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Example 1 with GroundStation

use of org.orekit.estimation.measurements.GroundStation in project Orekit by CS-SI.

the class IonoModifierTest method testRangeRateIonoModifier.

@Test
public void testRangeRateIonoModifier() 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 RangeRateMeasurementCreator(context, false), 1.0, 3.0, 300.0);
    propagator.setSlaveMode();
    final RangeRateIonosphericDelayModifier modifier = new RangeRateIonosphericDelayModifier(model, true);
    for (final ObservedMeasurement<?> measurement : measurements) {
        final AbsoluteDate date = measurement.getDate();
        final SpacecraftState refstate = propagator.propagate(date);
        RangeRate rangeRate = (RangeRate) measurement;
        EstimatedMeasurement<RangeRate> evalNoMod = rangeRate.estimate(0, 0, new SpacecraftState[] { refstate });
        // add modifier
        rangeRate.addModifier(modifier);
        // 
        EstimatedMeasurement<RangeRate> eval = rangeRate.estimate(0, 0, new SpacecraftState[] { refstate });
        final double diffMetersSec = eval.getEstimatedValue()[0] - evalNoMod.getEstimatedValue()[0];
        // TODO: check threshold
        Assert.assertEquals(0.0, diffMetersSec, 0.016);
    }
}
Also used : Context(org.orekit.estimation.Context) GroundStation(org.orekit.estimation.measurements.GroundStation) RangeRateIonosphericDelayModifier(org.orekit.estimation.measurements.modifiers.RangeRateIonosphericDelayModifier) AbsoluteDate(org.orekit.time.AbsoluteDate) SpacecraftState(org.orekit.propagation.SpacecraftState) NumericalPropagatorBuilder(org.orekit.propagation.conversion.NumericalPropagatorBuilder) Propagator(org.orekit.propagation.Propagator) RangeRate(org.orekit.estimation.measurements.RangeRate) ObservedMeasurement(org.orekit.estimation.measurements.ObservedMeasurement) RangeRateMeasurementCreator(org.orekit.estimation.measurements.RangeRateMeasurementCreator) Test(org.junit.Test)

Example 2 with GroundStation

use of org.orekit.estimation.measurements.GroundStation in project Orekit by CS-SI.

the class IonoModifierTest method testTurnAroundRangeIonoModifier.

@Test
public void testTurnAroundRangeIonoModifier() 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 turn-around measurements
    for (Map.Entry<GroundStation, GroundStation> entry : context.TARstations.entrySet()) {
        final GroundStation masterStation = entry.getKey();
        final GroundStation slaveStation = entry.getValue();
        masterStation.getEastOffsetDriver().setSelected(true);
        masterStation.getNorthOffsetDriver().setSelected(true);
        masterStation.getZenithOffsetDriver().setSelected(true);
        slaveStation.getEastOffsetDriver().setSelected(true);
        slaveStation.getNorthOffsetDriver().setSelected(true);
        slaveStation.getZenithOffsetDriver().setSelected(true);
    }
    final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new TurnAroundRangeMeasurementCreator(context), 1.0, 3.0, 300.0);
    propagator.setSlaveMode();
    final TurnAroundRangeIonosphericDelayModifier modifier = new TurnAroundRangeIonosphericDelayModifier(model);
    for (final ObservedMeasurement<?> measurement : measurements) {
        final AbsoluteDate date = measurement.getDate();
        final SpacecraftState refstate = propagator.propagate(date);
        TurnAroundRange turnAroundRange = (TurnAroundRange) measurement;
        EstimatedMeasurement<TurnAroundRange> evalNoMod = turnAroundRange.estimate(12, 17, new SpacecraftState[] { refstate });
        Assert.assertEquals(12, evalNoMod.getIteration());
        Assert.assertEquals(17, evalNoMod.getCount());
        // Add modifier
        turnAroundRange.addModifier(modifier);
        boolean found = false;
        for (final EstimationModifier<TurnAroundRange> existing : turnAroundRange.getModifiers()) {
            found = found || existing == modifier;
        }
        Assert.assertTrue(found);
        // 
        EstimatedMeasurement<TurnAroundRange> eval = turnAroundRange.estimate(12, 17, 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);
    }
}
Also used : Context(org.orekit.estimation.Context) GroundStation(org.orekit.estimation.measurements.GroundStation) TurnAroundRangeIonosphericDelayModifier(org.orekit.estimation.measurements.modifiers.TurnAroundRangeIonosphericDelayModifier) ParameterDriver(org.orekit.utils.ParameterDriver) AbsoluteDate(org.orekit.time.AbsoluteDate) OrekitIllegalArgumentException(org.orekit.errors.OrekitIllegalArgumentException) SpacecraftState(org.orekit.propagation.SpacecraftState) NumericalPropagatorBuilder(org.orekit.propagation.conversion.NumericalPropagatorBuilder) Propagator(org.orekit.propagation.Propagator) TurnAroundRange(org.orekit.estimation.measurements.TurnAroundRange) Map(java.util.Map) ObservedMeasurement(org.orekit.estimation.measurements.ObservedMeasurement) TurnAroundRangeMeasurementCreator(org.orekit.estimation.measurements.TurnAroundRangeMeasurementCreator) Test(org.junit.Test)

Example 3 with GroundStation

use of org.orekit.estimation.measurements.GroundStation in project Orekit by CS-SI.

the class IonoModifierTest method testAngularIonoModifier.

