AngularAzElBuilder.java

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package org.orekit.estimation.measurements.generation;

import java.util.Map;

import org.hipparchus.random.CorrelatedRandomVectorGenerator;
import org.orekit.estimation.measurements.AngularAzEl;
import org.orekit.estimation.measurements.EstimationModifier;
import org.orekit.estimation.measurements.GroundStation;
import org.orekit.estimation.measurements.ObservableSatellite;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.sampling.OrekitStepInterpolator;
import org.orekit.time.AbsoluteDate;
import org.orekit.utils.ParameterDriver;


/** Builder for {@link AngularAzEl} measurements.
 * @author Luc Maisonobe
 * @since 9.3
 */
public class AngularAzElBuilder extends AbstractMeasurementBuilder<AngularAzEl> {

    /** Ground station from which measurement is performed. */
    private final GroundStation station;

    /** Satellite related to this builder.
     * @since 12.0
     */
    private final ObservableSatellite satellite;

    /** Simple constructor.
     * @param noiseSource noise source, may be null for generating perfect measurements
     * @param station ground station from which measurement is performed
     * @param sigma theoretical standard deviation
     * @param baseWeight base weight
     * @param satellite satellite related to this builder
     */
    public AngularAzElBuilder(final CorrelatedRandomVectorGenerator noiseSource,
                              final GroundStation station,
                              final double[] sigma, final double[] baseWeight,
                              final ObservableSatellite satellite) {
        super(noiseSource, sigma, baseWeight, satellite);
        this.station   = station;
        this.satellite = satellite;
    }

    /** {@inheritDoc} */
    @Override
    public AngularAzEl build(final AbsoluteDate date, final Map<ObservableSatellite, OrekitStepInterpolator> interpolators) {

        final double[] sigma                = getTheoreticalStandardDeviation();
        final double[] baseWeight           = getBaseWeight();
        final SpacecraftState[] relevant    = new SpacecraftState[] { interpolators.get(satellite).getInterpolatedState(date) };

        // create a dummy measurement
        final AngularAzEl dummy = new AngularAzEl(station, relevant[0].getDate(),
                                                  new double[] {
                                                      0.0, 0.0
                                                  }, sigma, baseWeight, satellite);
        for (final EstimationModifier<AngularAzEl> modifier : getModifiers()) {
            dummy.addModifier(modifier);
        }

        // set a reference date for parameters missing one
        for (final ParameterDriver driver : dummy.getParametersDrivers()) {
            if (driver.getReferenceDate() == null) {
                final AbsoluteDate start = getStart();
                final AbsoluteDate end   = getEnd();
                driver.setReferenceDate(start.durationFrom(end) <= 0 ? start : end);
            }
        }

        // estimate the perfect value of the measurement
        final double[] angular = dummy.estimateWithoutDerivatives(relevant).getEstimatedValue();

        // add the noise
        final double[] noise = getNoise();
        if (noise != null) {
            angular[0] += noise[0];
            angular[1] += noise[1];
        }

        // generate measurement
        final AngularAzEl measurement = new AngularAzEl(station, relevant[0].getDate(), angular,
                                                        sigma, baseWeight, satellite);
        for (final EstimationModifier<AngularAzEl> modifier : getModifiers()) {
            measurement.addModifier(modifier);
        }
        return measurement;

    }

}