/* Copyright 2022-2025 Romain Serra
    * 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.numerical;
  
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.hipparchus.util.FastMath;
  import org.orekit.errors.OrekitIllegalArgumentException;
  import org.orekit.errors.OrekitMessages;
  import org.orekit.forces.ForceModel;
  import org.orekit.orbits.OrbitType;
  import org.orekit.orbits.PositionAngleType;
  import org.orekit.propagation.SpacecraftState;
  
  import java.util.Arrays;
  import java.util.List;
  
  /**
   * First-order differential model representing the equations of motion.
   *
   * @author Luc Maisonobe
   * @author Romain Serra
   * @since 13.1
   * @see NumericalPropagator
   */
  class NumericalTimeDerivativesEquations implements TimeDerivativesEquations {
  
      /** Derivatives array. */
      private final double[] yDot;
  
      /** Orbit type of coordinates. */
      private final OrbitType orbitType;
  
      /** Position angle type of coordinates. */
      private final PositionAngleType positionAngleType;
  
      /** Forces list. */
      private final List<ForceModel> forceModels;
  
      /** Jacobian of the orbital parameters with respect to the Cartesian parameters. */
      private double[][] coordinatesJacobian;
  
      /** Current state. */
      private SpacecraftState currentState;
  
      /**
       * Constructor.
       * @param orbitType orbit type used in equations
       * @param positionAngleType angle type used in equations if applicable
       * @param forceModels forces
       */
      NumericalTimeDerivativesEquations(final OrbitType orbitType, final PositionAngleType positionAngleType,
                                        final List<ForceModel> forceModels) {
          this.orbitType = orbitType;
          this.positionAngleType = positionAngleType;
          this.forceModels = forceModels;
          this.yDot     = new double[7];
          this.coordinatesJacobian = new double[6][6];
          // default value for Jacobian is identity
          for (int i = 0; i < coordinatesJacobian.length; ++i) {
              Arrays.fill(coordinatesJacobian[i], 0.0);
              coordinatesJacobian[i][i] = 1.0;
          }
      }
  
      /**
       * Getter for the force models.
       * @return forces
       */
      List<ForceModel> getForceModels() {
          return forceModels;
      }
  
      /**
       * Setter for the coordinates' Jacobian matrix.
       * @param coordinatesJacobian matrix
       */
      void setCoordinatesJacobian(final double[][] coordinatesJacobian) {
          this.coordinatesJacobian = coordinatesJacobian;
      }
  
      /**
       * Setter for the current state.
       * @param currentState state
       */
      void setCurrentState(final SpacecraftState currentState) {
         this.currentState = currentState;
     }
 
     /**
      * Compute first-order, time derivatives a.k.a. rates.
      * @param state state where to evaluate derivatives
      * @return derivatives
      */
     double[] computeTimeDerivatives(final SpacecraftState state) {
         currentState = state;
         Arrays.fill(yDot, 0.0);
 
         // compute the contributions of all perturbing forces,
         // using the Kepler contribution at the end since
         // NewtonianAttraction is always the last instance in the list
         for (final ForceModel forceModel : forceModels) {
             forceModel.addContribution(state, this);
         }
 
         if (orbitType == null) {
             // position derivative is velocity, and was not added above in the force models
             // (it is added when orbit type is non-null because NewtonianAttraction considers it)
             final Vector3D velocity = state.getPVCoordinates().getVelocity();
             yDot[0] += velocity.getX();
             yDot[1] += velocity.getY();
             yDot[2] += velocity.getZ();
         }
 
         return yDot.clone();
     }
 
     /** {@inheritDoc} */
     @Override
     public void addKeplerContribution(final double mu) {
         if (orbitType == null) {
             // if mu is neither 0 nor NaN, we want to include Newtonian acceleration
             if (mu > 0) {
                 // velocity derivative is Newtonian acceleration
                 final Vector3D position = currentState.getPosition();
                 final double r2         = position.getNormSq();
                 final double coeff      = -mu / (r2 * FastMath.sqrt(r2));
                 yDot[3] += coeff * position.getX();
                 yDot[4] += coeff * position.getY();
                 yDot[5] += coeff * position.getZ();
             }
 
         } else {
             // propagation uses regular orbits
             orbitType.convertType(currentState.getOrbit()).addKeplerContribution(positionAngleType, mu, yDot);
         }
     }
 
     /** {@inheritDoc} */
     @Override
     public void addNonKeplerianAcceleration(final Vector3D gamma) {
         for (int i = 0; i < 6; ++i) {
             final double[] jRow = coordinatesJacobian[i];
             yDot[i] += jRow[3] * gamma.getX() + jRow[4] * gamma.getY() + jRow[5] * gamma.getZ();
         }
     }
 
     /** {@inheritDoc} */
     @Override
     public void addMassDerivative(final double q) {
         if (q > 0) {
             throw new OrekitIllegalArgumentException(OrekitMessages.POSITIVE_FLOW_RATE, q);
         }
         yDot[6] += q;
     }
 }