Examples with OrekitException org.orekit.errors.OrekitException used on opensource projects

Example 31 with OrekitException

use of org.orekit.errors.OrekitException in project Orekit by CS-SI.

the class RangeRateTest method testParameterDerivativesOneWay.

@Test
public void testParameterDerivativesOneWay() throws OrekitException {
    Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
    final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
    // create perfect range rate measurements
    for (final GroundStation station : context.stations) {
        station.getEastOffsetDriver().setSelected(true);
        station.getNorthOffsetDriver().setSelected(true);
        station.getZenithOffsetDriver().setSelected(true);
    }
    final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new RangeRateMeasurementCreator(context, false), 1.0, 3.0, 300.0);
    propagator.setSlaveMode();
    double maxRelativeError = 0;
    for (final ObservedMeasurement<?> measurement : measurements) {
        // parameter corresponding to station position offset
        final GroundStation stationParameter = ((RangeRate) measurement).getStation();
        // We intentionally propagate to a date which is close to the
        // real spacecraft state but is *not* the accurate date, by
        // compensating only part of the downlink delay. This is done
        // in order to validate the partial derivatives with respect
        // to velocity. If we had chosen the proper state date, the
        // range would have depended only on the current position but
        // not on the current velocity.
        final double meanDelay = measurement.getObservedValue()[0] / Constants.SPEED_OF_LIGHT;
        final AbsoluteDate date = measurement.getDate().shiftedBy(-0.75 * meanDelay);
        final SpacecraftState state = propagator.propagate(date);
        final ParameterDriver[] drivers = new ParameterDriver[] { stationParameter.getEastOffsetDriver(), stationParameter.getNorthOffsetDriver(), stationParameter.getZenithOffsetDriver() };
        for (int i = 0; i < 3; ++i) {
            final double[] gradient = measurement.estimate(0, 0, new SpacecraftState[] { state }).getParameterDerivatives(drivers[i]);
            Assert.assertEquals(1, measurement.getDimension());
            Assert.assertEquals(1, gradient.length);
            final ParameterFunction dMkdP = Differentiation.differentiate(new ParameterFunction() {

                /**
                 * {@inheritDoc}
                 */
                @Override
                public double value(final ParameterDriver parameterDriver) throws OrekitException {
                    return measurement.estimate(0, 0, new SpacecraftState[] { state }).getEstimatedValue()[0];
                }
            }, drivers[i], 3, 20.0);
            final double ref = dMkdP.value(drivers[i]);
            maxRelativeError = FastMath.max(maxRelativeError, FastMath.abs((ref - gradient[0]) / ref));
        }
    }
    Assert.assertEquals(0, maxRelativeError, 1.2e-6);
}

Example 32 with OrekitException

use of org.orekit.errors.OrekitException in project Orekit by CS-SI.

the class RangeRateTest method testParameterDerivativesTwoWays.

@Test
public void testParameterDerivativesTwoWays() throws OrekitException {
    Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
    final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
    // create perfect range rate measurements
    for (final GroundStation station : context.stations) {
        station.getEastOffsetDriver().setSelected(true);
        station.getNorthOffsetDriver().setSelected(true);
        station.getZenithOffsetDriver().setSelected(true);
    }
    final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new RangeRateMeasurementCreator(context, true), 1.0, 3.0, 300.0);
    propagator.setSlaveMode();
    double maxRelativeError = 0;
    for (final ObservedMeasurement<?> measurement : measurements) {
        // parameter corresponding to station position offset
        final GroundStation stationParameter = ((RangeRate) measurement).getStation();
        // We intentionally propagate to a date which is close to the
        // real spacecraft state but is *not* the accurate date, by
        // compensating only part of the downlink delay. This is done
        // in order to validate the partial derivatives with respect
        // to velocity. If we had chosen the proper state date, the
        // range would have depended only on the current position but
        // not on the current velocity.
        final double meanDelay = measurement.getObservedValue()[0] / Constants.SPEED_OF_LIGHT;
        final AbsoluteDate date = measurement.getDate().shiftedBy(-0.75 * meanDelay);
        final SpacecraftState state = propagator.propagate(date);
        final ParameterDriver[] drivers = new ParameterDriver[] { stationParameter.getEastOffsetDriver(), stationParameter.getNorthOffsetDriver(), stationParameter.getZenithOffsetDriver() };
        for (int i = 0; i < 3; ++i) {
            final double[] gradient = measurement.estimate(0, 0, new SpacecraftState[] { state }).getParameterDerivatives(drivers[i]);
            Assert.assertEquals(1, measurement.getDimension());
            Assert.assertEquals(1, gradient.length);
            final ParameterFunction dMkdP = Differentiation.differentiate(new ParameterFunction() {

