Examples with DerivativeStructure org.hipparchus.analysis.differentiation.DerivativeStructure used on opensource projects

Example 6 with DerivativeStructure

use of org.hipparchus.analysis.differentiation.DerivativeStructure in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method RealFieldTest.

/**
 *Testing if the propagation between the FieldPropagation and the propagation
 * is equivalent.
 * Also testing if propagating X+dX with the propagation is equivalent to
 * propagation X with the FieldPropagation and then applying the taylor
 * expansion of dX to the result.
 */
@Test
public void RealFieldTest() throws OrekitException {
    DSFactory factory = new DSFactory(6, 4);
    DerivativeStructure a_0 = factory.variable(0, 7201009.7124401);
    DerivativeStructure e_0 = factory.variable(1, 1e-3);
    DerivativeStructure i_0 = factory.variable(2, 98.7 * FastMath.PI / 180);
    DerivativeStructure R_0 = factory.variable(3, 15.0 * 22.5 * FastMath.PI / 180);
    DerivativeStructure O_0 = factory.variable(4, 93.0 * FastMath.PI / 180);
    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.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(10.0, 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);
    double[][] c = new double[3][1];
    c[0][0] = 0.0;
    c[2][0] = normalizedC20;
    double[][] s = new double[3][1];
    NormalizedSphericalHarmonicsProvider provider = GravityFieldFactory.getNormalizedProvider(6378136.460, mu, TideSystem.UNKNOWN, c, s);
    HolmesFeatherstoneAttractionModel forceModel = new HolmesFeatherstoneAttractionModel(itrf, provider);
    FNP.addForceModel(forceModel);
    NP.addForceModel(forceModel);
    FieldAbsoluteDate<DerivativeStructure> target = J2000.shiftedBy(1005.);
    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(finPVC_DS.toPVCoordinates().getPosition().getX(), finPVC_R.getPosition().getX(), FastMath.abs(finPVC_R.getPosition().getX()) * 1e-11);
    Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getY(), finPVC_R.getPosition().getY(), FastMath.abs(finPVC_R.getPosition().getY()) * 1e-11);
    Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getZ(), finPVC_R.getPosition().getZ(), FastMath.abs(finPVC_R.getPosition().getZ()) * 1e-11);
    long number = 23091991;
    RandomGenerator RG = new Well19937a(number);
    GaussianRandomGenerator NGG = new GaussianRandomGenerator(RG);
    UncorrelatedRandomVectorGenerator URVG = new UncorrelatedRandomVectorGenerator(new double[] { 0.0, 0.0, 0.0, 0.0, 0.0, 0.0 }, new double[] { 1e1, 0.001, 0.001, 0.001, 0.001, 0.001 }, NGG);
    double a_R = a_0.getReal();
    double e_R = e_0.getReal();
    double i_R = i_0.getReal();
    double R_R = R_0.getReal();
    double O_R = O_0.getReal();
    double n_R = n_0.getReal();
    for (int ii = 0; ii < 1; ii++) {
        double[] rand_next = URVG.nextVector();
        double a_shift = a_R + rand_next[0];
        double e_shift = e_R + rand_next[1];
        double i_shift = i_R + rand_next[2];
        double R_shift = R_R + rand_next[3];
        double O_shift = O_R + rand_next[4];
        double n_shift = n_R + rand_next[5];
        KeplerianOrbit shiftedOrb = new KeplerianOrbit(a_shift, e_shift, i_shift, R_shift, O_shift, n_shift, PositionAngle.MEAN, EME, J2000.toAbsoluteDate(), Constants.EIGEN5C_EARTH_MU);
        SpacecraftState shift_iSR = new SpacecraftState(shiftedOrb);
        NumericalPropagator shift_NP = new NumericalPropagator(RIntegrator);
        shift_NP.setOrbitType(type);
        shift_NP.setInitialState(shift_iSR);
        shift_NP.addForceModel(forceModel);
        SpacecraftState finalState_shift = shift_NP.propagate(target.toAbsoluteDate());
        PVCoordinates finPVC_shift = finalState_shift.getPVCoordinates();
        // position check
        FieldVector3D<DerivativeStructure> pos_DS = finPVC_DS.getPosition();
        double x_DS = pos_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double y_DS = pos_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double z_DS = pos_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double x = finPVC_shift.getPosition().getX();
        double y = finPVC_shift.getPosition().getY();
        double z = finPVC_shift.getPosition().getZ();
        Assert.assertEquals(x_DS, x, FastMath.abs(x - pos_DS.getX().getReal()) * 1e-8);
        Assert.assertEquals(y_DS, y, FastMath.abs(y - pos_DS.getY().getReal()) * 1e-8);
        Assert.assertEquals(z_DS, z, FastMath.abs(z - pos_DS.getZ().getReal()) * 1e-8);
        // velocity check
        FieldVector3D<DerivativeStructure> vel_DS = finPVC_DS.getVelocity();
        double vx_DS = vel_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double vy_DS = vel_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double vz_DS = vel_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double vx = finPVC_shift.getVelocity().getX();
        double vy = finPVC_shift.getVelocity().getY();
        double vz = finPVC_shift.getVelocity().getZ();
        Assert.assertEquals(vx_DS, vx, FastMath.abs(vx) * 1e-9);
        Assert.assertEquals(vy_DS, vy, FastMath.abs(vy) * 1e-9);
        Assert.assertEquals(vz_DS, vz, FastMath.abs(vz) * 1e-9);
        // acceleration check
        FieldVector3D<DerivativeStructure> acc_DS = finPVC_DS.getAcceleration();
        double ax_DS = acc_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double ay_DS = acc_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double az_DS = acc_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double ax = finPVC_shift.getAcceleration().getX();
        double ay = finPVC_shift.getAcceleration().getY();
        double az = finPVC_shift.getAcceleration().getZ();
        Assert.assertEquals(ax_DS, ax, FastMath.abs(ax) * 1e-9);
        Assert.assertEquals(ay_DS, ay, FastMath.abs(ay) * 1e-9);
        Assert.assertEquals(az_DS, az, FastMath.abs(az) * 1e-9);
    }
}

