Examples with ICGEMFormatReader org.orekit.forces.gravity.potential.ICGEMFormatReader used on opensource projects

Example 11 with ICGEMFormatReader

use of org.orekit.forces.gravity.potential.ICGEMFormatReader in project Orekit by CS-SI.

the class KalmanOrbitDeterminationTest method run.

/**
 * Function running the Kalman filter estimation.
 * @param input Input configuration file
 * @param orbitType Orbit type to use (calculation and display)
 * @param print Choose whether the results are printed on console or not
 * @param cartesianOrbitalP Orbital part of the initial covariance matrix in Cartesian formalism
 * @param cartesianOrbitalQ Orbital part of the process noise matrix in Cartesian formalism
 * @param propagationP Propagation part of the initial covariance matrix
 * @param propagationQ Propagation part of the process noise matrix
 * @param measurementP Measurement part of the initial covariance matrix
 * @param measurementQ Measurement part of the process noise matrix
 */
private ResultKalman run(final File input, final OrbitType orbitType, final boolean print, final RealMatrix cartesianOrbitalP, final RealMatrix cartesianOrbitalQ, final RealMatrix propagationP, final RealMatrix propagationQ, final RealMatrix measurementP, final RealMatrix measurementQ) throws IOException, IllegalArgumentException, OrekitException, ParseException {
    // Read input parameters
    KeyValueFileParser<ParameterKey> parser = new KeyValueFileParser<ParameterKey>(ParameterKey.class);
    parser.parseInput(input.getAbsolutePath(), new FileInputStream(input));
    // Log files
    final RangeLog rangeLog = new RangeLog();
    final RangeRateLog rangeRateLog = new RangeRateLog();
    final AzimuthLog azimuthLog = new AzimuthLog();
    final ElevationLog elevationLog = new ElevationLog();
    final PositionLog positionLog = new PositionLog();
    final VelocityLog velocityLog = new VelocityLog();
    // Gravity field
    GravityFieldFactory.addPotentialCoefficientsReader(new ICGEMFormatReader("eigen-5c.gfc", true));
    final NormalizedSphericalHarmonicsProvider gravityField = createGravityField(parser);
    // Orbit initial guess
    Orbit initialGuess = createOrbit(parser, gravityField.getMu());
    // Convert to desired orbit type
    initialGuess = orbitType.convertType(initialGuess);
    // IERS conventions
    final IERSConventions conventions;
    if (!parser.containsKey(ParameterKey.IERS_CONVENTIONS)) {
        conventions = IERSConventions.IERS_2010;
    } else {
        conventions = IERSConventions.valueOf("IERS_" + parser.getInt(ParameterKey.IERS_CONVENTIONS));
    }
    // Central body
    final OneAxisEllipsoid body = createBody(parser);
    // Propagator builder
    final NumericalPropagatorBuilder propagatorBuilder = createPropagatorBuilder(parser, conventions, gravityField, body, initialGuess);
    // Measurements
    final List<ObservedMeasurement<?>> measurements = new ArrayList<ObservedMeasurement<?>>();
    for (final String fileName : parser.getStringsList(ParameterKey.MEASUREMENTS_FILES, ',')) {
        measurements.addAll(readMeasurements(new File(input.getParentFile(), fileName), createStationsData(parser, body), createPVData(parser), createSatRangeBias(parser), createWeights(parser), createRangeOutliersManager(parser), createRangeRateOutliersManager(parser), createAzElOutliersManager(parser), createPVOutliersManager(parser)));
    }
    // Building the Kalman filter:
    // - Gather the estimated measurement parameters in a list
    // - Prepare the initial covariance matrix and the process noise matrix
    // - Build the Kalman filter
    // --------------------------------------------------------------------
    // Build the list of estimated measurements
    final ParameterDriversList estimatedMeasurementsParameters = new ParameterDriversList();
    for (ObservedMeasurement<?> measurement : measurements) {
        final List<ParameterDriver> drivers = measurement.getParametersDrivers();
        for (ParameterDriver driver : drivers) {
            if (driver.isSelected()) {
                // Add the driver
                estimatedMeasurementsParameters.add(driver);
            }
        }
    }
    // Sort the list lexicographically
    estimatedMeasurementsParameters.sort();
    // Orbital covariance matrix initialization
    // Jacobian of the orbital parameters w/r to Cartesian
    final double[][] dYdC = new double[6][6];
    initialGuess.getJacobianWrtCartesian(propagatorBuilder.getPositionAngle(), dYdC);
    final RealMatrix Jac = MatrixUtils.createRealMatrix(dYdC);
    RealMatrix orbitalP = Jac.multiply(cartesianOrbitalP.multiply(Jac.transpose()));
    // Orbital process noise matrix
    RealMatrix orbitalQ = Jac.multiply(cartesianOrbitalQ.multiply(Jac.transpose()));
    // Build the full covariance matrix and process noise matrix
    final int nbPropag = (propagationP != null) ? propagationP.getRowDimension() : 0;
    final int nbMeas = (measurementP != null) ? measurementP.getRowDimension() : 0;
    final RealMatrix initialP = MatrixUtils.createRealMatrix(6 + nbPropag + nbMeas, 6 + nbPropag + nbMeas);
    final RealMatrix Q = MatrixUtils.createRealMatrix(6 + nbPropag + nbMeas, 6 + nbPropag + nbMeas);
    // Orbital part
    initialP.setSubMatrix(orbitalP.getData(), 0, 0);
    Q.setSubMatrix(orbitalQ.getData(), 0, 0);
    // Propagation part
    if (propagationP != null) {
        initialP.setSubMatrix(propagationP.getData(), 6, 6);
        Q.setSubMatrix(propagationQ.getData(), 6, 6);
    }
    // Measurement part
    if (measurementP != null) {
        initialP.setSubMatrix(measurementP.getData(), 6 + nbPropag, 6 + nbPropag);
        Q.setSubMatrix(measurementQ.getData(), 6 + nbPropag, 6 + nbPropag);
    }
    // Build the Kalman
    KalmanEstimatorBuilder kalmanBuilder = new KalmanEstimatorBuilder();
    kalmanBuilder.builder(propagatorBuilder);
    kalmanBuilder.estimatedMeasurementsParameters(estimatedMeasurementsParameters);
    kalmanBuilder.initialCovarianceMatrix(initialP);
    kalmanBuilder.processNoiseMatrixProvider(new ConstantProcessNoise(Q));
    final KalmanEstimator kalman = kalmanBuilder.build();
    // Add an observer
    kalman.setObserver(new KalmanObserver() {

