FieldPropagator.java

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 * this work for additional information regarding copyright ownership.
 * CS licenses this file to You under the Apache License, Version 2.0
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 *
 *   http://www.apache.org/licenses/LICENSE-2.0
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package org.orekit.propagation;

import java.util.Collection;
import java.util.List;

import org.hipparchus.CalculusFieldElement;
import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
import org.orekit.attitudes.AttitudeProvider;
import org.orekit.frames.Frame;
import org.orekit.propagation.events.FieldEventDetector;
import org.orekit.propagation.sampling.FieldOrekitFixedStepHandler;
import org.orekit.propagation.sampling.FieldOrekitStepHandler;
import org.orekit.propagation.sampling.FieldStepHandlerMultiplexer;
import org.orekit.time.FieldAbsoluteDate;
import org.orekit.utils.FieldPVCoordinatesProvider;
import org.orekit.utils.TimeStampedFieldPVCoordinates;

/** This interface provides a way to propagate an orbit at any time.
 *
 * <p>This interface is the top-level abstraction for orbit propagation.
 * It only allows propagation to a predefined date.
 * It is implemented by analytical models which have no time limit,
 * by orbit readers based on external data files, by numerical integrators
 * using rich force models and by continuous models built after numerical
 * integration has been completed and dense output data as been
 * gathered.</p>
 * @param <T> the type of the field elements

 * @author Luc Maisonobe
 * @author V&eacute;ronique Pommier-Maurussane
 *
 */

public interface FieldPropagator<T extends CalculusFieldElement<T>> extends FieldPVCoordinatesProvider<T> {

    /** Default mass. */
    double DEFAULT_MASS = 1000.0;

    /** Get the multiplexer holding all step handlers.
     * @return multiplexer holding all step handlers
     * @since 11.0
     */
    FieldStepHandlerMultiplexer<T> getMultiplexer();

    /** Remove all step handlers.
     * <p>This convenience method is equivalent to call {@code getMultiplexer().clear()}</p>
     * @see #getMultiplexer()
     * @see FieldStepHandlerMultiplexer#clear()
     * @since 11.0
     */
    default void clearStepHandlers() {
        getMultiplexer().clear();
    }

    /** Set a single handler for fixed stepsizes.
     * <p>This convenience method is equivalent to call {@code getMultiplexer().clear()}
     * followed by {@code getMultiplexer().add(h, handler)}</p>
     * @param h fixed stepsize (s)
     * @param handler handler called at the end of each finalized step
     * @see #getMultiplexer()
     * @see FieldStepHandlerMultiplexer#add(CalculusFieldElement, FieldOrekitFixedStepHandler)
     * @since 11.0
     */
    default void setStepHandler(final T h, final FieldOrekitFixedStepHandler<T> handler) {
        getMultiplexer().clear();
        getMultiplexer().add(h, handler);
    }

    /** Set a single handler for variable stepsizes.
     * <p>This convenience method is equivalent to call {@code getMultiplexer().clear()}
     * followed by {@code getMultiplexer().add(handler)}</p>
     * @param handler handler called at the end of each finalized step
     * @see #getMultiplexer()
     * @see FieldStepHandlerMultiplexer#add(FieldOrekitStepHandler)
     * @since 11.0
     */
    default void setStepHandler(final FieldOrekitStepHandler<T> handler) {
        getMultiplexer().clear();
        getMultiplexer().add(handler);
    }

    /**
     * Set up an ephemeris generator that will monitor the propagation for building
     * an ephemeris from it once completed.
     *
     * <p>
     * This generator can be used when the user needs fast random access to the orbit
     * state at any time between the initial and target times. A typical example is the
     * implementation of search and iterative algorithms that may navigate forward and
     * backward inside the propagation range before finding their result even if the
     * propagator used is integration-based and only goes from one initial time to one
     * target time.
     * </p>
     * <p>
     * Beware that when used with integration-based propagators, the generator will
     * store <strong>all</strong> intermediate results. It is therefore memory intensive
     * for long integration-based ranges and high precision/short time steps. When
     * used with analytical propagators, the generator only stores start/stop time
     * and a reference to the analytical propagator itself to call it back as needed,
     * so it is less memory intensive.
     * </p>
     * <p>
     * The returned ephemeris generator will be initially empty, it will be filled
     * with propagation data when a subsequent call to either {@link #propagate(FieldAbsoluteDate)
     * propagate(target)} or {@link #propagate(FieldAbsoluteDate, FieldAbsoluteDate)
     * propagate(start, target)} is called. The proper way to use this method is
     * therefore to do:
     * </p>
     * <pre>
     *   FieldEphemerisGenerator&lt;T&gt; generator = propagator.getEphemerisGenerator();
     *   propagator.propagate(target);
     *   FieldBoundedPropagator&lt;T&gt; ephemeris = generator.getGeneratedEphemeris();
     * </pre>
     * @return ephemeris generator
     */
    FieldEphemerisGenerator<T> getEphemerisGenerator();

    /** Get the propagator initial state.
     * @return initial state
     */
    FieldSpacecraftState<T> getInitialState();

