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  package org.orekit.forces.maneuvers.trigger;
  
  import java.util.Collections;
  import java.util.List;
  import java.util.stream.Stream;
  
  import org.hipparchus.CalculusFieldElement;
  import org.hipparchus.Field;
  import org.hipparchus.util.Binary64Field;
  import org.junit.jupiter.api.Assertions;
  import org.junit.jupiter.api.Test;
  import org.orekit.frames.FramesFactory;
  import org.orekit.orbits.KeplerianOrbit;
  import org.orekit.orbits.PositionAngleType;
  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;
  import org.orekit.utils.ParameterDriver;
  
  public class ManeuverTriggersTest {
  
      @Test
      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;
              }
              @Override
              public List<ParameterDriver> getParametersDrivers() {
                  return Collections.emptyList();
              }
              @Override
              public Stream<EventDetector> getEventDetectors() {
                  return Stream.empty();
              }
              @Override
              public <T extends CalculusFieldElement<T>> Stream<FieldEventDetector<T>> getFieldEventDetectors(Field<T> field) {
                  return Stream.empty();
              }
          };
  
          SpacecraftState state = new SpacecraftState(new KeplerianOrbit(7e6, 0.1, 0.2, 0.3, 0.4, 0.5,
                                                                         PositionAngleType.MEAN, FramesFactory.getGCRF(),
                                                                         AbsoluteDate.J2000_EPOCH,
                                                                         Constants.EIGEN5C_EARTH_MU));
          dummy.init(state, state.getDate().shiftedBy(60));
          dummy.init(new FieldSpacecraftState<>(Binary64Field.getInstance(), state),
                     new FieldAbsoluteDate<>(Binary64Field.getInstance(), state.getDate().shiftedBy(60)));
          Assertions.assertEquals("", dummy.getName());
  
      }
  
  }