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

Example 11 with FieldVector3D

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

the class DTM2000 method getDensity.

/**
 * {@inheritDoc}
 */
@Override
public <T extends RealFieldElement<T>> T getDensity(final FieldAbsoluteDate<T> date, final FieldVector3D<T> position, final Frame frame) throws OrekitException {
    // check if data are available :
    final AbsoluteDate dateD = date.toAbsoluteDate();
    if ((dateD.compareTo(inputParams.getMaxDate()) > 0) || (dateD.compareTo(inputParams.getMinDate()) < 0)) {
        throw new OrekitException(OrekitMessages.NO_SOLAR_ACTIVITY_AT_DATE, dateD, inputParams.getMinDate(), inputParams.getMaxDate());
    }
    // compute day number in current year
    final Calendar cal = new GregorianCalendar();
    cal.setTime(date.toDate(TimeScalesFactory.getUTC()));
    final int day = cal.get(Calendar.DAY_OF_YEAR);
    // position in ECEF so we only have to do the transform once
    final Frame ecef = earth.getBodyFrame();
    final FieldVector3D<T> pEcef = frame.getTransformTo(ecef, date).transformPosition(position);
    // compute geodetic position
    final FieldGeodeticPoint<T> inBody = earth.transform(pEcef, ecef, date);
    final T alti = inBody.getAltitude();
    final T lon = inBody.getLongitude();
    final T lat = inBody.getLatitude();
    // compute local solar time
    final Vector3D sunPos = sun.getPVCoordinates(dateD, ecef).getPosition();
    final T y = pEcef.getY().multiply(sunPos.getX()).subtract(pEcef.getX().multiply(sunPos.getY()));
    final T x = pEcef.getX().multiply(sunPos.getX()).add(pEcef.getY().multiply(sunPos.getY()));
    final T hl = y.atan2(x).add(FastMath.PI);
    // get current solar activity data and compute
    return getDensity(day, alti, lon, lat, hl, inputParams.getInstantFlux(dateD), inputParams.getMeanFlux(dateD), inputParams.getThreeHourlyKP(dateD), inputParams.get24HoursKp(dateD));
}

Example 12 with FieldVector3D

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

the class NRLMSISE00 method localSolarTime.

/**
 * Get local solar time.
 * @param date current date
 * @param position current position in frame
 * @param frame the frame in which is defined the position
 * @param <T> type of the filed elements
 * @return the local solar time (hour in [0, 24[)
 * @throws OrekitException if position cannot be computed in given frame
 */
private <T extends RealFieldElement<T>> T localSolarTime(final AbsoluteDate date, final FieldVector3D<T> position, final Frame frame) throws OrekitException {
    final Vector3D sunPos = sun.getPVCoordinates(date, frame).getPosition();
    final T y = position.getY().multiply(sunPos.getX()).subtract(position.getX().multiply(sunPos.getY()));
    final T x = position.getX().multiply(sunPos.getX()).add(position.getY().multiply(sunPos.getY()));
    final T hl = y.atan2(x).add(FastMath.PI);
    return hl.multiply(12. / FastMath.PI);
}

Example 13 with FieldVector3D

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

the class HarrisPriester method getDensity.

/**
 * Get the local density.
 * @param sunInEarth position of the Sun in Earth frame (m)
 * @param posInEarth target position in Earth frame (m)
 * @return the local density (kg/m³)
 * @param <T> instance of RealFieldElement<T>
 * @exception OrekitException if altitude is below the model minimal altitude
 */
public <T extends RealFieldElement<T>> T getDensity(final Vector3D sunInEarth, final FieldVector3D<T> posInEarth) throws OrekitException {
    final T zero = posInEarth.getX().getField().getZero();
    final T posAlt = getHeight(posInEarth);
    // Check for height boundaries
    if (posAlt.getReal() < getMinAlt()) {
        throw new OrekitException(OrekitMessages.ALTITUDE_BELOW_ALLOWED_THRESHOLD, posAlt, getMinAlt());
    }
    if (posAlt.getReal() > getMaxAlt()) {
        return zero;
    }
    // Diurnal bulge apex direction
    final Vector3D sunDir = sunInEarth.normalize();
    final Vector3D bulDir = new Vector3D(sunDir.getX() * COSLAG - sunDir.getY() * SINLAG, sunDir.getX() * SINLAG + sunDir.getY() * COSLAG, sunDir.getZ());
    // Cosine of angle Psi between the diurnal bulge apex and the satellite
    final T cosPsi = posInEarth.normalize().dotProduct(bulDir.normalize());
    // (1 + cos(Psi))/2 = cos²(Psi/2)
    final T c2Psi2 = cosPsi.add(1.).divide(2);
    final T cPsi2 = c2Psi2.sqrt();
    final T cosPow = (cPsi2.getReal() > MIN_COS) ? c2Psi2.multiply(cPsi2.pow(n - 2)) : zero;
    // Search altitude index in density table
    int ia = 0;
    while (ia < tabAltRho.length - 2 && posAlt.getReal() > tabAltRho[ia + 1][0]) {
        ia++;
    }
    // Fractional satellite height
    final T dH = posAlt.negate().add(tabAltRho[ia][0]).divide(tabAltRho[ia][0] - tabAltRho[ia + 1][0]);
    // Min exponential density interpolation
    final T rhoMin = zero.add(tabAltRho[ia + 1][1] / tabAltRho[ia][1]).pow(dH).multiply(tabAltRho[ia][1]);
    if (Precision.equals(cosPow.getReal(), 0.)) {
        return zero.add(rhoMin);
    } else {
        // Max exponential density interpolation
        final T rhoMax = zero.add(tabAltRho[ia + 1][2] / tabAltRho[ia][2]).pow(dH).multiply(tabAltRho[ia][2]);
        return rhoMin.add(rhoMax.subtract(rhoMin).multiply(cosPow));
    }
}

