/* 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,
   * 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.gnss;
  
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.hipparchus.stat.descriptive.moment.Mean;
  import org.hipparchus.stat.descriptive.rank.Max;
  import org.hipparchus.stat.descriptive.rank.Median;
  import org.hipparchus.stat.descriptive.rank.Min;
  import org.hipparchus.util.FastMath;
  import org.junit.jupiter.api.Assertions;
  import org.junit.jupiter.api.Test;
  import org.orekit.estimation.Context;
  import org.orekit.estimation.EstimationTestUtils;
  import org.orekit.estimation.measurements.EstimatedMeasurementBase;
  import org.orekit.estimation.measurements.ObservedMeasurement;
  import org.orekit.orbits.CartesianOrbit;
  import org.orekit.orbits.Orbit;
  import org.orekit.orbits.OrbitType;
  import org.orekit.orbits.PositionAngleType;
  import org.orekit.propagation.BoundedPropagator;
  import org.orekit.propagation.EphemerisGenerator;
  import org.orekit.propagation.Propagator;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.conversion.NumericalPropagatorBuilder;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.utils.Constants;
  import org.orekit.utils.Differentiation;
  import org.orekit.utils.ParameterDriver;
  import org.orekit.utils.ParameterFunction;
  import org.orekit.utils.TimeSpanMap.Span;
  import org.orekit.utils.TimeStampedPVCoordinates;
  
  import java.util.ArrayList;
  import java.util.Comparator;
  import java.util.List;
  import java.util.Locale;
  
  public class OneWayGNSSRangeRateTest {
  
      /**
       * Test the values of the range rate comparing the observed values and the estimated values
       * Both are calculated with a different algorithm
       */
      @Test
      public void testValues() {
          boolean printResults = false;
          if (printResults) {
              System.out.println("\nTest One-way GNSS range rate Values\n");
          }
          // Run test
          this.genericTestValues(printResults);
      }
  
      /**
       * Test the values of the state derivatives using a numerical
       * finite differences calculation as a reference
       */
      @Test
      public void testStateDerivatives() {
  
          boolean printResults = false;
          if (printResults) {
              System.out.println("\nTest One-way GNSS range rate State Derivatives - Finite Differences Comparison\n");
          }
          // Run test
          // the following relative tolerances for derivatives with respect to velocity
          // may seem high, but they have been validated. The partial derivative of
          // signal flight time with respect to velocity ∂τ/∂{vx, vy, vz} is about 10⁻¹³
          // when the signal flight time τ is about 10⁻⁴, so finite differences lose
          // about 9 significant figures, so it is expected that partial derivatives
          // computed with finite differences will only have a few digits corrects and
          // that there will be outliers
          double refErrorsPMedian = 5.6e-10;
          double refErrorsPMean   = 3.4e-09;
          double refErrorsPMax    = 6.8e-07;
          double refErrorsVMedian = 6.6e-11;
          double refErrorsVMean   = 1.8e-10;
          double refErrorsVMax    = 7.1e-09;
          this.genericTestStateDerivatives(printResults, 0,
                                           refErrorsPMedian, refErrorsPMean, refErrorsPMax,
                                           refErrorsVMedian, refErrorsVMean, refErrorsVMax);
      }
  
      /**
      * Test the values of the parameters' derivatives using a numerical
      * finite differences calculation as a reference
      */
     @Test
     public void testParameterDerivatives() {
 
         // Print the results ?
         boolean printResults = false;
 
         if (printResults) {
             System.out.println("\nTest One-way GNSS range rate Derivatives - Finite Differences Comparison\n");
         }
         // Run test
         double refErrorsMedian = 6.7e-8;
         double refErrorsMean   = 2.1e-7;
         double refErrorsMax    = 2.8e-6;
         this.genericTestParameterDerivatives(printResults,
                                              refErrorsMedian, refErrorsMean, refErrorsMax);
 
     }
 
     /**
      * Generic test function for values of the one-way GNSS range
      * @param printResults Print the results ?
      */
     void genericTestValues(final boolean printResults) {
 
         Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
 
         final NumericalPropagatorBuilder propagatorBuilder =
                         context.createBuilder(OrbitType.KEPLERIAN, PositionAngleType.TRUE, true,
                                               1.0e-6, 60.0, 0.001);
 