Example 7 with DerivativeStructure

use of org.hipparchus.analysis.differentiation.DerivativeStructure 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 8 with DerivativeStructure

use of org.hipparchus.analysis.differentiation.DerivativeStructure in project Orekit by CS-SI.

the class AbstractLegacyForceModelTest method checkStateJacobianVs80Implementation.

protected void checkStateJacobianVs80Implementation(final SpacecraftState state, final ForceModel forceModel, final AttitudeProvider attitudeProvider, final double checkTolerance, final boolean print) throws OrekitException {
    FieldSpacecraftState<DerivativeStructure> fState = toDS(state, attitudeProvider);
    FieldVector3D<DerivativeStructure> dsNew = forceModel.acceleration(fState, forceModel.getParameters(fState.getDate().getField()));
    FieldVector3D<DerivativeStructure> dsOld = accelerationDerivatives(forceModel, fState.getDate().toAbsoluteDate(), fState.getFrame(), fState.getPVCoordinates().getPosition(), fState.getPVCoordinates().getVelocity(), fState.getAttitude().getRotation(), fState.getMass());
    Vector3D dFdPXRef = new Vector3D(dsOld.getX().getPartialDerivative(1, 0, 0, 0, 0, 0), dsOld.getY().getPartialDerivative(1, 0, 0, 0, 0, 0), dsOld.getZ().getPartialDerivative(1, 0, 0, 0, 0, 0));
    Vector3D dFdPXRes = new Vector3D(dsNew.getX().getPartialDerivative(1, 0, 0, 0, 0, 0), dsNew.getY().getPartialDerivative(1, 0, 0, 0, 0, 0), dsNew.getZ().getPartialDerivative(1, 0, 0, 0, 0, 0));
    Vector3D dFdPYRef = new Vector3D(dsOld.getX().getPartialDerivative(0, 1, 0, 0, 0, 0), dsOld.getY().getPartialDerivative(0, 1, 0, 0, 0, 0), dsOld.getZ().getPartialDerivative(0, 1, 0, 0, 0, 0));
    Vector3D dFdPYRes = new Vector3D(dsNew.getX().getPartialDerivative(0, 1, 0, 0, 0, 0), dsNew.getY().getPartialDerivative(0, 1, 0, 0, 0, 0), dsNew.getZ().getPartialDerivative(0, 1, 0, 0, 0, 0));
    Vector3D dFdPZRef = new Vector3D(dsOld.getX().getPartialDerivative(0, 0, 1, 0, 0, 0), dsOld.getY().getPartialDerivative(0, 0, 1, 0, 0, 0), dsOld.getZ().getPartialDerivative(0, 0, 1, 0, 0, 0));
    Vector3D dFdPZRes = new Vector3D(dsNew.getX().getPartialDerivative(0, 0, 1, 0, 0, 0), dsNew.getY().getPartialDerivative(0, 0, 1, 0, 0, 0), dsNew.getZ().getPartialDerivative(0, 0, 1, 0, 0, 0));
    Vector3D dFdVXRef = new Vector3D(dsOld.getX().getPartialDerivative(0, 0, 0, 1, 0, 0), dsOld.getY().getPartialDerivative(0, 0, 0, 1, 0, 0), dsOld.getZ().getPartialDerivative(0, 0, 0, 1, 0, 0));
    Vector3D dFdVXRes = new Vector3D(dsNew.getX().getPartialDerivative(0, 0, 0, 1, 0, 0), dsNew.getY().getPartialDerivative(0, 0, 0, 1, 0, 0), dsNew.getZ().getPartialDerivative(0, 0, 0, 1, 0, 0));
