Examples with FieldAbsoluteDate org.orekit.time.FieldAbsoluteDate used on opensource projects

Example 21 with FieldAbsoluteDate

use of org.orekit.time.FieldAbsoluteDate in project Orekit by CS-SI.

the class RelativityTest method RealFieldExpectErrorTest.

/**
 *Same test as the previous one but not adding the ForceModel to the NumericalPropagator
 *        it is a test to validate the previous test.
 *        (to test if the ForceModel it's actually
 *        doing something in the Propagator and the FieldPropagator)
 */
@Test
public void RealFieldExpectErrorTest() throws OrekitException {
    DSFactory factory = new DSFactory(6, 0);
    DerivativeStructure a_0 = factory.variable(0, 7e7);
    DerivativeStructure e_0 = factory.variable(1, 0.4);
    DerivativeStructure i_0 = factory.variable(2, 85 * FastMath.PI / 180);
    DerivativeStructure R_0 = factory.variable(3, 0.7);
    DerivativeStructure O_0 = factory.variable(4, 0.5);
    DerivativeStructure n_0 = factory.variable(5, 0.1);
    Field<DerivativeStructure> field = a_0.getField();
    DerivativeStructure zero = field.getZero();
    FieldAbsoluteDate<DerivativeStructure> J2000 = new FieldAbsoluteDate<>(field);
    Frame EME = FramesFactory.getEME2000();
    FieldKeplerianOrbit<DerivativeStructure> FKO = new FieldKeplerianOrbit<>(a_0, e_0, i_0, R_0, O_0, n_0, PositionAngle.MEAN, EME, J2000, Constants.EIGEN5C_EARTH_MU);
    FieldSpacecraftState<DerivativeStructure> initialState = new FieldSpacecraftState<>(FKO);
    SpacecraftState iSR = initialState.toSpacecraftState();
    OrbitType type = OrbitType.KEPLERIAN;
    double[][] tolerance = NumericalPropagator.tolerances(0.001, FKO.toOrbit(), type);
    AdaptiveStepsizeFieldIntegrator<DerivativeStructure> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(zero.add(60));
    AdaptiveStepsizeIntegrator RIntegrator = new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
    RIntegrator.setInitialStepSize(60);
    FieldNumericalPropagator<DerivativeStructure> FNP = new FieldNumericalPropagator<>(field, integrator);
    FNP.setOrbitType(type);
    FNP.setInitialState(initialState);
    NumericalPropagator NP = new NumericalPropagator(RIntegrator);
    NP.setOrbitType(type);
    NP.setInitialState(iSR);
    final Relativity forceModel = new Relativity(Constants.EIGEN5C_EARTH_MU);
    FNP.addForceModel(forceModel);
    // NOT ADDING THE FORCE MODEL TO THE NUMERICAL PROPAGATOR   NP.addForceModel(forceModel);
    FieldAbsoluteDate<DerivativeStructure> target = J2000.shiftedBy(1000.);
    FieldSpacecraftState<DerivativeStructure> finalState_DS = FNP.propagate(target);
    SpacecraftState finalState_R = NP.propagate(target.toAbsoluteDate());
    FieldPVCoordinates<DerivativeStructure> finPVC_DS = finalState_DS.getPVCoordinates();
    PVCoordinates finPVC_R = finalState_R.getPVCoordinates();
    Assert.assertEquals(0, Vector3D.distance(finPVC_DS.toPVCoordinates().getPosition(), finPVC_R.getPosition()), 8.0e-13 * finPVC_R.getPosition().getNorm());
}

Example 22 with FieldAbsoluteDate

use of org.orekit.time.FieldAbsoluteDate in project Orekit by CS-SI.

the class SolidTidesFieldTest method testK1Example.

@Test
public void testK1Example() throws OrekitException, NoSuchFieldException, IllegalAccessException, NoSuchMethodException, InvocationTargetException {
    // the reference for this test is the example at the bottom of page 86, IERS conventions 2010 section 6.2.1
    final PoissonSeriesParser k21Parser = new PoissonSeriesParser(18).withOptionalColumn(1).withDoodson(4, 3).withFirstDelaunay(10);
    final String name = "/tides/tab6.5a-only-K1.txt";
    final double pico = 1.0e-12;
    final PoissonSeries c21Series = k21Parser.withSinCos(0, 17, pico, 18, pico).parse(getClass().getResourceAsStream(name), name);
    final PoissonSeries s21Series = k21Parser.withSinCos(0, 18, -pico, 17, pico).parse(getClass().getResourceAsStream(name), name);
    final UT1Scale ut1 = TimeScalesFactory.getUT1(IERSConventions.IERS_2010, false);
    final TimeScalarFunction gmstFunction = IERSConventions.IERS_2010.getGMSTFunction(ut1);
    Method getNA = IERSConventions.class.getDeclaredMethod("getNutationArguments", TimeScale.class);
    getNA.setAccessible(true);
    final FundamentalNutationArguments arguments = (FundamentalNutationArguments) getNA.invoke(IERSConventions.IERS_2010, ut1);
    TimeVectorFunction deltaCSFunction = new TimeVectorFunction() {

