AbstractIntegratedPropagator.java

  1. /* Copyright 2002-2024 CS GROUP
  2.  * Licensed to CS GROUP (CS) under one or more
  3.  * contributor license agreements.  See the NOTICE file distributed with
  4.  * this work for additional information regarding copyright ownership.
  5.  * CS licenses this file to You under the Apache License, Version 2.0
  6.  * (the "License"); you may not use this file except in compliance with
  7.  * the License.  You may obtain a copy of the License at
  8.  *
  9.  *   http://www.apache.org/licenses/LICENSE-2.0
  10.  *
  11.  * Unless required by applicable law or agreed to in writing, software
  12.  * distributed under the License is distributed on an "AS IS" BASIS,
  13.  * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
  14.  * See the License for the specific language governing permissions and
  15.  * limitations under the License.
  16.  */
  17. package org.orekit.propagation.integration;

  19. import java.util.ArrayList;
  20. import java.util.Arrays;
  21. import java.util.Collection;
  22. import java.util.Collections;
  23. import java.util.HashMap;
  24. import java.util.LinkedList;
  25. import java.util.List;
  26. import java.util.Map;
  27. import java.util.Queue;

  29. import org.hipparchus.analysis.UnivariateFunction;
  30. import org.hipparchus.analysis.solvers.BracketedUnivariateSolver;
  31. import org.hipparchus.analysis.solvers.BracketingNthOrderBrentSolver;
  32. import org.hipparchus.exception.MathRuntimeException;
  33. import org.hipparchus.ode.DenseOutputModel;
  34. import org.hipparchus.ode.ExpandableODE;
  35. import org.hipparchus.ode.ODEIntegrator;
  36. import org.hipparchus.ode.ODEState;
  37. import org.hipparchus.ode.ODEStateAndDerivative;
  38. import org.hipparchus.ode.OrdinaryDifferentialEquation;
  39. import org.hipparchus.ode.SecondaryODE;
  40. import org.hipparchus.ode.events.Action;
  41. import org.hipparchus.ode.events.AdaptableInterval;
  42. import org.hipparchus.ode.events.ODEEventDetector;
  43. import org.hipparchus.ode.events.ODEEventHandler;
  44. import org.hipparchus.ode.sampling.AbstractODEStateInterpolator;
  45. import org.hipparchus.ode.sampling.ODEStateInterpolator;
  46. import org.hipparchus.ode.sampling.ODEStepHandler;
  47. import org.hipparchus.util.Precision;
  48. import org.orekit.attitudes.AttitudeProvider;
  49. import org.orekit.errors.OrekitException;
  50. import org.orekit.errors.OrekitInternalError;
  51. import org.orekit.errors.OrekitMessages;
  52. import org.orekit.frames.Frame;
  53. import org.orekit.orbits.OrbitType;
  54. import org.orekit.orbits.PositionAngleType;
  55. import org.orekit.propagation.AbstractPropagator;
  56. import org.orekit.propagation.BoundedPropagator;
  57. import org.orekit.propagation.EphemerisGenerator;
  58. import org.orekit.propagation.PropagationType;
  59. import org.orekit.propagation.SpacecraftState;
  60. import org.orekit.propagation.events.EventDetector;
  61. import org.orekit.propagation.events.handlers.EventHandler;
  62. import org.orekit.propagation.sampling.OrekitStepHandler;
  63. import org.orekit.propagation.sampling.OrekitStepInterpolator;
  64. import org.orekit.time.AbsoluteDate;
  65. import org.orekit.utils.DoubleArrayDictionary;


  68. /** Common handling of {@link org.orekit.propagation.Propagator Propagator}
  69.  *  methods for both numerical and semi-analytical propagators.
  70.  *  @author Luc Maisonobe
  71.  */
  72. public abstract class AbstractIntegratedPropagator extends AbstractPropagator {

  74.     /** Internal name used for complete secondary state dimension.
  75.      * @since 11.1
  76.      */
  77.     private static final String SECONDARY_DIMENSION = "Orekit-secondary-dimension";

  79.     /** Event detectors not related to force models. */
  80.     private final List<EventDetector> detectors;

  82.     /** Step handlers dedicated to ephemeris generation. */
  83.     private final List<StoringStepHandler> ephemerisGenerators;

  85.     /** Integrator selected by the user for the orbital extrapolation process. */
  86.     private final ODEIntegrator integrator;

  88.     /** Offsets of secondary states managed by {@link AdditionalDerivativesProvider}.
  89.      * @since 11.1
  90.      */
  91.     private final Map<String, Integer> secondaryOffsets;

  93.     /** Additional derivatives providers.
  94.      * @since 11.1
  95.      */
  96.     private final List<AdditionalDerivativesProvider> additionalDerivativesProviders;

  98.     /** Map of secondary equation offset in main
  99.     /** Counter for differential equations calls. */
  100.     private int calls;

  102.     /** Mapper between raw double components and space flight dynamics objects. */
  103.     private StateMapper stateMapper;

  105.     /**
  106.      * Attitude provider when evaluating derivatives. Can be a frozen one for performance.
  107.      * @since 12.1
  108.      */
  109.     private AttitudeProvider attitudeProviderForDerivatives;

  111.     /** Flag for resetting the state at end of propagation. */
  112.     private boolean resetAtEnd;

  114.     /** Type of orbit to output (mean or osculating) <br/>
  115.      * <p>
  116.      * This is used only in the case of semi-analytical propagators where there is a clear separation between
  117.      * mean and short periodic elements. It is ignored by the Numerical propagator.
  118.      * </p>
  119.      */
  120.     private final PropagationType propagationType;

  122.     /** Build a new instance.
  123.      * @param integrator numerical integrator to use for propagation.
  124.      * @param propagationType type of orbit to output (mean or osculating).
  125.      */
  126.     protected AbstractIntegratedPropagator(final ODEIntegrator integrator, final PropagationType propagationType) {
  127.         detectors                      = new ArrayList<>();
  128.         ephemerisGenerators            = new ArrayList<>();
  129.         additionalDerivativesProviders = new ArrayList<>();
  130.         this.secondaryOffsets          = new HashMap<>();
  131.         this.integrator                = integrator;
  132.         this.propagationType           = propagationType;
  133.         this.resetAtEnd                = true;
  134.     }