        /**
         * Date of the first measurement.
         */
        private AbsoluteDate t0;

        /**
         * {@inheritDoc}
         * @throws OrekitException
         */
        @Override
        @SuppressWarnings("unchecked")
        public void evaluationPerformed(final KalmanEstimation estimation) throws OrekitException {
            // Current measurement number, date and status
            final EstimatedMeasurement<?> estimatedMeasurement = estimation.getCorrectedMeasurement();
            final int currentNumber = estimation.getCurrentMeasurementNumber();
            final AbsoluteDate currentDate = estimatedMeasurement.getDate();
            final EstimatedMeasurement.Status currentStatus = estimatedMeasurement.getStatus();
            // Current estimated measurement
            final ObservedMeasurement<?> observedMeasurement = estimatedMeasurement.getObservedMeasurement();
            // Measurement type & Station name
            String measType = "";
            String stationName = "";
            // Register the measurement in the proper measurement logger
            if (observedMeasurement instanceof Range) {
                // Add the tuple (estimation, prediction) to the log
                rangeLog.add(currentNumber, (EstimatedMeasurement<Range>) estimatedMeasurement);
                // Measurement type & Station name
                measType = "RANGE";
                stationName = ((EstimatedMeasurement<Range>) estimatedMeasurement).getObservedMeasurement().getStation().getBaseFrame().getName();
            } else if (observedMeasurement instanceof RangeRate) {
                rangeRateLog.add(currentNumber, (EstimatedMeasurement<RangeRate>) estimatedMeasurement);
                measType = "RANGE_RATE";
                stationName = ((EstimatedMeasurement<RangeRate>) estimatedMeasurement).getObservedMeasurement().getStation().getBaseFrame().getName();
            } else if (observedMeasurement instanceof AngularAzEl) {
                azimuthLog.add(currentNumber, (EstimatedMeasurement<AngularAzEl>) estimatedMeasurement);
                elevationLog.add(currentNumber, (EstimatedMeasurement<AngularAzEl>) estimatedMeasurement);
                measType = "AZ_EL";
                stationName = ((EstimatedMeasurement<AngularAzEl>) estimatedMeasurement).getObservedMeasurement().getStation().getBaseFrame().getName();
            } else if (observedMeasurement instanceof PV) {
                positionLog.add(currentNumber, (EstimatedMeasurement<PV>) estimatedMeasurement);
                velocityLog.add(currentNumber, (EstimatedMeasurement<PV>) estimatedMeasurement);
                measType = "PV";
            }
            // Header
            if (print) {
                if (currentNumber == 1) {
                    // Set t0 to first measurement date
                    t0 = currentDate;
                    // Print header
                    final String formatHeader = "%-4s\t%-25s\t%15s\t%-10s\t%-10s\t%-20s\t%20s\t%20s";
                    String header = String.format(Locale.US, formatHeader, "Nb", "Epoch", "Dt[s]", "Status", "Type", "Station", "DP Corr", "DV Corr");
                    // Orbital drivers
                    for (DelegatingDriver driver : estimation.getEstimatedOrbitalParameters().getDrivers()) {
                        header += String.format(Locale.US, "\t%20s", driver.getName());
                        header += String.format(Locale.US, "\t%20s", "D" + driver.getName());
                    }
                    // Propagation drivers
                    for (DelegatingDriver driver : estimation.getEstimatedPropagationParameters().getDrivers()) {
                        header += String.format(Locale.US, "\t%20s", driver.getName());
                        header += String.format(Locale.US, "\t%20s", "D" + driver.getName());
                    }
                    // Measurements drivers
                    for (DelegatingDriver driver : estimation.getEstimatedMeasurementsParameters().getDrivers()) {
                        header += String.format(Locale.US, "\t%20s", driver.getName());
                        header += String.format(Locale.US, "\t%20s", "D" + driver.getName());
                    }
                    // Print header
                    System.out.println(header);
                }
                // Print current measurement info in terminal
                String line = "";
                // Line format
                final String lineFormat = "%4d\t%-25s\t%15.3f\t%-10s\t%-10s\t%-20s\t%20.9e\t%20.9e";
                // Orbital correction = DP & DV between predicted orbit and estimated orbit
