ElevationExtremumDetector.java

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package org.orekit.propagation.events;

import org.hipparchus.analysis.differentiation.UnivariateDerivative1;
import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
import org.orekit.frames.KinematicTransform;
import org.orekit.frames.TopocentricFrame;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.events.handlers.EventHandler;
import org.orekit.propagation.events.handlers.StopOnIncreasing;
import org.orekit.utils.TimeStampedPVCoordinates;

/** Detector for elevation extremum with respect to a ground point.
 * <p>This detector identifies when a spacecraft reaches its
 * extremum elevation with respect to a ground point.</p>
 * <p>
 * As in most cases only the elevation maximum is needed and the
 * minimum is often irrelevant, this detector is often wrapped into
 * an {@link EventSlopeFilter event slope filter} configured with
 * {@link FilterType#TRIGGER_ONLY_DECREASING_EVENTS} (i.e. when the
 * elevation derivative decreases from positive values to negative values,
 * which correspond to a maximum). Setting up this filter saves some computation
 * time as the elevation minimum occurrences are not even looked at. It is
 * however still often necessary to do an additional filtering
 * </p>
 * @author Luc Maisonobe
 * @since 7.1
 */
public class ElevationExtremumDetector extends AbstractDetector<ElevationExtremumDetector> {

    /** Topocentric frame in which elevation should be evaluated. */
    private final TopocentricFrame topo;

    /** Build a new detector.
     * <p>The new instance uses default values for maximal checking interval
     * ({@link #DEFAULT_MAX_CHECK}) and convergence threshold ({@link
     * #DEFAULT_THRESHOLD}).</p>
     * @param topo topocentric frame centered on ground point
     */
    public ElevationExtremumDetector(final TopocentricFrame topo) {
        this(DEFAULT_MAX_CHECK, DEFAULT_THRESHOLD, topo);
    }

    /** Build a detector.
     * @param maxCheck maximal checking interval (s)
     * @param threshold convergence threshold (s)
     * @param topo topocentric frame centered on ground point
     */
    public ElevationExtremumDetector(final double maxCheck, final double threshold,
                                     final TopocentricFrame topo) {
        this(new EventDetectionSettings(maxCheck, threshold, DEFAULT_MAX_ITER), new StopOnIncreasing(), topo);
    }

    /** Protected constructor with full parameters.
     * <p>
     * This constructor is not public as users are expected to use the builder
     * API with the various {@code withXxx()} methods to set up the instance
     * in a readable manner without using a huge amount of parameters.
     * </p>
     * @param detectionSettings event detection settings
     * @param handler event handler to call at event occurrences
     * @param topo topocentric frame centered on ground point
     * @since 13.0
     */
    protected ElevationExtremumDetector(final EventDetectionSettings detectionSettings, final EventHandler handler,
                                        final TopocentricFrame topo) {
        super(detectionSettings, handler);
        this.topo = topo;
    }

    /** {@inheritDoc} */
    @Override
    protected ElevationExtremumDetector create(final EventDetectionSettings detectionSettings,
                                              final EventHandler newHandler) {
        return new ElevationExtremumDetector(detectionSettings, newHandler, topo);
    }

    /**
     * Returns the topocentric frame centered on ground point.
     * @return topocentric frame centered on ground point
     */
    public TopocentricFrame getTopocentricFrame() {
        return this.topo;
    }

    /** Get the elevation value.
     * @param s the current state information: date, kinematics, attitude
     * @return spacecraft elevation
     */
    public double getElevation(final SpacecraftState s) {
        return topo.getElevation(s.getPosition(), s.getFrame(), s.getDate());
    }

    /** Compute the value of the detection function.
     * <p>
     * The value is the spacecraft elevation first time derivative.
     * </p>
     * @param s the current state information: date, kinematics, attitude
     * @return spacecraft elevation first time derivative
     */
    public double g(final SpacecraftState s) {

        // get position, velocity of spacecraft in topocentric frame
        final KinematicTransform inertToTopo = s.getFrame().getKinematicTransformTo(topo, s.getDate());
        final TimeStampedPVCoordinates pvTopo = inertToTopo.transformOnlyPV(s.getPVCoordinates());

        // convert the coordinates to UnivariateDerivative1 based vector
        // instead of having vector position, then vector velocity then vector acceleration
        // we get one vector and each coordinate is a DerivativeStructure containing
        // value, first time derivative (we don't need second time derivative here)
        final FieldVector3D<UnivariateDerivative1> pvDS = pvTopo.toUnivariateDerivative1Vector();

        // compute elevation and its first time derivative
        final UnivariateDerivative1 elevation = pvDS.getZ().divide(pvDS.getNorm()).asin();

        // return elevation first time derivative
        return elevation.getDerivative(1);

    }

}