  136.     /** Allow/disallow resetting the initial state at end of propagation.
  137.      * <p>
  138.      * By default, at the end of the propagation, the propagator resets the initial state
  139.      * to the final state, thus allowing a new propagation to be started from there without
  140.      * recomputing the part already performed. Calling this method with {@code resetAtEnd} set
  141.      * to false changes prevents such reset.
  142.      * </p>
  143.      * @param resetAtEnd if true, at end of each propagation, the {@link
  144.      * #getInitialState() initial state} will be reset to the final state of
  145.      * the propagation, otherwise the initial state will be preserved
  146.      * @since 9.0
  147.      */
  148.     public void setResetAtEnd(final boolean resetAtEnd) {
  149.         this.resetAtEnd = resetAtEnd;
  150.     }

  152.     /** Getter for the resetting flag regarding initial state.
  153.      * @return resetting flag
  154.      * @since 12.0
  155.      */
  156.     public boolean getResetAtEnd() {
  157.         return this.resetAtEnd;
  158.     }

  160.     /**
  161.      * Method called when initializing the attitude provider used when evaluating derivatives.
  162.      * @return attitude provider for derivatives
  163.      */
  164.     protected AttitudeProvider initializeAttitudeProviderForDerivatives() {
  165.         return getAttitudeProvider();
  166.     }

  168.     /** Initialize the mapper. */
  169.     protected void initMapper() {
  170.         stateMapper = createMapper(null, Double.NaN, null, null, null, null);
  171.     }

  173.     /** Get the integrator's name.
  174.      * @return name of underlying integrator
  175.      * @since 12.0
  176.      */
  177.     public String getIntegratorName() {
  178.         return integrator.getName();
  179.     }

  181.     /**  {@inheritDoc} */
  182.     @Override
  183.     public void setAttitudeProvider(final AttitudeProvider attitudeProvider) {
  184.         super.setAttitudeProvider(attitudeProvider);
  185.         stateMapper = createMapper(stateMapper.getReferenceDate(), stateMapper.getMu(),
  186.                                    stateMapper.getOrbitType(), stateMapper.getPositionAngleType(),
  187.                                    attitudeProvider, stateMapper.getFrame());
  188.     }

  190.     /** Set propagation orbit type.
  191.      * @param orbitType orbit type to use for propagation, null for
  192.      * propagating using {@link org.orekit.utils.AbsolutePVCoordinates AbsolutePVCoordinates}
  193.      * rather than {@link org.orekit.orbits Orbit}
  194.      */
  195.     protected void setOrbitType(final OrbitType orbitType) {
  196.         stateMapper = createMapper(stateMapper.getReferenceDate(), stateMapper.getMu(),
  197.                                    orbitType, stateMapper.getPositionAngleType(),
  198.                                    stateMapper.getAttitudeProvider(), stateMapper.getFrame());
  199.     }

  201.     /** Get propagation parameter type.
  202.      * @return orbit type used for propagation, null for
  203.      * propagating using {@link org.orekit.utils.AbsolutePVCoordinates AbsolutePVCoordinates}
  204.      * rather than {@link org.orekit.orbits Orbit}
  205.      */
  206.     protected OrbitType getOrbitType() {
  207.         return stateMapper.getOrbitType();
  208.     }

  210.     /** Get the propagation type.
  211.      * @return propagation type.
  212.      * @since 11.1
  213.      */
  214.     public PropagationType getPropagationType() {
  215.         return propagationType;
  216.     }

  218.     /** Set position angle type.
  219.      * <p>
  220.      * The position parameter type is meaningful only if {@link
  221.      * #getOrbitType() propagation orbit type}
  222.      * support it. As an example, it is not meaningful for propagation
  223.      * in {@link OrbitType#CARTESIAN Cartesian} parameters.
  224.      * </p>
  225.      * @param positionAngleType angle type to use for propagation
  226.      */
  227.     protected void setPositionAngleType(final PositionAngleType positionAngleType) {
  228.         stateMapper = createMapper(stateMapper.getReferenceDate(), stateMapper.getMu(),
  229.                                    stateMapper.getOrbitType(), positionAngleType,
  230.                                    stateMapper.getAttitudeProvider(), stateMapper.getFrame());
  231.     }

  233.     /** Get propagation parameter type.
  234.      * @return angle type to use for propagation
  235.      */
  236.     protected PositionAngleType getPositionAngleType() {
  237.         return stateMapper.getPositionAngleType();
  238.     }

  240.     /** Set the central attraction coefficient μ.
  241.      * @param mu central attraction coefficient (m³/s²)
  242.      */
  243.     public void setMu(final double mu) {
  244.         stateMapper = createMapper(stateMapper.getReferenceDate(), mu,
  245.                                    stateMapper.getOrbitType(), stateMapper.getPositionAngleType(),
  246.                                    stateMapper.getAttitudeProvider(), stateMapper.getFrame());
  247.     }

  249.     /** Get the central attraction coefficient μ.
  250.      * @return mu central attraction coefficient (m³/s²)
  251.      * @see #setMu(double)
  252.      */
  253.     public double getMu() {
  254.         return stateMapper.getMu();
  255.     }

  257.     /** Get the number of calls to the differential equations computation method.
  258.      * <p>The number of calls is reset each time the {@link #propagate(AbsoluteDate)}
  259.      * method is called.</p>
  260.      * @return number of calls to the differential equations computation method
  261.      */
  262.     public int getCalls() {
  263.         return calls;
  264.     }

  266.     /** {@inheritDoc} */
  267.     @Override
  268.     public boolean isAdditionalStateManaged(final String name) {

  270.         // first look at already integrated states
  271.         if (super.isAdditionalStateManaged(name)) {
  272.             return true;
  273.         }

  275.         // then look at states we integrate ourselves
  276.         for (final AdditionalDerivativesProvider provider : additionalDerivativesProviders) {
  277.             if (provider.getName().equals(name)) {
  278.                 return true;
  279.             }
  280.         }

  282.         return false;
  283.     }

  285.     /** {@inheritDoc} */
  286.     @Override
  287.     public String[] getManagedAdditionalStates() {
  288.         final String[] alreadyIntegrated = super.getManagedAdditionalStates();
  289.         final String[] managed = new String[alreadyIntegrated.length + additionalDerivativesProviders.size()];
  290.         System.arraycopy(alreadyIntegrated, 0, managed, 0, alreadyIntegrated.length);
  291.         for (int i = 0; i < additionalDerivativesProviders.size(); ++i) {
  292.             managed[i + alreadyIntegrated.length] = additionalDerivativesProviders.get(i).getName();
  293.         }
  294.         return managed;
  295.     }

