/* Copyright 2002-2025 CS GROUP
    * Licensed to CS GROUP (CS) under one or more
    * contributor license agreements.  See the NOTICE file distributed with
    * this work for additional information regarding copyright ownership.
    * CS licenses this file to You under the Apache License, Version 2.0
    * (the "License"); you may not use this file except in compliance with
    * the License.  You may obtain a copy of the License at
    *
    *   http://www.apache.org/licenses/LICENSE-2.0
   *
   * Unless required by applicable law or agreed to in writing, software
   * distributed under the License is distributed on an "AS IS" BASIS,
   * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
   * See the License for the specific language governing permissions and
   * limitations under the License.
   */
  package org.orekit.orbits;
  
  
  
  import org.hipparchus.CalculusFieldElement;
  import org.hipparchus.Field;
  import org.hipparchus.analysis.differentiation.Derivative;
  import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
  import org.hipparchus.linear.FieldDecompositionSolver;
  import org.hipparchus.linear.FieldLUDecomposition;
  import org.hipparchus.linear.FieldMatrix;
  import org.hipparchus.linear.MatrixUtils;
  import org.hipparchus.util.MathArrays;
  import org.orekit.errors.OrekitIllegalArgumentException;
  import org.orekit.errors.OrekitInternalError;
  import org.orekit.errors.OrekitMessages;
  import org.orekit.frames.FieldStaticTransform;
  import org.orekit.frames.FieldTransform;
  import org.orekit.frames.Frame;
  import org.orekit.time.FieldAbsoluteDate;
  import org.orekit.time.FieldTimeShiftable;
  import org.orekit.time.FieldTimeStamped;
  import org.orekit.utils.FieldPVCoordinates;
  import org.orekit.utils.FieldPVCoordinatesProvider;
  import org.orekit.utils.TimeStampedFieldPVCoordinates;
  import org.orekit.utils.TimeStampedPVCoordinates;
  
  /**
   * This class handles orbital parameters.
  
   * <p>
   * For user convenience, both the Cartesian and the equinoctial elements
   * are provided by this class, regardless of the canonical representation
   * implemented in the derived class (which may be classical Keplerian
   * elements for example).
   * </p>
   * <p>
   * The parameters are defined in a frame specified by the user. It is important
   * to make sure this frame is consistent: it probably is inertial and centered
   * on the central body. This information is used for example by some
   * force models.
   * </p>
   * <p>
   * Instance of this class are guaranteed to be immutable.
   * </p>
   * @author Luc Maisonobe
   * @author Guylaine Prat
   * @author Fabien Maussion
   * @author V&eacute;ronique Pommier-Maurussane
   * @since 9.0
   * @see Orbit
   * @param <T> type of the field elements
   */
  public abstract class FieldOrbit<T extends CalculusFieldElement<T>>
      implements FieldPVCoordinatesProvider<T>, FieldTimeStamped<T>, FieldTimeShiftable<FieldOrbit<T>, T> {
  
      /** Absolute tolerance when checking if the rate of the position angle is Keplerian or not. */
      protected static final double TOLERANCE_POSITION_ANGLE_RATE = 1e-15;
  
      /** Frame in which are defined the orbital parameters. */
      private final Frame frame;
  
      /** Date of the orbital parameters. */
      private final FieldAbsoluteDate<T> date;
  
      /** Value of mu used to compute position and velocity (m³/s²). */
      private final T mu;
  
      /** Field-valued one.
       * @since 12.0
       * */
      private final T one;
  
      /** Field-valued zero.
       * @since 12.0
       * */
      private final T zero;
  
      /** Field used by this class.
       * @since 12.0
       */
      private final Field<T> field;
  
     /** Computed position.
      * @since 12.0
      */
     private FieldVector3D<T> position;
 
     /** Computed PVCoordinates. */
     private TimeStampedFieldPVCoordinates<T> pvCoordinates;
 
     /** Jacobian of the orbital parameters with mean angle with respect to the Cartesian coordinates. */
     private T[][] jacobianMeanWrtCartesian;
 
     /** Jacobian of the Cartesian coordinates with respect to the orbital parameters with mean angle. */
     private T[][] jacobianWrtParametersMean;
 
     /** Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian coordinates. */
     private T[][] jacobianEccentricWrtCartesian;
 
