Examples with ParameterDriver org.orekit.utils.ParameterDriver used on opensource projects

Example 41 with ParameterDriver

use of org.orekit.utils.ParameterDriver in project Orekit by CS-SI.

the class GroundStationTest method testNoReferenceDate.

@Test
public void testNoReferenceDate() throws OrekitException {
    Utils.setDataRoot("regular-data");
    final Frame eme2000 = FramesFactory.getEME2000();
    final AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final GroundStation station = new GroundStation(new TopocentricFrame(earth, new GeodeticPoint(0.1, 0.2, 100), "dummy"));
    try {
        station.getOffsetToInertial(eme2000, date);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.NO_REFERENCE_DATE_FOR_PARAMETER, oe.getSpecifier());
        Assert.assertEquals("prime-meridian-offset", (String) oe.getParts()[0]);
    }
    try {
        DSFactory factory = new DSFactory(9, 1);
        Map<String, Integer> indices = new HashMap<>();
        for (final ParameterDriver driver : Arrays.asList(station.getPrimeMeridianOffsetDriver(), station.getPrimeMeridianDriftDriver(), station.getPolarOffsetXDriver(), station.getPolarDriftXDriver(), station.getPolarOffsetYDriver(), station.getPolarDriftYDriver(), station.getEastOffsetDriver(), station.getNorthOffsetDriver(), station.getZenithOffsetDriver())) {
            indices.put(driver.getName(), indices.size());
        }
        station.getOffsetToInertial(eme2000, new FieldAbsoluteDate<>(factory.getDerivativeField(), date), factory, indices);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.NO_REFERENCE_DATE_FOR_PARAMETER, oe.getSpecifier());
        Assert.assertEquals("prime-meridian-offset", (String) oe.getParts()[0]);
    }
}

Example 42 with ParameterDriver

use of org.orekit.utils.ParameterDriver in project Orekit by CS-SI.

the class GroundStationTest method doTestAngularDerivatives.

