FieldAbstractIntegratedPropagator.java

  1. /* Copyright 2002-2022 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.CalculusFieldElement;
  30. import org.hipparchus.Field;
  31. import org.hipparchus.exception.MathIllegalArgumentException;
  32. import org.hipparchus.exception.MathIllegalStateException;
  33. import org.hipparchus.ode.FieldDenseOutputModel;
  34. import org.hipparchus.ode.FieldExpandableODE;
  35. import org.hipparchus.ode.FieldODEIntegrator;
  36. import org.hipparchus.ode.FieldODEState;
  37. import org.hipparchus.ode.FieldODEStateAndDerivative;
  38. import org.hipparchus.ode.FieldOrdinaryDifferentialEquation;
  39. import org.hipparchus.ode.FieldSecondaryODE;
  40. import org.hipparchus.ode.events.Action;
  41. import org.hipparchus.ode.events.FieldEventHandlerConfiguration;
  42. import org.hipparchus.ode.events.FieldODEEventHandler;
  43. import org.hipparchus.ode.sampling.AbstractFieldODEStateInterpolator;
  44. import org.hipparchus.ode.sampling.FieldODEStateInterpolator;
  45. import org.hipparchus.ode.sampling.FieldODEStepHandler;
  46. import org.hipparchus.util.MathArrays;
  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.PositionAngle;
  55. import org.orekit.propagation.FieldAbstractPropagator;
  56. import org.orekit.propagation.FieldBoundedPropagator;
  57. import org.orekit.propagation.FieldEphemerisGenerator;
  58. import org.orekit.propagation.FieldSpacecraftState;
  59. import org.orekit.propagation.PropagationType;
  60. import org.orekit.propagation.events.FieldEventDetector;
  61. import org.orekit.propagation.sampling.FieldOrekitStepHandler;
  62. import org.orekit.propagation.sampling.FieldOrekitStepInterpolator;
  63. import org.orekit.time.FieldAbsoluteDate;
  64. import org.orekit.utils.FieldArrayDictionary;


  67. /** Common handling of {@link org.orekit.propagation.FieldPropagator FieldPropagator}
  68.  *  methods for both numerical and semi-analytical propagators.
  69.  *  @param <T> the type of the field elements
  70.  *  @author Luc Maisonobe
  71.  */
  72. public abstract class FieldAbstractIntegratedPropagator<T extends CalculusFieldElement<T>> extends FieldAbstractPropagator<T> {

  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<FieldEventDetector<T>> detectors;

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

  85.     /** Integrator selected by the user for the orbital extrapolation process. */
  86.     private final FieldODEIntegrator<T> integrator;

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

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

  98.     /** Counter for differential equations calls. */
  99.     private int calls;

  101.     /** Mapper between raw double components and space flight dynamics objects. */
  102.     private FieldStateMapper<T> stateMapper;

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

  107.     /** Type of orbit to output (mean or osculating) <br/>
  108.      * <p>
  109.      * This is used only in the case of semianalitical propagators where there is a clear separation between
  110.      * mean and short periodic elements. It is ignored by the Numerical propagator.
  111.      * </p>
  112.      */
  113.     private PropagationType propagationType;

  115.     /** Build a new instance.
  116.      * @param integrator numerical integrator to use for propagation.
  117.      * @param propagationType type of orbit to output (mean or osculating).
  118.      * @param field Field used by default
  119.      */
  120.     protected FieldAbstractIntegratedPropagator(final Field<T> field, final FieldODEIntegrator<T> integrator, final PropagationType propagationType) {
  121.         super(field);
  122.         detectors                      = new ArrayList<>();
  123.         ephemerisGenerators            = new ArrayList<>();
  124.         additionalDerivativesProviders = new ArrayList<>();
  125.         this.secondaryOffsets          = new HashMap<>();
  126.         this.integrator                = integrator;
  127.         this.propagationType           = propagationType;
  128.         this.resetAtEnd                = true;
  129.     }

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

  147.     /** Initialize the mapper.
  148.      * @param field Field used by default
  149.      */
  150.     protected void initMapper(final Field<T> field) {
  151.         final T zero = field.getZero();
  152.         stateMapper = createMapper(null, zero.add(Double.NaN), null, null, null, null);
  153.     }

  155.     /**  {@inheritDoc} */
  156.     public void setAttitudeProvider(final AttitudeProvider attitudeProvider) {
  157.         super.setAttitudeProvider(attitudeProvider);
  158.         stateMapper = createMapper(stateMapper.getReferenceDate(), stateMapper.getMu(),
  159.                                    stateMapper.getOrbitType(), stateMapper.getPositionAngleType(),
  160.                                    attitudeProvider, stateMapper.getFrame());
  161.     }

  163.     /** Set propagation orbit type.
  164.      * @param orbitType orbit type to use for propagation
  165.      */
  166.     protected void setOrbitType(final OrbitType orbitType) {
  167.         stateMapper = createMapper(stateMapper.getReferenceDate(), stateMapper.getMu(),
  168.                                    orbitType, stateMapper.getPositionAngleType(),
  169.                                    stateMapper.getAttitudeProvider(), stateMapper.getFrame());
  170.     }

  172.     /** Get propagation parameter type.
  173.      * @return orbit type used for propagation
  174.      */
  175.     protected OrbitType getOrbitType() {
  176.         return stateMapper.getOrbitType();
  177.     }

  179.     /** Check if only the mean elements should be used in a semianalitical propagation.
  180.      * @return {@link PropagationType MEAN} if only mean elements have to be used or
  181.      *         {@link PropagationType OSCULATING} if osculating elements have to be also used.
  182.      */
  183.     protected PropagationType isMeanOrbit() {
  184.         return propagationType;
  185.     }