                final Vector3D predictedP = estimation.getPredictedSpacecraftStates()[0].getPVCoordinates().getPosition();
                final Vector3D predictedV = estimation.getPredictedSpacecraftStates()[0].getPVCoordinates().getVelocity();
                final Vector3D estimatedP = estimation.getCorrectedSpacecraftStates()[0].getPVCoordinates().getPosition();
                final Vector3D estimatedV = estimation.getCorrectedSpacecraftStates()[0].getPVCoordinates().getVelocity();
                final double DPcorr = Vector3D.distance(predictedP, estimatedP);
                final double DVcorr = Vector3D.distance(predictedV, estimatedV);
                line = String.format(Locale.US, lineFormat, currentNumber, currentDate.toString(), currentDate.durationFrom(t0), currentStatus.toString(), measType, stationName, DPcorr, DVcorr);
                // Handle parameters printing (value and error)
                int jPar = 0;
                final RealMatrix Pest = estimation.getPhysicalEstimatedCovarianceMatrix();
                // Orbital drivers
                for (DelegatingDriver driver : estimation.getEstimatedOrbitalParameters().getDrivers()) {
                    line += String.format(Locale.US, "\t%20.9f", driver.getValue());
                    line += String.format(Locale.US, "\t%20.9e", FastMath.sqrt(Pest.getEntry(jPar, jPar)));
                    jPar++;
                }
                // Propagation drivers
                for (DelegatingDriver driver : estimation.getEstimatedPropagationParameters().getDrivers()) {
                    line += String.format(Locale.US, "\t%20.9f", driver.getValue());
                    line += String.format(Locale.US, "\t%20.9e", FastMath.sqrt(Pest.getEntry(jPar, jPar)));
                    jPar++;
                }
                // Measurements drivers
                for (DelegatingDriver driver : estimatedMeasurementsParameters.getDrivers()) {
                    line += String.format(Locale.US, "\t%20.9f", driver.getValue());
                    line += String.format(Locale.US, "\t%20.9e", FastMath.sqrt(Pest.getEntry(jPar, jPar)));
                    jPar++;
                }
                // Print the line
                System.out.println(line);
            }
        }
    });
    // Process the list measurements
    final Orbit estimated = kalman.processMeasurements(measurements).getInitialState().getOrbit();
    // Get the last estimated physical covariances
    final RealMatrix covarianceMatrix = kalman.getPhysicalEstimatedCovarianceMatrix();
    // Parameters and measurements.
    final ParameterDriversList propagationParameters = kalman.getPropagationParametersDrivers(true);
    final ParameterDriversList measurementsParameters = kalman.getEstimatedMeasurementsParameters();
    // Eventually, print parameter changes, statistics and covariances
    if (print) {
        // Display parameter change for non orbital drivers
        int length = 0;
        for (final ParameterDriver parameterDriver : propagationParameters.getDrivers()) {
            length = FastMath.max(length, parameterDriver.getName().length());
        }
        for (final ParameterDriver parameterDriver : measurementsParameters.getDrivers()) {
            length = FastMath.max(length, parameterDriver.getName().length());
        }
        if (propagationParameters.getNbParams() > 0) {
            displayParametersChanges(System.out, "Estimated propagator parameters changes: ", true, length, propagationParameters);
        }
        if (measurementsParameters.getNbParams() > 0) {
            displayParametersChanges(System.out, "Estimated measurements parameters changes: ", true, length, measurementsParameters);
        }
        // Measurements statistics summary
        System.out.println("");
        rangeLog.displaySummary(System.out);
        rangeRateLog.displaySummary(System.out);
        azimuthLog.displaySummary(System.out);
        elevationLog.displaySummary(System.out);
        positionLog.displaySummary(System.out);
        velocityLog.displaySummary(System.out);
        // Covariances and sigmas
        displayFinalCovariances(System.out, kalman);
    }
    // Instantiation of the results
    return new ResultKalman(propagationParameters, measurementsParameters, kalman.getCurrentMeasurementNumber(), estimated.getPVCoordinates(), rangeLog.createStatisticsSummary(), rangeRateLog.createStatisticsSummary(), azimuthLog.createStatisticsSummary(), elevationLog.createStatisticsSummary(), positionLog.createStatisticsSummary(), velocityLog.createStatisticsSummary(), covarianceMatrix);
}

