/* Copyright 2002-2026 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.propagation.analytical;
  
  import java.util.Arrays;
  import java.util.List;
  
  import org.hipparchus.analysis.differentiation.Gradient;
  import org.hipparchus.linear.MatrixUtils;
  import org.hipparchus.linear.RealMatrix;
  import org.orekit.orbits.FieldOrbit;
  import org.orekit.orbits.OrbitParamsType;
  import org.orekit.orbits.PositionAngleType;
  import org.orekit.propagation.AbstractMatricesHarvester;
  import org.orekit.propagation.AdditionalDataProvider;
  import org.orekit.propagation.FieldSpacecraftState;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.time.FieldAbsoluteDate;
  import org.orekit.utils.DoubleArrayDictionary;
  import org.orekit.utils.drivers.ParameterDriver;
  
  /**
   * Base class harvester between two-dimensional Jacobian
   * matrices and analytical orbit propagator.
   * @author Thomas Paulet
   * @author Bryan Cazabonne
   * @since 11.1
   */
  public abstract class AbstractAnalyticalMatricesHarvester extends AbstractMatricesHarvester
          implements AdditionalDataProvider<double[]> {
  
      /** Columns names for parameters. */
      private List<String> columnsNames;
  
      /** Epoch of the last computed state transition matrix. */
      private AbsoluteDate epoch;
  
      /** Analytical derivatives that apply to State Transition Matrix. */
      private double[][] analyticalDerivativesStm;
  
      /** Analytical derivatives that apply to Jacobians columns. */
      private final DoubleArrayDictionary analyticalDerivativesJacobianColumns;
  
      /** Propagator bound to this harvester. */
      private final AbstractAnalyticalPropagator propagator;
  
      /** Simple constructor.
       * <p>
       * The arguments for initial matrices <em>must</em> be compatible with the
       * {@link OrbitParamsType orbit type}
       * and {@link PositionAngleType position angle} that will be used by propagator
       * </p>
       * @param propagator propagator bound to this harvester
       */
      protected AbstractAnalyticalMatricesHarvester(final AbstractAnalyticalPropagator propagator) {
          this.propagator                           = propagator;
          this.epoch                                = propagator.getInitialState().getDate();
          this.columnsNames                         = null;
          this.analyticalDerivativesJacobianColumns = new DoubleArrayDictionary();
      }
  
      /** {@inheritDoc} */
      @Override
      protected void setInitialStm(final String stmName, final RealMatrix stm) {
          super.setInitialStm(stmName, stm);
          this.analyticalDerivativesStm = getInitialStateTransitionMatrix().getData();
      }
  
      /** {@inheritDoc} */
      @Override
      public List<String> getJacobiansColumnsNames() {
          return columnsNames == null ? propagator.getJacobiansColumnsNames() : columnsNames;
      }
  
      /** {@inheritDoc} */
      @Override
      public void freezeColumnsNames() {
          columnsNames = getJacobiansColumnsNames();
      }
  
      /** {@inheritDoc} */
      @Override
      public String getName() {
          return getStmName();
     }
 
     /** {@inheritDoc} */
     @Override
     public double[] getAdditionalData(final SpacecraftState state) {
         // Update the partial derivatives if needed
         updateDerivativesIfNeeded(state);
         // Return the state transition matrix in an array
         return toArray(analyticalDerivativesStm);
     }
 
     /** {@inheritDoc} */
     @Override
     public RealMatrix getStateTransitionMatrix(final SpacecraftState state) {
         // Check if additional state is defined
         if (!state.hasAdditionalData(getName())) {
             return null;
         }
         // Return the state transition matrix
         return toSquareMatrix(state.getAdditionalState(getName()));
     }
 
     /** {@inheritDoc} */
     @Override
     public RealMatrix getParametersJacobian(final SpacecraftState state) {
 
         // Update the partial derivatives if needed
         updateDerivativesIfNeeded(state);
 
         // Estimated parameters
         final List<String> names = getJacobiansColumnsNames();
         if (names == null || names.isEmpty()) {
             return null;
         }
 
         // Initialize Jacobian
         final RealMatrix dYdP = MatrixUtils.createRealMatrix(getStateDimension(), names.size());
 