  187.     /** Set position angle type.
  188.      * <p>
  189.      * The position parameter type is meaningful only if {@link
  190.      * #getOrbitType() propagation orbit type}
  191.      * support it. As an example, it is not meaningful for propagation
  192.      * in {@link OrbitType#CARTESIAN Cartesian} parameters.
  193.      * </p>
  194.      * @param positionAngleType angle type to use for propagation
  195.      */
  196.     protected void setPositionAngleType(final PositionAngle positionAngleType) {
  197.         stateMapper = createMapper(stateMapper.getReferenceDate(), stateMapper.getMu(),
  198.                                    stateMapper.getOrbitType(), positionAngleType,
  199.                                    stateMapper.getAttitudeProvider(), stateMapper.getFrame());
  200.     }

  202.     /** Get propagation parameter type.
  203.      * @return angle type to use for propagation
  204.      */
  205.     protected PositionAngle getPositionAngleType() {
  206.         return stateMapper.getPositionAngleType();
  207.     }

  209.     /** Set the central attraction coefficient μ.
  210.      * @param mu central attraction coefficient (m³/s²)
  211.      */
  212.     public void setMu(final T mu) {
  213.         stateMapper = createMapper(stateMapper.getReferenceDate(), mu,
  214.                                    stateMapper.getOrbitType(), stateMapper.getPositionAngleType(),
  215.                                    stateMapper.getAttitudeProvider(), stateMapper.getFrame());
  216.     }

  218.     /** Get the central attraction coefficient μ.
  219.      * @return mu central attraction coefficient (m³/s²)
  220.      * @see #setMu(CalculusFieldElement)
  221.      */
  222.     public T getMu() {
  223.         return stateMapper.getMu();
  224.     }

  226.     /** Get the number of calls to the differential equations computation method.
  227.      * <p>The number of calls is reset each time the {@link #propagate(FieldAbsoluteDate)}
  228.      * method is called.</p>
  229.      * @return number of calls to the differential equations computation method
  230.      */
  231.     public int getCalls() {
  232.         return calls;
  233.     }

  235.     /** {@inheritDoc} */
  236.     @Override
  237.     public boolean isAdditionalStateManaged(final String name) {

  239.         // first look at already integrated states
  240.         if (super.isAdditionalStateManaged(name)) {
  241.             return true;
  242.         }

  244.         // then look at states we integrate ourselves
  245.         for (final FieldAdditionalDerivativesProvider<T> provider : additionalDerivativesProviders) {
  246.             if (provider.getName().equals(name)) {
  247.                 return true;
  248.             }
  249.         }

  251.         return false;
  252.     }

  254.     /** {@inheritDoc} */
  255.     @Override
  256.     public String[] getManagedAdditionalStates() {
  257.         final String[] alreadyIntegrated = super.getManagedAdditionalStates();
  258.         final String[] managed = new String[alreadyIntegrated.length + additionalDerivativesProviders.size()];
  259.         System.arraycopy(alreadyIntegrated, 0, managed, 0, alreadyIntegrated.length);
  260.         for (int i = 0; i < additionalDerivativesProviders.size(); ++i) {
  261.             managed[i + alreadyIntegrated.length] = additionalDerivativesProviders.get(i).getName();
  262.         }
  263.         return managed;
  264.     }

  266.     /** Add a set of user-specified equations to be integrated along with the orbit propagation.
  267.      * @param additional additional equations
  268.      * @deprecated as of 11.1, replaced by {@link #addAdditionalDerivativesProvider(FieldAdditionalDerivativesProvider)}
  269.      */
  270.     @Deprecated
  271.     public void addAdditionalEquations(final FieldAdditionalEquations<T> additional) {
  272.         addAdditionalDerivativesProvider(new FieldAdditionalEquationsAdapter<>(additional, this::getInitialState));
  273.     }

  275.     /** Add a provider for user-specified state derivatives to be integrated along with the orbit propagation.
  276.      * @param provider provider for additional derivatives
  277.      * @see #addAdditionalStateProvider(org.orekit.propagation.FieldAdditionalStateProvider)
  278.      * @since 11.1
  279.      */
  280.     public void addAdditionalDerivativesProvider(final FieldAdditionalDerivativesProvider<T> provider) {
  281.         // check if the name is already used
  282.         if (isAdditionalStateManaged(provider.getName())) {
  283.             // these derivatives are already registered, complain
  284.             throw new OrekitException(OrekitMessages.ADDITIONAL_STATE_NAME_ALREADY_IN_USE,
  285.                                       provider.getName());
  286.         }

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

  291.         secondaryOffsets.clear();

  293.     }

  295.     /** Get an unmodifiable list of providers for additional derivatives.
  296.      * @return providers for additional derivatives
  297.      * @since 11.1
  298.      */
  299.     public List<FieldAdditionalDerivativesProvider<T>> getAdditionalDerivativesProviders() {
  300.         return Collections.unmodifiableList(additionalDerivativesProviders);
  301.     }

  303.     /** {@inheritDoc} */
  304.     public <D extends FieldEventDetector<T>> void addEventDetector(final D detector) {
  305.         detectors.add(detector);
  306.     }

  308.     /** {@inheritDoc} */
  309.     public Collection<FieldEventDetector<T>> getEventsDetectors() {
  310.         return Collections.unmodifiableCollection(detectors);
  311.     }

  313.     /** {@inheritDoc} */
  314.     public void clearEventsDetectors() {
  315.         detectors.clear();
  316.     }

  318.     /** Set up all user defined event detectors.
  319.      */
  320.     protected void setUpUserEventDetectors() {
  321.         for (final FieldEventDetector<T> detector : detectors) {
  322.             setUpEventDetector(integrator, detector);
  323.         }
  324.     }

  326.     /** Wrap an Orekit event detector and register it to the integrator.
  327.      * @param integ integrator into which event detector should be registered
  328.      * @param detector event detector to wrap
  329.      */
  330.     protected void setUpEventDetector(final FieldODEIntegrator<T> integ, final FieldEventDetector<T> detector) {
  331.         integ.addEventHandler(new FieldAdaptedEventDetector(detector),
  332.                               detector.getMaxCheckInterval().getReal(),
  333.                               detector.getThreshold().getReal(),
  334.                               detector.getMaxIterationCount());
  335.     }

