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

Example 11 with OrekitException

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

the class OceanTidesTest method testNoSetParameter.

@Test
public void testNoSetParameter() throws OrekitException {
    AstronomicalAmplitudeReader aaReader = new AstronomicalAmplitudeReader("hf-fes2004.dat", 5, 2, 3, 1.0);
    DataProvidersManager.getInstance().feed(aaReader.getSupportedNames(), aaReader);
    Map<Integer, Double> map = aaReader.getAstronomicalAmplitudesMap();
    GravityFieldFactory.addOceanTidesReader(new FESCHatEpsilonReader("fes2004-7x7.dat", 0.01, FastMath.toRadians(1.0), OceanLoadDeformationCoefficients.IERS_2010, map));
    ForceModel fm = new OceanTides(FramesFactory.getITRF(IERSConventions.IERS_1996, false), Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_MU, 5, 5, IERSConventions.IERS_1996, TimeScalesFactory.getUT1(IERSConventions.IERS_1996, false));
    Assert.assertEquals(1, fm.getParametersDrivers().length);
    try {
        fm.getParameterDriver("unknown").setValue(0.0);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException miae) {
        Assert.assertEquals(OrekitMessages.UNSUPPORTED_PARAMETER_NAME, miae.getSpecifier());
    }
}

Example 12 with OrekitException

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

the class AngularRaDecTest method testParameterDerivatives.

@Test
public void testParameterDerivatives() throws OrekitException {
    Context context = EstimationTestUtils.geoStationnaryContext("regular-data:potential:tides");
    final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.EQUINOCTIAL, PositionAngle.TRUE, false, 1.0e-6, 60.0, 0.001);
    // create perfect azimuth-elevation 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 AngularRaDecMeasurementCreator(context), 0.25, 3.0, 600.0);
    propagator.setSlaveMode();
    for (final ObservedMeasurement<?> measurement : measurements) {
        // parameter corresponding to station position offset
        final GroundStation stationParameter = ((AngularRaDec) 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
        // angular would have depended only on the current position but
        // not on the current velocity.
        final AbsoluteDate datemeas = measurement.getDate();
        final SpacecraftState stateini = propagator.propagate(datemeas);
        final Vector3D stationP = stationParameter.getOffsetToInertial(stateini.getFrame(), datemeas).transformPosition(Vector3D.ZERO);
        final double meanDelay = AbstractMeasurement.signalTimeOfFlight(stateini.getPVCoordinates(), stationP, datemeas);
        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(2, measurement.getDimension());
            Assert.assertEquals(2, gradient.length);
            for (final int k : new int[] { 0, 1 }) {
                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()[k];
                    }
                }, drivers[i], 3, 50.0);
                final double ref = dMkdP.value(drivers[i]);
                if (ref > 1.e-12) {
                    Assert.assertEquals(ref, gradient[k], 3e-9 * FastMath.abs(ref));
                }
            }
        }
    }
}

Example 13 with OrekitException

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

the class InterSatellitesRangeTest method genericTestStateDerivatives.

void genericTestStateDerivatives(final boolean printResults, final int index, final double refErrorsPMedian, final double refErrorsPMean, final double refErrorsPMax, final double refErrorsVMedian, final double refErrorsVMean, final double refErrorsVMax) 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 inter-satellites range measurements
    final TimeStampedPVCoordinates original = context.initialOrbit.getPVCoordinates();
    final Orbit closeOrbit = new CartesianOrbit(new TimeStampedPVCoordinates(context.initialOrbit.getDate(), original.getPosition().add(new Vector3D(1000, 2000, 3000)), original.getVelocity().add(new Vector3D(-0.03, 0.01, 0.02))), context.initialOrbit.getFrame(), context.initialOrbit.getMu());
    final Propagator closePropagator = EstimationTestUtils.createPropagator(closeOrbit, propagatorBuilder);
    closePropagator.setEphemerisMode();
    closePropagator.propagate(context.initialOrbit.getDate().shiftedBy(3.5 * closeOrbit.getKeplerianPeriod()));
    final BoundedPropagator ephemeris = closePropagator.getGeneratedEphemeris();
    final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new InterSatellitesRangeMeasurementCreator(ephemeris), 1.0, 3.0, 300.0);
    // Lists for results' storage - Used only for derivatives with respect to state
    // "final" value to be seen by "handleStep" function of the propagator
    final List<Double> errorsP = new ArrayList<Double>();
    final List<Double> errorsV = 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.)) {
                // 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.
                final double meanDelay = measurement.getObservedValue()[0] / Constants.SPEED_OF_LIGHT;
                final AbsoluteDate date = measurement.getDate().shiftedBy(-0.75 * meanDelay);
                final SpacecraftState[] states = { interpolator.getInterpolatedState(date), ephemeris.propagate(date) };
                final double[][] jacobian = measurement.estimate(0, 0, states).getStateDerivatives(index);
                // Jacobian reference value
                final double[][] jacobianRef;
                // Compute a reference value using finite differences
                jacobianRef = Differentiation.differentiate(new StateFunction() {