@Test
public void testAngularIonoModifier() 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 AngularAzElMeasurementCreator(context), 1.0, 3.0, 300.0);
    propagator.setSlaveMode();
    final AngularIonosphericDelayModifier modifier = new AngularIonosphericDelayModifier(model);
    for (final ObservedMeasurement<?> measurement : measurements) {
        final AbsoluteDate date = measurement.getDate();
        final SpacecraftState refstate = propagator.propagate(date);
        AngularAzEl angular = (AngularAzEl) measurement;
        EstimatedMeasurement<AngularAzEl> evalNoMod = angular.estimate(0, 0, new SpacecraftState[] { refstate });
        // add modifier
        angular.addModifier(modifier);
        // 
        EstimatedMeasurement<AngularAzEl> eval = angular.estimate(0, 0, new SpacecraftState[] { refstate });
        final double diffAz = MathUtils.normalizeAngle(eval.getEstimatedValue()[0], evalNoMod.getEstimatedValue()[0]) - evalNoMod.getEstimatedValue()[0];
        final double diffEl = MathUtils.normalizeAngle(eval.getEstimatedValue()[1], evalNoMod.getEstimatedValue()[1]) - evalNoMod.getEstimatedValue()[1];
        // TODO: check threshold
        Assert.assertEquals(0.0, diffAz, 5.0e-5);
        Assert.assertEquals(0.0, diffEl, 5.0e-6);
    }
}
Also used : Context(org.orekit.estimation.Context) GroundStation(org.orekit.estimation.measurements.GroundStation) AngularIonosphericDelayModifier(org.orekit.estimation.measurements.modifiers.AngularIonosphericDelayModifier) AbsoluteDate(org.orekit.time.AbsoluteDate) SpacecraftState(org.orekit.propagation.SpacecraftState) NumericalPropagatorBuilder(org.orekit.propagation.conversion.NumericalPropagatorBuilder) Propagator(org.orekit.propagation.Propagator) AngularAzElMeasurementCreator(org.orekit.estimation.measurements.AngularAzElMeasurementCreator) AngularAzEl(org.orekit.estimation.measurements.AngularAzEl) ObservedMeasurement(org.orekit.estimation.measurements.ObservedMeasurement) Test(org.junit.Test)

Example 4 with GroundStation

use of org.orekit.estimation.measurements.GroundStation in project Orekit by CS-SI.

the class TropoModifierTest method testTurnAroundRangeTropoModifier.

@Test
public void testTurnAroundRangeTropoModifier() 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 turn-around measurements
    for (Map.Entry<GroundStation, GroundStation> entry : context.TARstations.entrySet()) {
        final GroundStation masterStation = entry.getKey();
        final GroundStation slaveStation = entry.getValue();
        masterStation.getEastOffsetDriver().setSelected(true);
        masterStation.getNorthOffsetDriver().setSelected(true);
        masterStation.getZenithOffsetDriver().setSelected(true);
        slaveStation.getEastOffsetDriver().setSelected(true);
        slaveStation.getNorthOffsetDriver().setSelected(true);
        slaveStation.getZenithOffsetDriver().setSelected(true);
    }
    final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new TurnAroundRangeMeasurementCreator(context), 1.0, 3.0, 300.0);
    propagator.setSlaveMode();
    final TurnAroundRangeTroposphericDelayModifier modifier = new TurnAroundRangeTroposphericDelayModifier(SaastamoinenModel.getStandardModel());
    for (final ObservedMeasurement<?> measurement : measurements) {
        final AbsoluteDate date = measurement.getDate();
        final SpacecraftState refState = propagator.propagate(date);
        TurnAroundRange turnAroundRange = (TurnAroundRange) measurement;
        EstimatedMeasurement<TurnAroundRange> evalNoMod = turnAroundRange.estimate(0, 0, new SpacecraftState[] { refState });
        // add modifier
        turnAroundRange.addModifier(modifier);
        // 
        EstimatedMeasurement<TurnAroundRange> eval = turnAroundRange.estimate(0, 0, new SpacecraftState[] { refState });
        final double diffMeters = eval.getEstimatedValue()[0] - evalNoMod.getEstimatedValue()[0];
        final double epsilon = 1e-6;
        Assert.assertTrue(Precision.compareTo(diffMeters, 12., epsilon) < 0);
        Assert.assertTrue(Precision.compareTo(diffMeters, 0., epsilon) > 0);
    }
}
Also used : Context(org.orekit.estimation.Context) GroundStation(org.orekit.estimation.measurements.GroundStation) AbsoluteDate(org.orekit.time.AbsoluteDate) SpacecraftState(org.orekit.propagation.SpacecraftState) NumericalPropagatorBuilder(org.orekit.propagation.conversion.NumericalPropagatorBuilder) Propagator(org.orekit.propagation.Propagator) TurnAroundRangeTroposphericDelayModifier(org.orekit.estimation.measurements.modifiers.TurnAroundRangeTroposphericDelayModifier) TurnAroundRange(org.orekit.estimation.measurements.TurnAroundRange) Map(java.util.Map) ObservedMeasurement(org.orekit.estimation.measurements.ObservedMeasurement) TurnAroundRangeMeasurementCreator(org.orekit.estimation.measurements.TurnAroundRangeMeasurementCreator) Test(org.junit.Test)