  337.     /** {@inheritDoc} */
  338.     @Override
  339.     public FieldEphemerisGenerator<T> getEphemerisGenerator() {
  340.         final FieldStoringStepHandler storingHandler = new FieldStoringStepHandler();
  341.         ephemerisGenerators.add(storingHandler);
  342.         return storingHandler;
  343.     }

  345.     /** Create a mapper between raw double components and spacecraft state.
  346.     /** Simple constructor.
  347.      * <p>
  348.      * The position parameter type is meaningful only if {@link
  349.      * #getOrbitType() propagation orbit type}
  350.      * support it. As an example, it is not meaningful for propagation
  351.      * in {@link OrbitType#CARTESIAN Cartesian} parameters.
  352.      * </p>
  353.      * @param referenceDate reference date
  354.      * @param mu central attraction coefficient (m³/s²)
  355.      * @param orbitType orbit type to use for mapping
  356.      * @param positionAngleType angle type to use for propagation
  357.      * @param attitudeProvider attitude provider
  358.      * @param frame inertial frame
  359.      * @return new mapper
  360.      */
  361.     protected abstract FieldStateMapper<T> createMapper(FieldAbsoluteDate<T> referenceDate, T mu,
  362.                                                         OrbitType orbitType, PositionAngle positionAngleType,
  363.                                                         AttitudeProvider attitudeProvider, Frame frame);

  365.     /** Get the differential equations to integrate (for main state only).
  366.      * @param integ numerical integrator to use for propagation.
  367.      * @return differential equations for main state
  368.      */
  369.     protected abstract MainStateEquations<T> getMainStateEquations(FieldODEIntegrator<T> integ);

  371.     /** {@inheritDoc} */
  372.     public FieldSpacecraftState<T> propagate(final FieldAbsoluteDate<T> target) {
  373.         if (getStartDate() == null) {
  374.             if (getInitialState() == null) {
  375.                 throw new OrekitException(OrekitMessages.INITIAL_STATE_NOT_SPECIFIED_FOR_ORBIT_PROPAGATION);
  376.             }
  377.             setStartDate(getInitialState().getDate());
  378.         }
  379.         return propagate(getStartDate(), target);
  380.     }

  382.     /** {@inheritDoc} */
  383.     public FieldSpacecraftState<T> propagate(final FieldAbsoluteDate<T> tStart, final FieldAbsoluteDate<T> tEnd) {

  385.         if (getInitialState() == null) {
  386.             throw new OrekitException(OrekitMessages.INITIAL_STATE_NOT_SPECIFIED_FOR_ORBIT_PROPAGATION);
  387.         }

  389.         // make sure the integrator will be reset properly even if we change its events handlers and step handlers
  390.         try (IntegratorResetter<T> resetter = new IntegratorResetter<>(integrator)) {

  392.             // Initialize additional states
  393.             initializeAdditionalStates(tEnd);

  395.             if (!tStart.equals(getInitialState().getDate())) {
  396.                 // if propagation start date is not initial date,
  397.                 // propagate from initial to start date without event detection
  398.                 try (IntegratorResetter<T> startResetter = new IntegratorResetter<>(integrator)) {
  399.                     integrateDynamics(tStart);
  400.                 }
  401.             }

  403.             // set up events added by user
  404.             setUpUserEventDetectors();

  406.             // set up step handlers
  407.             for (final FieldOrekitStepHandler<T> handler : getMultiplexer().getHandlers()) {
  408.                 integrator.addStepHandler(new FieldAdaptedStepHandler(handler));
  409.             }
  410.             for (final FieldStoringStepHandler generator : ephemerisGenerators) {
  411.                 generator.setEndDate(tEnd);
  412.                 integrator.addStepHandler(generator);
  413.             }

  415.             // propagate from start date to end date with event detection
  416.             return integrateDynamics(tEnd);

  418.         }

  420.     }

  422.     /** Propagation with or without event detection.
  423.      * @param tEnd target date to which orbit should be propagated
  424.      * @return state at end of propagation
  425.      */
  426.     private FieldSpacecraftState<T> integrateDynamics(final FieldAbsoluteDate<T> tEnd) {
  427.         try {

  429.             initializePropagation();

  431.             if (getInitialState().getDate().equals(tEnd)) {
  432.                 // don't extrapolate
  433.                 return getInitialState();
  434.             }
  435.             // space dynamics view
  436.             stateMapper = createMapper(getInitialState().getDate(), stateMapper.getMu(),
  437.                                        stateMapper.getOrbitType(), stateMapper.getPositionAngleType(),
  438.                                        stateMapper.getAttitudeProvider(), getInitialState().getFrame());


  441.             // set propagation orbit type
  442.             //final FieldOrbit<T> initialOrbit = stateMapper.getOrbitType().convertType(getInitialState().getOrbit());
  443.             if (Double.isNaN(getMu().getReal())) {
  444.                 setMu(getInitialState().getMu());
  445.             }
  446.             if (getInitialState().getMass().getReal() <= 0.0) {
  447.                 throw new OrekitException(OrekitMessages.SPACECRAFT_MASS_BECOMES_NEGATIVE,
  448.                                                getInitialState().getMass());
  449.             }

  451.             // convert space flight dynamics API to math API
  452.             final FieldSpacecraftState<T> initialIntegrationState = getInitialIntegrationState();
  453.             final FieldODEState<T> mathInitialState = createInitialState(initialIntegrationState);
  454.             final FieldExpandableODE<T> mathODE = createODE(integrator, mathInitialState);

  456.             // mathematical integration
  457.             final FieldODEStateAndDerivative<T> mathFinalState;
  458.             beforeIntegration(initialIntegrationState, tEnd);
  459.             mathFinalState = integrator.integrate(mathODE, mathInitialState,
  460.                                                   tEnd.durationFrom(getInitialState().getDate()));

  462.             afterIntegration();

