NavICAlmanac.java

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 * contributor license agreements.  See the NOTICE file distributed with
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 * CS licenses this file to You under the Apache License, Version 2.0
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package org.orekit.propagation.analytical.gnss.data;

import org.hipparchus.CalculusFieldElement;
import org.orekit.frames.Frame;
import org.orekit.orbits.FieldKeplerianOrbit;
import org.orekit.orbits.KeplerianOrbit;
import org.orekit.time.FieldGNSSDate;
import org.orekit.time.GNSSDate;
import org.orekit.time.TimeScales;

import java.util.function.DoubleFunction;

/**
 * Class for NavIC almanac.
 *
 * @see "Indian Regional Navigation Satellite System, Signal In Space ICD
 *       for standard positioning service, version 1.1 - Table 28"
 *
 * @author Bryan Cazabonne
 * @since 10.1
 *
 */
public class NavICAlmanac extends GNSSOrbitalElements<NavICAlmanac> {

    /**
     * Constructor.
     * @param timeScales known time scales
     * @param prn        PRN number of the satellite
     * @param toe        time of ephemeris (<em>must</em> be consistent with {@code orbit})
     * @param orbit      Keplerian orbit in Earth-frozen frame
     * @param aDot       change rate in semi-major axis (m/s)
     * @param deltaN0    delta of satellite mean motion
     * @param deltaN0Dot change rate in Δn₀
     * @param iDot       inclination rate (rad/s)
     * @param omegaDot   rate of right ascension (rad/s)
     * @param cuc        amplitude of the cosine harmonic correction term to the argument of latitude
     * @param cus        amplitude of the sine harmonic correction term to the argument of latitude
     * @param crc        amplitude of the cosine harmonic correction term to the orbit radius
     * @param crs        amplitude of the sine harmonic correction term to the orbit radius
     * @param cic        amplitude of the cosine harmonic correction term to the inclination
     * @param cis        amplitude of the sine harmonic correction term to the inclination
     * @param af0        zero-th order clock correction (s)
     * @param af1        first order clock correction (s/s)
     * @param af2        second order clock correction (s/s²)
     * @param tgd        group delay differential TGD for L1-L2 correction
     * @param toc        time of clock
     */
    public NavICAlmanac(final TimeScales timeScales, final int prn,
                        final GNSSDate toe, final KeplerianOrbit orbit,
                        final double aDot, final double deltaN0, final double deltaN0Dot,
                        final double iDot, final double omegaDot,
                        final double cuc, final double cus,
                        final double crc, final double crs,
                        final double cic, final double cis,
                        final double af0, final double af1, final double af2,
                        final double tgd, final GNSSDate toc) {
        super(GNSSConstants.NAVIC_AV, GNSSConstants.NAVIC_WEEK_NB,
              timeScales, null, prn, toe, orbit,
              aDot, deltaN0, deltaN0Dot, iDot, omegaDot, cuc, cus, crc, crs, cic, cis,
              af0, af1, af2, tgd, toc);
    }

    /** Constructor from field instance.
     * @param <T> type of the field elements
     * @param original regular field instance
     */
    public <T extends CalculusFieldElement<T>> NavICAlmanac(final FieldNavICAlmanac<T> original) {
        super(original);
    }

    /** {@inheritDoc} */
    @Override
    public <T extends CalculusFieldElement<T>>
        FieldNavICAlmanac<T> toField(final FieldKeplerianOrbit<T> orbit,
                                     final T[] nonKeplerian,
                                     final DoubleFunction<T> converter) {
        return new FieldNavICAlmanac<>(getAngularVelocity(), getWeeksInCycle(), getTimeScales(),
                                       getType(), getPrn(),
                                       new FieldGNSSDate<>(orbit.getDate().getField(), getTimeOfEphemeris()),
                                       orbit,  nonKeplerian,
                                       converter.apply(getTgd()),
                                       new FieldGNSSDate<>(orbit.getDate().getField(), getTimeOfClock()));
    }

    /** {@inheritDoc} */
    @Override
    public NavICAlmanacFactory baseFactory(final Frame inertial, final Frame bodyFixed) {
        return new NavICAlmanacFactory(getTimeScales(), getTimeOfEphemeris().getSystem(), inertial, bodyFixed);
    }

}