                    public double[] value(final SpacecraftState state) throws OrekitException {
                        final SpacecraftState[] s = states.clone();
                        s[index] = state;
                        return measurement.estimate(0, 0, s).getEstimatedValue();
                    }
                }, measurement.getDimension(), propagator.getAttitudeProvider(), OrbitType.CARTESIAN, PositionAngle.TRUE, 2.0, 3).value(states[index]);
                Assert.assertEquals(jacobianRef.length, jacobian.length);
                Assert.assertEquals(jacobianRef[0].length, jacobian[0].length);
                // Errors & relative errors on the Jacobian
                double[][] dJacobian = new double[jacobian.length][jacobian[0].length];
                double[][] dJacobianRelative = new double[jacobian.length][jacobian[0].length];
                for (int i = 0; i < jacobian.length; ++i) {
                    for (int j = 0; j < jacobian[i].length; ++j) {
                        dJacobian[i][j] = jacobian[i][j] - jacobianRef[i][j];
                        dJacobianRelative[i][j] = FastMath.abs(dJacobian[i][j] / jacobianRef[i][j]);
                        if (j < 3) {
                            errorsP.add(dJacobianRelative[i][j]);
                        } else {
                            errorsV.add(dJacobianRelative[i][j]);
                        }
                    }
                }
                // Print values in console ?
                if (printResults) {
                    System.out.format(Locale.US, "%-23s  %-23s  " + "%10.3e  %10.3e  %10.3e  " + "%10.3e  %10.3e  %10.3e  " + "%10.3e  %10.3e  %10.3e  " + "%10.3e  %10.3e  %10.3e%n", measurement.getDate(), date, dJacobian[0][0], dJacobian[0][1], dJacobian[0][2], dJacobian[0][3], dJacobian[0][4], dJacobian[0][5], dJacobianRelative[0][0], dJacobianRelative[0][1], dJacobianRelative[0][2], dJacobianRelative[0][3], dJacobianRelative[0][4], dJacobianRelative[0][5]);
                }
            }
        // End if measurement date between previous and current interpolator step
        }
    // End for loop on the measurements
    });
    // Print results on console ?
    if (printResults) {
        System.out.format(Locale.US, "%-23s  %-23s  " + "%10s  %10s  %10s  " + "%10s  %10s  %10s  " + "%10s  %10s  %10s  " + "%10s  %10s  %10s%n", "Measurement Date", "State Date", "ΔdPx", "ΔdPy", "ΔdPz", "ΔdVx", "ΔdVy", "ΔdVz", "rel ΔdPx", "rel ΔdPy", "rel ΔdPz", "rel ΔdVx", "rel ΔdVy", "rel ΔdVz");
    }
    // Rewind the propagator to initial date
    propagator.propagate(context.initialOrbit.getDate());
    // Sort measurements chronologically
    measurements.sort(new ChronologicalComparator());
    // Propagate to final measurement's date
    propagator.propagate(measurements.get(measurements.size() - 1).getDate());
    // Convert lists to double[] and evaluate some statistics
    final double[] relErrorsP = errorsP.stream().mapToDouble(Double::doubleValue).toArray();
    final double[] relErrorsV = errorsV.stream().mapToDouble(Double::doubleValue).toArray();
    final double errorsPMedian = new Median().evaluate(relErrorsP);
    final double errorsPMean = new Mean().evaluate(relErrorsP);
    final double errorsPMax = new Max().evaluate(relErrorsP);
    final double errorsVMedian = new Median().evaluate(relErrorsV);
    final double errorsVMean = new Mean().evaluate(relErrorsV);
    final double errorsVMax = new Max().evaluate(relErrorsV);
    // Print the results on console ?
    if (printResults) {
        System.out.println();
        System.out.format(Locale.US, "Relative errors dR/dP -> Median: %6.3e / Mean: %6.3e / Max: %6.3e%n", errorsPMedian, errorsPMean, errorsPMax);
        System.out.format(Locale.US, "Relative errors dR/dV -> Median: %6.3e / Mean: %6.3e / Max: %6.3e%n", errorsVMedian, errorsVMean, errorsVMax);
    }
    Assert.assertEquals(0.0, errorsPMedian, refErrorsPMedian);
    Assert.assertEquals(0.0, errorsPMean, refErrorsPMean);
    Assert.assertEquals(0.0, errorsPMax, refErrorsPMax);
    Assert.assertEquals(0.0, errorsVMedian, refErrorsVMedian);
    Assert.assertEquals(0.0, errorsVMean, refErrorsVMean);
    Assert.assertEquals(0.0, errorsVMax, refErrorsVMax);
}

Example 14 with OrekitException

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

the class KalmanOrbitDeterminationTest method readMeasurements.

