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    *   http://www.apache.org/licenses/LICENSE-2.0
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   * Unless required by applicable law or agreed to in writing, software
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  package org.orekit.propagation.events;
  
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.hipparchus.ode.nonstiff.AdaptiveStepsizeIntegrator;
  import org.hipparchus.ode.nonstiff.DormandPrince853Integrator;
  import org.hipparchus.util.FastMath;
  import org.junit.jupiter.api.AfterEach;
  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.CelestialBodyFactory;
  import org.orekit.errors.OrekitException;
  import org.orekit.frames.FramesFactory;
  import org.orekit.orbits.EquinoctialOrbit;
  import org.orekit.orbits.Orbit;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.numerical.NumericalPropagator;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.time.TimeScalesFactory;
  import org.orekit.utils.PVCoordinates;
  import org.orekit.utils.PVCoordinatesProvider;
  
  public class AlignmentDetectorTest {
  
      private AbsoluteDate         iniDate;
      private SpacecraftState      initialState;
      private NumericalPropagator  propagator;
  
      @Test
      public void testAlignment() {
  
          double alignAngle = FastMath.toRadians(0.0);
          PVCoordinatesProvider sun = CelestialBodyFactory.getSun();
          AlignmentDetector alignDetector =
              new AlignmentDetector(initialState.getOrbit(), sun, alignAngle).
              withMaxCheck(60.0);
          Assertions.assertEquals(alignAngle, alignDetector.getAlignAngle(), 1.0e-15);
          Assertions.assertSame(sun, alignDetector.getPVCoordinatesProvider());
          Assertions.assertEquals(60.0, alignDetector.getMaxCheckInterval().currentInterval(null, true), 1.0e-15);
          propagator.addEventDetector(alignDetector);
          final SpacecraftState finalState = propagator.propagate(iniDate.shiftedBy(6000));
          Assertions.assertEquals(383.3662, finalState.getDate().durationFrom(iniDate), 1.0e-3);
  
      }
  
      @BeforeEach
      public void setUp() {
          try {
              Utils.setDataRoot("regular-data");
              double mu = 3.9860047e14;
              final Vector3D position  = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
              final Vector3D velocity  = new Vector3D(505.8479685, 942.7809215, 7435.922231);
              iniDate = new AbsoluteDate(1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
              final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position,  velocity),
                                                       FramesFactory.getEME2000(), iniDate, mu);
              initialState = new SpacecraftState(orbit);
              double[] absTolerance = {
                  0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001
              };
              double[] relTolerance = {
                  1.0e-7, 1.0e-4, 1.0e-4, 1.0e-7, 1.0e-7, 1.0e-7, 1.0e-7
              };
              AdaptiveStepsizeIntegrator integrator =
                  new DormandPrince853Integrator(0.001, 1000, absTolerance, relTolerance);
              integrator.setInitialStepSize(60);
              propagator = new NumericalPropagator(integrator);
              propagator.setInitialState(initialState);
          } catch (OrekitException oe) {
              Assertions.fail(oe.getLocalizedMessage());
          }
      }
  
      @AfterEach
      public void tearDown() {
          iniDate = null;
          initialState = null;
          propagator = null;
      }
  
  }