAttitude().getRotation(), h.multiply(2));
    Assert.assertEquals(0.0, spin0.subtract(reference).getNorm().getReal(), 1.0e-14);
}