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

Example 36 with FieldAbsoluteDate

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

the class GTODProviderTest method testAASReferenceGEOField.

@Test
public void testAASReferenceGEOField() throws OrekitException {
    // this reference test has been extracted from the following paper:
    // Implementation Issues Surrounding the New IAU Reference Systems for Astrodynamics
    // David A. Vallado, John H. Seago, P. Kenneth Seidelmann
    // http://www.centerforspace.com/downloads/files/pubs/AAS-06-134.pdf
    Utils.setLoaders(IERSConventions.IERS_1996, Utils.buildEOPList(IERSConventions.IERS_1996, ITRFVersion.ITRF_2008, new double[][] { { 53153, -0.4709050, 0.0000000, -0.083853, 0.467217, -0.053614, -0.004494, Double.NaN, Double.NaN }, { 53154, -0.4709050, 0.0000000, -0.083853, 0.467217, -0.053614, -0.004494, Double.NaN, Double.NaN }, { 53155, -0.4709050, 0.0000000, -0.083853, 0.467217, -0.053614, -0.004494, Double.NaN, Double.NaN }, { 53156, -0.4709050, 0.0000000, -0.083853, 0.467217, -0.053614, -0.004494, Double.NaN, Double.NaN }, { 53157, -0.4709050, 0.0000000, -0.083853, 0.467217, -0.053614, -0.004494, Double.NaN, Double.NaN }, { 53158, -0.4709050, 0.0000000, -0.083853, 0.467217, -0.053614, -0.004494, Double.NaN, Double.NaN }, { 53159, -0.4709050, 0.0000000, -0.083853, 0.467217, -0.053614, -0.004494, Double.NaN, Double.NaN }, { 53160, -0.4709050, 0.0000000, -0.083853, 0.467217, -0.053614, -0.004494, Double.NaN, Double.NaN } }));
    FieldAbsoluteDate<Decimal64> t0 = new FieldAbsoluteDate<>(Decimal64Field.getInstance(), new DateComponents(2004, 06, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
    FieldTransform<Decimal64> t = FramesFactory.getTOD(IERSConventions.IERS_1996, true).getTransformTo(FramesFactory.getGTOD(IERSConventions.IERS_1996, true), t0);
    // TOD iau76
    PVCoordinates pvTOD = new PVCoordinates(new Vector3D(-40577427.7501, -11500096.1306, 10293.2583), new Vector3D(837.552338, -2957.524176, -0.928772));
    // PEF iau76
    PVCoordinates pvPEF = new PVCoordinates(new Vector3D(24796919.2956, -34115870.9001, 10293.2583), new Vector3D(-0.979178, -1.476540, -0.928772));
    // it seems the induced effect of pole nutation correction δΔψ on the equation of the equinoxes
    // was not taken into account in the reference paper, so we fix it here for the test
    final Decimal64 dDeltaPsi = FramesFactory.getEOPHistory(IERSConventions.IERS_1996, true).getEquinoxNutationCorrection(t0)[0];
    final Decimal64 epsilonA = IERSConventions.IERS_1996.getMeanObliquityFunction().value(t0);
    final FieldTransform<Decimal64> fix = new FieldTransform<>(t0, new FieldRotation<>(FieldVector3D.getPlusK(Decimal64Field.getInstance()), dDeltaPsi.multiply(epsilonA.cos()), RotationConvention.FRAME_TRANSFORM));
    checkPV(fix.transformPVCoordinates(pvPEF), t.transformPVCoordinates(pvTOD), 0.0503, 3.59e-4);
    // if we forget to apply nutation corrections, results are much worse, which is expected
    t = FramesFactory.getTOD(false).getTransformTo(FramesFactory.getGTOD(false), t0);
    checkPV(fix.transformPVCoordinates(pvPEF), t.transformPVCoordinates(pvTOD), 1458.27, 3.847e-4);
}

Example 37 with FieldAbsoluteDate

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

the class InterpolatingTransformProviderTest method testForwardException.

@Test(expected = OrekitException.class)
public void testForwardException() throws OrekitException {
    InterpolatingTransformProvider interpolatingProvider = new InterpolatingTransformProvider(new TransformProvider() {

        private static final long serialVersionUID = -3126512810306982868L;

        public Transform getTransform(AbsoluteDate date) throws OrekitException {
            throw new OrekitException(OrekitMessages.INTERNAL_ERROR);
        }

        public <T extends RealFieldElement<T>> FieldTransform<T> getTransform(final FieldAbsoluteDate<T> date) {
            throw new UnsupportedOperationException("never called in this test");
        }
    }, CartesianDerivativesFilter.USE_PVA, AngularDerivativesFilter.USE_RRA, 5, 0.8, 10, 60.0, 60.0);
    interpolatingProvider.getTransform(AbsoluteDate.J2000_EPOCH);
}

Example 38 with FieldAbsoluteDate

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

the class Range method theoreticalEvaluation.

