Examples with Vector3D org.hipparchus.geometry.euclidean.threed.Vector3D used on opensource projects

Example 16 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class TurnAroundRangeMeasurementCreator method handleStep.

/**
 * Function handling the steps of the propagator
 * A turn-around measurement needs 2 stations, a master and a slave
 * The measurement is a signal:
 * - Emitted from the master ground station
 * - Reflected on the spacecraft
 * - Reflected on the slave ground station
 * - Reflected on the spacecraft again
 * - Received on the master ground station
 * Its value is the elapsed time between emission and reception
 * divided by 2c were c is the speed of light.
 *
 * The path of the signal is divided into 2 legs:
 *  - The 1st leg goes from emission by the master station to reception by the slave station
 *  - The 2nd leg goes from emission by the slave station to reception by the master station
 *
 * The spacecraft state date should, after a few iterations of the estimation process, be
 * set to the date of arrival/departure of the signal to/from the slave station.
 * It is guaranteed by implementation of the estimated measurement.
 * This is done to avoid big shifts in time to compute the transit states.
 * See TurnAroundRange.java for more
 * Thus the spacecraft date is the date when the 1st leg of the path ends and the 2nd leg begins
 */
public void handleStep(final SpacecraftState currentState, final boolean isLast) throws OrekitException {
    try {
        for (Map.Entry<GroundStation, GroundStation> entry : context.TARstations.entrySet()) {
            final GroundStation masterStation = entry.getKey();
            final GroundStation slaveStation = entry.getValue();
            final AbsoluteDate date = currentState.getDate();
            final Frame inertial = currentState.getFrame();
            final Vector3D position = currentState.toTransform().getInverse().transformPosition(antennaPhaseCenter);
            // Create a TAR measurement only if elevation for both stations is higher than elevationMin°
            if ((masterStation.getBaseFrame().getElevation(position, inertial, date) > FastMath.toRadians(30.0)) && (slaveStation.getBaseFrame().getElevation(position, inertial, date) > FastMath.toRadians(30.0))) {
                // The solver used
                final UnivariateSolver solver = new BracketingNthOrderBrentSolver(1.0e-12, 5);
                // Spacecraft date t = date of arrival/departure of the signal to/from from the slave station
                // Slave station position in inertial frame at t
                final Vector3D slaveStationPosition = slaveStation.getOffsetToInertial(inertial, date).transformPosition(Vector3D.ZERO);
                // Downlink time of flight to slave station
                // The date of arrival/departure of the signal to/from the slave station is known and
                // equal to spacecraft date t.
                // Therefore we can use the function "downlinkTimeOfFlight" from GroundStation class
                // final double slaveTauD = slaveStation.downlinkTimeOfFlight(currentState, date);
                final double slaveTauD = solver.solve(1000, new UnivariateFunction() {

                    public double value(final double x) throws OrekitExceptionWrapper {
                        final SpacecraftState transitState = currentState.shiftedBy(-x);
                        final double d = Vector3D.distance(transitState.toTransform().getInverse().transformPosition(antennaPhaseCenter), slaveStationPosition);
                        return d - x * Constants.SPEED_OF_LIGHT;
                    }
                }, -1.0, 1.0);
                // Uplink time of flight from slave station
                // A solver is used to know where the satellite is when it receives the signal
                // back from the slave station
                final double slaveTauU = solver.solve(1000, new UnivariateFunction() {

                    public double value(final double x) throws OrekitExceptionWrapper {
                        final SpacecraftState transitState = currentState.shiftedBy(+x);
                        final double d = Vector3D.distance(transitState.toTransform().getInverse().transformPosition(antennaPhaseCenter), slaveStationPosition);
                        return d - x * Constants.SPEED_OF_LIGHT;
                    }
                }, -1.0, 1.0);
                // Find the position of the master station at signal departure and arrival
                // ----
                // Transit state position & date for the 1st leg of the signal path
                final SpacecraftState S1 = currentState.shiftedBy(-slaveTauD);
                final Vector3D P1 = S1.toTransform().getInverse().transformPosition(antennaPhaseCenter);
                final AbsoluteDate T1 = date.shiftedBy(-slaveTauD);
                // Transit state position & date for the 2nd leg of the signal path
                final Vector3D P2 = currentState.shiftedBy(+slaveTauU).toTransform().getInverse().transformPosition(antennaPhaseCenter);
                final AbsoluteDate T2 = date.shiftedBy(+slaveTauU);
                // Master station downlink delay - from P2 to master station
                // We use a solver to know where the master station is when it receives
                // the signal back from the satellite on the 2nd leg of the path
                final double masterTauD = solver.solve(1000, new UnivariateFunction() {