Example 14 with FieldVector3D

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

the class HarrisPriester method getDensity.

/**
 * Get the local density at some position.
 * @param date current date
 * @param position current position
 * @param <T> implements a RealFieldElement
 * @param frame the frame in which is defined the position
 * @return local density (kg/m³)
 * @exception OrekitException if some frame conversion cannot be performed
 *            or if altitude is below the model minimal altitude
 */
public <T extends RealFieldElement<T>> T getDensity(final FieldAbsoluteDate<T> date, final FieldVector3D<T> position, final Frame frame) throws OrekitException {
    // Sun position in earth frame
    final Vector3D sunInEarth = sun.getPVCoordinates(date.toAbsoluteDate(), earth.getBodyFrame()).getPosition();
    // Target position in earth frame
    final FieldVector3D<T> posInEarth = frame.getTransformTo(earth.getBodyFrame(), date.toAbsoluteDate()).transformPosition(position);
    return getDensity(sunInEarth, posInEarth);
}

Example 15 with FieldVector3D

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

the class FieldNumericalPropagatorTest method doTestPropagationTypesElliptical.

private <T extends RealFieldElement<T>> void doTestPropagationTypesElliptical(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);
    ForceModel gravityField = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), GravityFieldFactory.getNormalizedProvider(5, 5));
    propagator.addForceModel(gravityField);
    // Propagation of the initial at t + dt
    final FieldPVCoordinates<T> pv = initialState.getPVCoordinates();
    final T dP = zero.add(0.001);
    final T dV = pv.getPosition().getNormSq().multiply(pv.getVelocity().getNorm()).reciprocal().multiply(dP.multiply(initialState.getMu()));
    final FieldPVCoordinates<T> pvcM = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.MEAN, propagator);
    final FieldPVCoordinates<T> pviM = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.MEAN, propagator);
    final FieldPVCoordinates<T> pveM = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.MEAN, propagator);
    final FieldPVCoordinates<T> pvkM = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.MEAN, propagator);
    final FieldPVCoordinates<T> pvcE = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.ECCENTRIC, propagator);
    final FieldPVCoordinates<T> pviE = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.ECCENTRIC, propagator);
    final FieldPVCoordinates<T> pveE = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.ECCENTRIC, propagator);
    final FieldPVCoordinates<T> pvkE = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.ECCENTRIC, propagator);
    final FieldPVCoordinates<T> pvcT = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.TRUE, propagator);
    final FieldPVCoordinates<T> pviT = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.TRUE, propagator);
    final FieldPVCoordinates<T> pveT = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.TRUE, propagator);
    final FieldPVCoordinates<T> pvkT = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.TRUE, propagator);
    Assert.assertEquals(0, pvcM.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 3.0);
    Assert.assertEquals(0, pvcM.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 2.0);
    Assert.assertEquals(0, pviM.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.6);
    Assert.assertEquals(0, pviM.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.4);
    Assert.assertEquals(0, pvkM.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.5);
    Assert.assertEquals(0, pvkM.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.3);
    Assert.assertEquals(0, pveM.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.2);
    Assert.assertEquals(0, pveM.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.2);
    Assert.assertEquals(0, pvcE.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 3.0);
    Assert.assertEquals(0, pvcE.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 2.0);
    Assert.assertEquals(0, pviE.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.03);
    Assert.assertEquals(0, pviE.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.04);
    Assert.assertEquals(0, pvkE.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.4);
    Assert.assertEquals(0, pvkE.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.3);
    Assert.assertEquals(0, pveE.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.2);
    Assert.assertEquals(0, pveE.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.07);
    Assert.assertEquals(0, pvcT.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 3.0);
    Assert.assertEquals(0, pvcT.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 2.0);
    Assert.assertEquals(0, pviT.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.3);
    Assert.assertEquals(0, pviT.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.2);
    Assert.assertEquals(0, pvkT.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.4);
    Assert.assertEquals(0, pvkT.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.2);
}