    Vector3D dFdVYRef = new Vector3D(dsOld.getX().getPartialDerivative(0, 0, 0, 0, 1, 0), dsOld.getY().getPartialDerivative(0, 0, 0, 0, 1, 0), dsOld.getZ().getPartialDerivative(0, 0, 0, 0, 1, 0));
    Vector3D dFdVYRes = new Vector3D(dsNew.getX().getPartialDerivative(0, 0, 0, 0, 1, 0), dsNew.getY().getPartialDerivative(0, 0, 0, 0, 1, 0), dsNew.getZ().getPartialDerivative(0, 0, 0, 0, 1, 0));
    Vector3D dFdVZRef = new Vector3D(dsOld.getX().getPartialDerivative(0, 0, 0, 0, 0, 1), dsOld.getY().getPartialDerivative(0, 0, 0, 0, 0, 1), dsOld.getZ().getPartialDerivative(0, 0, 0, 0, 0, 1));
    Vector3D dFdVZRes = new Vector3D(dsNew.getX().getPartialDerivative(0, 0, 0, 0, 0, 1), dsNew.getY().getPartialDerivative(0, 0, 0, 0, 0, 1), dsNew.getZ().getPartialDerivative(0, 0, 0, 0, 0, 1));
    if (print) {
        System.out.println("dF/dPX ref norm: " + dFdPXRef.getNorm() + ", abs error: " + Vector3D.distance(dFdPXRef, dFdPXRes) + ", rel error: " + (Vector3D.distance(dFdPXRef, dFdPXRes) / dFdPXRef.getNorm()));
        System.out.println("dF/dPY ref norm: " + dFdPYRef.getNorm() + ", abs error: " + Vector3D.distance(dFdPYRef, dFdPYRes) + ", rel error: " + (Vector3D.distance(dFdPYRef, dFdPYRes) / dFdPYRef.getNorm()));
        System.out.println("dF/dPZ ref norm: " + dFdPZRef.getNorm() + ", abs error: " + Vector3D.distance(dFdPZRef, dFdPZRes) + ", rel error: " + (Vector3D.distance(dFdPZRef, dFdPZRes) / dFdPZRef.getNorm()));
        System.out.println("dF/dVX ref norm: " + dFdVXRef.getNorm() + ", abs error: " + Vector3D.distance(dFdVXRef, dFdVXRes) + ", rel error: " + (Vector3D.distance(dFdVXRef, dFdVXRes) / dFdVXRef.getNorm()));
        System.out.println("dF/dVY ref norm: " + dFdVYRef.getNorm() + ", abs error: " + Vector3D.distance(dFdVYRef, dFdVYRes) + ", rel error: " + (Vector3D.distance(dFdVYRef, dFdVYRes) / dFdVYRef.getNorm()));
        System.out.println("dF/dVZ ref norm: " + dFdVZRef.getNorm() + ", abs error: " + Vector3D.distance(dFdVZRef, dFdVZRes) + ", rel error: " + (Vector3D.distance(dFdVZRef, dFdVZRes) / dFdVZRef.getNorm()));
    }
    checkdFdP(dFdPXRef, dFdPXRes, checkTolerance);
    checkdFdP(dFdPYRef, dFdPYRes, checkTolerance);
    checkdFdP(dFdPZRef, dFdPZRes, checkTolerance);
    checkdFdP(dFdVXRef, dFdVXRes, checkTolerance);
    checkdFdP(dFdVYRef, dFdVYRes, checkTolerance);
    checkdFdP(dFdVZRef, dFdVZRes, checkTolerance);
}

Example 9 with DerivativeStructure

use of org.hipparchus.analysis.differentiation.DerivativeStructure in project Orekit by CS-SI.

the class BoxAndSolarArraySpacecraftTest method testBackwardIllumination.