  297.     /** Add a provider for user-specified state derivatives to be integrated along with the orbit propagation.
  298.      * @param provider provider for additional derivatives
  299.      * @see #addAdditionalStateProvider(org.orekit.propagation.AdditionalStateProvider)
  300.      * @since 11.1
  301.      */
  302.     public void addAdditionalDerivativesProvider(final AdditionalDerivativesProvider provider) {

  304.         // check if the name is already used
  305.         if (isAdditionalStateManaged(provider.getName())) {
  306.             // these derivatives are already registered, complain
  307.             throw new OrekitException(OrekitMessages.ADDITIONAL_STATE_NAME_ALREADY_IN_USE,
  308.                                       provider.getName());
  309.         }

  311.         // this is really a new set of derivatives, add it
  312.         additionalDerivativesProviders.add(provider);

  314.         secondaryOffsets.clear();

  316.     }

  318.     /** Get an unmodifiable list of providers for additional derivatives.
  319.      * @return providers for the additional derivatives
  320.      * @since 11.1
  321.      */
  322.     public List<AdditionalDerivativesProvider> getAdditionalDerivativesProviders() {
  323.         return Collections.unmodifiableList(additionalDerivativesProviders);
  324.     }

  326.     /** {@inheritDoc} */
  327.     public void addEventDetector(final EventDetector detector) {
  328.         detectors.add(detector);
  329.     }

  331.     /** {@inheritDoc} */
  332.     public Collection<EventDetector> getEventsDetectors() {
  333.         return Collections.unmodifiableCollection(detectors);
  334.     }

  336.     /** {@inheritDoc} */
  337.     public void clearEventsDetectors() {
  338.         detectors.clear();
  339.     }

  341.     /** Set up all user defined event detectors.
  342.      */
  343.     protected void setUpUserEventDetectors() {
  344.         for (final EventDetector detector : detectors) {
  345.             setUpEventDetector(integrator, detector);
  346.         }
  347.     }

  349.     /** Wrap an Orekit event detector and register it to the integrator.
  350.      * @param integ integrator into which event detector should be registered
  351.      * @param detector event detector to wrap
  352.      */
  353.     protected void setUpEventDetector(final ODEIntegrator integ, final EventDetector detector) {
  354.         integ.addEventDetector(new AdaptedEventDetector(detector));
  355.     }

  357.     /** {@inheritDoc} */
  358.     @Override
  359.     public EphemerisGenerator getEphemerisGenerator() {
  360.         final StoringStepHandler storingHandler = new StoringStepHandler();
  361.         ephemerisGenerators.add(storingHandler);
  362.         return storingHandler;
  363.     }

  365.     /** Create a mapper between raw double components and spacecraft state.
  366.     /** Simple constructor.
  367.      * <p>
  368.      * The position parameter type is meaningful only if {@link
  369.      * #getOrbitType() propagation orbit type}
  370.      * support it. As an example, it is not meaningful for propagation
  371.      * in {@link OrbitType#CARTESIAN Cartesian} parameters.
  372.      * </p>
  373.      * @param referenceDate reference date
  374.      * @param mu central attraction coefficient (m³/s²)
  375.      * @param orbitType orbit type to use for mapping
  376.      * @param positionAngleType angle type to use for propagation
  377.      * @param attitudeProvider attitude provider
  378.      * @param frame inertial frame
  379.      * @return new mapper
  380.      */
  381.     protected abstract StateMapper createMapper(AbsoluteDate referenceDate, double mu,
  382.                                                 OrbitType orbitType, PositionAngleType positionAngleType,
  383.                                                 AttitudeProvider attitudeProvider, Frame frame);

  385.     /** Get the differential equations to integrate (for main state only).
  386.      * @param integ numerical integrator to use for propagation.
  387.      * @return differential equations for main state
  388.      */
  389.     protected abstract MainStateEquations getMainStateEquations(ODEIntegrator integ);

  391.     /** {@inheritDoc} */
  392.     @Override
  393.     public SpacecraftState propagate(final AbsoluteDate target) {
  394.         if (getStartDate() == null) {
  395.             if (getInitialState() == null) {
  396.                 throw new OrekitException(OrekitMessages.INITIAL_STATE_NOT_SPECIFIED_FOR_ORBIT_PROPAGATION);
  397.             }
  398.             setStartDate(getInitialState().getDate());
  399.         }
  400.         return propagate(getStartDate(), target);
  401.     }

  403.     /** {@inheritDoc} */
  404.     public SpacecraftState propagate(final AbsoluteDate tStart, final AbsoluteDate tEnd) {

  406.         if (getInitialState() == null) {
  407.             throw new OrekitException(OrekitMessages.INITIAL_STATE_NOT_SPECIFIED_FOR_ORBIT_PROPAGATION);
  408.         }

  410.         // make sure the integrator will be reset properly even if we change its events handlers and step handlers
  411.         try (IntegratorResetter resetter = new IntegratorResetter(integrator)) {

  413.             // prepare handling of STM and Jacobian matrices
  414.             setUpStmAndJacobianGenerators();

  416.             // Initialize additional states
  417.             initializeAdditionalStates(tEnd);

  419.             if (!tStart.equals(getInitialState().getDate())) {
  420.                 // if propagation start date is not initial date,
  421.                 // propagate from initial to start date without event detection
  422.                 try (IntegratorResetter startResetter = new IntegratorResetter(integrator)) {
  423.                     integrateDynamics(tStart, true);
  424.                 }
  425.             }

  427.             // set up events added by user
  428.             setUpUserEventDetectors();

  430.             // set up step handlers
  431.             for (final OrekitStepHandler handler : getMultiplexer().getHandlers()) {
  432.                 integrator.addStepHandler(new AdaptedStepHandler(handler));
  433.             }
  434.             for (final StoringStepHandler generator : ephemerisGenerators) {
  435.                 generator.setEndDate(tEnd);
  436.                 integrator.addStepHandler(generator);
  437.             }

  439.             // propagate from start date to end date with event detection
  440.             final SpacecraftState finalState = integrateDynamics(tEnd, false);

  442.             return finalState;

  444.         }

  446.     }

  448.     /** Set up State Transition Matrix and Jacobian matrix handling.
  449.      * @since 11.1
  450.      */
  451.     protected void setUpStmAndJacobianGenerators() {
  452.         // nothing to do by default
  453.     }

  455.     /** Propagation with or without event detection.
  456.      * @param tEnd target date to which orbit should be propagated
  457.      * @param forceResetAtEnd flag to force resetting state and date after integration
  458.      * @return state at end of propagation
  459.      */
  460.     private SpacecraftState integrateDynamics(final AbsoluteDate tEnd, final boolean forceResetAtEnd) {
  461.         try {

