use of org.hipparchus.stat.descriptive.rank.Min in project Orekit by CS-SI.
the class TurnAroundRangeAnalyticTest method genericTestValues.
/**
* Generic test function for values of the TAR
* @param printResults Print the results ?
* @throws OrekitException
*/
void genericTestValues(final boolean printResults) throws OrekitException {
Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
// Context context = EstimationTestUtils.geoStationnaryContext();
final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
// create perfect range measurements
final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new TurnAroundRangeMeasurementCreator(context), 1.0, 3.0, 300.0);
propagator.setSlaveMode();
double[] absoluteErrors = new double[measurements.size()];
double[] relativeErrors = new double[measurements.size()];
int index = 0;
// Print the results ? Header
if (printResults) {
System.out.format(Locale.US, "%-15s %-15s %-23s %-23s %17s %17s %13s %13s%n", "Master Station", "Slave Station", "Measurement Date", "State Date", "TAR observed [m]", "TAR estimated [m]", "|ΔTAR| [m]", "rel |ΔTAR|");
}
// Loop on the measurements
for (final ObservedMeasurement<?> measurement : measurements) {
final double meanDelay = measurement.getObservedValue()[0] / Constants.SPEED_OF_LIGHT;
final AbsoluteDate date = measurement.getDate().shiftedBy(meanDelay);
final SpacecraftState state = propagator.propagate(date);
// Values of the TAR & errors
final double TARobserved = measurement.getObservedValue()[0];
final double TARestimated = new TurnAroundRangeAnalytic((TurnAroundRange) measurement).theoreticalEvaluationAnalytic(0, 0, propagator.getInitialState(), state).getEstimatedValue()[0];
absoluteErrors[index] = TARestimated - TARobserved;
relativeErrors[index] = FastMath.abs(absoluteErrors[index]) / FastMath.abs(TARobserved);
index++;
// Print results ? Values
if (printResults) {
final AbsoluteDate measurementDate = measurement.getDate();
String masterStationName = ((TurnAroundRange) measurement).getMasterStation().getBaseFrame().getName();
String slaveStationName = ((TurnAroundRange) measurement).getSlaveStation().getBaseFrame().getName();
System.out.format(Locale.US, "%-15s %-15s %-23s %-23s %17.6f %17.6f %13.6e %13.6e%n", masterStationName, slaveStationName, measurementDate, date, TARobserved, TARestimated, FastMath.abs(TARestimated - TARobserved), FastMath.abs((TARestimated - TARobserved) / TARobserved));
}
}
// Compute some statistics
final double absErrorsMedian = new Median().evaluate(absoluteErrors);
final double absErrorsMin = new Min().evaluate(absoluteErrors);
final double absErrorsMax = new Max().evaluate(absoluteErrors);
final double relErrorsMedian = new Median().evaluate(relativeErrors);
final double relErrorsMax = new Max().evaluate(relativeErrors);
// 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);
}
// Assert statistical errors
Assert.assertEquals(0.0, absErrorsMedian, 8.4e-08);
Assert.assertEquals(0.0, absErrorsMin, 9.0e-08);
Assert.assertEquals(0.0, absErrorsMax, 2.0e-07);
Assert.assertEquals(0.0, relErrorsMedian, 5.1e-15);
Assert.assertEquals(0.0, relErrorsMax, 1.2e-14);
}
use of org.hipparchus.stat.descriptive.rank.Min in project Orekit by CS-SI.
the class TurnAroundRangeTest method genericTestValues.
/**
* Generic test function for values of the TAR
* @param printResults Print the results ?