        public double[] value(final AbsoluteDate date) {
            final BodiesElements elements = arguments.evaluateAll(date);
            return new double[] { 0.0, c21Series.value(elements), s21Series.value(elements), 0.0, 0.0 };
        }

        public <T extends RealFieldElement<T>> T[] value(final FieldAbsoluteDate<T> date) {
            // never called in this test
            throw new OrekitInternalError(null);
        }
    };
    SolidTidesField tf = new SolidTidesField(IERSConventions.IERS_2010.getLoveNumbers(), deltaCSFunction, IERSConventions.IERS_2010.getPermanentTide(), IERSConventions.IERS_2010.getSolidPoleTide(ut1.getEOPHistory()), FramesFactory.getITRF(IERSConventions.IERS_2010, false), Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS, Constants.EIGEN5C_EARTH_MU, TideSystem.ZERO_TIDE, CelestialBodyFactory.getSun(), CelestialBodyFactory.getMoon());
    Method frequencyDependentPart = SolidTidesField.class.getDeclaredMethod("frequencyDependentPart", AbsoluteDate.class, double[][].class, double[][].class);
    frequencyDependentPart.setAccessible(true);
    double[][] cachedCNM = new double[5][5];
    double[][] cachedSNM = new double[5][5];
    AbsoluteDate t0 = new AbsoluteDate(2003, 5, 6, 13, 43, 32.125, TimeScalesFactory.getUTC());
    for (double dt = 0; dt < Constants.JULIAN_DAY; dt += 300) {
        AbsoluteDate date = t0.shiftedBy(dt);
        for (int i = 0; i < cachedCNM.length; ++i) {
            Arrays.fill(cachedCNM[i], 0.0);
            Arrays.fill(cachedSNM[i], 0.0);
        }
        frequencyDependentPart.invoke(tf, date, cachedCNM, cachedSNM);
        double thetaPlusPi = gmstFunction.value(date) + FastMath.PI;
        Assert.assertEquals(470.9e-12 * FastMath.sin(thetaPlusPi) - 30.2e-12 * FastMath.cos(thetaPlusPi), cachedCNM[2][1], 2.0e-25);
        Assert.assertEquals(470.9e-12 * FastMath.cos(thetaPlusPi) + 30.2e-12 * FastMath.sin(thetaPlusPi), cachedSNM[2][1], 2.0e-25);
    }
}

Example 23 with FieldAbsoluteDate

use of org.orekit.time.FieldAbsoluteDate in project Orekit by CS-SI.

the class FieldCartesianOrbitTest method doTestCartesianToCartesian.

private <T extends RealFieldElement<T>> void doTestCartesianToCartesian(Field<T> field) throws NoSuchMethodException, SecurityException, IllegalAccessException, IllegalArgumentException, InvocationTargetException {
    T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field);
    FieldVector3D<T> position = new FieldVector3D<>(zero.add(-29536113.0), zero.add(30329259.0), zero.add(-100125.0));
    FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(-2194.0), zero.add(-2141.0), zero.add(-8.0));
    FieldPVCoordinates<T> FieldPVCoordinates = new FieldPVCoordinates<>(position, velocity);
    double mu = 3.9860047e14;
    FieldCartesianOrbit<T> p = new FieldCartesianOrbit<>(FieldPVCoordinates, FramesFactory.getEME2000(), date, mu);
    Assert.assertEquals(p.getPVCoordinates().getPosition().getX().getReal(), FieldPVCoordinates.getPosition().getX().getReal(), Utils.epsilonTest * FastMath.abs(FieldPVCoordinates.getPosition().getX().getReal()));
    Assert.assertEquals(p.getPVCoordinates().getPosition().getY().getReal(), FieldPVCoordinates.getPosition().getY().getReal(), Utils.epsilonTest * FastMath.abs(FieldPVCoordinates.getPosition().getY().getReal()));
    Assert.assertEquals(p.getPVCoordinates().getPosition().getZ().getReal(), FieldPVCoordinates.getPosition().getZ().getReal(), Utils.epsilonTest * FastMath.abs(FieldPVCoordinates.getPosition().getZ().getReal()));
    Assert.assertEquals(p.getPVCoordinates().getVelocity().getX().getReal(), FieldPVCoordinates.getVelocity().getX().getReal(), Utils.epsilonTest * FastMath.abs(FieldPVCoordinates.getVelocity().getX().getReal()));
    Assert.assertEquals(p.getPVCoordinates().getVelocity().getY().getReal(), FieldPVCoordinates.getVelocity().getY().getReal(), Utils.epsilonTest * FastMath.abs(FieldPVCoordinates.getVelocity().getY().getReal()));
    Assert.assertEquals(p.getPVCoordinates().getVelocity().getZ().getReal(), FieldPVCoordinates.getVelocity().getZ().getReal(), Utils.epsilonTest * FastMath.abs(FieldPVCoordinates.getVelocity().getZ().getReal()));
    Method initPV = FieldCartesianOrbit.class.getDeclaredMethod("initPVCoordinates", new Class[0]);
    initPV.setAccessible(true);
    Assert.assertSame(p.getPVCoordinates(), initPV.invoke(p, new Object[0]));
}

