/* Copyright 2022-2025 Romain Serra
    * 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.semianalytical.dsst.forces;
  
  import org.hipparchus.CalculusFieldElement;
  import org.hipparchus.Field;
  import org.hipparchus.complex.Complex;
  import org.hipparchus.complex.ComplexField;
  import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.hipparchus.util.MathArrays;
  import org.hipparchus.util.MathUtils;
  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.FrameAlignedProvider;
  import org.orekit.forces.ForceModel;
  import org.orekit.frames.FramesFactory;
  import org.orekit.orbits.EquinoctialOrbit;
  import org.orekit.orbits.FieldEquinoctialOrbit;
  import org.orekit.orbits.FieldOrbit;
  import org.orekit.orbits.PositionAngleType;
  import org.orekit.propagation.FieldSpacecraftState;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.semianalytical.dsst.utilities.AuxiliaryElements;
  import org.orekit.propagation.semianalytical.dsst.utilities.FieldAuxiliaryElements;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.utils.Constants;
  import org.orekit.utils.ParameterDriver;
  
  import java.util.Collections;
  import java.util.List;
  
  class AbstractGaussianContributionTest {
  
      @Test
      @DisplayName("Coverage test for attitude building when not depending on rate")
      void testGetMeanElementRateWhenNotDependingOnAttitudeRate() {
          testTemplateGetMeanElementRate(false);
      }
  
      @Test
      @DisplayName("Coverage test for attitude building when depending on rate")
      void testGetMeanElementRateWhenDependingOnAttitudeRate() {
          testTemplateGetMeanElementRate(true);
      }
  
      void testTemplateGetMeanElementRate(final boolean dependsOnAttitudeRate) {
          // GIVEN
          final double mu = Constants.EIGEN5C_EARTH_MU;
          final EquinoctialOrbit orbit = new EquinoctialOrbit(7e6, 0., 0.001, 0.01, 0., 0., PositionAngleType.ECCENTRIC,
                  FramesFactory.getGCRF(), AbsoluteDate.ARBITRARY_EPOCH, mu);
          final ForceModel mockedForce = Mockito.mock(ForceModel.class);
          Mockito.when(mockedForce.dependsOnAttitudeRate()).thenReturn(dependsOnAttitudeRate);
          Mockito.when(mockedForce.acceleration(Mockito.any(SpacecraftState.class), Mockito.any())).thenReturn(Vector3D.ZERO);
          final TestContribution testContribution = new TestContribution("", 1., mockedForce,
                  mu);
          final SpacecraftState state = new SpacecraftState(orbit);
          final AuxiliaryElements elements = new AuxiliaryElements(orbit, 1);
          testContribution.registerAttitudeProvider(new FrameAlignedProvider(orbit.getFrame()));
          // WHEN
          final double[] rates = testContribution.getMeanElementRate(state, elements, new double[1]);
          // THEN
          Assertions.assertEquals(6, rates.length);
      }
  
      @Test
      @DisplayName("Coverage test for Field attitude building when depending on rate")
      void testFieldGetMeanElementRateWhenDependingOnAttitudeRate() {
          testTemplateFieldGetMeanElementRate(true);
      }
  
      @Test
      @DisplayName("Coverage test for Field attitude building when not depending on rate")
      void testFieldGetMeanElementRateWhenNotDependingOnAttitudeRate() {
          testTemplateFieldGetMeanElementRate(false);
      }
  
      @SuppressWarnings("unchecked")
      void testTemplateFieldGetMeanElementRate(final boolean dependsOnAttitudeRate) {
          // GIVEN
          final Field<Complex> field = ComplexField.getInstance();
          final double mu = Constants.EIGEN5C_EARTH_MU;
          final EquinoctialOrbit orbit = new EquinoctialOrbit(7e6, 0., 0.001, 0.01, 0., 0., PositionAngleType.ECCENTRIC,
                 FramesFactory.getGCRF(), AbsoluteDate.ARBITRARY_EPOCH, mu);
         final FieldOrbit<Complex> fieldOrbit = new FieldEquinoctialOrbit<>(field, orbit);
         final ForceModel mockedForce = Mockito.mock(ForceModel.class);
         Mockito.when(mockedForce.dependsOnAttitudeRate()).thenReturn(dependsOnAttitudeRate);
         Mockito.when(mockedForce.acceleration(Mockito.any(FieldSpacecraftState.class), Mockito.any()))
                 .thenReturn(FieldVector3D.getZero(field));
         final TestContribution testContribution = new TestContribution("", 1., mockedForce,
                 mu);
         final FieldAuxiliaryElements<Complex> elements = new FieldAuxiliaryElements<>(fieldOrbit, 1);
         testContribution.registerAttitudeProvider(new FrameAlignedProvider(orbit.getFrame()));
         final Complex[] parameters = MathArrays.buildArray(field, 1);
         parameters[0] = field.getOne();
         // WHEN
         final Complex[] rates = testContribution.getMeanElementRate(new FieldSpacecraftState<>(fieldOrbit), elements, parameters);
         // THEN
         Assertions.assertEquals(6, rates.length);
     }
 
     private static class TestContribution extends AbstractGaussianContribution {
 
         protected TestContribution(String coefficientsKeyPrefix, double threshold, ForceModel contribution, double mu) {
             super(coefficientsKeyPrefix, threshold, contribution, mu);
         }
 
         @Override
         protected List<ParameterDriver> getParametersDriversWithoutMu() {
             return Collections.emptyList();
         }
 
         @Override
         protected double[] getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements) {
             return new double[] {0., 1.};
         }
 
         @Override
         protected <T extends CalculusFieldElement<T>> T[] getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements) {
             final Field<T> field = state.getDate().getField();
             final T[] array = MathArrays.buildArray(field, 2);
             array[0] = field.getZero();
             array[1] = field.getOne();
             return array;
 
         }
     }
 
 }