Package org.orekit.propagation.analytical.gnss.data

Interface GLONASSOrbitalElements

All Superinterfaces:
TimeStamped
All Known Implementing Classes:
GLONASSAlmanac, GLONASSEphemeris, GLONASSFdmaNavigationMessage
public interface GLONASSOrbitalElements extends TimeStamped
This interface provides the minimal set of orbital elements needed by the GLONASSAnalyticalPropagator and the GLONASSNumericalPropagator.

Because input data are different between numerical and analytical GLONASS propagators the methods present in this interface are implemented by default. Depending if the user wants to use a GLONASSNumericalPropagator or a GLONASSAnalyticalPropagator he can create an instance of a GLONASSEphemeris or GLONASSAlmanac.

Since:
10.0
Author:
Bryan Cazabonne
See Also:

  • Method Summary

    Modifier and Type
    Method
    Description
    default double
    getDeltaI()
    Get the correction to the mean value of inclination.
    default double
    getDeltaT()
    Get the correction to the mean value of Draconian period.
    default double
    getDeltaTDot()
    Get the rate of change of Draconian period.
    default double
    getE()
    Get the Eccentricity.
    default double
    getGammaN()
    Get the relative deviation of predicted satellite carrier frequency from nominal value.
    default int
    getIOD()
    Gets the GLONASS Issue Of Data (IOD).
    default double
    getLambda()
    Get the longitude of ascending node of orbit.
    default int
    getN4()
    Get the number of the current four year interval.
    default int
    getNa()
    Get the number of the current day in a four year interval.
    default double
    getPa()
    Get the Argument of Perigee.
    default double
    getTime()
    Get the Reference Time.
    default double
    getTN()
    Get the correction to the satellite time relative to GLONASS system time.
    default double
    getX()
    Get the ECEF-X component of satellite coordinates in PZ-90 datum.
    default double
    getXDot()
    Get the ECEF-X component of satellite velocity vector in PZ-90 datum.
    default double
    getXDotDot()
    Get the GLONASS ECEF-X component of satellite acceleration vector in PZ-90 datum.
    default double
    getY()
    Get the ECEF-Y component of satellite coordinates in PZ-90 datum.
    default double
    getYDot()
    Get the ECEF-Y component of satellite velocity vector in PZ-90 datum.
    default double
    getYDotDot()
    Get the GLONASS ECEF-Y component of satellite acceleration vector in PZ-90 datum.
    default double
    getZ()
    Get the ECEF-Z component of satellite coordinates in PZ-90 datum.
    default double
    getZDot()
    Get the ECEF-Z component of satellite velocity vector in PZ-90 datum.
    default double
    getZDotDot()
    Get the GLONASS ECEF-Z component of satellite acceleration vector in PZ-90 datum.

    Methods inherited from interface org.orekit.time.TimeStamped

    durationFrom, getDate

  • Method Details

    • getNa

      default int getNa()
      Get the number of the current day in a four year interval.
      Returns:
      the number of the current day in a four year interval

    • getN4

      default int getN4()
      Get the number of the current four year interval.
      Returns:
      the number of the current four year interval

    • getTime

      default double getTime()
      Get the Reference Time.
      Returns:
      the Reference Time (s)

    • getLambda

      default double getLambda()
      Get the longitude of ascending node of orbit.
      Returns:
      the longitude of ascending node of orbit (rad)

    • getE

      default double getE()
      Get the Eccentricity.
      Returns:
      the Eccentricity

    • getPa

      default double getPa()
      Get the Argument of Perigee.
      Returns:
      the Argument of Perigee (rad)

    • getDeltaI

      default double getDeltaI()
      Get the correction to the mean value of inclination.
      Returns:
      the correction to the mean value of inclination (rad)

    • getDeltaT

      default double getDeltaT()
      Get the correction to the mean value of Draconian period.
      Returns:
      the correction to the mean value of Draconian period (s)

    • getDeltaTDot

      default double getDeltaTDot()
      Get the rate of change of Draconian period.
      Returns:
      the rate of change of Draconian period

    • getGammaN

      default double getGammaN()
      Get the relative deviation of predicted satellite carrier frequency from nominal value.
      Returns:
      the relative deviation of predicted satellite carrier frequency from nominal value

    • getTN

      default double getTN()
      Get the correction to the satellite time relative to GLONASS system time.
      Returns:
      the correction to the satellite time relative to GLONASS system time (s)

    • getXDot

      default double getXDot()
      Get the ECEF-X component of satellite velocity vector in PZ-90 datum.
      Returns:
      the the ECEF-X component of satellite velocity vector in PZ-90 datum (m/s)

    • getX

      default double getX()
      Get the ECEF-X component of satellite coordinates in PZ-90 datum.
      Returns:
      the ECEF-X component of satellite coordinates in PZ-90 datum (m)

    • getXDotDot

      default double getXDotDot()
      Get the GLONASS ECEF-X component of satellite acceleration vector in PZ-90 datum.
      Returns:
      the GLONASS ECEF-X component of satellite acceleration vector in PZ-90 datum (m/s²)

    • getYDot

      default double getYDot()
      Get the ECEF-Y component of satellite velocity vector in PZ-90 datum.
      Returns:
      the ECEF-Y component of satellite velocity vector in PZ-90 datum (m/s)

    • getY

      default double getY()
      Get the ECEF-Y component of satellite coordinates in PZ-90 datum.
      Returns:
      the ECEF-Y component of satellite coordinates in PZ-90 datum (m)

    • getYDotDot

      default double getYDotDot()
      Get the GLONASS ECEF-Y component of satellite acceleration vector in PZ-90 datum.
      Returns:
      the GLONASS ECEF-Y component of satellite acceleration vector in PZ-90 datum (m/s²)

    • getZDot

      default double getZDot()
      Get the ECEF-Z component of satellite velocity vector in PZ-90 datum.
      Returns:
      the the ECEF-Z component of satellite velocity vector in PZ-90 datum (m/s)

    • getZ

      default double getZ()
      Get the ECEF-Z component of satellite coordinates in PZ-90 datum.
      Returns:
      the ECEF-Z component of satellite coordinates in PZ-90 datum (m)

    • getZDotDot

      default double getZDotDot()
      Get the GLONASS ECEF-Z component of satellite acceleration vector in PZ-90 datum.
      Returns:
      the GLONASS ECEF-Z component of satellite acceleration vector in PZ-90 datum (m/s²)

    • getIOD

      default int getIOD()
      Gets the GLONASS Issue Of Data (IOD).
      Returns:
      the IOD