     /** Jacobian of the Cartesian coordinates with respect to the orbital parameters with eccentric angle. */
     private T[][] jacobianWrtParametersEccentric;
 
     /** Jacobian of the orbital parameters with true angle with respect to the Cartesian coordinates. */
     private T[][] jacobianTrueWrtCartesian;
 
     /** Jacobian of the Cartesian coordinates with respect to the orbital parameters with true angle. */
     private T[][] jacobianWrtParametersTrue;
 
     /** Default constructor.
      * Build a new instance with arbitrary default elements.
      * @param frame the frame in which the parameters are defined
      * (<em>must</em> be a {@link Frame#isPseudoInertial pseudo-inertial frame})
      * @param date date of the orbital parameters
      * @param mu central attraction coefficient (m^3/s^2)
      * @exception IllegalArgumentException if frame is not a {@link
      * Frame#isPseudoInertial pseudo-inertial frame}
      */
     protected FieldOrbit(final Frame frame, final FieldAbsoluteDate<T> date, final T mu)
         throws IllegalArgumentException {
         ensurePseudoInertialFrame(frame);
         this.field = mu.getField();
         this.zero = this.field.getZero();
         this.one = this.field.getOne();
         this.date                      = date;
         this.mu                        = mu;
         this.pvCoordinates             = null;
         this.frame                     = frame;
         jacobianMeanWrtCartesian       = null;
         jacobianWrtParametersMean      = null;
         jacobianEccentricWrtCartesian  = null;
         jacobianWrtParametersEccentric = null;
         jacobianTrueWrtCartesian       = null;
         jacobianWrtParametersTrue      = null;
     }
 
     /** Set the orbit from Cartesian parameters.
      *
      * <p> The acceleration provided in {@code FieldPVCoordinates} is accessible using
      * {@link #getPVCoordinates()} and {@link #getPVCoordinates(Frame)}. All other methods
      * use {@code mu} and the position to compute the acceleration, including
      * {@link #shiftedBy(CalculusFieldElement)} and {@link #getPVCoordinates(FieldAbsoluteDate, Frame)}.
      *
      * @param fieldPVCoordinates the position and velocity in the inertial frame
      * @param frame the frame in which the {@link TimeStampedPVCoordinates} are defined
      * (<em>must</em> be a {@link Frame#isPseudoInertial pseudo-inertial frame})
      * @param mu central attraction coefficient (m^3/s^2)
      * @exception IllegalArgumentException if frame is not a {@link
      * Frame#isPseudoInertial pseudo-inertial frame}
      */
     protected FieldOrbit(final TimeStampedFieldPVCoordinates<T> fieldPVCoordinates, final Frame frame, final T mu)
         throws IllegalArgumentException {
         ensurePseudoInertialFrame(frame);
         this.field = mu.getField();
         this.zero = this.field.getZero();
         this.one = this.field.getOne();
         this.date = fieldPVCoordinates.getDate();
         this.mu = mu;
         if (fieldPVCoordinates.getAcceleration().getNormSq().getReal() == 0.0) {
             // the acceleration was not provided,
             // compute it from Newtonian attraction
             final T r2 = fieldPVCoordinates.getPosition().getNormSq();
             final T r3 = r2.multiply(r2.sqrt());
             this.pvCoordinates = new TimeStampedFieldPVCoordinates<>(fieldPVCoordinates.getDate(),
                                                                      fieldPVCoordinates.getPosition(),
                                                                      fieldPVCoordinates.getVelocity(),
                                                                      new FieldVector3D<>(r3.reciprocal().multiply(mu.negate()), fieldPVCoordinates.getPosition()));
         } else {
             this.pvCoordinates = fieldPVCoordinates;
         }
         this.frame = frame;
     }
 
     /** Check if Cartesian coordinates include non-Keplerian acceleration.
      * @param pva Cartesian coordinates
      * @param mu central attraction coefficient
      * @param <T> type of the field elements
      * @return true if Cartesian coordinates include non-Keplerian acceleration
      */
     protected static <T extends CalculusFieldElement<T>> boolean hasNonKeplerianAcceleration(final FieldPVCoordinates<T> pva, final T mu) {
 
         if (mu.getField().getZero() instanceof Derivative<?>) {
             return Orbit.hasNonKeplerianAcceleration(pva.toPVCoordinates(), mu.getReal()); // for performance
 
