Examples with FieldVector3D org.hipparchus.geometry.euclidean.threed.FieldVector3D used on opensource projects

Example 51 with FieldVector3D

use of org.hipparchus.geometry.euclidean.threed.FieldVector3D in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestNoExtrapolation.

private <T extends RealFieldElement<T>> void doTestNoExtrapolation(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    final FieldAbsoluteDate<T> initDate = FieldAbsoluteDate.getJ2000Epoch(field);
    FieldSpacecraftState<T> initialState;
    FieldNumericalPropagator<T> propagator;
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(7.0e6), zero.add(1.0e6), zero.add(4.0e6));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(-500.0), zero.add(8000.0), zero.add(1000.0));
    final FieldOrbit<T> orbit = new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    initialState = new FieldSpacecraftState<>(orbit);
    OrbitType type = OrbitType.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit.toOrbit(), type);
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(zero.add(60));
    propagator = new FieldNumericalPropagator<>(field, integrator);
    propagator.setOrbitType(type);
    propagator.setInitialState(initialState);
    // Propagate of the initial at the initial date
    final FieldSpacecraftState<T> finalState = propagator.propagate(initDate);
    // Initial orbit definition
    final FieldVector3D<T> initialPosition = initialState.getPVCoordinates().getPosition();
    final FieldVector3D<T> initialVelocity = initialState.getPVCoordinates().getVelocity();
    // Final orbit definition
    final FieldVector3D<T> finalPosition = finalState.getPVCoordinates().getPosition();
    final FieldVector3D<T> finalVelocity = finalState.getPVCoordinates().getVelocity();
    // Check results
    Assert.assertEquals(initialPosition.getX().getReal(), finalPosition.getX().getReal(), 1.0e-10);
    Assert.assertEquals(initialPosition.getY().getReal(), finalPosition.getY().getReal(), 1.0e-10);
    Assert.assertEquals(initialPosition.getZ().getReal(), finalPosition.getZ().getReal(), 1.0e-10);
    Assert.assertEquals(initialVelocity.getX().getReal(), finalVelocity.getX().getReal(), 1.0e-10);
    Assert.assertEquals(initialVelocity.getY().getReal(), finalVelocity.getY().getReal(), 1.0e-10);
    Assert.assertEquals(initialVelocity.getZ().getReal(), finalVelocity.getZ().getReal(), 1.0e-10);
}

Example 52 with FieldVector3D

use of org.hipparchus.geometry.euclidean.threed.FieldVector3D in project Orekit by CS-SI.

the class BodyCenterPointingTest method doTestSpin.

