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

Example 41 with DerivativeStructure

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

the class CircularOrbit method getAlphaEDot.

/**
 * Get the eccentric latitude argument derivative.
 * <p>
 * If the orbit was created without derivatives, the value returned is {@link Double#NaN}.
 * </p>
 * @return d(E + ω)/dt eccentric latitude argument derivative (rad/s)
 * @since 9.0
 */
public double getAlphaEDot() {
    final DerivativeStructure alphaVDS = FACTORY.build(alphaV, alphaVDot);
    final DerivativeStructure exDS = FACTORY.build(ex, exDot);
    final DerivativeStructure eyDS = FACTORY.build(ey, eyDot);
    final DerivativeStructure alphaEDS = FieldCircularOrbit.trueToEccentric(alphaVDS, exDS, eyDS);
    return alphaEDS.getPartialDerivative(1);
}

Example 42 with DerivativeStructure

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

the class CircularOrbit method getAlphaMDot.

/**
 * Get the mean latitude argument derivative.
 * <p>
 * If the orbit was created without derivatives, the value returned is {@link Double#NaN}.
 * </p>
 * @return d(M + ω)/dt mean latitude argument derivative (rad/s)
 * @since 9.0
 */
public double getAlphaMDot() {
    final DerivativeStructure alphaVDS = FACTORY.build(alphaV, alphaVDot);
    final DerivativeStructure exDS = FACTORY.build(ex, exDot);
    final DerivativeStructure eyDS = FACTORY.build(ey, eyDot);
    final DerivativeStructure alphaMDS = FieldCircularOrbit.eccentricToMean(FieldCircularOrbit.trueToEccentric(alphaVDS, exDS, eyDS), exDS, eyDS);
    return alphaMDS.getPartialDerivative(1);
}

Example 43 with DerivativeStructure

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

the class IsotropicRadiationCNES95Convention method radiationPressureAcceleration.

/**
 * {@inheritDoc}
 */
@Override
public FieldVector3D<DerivativeStructure> radiationPressureAcceleration(final AbsoluteDate date, final Frame frame, final Vector3D position, final Rotation rotation, final double mass, final Vector3D flux, final double[] parameters, final String paramName) throws OrekitException {
    final DerivativeStructure absorptionCoeffDS;
    final DerivativeStructure specularReflectionCoeffDS;
    if (ABSORPTION_COEFFICIENT.equals(paramName)) {
        absorptionCoeffDS = factory.variable(0, parameters[0]);
        specularReflectionCoeffDS = factory.constant(parameters[1]);
    } else if (REFLECTION_COEFFICIENT.equals(paramName)) {
        absorptionCoeffDS = factory.constant(parameters[0]);
        specularReflectionCoeffDS = factory.variable(0, parameters[1]);
    } else {
        throw new OrekitException(OrekitMessages.UNSUPPORTED_PARAMETER_NAME, paramName, ABSORPTION_COEFFICIENT + ", " + REFLECTION_COEFFICIENT);
    }
    final DerivativeStructure kP = absorptionCoeffDS.subtract(1).multiply(specularReflectionCoeffDS.subtract(1)).multiply(4.0 / 9.0).add(1).multiply(crossSection);
    return new FieldVector3D<>(kP.divide(mass), flux);
}

Example 44 with DerivativeStructure

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

the class DSSTTesseral method computeNSum.