  463.             initializePropagation();

  465.             if (getInitialState().getDate().equals(tEnd)) {
  466.                 // don't extrapolate
  467.                 return getInitialState();
  468.             }

  470.             // space dynamics view
  471.             stateMapper = createMapper(getInitialState().getDate(), stateMapper.getMu(),
  472.                                        stateMapper.getOrbitType(), stateMapper.getPositionAngleType(),
  473.                                        stateMapper.getAttitudeProvider(), getInitialState().getFrame());
  474.             attitudeProviderForDerivatives = initializeAttitudeProviderForDerivatives();

  476.             if (Double.isNaN(getMu())) {
  477.                 setMu(getInitialState().getMu());
  478.             }

  480.             if (getInitialState().getMass() <= 0.0) {
  481.                 throw new OrekitException(OrekitMessages.NOT_POSITIVE_SPACECRAFT_MASS,
  482.                                           getInitialState().getMass());
  483.             }

  485.             // convert space flight dynamics API to math API
  486.             final SpacecraftState initialIntegrationState = getInitialIntegrationState();
  487.             final ODEState mathInitialState = createInitialState(initialIntegrationState);
  488.             final ExpandableODE mathODE = createODE(integrator);

  490.             // mathematical integration
  491.             final ODEStateAndDerivative mathFinalState;
  492.             beforeIntegration(initialIntegrationState, tEnd);
  493.             mathFinalState = integrator.integrate(mathODE, mathInitialState,
  494.                                                   tEnd.durationFrom(getInitialState().getDate()));
  495.             afterIntegration();

  497.             // get final state
  498.             SpacecraftState finalState =
  499.                             stateMapper.mapArrayToState(stateMapper.mapDoubleToDate(mathFinalState.getTime(),
  500.                                                                                     tEnd),
  501.                                                         mathFinalState.getPrimaryState(),
  502.                                                         mathFinalState.getPrimaryDerivative(),
  503.                                                         propagationType);

  505.             finalState = updateAdditionalStatesAndDerivatives(finalState, mathFinalState);

  507.             if (resetAtEnd || forceResetAtEnd) {
  508.                 resetInitialState(finalState);
  509.                 setStartDate(finalState.getDate());
  510.             }

  512.             return finalState;

  514.         } catch (MathRuntimeException mre) {
  515.             throw OrekitException.unwrap(mre);
  516.         }
  517.     }

  519.     /**
  520.      * Returns an updated version of the inputted state with additional states, including
  521.      * from derivatives providers.
  522.      * @param originalState input state
  523.      * @param os ODE state and derivative
  524.      * @return new state
  525.      * @since 12.1
  526.      */
  527.     private SpacecraftState updateAdditionalStatesAndDerivatives(final SpacecraftState originalState,
  528.                                                                  final ODEStateAndDerivative os) {
  529.         SpacecraftState updatedState = originalState;
  530.         if (os.getNumberOfSecondaryStates() > 0) {
  531.             final double[] secondary           = os.getSecondaryState(1);
  532.             final double[] secondaryDerivative = os.getSecondaryDerivative(1);
  533.             for (final AdditionalDerivativesProvider provider : additionalDerivativesProviders) {
  534.                 final String name      = provider.getName();
  535.                 final int    offset    = secondaryOffsets.get(name);
  536.                 final int    dimension = provider.getDimension();
  537.                 updatedState = updatedState.addAdditionalState(name, Arrays.copyOfRange(secondary, offset, offset + dimension));
  538.                 updatedState = updatedState.addAdditionalStateDerivative(name, Arrays.copyOfRange(secondaryDerivative, offset, offset + dimension));
  539.             }
  540.         }
  541.         return updateAdditionalStates(updatedState);
  542.     }

  544.     /** Get the initial state for integration.
  545.      * @return initial state for integration
  546.      */
  547.     protected SpacecraftState getInitialIntegrationState() {
  548.         return getInitialState();
  549.     }

  551.     /** Create an initial state.
  552.      * @param initialState initial state in flight dynamics world
  553.      * @return initial state in mathematics world
  554.      */
  555.     private ODEState createInitialState(final SpacecraftState initialState) {

  557.         // retrieve initial state
  558.         final double[] primary = new double[getBasicDimension()];
  559.         stateMapper.mapStateToArray(initialState, primary, null);

  561.         if (secondaryOffsets.isEmpty()) {
  562.             // compute dimension of the secondary state
  563.             int offset = 0;
  564.             for (final AdditionalDerivativesProvider provider : additionalDerivativesProviders) {
  565.                 secondaryOffsets.put(provider.getName(), offset);
  566.                 offset += provider.getDimension();
  567.             }
  568.             secondaryOffsets.put(SECONDARY_DIMENSION, offset);
  569.         }

  571.         return new ODEState(0.0, primary, secondary(initialState));

  573.     }

  575.     /** Create secondary state.
  576.      * @param state spacecraft state
  577.      * @return secondary state
  578.      * @since 11.1
  579.      */
  580.     private double[][] secondary(final SpacecraftState state) {

  582.         if (secondaryOffsets.isEmpty()) {
  583.             return null;
  584.         }

  586.         final double[][] secondary = new double[1][secondaryOffsets.get(SECONDARY_DIMENSION)];
  587.         for (final AdditionalDerivativesProvider provider : additionalDerivativesProviders) {
  588.             final String   name       = provider.getName();
  589.             final int      offset     = secondaryOffsets.get(name);
  590.             final double[] additional = state.getAdditionalState(name);
  591.             System.arraycopy(additional, 0, secondary[0], offset, additional.length);
  592.         }

  594.         return secondary;

  596.     }

  598.     /** Create secondary state derivative.
  599.      * @param state spacecraft state
  600.      * @return secondary state derivative
  601.      * @since 11.1
  602.      */
  603.     private double[][] secondaryDerivative(final SpacecraftState state) {

  605.         if (secondaryOffsets.isEmpty()) {
  606.             return null;
  607.         }

  609.         final double[][] secondaryDerivative = new double[1][secondaryOffsets.get(SECONDARY_DIMENSION)];
  610.         for (final AdditionalDerivativesProvider provider : additionalDerivativesProviders) {
  611.             final String   name       = provider.getName();
  612.             final int      offset     = secondaryOffsets.get(name);
  613.             final double[] additionalDerivative = state.getAdditionalStateDerivative(name);
  614.             System.arraycopy(additionalDerivative, 0, secondaryDerivative[0], offset, additionalDerivative.length);
  615.         }

