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    * contributor license agreements.  See the NOTICE file distributed with
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    * CS licenses this file to You under the Apache License, Version 2.0
    * (the "License"); you may not use this file except in compliance with
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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.forces.maneuvers.triggers;
  
  
  import java.util.stream.Stream;
  
  import org.hipparchus.CalculusFieldElement;
  import org.hipparchus.Field;
  import org.hipparchus.util.Decimal64Field;
  import org.junit.Assert;
  import org.junit.Test;
  import org.orekit.forces.maneuvers.trigger.ManeuverTriggers;
  import org.orekit.frames.FramesFactory;
  import org.orekit.orbits.KeplerianOrbit;
  import org.orekit.orbits.PositionAngle;
  import org.orekit.propagation.FieldSpacecraftState;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.events.EventDetector;
  import org.orekit.propagation.events.FieldEventDetector;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.time.FieldAbsoluteDate;
  import org.orekit.utils.Constants;
  
  public class ManeuverTriggersTest {
  
      @Test
      public void testNoOpDefault() {
          // just test the default no-op implementation can be called without side effects
          ManeuverTriggers dummy = new ManeuverTriggers() {
              public <T extends CalculusFieldElement<T>> boolean isFiring(FieldAbsoluteDate<T> date, T[] parameters) {
                  return false;
              }
              public boolean isFiring(AbsoluteDate date, double[] parameters) {
                  return false;
              }
              public <T extends CalculusFieldElement<T>> Stream<FieldEventDetector<T>> getFieldEventsDetectors(Field<T> field) {
                  return null;
              }
              public Stream<EventDetector> getEventsDetectors() {
                   return null;
              }
          };
  
          SpacecraftState state = new SpacecraftState(new KeplerianOrbit(7e6, 0.1, 0.2, 0.3, 0.4, 0.5,
                                                                         PositionAngle.MEAN, FramesFactory.getGCRF(),
                                                                         AbsoluteDate.J2000_EPOCH,
                                                                         Constants.EIGEN5C_EARTH_MU));
          dummy.init(state, state.getDate().shiftedBy(60));
          dummy.init(new FieldSpacecraftState<>(Decimal64Field.getInstance(), state),
                     new FieldAbsoluteDate<>(Decimal64Field.getInstance(), state.getDate().shiftedBy(60)));
          Assert.assertEquals("", dummy.getName());
  
      }
  
  }