                    public double value(final double x) throws OrekitExceptionWrapper {
                        try {
                            final Transform t = masterStation.getOffsetToInertial(inertial, T2.shiftedBy(+x));
                            final double d = Vector3D.distance(P2, t.transformPosition(Vector3D.ZERO));
                            return d - x * Constants.SPEED_OF_LIGHT;
                        } catch (OrekitException oe) {
                            throw new OrekitExceptionWrapper(oe);
                        }
                    }
                }, -1.0, 1.0);
                final AbsoluteDate masterReceptionDate = T2.shiftedBy(+masterTauD);
                final TimeStampedPVCoordinates masterStationAtReception = masterStation.getOffsetToInertial(inertial, masterReceptionDate).transformPVCoordinates(new TimeStampedPVCoordinates(masterReceptionDate, PVCoordinates.ZERO));
                // Master station uplink delay - from master station to P1
                // Here the state date is known. Thus we can use the function "signalTimeOfFlight"
                // of the AbstractMeasurement class
                final double masterTauU = AbstractMeasurement.signalTimeOfFlight(masterStationAtReception, P1, T1);
                final AbsoluteDate masterEmissionDate = T1.shiftedBy(-masterTauU);
                final Vector3D masterStationAtEmission = masterStation.getOffsetToInertial(inertial, masterEmissionDate).transformPosition(Vector3D.ZERO);
                // Uplink/downlink distance from/to slave station
                final double slaveDownLinkDistance = Vector3D.distance(P1, slaveStationPosition);
                final double slaveUpLinkDistance = Vector3D.distance(P2, slaveStationPosition);
                // Uplink/downlink distance from/to master station
                final double masterUpLinkDistance = Vector3D.distance(P1, masterStationAtEmission);
                final double masterDownLinkDistance = Vector3D.distance(P2, masterStationAtReception.getPosition());
                addMeasurement(new TurnAroundRange(masterStation, slaveStation, masterReceptionDate, 0.5 * (masterUpLinkDistance + slaveDownLinkDistance + slaveUpLinkDistance + masterDownLinkDistance), 1.0, 10));
            }
        }
    } catch (OrekitExceptionWrapper oew) {
        throw new OrekitException(oew.getException());
    } catch (OrekitException oe) {
        throw new OrekitException(oe);
    }
}

Example 17 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class OnBoardAntennaInterSatellitesRangeModifierTest method testPreliminary.

@Test
public void testPreliminary() throws OrekitException {
    // this test does not check OnBoardAntennaInterSatellitesRangeModifier at all,
    // it just checks InterSatellitesRangeMeasurementCreator 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 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 double xOffset1 = -2.5;
    final double yOffset2 = 0.8;
    final Propagator p2 = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> antennaCenteredMeasurements = EstimationTestUtils.createMeasurements(p2, new InterSatellitesRangeMeasurementCreator(ephemeris, new Vector3D(xOffset1, 0, 0), new Vector3D(0, yOffset2, 0)), 1.0, 3.0, 300.0);
    for (int i = 0; i < spacecraftCenteredMeasurements.size(); ++i) {
        InterSatellitesRange sr = (InterSatellitesRange) spacecraftCenteredMeasurements.get(i);
        InterSatellitesRange ar = (InterSatellitesRange) antennaCenteredMeasurements.get(i);
        Assert.assertEquals(0.0, sr.getDate().durationFrom(ar.getDate()), 2.0e-8);
        Assert.assertTrue(ar.getObservedValue()[0] - sr.getObservedValue()[0] >= -1.0);
        Assert.assertTrue(ar.getObservedValue()[0] - sr.getObservedValue()[0] <= -0.36);
    }
}

Example 18 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class OnBoardAntennaTurnAroundRangeModifierTest method testPreliminary.