Example 12 with ICGEMFormatReader

use of org.orekit.forces.gravity.potential.ICGEMFormatReader in project Orekit by CS-SI.

the class OrbitDeterminationTest method testW3B.

@Test
public // Orbit determination for range, azimuth elevation measurements
void testW3B() throws URISyntaxException, IllegalArgumentException, IOException, OrekitException, ParseException {
    // input in tutorial resources directory/output
    final String inputPath = OrbitDeterminationTest.class.getClassLoader().getResource("orbit-determination/W3B/od_test_W3.in").toURI().getPath();
    final File input = new File(inputPath);
    // configure Orekit data access
    Utils.setDataRoot("orbit-determination/W3B:potential/icgem-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new ICGEMFormatReader("eigen-6s-truncated", true));
    // orbit determination run.
    ResultOD odsatW3 = run(input, false);
    // test
    // definition of the accuracy for the test
    final double distanceAccuracy = 0.1;
    final double velocityAccuracy = 1e-4;
    final double angleAccuracy = 1e-5;
    // test on the convergence (with some margins)
    Assert.assertTrue(odsatW3.getNumberOfIteration() < 6);
    Assert.assertTrue(odsatW3.getNumberOfEvaluation() < 10);
    // test on the estimated position and velocity
    final Vector3D estimatedPos = odsatW3.getEstimatedPV().getPosition();
    final Vector3D estimatedVel = odsatW3.getEstimatedPV().getVelocity();
    final Vector3D refPos = new Vector3D(-40541446.255, -9905357.41, 206777.413);
    final Vector3D refVel = new Vector3D(759.0685, -1476.5156, 54.793);
    Assert.assertEquals(0.0, Vector3D.distance(refPos, estimatedPos), distanceAccuracy);
    Assert.assertEquals(0.0, Vector3D.distance(refVel, estimatedVel), velocityAccuracy);
    // test on propagator parameters
    final double dragCoef = -0.2154;
    Assert.assertEquals(dragCoef, odsatW3.propagatorParameters.getDrivers().get(0).getValue(), 1e-3);
    final Vector3D leakAcceleration0 = new Vector3D(odsatW3.propagatorParameters.getDrivers().get(1).getValue(), odsatW3.propagatorParameters.getDrivers().get(3).getValue(), odsatW3.propagatorParameters.getDrivers().get(5).getValue());
    // Assert.assertEquals(7.215e-6, leakAcceleration.getNorm(), 1.0e-8);
    Assert.assertEquals(8.002e-6, leakAcceleration0.getNorm(), 1.0e-8);
    final Vector3D leakAcceleration1 = new Vector3D(odsatW3.propagatorParameters.getDrivers().get(2).getValue(), odsatW3.propagatorParameters.getDrivers().get(4).getValue(), odsatW3.propagatorParameters.getDrivers().get(6).getValue());
    Assert.assertEquals(3.058e-10, leakAcceleration1.getNorm(), 1.0e-12);
    // test on measurements parameters
    final List<DelegatingDriver> list = new ArrayList<DelegatingDriver>();
    list.addAll(odsatW3.measurementsParameters.getDrivers());
    sortParametersChanges(list);
    // station CastleRock
    final double[] CastleAzElBias = { 0.062701342, -0.003613508 };
    final double CastleRangeBias = 11274.4677;
    Assert.assertEquals(CastleAzElBias[0], FastMath.toDegrees(list.get(0).getValue()), angleAccuracy);
    Assert.assertEquals(CastleAzElBias[1], FastMath.toDegrees(list.get(1).getValue()), angleAccuracy);
    Assert.assertEquals(CastleRangeBias, list.get(2).getValue(), distanceAccuracy);
    // station Fucino
    final double[] FucAzElBias = { -0.053526137, 0.075483886 };
    final double FucRangeBias = 13467.8256;
    Assert.assertEquals(FucAzElBias[0], FastMath.toDegrees(list.get(3).getValue()), angleAccuracy);
    Assert.assertEquals(FucAzElBias[1], FastMath.toDegrees(list.get(4).getValue()), angleAccuracy);
    Assert.assertEquals(FucRangeBias, list.get(5).getValue(), distanceAccuracy);
    // station Kumsan