/**
 * Compute the n-SUM for potential derivatives components.
 *  @param date current date
 *  @param j resonant index <i>j</i>
 *  @param m resonant order <i>m</i>
 *  @param s d'Alembert characteristic <i>s</i>
 *  @param maxN maximum possible value for <i>n</i> index
 *  @param roaPow powers of R/a up to degree <i>n</i>
 *  @param ghMSJ G<sup>j</sup><sub>m,s</sub> and H<sup>j</sup><sub>m,s</sub> polynomials
 *  @param gammaMNS &Gamma;<sup>m</sup><sub>n,s</sub>(γ) function
 *  @return Components of U<sub>n</sub> derivatives for fixed j, m, s
 * @throws OrekitException if some error occurred
 */
private double[][] computeNSum(final AbsoluteDate date, final int j, final int m, final int s, final int maxN, final double[] roaPow, final GHmsjPolynomials ghMSJ, final GammaMnsFunction gammaMNS) throws OrekitException {
    // spherical harmonics
    final UnnormalizedSphericalHarmonics harmonics = provider.onDate(date);
    // Potential derivatives components
    double dUdaCos = 0.;
    double dUdaSin = 0.;
    double dUdhCos = 0.;
    double dUdhSin = 0.;
    double dUdkCos = 0.;
    double dUdkSin = 0.;
    double dUdlCos = 0.;
    double dUdlSin = 0.;
    double dUdAlCos = 0.;
    double dUdAlSin = 0.;
    double dUdBeCos = 0.;
    double dUdBeSin = 0.;
    double dUdGaCos = 0.;
    double dUdGaSin = 0.;
    // I^m
    @SuppressWarnings("unused") final int Im = I > 0 ? 1 : (m % 2 == 0 ? 1 : -1);
    // jacobi v, w, indices from 2.7.1-(15)
    final int v = FastMath.abs(m - s);
    final int w = FastMath.abs(m + s);
    // Initialise lower degree nmin = (Max(2, m, |s|)) for summation over n
    final int nmin = FastMath.max(FastMath.max(2, m), FastMath.abs(s));
    // Get the corresponding Hansen object
    final int sIndex = maxDegree + (j < 0 ? -s : s);
    final int jIndex = FastMath.abs(j);
    final HansenTesseralLinear hans = this.hansenObjects[sIndex][jIndex];
    // n-SUM from nmin to N
    for (int n = nmin; n <= maxN; n++) {
        // If (n - s) is odd, the contribution is null because of Vmns
        if ((n - s) % 2 == 0) {
            // Vmns coefficient
            final double vMNS = CoefficientsFactory.getVmns(m, n, s);
            // Inclination function Gamma and derivative
            final double gaMNS = gammaMNS.getValue(m, n, s);
            final double dGaMNS = gammaMNS.getDerivative(m, n, s);
            // Hansen kernel value and derivative
            final double kJNS = hans.getValue(-n - 1, chi);
            final double dkJNS = hans.getDerivative(-n - 1, chi);
            // Gjms, Hjms polynomials and derivatives
            final double gMSJ = ghMSJ.getGmsj(m, s, j);
            final double hMSJ = ghMSJ.getHmsj(m, s, j);
            final double dGdh = ghMSJ.getdGmsdh(m, s, j);
            final double dGdk = ghMSJ.getdGmsdk(m, s, j);
            final double dGdA = ghMSJ.getdGmsdAlpha(m, s, j);
            final double dGdB = ghMSJ.getdGmsdBeta(m, s, j);
            final double dHdh = ghMSJ.getdHmsdh(m, s, j);
            final double dHdk = ghMSJ.getdHmsdk(m, s, j);
            final double dHdA = ghMSJ.getdHmsdAlpha(m, s, j);
            final double dHdB = ghMSJ.getdHmsdBeta(m, s, j);
            // Jacobi l-index from 2.7.1-(15)
            final int l = FastMath.min(n - m, n - FastMath.abs(s));
            // Jacobi polynomial and derivative
            final DerivativeStructure jacobi = JacobiPolynomials.getValue(l, v, w, factory.variable(0, gamma));
            // Geopotential coefficients
            final double cnm = harmonics.getUnnormalizedCnm(n, m);
            final double snm = harmonics.getUnnormalizedSnm(n, m);
            // Common factors from expansion of equations 3.3-4
            final double cf_0 = roaPow[n] * Im * vMNS;
            final double cf_1 = cf_0 * gaMNS * jacobi.getValue();
            final double cf_2 = cf_1 * kJNS;
            final double gcPhs = gMSJ * cnm + hMSJ * snm;
            final double gsMhc = gMSJ * snm - hMSJ * cnm;
            final double dKgcPhsx2 = 2. * dkJNS * gcPhs;
            final double dKgsMhcx2 = 2. * dkJNS * gsMhc;
            final double dUdaCoef = (n + 1) * cf_2;
            final double dUdlCoef = j * cf_2;
            final double dUdGaCoef = cf_0 * kJNS * (jacobi.getValue() * dGaMNS + gaMNS * jacobi.getPartialDerivative(1));
            // dU / da components
            dUdaCos += dUdaCoef * gcPhs;
            dUdaSin += dUdaCoef * gsMhc;
            // dU / dh components
            dUdhCos += cf_1 * (kJNS * (cnm * dGdh + snm * dHdh) + h * dKgcPhsx2);
            dUdhSin += cf_1 * (kJNS * (snm * dGdh - cnm * dHdh) + h * dKgsMhcx2);
            // dU / dk components
            dUdkCos += cf_1 * (kJNS * (cnm * dGdk + snm * dHdk) + k * dKgcPhsx2);
            dUdkSin += cf_1 * (kJNS * (snm * dGdk - cnm * dHdk) + k * dKgsMhcx2);
            // dU / dLambda components
            dUdlCos += dUdlCoef * gsMhc;
            dUdlSin += -dUdlCoef * gcPhs;
            // dU / alpha components
            dUdAlCos += cf_2 * (dGdA * cnm + dHdA * snm);
            dUdAlSin += cf_2 * (dGdA * snm - dHdA * cnm);
            // dU / dBeta components
            dUdBeCos += cf_2 * (dGdB * cnm + dHdB * snm);
            dUdBeSin += cf_2 * (dGdB * snm - dHdB * cnm);
            // dU / dGamma components
            dUdGaCos += dUdGaCoef * gcPhs;
            dUdGaSin += dUdGaCoef * gsMhc;
        }
    }
    return new double[][] { { dUdaCos, dUdaSin }, { dUdhCos, dUdhSin }, { dUdkCos, dUdkSin }, { dUdlCos, dUdlSin }, { dUdAlCos, dUdAlSin }, { dUdBeCos, dUdBeSin }, { dUdGaCos, dUdGaSin } };
}

Example 45 with DerivativeStructure

use of org.hipparchus.analysis.differentiation.DerivativeStructure 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);
}