         } else {
             final FieldVector3D<T> a = pva.getAcceleration();
             if (a == null) {
                 return false;
             }
 
             final FieldVector3D<T> p = pva.getPosition();
             final T r2 = p.getNormSq();
 
             // Check if acceleration is relatively close to 0 compared to the Keplerian acceleration
             final double tolerance = mu.getReal() * 1e-9;
             final FieldVector3D<T> aTimesR2 = a.scalarMultiply(r2);
             if (aTimesR2.getNorm().getReal() < tolerance) {
                 return false;
             }
 
             if ((aTimesR2.add(p.normalize().scalarMultiply(mu))).getNorm().getReal() > tolerance) {
                 // we have a relevant acceleration, we can compute derivatives
                 return true;
             } else {
                 // the provided acceleration is either too small to be reliable (probably even 0), or NaN
                 return false;
             }
         }
 
     }
 
     /** Returns true if and only if the orbit is elliptical i.e. has a non-negative semi-major axis.
      * @return true if getA() is strictly greater than 0
      * @since 12.0
      */
     public boolean isElliptical() {
         return getA().getReal() > 0.;
     }
 
     /** Get the orbit type.
      * @return orbit type
      */
     public abstract OrbitType getType();
 
     /** Ensure the defining frame is a pseudo-inertial frame.
      * @param frame frame to check
      * @exception IllegalArgumentException if frame is not a {@link
      * Frame#isPseudoInertial pseudo-inertial frame}
      */
     private static void ensurePseudoInertialFrame(final Frame frame)
         throws IllegalArgumentException {
         if (!frame.isPseudoInertial()) {
             throw new OrekitIllegalArgumentException(OrekitMessages.NON_PSEUDO_INERTIAL_FRAME,
                                                      frame.getName());
         }
     }
 
     /** Get the frame in which the orbital parameters are defined.
      * @return frame in which the orbital parameters are defined
      */
     public Frame getFrame() {
         return frame;
     }
 
     /**Transforms the FieldOrbit instance into an Orbit instance.
      * @return Orbit instance with same properties
      */
     public abstract Orbit toOrbit();
 
     /** Get the semi-major axis.
      * <p>Note that the semi-major axis is considered negative for hyperbolic orbits.</p>
      * @return semi-major axis (m)
      */
     public abstract T getA();
 
     /** Get the semi-major axis derivative.
      * <p>Note that the semi-major axis is considered negative for hyperbolic orbits.</p>
      * <p>
      * If the orbit was created without derivatives, the value returned is null.
      * </p>
      * @return semi-major axis  derivative (m/s)
      */
     public abstract T getADot();
 
     /** Get the first component of the equinoctial eccentricity vector.
      * @return first component of the equinoctial eccentricity vector
      */
     public abstract T getEquinoctialEx();
 
     /** Get the first component of the equinoctial eccentricity vector derivative.
      * <p>
      * If the orbit was created without derivatives, the value returned is null.
      * </p>
      * @return first component of the equinoctial eccentricity vector derivative
      */
     public abstract T getEquinoctialExDot();
 
     /** Get the second component of the equinoctial eccentricity vector.
      * @return second component of the equinoctial eccentricity vector
      */
     public abstract T getEquinoctialEy();
 
     /** Get the second component of the equinoctial eccentricity vector derivative.
      * <p>
      * If the orbit was created without derivatives, the value returned is null.
      * </p>
      * @return second component of the equinoctial eccentricity vector derivative
      */
     public abstract T getEquinoctialEyDot();
 
     /** Get the first component of the inclination vector.
      * @return first component of the inclination vector
      */
     public abstract T getHx();
 
     /** Get the first component of the inclination vector derivative.
      * <p>
      * If the orbit was created without derivatives, the value returned is null.
      * </p>
      * @return first component of the inclination vector derivative
      */
     public abstract T getHxDot();
 
     /** Get the second component of the inclination vector.
      * @return second component of the inclination vector
      */
     public abstract T getHy();
 
     /** Get the second component of the inclination vector derivative.
      * @return second component of the inclination vector derivative
      */
     public abstract T getHyDot();
 
     /** Get the eccentric longitude argument.
      * @return E + ω + Ω eccentric longitude argument (rad)
      */
     public abstract T getLE();
 