         // Create perfect inter-satellites range rate measurements
         final TimeStampedPVCoordinates original = context.initialOrbit.getPVCoordinates();
         final Orbit closeOrbit = new CartesianOrbit(new TimeStampedPVCoordinates(context.initialOrbit.getDate(),
                                                                                  original.getPosition().add(new Vector3D(1000, 2000, 3000)),
                                                                                  original.getVelocity().add(new Vector3D(-0.03, 0.01, 0.02))),
                                                     context.initialOrbit.getFrame(),
                                                     context.initialOrbit.getMu());
         final Propagator closePropagator = EstimationTestUtils.createPropagator(closeOrbit,
                                                                                 propagatorBuilder);
         final EphemerisGenerator generator = closePropagator.getEphemerisGenerator();
         closePropagator.propagate(context.initialOrbit.getDate().shiftedBy(3.5 * closeOrbit.getKeplerianPeriod()));
         final BoundedPropagator ephemeris = generator.getGeneratedEphemeris();
         final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit,
                                                                            propagatorBuilder);
 
         final double localClockOffset        =   0.14e-06;
         final double localClockRate          =  -0.12e-10;
         final double localClockAcceleration  =   1.4e-13;
         final double remoteClockOffset       = 469.0e-06;
         final double remoteClockRate         =  33.0e-10;
         final double remoteClockAcceleration =   0.5e-13;
         final List<ObservedMeasurement<?>> measurements =
                         EstimationTestUtils.createMeasurements(propagator,
                                                                new OneWayGNSSRangeRateCreator(ephemeris,
                                                                                               localClockOffset, localClockRate, localClockAcceleration,
                                                                                               remoteClockOffset, remoteClockRate, remoteClockAcceleration),
                                                                1.0, 3.0, 300.0);
 
         // Lists for results' storage - Used only for derivatives with respect to state
         // "final" value to be seen by "handleStep" function of the propagator
         final List<Double> absoluteErrors = new ArrayList<>();
         final List<Double> relativeErrors = new ArrayList<>();
 
         // Use a lambda function to implement "handleStep" function
         propagator.setStepHandler(interpolator -> {
 
             for (final ObservedMeasurement<?> measurement : measurements) {
 
                 //  Play test if the measurement date is between interpolator previous and current date
                 if ((measurement.getDate().durationFrom(interpolator.getPreviousState().getDate()) > 0.) &&
                     (measurement.getDate().durationFrom(interpolator.getCurrentState().getDate())  <=  0.)
                    ) {
                     // We intentionally propagate to a date which is close to the
                     // real spacecraft state but is *not* the accurate date, by
                     // compensating only part of the downlink delay. This is done
                     // in order to validate the partial derivatives with respect
                     // to velocity.
                     final double          meanDelay = measurement.getObservedValue()[0] / Constants.SPEED_OF_LIGHT;
                     final AbsoluteDate    date      = measurement.getDate().shiftedBy(-0.75 * meanDelay);
                     final SpacecraftState state     = interpolator.getInterpolatedState(date);
 
                     // Values of the range rate & errors
                     final double rangeObserved  = measurement.getObservedValue()[0];
                     final EstimatedMeasurementBase<?> estimated = measurement.estimateWithoutDerivatives(new SpacecraftState[] {
                                                                                                              state,
                                                                                                              ephemeris.propagate(state.getDate())
                                                                                                          });
 
                     final double rangeEstimated = estimated.getEstimatedValue()[0];
                     final double absoluteError = rangeEstimated-rangeObserved;
                     absoluteErrors.add(absoluteError);
                     relativeErrors.add(FastMath.abs(absoluteError)/FastMath.abs(rangeObserved));
 
                     // Print results on console ?
                     if (printResults) {
                         final AbsoluteDate measurementDate = measurement.getDate();
 
                         System.out.format(Locale.US, "%-23s  %-23s  %19.6f  %19.6f  %13.6e  %13.6e%n",
                                          measurementDate, date,
                                          rangeObserved, rangeEstimated,
                                          FastMath.abs(rangeEstimated-rangeObserved),
                                          FastMath.abs((rangeEstimated-rangeObserved)/rangeObserved));
                     }
 
                 } // End if measurement date between previous and current interpolator step
             } // End for loop on the measurements
         }); // End lambda function handlestep
 
         // Print results on console ? Header
         if (printResults) {
             System.out.format(Locale.US, "%-23s  %-23s  %19s  %19s  %19s  %19s%n",
                               "Measurement Date", "State Date",
                               "range rate observed [m/s]", "range rate estimated [m/s]",
                               "Δrange rate[m/s]", "rel ΔRange rate");
         }
 