    final double[] KumAzElBias = { -0.023574208, -0.054520756 };
    final double KumRangeBias = 13512.57594;
    Assert.assertEquals(KumAzElBias[0], FastMath.toDegrees(list.get(6).getValue()), angleAccuracy);
    Assert.assertEquals(KumAzElBias[1], FastMath.toDegrees(list.get(7).getValue()), angleAccuracy);
    Assert.assertEquals(KumRangeBias, list.get(8).getValue(), distanceAccuracy);
    // station Pretoria
    final double[] PreAzElBias = { 0.030201539, 0.009747877 };
    final double PreRangeBias = 13594.11889;
    Assert.assertEquals(PreAzElBias[0], FastMath.toDegrees(list.get(9).getValue()), angleAccuracy);
    Assert.assertEquals(PreAzElBias[1], FastMath.toDegrees(list.get(10).getValue()), angleAccuracy);
    Assert.assertEquals(PreRangeBias, list.get(11).getValue(), distanceAccuracy);
    // station Uralla
    final double[] UraAzElBias = { 0.167814449, -0.12305252 };
    final double UraRangeBias = 13450.26738;
    Assert.assertEquals(UraAzElBias[0], FastMath.toDegrees(list.get(12).getValue()), angleAccuracy);
    Assert.assertEquals(UraAzElBias[1], FastMath.toDegrees(list.get(13).getValue()), angleAccuracy);
    Assert.assertEquals(UraRangeBias, list.get(14).getValue(), distanceAccuracy);
    // test on statistic for the range residuals
    final long nbRange = 182;
    // statistics for the range residual (min, max, mean, std)
    final double[] RefStatRange = { -18.39149369, 12.54165259, -4.32E-05, 4.374712716 };
    Assert.assertEquals(nbRange, odsatW3.getRangeStat().getN());
    Assert.assertEquals(RefStatRange[0], odsatW3.getRangeStat().getMin(), distanceAccuracy);
    Assert.assertEquals(RefStatRange[1], odsatW3.getRangeStat().getMax(), distanceAccuracy);
    Assert.assertEquals(RefStatRange[2], odsatW3.getRangeStat().getMean(), distanceAccuracy);
    Assert.assertEquals(RefStatRange[3], odsatW3.getRangeStat().getStandardDeviation(), distanceAccuracy);
    // test on statistic for the azimuth residuals
    final long nbAzi = 339;
    // statistics for the azimuth residual (min, max, mean, std)
    final double[] RefStatAzi = { -0.043033616, 0.025297558, -1.39E-10, 0.010063041 };
    Assert.assertEquals(nbAzi, odsatW3.getAzimStat().getN());
    Assert.assertEquals(RefStatAzi[0], odsatW3.getAzimStat().getMin(), angleAccuracy);
    Assert.assertEquals(RefStatAzi[1], odsatW3.getAzimStat().getMax(), angleAccuracy);
    Assert.assertEquals(RefStatAzi[2], odsatW3.getAzimStat().getMean(), angleAccuracy);
    Assert.assertEquals(RefStatAzi[3], odsatW3.getAzimStat().getStandardDeviation(), angleAccuracy);
    // test on statistic for the elevation residuals
    final long nbEle = 339;
    final double[] RefStatEle = { -0.025061971, 0.056294405, -4.10E-11, 0.011604931 };
    Assert.assertEquals(nbEle, odsatW3.getElevStat().getN());
    Assert.assertEquals(RefStatEle[0], odsatW3.getElevStat().getMin(), angleAccuracy);
    Assert.assertEquals(RefStatEle[1], odsatW3.getElevStat().getMax(), angleAccuracy);
    Assert.assertEquals(RefStatEle[2], odsatW3.getElevStat().getMean(), angleAccuracy);
    Assert.assertEquals(RefStatEle[3], odsatW3.getElevStat().getStandardDeviation(), angleAccuracy);
    RealMatrix covariances = odsatW3.getCovariances();
    Assert.assertEquals(28, covariances.getRowDimension());
    Assert.assertEquals(28, covariances.getColumnDimension());
    // drag coefficient variance
    Assert.assertEquals(0.687998, covariances.getEntry(6, 6), 1.0e-5);
    // leak-X constant term variance
    Assert.assertEquals(2.0540e-12, covariances.getEntry(7, 7), 1.0e-16);
    // leak-Y constant term variance
    Assert.assertEquals(2.4930e-11, covariances.getEntry(9, 9), 1.0e-15);
    // leak-Z constant term variance
    Assert.assertEquals(7.6720e-11, covariances.getEntry(11, 11), 1.0e-15);
}