  617.         return secondaryDerivative;

  619.     }

  621.     /** Create an ODE with all equations.
  622.      * @param integ numerical integrator to use for propagation.
  623.      * @return a new ode
  624.      */
  625.     private ExpandableODE createODE(final ODEIntegrator integ) {

  627.         final ExpandableODE ode =
  628.                 new ExpandableODE(new ConvertedMainStateEquations(getMainStateEquations(integ)));

  630.         // secondary part of the ODE
  631.         if (!additionalDerivativesProviders.isEmpty()) {
  632.             ode.addSecondaryEquations(new ConvertedSecondaryStateEquations());
  633.         }

  635.         return ode;

  637.     }

  639.     /** Method called just before integration.
  640.      * <p>
  641.      * The default implementation does nothing, it may be specialized in subclasses.
  642.      * </p>
  643.      * @param initialState initial state
  644.      * @param tEnd target date at which state should be propagated
  645.      */
  646.     protected void beforeIntegration(final SpacecraftState initialState,
  647.                                      final AbsoluteDate tEnd) {
  648.         // do nothing by default
  649.     }

  651.     /** Method called just after integration.
  652.      * <p>
  653.      * The default implementation does nothing, it may be specialized in subclasses.
  654.      * </p>
  655.      */
  656.     protected void afterIntegration() {
  657.         // do nothing by default
  658.     }

  660.     /** Get state vector dimension without additional parameters.
  661.      * @return state vector dimension without additional parameters.
  662.      */
  663.     public int getBasicDimension() {
  664.         return 7;
  665.     }

  667.     /** Get the integrator used by the propagator.
  668.      * @return the integrator.
  669.      */
  670.     protected ODEIntegrator getIntegrator() {
  671.         return integrator;
  672.     }

  674.     /** Convert a state from mathematical world to space flight dynamics world.
  675.      * @param os mathematical state
  676.      * @return space flight dynamics state
  677.      */
  678.     private SpacecraftState convert(final ODEStateAndDerivative os) {

  680.         final SpacecraftState s = stateMapper.mapArrayToState(os.getTime(), os.getPrimaryState(),
  681.             os.getPrimaryDerivative(), propagationType);
  682.         return updateAdditionalStatesAndDerivatives(s, os);
  683.     }

  685.     /** Convert a state from space flight dynamics world to mathematical world.
  686.      * @param state space flight dynamics state
  687.      * @return mathematical state
  688.      */
  689.     private ODEStateAndDerivative convert(final SpacecraftState state) {

  691.         // retrieve initial state
  692.         final double[] primary    = new double[getBasicDimension()];
  693.         final double[] primaryDot = new double[getBasicDimension()];
  694.         stateMapper.mapStateToArray(state, primary, primaryDot);

  696.         // secondary part of the ODE
  697.         final double[][] secondary           = secondary(state);
  698.         final double[][] secondaryDerivative = secondaryDerivative(state);

  700.         return new ODEStateAndDerivative(stateMapper.mapDateToDouble(state.getDate()),
  701.                                          primary, primaryDot,
  702.                                          secondary, secondaryDerivative);

  704.     }

  706.     /** Differential equations for the main state (orbit, attitude and mass). */
  707.     public interface MainStateEquations {

  709.         /**
  710.          * Initialize the equations at the start of propagation. This method will be
  711.          * called before any calls to {@link #computeDerivatives(SpacecraftState)}.
  712.          *
  713.          * <p> The default implementation of this method does nothing.
  714.          *
  715.          * @param initialState initial state information at the start of propagation.
  716.          * @param target       date of propagation. Not equal to {@code
  717.          *                     initialState.getDate()}.
  718.          */
  719.         default void init(final SpacecraftState initialState, final AbsoluteDate target) {
  720.         }

  722.         /** Compute differential equations for main state.
  723.          * @param state current state
  724.          * @return derivatives of main state
  725.          */
  726.         double[] computeDerivatives(SpacecraftState state);

  728.     }

  730.     /** Differential equations for the main state (orbit, attitude and mass), with converted API. */
  731.     private class ConvertedMainStateEquations implements OrdinaryDifferentialEquation {

  733.         /** Main state equations. */
  734.         private final MainStateEquations main;

  736.         /** Simple constructor.
  737.          * @param main main state equations
  738.          */
  739.         ConvertedMainStateEquations(final MainStateEquations main) {
  740.             this.main = main;
  741.             calls = 0;
  742.         }

  744.         /** {@inheritDoc} */
  745.         public int getDimension() {
  746.             return getBasicDimension();
  747.         }

  749.         @Override
  750.         public void init(final double t0, final double[] y0, final double finalTime) {
  751.             // update space dynamics view
  752.             SpacecraftState initialState = stateMapper.mapArrayToState(t0, y0, null, PropagationType.MEAN);
  753.             initialState = updateAdditionalStates(initialState);
  754.             initialState = updateStatesFromAdditionalDerivativesIfKnown(initialState);
  755.             final AbsoluteDate target = stateMapper.mapDoubleToDate(finalTime);
  756.             main.init(initialState, target);
  757.             attitudeProviderForDerivatives = initializeAttitudeProviderForDerivatives();
  758.         }

  760.         /**
  761.          * Returns an updated version of the inputted state, with additional states from
  762.          * derivatives providers as given in the stored initial state.
  763.          * @param originalState input state
  764.          * @return new state
  765.          * @since 12.1
  766.          */
  767.         private SpacecraftState updateStatesFromAdditionalDerivativesIfKnown(final SpacecraftState originalState) {
  768.             SpacecraftState updatedState = originalState;
  769.             final SpacecraftState storedInitialState = getInitialState();
  770.             final double originalTime = stateMapper.mapDateToDouble(originalState.getDate());
  771.             if (storedInitialState != null && stateMapper.mapDateToDouble(storedInitialState.getDate()) == originalTime) {
  772.                 for (final AdditionalDerivativesProvider provider: additionalDerivativesProviders) {
  773.                     final String name = provider.getName();
  774.                     final double[] value = storedInitialState.getAdditionalState(name);
  775.                     updatedState = updatedState.addAdditionalState(name, value);
  776.                 }
  777.             }
  778.             return updatedState;
  779.         }

  781.         /** {@inheritDoc} */
  782.         public double[] computeDerivatives(final double t, final double[] y) {

  784.             // increment calls counter
  785.             ++calls;