     /** Get the eccentric longitude argument derivative.
      * <p>
      * If the orbit was created without derivatives, the value returned is null.
      * </p>
      * @return d(E + ω + Ω)/dt eccentric longitude argument derivative (rad/s)
      */
     public abstract T getLEDot();
 
     /** Get the true longitude argument.
      * @return v + ω + Ω true longitude argument (rad)
      */
     public abstract T getLv();
 
     /** Get the true longitude argument derivative.
      * <p>
      * If the orbit was created without derivatives, the value returned is null.
      * </p>
      * @return d(v + ω + Ω)/dt true longitude argument derivative (rad/s)
      */
     public abstract T getLvDot();
 
     /** Get the mean longitude argument.
      * @return M + ω + Ω mean longitude argument (rad)
      */
     public abstract T getLM();
 
     /** Get the mean longitude argument derivative.
      * <p>
      * If the orbit was created without derivatives, the value returned is null.
      * </p>
      * @return d(M + ω + Ω)/dt mean longitude argument derivative (rad/s)
      */
     public abstract T getLMDot();
 
     // Additional orbital elements
 
     /** Get the eccentricity.
      * @return eccentricity
      */
     public abstract T getE();
 
     /** Get the eccentricity derivative.
      * <p>
      * If the orbit was created without derivatives, the value returned is null.
      * </p>
      * @return eccentricity derivative
      */
     public abstract T getEDot();
 
     /** Get the inclination.
      * <p>
      * If the orbit was created without derivatives, the value returned is null.
      * </p>
      * @return inclination (rad)
      */
     public abstract T getI();
 
     /** Get the inclination derivative.
      * @return inclination derivative (rad/s)
      */
     public abstract T getIDot();
 
     /** Check if orbit includes non-Keplerian rates.
      * @return true if orbit includes non-Keplerian derivatives
      * @see #getADot()
      * @see #getEquinoctialExDot()
      * @see #getEquinoctialEyDot()
      * @see #getHxDot()
      * @see #getHyDot()
      * @see #getLEDot()
      * @see #getLvDot()
      * @see #getLMDot()
      * @see #getEDot()
      * @see #getIDot()
      * @since 13.0
      */
     public boolean hasNonKeplerianAcceleration() {
         return hasNonKeplerianAcceleration(getPVCoordinates(), getMu());
     }
 
     /** Get the central attraction coefficient used for position and velocity conversions (m³/s²).
      * @return central attraction coefficient used for position and velocity conversions (m³/s²)
      */
     public T getMu() {
         return mu;
     }
 
     /** Get the Keplerian period.
      * <p>The Keplerian period is computed directly from semi major axis
      * and central acceleration constant.</p>
      * @return Keplerian period in seconds, or positive infinity for hyperbolic orbits
      */
     public T getKeplerianPeriod() {
         final T a = getA();
         return isElliptical() ?
                a.multiply(a.getPi().multiply(2.0)).multiply(a.divide(mu).sqrt()) :
                zero.add(Double.POSITIVE_INFINITY);
     }
 
     /** Get the Keplerian mean motion.
      * <p>The Keplerian mean motion is computed directly from semi major axis
      * and central acceleration constant.</p>
      * @return Keplerian mean motion in radians per second
      */
     public T getKeplerianMeanMotion() {
         final T absA = getA().abs();
         return absA.reciprocal().multiply(mu).sqrt().divide(absA);
     }
 
     /** Get the derivative of the mean anomaly with respect to the semi major axis.
      * @return derivative of the mean anomaly with respect to the semi major axis
      */
     public T getMeanAnomalyDotWrtA() {
         return getKeplerianMeanMotion().divide(getA()).multiply(-1.5);
     }
 
     /** Get the date of orbital parameters.
      * @return date of the orbital parameters
      */
     public FieldAbsoluteDate<T> getDate() {
         return date;
     }
 
     /** Get the {@link TimeStampedPVCoordinates} in a specified frame.
      * @param outputFrame frame in which the position/velocity coordinates shall be computed
      * @return FieldPVCoordinates in the specified output frame
           * @see #getPVCoordinates()
      */
     public TimeStampedFieldPVCoordinates<T> getPVCoordinates(final Frame outputFrame) {
         if (pvCoordinates == null) {
             pvCoordinates = initPVCoordinates();
         }
 