                /**
                 * {@inheritDoc}
                 */
                @Override
                public double value(final ParameterDriver parameterDriver) throws OrekitException {
                    return measurement.estimate(0, 0, new SpacecraftState[] { state }).getEstimatedValue()[0];
                }
            }, drivers[i], 3, 20.0);
            final double ref = dMkdP.value(drivers[i]);
            maxRelativeError = FastMath.max(maxRelativeError, FastMath.abs((ref - gradient[0]) / ref));
        }
    }
    Assert.assertEquals(0, maxRelativeError, 5.2e-5);
}

Example 33 with OrekitException

use of org.orekit.errors.OrekitException in project Orekit by CS-SI.

the class RangeTest method genericTestParameterDerivatives.

void genericTestParameterDerivatives(final boolean isModifier, final boolean printResults, final double refErrorsMedian, final double refErrorsMean, final double refErrorsMax) throws OrekitException {
    Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
    final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
    // Create perfect range measurements
    for (final GroundStation station : context.stations) {
        station.getEastOffsetDriver().setSelected(true);
        station.getNorthOffsetDriver().setSelected(true);
        station.getZenithOffsetDriver().setSelected(true);
    }
    final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new RangeMeasurementCreator(context), 1.0, 3.0, 300.0);
    // List to store the results
    final List<Double> relErrorList = new ArrayList<Double>();
    // Set master mode
    // Use a lambda function to implement "handleStep" function
    propagator.setMasterMode((OrekitStepInterpolator interpolator, boolean isLast) -> {
        for (final ObservedMeasurement<?> measurement : measurements) {
            // Play test if the measurement date is between interpolator previous and current date
            if ((measurement.getDate().durationFrom(interpolator.getPreviousState().getDate()) > 0.) && (measurement.getDate().durationFrom(interpolator.getCurrentState().getDate()) <= 0.)) {
                // Add modifiers if test implies it
                final RangeTroposphericDelayModifier modifier = new RangeTroposphericDelayModifier(SaastamoinenModel.getStandardModel());
                if (isModifier) {
                    ((Range) measurement).addModifier(modifier);
                }
                // Parameter corresponding to station position offset
                final GroundStation stationParameter = ((Range) measurement).getStation();
                // We intentionally propagate to a date which is close to the
                // real spacecraft state but is *not* the accurate date, by
                // compensating only part of the downlink delay. This is done
                // in order to validate the partial derivatives with respect
                // to velocity. If we had chosen the proper state date, the
                // range would have depended only on the current position but
                // not on the current velocity.
                final double meanDelay = measurement.getObservedValue()[0] / Constants.SPEED_OF_LIGHT;
                final AbsoluteDate date = measurement.getDate().shiftedBy(-0.75 * meanDelay);
                final SpacecraftState state = interpolator.getInterpolatedState(date);
                final ParameterDriver[] drivers = new ParameterDriver[] { stationParameter.getEastOffsetDriver(), stationParameter.getNorthOffsetDriver(), stationParameter.getZenithOffsetDriver() };
                if (printResults) {
                    String stationName = ((Range) measurement).getStation().getBaseFrame().getName();
                    System.out.format(Locale.US, "%-15s  %-23s  %-23s  ", stationName, measurement.getDate(), date);
                }
                for (int i = 0; i < 3; ++i) {
                    final double[] gradient = measurement.estimate(0, 0, new SpacecraftState[] { state }).getParameterDerivatives(drivers[i]);
                    Assert.assertEquals(1, measurement.getDimension());
                    Assert.assertEquals(1, gradient.length);
                    // Compute a reference value using finite differences
                    final ParameterFunction dMkdP = Differentiation.differentiate(new ParameterFunction() {

