Examples with FieldCartesianOrbit org.orekit.orbits.FieldCartesianOrbit used on opensource projects

Example 1 with FieldCartesianOrbit

use of org.orekit.orbits.FieldCartesianOrbit in project Orekit by CS-SI.

the class AbstractForceModelTest method toDS.

protected FieldSpacecraftState<DerivativeStructure> toDS(final SpacecraftState state, final AttitudeProvider attitudeProvider) throws OrekitException {
    final Vector3D p = state.getPVCoordinates().getPosition();
    final Vector3D v = state.getPVCoordinates().getVelocity();
    final Vector3D a = state.getPVCoordinates().getAcceleration();
    DSFactory factory = new DSFactory(6, 1);
    Field<DerivativeStructure> field = factory.getDerivativeField();
    final FieldAbsoluteDate<DerivativeStructure> fDate = new FieldAbsoluteDate<>(field, state.getDate());
    final TimeStampedFieldPVCoordinates<DerivativeStructure> fPVA = new TimeStampedFieldPVCoordinates<>(fDate, new FieldVector3D<>(factory.variable(0, p.getX()), factory.variable(1, p.getY()), factory.variable(2, p.getZ())), new FieldVector3D<>(factory.variable(3, v.getX()), factory.variable(4, v.getY()), factory.variable(5, v.getZ())), new FieldVector3D<>(factory.constant(a.getX()), factory.constant(a.getY()), factory.constant(a.getZ())));
    final FieldCartesianOrbit<DerivativeStructure> orbit = new FieldCartesianOrbit<>(fPVA, state.getFrame(), state.getMu());
    final FieldAttitude<DerivativeStructure> attitude = attitudeProvider.getAttitude(orbit, orbit.getDate(), orbit.getFrame());
    return new FieldSpacecraftState<>(orbit, attitude, field.getZero().add(state.getMass()));
}

Example 2 with FieldCartesianOrbit

use of org.orekit.orbits.FieldCartesianOrbit in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestEphemerisDatesBackward.

private <T extends RealFieldElement<T>> void doTestEphemerisDatesBackward(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    TimeScale tai = TimeScalesFactory.getTAI();
    FieldAbsoluteDate<T> initialDate = new FieldAbsoluteDate<>(field, "2015-07-05", tai);
    FieldAbsoluteDate<T> startDate = new FieldAbsoluteDate<>(field, "2015-07-03", tai).shiftedBy(-0.1);
    FieldAbsoluteDate<T> endDate = new FieldAbsoluteDate<>(field, "2015-07-04", tai);
    Frame eci = FramesFactory.getGCRF();
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(zero.add(600e3 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS), zero, zero, zero, zero, zero, PositionAngle.TRUE, eci, initialDate, mu);
    OrbitType type = OrbitType.CARTESIAN;
    double[][] tol = NumericalPropagator.tolerances(1e-3, orbit.toOrbit(), type);
    FieldNumericalPropagator<T> prop = new FieldNumericalPropagator<>(field, new DormandPrince853FieldIntegrator<>(field, 0.1, 500, tol[0], tol[1]));
    prop.setOrbitType(type);
    prop.resetInitialState(new FieldSpacecraftState<>(new FieldCartesianOrbit<>(orbit)));
    // action
    prop.setEphemerisMode();
    prop.propagate(endDate, startDate);
    FieldBoundedPropagator<T> ephemeris = prop.getGeneratedEphemeris();
    // verify
    TimeStampedFieldPVCoordinates<T> actualPV = ephemeris.getPVCoordinates(startDate, eci);
    TimeStampedFieldPVCoordinates<T> expectedPV = orbit.getPVCoordinates(startDate, eci);
    MatcherAssert.assertThat(actualPV.getPosition().toVector3D(), OrekitMatchers.vectorCloseTo(expectedPV.getPosition().toVector3D(), 1.0));
    MatcherAssert.assertThat(actualPV.getVelocity().toVector3D(), OrekitMatchers.vectorCloseTo(expectedPV.getVelocity().toVector3D(), 1.0));
    MatcherAssert.assertThat(ephemeris.getMinDate().durationFrom(startDate).getReal(), OrekitMatchers.closeTo(0, 0));
    MatcherAssert.assertThat(ephemeris.getMaxDate().durationFrom(endDate).getReal(), OrekitMatchers.closeTo(0, 0));
    // test date
    FieldAbsoluteDate<T> date = endDate.shiftedBy(-0.11);
    Assert.assertEquals(ephemeris.propagate(date).getDate().durationFrom(date).getReal(), 0, 0);
}

Example 3 with FieldCartesianOrbit

use of org.orekit.orbits.FieldCartesianOrbit in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestEphemerisDates.