         // If output frame requested is the same as definition frame,
         // PV coordinates are returned directly
         if (outputFrame == frame) {
             return pvCoordinates;
         }
 
         // Else, PV coordinates are transformed to output frame
         final FieldTransform<T> t = frame.getTransformTo(outputFrame, date);
         return t.transformPVCoordinates(pvCoordinates);
     }
 
     /** {@inheritDoc} */
     public TimeStampedFieldPVCoordinates<T> getPVCoordinates(final FieldAbsoluteDate<T> otherDate, final Frame otherFrame) {
         return shiftedBy(otherDate.durationFrom(getDate())).getPVCoordinates(otherFrame);
     }
 
     /** {@inheritDoc} */
     @Override
     public FieldVector3D<T> getPosition(final FieldAbsoluteDate<T> otherDate, final Frame otherFrame) {
         return shiftedBy(otherDate.durationFrom(getDate())).getPosition(otherFrame);
     }
 
     /** Get the position in a specified frame.
      * @param outputFrame frame in which the position coordinates shall be computed
      * @return position in the specified output frame
      * @see #getPosition()
      * @since 12.0
      */
     public FieldVector3D<T> getPosition(final Frame outputFrame) {
         if (position == null) {
             position = initPosition();
         }
 
         // If output frame requested is the same as definition frame,
         // Position vector is returned directly
         if (outputFrame == frame) {
             return position;
         }
 
         // Else, position vector is transformed to output frame
         final FieldStaticTransform<T> t = frame.getStaticTransformTo(outputFrame, date);
         return t.transformPosition(position);
 
     }
 
     /** Get the position in definition frame.
      * @return position in the definition frame
      * @see #getPVCoordinates()
      * @since 12.0
      */
     public FieldVector3D<T> getPosition() {
         if (position == null) {
             position = initPosition();
         }
         return position;
     }
 
     /** Get the {@link TimeStampedPVCoordinates} in definition frame.
      * @return FieldPVCoordinates in the definition frame
      * @see #getPVCoordinates(Frame)
      */
     public TimeStampedFieldPVCoordinates<T> getPVCoordinates() {
         if (pvCoordinates == null) {
             pvCoordinates = initPVCoordinates();
             position      = pvCoordinates.getPosition();
         }
         return pvCoordinates;
     }
 
     /** Getter for Field-valued one.
      * @return one
      * */
     protected T getOne() {
         return one;
     }
 
     /** Getter for Field-valued zero.
      * @return zero
      * */
     protected T getZero() {
         return zero;
     }
 
     /** Getter for Field.
      * @return CalculusField
      * */
     protected Field<T> getField() {
         return field;
     }
 
     /** Compute the position coordinates from the canonical parameters.
      * @return computed position coordinates
      * @since 12.0
      */
     protected abstract FieldVector3D<T> initPosition();
 
     /** Compute the position/velocity coordinates from the canonical parameters.
      * @return computed position/velocity coordinates
      */
     protected abstract TimeStampedFieldPVCoordinates<T> initPVCoordinates();
 
     /**
      * Create a new object representing the same physical orbital state, but attached to a different reference frame.
      * If the new frame is not inertial, an exception will be thrown.
      *
      * @param inertialFrame reference frame of output orbit
      * @return orbit with different frame
      * @since 13.0
      */
     public abstract FieldOrbit<T> inFrame(Frame inertialFrame);
 
     /** Get a time-shifted orbit.
      * <p>
      * The orbit can be slightly shifted to close dates. This shift is based on
      * a simple Keplerian model. It is <em>not</em> intended as a replacement
      * for proper orbit and attitude propagation but should be sufficient for
      * small time shifts or coarse accuracy.
      * </p>
      * @param dt time shift in seconds
      * @return a new orbit, shifted with respect to the instance (which is immutable)
      */
     public abstract FieldOrbit<T> shiftedBy(T dt);
 