/**
 * Read a measurements file.
 * @param file measurements file
 * @param stations name to stations data map
 * @param pvData PV measurements data
 * @param satRangeBias range bias due to transponder delay
 * @param weights base weights for measurements
 * @param rangeOutliersManager manager for range measurements outliers (null if none configured)
 * @param rangeRateOutliersManager manager for range-rate measurements outliers (null if none configured)
 * @param azElOutliersManager manager for azimuth-elevation measurements outliers (null if none configured)
 * @param pvOutliersManager manager for PV measurements outliers (null if none configured)
 * @return measurements list
 */
private List<ObservedMeasurement<?>> readMeasurements(final File file, final Map<String, StationData> stations, final PVData pvData, final Bias<Range> satRangeBias, final Weights weights, final OutlierFilter<Range> rangeOutliersManager, final OutlierFilter<RangeRate> rangeRateOutliersManager, final OutlierFilter<AngularAzEl> azElOutliersManager, final OutlierFilter<PV> pvOutliersManager) throws UnsupportedEncodingException, IOException, OrekitException {
    final List<ObservedMeasurement<?>> measurements = new ArrayList<ObservedMeasurement<?>>();
    BufferedReader br = null;
    try {
        br = new BufferedReader(new InputStreamReader(new FileInputStream(file), "UTF-8"));
        int lineNumber = 0;
        for (String line = br.readLine(); line != null; line = br.readLine()) {
            ++lineNumber;
            line = line.trim();
            if (line.length() > 0 && !line.startsWith("#")) {
                String[] fields = line.split("\\s+");
                if (fields.length < 2) {
                    throw new OrekitException(OrekitMessages.UNABLE_TO_PARSE_LINE_IN_FILE, lineNumber, file.getName(), line);
                }
                switch(fields[1]) {
                    case "RANGE":
                        final Range range = new RangeParser().parseFields(fields, stations, pvData, satRangeBias, weights, line, lineNumber, file.getName());
                        if (rangeOutliersManager != null) {
                            range.addModifier(rangeOutliersManager);
                        }
                        addIfNonZeroWeight(range, measurements);
                        break;
                    case "RANGE_RATE":
                        final RangeRate rangeRate = new RangeRateParser().parseFields(fields, stations, pvData, satRangeBias, weights, line, lineNumber, file.getName());
                        if (rangeOutliersManager != null) {
                            rangeRate.addModifier(rangeRateOutliersManager);
                        }
                        addIfNonZeroWeight(rangeRate, measurements);
                        break;
                    case "AZ_EL":
                        final AngularAzEl angular = new AzElParser().parseFields(fields, stations, pvData, satRangeBias, weights, line, lineNumber, file.getName());
                        if (azElOutliersManager != null) {
                            angular.addModifier(azElOutliersManager);
                        }
                        addIfNonZeroWeight(angular, measurements);
                        break;
                    case "PV":
                        final PV pv = new PVParser().parseFields(fields, stations, pvData, satRangeBias, weights, line, lineNumber, file.getName());
                        if (pvOutliersManager != null) {
                            pv.addModifier(pvOutliersManager);
                        }
                        addIfNonZeroWeight(pv, measurements);
                        break;
                    default:
                        throw new OrekitException(LocalizedCoreFormats.SIMPLE_MESSAGE, "unknown measurement type " + fields[1] + " at line " + lineNumber + " in file " + file.getName());
                }
            }
        }
    } finally {
        if (br != null) {
            br.close();
        }
    }
    if (measurements.isEmpty()) {
        throw new OrekitException(LocalizedCoreFormats.SIMPLE_MESSAGE, "not measurements read from file " + file.getAbsolutePath());
    }
    return measurements;
}

Example 15 with OrekitException

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

the class OMMParserTest method testParseOMM1.