private <T extends RealFieldElement<T>> void doTestSpin(final Field<T> field) throws OrekitException {
    final double ehMu = 3.9860047e14;
    final double ae = 6.378137e6;
    final double c20 = -1.08263e-3;
    final double c30 = 2.54e-6;
    final double c40 = 1.62e-6;
    final double c50 = 2.3e-7;
    final double c60 = -5.5e-7;
    // Satellite position as circular parameters
    final T zero = field.getZero();
    final T a = zero.add(7178000.0);
    final T e = zero.add(7e-5);
    final T i = zero.add(FastMath.toRadians(50.));
    final T pa = zero.add(FastMath.toRadians(45.));
    final T raan = zero.add(FastMath.toRadians(270.));
    final T m = zero.add(FastMath.toRadians(5.3 - 270));
    // Computation date
    FieldAbsoluteDate<T> date_R = new FieldAbsoluteDate<>(field, new DateComponents(2008, 04, 07), TimeComponents.H00, TimeScalesFactory.getUTC());
    // Orbit
    FieldKeplerianOrbit<T> circ = new FieldKeplerianOrbit<>(a, e, i, pa, raan, m, PositionAngle.MEAN, FramesFactory.getEME2000(), date_R, ehMu);
    // WGS84 Earth model
    OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    // Earth center pointing attitude provider
    BodyCenterPointing earthCenterAttitudeLaw = new BodyCenterPointing(circ.getFrame(), earth);
    final FieldAbsoluteDate<T> date = FieldAbsoluteDate.getJ2000Epoch(field).shiftedBy(584.);
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(3220103.), zero.add(69623.), zero.add(6449822.));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(6414.7), zero.add(-2006.), zero.add(-3180.));
    final FieldCircularOrbit<T> initialOrbit = new FieldCircularOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), date, ehMu);
    FieldEcksteinHechlerPropagator<T> propagator = new FieldEcksteinHechlerPropagator<>(initialOrbit, ae, ehMu, c20, c30, c40, c50, c60);
    propagator.setAttitudeProvider(earthCenterAttitudeLaw);
    double h = 0.01;
    FieldSpacecraftState<T> s0 = propagator.propagate(date);
    FieldSpacecraftState<T> sMinus = propagator.propagate(date.shiftedBy(-h));
    FieldSpacecraftState<T> sPlus = propagator.propagate(date.shiftedBy(h));
    // check spin is consistent with attitude evolution
    T errorAngleMinus = FieldRotation.distance(sMinus.shiftedBy(zero.add(h)).getAttitude().getRotation(), s0.getAttitude().getRotation());
    T evolutionAngleMinus = FieldRotation.distance(sMinus.getAttitude().getRotation(), s0.getAttitude().getRotation());
    Assert.assertEquals(0.0, errorAngleMinus.getReal(), 1.0e-6 * evolutionAngleMinus.getReal());
    T errorAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.shiftedBy(zero.add(-h)).getAttitude().getRotation());
    T evolutionAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.getAttitude().getRotation());
    Assert.assertEquals(0.0, errorAnglePlus.getReal(), 1.0e-6 * evolutionAnglePlus.getReal());
    FieldVector3D<T> spin0 = s0.getAttitude().getSpin();
    FieldVector3D<T> reference = FieldAngularCoordinates.estimateRate(sMinus.getAttitude().getRotation(), sPlus.getAttitude().getRotation(), 2 * h);
    Assert.assertTrue(spin0.getNorm().getReal() > 1.0e-3);
    Assert.assertEquals(0.0, spin0.subtract(reference).getNorm().getReal(), 1.0e-13);
}

Example 53 with FieldVector3D

use of org.hipparchus.geometry.euclidean.threed.FieldVector3D in project Orekit by CS-SI.

the class OneAxisEllipsoidTest method checkCartesianToEllipsoidic.

private void checkCartesianToEllipsoidic(double ae, double f, double x, double y, double z, double longitude, double latitude, double altitude) throws OrekitException {
    AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
    Frame frame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    OneAxisEllipsoid model = new OneAxisEllipsoid(ae, f, frame);
    GeodeticPoint gp = model.transform(new Vector3D(x, y, z), frame, date);
    Assert.assertEquals(longitude, MathUtils.normalizeAngle(gp.getLongitude(), longitude), 1.0e-10);
    Assert.assertEquals(latitude, gp.getLatitude(), 1.0e-10);
    Assert.assertEquals(altitude, gp.getAltitude(), 1.0e-10 * FastMath.abs(ae));
    Vector3D rebuiltNadir = Vector3D.crossProduct(gp.getSouth(), gp.getWest());
    Assert.assertEquals(0, rebuiltNadir.subtract(gp.getNadir()).getNorm(), 1.0e-15);
    FieldGeodeticPoint<Decimal64> gp64 = model.transform(new FieldVector3D<Decimal64>(new Decimal64(x), new Decimal64(y), new Decimal64(z)), frame, new FieldAbsoluteDate<>(Decimal64Field.getInstance(), date));
    Assert.assertEquals(longitude, MathUtils.normalizeAngle(gp64.getLongitude().getReal(), longitude), 1.0e-10);
    Assert.assertEquals(latitude, gp64.getLatitude().getReal(), 1.0e-10);
    Assert.assertEquals(altitude, gp64.getAltitude().getReal(), 1.0e-10 * FastMath.abs(ae));
    FieldVector3D<Decimal64> rebuiltNadir64 = FieldVector3D.crossProduct(gp64.getSouth(), gp64.getWest());
    Assert.assertEquals(0, rebuiltNadir64.subtract(gp64.getNadir()).getNorm().getReal(), 1.0e-15);
}

Example 54 with FieldVector3D

use of org.hipparchus.geometry.euclidean.threed.FieldVector3D in project Orekit by CS-SI.