     /** Compute the Jacobian of the orbital parameters with respect to the Cartesian parameters.
      * <p>
      * Element {@code jacobian[i][j]} is the derivative of parameter i of the orbit with
      * respect to Cartesian coordinate j. This means each row corresponds to one orbital parameter
      * whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.
      * </p>
      * @param type type of the position angle to use
      * @param jacobian placeholder 6x6 (or larger) matrix to be filled with the Jacobian, if matrix
      * is larger than 6x6, only the 6x6 upper left corner will be modified
      */
     public void getJacobianWrtCartesian(final PositionAngleType type, final T[][] jacobian) {
 
         final T[][] cachedJacobian;
         synchronized (this) {
             switch (type) {
                 case MEAN :
                     if (jacobianMeanWrtCartesian == null) {
                         // first call, we need to compute the Jacobian and cache it
                         jacobianMeanWrtCartesian = computeJacobianMeanWrtCartesian();
                     }
                     cachedJacobian = jacobianMeanWrtCartesian;
                     break;
                 case ECCENTRIC :
                     if (jacobianEccentricWrtCartesian == null) {
                         // first call, we need to compute the Jacobian and cache it
                         jacobianEccentricWrtCartesian = computeJacobianEccentricWrtCartesian();
                     }
                     cachedJacobian = jacobianEccentricWrtCartesian;
                     break;
                 case TRUE :
                     if (jacobianTrueWrtCartesian == null) {
                         // first call, we need to compute the Jacobian and cache it
                         jacobianTrueWrtCartesian = computeJacobianTrueWrtCartesian();
                     }
                     cachedJacobian = jacobianTrueWrtCartesian;
                     break;
                 default :
                     throw new OrekitInternalError(null);
             }
         }
 
         // fill the user provided array
         for (int i = 0; i < cachedJacobian.length; ++i) {
             System.arraycopy(cachedJacobian[i], 0, jacobian[i], 0, cachedJacobian[i].length);
         }
 
     }
 
     /** Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters.
      * <p>
      * Element {@code jacobian[i][j]} is the derivative of Cartesian coordinate i of the orbit with
      * respect to orbital parameter j. This means each row corresponds to one Cartesian coordinate
      * x, y, z, xdot, ydot, zdot whereas columns 0 to 5 correspond to the orbital parameters.
      * </p>
      * @param type type of the position angle to use
      * @param jacobian placeholder 6x6 (or larger) matrix to be filled with the Jacobian, if matrix
      * is larger than 6x6, only the 6x6 upper left corner will be modified
      */
     public void getJacobianWrtParameters(final PositionAngleType type, final T[][] jacobian) {
 
         final T[][] cachedJacobian;
         synchronized (this) {
             switch (type) {
                 case MEAN :
                     if (jacobianWrtParametersMean == null) {
                         // first call, we need to compute the Jacobian and cache it
                         jacobianWrtParametersMean = createInverseJacobian(type);
                     }
                     cachedJacobian = jacobianWrtParametersMean;
                     break;
                 case ECCENTRIC :
                     if (jacobianWrtParametersEccentric == null) {
                         // first call, we need to compute the Jacobian and cache it
                         jacobianWrtParametersEccentric = createInverseJacobian(type);
                     }
                     cachedJacobian = jacobianWrtParametersEccentric;
                     break;
                 case TRUE :
                     if (jacobianWrtParametersTrue == null) {
                         // first call, we need to compute the Jacobian and cache it
                         jacobianWrtParametersTrue = createInverseJacobian(type);
                     }
                     cachedJacobian = jacobianWrtParametersTrue;
                     break;
                 default :
                     throw new OrekitInternalError(null);
             }
         }
 
         // fill the user-provided array
         for (int i = 0; i < cachedJacobian.length; ++i) {
             System.arraycopy(cachedJacobian[i], 0, jacobian[i], 0, cachedJacobian[i].length);
         }
 
     }
 
     /** Create an inverse Jacobian.
      * @param type type of the position angle to use
      * @return inverse Jacobian
      */
     private T[][] createInverseJacobian(final PositionAngleType type) {
 
         // get the direct Jacobian
         final T[][] directJacobian = MathArrays.buildArray(getA().getField(), 6, 6);
         getJacobianWrtCartesian(type, directJacobian);
 
         // invert the direct Jacobian
         final FieldMatrix<T> matrix = MatrixUtils.createFieldMatrix(directJacobian);
         final FieldDecompositionSolver<T> solver = new FieldLUDecomposition<>(matrix).getSolver();
         return solver.getInverse().getData();
 