Example 13 with ICGEMFormatReader

use of org.orekit.forces.gravity.potential.ICGEMFormatReader in project Orekit by CS-SI.

the class OrbitDeterminationTest method testLageos2.

@Test
public // Orbit determination for Lageos2 based on SLR (range) measurements
void testLageos2() throws URISyntaxException, IllegalArgumentException, IOException, OrekitException, ParseException {
    // input in tutorial resources directory/output
    final String inputPath = OrbitDeterminationTest.class.getClassLoader().getResource("orbit-determination/Lageos2/od_test_Lageos2.in").toURI().getPath();
    final File input = new File(inputPath);
    // configure Orekit data acces
    Utils.setDataRoot("orbit-determination/Lageos2:potential/icgem-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new ICGEMFormatReader("eigen-6s-truncated", true));
    // orbit determination run.
    ResultOD odLageos2 = run(input, false);
    // test
    // definition of the accuracy for the test
    final double distanceAccuracy = 0.1;
    final double velocityAccuracy = 1e-4;
    // test on the convergence
    final int numberOfIte = 4;
    final int numberOfEval = 4;
    Assert.assertEquals(numberOfIte, odLageos2.getNumberOfIteration());
    Assert.assertEquals(numberOfEval, odLageos2.getNumberOfEvaluation());
    // test on the estimated position and velocity
    final Vector3D estimatedPos = odLageos2.getEstimatedPV().getPosition();
    final Vector3D estimatedVel = odLageos2.getEstimatedPV().getVelocity();
    // final Vector3D refPos = new Vector3D(-5532124.989973327, 10025700.01763335, -3578940.840115321);
    // final Vector3D refVel = new Vector3D(-3871.2736402553, -607.8775965705, 4280.9744110925);
    final Vector3D refPos = new Vector3D(-5532131.956902, 10025696.592156, -3578940.040009);
    final Vector3D refVel = new Vector3D(-3871.275109, -607.880985, 4280.972530);
    Assert.assertEquals(0.0, Vector3D.distance(refPos, estimatedPos), distanceAccuracy);
    Assert.assertEquals(0.0, Vector3D.distance(refVel, estimatedVel), velocityAccuracy);
    // test on measurements parameters
    final List<DelegatingDriver> list = new ArrayList<DelegatingDriver>();
    list.addAll(odLageos2.measurementsParameters.getDrivers());
    sortParametersChanges(list);
    // final double[] stationOffSet = { -1.351682,  -2.180542,  -5.278784 };
    // final double rangeBias = -7.923393;
    final double[] stationOffSet = { 1.659203, 0.861250, -0.885352 };
    final double rangeBias = -0.286275;
    Assert.assertEquals(stationOffSet[0], list.get(0).getValue(), distanceAccuracy);
    Assert.assertEquals(stationOffSet[1], list.get(1).getValue(), distanceAccuracy);
    Assert.assertEquals(stationOffSet[2], list.get(2).getValue(), distanceAccuracy);
    Assert.assertEquals(rangeBias, list.get(3).getValue(), distanceAccuracy);
    // test on statistic for the range residuals
    final long nbRange = 258;
    // final double[] RefStatRange = { -2.795816, 6.171529, 0.310848, 1.657809 };
    final double[] RefStatRange = { -2.431135, 2.218644, 0.038483, 0.982017 };