private void doTestAngularDerivatives(double latitude, double longitude, double altitude, double stepFactor, double toleranceRotationValue, double toleranceRotationDerivative, double toleranceRotationRateValue, double toleranceRotationRateDerivative, String... parameterPattern) throws OrekitException {
    Utils.setDataRoot("regular-data");
    final Frame eme2000 = FramesFactory.getEME2000();
    final AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
    final AbsoluteDate date0 = date.shiftedBy(50000);
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final GroundStation station = new GroundStation(new TopocentricFrame(earth, new GeodeticPoint(latitude, longitude, altitude), "dummy"));
    final DSFactory factory = new DSFactory(parameterPattern.length, 1);
    final FieldAbsoluteDate<DerivativeStructure> dateDS = new FieldAbsoluteDate<>(factory.getDerivativeField(), date);
    ParameterDriver[] selectedDrivers = new ParameterDriver[parameterPattern.length];
    UnivariateDifferentiableVectorFunction[] dFAngular = new UnivariateDifferentiableVectorFunction[parameterPattern.length];
    final ParameterDriver[] allDrivers = selectAllDrivers(station);
    for (ParameterDriver driver : allDrivers) {
        driver.setReferenceDate(date0);
    }
    Map<String, Integer> indices = new HashMap<>();
    for (int k = 0; k < dFAngular.length; ++k) {
        for (int i = 0; i < allDrivers.length; ++i) {
            if (allDrivers[i].getName().matches(parameterPattern[k])) {
                selectedDrivers[k] = allDrivers[i];
                dFAngular[k] = differentiatedTransformAngular(station, eme2000, date, selectedDrivers[k], stepFactor);
                indices.put(selectedDrivers[k].getName(), k);
            }
        }
    }
    ;
    DSFactory factory11 = new DSFactory(1, 1);
    RandomGenerator generator = new Well19937a(0xa01a1d8fe5d80af7l);
    double maxRotationValueError = 0;
    double maxRotationDerivativeError = 0;
    double maxRotationRateValueError = 0;
    double maxRotationRateDerivativeError = 0;
    for (int i = 0; i < 1000; ++i) {
        // randomly change one parameter
        ParameterDriver changed = allDrivers[generator.nextInt(allDrivers.length)];
        changed.setNormalizedValue(2 * generator.nextDouble() - 1);
        // transform to check
        FieldTransform<DerivativeStructure> t = station.getOffsetToInertial(eme2000, dateDS, factory, indices);
        for (int k = 0; k < dFAngular.length; ++k) {
            // reference values and derivatives computed using finite differences
            DerivativeStructure[] refAngular = dFAngular[k].value(factory11.variable(0, selectedDrivers[k].getValue()));
            // rotation
            final Rotation refQ = new Rotation(refAngular[0].getValue(), refAngular[1].getValue(), refAngular[2].getValue(), refAngular[3].getValue(), true);
            final Rotation resQ = t.getRotation().toRotation();
            maxRotationValueError = FastMath.max(maxRotationValueError, Rotation.distance(refQ, resQ));
            double sign = FastMath.copySign(1.0, refAngular[0].getValue() * t.getRotation().getQ0().getValue() + refAngular[1].getValue() * t.getRotation().getQ1().getValue() + refAngular[2].getValue() * t.getRotation().getQ2().getValue() + refAngular[3].getValue() * t.getRotation().getQ3().getValue());
            maxRotationDerivativeError = FastMath.max(maxRotationDerivativeError, FastMath.abs(sign * refAngular[0].getPartialDerivative(1) - t.getRotation().getQ0().getAllDerivatives()[k + 1]));
            maxRotationDerivativeError = FastMath.max(maxRotationDerivativeError, FastMath.abs(sign * refAngular[1].getPartialDerivative(1) - t.getRotation().getQ1().getAllDerivatives()[k + 1]));
            maxRotationDerivativeError = FastMath.max(maxRotationDerivativeError, FastMath.abs(sign * refAngular[2].getPartialDerivative(1) - t.getRotation().getQ2().getAllDerivatives()[k + 1]));
            maxRotationDerivativeError = FastMath.max(maxRotationDerivativeError, FastMath.abs(sign * refAngular[3].getPartialDerivative(1) - t.getRotation().getQ3().getAllDerivatives()[k + 1]));
            // rotation rate
            final Vector3D refRate = new Vector3D(refAngular[4].getValue(), refAngular[5].getValue(), refAngular[6].getValue());
            final Vector3D resRate = t.getRotationRate().toVector3D();
            final Vector3D refRateD = new Vector3D(refAngular[4].getPartialDerivative(1), refAngular[5].getPartialDerivative(1), refAngular[6].getPartialDerivative(1));
            final Vector3D resRateD = new Vector3D(t.getRotationRate().getX().getAllDerivatives()[k + 1], t.getRotationRate().getY().getAllDerivatives()[k + 1], t.getRotationRate().getZ().getAllDerivatives()[k + 1]);
            maxRotationRateValueError = FastMath.max(maxRotationRateValueError, Vector3D.distance(refRate, resRate));
            maxRotationRateDerivativeError = FastMath.max(maxRotationRateDerivativeError, Vector3D.distance(refRateD, resRateD));
        }
    }
    Assert.assertEquals(0.0, maxRotationValueError, toleranceRotationValue);
    Assert.assertEquals(0.0, maxRotationDerivativeError, toleranceRotationDerivative);
    Assert.assertEquals(0.0, maxRotationRateValueError, toleranceRotationRateValue);
    Assert.assertEquals(0.0, maxRotationRateDerivativeError, toleranceRotationRateDerivative);
}

Example 43 with ParameterDriver

use of org.orekit.utils.ParameterDriver in project Orekit by CS-SI.

the class GroundStationTest method testEstimateEOP.