     }
 
     /** Compute the Jacobian of the orbital parameters with mean angle with respect to the Cartesian parameters.
      * <p>
      * Element {@code jacobian[i][j]} is the derivative of parameter i of the orbit with
      * respect to Cartesian coordinate j. This means each row correspond to one orbital parameter
      * whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.
      * </p>
      * @return 6x6 Jacobian matrix
      * @see #computeJacobianEccentricWrtCartesian()
      * @see #computeJacobianTrueWrtCartesian()
      */
     protected abstract T[][] computeJacobianMeanWrtCartesian();
 
     /** Compute the Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian parameters.
      * <p>
      * Element {@code jacobian[i][j]} is the derivative of parameter i of the orbit with
      * respect to Cartesian coordinate j. This means each row correspond to one orbital parameter
      * whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.
      * </p>
      * @return 6x6 Jacobian matrix
      * @see #computeJacobianMeanWrtCartesian()
      * @see #computeJacobianTrueWrtCartesian()
      */
     protected abstract T[][] computeJacobianEccentricWrtCartesian();
 
     /** Compute the Jacobian of the orbital parameters with true angle with respect to the Cartesian parameters.
      * <p>
      * Element {@code jacobian[i][j]} is the derivative of parameter i of the orbit with
      * respect to Cartesian coordinate j. This means each row correspond to one orbital parameter
      * whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.
      * </p>
      * @return 6x6 Jacobian matrix
      * @see #computeJacobianMeanWrtCartesian()
      * @see #computeJacobianEccentricWrtCartesian()
      */
     protected abstract T[][] computeJacobianTrueWrtCartesian();
 
     /** Add the contribution of the Keplerian motion to parameters derivatives
      * <p>
      * This method is used by integration-based propagators to evaluate the part of Keplerian
      * motion to evolution of the orbital state.
      * </p>
      * @param type type of the position angle in the state
      * @param gm attraction coefficient to use
      * @param pDot array containing orbital state derivatives to update (the Keplerian
      * part must be <em>added</em> to the array components, as the array may already
      * contain some non-zero elements corresponding to non-Keplerian parts)
      */
     public abstract void addKeplerContribution(PositionAngleType type, T gm, T[] pDot);
 
         /** Fill a Jacobian half row with a single vector.
      * @param a coefficient of the vector
      * @param v vector
      * @param row Jacobian matrix row
      * @param j index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
      */
 
     protected void fillHalfRow(final T a, final FieldVector3D<T> v, final T[] row, final int j) {
         row[j]     = a.multiply(v.getX());
         row[j + 1] = a.multiply(v.getY());
         row[j + 2] = a.multiply(v.getZ());
     }
 
     /** Fill a Jacobian half row with a linear combination of vectors.
      * @param a1 coefficient of the first vector
      * @param v1 first vector
      * @param a2 coefficient of the second vector
      * @param v2 second vector
      * @param row Jacobian matrix row
      * @param j index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
      */
     protected void fillHalfRow(final T a1, final FieldVector3D<T> v1, final T a2, final FieldVector3D<T> v2,
                                       final T[] row, final int j) {
         row[j]     = a1.linearCombination(a1, v1.getX(), a2, v2.getX());
         row[j + 1] = a1.linearCombination(a1, v1.getY(), a2, v2.getY());
         row[j + 2] = a1.linearCombination(a1, v1.getZ(), a2, v2.getZ());
 
     }
 
     /** Fill a Jacobian half row with a linear combination of vectors.
      * @param a1 coefficient of the first vector
      * @param v1 first vector
      * @param a2 coefficient of the second vector
      * @param v2 second vector
      * @param a3 coefficient of the third vector
      * @param v3 third vector
      * @param row Jacobian matrix row
      * @param j index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
      */
     protected void fillHalfRow(final T a1, final FieldVector3D<T> v1,
                                final T a2, final FieldVector3D<T> v2,
                                final T a3, final FieldVector3D<T> v3,
                                       final T[] row, final int j) {
         row[j]     = a1.linearCombination(a1, v1.getX(), a2, v2.getX(), a3, v3.getX());
         row[j + 1] = a1.linearCombination(a1, v1.getY(), a2, v2.getY(), a3, v3.getY());
         row[j + 2] = a1.linearCombination(a1, v1.getZ(), a2, v2.getZ(), a3, v3.getZ());
 