         // Rewind the propagator to initial date
         propagator.propagate(context.initialOrbit.getDate());
 
         // Sort measurements chronologically
         measurements.sort(Comparator.naturalOrder());
 
         // Propagate to final measurement's date
         propagator.propagate(measurements.get(measurements.size()-1).getDate());
 
         // Convert lists to double array
         final double[] absErrors = absoluteErrors.stream().mapToDouble(Double::doubleValue).toArray();
         final double[] relErrors = relativeErrors.stream().mapToDouble(Double::doubleValue).toArray();
 
         // Statistics' assertion
         final double absErrorsMedian = new Median().evaluate(absErrors);
         final double absErrorsMin    = new Min().evaluate(absErrors);
         final double absErrorsMax    = new Max().evaluate(absErrors);
         final double relErrorsMedian = new Median().evaluate(relErrors);
         final double relErrorsMax    = new Max().evaluate(relErrors);
 
         // Print the results on console ? Final results
         if (printResults) {
             System.out.println();
             System.out.println("Absolute errors median: " +  absErrorsMedian);
             System.out.println("Absolute errors min   : " +  absErrorsMin);
             System.out.println("Absolute errors max   : " +  absErrorsMax);
             System.out.println("Relative errors median: " +  relErrorsMedian);
             System.out.println("Relative errors max   : " +  relErrorsMax);
         }
 
         Assertions.assertEquals(0.0, absErrorsMedian, 3.9e-9);
         Assertions.assertEquals(0.0, absErrorsMin,    1.2e-11);
         Assertions.assertEquals(0.0, absErrorsMax,    1.6e-8);
         Assertions.assertEquals(0.0, relErrorsMedian, 1.1e-9);
         Assertions.assertEquals(0.0, relErrorsMax,    1.1e-7);
 
         // Test measurement type
         Assertions.assertEquals(OneWayGNSSRangeRate.MEASUREMENT_TYPE, measurements.get(0).getMeasurementType());
     }
 
     void genericTestStateDerivatives(final boolean printResults, final int index,
                                      final double refErrorsPMedian, final double refErrorsPMean, final double refErrorsPMax,
                                      final double refErrorsVMedian, final double refErrorsVMean, final double refErrorsVMax) {
 
         Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
 
         final NumericalPropagatorBuilder propagatorBuilder =
                         context.createBuilder(OrbitType.KEPLERIAN, PositionAngleType.TRUE, true,
                                               1.0e-6, 60.0, 0.001);
 
         // Create perfect one-way GNSS range rate measurements
         final TimeStampedPVCoordinates original = context.initialOrbit.getPVCoordinates();
         final Orbit closeOrbit = new CartesianOrbit(new TimeStampedPVCoordinates(context.initialOrbit.getDate(),
                                                                                  original.getPosition().add(new Vector3D(1000, 2000, 3000)),
                                                                                  original.getVelocity().add(new Vector3D(-0.03, 0.01, 0.02))),
                                                     context.initialOrbit.getFrame(),
                                                     context.initialOrbit.getMu());
         final Propagator closePropagator = EstimationTestUtils.createPropagator(closeOrbit,
                                                                                 propagatorBuilder);
         final EphemerisGenerator generator = closePropagator.getEphemerisGenerator();
         closePropagator.propagate(context.initialOrbit.getDate().shiftedBy(3.5 * closeOrbit.getKeplerianPeriod()));
         final BoundedPropagator ephemeris = generator.getGeneratedEphemeris();
         final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit,
                                                                            propagatorBuilder);
 
         final double localClockOffset        =   0.14e-06;
         final double localClockRate          =  -0.12e-10;
         final double localClockAcceleration  =   1.4e-13;
         final double remoteClockOffset       = 469.0e-06;
         final double remoteClockRate         =  33.0e-10;
         final double remoteClockAcceleration =   0.5e-13;
         final List<ObservedMeasurement<?>> measurements =
                         EstimationTestUtils.createMeasurements(propagator,
                                                                new OneWayGNSSRangeRateCreator(ephemeris,
                                                                                               localClockOffset, localClockRate, localClockAcceleration,
                                                                                               remoteClockOffset, remoteClockRate, remoteClockAcceleration),
                                                                1.0, 3.0, 300.0);
 
         // Lists for results' storage - Used only for derivatives with respect to state
         // "final" value to be seen by "handleStep" function of the propagator
         final List<Double> errorsP = new ArrayList<>();
         final List<Double> errorsV = new ArrayList<>();
 