  787.             // update space dynamics view
  788.             stateMapper.setAttitudeProvider(attitudeProviderForDerivatives);
  789.             SpacecraftState currentState = stateMapper.mapArrayToState(t, y, null, PropagationType.MEAN);
  790.             stateMapper.setAttitudeProvider(getAttitudeProvider());

  792.             currentState = updateAdditionalStates(currentState);
  793.             // compute main state differentials
  794.             return main.computeDerivatives(currentState);

  796.         }

  798.     }

  800.     /** Differential equations for the secondary state (Jacobians, user variables ...), with converted API. */
  801.     private class ConvertedSecondaryStateEquations implements SecondaryODE {

  803.         /** Dimension of the combined additional states. */
  804.         private final int combinedDimension;

  806.         /** Simple constructor.
  807.           */
  808.         ConvertedSecondaryStateEquations() {
  809.             this.combinedDimension = secondaryOffsets.get(SECONDARY_DIMENSION);
  810.         }

  812.         /** {@inheritDoc} */
  813.         @Override
  814.         public int getDimension() {
  815.             return combinedDimension;
  816.         }

  818.         /** {@inheritDoc} */
  819.         @Override
  820.         public void init(final double t0, final double[] primary0,
  821.                          final double[] secondary0, final double finalTime) {
  822.             // update space dynamics view
  823.             final SpacecraftState initialState = convert(t0, primary0, null, secondary0);

  825.             final AbsoluteDate target = stateMapper.mapDoubleToDate(finalTime);
  826.             for (final AdditionalDerivativesProvider provider : additionalDerivativesProviders) {
  827.                 provider.init(initialState, target);
  828.             }

  830.         }

  832.         /** {@inheritDoc} */
  833.         @Override
  834.         public double[] computeDerivatives(final double t, final double[] primary,
  835.                                            final double[] primaryDot, final double[] secondary) {

  837.             // update space dynamics view
  838.             // the integrable generators generate method will be called here,
  839.             // according to the generators yield order
  840.             SpacecraftState updated = convert(t, primary, primaryDot, secondary);

  842.             // set up queue for equations
  843.             final Queue<AdditionalDerivativesProvider> pending = new LinkedList<>(additionalDerivativesProviders);

  845.             // gather the derivatives from all additional equations, taking care of dependencies
  846.             final double[] secondaryDot = new double[combinedDimension];
  847.             int yieldCount = 0;
  848.             while (!pending.isEmpty()) {
  849.                 final AdditionalDerivativesProvider provider = pending.remove();
  850.                 if (provider.yields(updated)) {
  851.                     // this provider has to wait for another one,
  852.                     // we put it again in the pending queue
  853.                     pending.add(provider);
  854.                     if (++yieldCount >= pending.size()) {
  855.                         // all pending providers yielded!, they probably need data not yet initialized
  856.                         // we let the propagation proceed, if these data are really needed right now
  857.                         // an appropriate exception will be triggered when caller tries to access them
  858.                         break;
  859.                     }
  860.                 } else {
  861.                     // we can use these equations right now
  862.                     final String              name           = provider.getName();
  863.                     final int                 offset         = secondaryOffsets.get(name);
  864.                     final int                 dimension      = provider.getDimension();
  865.                     final CombinedDerivatives derivatives    = provider.combinedDerivatives(updated);
  866.                     final double[]            additionalPart = derivatives.getAdditionalDerivatives();
  867.                     final double[]            mainPart       = derivatives.getMainStateDerivativesIncrements();
  868.                     System.arraycopy(additionalPart, 0, secondaryDot, offset, dimension);
  869.                     updated = updated.addAdditionalStateDerivative(name, additionalPart);
  870.                     if (mainPart != null) {
  871.                         // this equation does change the main state derivatives
  872.                         for (int i = 0; i < mainPart.length; ++i) {
  873.                             primaryDot[i] += mainPart[i];
  874.                         }
  875.                     }
  876.                     yieldCount = 0;
  877.                 }
  878.             }

  880.             return secondaryDot;

  882.         }

  884.         /** Convert mathematical view to space view.
  885.          * @param t current value of the independent <I>time</I> variable
  886.          * @param primary array containing the current value of the primary state vector
  887.          * @param primaryDot array containing the derivative of the primary state vector
  888.          * @param secondary array containing the current value of the secondary state vector
  889.          * @return space view of the state
  890.          */
  891.         private SpacecraftState convert(final double t, final double[] primary,
  892.                                         final double[] primaryDot, final double[] secondary) {

  894.             SpacecraftState initialState = stateMapper.mapArrayToState(t, primary, primaryDot, PropagationType.MEAN);

  896.             for (final AdditionalDerivativesProvider provider : additionalDerivativesProviders) {
  897.                 final String name      = provider.getName();
  898.                 final int    offset    = secondaryOffsets.get(name);
  899.                 final int    dimension = provider.getDimension();
  900.                 initialState = initialState.addAdditionalState(name, Arrays.copyOfRange(secondary, offset, offset + dimension));
  901.             }

  903.             return updateAdditionalStates(initialState);

  905.         }

  907.     }

  909.     /** Adapt an {@link org.orekit.propagation.events.EventDetector}
  910.      * to Hipparchus {@link org.hipparchus.ode.events.ODEEventDetector} interface.
  911.      * @author Fabien Maussion
  912.      */
  913.     private class AdaptedEventDetector implements ODEEventDetector {

  915.         /** Underlying event detector. */
  916.         private final EventDetector detector;

  918.         /** Underlying event handler.
  919.          * @since 12.0
  920.          */
  921.         private final EventHandler handler;

  923.         /** Time of the previous call to g. */
  924.         private double lastT;

  926.         /** Value from the previous call to g. */
  927.         private double lastG;

  929.         /** Build a wrapped event detector.
  930.          * @param detector event detector to wrap
  931.         */
  932.         AdaptedEventDetector(final EventDetector detector) {
  933.             this.detector = detector;
  934.             this.handler  = detector.getHandler();
  935.             this.lastT    = Double.NaN;
  936.             this.lastG    = Double.NaN;
  937.         }

  939.         /** {@inheritDoc} */
  940.         @Override
  941.         public AdaptableInterval getMaxCheckInterval() {
  942.             return s -> detector.getMaxCheckInterval().currentInterval(convert(s));
  943.         }

  945.         /** {@inheritDoc} */
  946.         @Override
  947.         public int getMaxIterationCount() {
  948.             return detector.getMaxIterationCount();
  949.         }

  951.         /** {@inheritDoc} */
  952.         @Override
  953.         public BracketedUnivariateSolver<UnivariateFunction> getSolver() {
  954.             return new BracketingNthOrderBrentSolver(0, detector.getThreshold(), 0, 5);
  955.         }