                        /**
                         * {@inheritDoc}
                         */
                        @Override
                        public double value(final ParameterDriver parameterDriver) throws OrekitException {
                            return measurement.estimate(0, 0, new SpacecraftState[] { state }).getEstimatedValue()[0];
                        }
                    }, drivers[i], 3, 20.0);
                    final double ref = dMkdP.value(drivers[i]);
                    if (printResults) {
                        System.out.format(Locale.US, "%10.3e  %10.3e  ", gradient[0] - ref, FastMath.abs((gradient[0] - ref) / ref));
                    }
                    final double relError = FastMath.abs((ref - gradient[0]) / ref);
                    relErrorList.add(relError);
                // Assert.assertEquals(ref, gradient[0], 6.1e-5 * FastMath.abs(ref));
                }
                if (printResults) {
                    System.out.format(Locale.US, "%n");
                }
            }
        // End if measurement date between previous and current interpolator step
        }
    // End for loop on the measurements
    });
    // Rewind the propagator to initial date
    propagator.propagate(context.initialOrbit.getDate());
    // Sort measurements chronologically
    measurements.sort(new ChronologicalComparator());
    // Print results ? Header
    if (printResults) {
        System.out.format(Locale.US, "%-15s  %-23s  %-23s  " + "%10s  %10s  %10s  " + "%10s  %10s  %10s%n", "Station", "Measurement Date", "State Date", "ΔdQx", "rel ΔdQx", "ΔdQy", "rel ΔdQy", "ΔdQz", "rel ΔdQz");
    }
    // Propagate to final measurement's date
    propagator.propagate(measurements.get(measurements.size() - 1).getDate());
    // Convert error list to double[]
    final double[] relErrors = relErrorList.stream().mapToDouble(Double::doubleValue).toArray();
    // Compute statistics
    final double relErrorsMedian = new Median().evaluate(relErrors);
    final double relErrorsMean = new Mean().evaluate(relErrors);
    final double relErrorsMax = new Max().evaluate(relErrors);
    // Print the results on console ?
    if (printResults) {
        System.out.println();
        System.out.format(Locale.US, "Relative errors dR/dQ -> Median: %6.3e / Mean: %6.3e / Max: %6.3e%n", relErrorsMedian, relErrorsMean, relErrorsMax);
    }
    Assert.assertEquals(0.0, relErrorsMedian, refErrorsMedian);
    Assert.assertEquals(0.0, relErrorsMean, refErrorsMean);
    Assert.assertEquals(0.0, relErrorsMax, refErrorsMax);
}

Example 34 with OrekitException

use of org.orekit.errors.OrekitException in project Orekit by CS-SI.

the class PoissonSeriesParserTest method testMissingTerms.

@Test
public void testMissingTerms() throws OrekitException {
    try {
        String data = "  0.0 + 0.0 x - 0.0 x^2 - 0.0 x^3 - 0.0 x^4 + 0.0 x^5\n" + "j = 0  Nb of terms = 1\n" + "1 1.0 0.0 0 0 0 0 1 0 0 0 0 0 0 0 0 0\n" + "j = 1  Nb of terms = 3\n" + "2 1.0 0.0 0 0 0 0 1 0 0 0 0 0 0 0 0 0\n" + "3 1.0 0.0 0 0 0 0 0 2 0 0 0 0 0 0 0 0\n" + "j = 2  Nb of terms = 1\n" + "4 1.0 0.0 0 0 0 0 1 0 0 0 0 0 0 0 0 0\n";
        new PoissonSeriesParser(17).withPolynomialPart('x', PolynomialParser.Unit.NO_UNITS).withFirstDelaunay(4).withFirstPlanetary(9).withSinCos(0, 2, 1.0, 3, 1.0).parse(new ByteArrayInputStream(data.getBytes()), "");
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.NOT_A_SUPPORTED_IERS_DATA_FILE, oe.getSpecifier());
    }
}

Example 35 with OrekitException

use of org.orekit.errors.OrekitException in project Orekit by CS-SI.

the class PoissonSeriesParserTest method testWrongIndex.