private <T extends RealFieldElement<T>> void doTestEphemerisDates(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    TimeScale tai = TimeScalesFactory.getTAI();
    FieldAbsoluteDate<T> initialDate = new FieldAbsoluteDate<>(field, "2015-07-01", tai);
    FieldAbsoluteDate<T> startDate = new FieldAbsoluteDate<>(field, "2015-07-03", tai).shiftedBy(-0.1);
    FieldAbsoluteDate<T> endDate = new FieldAbsoluteDate<>(field, "2015-07-04", tai);
    Frame eci = FramesFactory.getGCRF();
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(zero.add(600e3 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS), zero, zero, zero, zero, zero, PositionAngle.TRUE, eci, initialDate, mu);
    OrbitType type = OrbitType.CARTESIAN;
    double[][] tol = NumericalPropagator.tolerances(1e-3, orbit.toOrbit(), type);
    FieldNumericalPropagator<T> prop = new FieldNumericalPropagator<>(field, new DormandPrince853FieldIntegrator<>(field, 0.1, 500, tol[0], tol[1]));
    prop.setOrbitType(type);
    prop.resetInitialState(new FieldSpacecraftState<>(new FieldCartesianOrbit<>(orbit)));
    // action
    prop.setEphemerisMode();
    prop.propagate(startDate, endDate);
    FieldBoundedPropagator<T> ephemeris = prop.getGeneratedEphemeris();
    // verify
    TimeStampedFieldPVCoordinates<T> actualPV = ephemeris.getPVCoordinates(startDate, eci);
    TimeStampedFieldPVCoordinates<T> expectedPV = orbit.getPVCoordinates(startDate, eci);
    MatcherAssert.assertThat(actualPV.getPosition().toVector3D(), OrekitMatchers.vectorCloseTo(expectedPV.getPosition().toVector3D(), 1.0));
    MatcherAssert.assertThat(actualPV.getVelocity().toVector3D(), OrekitMatchers.vectorCloseTo(expectedPV.getVelocity().toVector3D(), 1.0));
    MatcherAssert.assertThat(ephemeris.getMinDate().durationFrom(startDate).getReal(), OrekitMatchers.closeTo(0, 0));
    MatcherAssert.assertThat(ephemeris.getMaxDate().durationFrom(endDate).getReal(), OrekitMatchers.closeTo(0, 0));
    // test date
    FieldAbsoluteDate<T> date = endDate.shiftedBy(-0.11);
    Assert.assertEquals(ephemeris.propagate(date).getDate().durationFrom(date).getReal(), 0, 0);
}

Example 4 with FieldCartesianOrbit

use of org.orekit.orbits.FieldCartesianOrbit in project Orekit by CS-SI.

the class FieldPVCoordinatesTest method testJounceIsAccelerationSecondDerivative.

@Test
public void testJounceIsAccelerationSecondDerivative() throws OrekitException {
    final FieldCartesianOrbit<Decimal64> orbit = new FieldCartesianOrbit<>(new FieldPVCoordinates<>(new FieldVector3D<>(new Decimal64(-4947831.), new Decimal64(-3765382.), new Decimal64(-3708221.)), new FieldVector3D<>(new Decimal64(-2079.), new Decimal64(5291.), new Decimal64(-7842.))), FramesFactory.getEME2000(), FieldAbsoluteDate.getJ2000Epoch(Decimal64Field.getInstance()), Constants.EIGEN5C_EARTH_MU);
    FieldPVCoordinates<FieldDerivativeStructure<Decimal64>> fv = orbit.getPVCoordinates().toDerivativeStructurePV(2);
    FieldVector3D<Decimal64> numericalJounce = differentiate(orbit, o -> {
        FieldVector3D<FieldDerivativeStructure<Decimal64>> a = o.getPVCoordinates().toDerivativeStructurePV(1).getAcceleration();
        return new FieldVector3D<>(a.getX().getPartialDerivative(1), a.getY().getPartialDerivative(1), a.getZ().getPartialDerivative(1));
    });
    Assert.assertEquals(numericalJounce.getX().getReal(), fv.getAcceleration().getX().getPartialDerivative(2).getReal(), 1.0e-15);
    Assert.assertEquals(numericalJounce.getY().getReal(), fv.getAcceleration().getY().getPartialDerivative(2).getReal(), 1.0e-15);
    Assert.assertEquals(numericalJounce.getZ().getReal(), fv.getAcceleration().getZ().getPartialDerivative(2).getReal(), 1.0e-15);
}

Example 5 with FieldCartesianOrbit

use of org.orekit.orbits.FieldCartesianOrbit in project Orekit by CS-SI.

the class DSConverter method getState.

/**
 * Get the state with the number of parameters consistent with force model.
 * @param forceModel force model
 * @return state with the number of parameters consistent with force model
 */
public FieldSpacecraftState<DerivativeStructure> getState(final ForceModel forceModel) {
    // count the required number of parameters
    int nbParams = 0;
    for (final ParameterDriver driver : forceModel.getParametersDrivers()) {
        if (driver.isSelected()) {
            ++nbParams;
        }
    }
    // fill in intermediate slots
    while (dsStates.size() < nbParams + 1) {
        dsStates.add(null);
    }
    if (dsStates.get(nbParams) == null) {
        // it is the first time we need this number of parameters
        // we need to create the state
        final DSFactory factory = new DSFactory(freeStateParameters + nbParams, 1);
        final FieldSpacecraftState<DerivativeStructure> s0 = dsStates.get(0);
        // orbit
        final FieldPVCoordinates<DerivativeStructure> pv0 = s0.getPVCoordinates();
        final FieldOrbit<DerivativeStructure> dsOrbit = new FieldCartesianOrbit<>(new TimeStampedFieldPVCoordinates<>(s0.getDate().toAbsoluteDate(), extend(pv0.getPosition(), factory), extend(pv0.getVelocity(), factory), extend(pv0.getAcceleration(), factory)), s0.getFrame(), s0.getMu());
        // attitude
        final FieldAngularCoordinates<DerivativeStructure> ac0 = s0.getAttitude().getOrientation();
        final FieldAttitude<DerivativeStructure> dsAttitude = new FieldAttitude<>(s0.getAttitude().getReferenceFrame(), new TimeStampedFieldAngularCoordinates<>(dsOrbit.getDate(), extend(ac0.getRotation(), factory), extend(ac0.getRotationRate(), factory), extend(ac0.getRotationAcceleration(), factory)));
        // mass
        final DerivativeStructure dsM = extend(s0.getMass(), factory);
        dsStates.set(nbParams, new FieldSpacecraftState<>(dsOrbit, dsAttitude, dsM));
    }
    return dsStates.get(nbParams);
}