  957.         /** {@inheritDoc} */
  958.         @Override
  959.         public void init(final ODEStateAndDerivative s0, final double t) {
  960.             detector.init(convert(s0), stateMapper.mapDoubleToDate(t));
  961.             this.lastT = Double.NaN;
  962.             this.lastG = Double.NaN;
  963.         }

  965.         /** {@inheritDoc} */
  966.         public double g(final ODEStateAndDerivative s) {
  967.             if (!Precision.equals(lastT, s.getTime(), 0)) {
  968.                 lastT = s.getTime();
  969.                 lastG = detector.g(convert(s));
  970.             }
  971.             return lastG;
  972.         }

  974.         /** {@inheritDoc} */
  975.         public ODEEventHandler getHandler() {

  977.             return new ODEEventHandler() {

  979.                 /** {@inheritDoc} */
  980.                 public Action eventOccurred(final ODEStateAndDerivative s, final ODEEventDetector d, final boolean increasing) {
  981.                     return handler.eventOccurred(convert(s), detector, increasing);
  982.                 }

  984.                 /** {@inheritDoc} */
  985.                 @Override
  986.                 public ODEState resetState(final ODEEventDetector d, final ODEStateAndDerivative s) {

  988.                     final SpacecraftState oldState = convert(s);
  989.                     final SpacecraftState newState = handler.resetState(detector, oldState);
  990.                     stateChanged(newState);

  992.                     // main part
  993.                     final double[] primary    = new double[s.getPrimaryStateDimension()];
  994.                     stateMapper.mapStateToArray(newState, primary, null);

  996.                     // secondary part
  997.                     final double[][] secondary = new double[1][secondaryOffsets.get(SECONDARY_DIMENSION)];
  998.                     for (final AdditionalDerivativesProvider provider : additionalDerivativesProviders) {
  999.                         final String name      = provider.getName();
  1000.                         final int    offset    = secondaryOffsets.get(name);
  1001.                         final int    dimension = provider.getDimension();
  1002.                         System.arraycopy(newState.getAdditionalState(name), 0, secondary[0], offset, dimension);
  1003.                     }

  1005.                     return new ODEState(newState.getDate().durationFrom(getStartDate()),
  1006.                                         primary, secondary);

  1008.                 }

  1010.             };
  1011.         }

  1013.     }

  1015.     /** Adapt an {@link org.orekit.propagation.sampling.OrekitStepHandler}
  1016.      * to Hipparchus {@link ODEStepHandler} interface.
  1017.      * @author Luc Maisonobe
  1018.      */
  1019.     private class AdaptedStepHandler implements ODEStepHandler {

  1021.         /** Underlying handler. */
  1022.         private final OrekitStepHandler handler;

  1024.         /** Build an instance.
  1025.          * @param handler underlying handler to wrap
  1026.          */
  1027.         AdaptedStepHandler(final OrekitStepHandler handler) {
  1028.             this.handler = handler;
  1029.         }

  1031.         /** {@inheritDoc} */
  1032.         @Override
  1033.         public void init(final ODEStateAndDerivative s0, final double t) {
  1034.             handler.init(convert(s0), stateMapper.mapDoubleToDate(t));
  1035.         }

  1037.         /** {@inheritDoc} */
  1038.         @Override
  1039.         public void handleStep(final ODEStateInterpolator interpolator) {
  1040.             handler.handleStep(new AdaptedStepInterpolator(interpolator));
  1041.         }

  1043.         /** {@inheritDoc} */
  1044.         @Override
  1045.         public void finish(final ODEStateAndDerivative finalState) {
  1046.             handler.finish(convert(finalState));
  1047.         }

  1049.     }

  1051.     /** Adapt an Hipparchus {@link ODEStateInterpolator}
  1052.      * to an orekit {@link OrekitStepInterpolator} interface.
  1053.      * @author Luc Maisonobe
  1054.      */
  1055.     private class AdaptedStepInterpolator implements OrekitStepInterpolator {

  1057.         /** Underlying raw rawInterpolator. */
  1058.         private final ODEStateInterpolator mathInterpolator;

  1060.         /** Simple constructor.
  1061.          * @param mathInterpolator underlying raw interpolator
  1062.          */
  1063.         AdaptedStepInterpolator(final ODEStateInterpolator mathInterpolator) {
  1064.             this.mathInterpolator = mathInterpolator;
  1065.         }

  1067.         /** {@inheritDoc}} */
  1068.         @Override
  1069.         public SpacecraftState getPreviousState() {
  1070.             return convert(mathInterpolator.getPreviousState());
  1071.         }

  1073.         /** {@inheritDoc}} */
  1074.         @Override
  1075.         public boolean isPreviousStateInterpolated() {
  1076.             return mathInterpolator.isPreviousStateInterpolated();
  1077.         }

  1079.         /** {@inheritDoc}} */
  1080.         @Override
  1081.         public SpacecraftState getCurrentState() {
  1082.             return convert(mathInterpolator.getCurrentState());
  1083.         }

  1085.         /** {@inheritDoc}} */
  1086.         @Override
  1087.         public boolean isCurrentStateInterpolated() {
  1088.             return mathInterpolator.isCurrentStateInterpolated();
  1089.         }

  1091.         /** {@inheritDoc}} */
  1092.         @Override
  1093.         public SpacecraftState getInterpolatedState(final AbsoluteDate date) {
  1094.             return convert(mathInterpolator.getInterpolatedState(date.durationFrom(stateMapper.getReferenceDate())));
  1095.         }

  1097.         /** {@inheritDoc}} */
  1098.         @Override
  1099.         public boolean isForward() {
  1100.             return mathInterpolator.isForward();
  1101.         }

  1103.         /** {@inheritDoc}} */
  1104.         @Override
  1105.         public AdaptedStepInterpolator restrictStep(final SpacecraftState newPreviousState,
  1106.                                                     final SpacecraftState newCurrentState) {
  1107.             try {
  1108.                 final AbstractODEStateInterpolator aosi = (AbstractODEStateInterpolator) mathInterpolator;
  1109.                 return new AdaptedStepInterpolator(aosi.restrictStep(convert(newPreviousState),
  1110.                                                                      convert(newCurrentState)));
  1111.             } catch (ClassCastException cce) {
  1112.                 // this should never happen
  1113.                 throw new OrekitInternalError(cce);
  1114.             }
  1115.         }