@Test
public void testWrongIndex() throws OrekitException {
    String data = "Expression for the X coordinate of the CIP in the GCRS based on the IAU2000A\n" + "precession-nutation model\n" + "\n" + "\n" + "----------------------------------------------------------------------\n" + "\n" + "X = polynomial part + non-polynomial part\n" + "\n" + "----------------------------------------------------------------------\n" + "\n" + "Polynomial part (unit microarcsecond)\n" + "\n" + "  -16616.99 + 2004191742.88 t - 427219.05 t^2 - 198620.54 t^3 - 46.05 t^4 + 5.98 t^5\n" + "\n" + "----------------------------------------------------------------------\n" + "\n" + "Non-polynomial part (unit microarcsecond)\n" + "(ARG being for various combination of the fundamental arguments of the nutation theory)\n" + "\n" + "  Sum_i[a_{s,0})_i * sin(ARG) + a_{c,0})_i * cos(ARG)] \n" + "\n" + "+ Sum_i)j=1,4 [a_{s,j})_i * t^j * sin(ARG) + a_{c,j})_i * cos(ARG)] * t^j]\n" + "\n" + "The Table below provides the values for a_{s,j})_i and a_{c,j})_i\n" + "\n" + "The expressions for the fundamental arguments appearing in columns 4 to 8 (luni-solar part) \n" + "and in columns 6 to 17 (planetary part) are those of the IERS Conventions 2000\n" + "\n" + "----------------------------------------------------------------------\n" + "\n" + "    i    a_{s,j})_i      a_{c,j})_i    l    l'   F    D   Om L_Me L_Ve  L_E L_Ma  L_J L_Sa  L_U L_Ne  p_A\n" + "\n" + "----------------------------------------------------------------------\n" + "-16616.99 + 2004191742.88 t - 427219.05 t^2 - 198620.54 t^3 - 46.05 t^4 + 5.98 t^5\n" + "j = 0  Nb of terms = 2\n" + "\n" + "   1    -6844318.44        1328.67    0    0    0    0    1    0    0    0    0    0    0    0    0    0\n" + "   2           0.11           0.00    0    0    4   -4    4    0    0    0    0    0    0    0    0    0\n" + "\n" + "j = 1  Nb of terms = 2\n" + "\n" + "   3       -3328.48      205833.15    0    0    0    0    1    0    0    0    0    0    0    0    0    0\n" + "   4           0.00          -0.10    1   -1   -2   -2   -1    0    0    0    0    0    0    0    0    0\n" + "\n" + " j = 2  Nb of terms = 2\n" + "\n" + "   5        2038.00          82.26    0    0    0    0    1    0    0    0    0    0    0    0    0    0\n" + "   6          -0.12           0.00    1    0   -2   -2   -1    0    0    0    0    0    0    0    0    0\n" + "  \n" + " j = 3  Nb of terms = 2\n" + "\n" + "   7           1.76         -20.39    0    0    0    0    1    0    0    0    0    0    0    0    0    0\n" + " 999           0.00           0.20    0    0    0    0    2    0    0    0    0    0    0    0    0    0\n" + "\n" + " j = 4  Nb of terms = 1\n" + "       \n" + "   9          -0.10          -0.02    0    0    0    0    1    0    0    0    0    0    0    0    0    0\n";
    try {
        new PoissonSeriesParser(17).withPolynomialPart('t', PolynomialParser.Unit.NO_UNITS).withFirstDelaunay(4).withFirstPlanetary(9).withSinCos(0, 2, 1.0, 3, 1.0).parse(new ByteArrayInputStream(data.getBytes()), "dummy");
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.UNABLE_TO_PARSE_LINE_IN_FILE, oe.getSpecifier());
        Assert.assertEquals(53, oe.getParts()[0]);
        Assert.assertTrue(((String) oe.getParts()[2]).startsWith(" 999           0.00"));
    }
}