@Test
public void testEstimateEOP() throws OrekitException {
    Context linearEOPContext = EstimationTestUtils.eccentricContext("linear-EOP:regular-data/de431-ephemerides:potential:tides");
    final AbsoluteDate refDate = new AbsoluteDate(2000, 2, 24, linearEOPContext.utc);
    final double dut10 = 0.3079738;
    final double lod = 0.0011000;
    final double xp0 = 68450.0e-6;
    final double xpDot = -50.0e-6;
    final double yp0 = 60.0e-6;
    final double ypDot = 2.0e-6;
    for (double dt = -2 * Constants.JULIAN_DAY; dt < 2 * Constants.JULIAN_DAY; dt += 300.0) {
        AbsoluteDate date = refDate.shiftedBy(dt);
        Assert.assertEquals(dut10 - dt * lod / Constants.JULIAN_DAY, linearEOPContext.ut1.getEOPHistory().getUT1MinusUTC(date), 1.0e-15);
        Assert.assertEquals(lod, linearEOPContext.ut1.getEOPHistory().getLOD(date), 1.0e-15);
        Assert.assertEquals((xp0 + xpDot * dt / Constants.JULIAN_DAY) * Constants.ARC_SECONDS_TO_RADIANS, linearEOPContext.ut1.getEOPHistory().getPoleCorrection(date).getXp(), 1.0e-15);
        Assert.assertEquals((yp0 + ypDot * dt / Constants.JULIAN_DAY) * Constants.ARC_SECONDS_TO_RADIANS, linearEOPContext.ut1.getEOPHistory().getPoleCorrection(date).getYp(), 1.0e-15);
    }
    final NumericalPropagatorBuilder linearPropagatorBuilder = linearEOPContext.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
    // create perfect range measurements
    final Propagator propagator = EstimationTestUtils.createPropagator(linearEOPContext.initialOrbit, linearPropagatorBuilder);
    final List<ObservedMeasurement<?>> linearMeasurements = EstimationTestUtils.createMeasurements(propagator, new RangeMeasurementCreator(linearEOPContext), 1.0, 5.0, 60.0);
    Utils.clearFactories();
    Context zeroEOPContext = EstimationTestUtils.eccentricContext("zero-EOP:regular-data/de431-ephemerides:potential:potential:tides");
    for (double dt = -2 * Constants.JULIAN_DAY; dt < 2 * Constants.JULIAN_DAY; dt += 300.0) {
        AbsoluteDate date = refDate.shiftedBy(dt);
        Assert.assertEquals(0.0, zeroEOPContext.ut1.getEOPHistory().getUT1MinusUTC(date), 1.0e-15);
        Assert.assertEquals(0.0, zeroEOPContext.ut1.getEOPHistory().getLOD(date), 1.0e-15);
        Assert.assertEquals(0.0, zeroEOPContext.ut1.getEOPHistory().getPoleCorrection(date).getXp(), 1.0e-15);
        Assert.assertEquals(0.0, zeroEOPContext.ut1.getEOPHistory().getPoleCorrection(date).getYp(), 1.0e-15);
    }
    // create orbit estimator
    final NumericalPropagatorBuilder zeroPropagatorBuilder = linearEOPContext.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
    final BatchLSEstimator estimator = new BatchLSEstimator(new LevenbergMarquardtOptimizer(), zeroPropagatorBuilder);
    for (final ObservedMeasurement<?> linearMeasurement : linearMeasurements) {
        Range linearRange = (Range) linearMeasurement;
        for (final GroundStation station : zeroEOPContext.stations) {
            if (station.getBaseFrame().getName().equals(linearRange.getStation().getBaseFrame().getName())) {
                Range zeroRange = new Range(station, linearRange.getDate(), linearRange.getObservedValue()[0], linearRange.getTheoreticalStandardDeviation()[0], linearRange.getBaseWeight()[0]);
                estimator.addMeasurement(zeroRange);
            }
        }
    }
    estimator.setParametersConvergenceThreshold(1.0e-3);
    estimator.setMaxIterations(100);
    estimator.setMaxEvaluations(200);
    // we want to estimate pole and prime meridian
    GroundStation station = zeroEOPContext.stations.get(0);
    station.getPrimeMeridianOffsetDriver().setReferenceDate(refDate);
    station.getPrimeMeridianOffsetDriver().setSelected(true);
    station.getPrimeMeridianDriftDriver().setSelected(true);
    station.getPolarOffsetXDriver().setReferenceDate(refDate);
    station.getPolarOffsetXDriver().setSelected(true);
    station.getPolarDriftXDriver().setSelected(true);
    station.getPolarOffsetYDriver().setReferenceDate(refDate);
    station.getPolarOffsetYDriver().setSelected(true);
    station.getPolarDriftYDriver().setSelected(true);
    // just for the fun and to speed up test, we will use orbit determination, *without* estimating orbit
    for (final ParameterDriver driver : zeroPropagatorBuilder.getOrbitalParametersDrivers().getDrivers()) {
        driver.setSelected(false);
    }
    estimator.estimate();
    final double computedDut1 = station.getPrimeMeridianOffsetDriver().getValue() / EstimatedEarthFrameProvider.EARTH_ANGULAR_VELOCITY;
    final double computedLOD = station.getPrimeMeridianDriftDriver().getValue() * (-Constants.JULIAN_DAY / EstimatedEarthFrameProvider.EARTH_ANGULAR_VELOCITY);
    final double computedXp = station.getPolarOffsetXDriver().getValue() / Constants.ARC_SECONDS_TO_RADIANS;
    final double computedXpDot = station.getPolarDriftXDriver().getValue() / Constants.ARC_SECONDS_TO_RADIANS * Constants.JULIAN_DAY;
    final double computedYp = station.getPolarOffsetYDriver().getValue() / Constants.ARC_SECONDS_TO_RADIANS;
    final double computedYpDot = station.getPolarDriftYDriver().getValue() / Constants.ARC_SECONDS_TO_RADIANS * Constants.JULIAN_DAY;
    Assert.assertEquals(dut10, computedDut1, 4.3e-10);
    Assert.assertEquals(lod, computedLOD, 4.9e-10);
    Assert.assertEquals(xp0, computedXp, 5.6e-9);
    Assert.assertEquals(xpDot, computedXpDot, 7.2e-9);
    Assert.assertEquals(yp0, computedYp, 1.1e-9);
    Assert.assertEquals(ypDot, computedYpDot, 2.8e-11);
// thresholds to use if orbit is estimated
// (i.e. when commenting out the loop above that sets orbital parameters drivers to "not selected")
// Assert.assertEquals(dut10, computedDut1,  6.6e-3);
// Assert.assertEquals(lod,   computedLOD,   1.1e-9);
// Assert.assertEquals(xp0,   computedXp,    3.3e-8);
// Assert.assertEquals(xpDot, computedXpDot, 2.2e-8);
// Assert.assertEquals(yp0,   computedYp,    3.3e-8);
// Assert.assertEquals(ypDot, computedYpDot, 3.8e-8);
}

