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  package org.orekit.propagation.events;
  
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.hipparchus.util.FastMath;
  import org.junit.jupiter.api.Assertions;
  import org.junit.jupiter.api.BeforeEach;
  import org.junit.jupiter.api.Test;
  import org.orekit.Utils;
  import org.orekit.bodies.OneAxisEllipsoid;
  import org.orekit.frames.FramesFactory;
  import org.orekit.orbits.EquinoctialOrbit;
  import org.orekit.orbits.Orbit;
  import org.orekit.propagation.Propagator;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.analytical.EcksteinHechlerPropagator;
  import org.orekit.propagation.events.EventsLogger.LoggedEvent;
  import org.orekit.propagation.events.handlers.ContinueOnEvent;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.time.TimeScale;
  import org.orekit.time.TimeScalesFactory;
  import org.orekit.utils.Constants;
  import org.orekit.utils.IERSConventions;
  import org.orekit.utils.PVCoordinates;
  
  public class LatitudeExtremumDetectorTest {
  
      @Test
      public void testLEO() {
  
          final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
                                                              Constants.WGS84_EARTH_FLATTENING,
                                                              FramesFactory.getITRF(IERSConventions.IERS_2010, true));
  
          LatitudeExtremumDetector d =
                  new LatitudeExtremumDetector(earth).
                  withMaxCheck(60).
                  withThreshold(1.e-6).
                  withHandler(new ContinueOnEvent());
  
          Assertions.assertEquals(60.0, d.getMaxCheckInterval().currentInterval(null, true), 1.0e-15);
          Assertions.assertEquals(1.0e-6, d.getThreshold(), 1.0e-15);
          Assertions.assertEquals(AbstractDetector.DEFAULT_MAX_ITER, d.getMaxIterationCount());
          Assertions.assertSame(earth, d.getBody());
  
          final TimeScale utc = TimeScalesFactory.getUTC();
          final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
          final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
          final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
          final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position,  velocity),
                                                   FramesFactory.getEME2000(), date,
                                                   Constants.EIGEN5C_EARTH_MU);
  
          Propagator propagator =
              new EcksteinHechlerPropagator(orbit,
                                            Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS,
                                            Constants.EIGEN5C_EARTH_MU,
                                            Constants.EIGEN5C_EARTH_C20,
                                            Constants.EIGEN5C_EARTH_C30,
                                            Constants.EIGEN5C_EARTH_C40,
                                            Constants.EIGEN5C_EARTH_C50,
                                            Constants.EIGEN5C_EARTH_C60);
  
          EventsLogger logger = new EventsLogger();
          propagator.addEventDetector(logger.monitorDetector(d));
  
          propagator.propagate(date.shiftedBy(Constants.JULIAN_DAY));
          for (LoggedEvent e : logger.getLoggedEvents()) {
              SpacecraftState state = e.getState();
              double latitude = earth.transform(state.getPosition(earth.getBodyFrame()),
                                                earth.getBodyFrame(), null).getLatitude();
              if (e.isIncreasing()) {
                  Assertions.assertEquals(-81.863, FastMath.toDegrees(latitude), 0.001);
              } else {
                  Assertions.assertEquals(+81.863, FastMath.toDegrees(latitude), 0.001);
              }
          }
          Assertions.assertEquals(29, logger.getLoggedEvents().size());
  
      }
  
      @BeforeEach
      public void setUp() {
          Utils.setDataRoot("regular-data");
     }
 
 }