    Assert.assertEquals(nbRange, odLageos2.getRangeStat().getN());
    Assert.assertEquals(RefStatRange[0], odLageos2.getRangeStat().getMin(), distanceAccuracy);
    Assert.assertEquals(RefStatRange[1], odLageos2.getRangeStat().getMax(), distanceAccuracy);
    Assert.assertEquals(RefStatRange[2], odLageos2.getRangeStat().getMean(), distanceAccuracy);
    Assert.assertEquals(RefStatRange[3], odLageos2.getRangeStat().getStandardDeviation(), distanceAccuracy);
}

Example 14 with ICGEMFormatReader

use of org.orekit.forces.gravity.potential.ICGEMFormatReader in project Orekit by CS-SI.

the class DSSTPropagatorTest method testIssue157.

@Test
public void testIssue157() throws OrekitException {
    Utils.setDataRoot("regular-data:potential/icgem-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new ICGEMFormatReader("^eigen-6s-truncated$", false));
    UnnormalizedSphericalHarmonicsProvider nshp = GravityFieldFactory.getUnnormalizedProvider(8, 8);
    Orbit orbit = new KeplerianOrbit(13378000, 0.05, 0, 0, FastMath.PI, 0, PositionAngle.MEAN, FramesFactory.getTOD(false), new AbsoluteDate(2003, 5, 6, TimeScalesFactory.getUTC()), nshp.getMu());
    double period = orbit.getKeplerianPeriod();
    double[][] tolerance = DSSTPropagator.tolerances(1.0, orbit);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(period / 100, period * 100, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(10 * period);
    DSSTPropagator propagator = new DSSTPropagator(integrator, true);
    OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getGTOD(false));
    CelestialBody sun = CelestialBodyFactory.getSun();
    CelestialBody moon = CelestialBodyFactory.getMoon();
    propagator.addForceModel(new DSSTZonal(nshp, 8, 7, 17));
    propagator.addForceModel(new DSSTTesseral(earth.getBodyFrame(), Constants.WGS84_EARTH_ANGULAR_VELOCITY, nshp, 8, 8, 4, 12, 8, 8, 4));
    propagator.addForceModel(new DSSTThirdBody(sun));
    propagator.addForceModel(new DSSTThirdBody(moon));
    propagator.addForceModel(new DSSTAtmosphericDrag(new HarrisPriester(sun, earth), 2.1, 180));
    propagator.addForceModel(new DSSTSolarRadiationPressure(1.2, 180, sun, earth.getEquatorialRadius()));
    propagator.setInitialState(new SpacecraftState(orbit, 45.0), true);
    SpacecraftState finalState = propagator.propagate(orbit.getDate().shiftedBy(30 * Constants.JULIAN_DAY));
    // the following comparison is in fact meaningless
    // the initial orbit is osculating the final orbit is a mean orbit
    // and they are not considered at the same epoch
    // we keep it only as is was an historical test
    Assert.assertEquals(2189.4, orbit.getA() - finalState.getA(), 1.0);
    propagator.setInitialState(new SpacecraftState(orbit, 45.0), false);
    finalState = propagator.propagate(orbit.getDate().shiftedBy(30 * Constants.JULIAN_DAY));
    // the following comparison is realistic
    // both the initial orbit and final orbit are mean orbits
    Assert.assertEquals(1478.05, orbit.getA() - finalState.getA(), 1.0);
}

