/* Copyright 2022-2025 Thales Alenia Space
    * 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,
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   * See the License for the specific language governing permissions and
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  package org.orekit.estimation.measurements.modifiers;
  
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  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.estimation.measurements.EstimatedMeasurement;
  import org.orekit.estimation.measurements.EstimatedMeasurementBase;
  import org.orekit.estimation.measurements.EstimationModifier;
  import org.orekit.estimation.measurements.gnss.InterSatellitesOneWayRangeRate;
  import org.orekit.estimation.measurements.ObservableSatellite;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.analytical.tle.TLE;
  import org.orekit.propagation.analytical.tle.TLEPropagator;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.time.TimeScalesFactory;
  import org.orekit.utils.Constants;
  import org.orekit.utils.PVCoordinates;
  
  public class RelativisticClockInterSatellitesOneWayRangeRateModifierTest {
  
      /** Date. */
      private static AbsoluteDate date;
  
      /** Spacecraft states. */
      private static SpacecraftState[] states;
  
      @Test
      public void testRelativisticClockCorrection() {
  
          // Measurement
          final PVCoordinates delta = new PVCoordinates(states[1].getPVCoordinates(),
                                                        states[0].getPVCoordinates());
          final InterSatellitesOneWayRangeRate range = new InterSatellitesOneWayRangeRate(new ObservableSatellite(0),
                                                                                          new ObservableSatellite(1),
                                                                                          date,
                                                                                          Vector3D.dotProduct(delta.getVelocity(),
                                                                                                              delta.getPosition().normalize()),
                                                                                          1.0, 1.0);
  
          // Inter-satellites range rate before applying the modifier
          final EstimatedMeasurementBase<InterSatellitesOneWayRangeRate> estimatedBefore = range.estimateWithoutDerivatives(states);
  
          // Inter-satellites range rate before applying the modifier
          final EstimationModifier<InterSatellitesOneWayRangeRate> modifier =
              new RelativisticClockInterSatellitesOneWayRangeRateModifier(Constants.EIGEN5C_EARTH_MU);
          range.addModifier(modifier);
          final EstimatedMeasurement<InterSatellitesOneWayRangeRate> estimatedAfter = range.estimate(0, 0, states);
  
          // Verify
          Assertions.assertEquals(1.63e-3, estimatedBefore.getEstimatedValue()[0] - estimatedAfter.getEstimatedValue()[0], 1.0e-5);
          Assertions.assertEquals(0, modifier.getParametersDrivers().size());
          Assertions.assertEquals(1,
                                  estimatedAfter.getAppliedEffects().entrySet().stream().
                                  filter(e -> e.getKey().getEffectName().equals("clock relativity")).count());
      }
  
      @BeforeEach
      public void setUp() {
          // Data root
          Utils.setDataRoot("regular-data");
  
          // Date
          date = new AbsoluteDate("2004-01-13T00:00:00.000", TimeScalesFactory.getUTC());
  
          // Spacecraft states
          states = new SpacecraftState[2];
          final TLE local = new TLE("1 27642U 03002A   04013.91734903  .00000108  00000-0  12227-4 0  3621",
                                    "2 27642  93.9970   6.8623 0003169  80.1383 280.0205 14.90871424 54508");
          final TLE remote = new TLE("1 20061U 89044A   04013.44391333  .00000095  00000-0  10000-3 0  3242",
                                     "2 20061  53.4233 172.2072 0234017 261.4179  95.8975  2.00577231106949");
          states[0] = TLEPropagator.selectExtrapolator(local).propagate(date);
          states[1] = TLEPropagator.selectExtrapolator(remote).propagate(date);
      }
  
  }