  1117.     }

  1119.     /** Specialized step handler storing interpolators for ephemeris generation.
  1120.      * @since 11.0
  1121.      */
  1122.     private class StoringStepHandler implements ODEStepHandler, EphemerisGenerator {

  1124.         /** Underlying raw mathematical model. */
  1125.         private DenseOutputModel model;

  1127.         /** the user supplied end date. Propagation may not end on this date. */
  1128.         private AbsoluteDate endDate;

  1130.         /** Generated ephemeris. */
  1131.         private BoundedPropagator ephemeris;

  1133.         /** Last interpolator handled by the object.*/
  1134.         private  ODEStateInterpolator lastInterpolator;

  1136.         /** Set the end date.
  1137.          * @param endDate end date
  1138.          */
  1139.         public void setEndDate(final AbsoluteDate endDate) {
  1140.             this.endDate = endDate;
  1141.         }

  1143.         /** {@inheritDoc} */
  1144.         @Override
  1145.         public void init(final ODEStateAndDerivative s0, final double t) {

  1147.             this.model = new DenseOutputModel();
  1148.             model.init(s0, t);

  1150.             // ephemeris will be generated when last step is processed
  1151.             this.ephemeris = null;

  1153.             this.lastInterpolator = null;

  1155.         }

  1157.         /** {@inheritDoc} */
  1158.         @Override
  1159.         public BoundedPropagator getGeneratedEphemeris() {
  1160.             // Each time we try to get the ephemeris, rebuild it using the last data.
  1161.             buildEphemeris();
  1162.             return ephemeris;
  1163.         }

  1165.         /** {@inheritDoc} */
  1166.         @Override
  1167.         public void handleStep(final ODEStateInterpolator interpolator) {
  1168.             model.handleStep(interpolator);
  1169.             lastInterpolator = interpolator;
  1170.         }

  1172.         /** {@inheritDoc} */
  1173.         @Override
  1174.         public void finish(final ODEStateAndDerivative finalState) {
  1175.             buildEphemeris();
  1176.         }

  1178.         /** Method used to produce ephemeris at a given time.
  1179.          * Can be used at multiple times, updating the ephemeris to
  1180.          * its last state.
  1181.          */
  1182.         private void buildEphemeris() {
  1183.             // buildEphemeris was built in order to allow access to what was previously the finish method.
  1184.             // This now allows to call it through getGeneratedEphemeris, therefore through an external call,
  1185.             // which was not previously the case.

  1187.             // Update the model's finalTime with the last interpolator.
  1188.             model.finish(lastInterpolator.getCurrentState());

  1190.             // set up the boundary dates
  1191.             final double tI = model.getInitialTime();
  1192.             final double tF = model.getFinalTime();
  1193.             // tI is almost? always zero
  1194.             final AbsoluteDate startDate =
  1195.                             stateMapper.mapDoubleToDate(tI);
  1196.             final AbsoluteDate finalDate =
  1197.                             stateMapper.mapDoubleToDate(tF, this.endDate);
  1198.             final AbsoluteDate minDate;
  1199.             final AbsoluteDate maxDate;
  1200.             if (tF < tI) {
  1201.                 minDate = finalDate;
  1202.                 maxDate = startDate;
  1203.             } else {
  1204.                 minDate = startDate;
  1205.                 maxDate = finalDate;
  1206.             }

  1208.             // get the initial additional states that are not managed
  1209.             final DoubleArrayDictionary unmanaged = new DoubleArrayDictionary();
  1210.             for (final DoubleArrayDictionary.Entry initial : getInitialState().getAdditionalStatesValues().getData()) {
  1211.                 if (!isAdditionalStateManaged(initial.getKey())) {
  1212.                     // this additional state was in the initial state, but is unknown to the propagator
  1213.                     // we simply copy its initial value as is
  1214.                     unmanaged.put(initial.getKey(), initial.getValue());
  1215.                 }
  1216.             }

  1218.             // get the names of additional states managed by differential equations
  1219.             final String[] names      = new String[additionalDerivativesProviders.size()];
  1220.             final int[]    dimensions = new int[additionalDerivativesProviders.size()];
  1221.             for (int i = 0; i < names.length; ++i) {
  1222.                 names[i] = additionalDerivativesProviders.get(i).getName();
  1223.                 dimensions[i] = additionalDerivativesProviders.get(i).getDimension();
  1224.             }

  1226.             // create the ephemeris
  1227.             ephemeris = new IntegratedEphemeris(startDate, minDate, maxDate,
  1228.                                                 stateMapper, propagationType, model,
  1229.                                                 unmanaged, getAdditionalStateProviders(),
  1230.                                                 names, dimensions);

  1232.         }

  1234.     }

  1236.     /** Wrapper for resetting an integrator handlers.
  1237.      * <p>
  1238.      * This class is intended to be used in a try-with-resource statement.
  1239.      * If propagator-specific event handlers and step handlers are added to
  1240.      * the integrator in the try block, they will be removed automatically
  1241.      * when leaving the block, so the integrator only keeps its own handlers
  1242.      * between calls to {@link AbstractIntegratedPropagator#propagate(AbsoluteDate, AbsoluteDate).
  1243.      * </p>
  1244.      * @since 11.0
  1245.      */
  1246.     private static class IntegratorResetter implements AutoCloseable {

  1248.         /** Wrapped integrator. */
  1249.         private final ODEIntegrator integrator;

  1251.         /** Initial event detectors list. */
  1252.         private final List<ODEEventDetector> detectors;

  1254.         /** Initial step handlers list. */
  1255.         private final List<ODEStepHandler> stepHandlers;

  1257.         /** Simple constructor.
  1258.          * @param integrator wrapped integrator
  1259.          */
  1260.         IntegratorResetter(final ODEIntegrator integrator) {
  1261.             this.integrator   = integrator;
  1262.             this.detectors    = new ArrayList<>(integrator.getEventDetectors());
  1263.             this.stepHandlers = new ArrayList<>(integrator.getStepHandlers());
  1264.         }

  1266.         /** {@inheritDoc}
  1267.          * <p>
  1268.          * Reset event handlers and step handlers back to the initial list
  1269.          * </p>
  1270.          */
  1271.         @Override
  1272.         public void close() {

  1274.             // reset event handlers
  1275.             integrator.clearEventDetectors();
  1276.             detectors.forEach(integrator::addEventDetector);

  1278.             // reset step handlers
  1279.             integrator.clearStepHandlers();
  1280.             stepHandlers.forEach(integrator::addStepHandler);

  1282.         }

  1284.     }

  1286. }
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