/**
 * {@inheritDoc}
 */
@Override
protected EstimatedMeasurement<Range> theoreticalEvaluation(final int iteration, final int evaluation, final SpacecraftState[] states) throws OrekitException {
    final SpacecraftState state = states[getPropagatorsIndices().get(0)];
    // Range derivatives are computed with respect to spacecraft state in inertial frame
    // and station parameters
    // ----------------------
    // 
    // Parameters:
    // - 0..2 - Position of the spacecraft in inertial frame
    // - 3..5 - Velocity of the spacecraft in inertial frame
    // - 6..n - station parameters (station offsets, pole, prime meridian...)
    int nbParams = 6;
    final Map<String, Integer> indices = new HashMap<>();
    for (ParameterDriver driver : getParametersDrivers()) {
        if (driver.isSelected()) {
            indices.put(driver.getName(), nbParams++);
        }
    }
    final DSFactory factory = new DSFactory(nbParams, 1);
    final Field<DerivativeStructure> field = factory.getDerivativeField();
    final FieldVector3D<DerivativeStructure> zero = FieldVector3D.getZero(field);
    // Coordinates of the spacecraft expressed as a derivative structure
    final TimeStampedFieldPVCoordinates<DerivativeStructure> pvaDS = getCoordinates(state, 0, factory);
    // transform between station and inertial frame, expressed as a derivative structure
    // The components of station's position in offset frame are the 3 last derivative parameters
    final AbsoluteDate downlinkDate = getDate();
    final FieldAbsoluteDate<DerivativeStructure> downlinkDateDS = new FieldAbsoluteDate<>(field, downlinkDate);
    final FieldTransform<DerivativeStructure> offsetToInertialDownlink = station.getOffsetToInertial(state.getFrame(), downlinkDateDS, factory, indices);
    // Station position in inertial frame at end of the downlink leg
    final TimeStampedFieldPVCoordinates<DerivativeStructure> stationDownlink = offsetToInertialDownlink.transformPVCoordinates(new TimeStampedFieldPVCoordinates<>(downlinkDateDS, zero, zero, zero));
    // Compute propagation times
    // (if state has already been set up to pre-compensate propagation delay,
    // we will have delta == tauD and transitState will be the same as state)
    // Downlink delay
    final DerivativeStructure tauD = signalTimeOfFlight(pvaDS, stationDownlink.getPosition(), downlinkDateDS);
    // Transit state
    final double delta = downlinkDate.durationFrom(state.getDate());
    final DerivativeStructure deltaMTauD = tauD.negate().add(delta);
    final SpacecraftState transitState = state.shiftedBy(deltaMTauD.getValue());
    // Transit state (re)computed with derivative structures
    final TimeStampedFieldPVCoordinates<DerivativeStructure> transitStateDS = pvaDS.shiftedBy(deltaMTauD);
    // Station at transit state date (derivatives of tauD taken into account)
    final TimeStampedFieldPVCoordinates<DerivativeStructure> stationAtTransitDate = stationDownlink.shiftedBy(tauD.negate());
    // Uplink delay
    final DerivativeStructure tauU = signalTimeOfFlight(stationAtTransitDate, transitStateDS.getPosition(), transitStateDS.getDate());
    final TimeStampedFieldPVCoordinates<DerivativeStructure> stationUplink = stationDownlink.shiftedBy(-tauD.getValue() - tauU.getValue());
    // Prepare the evaluation
    final EstimatedMeasurement<Range> estimated = new EstimatedMeasurement<Range>(this, iteration, evaluation, new SpacecraftState[] { transitState }, new TimeStampedPVCoordinates[] { stationUplink.toTimeStampedPVCoordinates(), transitStateDS.toTimeStampedPVCoordinates(), stationDownlink.toTimeStampedPVCoordinates() });
    // Range value
    final double cOver2 = 0.5 * Constants.SPEED_OF_LIGHT;
    final DerivativeStructure tau = tauD.add(tauU);
    final DerivativeStructure range = tau.multiply(cOver2);
    estimated.setEstimatedValue(range.getValue());
    // Range partial derivatives with respect to state
    final double[] derivatives = range.getAllDerivatives();
    estimated.setStateDerivatives(0, Arrays.copyOfRange(derivatives, 1, 7));
    // (beware element at index 0 is the value, not a derivative)
    for (final ParameterDriver driver : getParametersDrivers()) {
        final Integer index = indices.get(driver.getName());
        if (index != null) {
            estimated.setParameterDerivatives(driver, derivatives[index + 1]);
        }
    }
    return estimated;
}

Example 39 with FieldAbsoluteDate

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

the class InterSatellitesRange method theoreticalEvaluation.

