/* 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.analysis.differentiation.Gradient;
  import org.hipparchus.analysis.differentiation.GradientField;
  import org.hipparchus.linear.MatrixUtils;
  import org.hipparchus.linear.RealMatrix;
  import org.hipparchus.linear.RealVector;
  import org.hipparchus.ode.events.Action;
  import org.hipparchus.util.FastMath;
  import org.orekit.attitudes.Attitude;
  import org.orekit.attitudes.AttitudeProvider;
  import org.orekit.forces.ForceModel;
  import org.orekit.frames.Frame;
  import org.orekit.orbits.CartesianOrbit;
  import org.orekit.orbits.Orbit;
  import org.orekit.propagation.FieldSpacecraftState;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.events.EventDetector;
  import org.orekit.propagation.events.FieldEventDetector;
  import org.orekit.propagation.events.handlers.EventHandler;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.utils.AbsolutePVCoordinates;
  import org.orekit.utils.DataDictionary;
  import org.orekit.utils.DerivativeStateUtils;
  import org.orekit.utils.PVCoordinates;
  import org.orekit.utils.TimeStampedPVCoordinates;
  
  import java.util.Arrays;
  import java.util.List;
  import java.util.stream.Collectors;
  import java.util.stream.Stream;
  
  /**
   * Class handling the State Transition Matrix update in the presence of dynamics discontinuities.
   * Reference: Eq. (29-30) in Russell, R. P., “Primer Vector Theory Applied to Global Low-Thrust Trade Studies,”
   * Journal of Guidance, Control, and Dynamics, Vol. 30, No. 2, 2007, pp. 460-472.
   *
   * @author Romain Serra
   * @since 13.1
   * @see NumericalPropagator
   */
  class SwitchEventHandler implements EventHandler {
  
      /** Original event handler to wrap. */
      private final EventHandler wrappedHandler;
  
      /** Matrices harvester. */
      private final NumericalPropagationHarvester matricesHarvester;
  
      /** Differential equations. */
      private final NumericalTimeDerivativesEquations timeDerivativesEquations;
  
      /** Attitude provider. */
      private final AttitudeProvider attitudeProvider;
  
      /** Flag on propagation direction. */
      private boolean isForward;
  
      /** Field version of detector defining dynamics switch. */
      private FieldEventDetector<Gradient> switchFieldDetector;
  
      /**
       * Constructor.
       * @param wrappedHandler original event handler
       * @param matricesHarvester matrices harvester
       * @param timeDerivativesEquations differential equations
       * @param attitudeProvider attitude provider
       */
      SwitchEventHandler(final EventHandler wrappedHandler, final NumericalPropagationHarvester matricesHarvester,
                         final NumericalTimeDerivativesEquations timeDerivativesEquations,
                         final AttitudeProvider attitudeProvider) {
          this.wrappedHandler = wrappedHandler;
          this.matricesHarvester = matricesHarvester;
          this.timeDerivativesEquations = timeDerivativesEquations;
          this.attitudeProvider = attitudeProvider;
      }
  
      @Override
      public SpacecraftState resetState(final EventDetector detector, final SpacecraftState oldState) {
          if (switchFieldDetector == null) {
              return wrappedHandler.resetState(detector, oldState);
          } else {
             final SpacecraftState newState = updateState(oldState);
             switchFieldDetector = null;
             return newState;
         }
     }
 
     @Override
     public void init(final SpacecraftState initialState, final AbsoluteDate target, final EventDetector detector) {
         isForward = initialState.getDate().isBeforeOrEqualTo(target);
         switchFieldDetector = null;
         EventHandler.super.init(initialState, target, detector);
     }
 
     @Override
     public Action eventOccurred(final SpacecraftState s, final EventDetector detector, final boolean increasing) {
         final Action action = wrappedHandler.eventOccurred(s, detector, increasing);
         if (action == Action.RESET_DERIVATIVES) {
             switchFieldDetector = findSwitchDetector(detector, s);
             if (switchFieldDetector != null) {
                 return Action.RESET_STATE;
             }
         }
         return action;
     }
 