         // Use a lambda function to implement "handleStep" function
         propagator.setStepHandler(interpolator -> {
 
             for (final ObservedMeasurement<?> measurement : measurements) {
 
                 //  Play test if the measurement date is between interpolator previous and current date
                 if ((measurement.getDate().durationFrom(interpolator.getPreviousState().getDate()) > 0.) &&
                     (measurement.getDate().durationFrom(interpolator.getCurrentState().getDate())  <=  0.)
                    ) {
 
                     // We intentionally propagate to a date which is close to the
                     // real spacecraft state but is *not* the accurate date, by
                     // compensating only part of the downlink delay. This is done
                     // in order to validate the partial derivatives with respect
                     // to velocity.
                     final double            meanDelay = measurement.getObservedValue()[0] / Constants.SPEED_OF_LIGHT;
                     final AbsoluteDate      date      = measurement.getDate().shiftedBy(-0.9 * meanDelay);
                     final SpacecraftState[] states    = {
                         interpolator.getInterpolatedState(date),
                         ephemeris.propagate(date)
                     };
                     final double[][]      jacobian  = measurement.estimate(0, 0, states).getStateDerivatives(index);
 
                     // Jacobian reference value
                     final double[][] jacobianRef;
 
                     // Compute a reference value using finite differences
                     jacobianRef = Differentiation.differentiate(state -> {
                         final SpacecraftState[] s = states.clone();
                         s[index] = state;
                         return measurement.estimateWithoutDerivatives(s).getEstimatedValue();
                     }, measurement.getDimension(), propagator.getAttitudeProvider(),
                                                                 OrbitType.CARTESIAN, PositionAngleType.TRUE, 8.0, 5).value(states[index]);
 
                     Assertions.assertEquals(jacobianRef.length, jacobian.length);
                     Assertions.assertEquals(jacobianRef[0].length, jacobian[0].length);
 
                     // Errors & relative errors on the Jacobian
                     double [][] dJacobian         = new double[jacobian.length][jacobian[0].length];
                     double [][] dJacobianRelative = new double[jacobian.length][jacobian[0].length];
                     for (int i = 0; i < jacobian.length; ++i) {
                         for (int j = 0; j < jacobian[i].length; ++j) {
                             dJacobian[i][j] = jacobian[i][j] - jacobianRef[i][j];
                             dJacobianRelative[i][j] = FastMath.abs(dJacobian[i][j]/jacobianRef[i][j]);
 
                             if (j < 3) { errorsP.add(dJacobianRelative[i][j]);
                             } else { errorsV.add(dJacobianRelative[i][j]); }
                         }
                     }
                     // Print values in console ?
                     if (printResults) {
                         System.out.format(Locale.US, "%-23s  %-23s  " +
                                         "%10.3e  %10.3e  %10.3e  " +
                                         "%10.3e  %10.3e  %10.3e  " +
                                         "%10.3e  %10.3e  %10.3e  " +
                                         "%10.3e  %10.3e  %10.3e%n",
                                         measurement.getDate(), date,
                                         dJacobian[0][0], dJacobian[0][1], dJacobian[0][2],
                                         dJacobian[0][3], dJacobian[0][4], dJacobian[0][5],
                                         dJacobianRelative[0][0], dJacobianRelative[0][1], dJacobianRelative[0][2],
                                         dJacobianRelative[0][3], dJacobianRelative[0][4], dJacobianRelative[0][5]);
                     }
                 } // End if measurement date between previous and current interpolator step
             } // End for loop on the measurements
         });
 
         // Print results on console ?
         if (printResults) {
             System.out.format(Locale.US, "%-23s  %-23s  " +
                             "%10s  %10s  %10s  " +
                             "%10s  %10s  %10s  " +
                             "%10s  %10s  %10s  " +
                             "%10s  %10s  %10s%n",
                             "Measurement Date", "State Date",
                             "ΔdPx", "ΔdPy", "ΔdPz", "ΔdVx", "ΔdVy", "ΔdVz",
                             "rel ΔdPx", "rel ΔdPy", "rel ΔdPz",
                             "rel ΔdVx", "rel ΔdVy", "rel ΔdVz");
         }
 
         // Rewind the propagator to initial date
         propagator.propagate(context.initialOrbit.getDate());
 
         // Sort measurements, primarily chronologically
         measurements.sort(Comparator.naturalOrder());
 