  464.             // get final state
  465.             FieldSpacecraftState<T> finalState =
  466.                             stateMapper.mapArrayToState(stateMapper.mapDoubleToDate(mathFinalState.getTime(), tEnd),
  467.                                                         mathFinalState.getPrimaryState(),
  468.                                                         mathFinalState.getPrimaryDerivative(),
  469.                                                         propagationType);
  470.             if (!additionalDerivativesProviders.isEmpty()) {
  471.                 final T[] secondary            = mathFinalState.getSecondaryState(1);
  472.                 final T[] secondaryDerivatives = mathFinalState.getSecondaryDerivative(1);
  473.                 for (FieldAdditionalDerivativesProvider<T> provider : additionalDerivativesProviders) {
  474.                     final String   name        = provider.getName();
  475.                     final int      offset      = secondaryOffsets.get(name);
  476.                     final int      dimension   = provider.getDimension();
  477.                     finalState = finalState.
  478.                                  addAdditionalState(name, Arrays.copyOfRange(secondary, offset, offset + dimension)).
  479.                                  addAdditionalStateDerivative(name, Arrays.copyOfRange(secondaryDerivatives, offset, offset + dimension));
  480.                 }
  481.             }
  482.             finalState = updateAdditionalStates(finalState);

  484.             if (resetAtEnd) {
  485.                 resetInitialState(finalState);
  486.                 setStartDate(finalState.getDate());
  487.             }

  489.             return finalState;

  491.         } catch (OrekitException pe) {
  492.             throw pe;
  493.         } catch (MathIllegalArgumentException | MathIllegalStateException me) {
  494.             throw OrekitException.unwrap(me);
  495.         }
  496.     }

  498.     /** Get the initial state for integration.
  499.      * @return initial state for integration
  500.      */
  501.     protected FieldSpacecraftState<T> getInitialIntegrationState() {
  502.         return getInitialState();
  503.     }

  505.     /** Create an initial state.
  506.      * @param initialState initial state in flight dynamics world
  507.      * @return initial state in mathematics world
  508.      */
  509.     private FieldODEState<T> createInitialState(final FieldSpacecraftState<T> initialState) {

  511.         // retrieve initial state
  512.         final T[] primary  = MathArrays.buildArray(initialState.getA().getField(), getBasicDimension());
  513.         stateMapper.mapStateToArray(initialState, primary, null);

  515.         if (secondaryOffsets.isEmpty()) {
  516.             // compute dimension of the secondary state
  517.             int offset = 0;
  518.             for (final FieldAdditionalDerivativesProvider<T> provider : additionalDerivativesProviders) {
  519.                 secondaryOffsets.put(provider.getName(), offset);
  520.                 offset += provider.getDimension();
  521.             }
  522.             secondaryOffsets.put(SECONDARY_DIMENSION, offset);
  523.         }

  525.         return new FieldODEState<>(initialState.getA().getField().getZero(), primary, secondary(initialState));

  527.     }

  529.     /** Create secondary state.
  530.      * @param state spacecraft state
  531.      * @return secondary state
  532.      * @since 11.1
  533.      */
  534.     private T[][] secondary(final FieldSpacecraftState<T> state) {

  536.         if (secondaryOffsets.isEmpty()) {
  537.             return null;
  538.         }

  540.         final T[][] secondary = MathArrays.buildArray(state.getDate().getField(), 1, secondaryOffsets.get(SECONDARY_DIMENSION));
  541.         for (final FieldAdditionalDerivativesProvider<T> provider : additionalDerivativesProviders) {
  542.             final String name       = provider.getName();
  543.             final int    offset     = secondaryOffsets.get(name);
  544.             final T[]    additional = state.getAdditionalState(name);
  545.             System.arraycopy(additional, 0, secondary[0], offset, additional.length);
  546.         }

  548.         return secondary;

  550.     }

  552.     /** Create secondary state derivative.
  553.      * @param state spacecraft state
  554.      * @return secondary state derivative
  555.      * @since 11.1
  556.      */
  557.     private T[][] secondaryDerivative(final FieldSpacecraftState<T> state) {

  559.         if (secondaryOffsets.isEmpty()) {
  560.             return null;
  561.         }

  563.         final T[][] secondaryDerivative = MathArrays.buildArray(state.getDate().getField(), 1, secondaryOffsets.get(SECONDARY_DIMENSION));
  564.         for (final FieldAdditionalDerivativesProvider<T> providcer : additionalDerivativesProviders) {
  565.             final String name       = providcer.getName();
  566.             final int    offset     = secondaryOffsets.get(name);
  567.             final T[]    additionalDerivative = state.getAdditionalStateDerivative(name);
  568.             System.arraycopy(additionalDerivative, 0, secondaryDerivative[0], offset, additionalDerivative.length);
  569.         }

  571.         return secondaryDerivative;

  573.     }

  575.     /** Create an ODE with all equations.
  576.      * @param integ numerical integrator to use for propagation.
  577.      * @param mathInitialState initial state
  578.      * @return a new ode
  579.      */
  580.     private FieldExpandableODE<T> createODE(final FieldODEIntegrator<T> integ,
  581.                                     final FieldODEState<T> mathInitialState) {

  583.         final FieldExpandableODE<T> ode =
  584.                 new FieldExpandableODE<>(new ConvertedMainStateEquations(getMainStateEquations(integ)));

  586.         // secondary part of the ODE
  587.         if (!additionalDerivativesProviders.isEmpty()) {
  588.             ode.addSecondaryEquations(new ConvertedSecondaryStateEquations());
  589.         }

  591.         return ode;

  593.     }

  595.     /** Method called just before integration.
  596.      * <p>
  597.      * The default implementation does nothing, it may be specialized in subclasses.
  598.      * </p>
  599.      * @param initialState initial state
  600.      * @param tEnd target date at which state should be propagated
  601.      */
  602.     protected void beforeIntegration(final FieldSpacecraftState<T> initialState,
  603.                                      final FieldAbsoluteDate<T> tEnd) {
  604.         // do nothing by default
  605.     }

  607.     /** Method called just after integration.
  608.      * <p>
  609.      * The default implementation does nothing, it may be specialized in subclasses.
  610.      * </p>
  611.      */
  612.     protected void afterIntegration() {
  613.         // do nothing by default
  614.     }

  616.     /** Get state vector dimension without additional parameters.
  617.      * @return state vector dimension without additional parameters.
  618.      */
  619.     public int getBasicDimension() {
  620.         return 7;

