/* Contributed in the public domain.
    * Licensed to CS GROUP (CS) under one or more
    * contributor license agreements.  See the NOTICE file distributed with
    * this work for additional information regarding copyright ownership.
    * 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
    * the License.  You may obtain a copy of the License at
    *
    *   http://www.apache.org/licenses/LICENSE-2.0
   *
   * Unless required by applicable law or agreed to in writing, software
   * distributed under the License is distributed on an "AS IS" BASIS,
   * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
   * See the License for the specific language governing permissions and
   * limitations under the License.
   */
  
  package org.orekit.propagation.conversion;
  
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.junit.jupiter.api.Assertions;
  import org.junit.jupiter.api.DisplayName;
  import org.junit.jupiter.api.Test;
  import org.mockito.Mockito;
  import org.orekit.attitudes.AttitudeProvider;
  import org.orekit.frames.Frame;
  import org.orekit.frames.FramesFactory;
  import org.orekit.orbits.CartesianOrbit;
  import org.orekit.orbits.Orbit;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.SpacecraftStateInterpolator;
  import org.orekit.propagation.analytical.Ephemeris;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.time.TimeInterpolator;
  import org.orekit.utils.Constants;
  import org.orekit.utils.PVCoordinates;
  
  import java.util.ArrayList;
  import java.util.List;
  
  import static org.orekit.propagation.conversion.AbstractPropagatorBuilderTest.assertPropagatorBuilderIsACopy;
  
  /**
   * Unit tests for {@link EphemerisPropagatorBuilder}.
   *
   * @author Vincent Cucchietti
   */
  public class EphemerisPropagatorBuilderTest {
      @Test
      @DisplayName("Test buildPropagator method")
      void should_create_expected_propagator() {
  
          // Given
          final Orbit orbit = new CartesianOrbit(new PVCoordinates(
                  new Vector3D(Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS + 400000, 0, 0),
                  new Vector3D(0, 7668.6, 0)), FramesFactory.getGCRF(), new AbsoluteDate(),
                                                 Constants.EIGEN5C_EARTH_MU);
          final List<SpacecraftState> states = new ArrayList<>();
          states.add(new SpacecraftState(orbit));
          states.add(new SpacecraftState(orbit.shiftedBy(1)));
  
          final Frame                             frame             = FramesFactory.getGCRF();
          final TimeInterpolator<SpacecraftState> stateInterpolator = new SpacecraftStateInterpolator(frame);
  
          final EphemerisPropagatorBuilder builder =
                  new EphemerisPropagatorBuilder(states, stateInterpolator);
  
          // When
          final Ephemeris builtPropagator = (Ephemeris) builder.buildPropagator(builder.getSelectedNormalizedParameters());
  
          // Then
          final Ephemeris expectedPropagator = new Ephemeris(states, stateInterpolator);
  
          Assertions.assertEquals(expectedPropagator.getFrame(), builtPropagator.getFrame());
          Assertions.assertEquals(expectedPropagator.getMinDate(), builtPropagator.getMinDate());
          Assertions.assertEquals(expectedPropagator.getMaxDate(), builtPropagator.getMaxDate());
  
          Assertions.assertArrayEquals(expectedPropagator.getManagedAdditionalStates(),
                                       builtPropagator.getManagedAdditionalStates());
          // Initial state has also been verified to be equal between both ephemeris (except for the Attitude which is expected
          // to have different memory address)
      }
  
      @Test
      @DisplayName("Test copy method")
      void testCopyMethod() {
  
          // Given
          final Orbit orbit = new CartesianOrbit(new PVCoordinates(
                  new Vector3D(Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS + 400000, 0, 0),
                  new Vector3D(0, 7668.6, 0)), FramesFactory.getGCRF(),
                                                 new AbsoluteDate(), Constants.EIGEN5C_EARTH_MU);
          final List<SpacecraftState> states = new ArrayList<>();
          states.add(new SpacecraftState(orbit));
          states.add(new SpacecraftState(orbit));
  
          final Frame                             frame             = FramesFactory.getGCRF();
          final TimeInterpolator<SpacecraftState> stateInterpolator = new SpacecraftStateInterpolator(frame);
          final AttitudeProvider                  attitudeProvider  = Mockito.mock(AttitudeProvider.class);
 
         final EphemerisPropagatorBuilder builder =
                 new EphemerisPropagatorBuilder(states, stateInterpolator, attitudeProvider);
 
         // When
         final EphemerisPropagatorBuilder copyBuilder = builder.copy();
 
         // Then
         assertPropagatorBuilderIsACopy(builder, copyBuilder);
     }
 }