@Test
public void testBackwardIllumination() throws OrekitException {
    SpacecraftState state = propagator.getInitialState();
    CelestialBody sun = CelestialBodyFactory.getSun();
    BoxAndSolarArraySpacecraft s = new BoxAndSolarArraySpacecraft(0, 0, 0, sun, 20.0, Vector3D.PLUS_J, 0.0, 1.0, 0.0);
    Vector3D n = s.getNormal(state.getDate(), state.getFrame(), state.getPVCoordinates().getPosition(), state.getAttitude().getRotation());
    FieldVector3D<DerivativeStructure> aPlus = s.radiationPressureAcceleration(state.getDate(), state.getFrame(), state.getPVCoordinates().getPosition(), state.getAttitude().getRotation(), state.getMass(), n, getRadiationParameters(s), RadiationSensitive.ABSORPTION_COEFFICIENT);
    FieldVector3D<DerivativeStructure> aMinus = s.radiationPressureAcceleration(state.getDate(), state.getFrame(), state.getPVCoordinates().getPosition(), state.getAttitude().getRotation(), state.getMass(), n.negate(), getRadiationParameters(s), RadiationSensitive.ABSORPTION_COEFFICIENT);
    Assert.assertEquals(0.0, aPlus.add(aMinus).getNorm().getReal(), Double.MIN_VALUE);
}

Example 10 with DerivativeStructure

use of org.hipparchus.analysis.differentiation.DerivativeStructure in project Orekit by CS-SI.

the class PoissonSeriesParserTest method testDerivativesFromDoubleAPI.

@Test
public void testDerivativesFromDoubleAPI() throws OrekitException {
    Utils.setDataRoot("regular-data");
    String directory = "/assets/org/orekit/IERS-conventions/";
    PoissonSeriesParser parser = new PoissonSeriesParser(17).withPolynomialPart('t', PolynomialParser.Unit.NO_UNITS).withFirstDelaunay(4).withFirstPlanetary(9).withSinCos(0, 2, 1.0, 3, 1.0);
    InputStream xStream = getClass().getResourceAsStream(directory + "2010/tab5.2a.txt");
    PoissonSeries xSeries = parser.parse(xStream, "2010/tab5.2a.txt");
    InputStream yStream = getClass().getResourceAsStream(directory + "2010/tab5.2b.txt");
    PoissonSeries ySeries = parser.parse(yStream, "2010/tab5.2b.txt");
    InputStream zStream = getClass().getResourceAsStream(directory + "2010/tab5.2d.txt");
    PoissonSeries zSeries = parser.parse(zStream, "2010/tab5.2d.txt");
    final PoissonSeries.CompiledSeries compiled = PoissonSeries.compile(xSeries, ySeries, zSeries);
    TimeScale ut1 = TimeScalesFactory.getUT1(FramesFactory.getEOPHistory(IERSConventions.IERS_2010, true));
    final FundamentalNutationArguments arguments = IERSConventions.IERS_2010.getNutationArguments(ut1);
    UnivariateDifferentiableVectorFunction finite = new FiniteDifferencesDifferentiator(4, 0.4).differentiate((double t) -> compiled.value(arguments.evaluateAll(AbsoluteDate.J2000_EPOCH.shiftedBy(t))));
    DSFactory factory = new DSFactory(1, 1);
    for (double t = 0; t < Constants.JULIAN_DAY; t += 120) {
        // computation of derivatives from API
        double[] dAPI = compiled.derivative(arguments.evaluateAll(AbsoluteDate.J2000_EPOCH.shiftedBy(t)));
        // finite differences computation of derivatives
        DerivativeStructure[] d = finite.value(factory.variable(0, t));
        Assert.assertEquals(d.length, dAPI.length);
        for (int i = 0; i < d.length; ++i) {
            Assert.assertEquals(d[i].getPartialDerivative(1), dAPI[i], FastMath.abs(2.0e-7 * d[i].getPartialDerivative(1)));
        }
    }
}