* @throws OrekitException
*/
void genericTestValues(final boolean printResults) throws OrekitException {
Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
// Context context = EstimationTestUtils.geoStationnaryContext();
final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
// create perfect range measurements
final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new TurnAroundRangeMeasurementCreator(context), 1.0, 3.0, 300.0);
propagator.setSlaveMode();
double[] absoluteErrors = new double[measurements.size()];
double[] relativeErrors = new double[measurements.size()];
int index = 0;
// Print the results ? Header
if (printResults) {
System.out.format(Locale.US, "%-15s %-15s %-23s %-23s %17s %17s %13s %13s%n", "Master Station", "Slave Station", "Measurement Date", "State Date", "TAR observed [m]", "TAR estimated [m]", "|ΔTAR| [m]", "rel |ΔTAR|");
}
// Loop on the measurements
for (final ObservedMeasurement<?> measurement : measurements) {
final double meanDelay = measurement.getObservedValue()[0] / Constants.SPEED_OF_LIGHT;
final AbsoluteDate date = measurement.getDate().shiftedBy(meanDelay);
final SpacecraftState state = propagator.propagate(date);
// Values of the TAR & errors
final double TARobserved = measurement.getObservedValue()[0];
final EstimatedMeasurement<?> estimated = measurement.estimate(0, 0, new SpacecraftState[] { state });
final double TARestimated = estimated.getEstimatedValue()[0];
final TimeStampedPVCoordinates[] participants = estimated.getParticipants();
Assert.assertEquals(5, participants.length);
Assert.assertEquals(0.5 * Constants.SPEED_OF_LIGHT * participants[4].getDate().durationFrom(participants[0].getDate()), estimated.getEstimatedValue()[0], 2.0e-8);
absoluteErrors[index] = TARestimated - TARobserved;
relativeErrors[index] = FastMath.abs(absoluteErrors[index]) / FastMath.abs(TARobserved);
index++;
// Print results ? Values
if (printResults) {
final AbsoluteDate measurementDate = measurement.getDate();
String masterStationName = ((TurnAroundRange) measurement).getMasterStation().getBaseFrame().getName();
String slaveStationName = ((TurnAroundRange) measurement).getSlaveStation().getBaseFrame().getName();
System.out.format(Locale.US, "%-15s %-15s %-23s %-23s %17.6f %17.6f %13.6e %13.6e%n", masterStationName, slaveStationName, measurementDate, date, TARobserved, TARestimated, FastMath.abs(TARestimated - TARobserved), FastMath.abs((TARestimated - TARobserved) / TARobserved));
}
}
// Compute some statistics
final double absErrorsMedian = new Median().evaluate(absoluteErrors);
final double absErrorsMin = new Min().evaluate(absoluteErrors);
final double absErrorsMax = new Max().evaluate(absoluteErrors);
final double relErrorsMedian = new Median().evaluate(relativeErrors);
final double relErrorsMax = new Max().evaluate(relativeErrors);
// 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);
}
// Assert statistical errors
Assert.assertEquals(0.0, absErrorsMedian, 1.4e-7);
Assert.assertEquals(0.0, absErrorsMin, 5.0e-7);
Assert.assertEquals(0.0, absErrorsMax, 4.9e-7);
Assert.assertEquals(0.0, relErrorsMedian, 8.9e-15);
Assert.assertEquals(0.0, relErrorsMax, 2.9e-14);
}
use of org.hipparchus.stat.descriptive.rank.Min in project Orekit by CS-SI.
the class InterSatellitesRangeTest method genericTestValues.
/**
* Generic test function for values of the inter-satellites range
* @param printResults Print the results ?
* @throws OrekitException
*/
void genericTestValues(final boolean printResults) throws OrekitException {
Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
// Create perfect inter-satellites range 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);
closePropagator.setEphemerisMode();
closePropagator.propagate(context.initialOrbit.getDate().shiftedBy(3.5 * closeOrbit.getKeplerianPeriod()));
final BoundedPropagator ephemeris = closePropagator.getGeneratedEphemeris();
final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new InterSatellitesRangeMeasurementCreator(ephemeris), 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<Double>();
final List<Double> relativeErrors = new ArrayList<Double>();
// Set master mode
// Use a lambda function to implement "handleStep" function
propagator.setMasterMode((OrekitStepInterpolator interpolator, boolean isLast) -> {
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 & errors
final double RangeObserved = measurement.getObservedValue()[0];
final EstimatedMeasurement<?> estimated = measurement.estimate(0, 0, new SpacecraftState[] { state, ephemeris.propagate(state.getDate()) });
// the real state used for estimation is adjusted according to downlink delay
double adjustment = state.getDate().durationFrom(estimated.getStates()[0].getDate());
Assert.assertTrue(adjustment > 0.000006);
Assert.assertTrue(adjustment < 0.0003);
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
});
// Print results on console ? Header
if (printResults) {
System.out.format(Locale.US, "%-23s %-23s %19s %19s %13s %13s%n", "Measurement Date", "State Date", "Range observed [m]", "Range estimated [m]", "ΔRange [m]", "rel ΔRange");
}
// Rewind the propagator to initial date
propagator.propagate(context.initialOrbit.getDate());
// Sort measurements chronologically
measurements.sort(new ChronologicalComparator());
// 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);
}
Assert.assertEquals(0.0, absErrorsMedian, 1.3e-7);
Assert.assertEquals(0.0, absErrorsMin, 7.3e-7);
Assert.assertEquals(0.0, absErrorsMax, 1.8e-7);
Assert.assertEquals(0.0, relErrorsMedian, 1.0e-12);
Assert.assertEquals(0.0, relErrorsMax, 3.2e-12);
}
use of org.hipparchus.stat.descriptive.rank.Min in project Orekit by CS-SI.
the class RangeTest method genericTestValues.
