Examples with NumericalPropagatorBuilder org.orekit.propagation.conversion.NumericalPropagatorBuilder used on opensource projects

Example 56 with NumericalPropagatorBuilder

use of org.orekit.propagation.conversion.NumericalPropagatorBuilder in project Orekit by CS-SI.

the class IonoModifierTest method testRangeIonoModifier.

@Test
public void testRangeIonoModifier() 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);
    propagator.setSlaveMode();
    final RangeIonosphericDelayModifier modifier = new RangeIonosphericDelayModifier(model);
    for (final ObservedMeasurement<?> measurement : measurements) {
        final AbsoluteDate date = measurement.getDate();
        final SpacecraftState refstate = propagator.propagate(date);
        Range range = (Range) measurement;
        EstimatedMeasurement<Range> evalNoMod = range.estimate(12, 17, new SpacecraftState[] { refstate });
        Assert.assertEquals(12, evalNoMod.getIteration());
        Assert.assertEquals(17, evalNoMod.getCount());
        // add modifier
        range.addModifier(modifier);
        boolean found = false;
        for (final EstimationModifier<Range> existing : range.getModifiers()) {
            found = found || existing == modifier;
        }
        Assert.assertTrue(found);
        // 
        EstimatedMeasurement<Range> eval = range.estimate(0, 0, new SpacecraftState[] { refstate });
        Assert.assertEquals(evalNoMod.getStatus(), eval.getStatus());
        eval.setStatus(EstimatedMeasurement.Status.REJECTED);
        Assert.assertEquals(EstimatedMeasurement.Status.REJECTED, eval.getStatus());
        eval.setStatus(evalNoMod.getStatus());
        try {
            eval.getParameterDerivatives(new ParameterDriver("extra", 0, 1, -1, +1));
            Assert.fail("an exception should have been thrown");
        } catch (OrekitIllegalArgumentException oiae) {
            Assert.assertEquals(OrekitMessages.UNSUPPORTED_PARAMETER_NAME, oiae.getSpecifier());
        }
        final double diffMeters = eval.getEstimatedValue()[0] - evalNoMod.getEstimatedValue()[0];
        // TODO: check threshold
        Assert.assertEquals(0.0, diffMeters, 30.0);
    }
}

Example 57 with NumericalPropagatorBuilder

use of org.orekit.propagation.conversion.NumericalPropagatorBuilder in project Orekit by CS-SI.

the class IonoModifierTest method testKlobucharIonoModel.

@Test
public void testKlobucharIonoModel() 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);
    propagator.setSlaveMode();
    for (final ObservedMeasurement<?> measurement : measurements) {
        // parameter corresponding to station position offset
        final GroundStation station = ((Range) measurement).getStation();
        final AbsoluteDate date = ((Range) measurement).getDate();
        final SpacecraftState state = propagator.propagate(date);
        final Vector3D position = state.getPVCoordinates().getPosition();
        // 
        final GeodeticPoint geo = station.getBaseFrame().getPoint();
        // elevation
        final double elevation = station.getBaseFrame().getElevation(position, state.getFrame(), state.getDate());
        // elevation
        final double azimuth = station.getBaseFrame().getAzimuth(position, state.getFrame(), state.getDate());
        double delayMeters = model.pathDelay(date, geo, elevation, azimuth);
        final double epsilon = 1e-6;
        Assert.assertTrue(Precision.compareTo(delayMeters, 15., epsilon) < 0);
        Assert.assertTrue(Precision.compareTo(delayMeters, 0., epsilon) > 0);
    }
}

Example 58 with NumericalPropagatorBuilder

use of org.orekit.propagation.conversion.NumericalPropagatorBuilder in project Orekit by CS-SI.

the class OnBoardAntennaInterSatellitesRangeModifierTest method testEffect.

