/* Copyright 2002-2022 CS GROUP
    * 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.estimation.measurements.modifiers;
  
  import java.util.Arrays;
  
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.hipparchus.util.FastMath;
  import org.junit.Assert;
  import org.junit.Before;
  import org.junit.Test;
  import org.orekit.Utils;
  import org.orekit.bodies.GeodeticPoint;
  import org.orekit.bodies.OneAxisEllipsoid;
  import org.orekit.estimation.measurements.EstimatedMeasurement;
  import org.orekit.estimation.measurements.GroundStation;
  import org.orekit.estimation.measurements.ObservableSatellite;
  import org.orekit.estimation.measurements.Range;
  import org.orekit.frames.FramesFactory;
  import org.orekit.frames.TopocentricFrame;
  import org.orekit.orbits.CartesianOrbit;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.analytical.tle.TLE;
  import org.orekit.propagation.analytical.tle.TLEPropagator;
  import org.orekit.utils.Constants;
  import org.orekit.utils.IERSConventions;
  import org.orekit.utils.ParameterDriver;
  import org.orekit.utils.TimeStampedPVCoordinates;
  
  public class RelativisticClockRangeModifierTest {
  
      @Test
      public void testRelativisticClockCorrection() {
  
          // Station
          final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
                                                              Constants.WGS84_EARTH_FLATTENING,
                                                              FramesFactory.getITRF(IERSConventions.IERS_2010, true));
          final GeodeticPoint point    = new GeodeticPoint(FastMath.toRadians(42.0), FastMath.toRadians(1.0), 100.0);
          final TopocentricFrame topo  = new TopocentricFrame(earth, point, "");
          final GroundStation station  = new GroundStation(topo);
  
          // Satellite (GPS orbit from TLE)
          final TLE tle = new TLE("1 28474U 04045A   20252.59334296 -.00000043  00000-0  00000-0 0  9998",
                                  "2 28474  55.0265  49.5108 0200271 267.9106 149.0797  2.00552216116165");
          final TimeStampedPVCoordinates satPV = TLEPropagator.selectExtrapolator(tle).getPVCoordinates(tle.getDate(), FramesFactory.getEME2000());
          final SpacecraftState state = new SpacecraftState(new CartesianOrbit(satPV, FramesFactory.getEME2000(), Constants.WGS84_EARTH_MU));
  
          // Set reference date to station drivers
          for (ParameterDriver driver : Arrays.asList(station.getClockOffsetDriver(),
                                                      station.getEastOffsetDriver(),
                                                      station.getNorthOffsetDriver(),
                                                      station.getZenithOffsetDriver(),
                                                      station.getPrimeMeridianOffsetDriver(),
                                                      station.getPrimeMeridianDriftDriver(),
                                                      station.getPolarOffsetXDriver(),
                                                      station.getPolarDriftXDriver(),
                                                      station.getPolarOffsetYDriver(),
                                                      station.getPolarDriftYDriver())) {
              if (driver.getReferenceDate() == null) {
                  driver.setReferenceDate(state.getDate());
              }
          }
  
          // Station PV
          final Vector3D zero = Vector3D.ZERO;
          final TimeStampedPVCoordinates stationPV = station.getOffsetToInertial(state.getFrame(), state.getDate()).transformPVCoordinates(new TimeStampedPVCoordinates(state.getDate(), zero, zero, zero));
  
          // Range measurement
          final Range range = new Range(station, false, state.getDate(), 26584264.45, 1.0, 1.0, new ObservableSatellite(0));
          final EstimatedMeasurement<Range> estimated = new EstimatedMeasurement<Range>(range, 0, 0,
                          new SpacecraftState[] {state},
                          new TimeStampedPVCoordinates[] {state.getPVCoordinates(), stationPV});
          estimated.setEstimatedValue(range.getObservedValue()[0]);
          Assert.assertEquals(0.0, estimated.getObservedValue()[0] - estimated.getEstimatedValue()[0], 1.0e-3);
  
          // Measurement modifier
          final RelativisticClockRangeModifier modifier = new RelativisticClockRangeModifier();
          modifier.modify(estimated);
          Assert.assertEquals(0, modifier.getParametersDrivers().size());
  
          // Verify
          Assert.assertEquals(-6.87, estimated.getObservedValue()[0] - estimated.getEstimatedValue()[0], 1.0e-2);
  
      }
 
     @Before
     public void setUp() {
         Utils.setDataRoot("regular-data");
     }
 
 }