  622.     }

  624.     /** Get the integrator used by the propagator.
  625.      * @return the integrator.
  626.      */
  627.     protected FieldODEIntegrator<T> getIntegrator() {
  628.         return integrator;
  629.     }

  631.     /** Convert a state from mathematical world to space flight dynamics world.
  632.      * @param os mathematical state
  633.      * @return space flight dynamics state
  634.      */
  635.     private FieldSpacecraftState<T> convert(final FieldODEStateAndDerivative<T> os) {

  637.         FieldSpacecraftState<T> s =
  638.                         stateMapper.mapArrayToState(os.getTime(),
  639.                                                     os.getPrimaryState(),
  640.                                                     os.getPrimaryDerivative(),
  641.                                                     propagationType);
  642.         if (os.getNumberOfSecondaryStates() > 0) {
  643.             final T[] secondary           = os.getSecondaryState(1);
  644.             final T[] secondaryDerivative = os.getSecondaryDerivative(1);
  645.             for (final FieldAdditionalDerivativesProvider<T> equations : additionalDerivativesProviders) {
  646.                 final String name      = equations.getName();
  647.                 final int    offset    = secondaryOffsets.get(name);
  648.                 final int    dimension = equations.getDimension();
  649.                 s = s.addAdditionalState(name, Arrays.copyOfRange(secondary, offset, offset + dimension));
  650.                 s = s.addAdditionalStateDerivative(name, Arrays.copyOfRange(secondaryDerivative, offset, offset + dimension));
  651.             }
  652.         }
  653.         s = updateAdditionalStates(s);

  655.         return s;

  657.     }

  659.     /** Convert a state from space flight dynamics world to mathematical world.
  660.      * @param state space flight dynamics state
  661.      * @return mathematical state
  662.      */
  663.     private FieldODEStateAndDerivative<T> convert(final FieldSpacecraftState<T> state) {

  665.         // retrieve initial state
  666.         final T[] primary    = MathArrays.buildArray(getField(), getBasicDimension());
  667.         final T[] primaryDot = MathArrays.buildArray(getField(), getBasicDimension());
  668.         stateMapper.mapStateToArray(state, primary, primaryDot);

  670.         // secondary part of the ODE
  671.         final T[][] secondary           = secondary(state);
  672.         final T[][] secondaryDerivative = secondaryDerivative(state);

  674.         return new FieldODEStateAndDerivative<>(stateMapper.mapDateToDouble(state.getDate()),
  675.                                                 primary, primaryDot,
  676.                                                 secondary, secondaryDerivative);

  678.     }

  680.     /** Differential equations for the main state (orbit, attitude and mass). */
  681.     public interface MainStateEquations<T extends CalculusFieldElement<T>> {

  683.         /**
  684.          * Initialize the equations at the start of propagation. This method will be
  685.          * called before any calls to {@link #computeDerivatives(FieldSpacecraftState)}.
  686.          *
  687.          * <p> The default implementation of this method does nothing.
  688.          *
  689.          * @param initialState initial state information at the start of propagation.
  690.          * @param target       date of propagation. Not equal to {@code
  691.          *                     initialState.getDate()}.
  692.          */
  693.         void init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target);

  695.         /** Compute differential equations for main state.
  696.          * @param state current state
  697.          * @return derivatives of main state
  698.          */
  699.         T[] computeDerivatives(FieldSpacecraftState<T> state);

  701.     }

  703.     /** Differential equations for the main state (orbit, attitude and mass), with converted API. */
  704.     private class ConvertedMainStateEquations implements FieldOrdinaryDifferentialEquation<T> {

  706.         /** Main state equations. */
  707.         private final MainStateEquations<T> main;

  709.         /** Simple constructor.
  710.          * @param main main state equations
  711.          */
  712.         ConvertedMainStateEquations(final MainStateEquations<T> main) {
  713.             this.main = main;
  714.             calls = 0;
  715.         }

  717.         /** {@inheritDoc} */
  718.         public int getDimension() {
  719.             return getBasicDimension();
  720.         }

  722.         @Override
  723.         public void init(final T t0, final T[] y0, final T finalTime) {
  724.             // update space dynamics view
  725.             FieldSpacecraftState<T> initialState = stateMapper.mapArrayToState(t0, y0, null, PropagationType.MEAN);
  726.             initialState = updateAdditionalStates(initialState);
  727.             final FieldAbsoluteDate<T> target = stateMapper.mapDoubleToDate(finalTime);
  728.             main.init(initialState, target);
  729.         }
  730.         /** {@inheritDoc} */
  731.         public T[] computeDerivatives(final T t, final T[] y) {

  733.             // increment calls counter
  734.             ++calls;

  736.             // update space dynamics view
  737.             FieldSpacecraftState<T> currentState = stateMapper.mapArrayToState(t, y, null, PropagationType.MEAN);
  738.             currentState = updateAdditionalStates(currentState);

  740.             // compute main state differentials
  741.             return main.computeDerivatives(currentState);

  743.         }

  745.     }

  747.     /** Differential equations for the secondary state (Jacobians, user variables ...), with converted API. */
  748.     private class ConvertedSecondaryStateEquations implements FieldSecondaryODE<T> {

  750.         /** Dimension of the combined additional states. */
  751.         private final int combinedDimension;

  753.         /** Simple constructor.
  754.          */
  755.         ConvertedSecondaryStateEquations() {
  756.             this.combinedDimension = secondaryOffsets.get(SECONDARY_DIMENSION);
  757.         }

  759.         /** {@inheritDoc} */
  760.         @Override
  761.         public int getDimension() {
  762.             return combinedDimension;
  763.         }

  765.         /** {@inheritDoc} */
  766.         @Override
  767.         public void init(final T t0, final T[] primary0,
  768.                          final T[] secondary0, final T finalTime) {
  769.             // update space dynamics view
  770.             final FieldSpacecraftState<T> initialState = convert(t0, primary0, null, secondary0);