     /**
      * Method finding the Field detector corresponding to a non-Field, triggered one.
      * @param detector triggered event detector
      * @param state state
      * @return Field detector
      */
     private FieldEventDetector<Gradient> findSwitchDetector(final EventDetector detector, final SpacecraftState state) {
         final int variablesNumber = matricesHarvester.getStateDimension() + 1;
         final GradientField field = GradientField.getField(variablesNumber);
         Stream<FieldEventDetector<Gradient>> fieldDetectorsStream = attitudeProvider.getFieldEventDetectors(field);
         for (final ForceModel forceModel : timeDerivativesEquations.getForceModels()) {
             fieldDetectorsStream = Stream.concat(fieldDetectorsStream, forceModel.getFieldEventDetectors(field));
         }
         final List<FieldEventDetector<Gradient>> fieldDetectors = fieldDetectorsStream
                 .filter(fieldDetector -> !fieldDetector.dependsOnTimeOnly()).collect(Collectors.toList());
         final FieldSpacecraftState<Gradient> fieldState = new FieldSpacecraftState<>(field, state);
         fieldDetectors.forEach(fieldDetector -> fieldDetector.init(fieldState, fieldState.getDate()));
         final double g = detector.g(state);
         return findSwitchDetector(g, fieldState, fieldDetectors);
     }
 
     /**
      * Method finding the Field detector corresponding to a non-Field, triggered one.
      * @param g value of triggered detector
      * @param fieldState Field state
      * @param fieldDetectors candidate Field detectors
      * @return Field detector
      */
     private FieldEventDetector<Gradient> findSwitchDetector(final double g, final FieldSpacecraftState<Gradient> fieldState,
                                                             final List<FieldEventDetector<Gradient>> fieldDetectors) {
         for (final FieldEventDetector<Gradient> fieldDetector : fieldDetectors) {
             final Gradient fieldG = fieldDetector.g(fieldState);
             if (FastMath.abs(fieldG.getValue() - g) < 1e-11) {
                 return fieldDetector;
             }
         }
         return null;
     }
 
     /**
      * Update state, more precisely the additional data corresponding to the STM.
      * @param stateAtSwitch original state
      * @return updated state
      */
     private SpacecraftState updateState(final SpacecraftState stateAtSwitch) {
         final RealMatrix cartesianFactorMatrix = computeUpdateMatrix(stateAtSwitch);
         // update STM
         final String stmName = matricesHarvester.getStmName();
         final RealMatrix oldStm = matricesHarvester.toSquareMatrix(stateAtSwitch.getAdditionalState(stmName));
         final RealMatrix stm = cartesianFactorMatrix.multiply(oldStm).add(oldStm);
         final DataDictionary additionalData = new DataDictionary(stateAtSwitch.getAdditionalDataValues());
         additionalData.put(stmName, matricesHarvester.toArray(stm.getData()));
         // update model parameters Jacobian if present
         if (!matricesHarvester.getJacobiansColumnsNames().isEmpty()) {
             for (final String parameterName : matricesHarvester.getJacobiansColumnsNames()) {
                 final RealVector oldJacobian = MatrixUtils.createRealVector(stateAtSwitch.getAdditionalState(parameterName));
                 final RealVector jacobian = cartesianFactorMatrix.operate(oldJacobian).add(oldJacobian);
                 additionalData.put(parameterName, jacobian.toArray());
             }
         }
         return stateAtSwitch.withAdditionalData(additionalData);
     }
 