     }
 
     /** Fill a Jacobian half row with a linear combination of vectors.
      * @param a1 coefficient of the first vector
      * @param v1 first vector
      * @param a2 coefficient of the second vector
      * @param v2 second vector
      * @param a3 coefficient of the third vector
      * @param v3 third vector
      * @param a4 coefficient of the fourth vector
      * @param v4 fourth vector
      * @param row Jacobian matrix row
      * @param j index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
      */
     protected void fillHalfRow(final T a1, final FieldVector3D<T> v1, final T a2, final FieldVector3D<T> v2,
                                       final T a3, final FieldVector3D<T> v3, final T a4, final FieldVector3D<T> v4,
                                       final T[] row, final int j) {
         row[j]     = a1.linearCombination(a1, v1.getX(), a2, v2.getX(), a3, v3.getX(), a4, v4.getX());
         row[j + 1] = a1.linearCombination(a1, v1.getY(), a2, v2.getY(), a3, v3.getY(), a4, v4.getY());
         row[j + 2] = a1.linearCombination(a1, v1.getZ(), a2, v2.getZ(), a3, v3.getZ(), a4, v4.getZ());
 
     }
 
     /** Fill a Jacobian half row with a linear combination of vectors.
      * @param a1 coefficient of the first vector
      * @param v1 first vector
      * @param a2 coefficient of the second vector
      * @param v2 second vector
      * @param a3 coefficient of the third vector
      * @param v3 third vector
      * @param a4 coefficient of the fourth vector
      * @param v4 fourth vector
      * @param a5 coefficient of the fifth vector
      * @param v5 fifth vector
      * @param row Jacobian matrix row
      * @param j index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
      */
     protected void fillHalfRow(final T a1, final FieldVector3D<T> v1, final T a2, final FieldVector3D<T> v2,
                                       final T a3, final FieldVector3D<T> v3, final T a4, final FieldVector3D<T> v4,
                                       final T a5, final FieldVector3D<T> v5,
                                       final T[] row, final int j) {
         row[j]     = a1.linearCombination(a1, v1.getX(), a2, v2.getX(), a3, v3.getX(), a4, v4.getX()).add(a5.multiply(v5.getX()));
         row[j + 1] = a1.linearCombination(a1, v1.getY(), a2, v2.getY(), a3, v3.getY(), a4, v4.getY()).add(a5.multiply(v5.getY()));
         row[j + 2] = a1.linearCombination(a1, v1.getZ(), a2, v2.getZ(), a3, v3.getZ(), a4, v4.getZ()).add(a5.multiply(v5.getZ()));
 
     }
 
     /** Fill a Jacobian half row with a linear combination of vectors.
      * @param a1 coefficient of the first vector
      * @param v1 first vector
      * @param a2 coefficient of the second vector
      * @param v2 second vector
      * @param a3 coefficient of the third vector
      * @param v3 third vector
      * @param a4 coefficient of the fourth vector
      * @param v4 fourth vector
      * @param a5 coefficient of the fifth vector
      * @param v5 fifth vector
      * @param a6 coefficient of the sixth vector
      * @param v6 sixth vector
      * @param row Jacobian matrix row
      * @param j index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
      */
     protected void fillHalfRow(final T a1, final FieldVector3D<T> v1, final T a2, final FieldVector3D<T> v2,
                                       final T a3, final FieldVector3D<T> v3, final T a4, final FieldVector3D<T> v4,
                                       final T a5, final FieldVector3D<T> v5, final T a6, final FieldVector3D<T> v6,
                                       final T[] row, final int j) {
         row[j]     = a1.linearCombination(a1, v1.getX(), a2, v2.getX(), a3, v3.getX(), a4, v4.getX()).add(a1.linearCombination(a5, v5.getX(), a6, v6.getX()));
         row[j + 1] = a1.linearCombination(a1, v1.getY(), a2, v2.getY(), a3, v3.getY(), a4, v4.getY()).add(a1.linearCombination(a5, v5.getY(), a6, v6.getY()));
         row[j + 2] = a1.linearCombination(a1, v1.getZ(), a2, v2.getZ(), a3, v3.getZ(), a4, v4.getZ()).add(a1.linearCombination(a5, v5.getZ(), a6, v6.getZ()));
 
     }
 
 
 }