  772.             final FieldAbsoluteDate<T> target = stateMapper.mapDoubleToDate(finalTime);
  773.             for (final FieldAdditionalDerivativesProvider<T> provider : additionalDerivativesProviders) {
  774.                 provider.init(initialState, target);
  775.             }

  777.         }

  779.         /** {@inheritDoc} */
  780.         @Override
  781.         public T[] computeDerivatives(final T t, final T[] primary,
  782.                                       final T[] primaryDot, final T[] secondary) {

  784.             // update space dynamics view
  785.             // the integrable generators generate method will be called here,
  786.             // according to the generators yield order
  787.             FieldSpacecraftState<T> updated = convert(t, primary, primaryDot, secondary);

  789.             // set up queue for equations
  790.             final Queue<FieldAdditionalDerivativesProvider<T>> pending = new LinkedList<>(additionalDerivativesProviders);

  792.             // gather the derivatives from all additional equations, taking care of dependencies
  793.             final T[] secondaryDot = MathArrays.buildArray(t.getField(), combinedDimension);
  794.             int yieldCount = 0;
  795.             while (!pending.isEmpty()) {
  796.                 final FieldAdditionalDerivativesProvider<T> equations = pending.remove();
  797.                 if (equations.yield(updated)) {
  798.                     // these equations have to wait for another set,
  799.                     // we put them again in the pending queue
  800.                     pending.add(equations);
  801.                     if (++yieldCount >= pending.size()) {
  802.                         // all pending equations yielded!, they probably need data not yet initialized
  803.                         // we let the propagation proceed, if these data are really needed right now
  804.                         // an appropriate exception will be triggered when caller tries to access them
  805.                         break;
  806.                     }
  807.                 } else {
  808.                     // we can use these equations right now
  809.                     final String                      name           = equations.getName();
  810.                     final int                         offset         = secondaryOffsets.get(name);
  811.                     final int                         dimension      = equations.getDimension();
  812.                     final FieldCombinedDerivatives<T> derivatives    = equations.combinedDerivatives(updated);
  813.                     final T[]                         additionalPart = derivatives.getAdditionalDerivatives();
  814.                     final T[]                         mainPart       = derivatives.getMainStateDerivativesIncrements();
  815.                     System.arraycopy(additionalPart, 0, secondaryDot, offset, dimension);
  816.                     updated = updated.addAdditionalStateDerivative(name, additionalPart);
  817.                     if (mainPart != null) {
  818.                         // this equation does change the main state derivatives
  819.                         for (int i = 0; i < mainPart.length; ++i) {
  820.                             primaryDot[i] = primaryDot[i].add(mainPart[i]);
  821.                         }
  822.                     }
  823.                     yieldCount = 0;
  824.                 }
  825.             }

  827.             return secondaryDot;

  829.         }

  831.         /** Convert mathematical view to space view.
  832.          * @param t current value of the independent <I>time</I> variable
  833.          * @param primary array containing the current value of the primary state vector
  834.          * @param primaryDot array containing the derivative of the primary state vector
  835.          * @param secondary array containing the current value of the secondary state vector
  836.          * @return space view of the state
  837.          */
  838.         private FieldSpacecraftState<T> convert(final T t, final T[] primary,
  839.                                                 final T[] primaryDot, final T[] secondary) {

  841.             FieldSpacecraftState<T> initialState = stateMapper.mapArrayToState(t, primary, primaryDot, PropagationType.MEAN);

  843.             for (final FieldAdditionalDerivativesProvider<T> provider : additionalDerivativesProviders) {
  844.                 final String name      = provider.getName();
  845.                 final int    offset    = secondaryOffsets.get(name);
  846.                 final int    dimension = provider.getDimension();
  847.                 initialState = initialState.addAdditionalState(name, Arrays.copyOfRange(secondary, offset, offset + dimension));
  848.             }

  850.             return updateAdditionalStates(initialState);

  852.         }

  854.     }

  856.     /** Adapt an {@link org.orekit.propagation.events.FieldEventDetector<T>}
  857.      * to Hipparchus {@link org.hipparchus.ode.events.FieldODEEventHandler<T>} interface.
  858.      * @param <T> class type for the generic version
  859.      * @author Fabien Maussion
  860.      */
  861.     private class FieldAdaptedEventDetector implements FieldODEEventHandler<T> {

  863.         /** Underlying event detector. */
  864.         private final FieldEventDetector<T> detector;

  866.         /** Time of the previous call to g. */
  867.         private T lastT;

  869.         /** Value from the previous call to g. */
  870.         private T lastG;

  872.         /** Build a wrapped event detector.
  873.          * @param detector event detector to wrap
  874.         */
  875.         FieldAdaptedEventDetector(final FieldEventDetector<T> detector) {
  876.             this.detector = detector;
  877.             this.lastT    = getField().getZero().add(Double.NaN);
  878.             this.lastG    = getField().getZero().add(Double.NaN);
  879.         }

  881.         /** {@inheritDoc} */
  882.         public void init(final FieldODEStateAndDerivative<T> s0, final T t) {
  883.             detector.init(convert(s0), stateMapper.mapDoubleToDate(t));
  884.             this.lastT = getField().getZero().add(Double.NaN);
  885.             this.lastG = getField().getZero().add(Double.NaN);
  886.         }

  888.         /** {@inheritDoc} */
  889.         public T g(final FieldODEStateAndDerivative<T> s) {
  890.             if (!Precision.equals(lastT.getReal(), s.getTime().getReal(), 0)) {
  891.                 lastT = s.getTime();
  892.                 lastG = detector.g(convert(s));
  893.             }
  894.             return lastG;
  895.         }

  897.         /** {@inheritDoc} */
  898.         public Action eventOccurred(final FieldODEStateAndDerivative<T> s, final boolean increasing) {
  899.             return detector.eventOccurred(convert(s), increasing);
  900.         }

  902.         /** {@inheritDoc} */
  903.         public FieldODEState<T> resetState(final FieldODEStateAndDerivative<T> s) {

  905.             final FieldSpacecraftState<T> oldState = convert(s);
  906.             final FieldSpacecraftState<T> newState = detector.resetState(oldState);
  907.             stateChanged(newState);