     /**
      * Compute matrix needed to update STM and the like.
      * @param state state
      * @return matrix
      */
     private RealMatrix computeUpdateMatrix(final SpacecraftState state) {
         final double twoThreshold = switchFieldDetector.getThreshold().getValue() * 2.;
         final double dt = isForward ? -twoThreshold : twoThreshold;
         final SpacecraftState stateBefore = shift(state, dt);
         final double[] derivativesBefore = timeDerivativesEquations.computeTimeDerivatives(stateBefore);
         final SpacecraftState stateAfter = shift(state, -dt);
         final double[] derivativesAfter = timeDerivativesEquations.computeTimeDerivatives(stateAfter);
         final double[] deltaDerivatives = new double[7];
         for (int i = 3; i < 7; i++) {
             deltaDerivatives[i] = derivativesAfter[i] - derivativesBefore[i];
         }
         final Gradient g = evaluateG(buildCartesianState(state, state.getPVCoordinates()), derivativesBefore[6]);
         final double gLastDerivative = g.getPartialDerivative(7);
         final double gDot = isForward ? gLastDerivative : -gLastDerivative;
         final double[] gGradientState = Arrays.copyOfRange(g.getGradient(), 0, 7);
         final RealVector lhs = MatrixUtils.createRealVector(deltaDerivatives);
         final RealVector rhs = MatrixUtils.createRealVector(gGradientState).mapMultiply(1. / gDot);
         return lhs.outerProduct(rhs);
     }
 
     /**
      * Shift state using first order Taylor expansion for position.
      * @param stateAtSwitch state
      * @param dt time shift
      * @return new state
      */
     private SpacecraftState shift(final SpacecraftState stateAtSwitch, final double dt) {
         final PVCoordinates pvCoordinates = stateAtSwitch.getPVCoordinates();
         final AbsoluteDate shiftedDate = stateAtSwitch.getDate().shiftedBy(dt);
         final TimeStampedPVCoordinates shiftedPV = new TimeStampedPVCoordinates(shiftedDate,
                 pvCoordinates.getPosition().add(pvCoordinates.getVelocity().scalarMultiply(dt)), pvCoordinates.getVelocity());
         return buildCartesianState(stateAtSwitch, shiftedPV);
     }
 
     /**
      * Build state given template and new position-velocity vector.
      * @param templateState template state
      * @param pvCoordinates position-velocity vector
      * @return new state
      */
     private SpacecraftState buildCartesianState(final SpacecraftState templateState,
                                                 final TimeStampedPVCoordinates pvCoordinates) {
         final SpacecraftState state;
         final Frame frame = templateState.getFrame();
         if (templateState.isOrbitDefined()) {
             final Orbit templateOrbit = templateState.getOrbit();
             final CartesianOrbit orbit = new CartesianOrbit(pvCoordinates, frame, templateOrbit.getMu());
             final Attitude attitude = attitudeProvider.getAttitude(orbit, pvCoordinates.getDate(), frame);
             state = new SpacecraftState(orbit, attitude);
         } else {
             final AbsolutePVCoordinates absolutePVCoordinates = new AbsolutePVCoordinates(frame, pvCoordinates);
             final Attitude attitude = attitudeProvider.getAttitude(absolutePVCoordinates,
                     pvCoordinates.getDate(), frame);
             state = new SpacecraftState(absolutePVCoordinates, attitude);
         }
         return state.withMass(templateState.getMass())
                 .withAdditionalData(templateState.getAdditionalDataValues())
                 .withAdditionalStatesDerivatives(templateState.getAdditionalStatesDerivatives());
     }
 
     /**
      * Evaluate event function in Taylor algebra.
      * @param state state
      * @param massRate mass rate
      * @return g in Taylor algebra
      */
     private Gradient evaluateG(final SpacecraftState state, final double massRate) {
         Gradient time = Gradient.variable(8, 7, 0);
         if (!isForward) {
             time = time.negate();
         }
         final GradientField field = time.getField();
         FieldSpacecraftState<Gradient> fieldState = DerivativeStateUtils.buildSpacecraftStateGradient(field,
                 state, attitudeProvider);
         fieldState = fieldState.shiftedBy(time);
         final Gradient shiftedMass = time.multiply(massRate).add(state.getMass());
         fieldState = fieldState.withMass(shiftedMass);  // necessary because shiftedBy does not consider mass
         return switchFieldDetector.g(fieldState);
     }
 
 }