/**
 * {@inheritDoc}
 */
@Override
protected EstimatedMeasurement<InterSatellitesRange> theoreticalEvaluation(final int iteration, final int evaluation, final SpacecraftState[] states) throws OrekitException {
    // Range derivatives are computed with respect to spacecrafts states in inertial frame
    // ----------------------
    // 
    // Parameters:
    // - 0..2  - Position of the satellite 1 in inertial frame
    // - 3..5  - Velocity of the satellite 1 in inertial frame
    // - 6..8  - Position of the satellite 2 in inertial frame
    // - 9..11 - Velocity of the satellite 2 in inertial frame
    final int nbParams = 12;
    final DSFactory factory = new DSFactory(nbParams, 1);
    final Field<DerivativeStructure> field = factory.getDerivativeField();
    // coordinates of both satellites
    final SpacecraftState state1 = states[getPropagatorsIndices().get(0)];
    final TimeStampedFieldPVCoordinates<DerivativeStructure> pva1 = getCoordinates(state1, 0, factory);
    final SpacecraftState state2 = states[getPropagatorsIndices().get(1)];
    final TimeStampedFieldPVCoordinates<DerivativeStructure> pva2 = getCoordinates(state2, 6, factory);
    // compute propagation times
    // (if state has already been set up to pre-compensate propagation delay,
    // we will have delta == tauD and transitState will be the same as state)
    // downlink delay
    final FieldAbsoluteDate<DerivativeStructure> arrivalDate = new FieldAbsoluteDate<>(field, getDate());
    final TimeStampedFieldPVCoordinates<DerivativeStructure> s1Downlink = pva1.shiftedBy(arrivalDate.durationFrom(pva1.getDate()));
    final DerivativeStructure tauD = signalTimeOfFlight(pva2, s1Downlink.getPosition(), arrivalDate);
    // Transit state
    final double delta = getDate().durationFrom(state2.getDate());
    final DerivativeStructure deltaMTauD = tauD.negate().add(delta);
    // prepare the evaluation
    final EstimatedMeasurement<InterSatellitesRange> estimated;
    final DerivativeStructure range;
    if (twoway) {
        // Transit state (re)computed with derivative structures
        final TimeStampedFieldPVCoordinates<DerivativeStructure> transitStateDS = pva2.shiftedBy(deltaMTauD);
        // uplink delay
        final DerivativeStructure tauU = signalTimeOfFlight(pva1, transitStateDS.getPosition(), transitStateDS.getDate());
        estimated = new EstimatedMeasurement<>(this, iteration, evaluation, new SpacecraftState[] { state1.shiftedBy(deltaMTauD.getValue()), state2.shiftedBy(deltaMTauD.getValue()) }, new TimeStampedPVCoordinates[] { state1.shiftedBy(delta - tauD.getValue() - tauU.getValue()).getPVCoordinates(), state2.shiftedBy(delta - tauD.getValue()).getPVCoordinates(), state1.shiftedBy(delta).getPVCoordinates() });
        // Range value
        range = tauD.add(tauU).multiply(0.5 * Constants.SPEED_OF_LIGHT);
    } else {
        estimated = new EstimatedMeasurement<>(this, iteration, evaluation, new SpacecraftState[] { state1.shiftedBy(deltaMTauD.getValue()), state2.shiftedBy(deltaMTauD.getValue()) }, new TimeStampedPVCoordinates[] { state2.shiftedBy(delta - tauD.getValue()).getPVCoordinates(), state1.shiftedBy(delta).getPVCoordinates() });
        // Range value
        range = tauD.multiply(Constants.SPEED_OF_LIGHT);
    }
    estimated.setEstimatedValue(range.getValue());
    // Range partial derivatives with respect to states
    final double[] derivatives = range.getAllDerivatives();
    estimated.setStateDerivatives(0, Arrays.copyOfRange(derivatives, 1, 7));
    estimated.setStateDerivatives(1, Arrays.copyOfRange(derivatives, 7, 13));
    return estimated;
}

Example 40 with FieldAbsoluteDate

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

the class FieldEquinoctialOrbitTest method doTestNonInertialFrame.

private <T extends RealFieldElement<T>> void doTestNonInertialFrame(Field<T> field) throws IllegalArgumentException {
    T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field);
    FieldVector3D<T> position = new FieldVector3D<>(zero.add(4512.9), zero.add(18260.), zero.add(-5127.));
    FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(134664.6), zero.add(90066.8), zero.add(72047.6));
    FieldPVCoordinates<T> FieldPVCoordinates = new FieldPVCoordinates<>(position, velocity);
    new FieldEquinoctialOrbit<>(FieldPVCoordinates, new Frame(FramesFactory.getEME2000(), Transform.IDENTITY, "non-inertial", false), date, mu);
}