Example 24 with FieldAbsoluteDate

use of org.orekit.time.FieldAbsoluteDate in project Orekit by CS-SI.

the class FieldCircularOrbitTest method doTestNonKeplerianDerivatives.

private <T extends RealFieldElement<T>> void doTestNonKeplerianDerivatives(Field<T> field) throws OrekitException {
    final FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, "2003-05-01T00:00:20.000", TimeScalesFactory.getUTC());
    final FieldVector3D<T> position = new FieldVector3D<>(field.getZero().add(6896874.444705), field.getZero().add(1956581.072644), field.getZero().add(-147476.245054));
    final FieldVector3D<T> velocity = new FieldVector3D<>(field.getZero().add(166.816407662), field.getZero().add(-1106.783301861), field.getZero().add(-7372.745712770));
    final FieldVector3D<T> acceleration = new FieldVector3D<>(field.getZero().add(-7.466182457944), field.getZero().add(-2.118153357345), field.getZero().add(0.160004048437));
    final TimeStampedFieldPVCoordinates<T> pv = new TimeStampedFieldPVCoordinates<>(date, position, velocity, acceleration);
    final Frame frame = FramesFactory.getEME2000();
    final double mu = Constants.EIGEN5C_EARTH_MU;
    final FieldCircularOrbit<T> orbit = new FieldCircularOrbit<>(pv, frame, mu);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getA()), orbit.getADot().getReal(), 4.3e-8);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getEquinoctialEx()), orbit.getEquinoctialExDot().getReal(), 2.1e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getEquinoctialEy()), orbit.getEquinoctialEyDot().getReal(), 5.4e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getHx()), orbit.getHxDot().getReal(), 1.6e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getHy()), orbit.getHyDot().getReal(), 7.3e-17);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getLv()), orbit.getLvDot().getReal(), 3.4e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getLE()), orbit.getLEDot().getReal(), 3.5e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getLM()), orbit.getLMDot().getReal(), 5.3e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getE()), orbit.getEDot().getReal(), 6.8e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getI()), orbit.getIDot().getReal(), 5.7e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getCircularEx()), orbit.getCircularExDot().getReal(), 2.2e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getCircularEy()), orbit.getCircularEyDot().getReal(), 5.3e-17);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAlphaV()), orbit.getAlphaVDot().getReal(), 4.3e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAlphaE()), orbit.getAlphaEDot().getReal(), 1.2e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAlphaM()), orbit.getAlphaMDot().getReal(), 3.7e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAlpha(PositionAngle.TRUE)), orbit.getAlphaDot(PositionAngle.TRUE).getReal(), 4.3e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAlpha(PositionAngle.ECCENTRIC)), orbit.getAlphaDot(PositionAngle.ECCENTRIC).getReal(), 1.2e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAlpha(PositionAngle.MEAN)), orbit.getAlphaDot(PositionAngle.MEAN).getReal(), 3.7e-15);
}

Example 25 with FieldAbsoluteDate

use of org.orekit.time.FieldAbsoluteDate in project Orekit by CS-SI.

the class FieldCircularOrbitTest method doTestNonInertialFrame.

private <T extends RealFieldElement<T>> void doTestNonInertialFrame(Field<T> field) throws IllegalArgumentException {
    T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field);
    FieldVector3D<T> position = new FieldVector3D<>(zero.add(33051.2), zero.add(26184.9), zero.add(-1.3E-5));
    FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(-60376.2), zero.add(76208.), zero.add(2.7E-4));
    FieldPVCoordinates<T> pvCoordinates = new FieldPVCoordinates<>(position, velocity);
    new FieldCircularOrbit<>(pvCoordinates, new Frame(FramesFactory.getEME2000(), Transform.IDENTITY, "non-inertial", false), date, mu);
}