         // Propagate to final measurement's date
         propagator.propagate(measurements.get(measurements.size()-1).getDate());
 
         // Convert lists to double[] and evaluate some statistics
         final double[] relErrorsP = errorsP.stream().mapToDouble(Double::doubleValue).toArray();
         final double[] relErrorsV = errorsV.stream().mapToDouble(Double::doubleValue).toArray();
 
         final double errorsPMedian = new Median().evaluate(relErrorsP);
         final double errorsPMean   = new Mean().evaluate(relErrorsP);
         final double errorsPMax    = new Max().evaluate(relErrorsP);
         final double errorsVMedian = new Median().evaluate(relErrorsV);
         final double errorsVMean   = new Mean().evaluate(relErrorsV);
         final double errorsVMax    = new Max().evaluate(relErrorsV);
 
         // Print the results on console ?
         if (printResults) {
             System.out.println();
             System.out.format(Locale.US, "Relative errors dR/dP -> Median: %6.3e / Mean: %6.3e / Max: %6.3e%n",
                               errorsPMedian, errorsPMean, errorsPMax);
             System.out.format(Locale.US, "Relative errors dR/dV -> Median: %6.3e / Mean: %6.3e / Max: %6.3e%n",
                               errorsVMedian, errorsVMean, errorsVMax);
         }
 
         Assertions.assertEquals(0.0, errorsPMedian, refErrorsPMedian);
         Assertions.assertEquals(0.0, errorsPMean, refErrorsPMean);
         Assertions.assertEquals(0.0, errorsPMax, refErrorsPMax);
         Assertions.assertEquals(0.0, errorsVMedian, refErrorsVMedian);
         Assertions.assertEquals(0.0, errorsVMean, refErrorsVMean);
         Assertions.assertEquals(0.0, errorsVMax, refErrorsVMax);
     }
 
     void genericTestParameterDerivatives(final boolean printResults,
                                          final double refErrorsMedian, final double refErrorsMean, final double refErrorsMax) {
 
         Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
 
         final NumericalPropagatorBuilder propagatorBuilder =
                         context.createBuilder(OrbitType.KEPLERIAN, PositionAngleType.TRUE, true,
                                               1.0e-6, 60.0, 0.001);
 
         // Create perfect one-way GNSS range ratemeasurements
         final TimeStampedPVCoordinates original = context.initialOrbit.getPVCoordinates();
         final Orbit closeOrbit = new CartesianOrbit(new TimeStampedPVCoordinates(context.initialOrbit.getDate(),
                                                                                  original.getPosition().add(new Vector3D(1000, 2000, 3000)),
                                                                                  original.getVelocity().add(new Vector3D(-0.03, 0.01, 0.02))),
                                                     context.initialOrbit.getFrame(),
                                                     context.initialOrbit.getMu());
         final Propagator closePropagator = EstimationTestUtils.createPropagator(closeOrbit, propagatorBuilder);
         final EphemerisGenerator generator = closePropagator.getEphemerisGenerator();
         closePropagator.propagate(context.initialOrbit.getDate().shiftedBy(3.5 * closeOrbit.getKeplerianPeriod()));
         final BoundedPropagator ephemeris = generator.getGeneratedEphemeris();
 
         // Create perfect range ratemeasurements
         final double localClockOffset        =   0.14e-06;
         final double localClockRate          =  -0.12e-10;
         final double localClockAcceleration  =   1.4e-13;
         final double remoteClockOffset       = 469.0e-06;
         final double remoteClockRate         =  33.0e-10;
         final double remoteClockAcceleration =   0.5e-13;
         final OneWayGNSSRangeRateCreator creator = new OneWayGNSSRangeRateCreator(ephemeris,
                                                                                   localClockOffset, localClockRate, localClockAcceleration,
                                                                                   remoteClockOffset, remoteClockRate, remoteClockAcceleration);
         creator.getLocalSatellite().getClockOffsetDriver().setSelected(true);
 
         final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit,
                                                                            propagatorBuilder);
         final List<ObservedMeasurement<?>> measurements =
                         EstimationTestUtils.createMeasurements(propagator, creator, 1.0, 3.0, 300.0);
 
         // List to store the results
         final List<Double> relErrorList = new ArrayList<>();
 