Example 15 with ICGEMFormatReader

use of org.orekit.forces.gravity.potential.ICGEMFormatReader in project Orekit by CS-SI.

the class DSSTPropagatorTest method testShortPeriodCoefficients.

@Test
public void testShortPeriodCoefficients() throws OrekitException {
    Utils.setDataRoot("regular-data:potential/icgem-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new ICGEMFormatReader("^eigen-6s-truncated$", false));
    UnnormalizedSphericalHarmonicsProvider nshp = GravityFieldFactory.getUnnormalizedProvider(4, 4);
    Orbit orbit = new KeplerianOrbit(13378000, 0.05, 0, 0, FastMath.PI, 0, PositionAngle.MEAN, FramesFactory.getTOD(false), new AbsoluteDate(2003, 5, 6, TimeScalesFactory.getUTC()), nshp.getMu());
    double period = orbit.getKeplerianPeriod();
    double[][] tolerance = DSSTPropagator.tolerances(1.0, orbit);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(period / 100, period * 100, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(10 * period);
    DSSTPropagator propagator = new DSSTPropagator(integrator, false);
    OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getGTOD(false));
    CelestialBody sun = CelestialBodyFactory.getSun();
    CelestialBody moon = CelestialBodyFactory.getMoon();
    propagator.addForceModel(new DSSTZonal(nshp, 4, 3, 9));
    propagator.addForceModel(new DSSTTesseral(earth.getBodyFrame(), Constants.WGS84_EARTH_ANGULAR_VELOCITY, nshp, 4, 4, 4, 8, 4, 4, 2));
    propagator.addForceModel(new DSSTThirdBody(sun));
    propagator.addForceModel(new DSSTThirdBody(moon));
    propagator.addForceModel(new DSSTAtmosphericDrag(new HarrisPriester(sun, earth), 2.1, 180));
    propagator.addForceModel(new DSSTSolarRadiationPressure(1.2, 180, sun, earth.getEquatorialRadius()));
    final AbsoluteDate finalDate = orbit.getDate().shiftedBy(30 * Constants.JULIAN_DAY);
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateNoConfig = propagator.propagate(finalDate);
    Assert.assertEquals(0, stateNoConfig.getAdditionalStates().size());
    propagator.setSelectedCoefficients(new HashSet<String>());
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateConfigEmpty = propagator.propagate(finalDate);
    Assert.assertEquals(234, stateConfigEmpty.getAdditionalStates().size());
    final Set<String> selected = new HashSet<String>();
    selected.add("DSST-3rd-body-Moon-s[7]");
    selected.add("DSST-central-body-tesseral-c[-2][3]");
    propagator.setSelectedCoefficients(selected);
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateConfigeSelected = propagator.propagate(finalDate);
    Assert.assertEquals(selected.size(), stateConfigeSelected.getAdditionalStates().size());
    propagator.setSelectedCoefficients(null);
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateConfigNull = propagator.propagate(finalDate);
    Assert.assertEquals(0, stateConfigNull.getAdditionalStates().size());
}