@Test
public void testParseOMM1() throws OrekitException {
    // simple test for OMM file, contains p/v entries and other mandatory
    // data.
    final String ex = "/ccsds/OMMExample.txt";
    // initialize parser with purposely wrong international designator
    // (in order to check it is correctly overridden when parsing)
    final OMMParser parser = new OMMParser().withMu(398600e9).withInternationalDesignator(1998, 1, "a");
    final InputStream inEntry = getClass().getResourceAsStream(ex);
    final OMMFile file = parser.parse(inEntry);
    // Check Header Block;
    Assert.assertEquals(2.0, file.getFormatVersion(), 1.0e-10);
    Assert.assertEquals(new AbsoluteDate(2007, 03, 06, 16, 00, 00, TimeScalesFactory.getUTC()), file.getCreationDate());
    Assert.assertEquals("NOAA/USA", file.getOriginator());
    // Check Metadata Block;
    Assert.assertEquals("GOES 9", file.getMetaData().getObjectName());
    Assert.assertEquals("1995-025A", file.getMetaData().getObjectID());
    Assert.assertEquals("EARTH", file.getMetaData().getCenterName());
    Assert.assertTrue(file.getMetaData().getHasCreatableBody());
    Assert.assertEquals(file.getMetaData().getCenterBody(), CelestialBodyFactory.getEarth());
    Assert.assertEquals(file.getMetaData().getFrame(), FramesFactory.getTEME());
    Assert.assertEquals(file.getMetaData().getTimeSystem(), CcsdsTimeScale.UTC);
    Assert.assertEquals("SGP/SGP4", file.getMetaData().getMeanElementTheory());
    Assert.assertEquals("TEME", file.getMetaData().getFrame().toString());
    Assert.assertTrue(file.getTLERelatedParametersComment().isEmpty());
    // Check Mean Keplerian elements data block;
    Assert.assertEquals(new AbsoluteDate(2007, 03, 05, 10, 34, 41.4264, TimeScalesFactory.getUTC()), file.getEpoch());
    Assert.assertEquals(file.getMeanMotion(), 1.00273272 * FastMath.PI / 43200.0, 1e-10);
    Assert.assertEquals(file.getE(), 0.0005013, 1e-10);
    Assert.assertEquals(file.getI(), FastMath.toRadians(3.0539), 1e-10);
    Assert.assertEquals(file.getRaan(), FastMath.toRadians(81.7939), 1e-10);
    Assert.assertEquals(file.getPa(), FastMath.toRadians(249.2363), 1e-10);
    Assert.assertEquals(file.getAnomaly(), FastMath.toRadians(150.1602), 1e-10);
    Assert.assertEquals(file.getMuParsed(), 398600.8 * 1e9, 1e-10);
    Assert.assertEquals(file.getMuSet(), 398600e9, 1e-10);
    Assert.assertEquals(file.getMuCreated(), CelestialBodyFactory.getEarth().getGM(), 1e-10);
    // Check TLE Related Parameters data block;
    Assert.assertEquals(0, file.getEphemerisType());
    Assert.assertEquals('U', file.getClassificationType());
    int[] noradIDExpected = new int[23581];
    int[] noradIDActual = new int[file.getNoradID()];
    Assert.assertEquals(noradIDExpected[0], noradIDActual[0]);
    Assert.assertEquals("0925", file.getElementSetNumber());
    int[] revAtEpochExpected = new int[4316];
    int[] revAtEpochActual = new int[file.getRevAtEpoch()];
    Assert.assertEquals(1.00273272 * FastMath.PI / 43200.0, file.getMeanMotion(), 1e-10);
    Assert.assertEquals(revAtEpochExpected[0], revAtEpochActual[0]);
    Assert.assertEquals(file.getBStar(), 0.0001, 1e-10);
    Assert.assertEquals(file.getMeanMotionDot(), -0.00000113 * FastMath.PI / 1.86624e9, 1e-12);
    Assert.assertEquals(file.getMeanMotionDotDot(), 0.0 * FastMath.PI / 5.3747712e13, 1e-10);
    Assert.assertEquals(1995, file.getMetaData().getLaunchYear());
    Assert.assertEquals(25, file.getMetaData().getLaunchNumber());
    Assert.assertEquals("A", file.getMetaData().getLaunchPiece());
    file.generateCartesianOrbit();
    file.generateKeplerianOrbit();
    try {
        file.generateSpacecraftState();
    } catch (OrekitException orekitException) {
        Assert.assertEquals(OrekitMessages.CCSDS_UNKNOWN_SPACECRAFT_MASS, orekitException.getSpecifier());
    } finally {
    }
    file.generateTLE();
}