Example 5 with GroundStation

use of org.orekit.estimation.measurements.GroundStation in project Orekit by CS-SI.

the class TropoModifierTest method testAngularRadioRefractionModifier.

@Test
public void testAngularRadioRefractionModifier() 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 angular 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 AngularAzElMeasurementCreator(context), 1.0, 3.0, 300.0);
    propagator.setSlaveMode();
    for (final ObservedMeasurement<?> measurement : measurements) {
        final AbsoluteDate date = measurement.getDate();
        final SpacecraftState refState = propagator.propagate(date);
        AngularAzEl angular = (AngularAzEl) measurement;
        EstimatedMeasurement<AngularAzEl> evalNoMod = angular.estimate(0, 0, new SpacecraftState[] { refState });
        // get the altitude of the station (in kilometers)
        final double altitude = angular.getStation().getBaseFrame().getPoint().getAltitude() / 1000.;
        final AngularRadioRefractionModifier modifier = new AngularRadioRefractionModifier(new EarthITU453AtmosphereRefraction(altitude));
        // add modifier
        angular.addModifier(modifier);
        // 
        EstimatedMeasurement<AngularAzEl> eval = angular.estimate(0, 0, new SpacecraftState[] { refState });
        final double diffEl = MathUtils.normalizeAngle(eval.getEstimatedValue()[1], evalNoMod.getEstimatedValue()[1]) - evalNoMod.getEstimatedValue()[1];
        // TODO: check threshold
        Assert.assertEquals(0.0, diffEl, 1.0e-3);
    }
}
Also used : Context(org.orekit.estimation.Context) GroundStation(org.orekit.estimation.measurements.GroundStation) EarthITU453AtmosphereRefraction(org.orekit.models.earth.EarthITU453AtmosphereRefraction) AngularRadioRefractionModifier(org.orekit.estimation.measurements.modifiers.AngularRadioRefractionModifier) AbsoluteDate(org.orekit.time.AbsoluteDate) SpacecraftState(org.orekit.propagation.SpacecraftState) NumericalPropagatorBuilder(org.orekit.propagation.conversion.NumericalPropagatorBuilder) Propagator(org.orekit.propagation.Propagator) AngularAzElMeasurementCreator(org.orekit.estimation.measurements.AngularAzElMeasurementCreator) AngularAzEl(org.orekit.estimation.measurements.AngularAzEl) ObservedMeasurement(org.orekit.estimation.measurements.ObservedMeasurement) Test(org.junit.Test)

Aggregations

GroundStation (org.orekit.estimation.measurements.GroundStation)24 SpacecraftState (org.orekit.propagation.SpacecraftState)19 AbsoluteDate (org.orekit.time.AbsoluteDate)14 Test (org.junit.Test)10 Context (org.orekit.estimation.Context)10 ObservedMeasurement (org.orekit.estimation.measurements.ObservedMeasurement)10 Propagator (org.orekit.propagation.Propagator)10 NumericalPropagatorBuilder (org.orekit.propagation.conversion.NumericalPropagatorBuilder)10 AngularAzEl (org.orekit.estimation.measurements.AngularAzEl)9 Range (org.orekit.estimation.measurements.Range)8 ParameterDriver (org.orekit.utils.ParameterDriver)8 RangeRate (org.orekit.estimation.measurements.RangeRate)7 TurnAroundRange (org.orekit.estimation.measurements.TurnAroundRange)7 TurnAroundRangeMeasurementCreator (org.orekit.estimation.measurements.TurnAroundRangeMeasurementCreator)5 Vector3D (org.hipparchus.geometry.euclidean.threed.Vector3D)4 GeodeticPoint (org.orekit.bodies.GeodeticPoint)4 AngularRadioRefractionModifier (org.orekit.estimation.measurements.modifiers.AngularRadioRefractionModifier)4 RangeTroposphericDelayModifier (org.orekit.estimation.measurements.modifiers.RangeTroposphericDelayModifier)4 EarthITU453AtmosphereRefraction (org.orekit.models.earth.EarthITU453AtmosphereRefraction)4 HashMap (java.util.HashMap)3