  909.             // main part
  910.             final T[] primary    = MathArrays.buildArray(getField(), s.getPrimaryStateDimension());
  911.             stateMapper.mapStateToArray(newState, primary, null);

  913.             // secondary part
  914.             final T[][] secondary = MathArrays.buildArray(getField(), 1, additionalDerivativesProviders.size());
  915.             for (final FieldAdditionalDerivativesProvider<T> provider : additionalDerivativesProviders) {
  916.                 final String name      = provider.getName();
  917.                 final int    offset    = secondaryOffsets.get(name);
  918.                 final int    dimension = provider.getDimension();
  919.                 System.arraycopy(newState.getAdditionalState(name), 0, secondary[0], offset, dimension);
  920.             }

  922.             return new FieldODEState<>(newState.getDate().durationFrom(getStartDate()),
  923.                                        primary, secondary);
  924.         }

  926.     }

  928.     /** Adapt an {@link org.orekit.propagation.sampling.FieldOrekitStepHandler<T>}
  929.      * to Hipparchus {@link FieldODEStepHandler<T>} interface.
  930.      * @author Luc Maisonobe
  931.      */
  932.     private class FieldAdaptedStepHandler implements FieldODEStepHandler<T> {

  934.         /** Underlying handler. */
  935.         private final FieldOrekitStepHandler<T> handler;

  937.         /** Build an instance.
  938.          * @param handler underlying handler to wrap
  939.          */
  940.         FieldAdaptedStepHandler(final FieldOrekitStepHandler<T> handler) {
  941.             this.handler = handler;
  942.         }

  944.         /** {@inheritDoc} */
  945.         public void init(final FieldODEStateAndDerivative<T> s0, final T t) {
  946.             handler.init(convert(s0), stateMapper.mapDoubleToDate(t));
  947.         }

  949.         /** {@inheritDoc} */
  950.         public void handleStep(final FieldODEStateInterpolator<T> interpolator) {
  951.             handler.handleStep(new FieldAdaptedStepInterpolator(interpolator));
  952.         }

  954.         /** {@inheritDoc} */
  955.         @Override
  956.         public void finish(final FieldODEStateAndDerivative<T> finalState) {
  957.             handler.finish(convert(finalState));
  958.         }

  960.     }

  962.     /** Adapt an {@link org.orekit.propagation.sampling.FieldOrekitStepInterpolator<T>}
  963.      * to Hipparchus {@link FieldODEStepInterpolator<T>} interface.
  964.      * @author Luc Maisonobe
  965.      */
  966.     private class FieldAdaptedStepInterpolator implements FieldOrekitStepInterpolator<T> {

  968.         /** Underlying raw rawInterpolator. */
  969.         private final FieldODEStateInterpolator<T> mathInterpolator;

  971.         /** Build an instance.
  972.          * @param mathInterpolator underlying raw interpolator
  973.          */
  974.         FieldAdaptedStepInterpolator(final FieldODEStateInterpolator<T> mathInterpolator) {
  975.             this.mathInterpolator = mathInterpolator;
  976.         }

  978.         /** {@inheritDoc}} */
  979.         @Override
  980.         public FieldSpacecraftState<T> getPreviousState() {
  981.             return convert(mathInterpolator.getPreviousState());
  982.         }

  984.         /** {@inheritDoc}} */
  985.         @Override
  986.         public FieldSpacecraftState<T> getCurrentState() {
  987.             return convert(mathInterpolator.getCurrentState());
  988.         }

  990.         /** {@inheritDoc}} */
  991.         @Override
  992.         public FieldSpacecraftState<T> getInterpolatedState(final FieldAbsoluteDate<T> date) {
  993.             return convert(mathInterpolator.getInterpolatedState(date.durationFrom(getStartDate())));
  994.         }

  996.         /** Check is integration direction is forward in date.
  997.          * @return true if integration is forward in date
  998.          */
  999.         public boolean isForward() {
  1000.             return mathInterpolator.isForward();
  1001.         }

  1003.         /** {@inheritDoc}} */
  1004.         @Override
  1005.         public FieldAdaptedStepInterpolator restrictStep(final FieldSpacecraftState<T> newPreviousState,
  1006.                                                          final FieldSpacecraftState<T> newCurrentState) {
  1007.             try {
  1008.                 final AbstractFieldODEStateInterpolator<T> aosi = (AbstractFieldODEStateInterpolator<T>) mathInterpolator;
  1009.                 return new FieldAdaptedStepInterpolator(aosi.restrictStep(convert(newPreviousState),
  1010.                                                                           convert(newCurrentState)));
  1011.             } catch (ClassCastException cce) {
  1012.                 // this should never happen
  1013.                 throw new OrekitInternalError(cce);
  1014.             }
  1015.         }

  1017.     }

  1019.     /** Specialized step handler storing interpolators for ephemeris generation.
  1020.      * @since 11.0
  1021.      */
  1022.     private class FieldStoringStepHandler implements FieldODEStepHandler<T>, FieldEphemerisGenerator<T> {

  1024.         /** Underlying raw mathematical model. */
  1025.         private FieldDenseOutputModel<T> model;

  1027.         /** the user supplied end date. Propagation may not end on this date. */
  1028.         private FieldAbsoluteDate<T> endDate;

  1030.         /** Generated ephemeris. */
  1031.         private FieldBoundedPropagator<T> ephemeris;

  1033.         /** Last interpolator handled by the object.*/
  1034.         private  FieldODEStateInterpolator<T> lastInterpolator;

  1036.         /** Set the end date.
  1037.          * @param endDate end date
  1038.          */
  1039.         public void setEndDate(final FieldAbsoluteDate<T> endDate) {
  1040.             this.endDate = endDate;
  1041.         }

  1043.         /** {@inheritDoc} */
  1044.         @Override
  1045.         public void init(final FieldODEStateAndDerivative<T> s0, final T t) {
  1046.             this.model = new FieldDenseOutputModel<>();
  1047.             model.init(s0, t);

  1049.             // ephemeris will be generated when last step is processed
  1050.             this.ephemeris = null;