    /** Reset the propagator initial state.
     * @param state new initial state to consider
     */
    void resetInitialState(FieldSpacecraftState<T> state);

    /** Add a set of user-specified state parameters to be computed along with the orbit propagation.
     * @param additionalStateProvider provider for additional state
     */
    void addAdditionalStateProvider(FieldAdditionalStateProvider<T> additionalStateProvider);

    /** Get an unmodifiable list of providers for additional state.
     * @return providers for the additional states
     */
    List<FieldAdditionalStateProvider<T>> getAdditionalStateProviders();

    /** Check if an additional state is managed.
     * <p>
     * Managed states are states for which the propagators know how to compute
     * its evolution. They correspond to additional states for which an
     * {@link FieldAdditionalStateProvider additional state provider} has been registered
     * by calling the {@link #addAdditionalStateProvider(FieldAdditionalStateProvider)
     * addAdditionalStateProvider} method. If the propagator is an {@link
     * org.orekit.propagation.integration.FieldAbstractIntegratedPropagator integrator-based
     * propagator}, the states for which a set of {@link
     * org.orekit.propagation.integration.FieldAdditionalDerivativesProvider additional derivatives
     * provider} has been registered by calling the {@link
     * org.orekit.propagation.integration.FieldAbstractIntegratedPropagator#addAdditionalDerivativesProvider(
     * org.orekit.propagation.integration.FieldAdditionalDerivativesProvider) addAdditionalDerivativesProvider}
     * method are also counted as managed additional states.
     * </p>
     * <p>
     * Additional states that are present in the {@link #getInitialState() initial state}
     * but have no evolution method registered are <em>not</em> considered as managed states.
     * These unmanaged additional states are not lost during propagation, though. Their
     * value are piecewise constant between state resets that may change them if some
     * event handler {@link
     * org.orekit.propagation.events.handlers.FieldEventHandler#resetState(FieldEventDetector,
     * FieldSpacecraftState) resetState} method is called at an event occurrence and happens
     * to change the unmanaged additional state.
     * </p>
     * @param name name of the additional state
     * @return true if the additional state is managed
     */
    boolean isAdditionalStateManaged(String name);

    /** Get all the names of all managed states.
     * @return names of all managed states
     */
    String[] getManagedAdditionalStates();

    /** Add an event detector.
     * @param detector event detector to add
     * @see #clearEventsDetectors()
     * @see #getEventsDetectors()
     * @param <D> class type for the generic version
     */
    <D extends FieldEventDetector<T>> void addEventDetector(D detector);

    /** Get all the events detectors that have been added.
     * @return an unmodifiable collection of the added detectors
     * @see #addEventDetector(FieldEventDetector)
     * @see #clearEventsDetectors()
     */
    Collection<FieldEventDetector<T>> getEventsDetectors();

    /** Remove all events detectors.
     * @see #addEventDetector(FieldEventDetector)
     * @see #getEventsDetectors()
     */
    void clearEventsDetectors();

    /** Get attitude provider.
     * @return attitude provider
     */
    AttitudeProvider getAttitudeProvider();

    /** Set attitude provider.
     * @param attitudeProvider attitude provider
     */
    void setAttitudeProvider(AttitudeProvider attitudeProvider);

    /** Get the frame in which the orbit is propagated.
     * <p>
     * The propagation frame is the definition frame of the initial
     * state, so this method should be called after this state has
     * been set, otherwise it may return null.
     * </p>
     * @return frame in which the orbit is propagated
     * @see #resetInitialState(FieldSpacecraftState)
     */
    Frame getFrame();

    /** Propagate towards a target date.
     * <p>Simple propagators use only the target date as the specification for
     * computing the propagated state. More feature rich propagators can consider
     * other information and provide different operating modes or G-stop
     * facilities to stop at pinpointed events occurrences. In these cases, the
     * target date is only a hint, not a mandatory objective.</p>
     * @param target target date towards which orbit state should be propagated
     * @return propagated state
     */
    FieldSpacecraftState<T> propagate(FieldAbsoluteDate<T> target);

    /** Propagate from a start date towards a target date.
     * <p>Those propagators use a start date and a target date to
     * compute the propagated state. For propagators using event detection mechanism,
     * if the provided start date is different from the initial state date, a first,
     * simple propagation is performed, without processing any event computation.
     * Then complete propagation is performed from start date to target date.</p>
     * @param start start date from which orbit state should be propagated
     * @param target target date to which orbit state should be propagated
     * @return propagated state
     */
    FieldSpacecraftState<T> propagate(FieldAbsoluteDate<T> start, FieldAbsoluteDate<T> target);

    /** {@inheritDoc} */
    @Override
    default TimeStampedFieldPVCoordinates<T> getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame) {
        return propagate(date).getPVCoordinates(frame);
    }

    /** {@inheritDoc} */
    @Override
    default FieldVector3D<T> getPosition(final FieldAbsoluteDate<T> date, final Frame frame) {
        return propagate(date).getPosition(frame);
    }

}