@Test
public void testEffect() 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);
    propagatorBuilder.setAttitudeProvider(new LofOffset(propagatorBuilder.getFrame(), LOFType.LVLH));
    // create perfect inter-satellites range measurements without antenna offset
    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 p1 = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> spacecraftCenteredMeasurements = EstimationTestUtils.createMeasurements(p1, new InterSatellitesRangeMeasurementCreator(ephemeris, Vector3D.ZERO, Vector3D.ZERO), 1.0, 3.0, 300.0);
    // create perfect inter-satellites range measurements with antenna offset
    final Vector3D apc1 = new Vector3D(-2.5, 0.0, 0);
    final Vector3D apc2 = new Vector3D(0.0, 0.8, 0);
    final Propagator p2 = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> antennaCenteredMeasurements = EstimationTestUtils.createMeasurements(p2, new InterSatellitesRangeMeasurementCreator(ephemeris, apc1, apc2), 1.0, 3.0, 300.0);
    final Propagator p3 = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    OnBoardAntennaInterSatellitesRangeModifier modifier = new OnBoardAntennaInterSatellitesRangeModifier(apc1, apc2);
    for (int i = 0; i < spacecraftCenteredMeasurements.size(); ++i) {
        InterSatellitesRange sr = (InterSatellitesRange) spacecraftCenteredMeasurements.get(i);
        sr.addModifier(modifier);
        EstimatedMeasurement<InterSatellitesRange> estimated = sr.estimate(0, 0, new SpacecraftState[] { p3.propagate(sr.getDate()), ephemeris.propagate(sr.getDate()) });
        InterSatellitesRange ar = (InterSatellitesRange) antennaCenteredMeasurements.get(i);
        Assert.assertEquals(0.0, sr.getDate().durationFrom(ar.getDate()), 2.0e-8);
        Assert.assertEquals(ar.getObservedValue()[0], estimated.getEstimatedValue()[0], 2.0e-5);
    }
}

Example 59 with NumericalPropagatorBuilder

use of org.orekit.propagation.conversion.NumericalPropagatorBuilder in project Orekit by CS-SI.

the class OnBoardAntennaRangeModifierTest method testEffect.

@Test
public void testEffect() 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);
    propagatorBuilder.setAttitudeProvider(new LofOffset(propagatorBuilder.getFrame(), LOFType.LVLH));
    // create perfect range measurements without antenna offset
    final Propagator p1 = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> spacecraftCenteredMeasurements = EstimationTestUtils.createMeasurements(p1, new RangeMeasurementCreator(context, Vector3D.ZERO), 1.0, 3.0, 300.0);
    // create perfect range measurements with antenna offset
    final Vector3D apc = new Vector3D(-2.5, 0, 0);
    final Propagator p2 = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> antennaCenteredMeasurements = EstimationTestUtils.createMeasurements(p2, new RangeMeasurementCreator(context, apc), 1.0, 3.0, 300.0);
    final Propagator p3 = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    OnBoardAntennaRangeModifier modifier = new OnBoardAntennaRangeModifier(apc);
    for (int i = 0; i < spacecraftCenteredMeasurements.size(); ++i) {
        Range sr = (Range) spacecraftCenteredMeasurements.get(i);
        sr.addModifier(modifier);
        EstimatedMeasurement<Range> estimated = sr.estimate(0, 0, new SpacecraftState[] { p3.propagate(sr.getDate()) });
        Range ar = (Range) antennaCenteredMeasurements.get(i);
        Assert.assertEquals(0.0, sr.getDate().durationFrom(ar.getDate()), 1.0e-8);
        Assert.assertEquals(ar.getObservedValue()[0], estimated.getEstimatedValue()[0], 2.6e-7);
    }
}

Example 60 with NumericalPropagatorBuilder

use of org.orekit.propagation.conversion.NumericalPropagatorBuilder in project Orekit by CS-SI.

the class OnBoardAntennaRangeModifierTest method testPreliminary.

@Test
public void testPreliminary() throws OrekitException {
    // this test does not check OnBoardAntennaRangeModifier at all,
    // it just checks RangeMeasurementCreator behaves as necessary for the other test
    // the *real* test is testEffect below
    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);
    propagatorBuilder.setAttitudeProvider(new LofOffset(propagatorBuilder.getFrame(), LOFType.LVLH));
    // create perfect range measurements without antenna offset
    final Propagator p1 = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> spacecraftCenteredMeasurements = EstimationTestUtils.createMeasurements(p1, new RangeMeasurementCreator(context, Vector3D.ZERO), 1.0, 3.0, 300.0);
    // create perfect range measurements with antenna offset
    final double xOffset = -2.5;
    final Propagator p2 = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> antennaCenteredMeasurements = EstimationTestUtils.createMeasurements(p2, new RangeMeasurementCreator(context, new Vector3D(xOffset, 0, 0)), 1.0, 3.0, 300.0);
    for (int i = 0; i < spacecraftCenteredMeasurements.size(); ++i) {
        Range sr = (Range) spacecraftCenteredMeasurements.get(i);
        Range ar = (Range) antennaCenteredMeasurements.get(i);
        double alphaMax = FastMath.asin(Constants.WGS84_EARTH_EQUATORIAL_RADIUS / sr.getObservedValue()[0]);
        Assert.assertEquals(0.0, sr.getDate().durationFrom(ar.getDate()), 1.0e-8);
        Assert.assertTrue(ar.getObservedValue()[0] - sr.getObservedValue()[0] >= xOffset);
        Assert.assertTrue(ar.getObservedValue()[0] - sr.getObservedValue()[0] <= xOffset * FastMath.cos(alphaMax));
    }
}