FieldEventDetector.java

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package org.orekit.propagation.events;

import org.hipparchus.CalculusFieldElement;
import org.orekit.propagation.FieldSpacecraftState;
import org.orekit.propagation.events.handlers.FieldEventHandler;
import org.orekit.propagation.events.intervals.FieldAdaptableInterval;
import org.orekit.time.FieldAbsoluteDate;

/** This interface represents space-dynamics aware events detectors.
 *
 * <p>It mirrors the {@link org.hipparchus.ode.events.FieldODEEventHandler
 * FieldODEEventHandler} interface from <a href="https://hipparchus.org/">
 * Hipparchus</a> but provides a space-dynamics interface to the
 * methods.</p>
 *
 * <p>Events detectors are a useful solution to meet the requirements
 * of propagators concerning discrete conditions. The state of each
 * event detector is queried by the propagator from time to time, at least
 * once every {@link #getMaxCheckInterval() max check interval} but it may
 * be more frequent. When the sign of the underlying g switching function
 * changes, a root-finding algorithm is run to precisely locate the event,
 * down to a configured {@link #getThreshold() convergence threshold}. The
 * {@link #getMaxCheckInterval() max check interval} is therefore devoted to
 * separate roots and is often much larger than the  {@link #getThreshold()
 * convergence threshold}.</p>
 *
 * <p>The physical meaning of the g switching function is not really used
 * by the event detection algorithms. Its varies from event detector to
 * event detector. One example would be a visibility detector that could use the
 * angular elevation of the satellite above horizon as a g switching function.
 * In this case, the function would switch from negative to positive when the
 * satellite raises above horizon and it would switch from positive to negative
 * when it sets backs below horizon. Another example would be an apside detector
 * that could use the dot product of position and velocity. In this case, the
 * function would switch from negative to positive when the satellite crosses
 * periapsis and it would switch from positive to negative when the satellite
 * crosses apoapsis.</p>
 *
 * <p>When the precise state at which the g switching function changes has been
 * located, the corresponding event is triggered, by calling the {@link
 * FieldEventHandler#eventOccurred(FieldSpacecraftState, FieldEventDetector, boolean)
 * eventOccurred} method from the associated {@link #getHandler() handler}.
 * The method can do whatever it needs with the event (logging it, performing
 * some processing, ignore it ...). The return value of the method will be used by
 * the propagator to stop or resume propagation, possibly changing the state vector.</p>
 *
 * @param <T> type of the field element
 * @author Luc Maisonobe
 * @author V&eacute;ronique Pommier-Maurussane
 */
public interface FieldEventDetector <T extends CalculusFieldElement<T>> {

    /** Initialize event detector at the start of a propagation.
     * <p>
     * This method is called once at the start of the propagation. It
     * may be used by the event detector to initialize some internal data
     * if needed.
     * </p>
     * <p>
     * The default implementation initializes the handler.
     * </p>
     * @param s0 initial state
     * @param t target time for the integration
     *
     */
    default void init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) {
        getHandler().init(s0, t, this);
    }

    /** Reset the event detector during propagation when the state is modified by an event or an additional data provider.
     * <p>
     * The default implementation does nothing.
     * </p>
     * @param state current state
     * @param target target time for the integration
     * @since 13.0
     */
    default void reset(FieldSpacecraftState<T> state, FieldAbsoluteDate<T> target) {
        // nothing by default
    }

    /** Compute the value of the switching function.
     * This function must be continuous (at least in its roots neighborhood),
     * as the integrator will need to find its roots to locate the events.
     * @param s the current state information: date, kinematics, attitude
     * @return value of the switching function
     */
    T g(FieldSpacecraftState<T> s);

    /** Get the convergence threshold in the event time search.
     * @return convergence threshold (s)
     */
    default T getThreshold() {
        return getDetectionSettings().getThreshold();
    }

    /** Get maximal time interval between switching function checks.
     * @return maximal time interval (s) between switching function checks
     */
    default FieldAdaptableInterval<T> getMaxCheckInterval() {
        return getDetectionSettings().getMaxCheckInterval();
    }

    /** Get maximal number of iterations in the event time search.
     * @return maximal number of iterations in the event time search
     */
    default int getMaxIterationCount() {
        return getDetectionSettings().getMaxIterationCount();
    }

    /** Get the handler.
     * @return event handler to call at event occurrences
     * @since 12.0
     */
    FieldEventHandler<T> getHandler();

    /**
     * This method finalizes the event detector's job.
     * @param state state at propagation end
     * @since 12.2
     */
    default void finish(FieldSpacecraftState<T> state) {
        getHandler().finish(state, this);
    }

    /**
     * Getter for the settings.
     * @return detection settings
     * @since 12.2
     */
    FieldEventDetectionSettings<T> getDetectionSettings();
}