         // Add the derivatives
         for (int j = 0; j < names.size(); ++j) {
             final double[] column = analyticalDerivativesJacobianColumns.get(names.get(j));
             if (column != null) {
                 for (int i = 0; i < getStateDimension(); i++) {
                     dYdP.addToEntry(i, j, column[i]);
                 }
             }
         }
 
         // Return
         return dYdP;
 
     }
 
     /** {@inheritDoc} */
     @Override
     public void setReferenceState(final SpacecraftState reference) {
 
         // reset derivatives to zero
         for (final double[] row : analyticalDerivativesStm) {
             Arrays.fill(row, 0.0);
         }
         analyticalDerivativesJacobianColumns.clear();
 
         final AbstractAnalyticalGradientConverter converter           = getGradientConverter();
         final FieldAbstractAnalyticalPropagator<Gradient> gPropagator = converter.getPropagator();
 
         // Compute Jacobian
         final AbsoluteDate                   target           = reference.getDate();
         final FieldAbsoluteDate<Gradient>    start            = gPropagator.getInitialState().getDate();
         final double                         dt               = target.durationFrom(start.toAbsoluteDate());
         final FieldSpacecraftState<Gradient> state            = gPropagator.getInitialState();
         final Gradient[]                     parameters       = converter.getParameters(state, converter);
         final FieldOrbit<Gradient>           gOrbit           = gPropagator.propagateOrbit(start.shiftedBy(dt), parameters);
         final Gradient[]                     orbitDerivatives = new Gradient[6];
         getOrbitParamsType().mapOrbitToArray(gOrbit, getPositionAngleType(), orbitDerivatives, null);
 
         // Update Jacobian with respect to state
         for (int i = 0; i < orbitDerivatives.length; ++i) {
             addToRow(orbitDerivatives[i].getGradient(), i);
         }
 
         // Partial derivatives of the state with respect to propagation parameters
         int paramsIndex = converter.getFreeStateParameters();
         for (ParameterDriver driver : converter.getParametersDrivers()) {
             if (driver.isSelected()) {
 
                 // get the partials derivatives for this driver
                 DoubleArrayDictionary.Entry entry = analyticalDerivativesJacobianColumns.getEntry(driver.getName());
                 if (entry == null) {
                     // create an entry filled with zeroes
                     analyticalDerivativesJacobianColumns.put(driver.getName(), new double[getStateDimension()]);
                     entry = analyticalDerivativesJacobianColumns.getEntry(driver.getName());
                 }
 
                 // add the contribution of the current force model
                 entry.increment(new double[] {
                     orbitDerivatives[0].getPartialDerivative(paramsIndex),
                     orbitDerivatives[1].getPartialDerivative(paramsIndex),
                     orbitDerivatives[2].getPartialDerivative(paramsIndex),
                     orbitDerivatives[3].getPartialDerivative(paramsIndex),
                     orbitDerivatives[4].getPartialDerivative(paramsIndex),
                     orbitDerivatives[5].getPartialDerivative(paramsIndex)
                 });
                 ++paramsIndex;
             }
         }
 
         // Update the epoch of the last computed partial derivatives
         epoch = target;
 
     }
 
     /** Update the partial derivatives (if needed).
      * @param state current spacecraft state
      */
     private void updateDerivativesIfNeeded(final SpacecraftState state) {
         if (!state.getDate().isEqualTo(epoch)) {
             setReferenceState(state);
         }
     }
 
     /** Fill State Transition Matrix rows.
      * @param derivatives derivatives of a component
      * @param index component index
      */
     private void addToRow(final double[] derivatives, final int index) {
         for (int i = 0; i < 6; i++) {
             analyticalDerivativesStm[index][i] += derivatives[i];
         }
     }
 
     /** {@inheritDoc} */
     @Override
     public OrbitParamsType getOrbitParamsType() {
         // Set to CARTESIAN because analytical gradient converters uses Cartesian representation
         return OrbitParamsType.CARTESIAN;
     }
 
     /** {@inheritDoc} */
     @Override
     public PositionAngleType getPositionAngleType() {
         // Irrelevant: set a default value
         return PositionAngleType.MEAN;
     }
 
     /**
      * Get the gradient converter related to the analytical orbit propagator.
      * @return the gradient converter
      */
     public abstract AbstractAnalyticalGradientConverter getGradientConverter();
 
 }