         // Use a lambda function to implement "handleStep" function
         propagator.setStepHandler(interpolator -> {
 
             for (final ObservedMeasurement<?> measurement : measurements) {
 
                 //  Play test if the measurement date is between interpolator previous and current date
                 if ((measurement.getDate().durationFrom(interpolator.getPreviousState().getDate()) > 0.) &&
                     (measurement.getDate().durationFrom(interpolator.getCurrentState().getDate())  <=  0.)) {
 
                     // We intentionally propagate to a date which is close to the
                     // real spacecraft state but is *not* the accurate date, by
                     // compensating only part of the downlink delay. This is done
                     // in order to validate the partial derivatives with respect
                     // to velocity. If we had chosen the proper state date, the
                     // range rate would have depended only on the current position but
                     // not on the current velocity.
                     final double          meanDelay = measurement.getObservedValue()[0] / Constants.SPEED_OF_LIGHT;
                     final AbsoluteDate    date      = measurement.getDate().shiftedBy(-0.75 * meanDelay);
                     final SpacecraftState[] states    = {
                         interpolator.getInterpolatedState(date),
                         ephemeris.propagate(date)
                     };
                     final ParameterDriver[] drivers = new ParameterDriver[] {
                         measurement.getSatellites().get(0).getClockOffsetDriver(),
                     };
 
                     for (int i = 0; i < drivers.length; ++i) {
                         for (Span<String> span = drivers[i].getNamesSpanMap().getFirstSpan(); span != null; span = span.next()) {
 
                             final double[] gradient  = measurement.estimate(0, 0, states).getParameterDerivatives(drivers[i], span.getStart());
                             Assertions.assertEquals(1, measurement.getDimension());
                             Assertions.assertEquals(1, gradient.length);
                             
                             // Compute a reference value using finite differences
                             final ParameterFunction dMkdP =
                                             Differentiation.differentiate(new ParameterFunction() {
                                                 /** {@inheritDoc} */
                                                 @Override
                                                 public double value(final ParameterDriver parameterDriver, final AbsoluteDate date) {
                                                     return measurement.
                                                            estimateWithoutDerivatives(states).
                                                            getEstimatedValue()[0];
                                                 }
                                             }, 5, 10.0 * drivers[i].getScale());
                             final double ref = dMkdP.value(drivers[i], date);
                             
                             if (printResults) {
                                 System.out.format(Locale.US, "%10.3e  %10.3e  ", gradient[0]-ref, FastMath.abs((gradient[0]-ref)/ref));
                             }
                             
                             final double relError = FastMath.abs((ref-gradient[0])/ref);
                             relErrorList.add(relError);
                         }
                     }
                     if (printResults) {
                         System.out.format(Locale.US, "%n");
                     }
 
                 } // End if measurement date between previous and current interpolator step
             } // End for loop on the measurements
         });
 
         // Rewind the propagator to initial date
         propagator.propagate(context.initialOrbit.getDate());
 
         // Sort measurements chronologically
         measurements.sort(Comparator.naturalOrder());
 
         // Print results ? Header
         if (printResults) {
             System.out.format(Locale.US, "%-15s  %-23s  %-23s  " +
                               "%10s  %10s  %10s  %10s  %10s  %10s  %10s  %10s  %10s  %10s%n",
                               "Station", "Measurement Date", "State Date",
                               "Δt",    "rel Δt",
                               "ΔdQx",  "rel ΔdQx",
                               "ΔdQy",  "rel ΔdQy",
                               "ΔdQz",  "rel ΔdQz",
                               "Δtsat", "rel Δtsat");
          }
 
         // Propagate to final measurement's date
         propagator.propagate(measurements.get(measurements.size()-1).getDate());
 
         // Convert error list to double[]
         final double[] relErrors = relErrorList.stream().mapToDouble(Double::doubleValue).toArray();
 
         // Compute statistics
         final double relErrorsMedian = new Median().evaluate(relErrors);
         final double relErrorsMean   = new Mean().evaluate(relErrors);
         final double relErrorsMax    = new Max().evaluate(relErrors);
 
         // Print the results on console ?
         if (printResults) {
             System.out.println();
             System.out.format(Locale.US, "Relative errors dR/dQ -> Median: %6.3e / Mean: %6.3e / Max: %6.3e%n",
                               relErrorsMedian, relErrorsMean, relErrorsMax);
         }
 
         Assertions.assertEquals(0.0, relErrorsMedian, refErrorsMedian);
         Assertions.assertEquals(0.0, relErrorsMean, refErrorsMean);
         Assertions.assertEquals(0.0, relErrorsMax, refErrorsMax);
 
     }
 
 }