@Test
public void testPreliminary() throws OrekitException {
    // this test does not check OnBoardAntennaTurnAroundRangeModifier at all,
    // it just checks TurnAroundRangeMeasurementCreator 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 turn-around range measurements without antenna offset
    final Propagator p1 = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> spacecraftCenteredMeasurements = EstimationTestUtils.createMeasurements(p1, new TurnAroundRangeMeasurementCreator(context, Vector3D.ZERO), 1.0, 3.0, 300.0);
    // create perfect turn-around 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 TurnAroundRangeMeasurementCreator(context, new Vector3D(xOffset, 0, 0)), 1.0, 3.0, 300.0);
    for (int i = 0; i < spacecraftCenteredMeasurements.size(); ++i) {
        TurnAroundRange sr = (TurnAroundRange) spacecraftCenteredMeasurements.get(i);
        TurnAroundRange ar = (TurnAroundRange) antennaCenteredMeasurements.get(i);
        Assert.assertEquals(0.0, sr.getDate().durationFrom(ar.getDate()), 2.0e-8);
        Assert.assertTrue(ar.getObservedValue()[0] - sr.getObservedValue()[0] >= 2.0 * xOffset);
        Assert.assertTrue(ar.getObservedValue()[0] - sr.getObservedValue()[0] <= 1.8 * xOffset);
    }
}

Example 19 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class NRLMSISE00Test method testDensity.

@Test
public void testDensity() throws OrekitException, InstantiationException, IllegalAccessException, IllegalArgumentException, InvocationTargetException, NoSuchMethodException, SecurityException {
    // Build the input params provider
    final InputParams ip = new InputParams();
    // Get Sun
    final PVCoordinatesProvider sun = CelestialBodyFactory.getSun();
    // Get Earth body shape
    final Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, itrf);
    // Build the model
    final NRLMSISE00 atm = new NRLMSISE00(ip, sun, earth).withSwitch(9, -1);
    // Build the date
    final AbsoluteDate date = new AbsoluteDate(new DateComponents(2003, 172), new TimeComponents(29000.), TimeScalesFactory.getUT1(IERSConventions.IERS_2010, true));
    // Build the position
    final double alt = 400.;
    final double lat = 60.;
    final double lon = -70.;
    final GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(lat), FastMath.toRadians(lon), alt * 1000.);
    final Vector3D pos = earth.transform(point);
    // Run
    final double rho = atm.getDensity(date, pos, itrf);
    final double lst = 29000. / 3600. - 70. / 15.;
    final double[] ap = { 4., 100., 100., 100., 100., 100., 100. };
    Class<?> outputClass = getOutputClass();
    Constructor<?> cons = outputClass.getDeclaredConstructor(NRLMSISE00.class, Integer.TYPE, Double.TYPE, Double.TYPE, Double.TYPE, Double.TYPE, Double.TYPE, Double.TYPE, double[].class);
    cons.setAccessible(true);
    Method gtd7d = outputClass.getDeclaredMethod("gtd7d", Double.TYPE);
    gtd7d.setAccessible(true);
    Method getDensity = outputClass.getDeclaredMethod("getDensity", Integer.TYPE);
    getDensity.setAccessible(true);
    final Object out = createOutput(atm, 172, 29000., 60., -70, lst, 150., 150., ap);
    gtd7d.invoke(out, 400.0);
    Assert.assertEquals(rho, ((Double) getDensity.invoke(out, 5)).doubleValue(), rho * 1.e-3);
}

Example 20 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method testRelativeNumericPrecision.

@Test
public void testRelativeNumericPrecision() throws OrekitException {
    // this test is similar in spirit to section 4.2 of Holmes and Featherstone paper,
    // but reduced to lower degree since our reference implementation is MUCH slower
    // than the one used in the paper (Clenshaw method)
    int max = 50;
    NormalizedSphericalHarmonicsProvider provider = new GleasonProvider(max, max);
    HolmesFeatherstoneAttractionModel model = new HolmesFeatherstoneAttractionModel(itrf, provider);
    Assert.assertTrue(model.dependsOnPositionOnly());
    // Note that despite it uses adjustable high accuracy, the reference model
    // uses unstable formulas and hence loses lots of digits near poles.
    // This implies that if we still want about 16 digits near the poles, we
    // need to ask for at least 30 digits in computation. Setting for example
    // the following to 28 digits makes the test fail as the relative errors
    // raise to about 10^-12 near North pole and near 10^-11 near South pole.
    // The reason for this is that the reference becomes less accurate than
    // the model we are testing!
    int digits = 30;
    ReferenceFieldModel refModel = new ReferenceFieldModel(provider, digits);
    double r = 1.25;
    for (double theta = 0.01; theta < 3.14; theta += 0.1) {
        Vector3D position = new Vector3D(r * FastMath.sin(theta), 0.0, r * FastMath.cos(theta));
        Dfp refValue = refModel.nonCentralPart(null, position);
        double value = model.nonCentralPart(null, position, model.getMu());
        double relativeError = error(refValue, value).divide(refValue).toDouble();
        Assert.assertEquals(0, relativeError, 7.0e-15);
    }
}