the class FixedRateTest method doTestSpin.

private <T extends RealFieldElement<T>> void doTestSpin(final Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(1970, 01, 01), new TimeComponents(3, 25, 45.6789), TimeScalesFactory.getUTC());
    final T rate = zero.add(2 * FastMath.PI / (12 * 60));
    AttitudeProvider law = new FixedRate(new Attitude(date.toAbsoluteDate(), FramesFactory.getEME2000(), new Rotation(0.48, 0.64, 0.36, 0.48, false), new Vector3D(rate.getReal(), Vector3D.PLUS_K), Vector3D.ZERO));
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(zero.add(7178000.0), zero.add(1.e-4), zero.add(FastMath.toRadians(50.)), zero.add(FastMath.toRadians(10.)), zero.add(FastMath.toRadians(20.)), zero.add(FastMath.toRadians(30.)), PositionAngle.MEAN, FramesFactory.getEME2000(), date, 3.986004415e14);
    FieldPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit, law);
    T h = zero.add(0.01);
    FieldSpacecraftState<T> sMinus = propagator.propagate(date.shiftedBy(h.negate()));
    FieldSpacecraftState<T> s0 = propagator.propagate(date);
    FieldSpacecraftState<T> sPlus = propagator.propagate(date.shiftedBy(h));
    // check spin is consistent with attitude evolution
    double errorAngleMinus = FieldRotation.distance(sMinus.shiftedBy(h).getAttitude().getRotation(), s0.getAttitude().getRotation()).getReal();
    double evolutionAngleMinus = FieldRotation.distance(sMinus.getAttitude().getRotation(), s0.getAttitude().getRotation()).getReal();
    Assert.assertEquals(0.0, errorAngleMinus, 1.0e-6 * evolutionAngleMinus);
    double errorAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.shiftedBy(h.negate()).getAttitude().getRotation()).getReal();
    double evolutionAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.getAttitude().getRotation()).getReal();
    Assert.assertEquals(0.0, errorAnglePlus, 1.0e-6 * evolutionAnglePlus);
    FieldVector3D<T> spin0 = s0.getAttitude().getSpin();
    FieldVector3D<T> reference = FieldAngularCoordinates.estimateRate(sMinus.getAttitude().getRotation(), sPlus.getAttitude().getRotation(), h.multiply(2));
    Assert.assertEquals(0.0, spin0.subtract(reference).getNorm().getReal(), 1.0e-14);
}

Example 55 with FieldVector3D

use of org.hipparchus.geometry.euclidean.threed.FieldVector3D in project Orekit by CS-SI.

the class PVCoordinates method toDerivativeStructureVector.

/**
 * Transform the instance to a {@link FieldVector3D}<{@link DerivativeStructure}>.
 * <p>
 * The {@link DerivativeStructure} coordinates correspond to time-derivatives up
 * to the user-specified order.
 * </p>
 * @param order derivation order for the vector components (must be either 0, 1 or 2)
 * @return vector with time-derivatives embedded within the coordinates
 * @exception OrekitException if the user specified order is too large
 */
public FieldVector3D<DerivativeStructure> toDerivativeStructureVector(final int order) throws OrekitException {
    final DSFactory factory;
    final DerivativeStructure x;
    final DerivativeStructure y;
    final DerivativeStructure z;
    switch(order) {
        case 0:
            factory = new DSFactory(1, order);
            x = factory.build(position.getX());
            y = factory.build(position.getY());
            z = factory.build(position.getZ());
            break;
        case 1:
            factory = new DSFactory(1, order);
            x = factory.build(position.getX(), velocity.getX());
            y = factory.build(position.getY(), velocity.getY());
            z = factory.build(position.getZ(), velocity.getZ());
            break;
        case 2:
            factory = new DSFactory(1, order);
            x = factory.build(position.getX(), velocity.getX(), acceleration.getX());
            y = factory.build(position.getY(), velocity.getY(), acceleration.getY());
            z = factory.build(position.getZ(), velocity.getZ(), acceleration.getZ());
            break;
        default:
            throw new OrekitException(OrekitMessages.OUT_OF_RANGE_DERIVATION_ORDER, order);
    }
    return new FieldVector3D<>(x, y, z);
}