Example 44 with ParameterDriver

use of org.orekit.utils.ParameterDriver in project Orekit by CS-SI.

the class ConstantThrustManeuverTest method testNegativeDuration.

@Test
public void testNegativeDuration() throws OrekitException {
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2004, 01, 01), new TimeComponents(23, 30, 00.000), TimeScalesFactory.getUTC());
    ConstantThrustManeuver maneuver = new ConstantThrustManeuver(date, -10.0, 400.0, 300.0, Vector3D.PLUS_K, "1A-");
    ParameterDriver[] drivers = maneuver.getParametersDrivers();
    Assert.assertEquals(2, drivers.length);
    Assert.assertEquals("1A-thrust", drivers[0].getName());
    Assert.assertEquals("1A-flow rate", drivers[1].getName());
    EventDetector[] switches = maneuver.getEventsDetectors().toArray(EventDetector[]::new);
    Orbit o1 = dummyOrbit(date.shiftedBy(-11.0));
    Assert.assertTrue(switches[0].g(new SpacecraftState(o1)) < 0);
    Orbit o2 = dummyOrbit(date.shiftedBy(-9.0));
    Assert.assertTrue(switches[0].g(new SpacecraftState(o2)) > 0);
    Orbit o3 = dummyOrbit(date.shiftedBy(-1.0));
    Assert.assertTrue(switches[1].g(new SpacecraftState(o3)) < 0);
    Orbit o4 = dummyOrbit(date.shiftedBy(1.0));
    Assert.assertTrue(switches[1].g(new SpacecraftState(o4)) > 0);
}

Example 45 with ParameterDriver

use of org.orekit.utils.ParameterDriver in project Orekit by CS-SI.

the class ConstantThrustManeuverTest method testPositiveDuration.

@Test
public void testPositiveDuration() throws OrekitException {
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2004, 01, 01), new TimeComponents(23, 30, 00.000), TimeScalesFactory.getUTC());
    ConstantThrustManeuver maneuver = new ConstantThrustManeuver(date, 10.0, 400.0, 300.0, Vector3D.PLUS_K);
    Assert.assertFalse(maneuver.dependsOnPositionOnly());
    ParameterDriver[] drivers = maneuver.getParametersDrivers();
    Assert.assertEquals(2, drivers.length);
    Assert.assertEquals("thrust", drivers[0].getName());
    Assert.assertEquals("flow rate", drivers[1].getName());
    EventDetector[] switches = maneuver.getEventsDetectors().toArray(EventDetector[]::new);
    Orbit o1 = dummyOrbit(date.shiftedBy(-1.0));
    Assert.assertTrue(switches[0].g(new SpacecraftState(o1)) < 0);
    Orbit o2 = dummyOrbit(date.shiftedBy(1.0));
    Assert.assertTrue(switches[0].g(new SpacecraftState(o2)) > 0);
    Orbit o3 = dummyOrbit(date.shiftedBy(9.0));
    Assert.assertTrue(switches[1].g(new SpacecraftState(o3)) < 0);
    Orbit o4 = dummyOrbit(date.shiftedBy(11.0));
    Assert.assertTrue(switches[1].g(new SpacecraftState(o4)) > 0);
}