/**
* Generic test function for values of the range
* @param printResults Print the results ?
* @throws OrekitException
*/
void genericTestValues(final boolean printResults) throws OrekitException {
Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
// Create perfect range measurements
final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new RangeMeasurementCreator(context), 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<Double>();
final List<Double> relativeErrors = new ArrayList<Double>();
// Set master mode
// Use a lambda function to implement "handleStep" function
propagator.setMasterMode((OrekitStepInterpolator interpolator, boolean isLast) -> {
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 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 state = interpolator.getInterpolatedState(date);
// Values of the Range & errors
final double RangeObserved = measurement.getObservedValue()[0];
final EstimatedMeasurement<?> estimated = measurement.estimate(0, 0, new SpacecraftState[] { state });
final TimeStampedPVCoordinates[] participants = estimated.getParticipants();
Assert.assertEquals(3, participants.length);
Assert.assertEquals(0.5 * Constants.SPEED_OF_LIGHT * participants[2].getDate().durationFrom(participants[0].getDate()), estimated.getEstimatedValue()[0], 2.0e-8);
// the real state used for estimation is adjusted according to downlink delay
double adjustment = state.getDate().durationFrom(estimated.getStates()[0].getDate());
Assert.assertTrue(adjustment > 0.006);
Assert.assertTrue(adjustment < 0.010);
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();
String stationName = ((Range) measurement).getStation().getBaseFrame().getName();
System.out.format(Locale.US, "%-15s %-23s %-23s %19.6f %19.6f %13.6e %13.6e%n", stationName, 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
});
// Print results on console ? Header
if (printResults) {
System.out.format(Locale.US, "%-15s %-23s %-23s %19s %19s %13s %13s%n", "Station", "Measurement Date", "State Date", "Range observed [m]", "Range estimated [m]", "ΔRange [m]", "rel ΔRange");
}
// Rewind the propagator to initial date
propagator.propagate(context.initialOrbit.getDate());
// Sort measurements chronologically
measurements.sort(new ChronologicalComparator());
// 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);
}
Assert.assertEquals(0.0, absErrorsMedian, 4.9e-8);
Assert.assertEquals(0.0, absErrorsMin, 2.2e-7);
Assert.assertEquals(0.0, absErrorsMax, 2.1e-7);
Assert.assertEquals(0.0, relErrorsMedian, 1.0e-14);
Assert.assertEquals(0.0, relErrorsMax, 2.6e-14);
}
use of org.hipparchus.stat.descriptive.rank.Min in project Orekit by CS-SI.
the class RangeAnalyticTest method genericTestValues.
/**
* Generic test function for values of the range
* @param printResults Print the results ?
* @throws OrekitException
*/
void genericTestValues(final boolean printResults) throws OrekitException {
Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
// Create perfect range measurements
final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new RangeMeasurementCreator(context), 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<Double>();
final List<Double> relativeErrors = new ArrayList<Double>();
// Set master mode
// Use a lambda function to implement "handleStep" function
propagator.setMasterMode((OrekitStepInterpolator interpolator, boolean isLast) -> {
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 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 state = interpolator.getInterpolatedState(date);
// Values of the RangeAnalytic & errors
final double RangeObserved = measurement.getObservedValue()[0];
final double RangeEstimated = new RangeAnalytic((Range) measurement).theoreticalEvaluationAnalytic(0, 0, state).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();
String stationName = ((Range) measurement).getStation().getBaseFrame().getName();
System.out.format(Locale.US, "%-15s %-23s %-23s %19.6f %19.6f %13.6e %13.6e%n", stationName, 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
});
// Print results on console ? Header
if (printResults) {
System.out.format(Locale.US, "%-15s %-23s %-23s %19s %19s %13s %13s%n", "Station", "Measurement Date", "State Date", "Range observed [m]", "Range estimated [m]", "ΔRange [m]", "rel ΔRange");
}
// Rewind the propagator to initial date
propagator.propagate(context.initialOrbit.getDate());
// Sort measurements chronologically
measurements.sort(new ChronologicalComparator());
// 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);
}
Assert.assertEquals(0.0, absErrorsMedian, 3.8e-08);
Assert.assertEquals(0.0, absErrorsMin, 2.0e-07);
Assert.assertEquals(0.0, absErrorsMax, 2.3e-07);
Assert.assertEquals(0.0, relErrorsMedian, 6.5e-15);
Assert.assertEquals(0.0, relErrorsMax, 2.4e-14);
}
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