  1052.             this.lastInterpolator = null;

  1054.         }

  1056.         /** {@inheritDoc} */
  1057.         @Override
  1058.         public FieldBoundedPropagator<T> getGeneratedEphemeris() {
  1059.             // Each time we try to get the ephemeris, rebuild it using the last data.
  1060.             buildEphemeris();
  1061.             return ephemeris;
  1062.         }

  1064.         /** {@inheritDoc} */
  1065.         @Override
  1066.         public void handleStep(final FieldODEStateInterpolator<T> interpolator) {
  1067.             model.handleStep(interpolator);
  1068.             lastInterpolator = interpolator;
  1069.         }

  1071.         /** {@inheritDoc} */
  1072.         @Override
  1073.         public void finish(final FieldODEStateAndDerivative<T> finalState) {
  1074.             buildEphemeris();
  1075.         }

  1077.         /** Method used to produce ephemeris at a given time.
  1078.          * Can be used at multiple times, updating the ephemeris to
  1079.          * its last state.
  1080.          */
  1081.         private void buildEphemeris() {
  1082.             // buildEphemeris was built in order to allow access to what was previously the finish method.
  1083.             // This now allows to call it through getGeneratedEphemeris, therefore through an external call,
  1084.             // which was not previously the case.

  1086.             // Update the model's finalTime with the last interpolator.
  1087.             model.finish(lastInterpolator.getCurrentState());

  1089.             // set up the boundary dates
  1090.             final T tI = model.getInitialTime();
  1091.             final T tF = model.getFinalTime();
  1092.             // tI is almost? always zero
  1093.             final FieldAbsoluteDate<T> startDate =
  1094.                             stateMapper.mapDoubleToDate(tI);
  1095.             final FieldAbsoluteDate<T> finalDate =
  1096.                             stateMapper.mapDoubleToDate(tF, this.endDate);
  1097.             final FieldAbsoluteDate<T> minDate;
  1098.             final FieldAbsoluteDate<T> maxDate;
  1099.             if (tF.getReal() < tI.getReal()) {
  1100.                 minDate = finalDate;
  1101.                 maxDate = startDate;
  1102.             } else {
  1103.                 minDate = startDate;
  1104.                 maxDate = finalDate;
  1105.             }

  1107.             // get the initial additional states that are not managed
  1108.             final FieldArrayDictionary<T> unmanaged = new FieldArrayDictionary<>(startDate.getField());
  1109.             for (final FieldArrayDictionary<T>.Entry initial : getInitialState().getAdditionalStatesValues().getData()) {
  1110.                 if (!isAdditionalStateManaged(initial.getKey())) {
  1111.                     // this additional state was in the initial state, but is unknown to the propagator
  1112.                     // we simply copy its initial value as is
  1113.                     unmanaged.put(initial.getKey(), initial.getValue());
  1114.                 }
  1115.             }

  1117.             // get the names of additional states managed by differential equations
  1118.             final String[] names      = new String[additionalDerivativesProviders.size()];
  1119.             final int[]    dimensions = new int[additionalDerivativesProviders.size()];
  1120.             for (int i = 0; i < names.length; ++i) {
  1121.                 names[i] = additionalDerivativesProviders.get(i).getName();
  1122.                 dimensions[i] = additionalDerivativesProviders.get(i).getDimension();
  1123.             }

  1125.             // create the ephemeris
  1126.             ephemeris = new FieldIntegratedEphemeris<>(startDate, minDate, maxDate,
  1127.                                                        stateMapper, propagationType, model,
  1128.                                                        unmanaged, getAdditionalStateProviders(),
  1129.                                                        names, dimensions);

  1131.         }

  1133.     }

  1135.     /** Wrapper for resetting an integrator handlers.
  1136.      * <p>
  1137.      * This class is intended to be used in a try-with-resource statement.
  1138.      * If propagator-specific event handlers and step handlers are added to
  1139.      * the integrator in the try block, they will be removed automatically
  1140.      * when leaving the block, so the integrator only keep its own handlers
  1141.      * between calls to {@link AbstractIntegratedPropagator#propagate(AbsoluteDate, AbsoluteDate).
  1142.      * </p>
  1143.      * @param <T> the type of the field elements
  1144.      * @since 11.0
  1145.      */
  1146.     private static class IntegratorResetter<T extends CalculusFieldElement<T>> implements AutoCloseable {

  1148.         /** Wrapped integrator. */
  1149.         private final FieldODEIntegrator<T> integrator;

  1151.         /** Initial event handlers list. */
  1152.         private final List<FieldEventHandlerConfiguration<T>> eventHandlersConfigurations;

  1154.         /** Initial step handlers list. */
  1155.         private final List<FieldODEStepHandler<T>> stepHandlers;

  1157.         /** Simple constructor.
  1158.          * @param integrator wrapped integrator
  1159.          */
  1160.         IntegratorResetter(final FieldODEIntegrator<T> integrator) {
  1161.             this.integrator                  = integrator;
  1162.             this.eventHandlersConfigurations = new ArrayList<>(integrator.getEventHandlersConfigurations());
  1163.             this.stepHandlers                = new ArrayList<>(integrator.getStepHandlers());
  1164.         }

  1166.         /** {@inheritDoc}
  1167.          * <p>
  1168.          * Reset event handlers and step handlers back to the initial list
  1169.          * </p>
  1170.          */
  1171.         @Override
  1172.         public void close() {

  1174.             // reset event handlers
  1175.             integrator.clearEventHandlers();
  1176.             eventHandlersConfigurations.forEach(c -> integrator.addEventHandler(c.getEventHandler(),
  1177.                                                                                 c.getMaxCheckInterval(),
  1178.                                                                                 c.getConvergence().getReal(),
  1179.                                                                                 c.getMaxIterationCount(),
  1180.                                                                                 c.getSolver()));

  1182.             // reset step handlers
  1183.             integrator.clearStepHandlers();
  1184.             stepHandlers.forEach(stepHandler -> integrator.addStepHandler(stepHandler));

  1186.         }

  1188.     }

  1190. }
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