Interface GNSSOrbitalElements

    • Method Summary

      All Methods Instance Methods Abstract Methods Default Methods 
      Modifier and Type Method Description
      double getAngularVelocity()
      Gets the mean angular velocity of the Earth of the GNSS model.
      double getCic()
      Gets the Amplitude of the Cosine Harmonic Correction Term to the Angle of Inclination.
      double getCis()
      Gets the Amplitude of the Sine Harmonic Correction Term to the Angle of Inclination.
      double getCrc()
      Gets the Amplitude of the Cosine Harmonic Correction Term to the Orbit Radius.
      double getCrs()
      Gets the Amplitude of the Sine Harmonic Correction Term to the Orbit Radius.
      double getCuc()
      Gets the Amplitude of the Cosine Harmonic Correction Term to the Argument of Latitude.
      double getCus()
      Gets the Amplitude of the Sine Harmonic Correction Term to the Argument of Latitude.
      double getCycleDuration()
      Gets the duration of the GNSS cycle in seconds.
      double getE()
      Gets the Eccentricity.
      double getI0()
      Gets the Inclination Angle at Reference Time.
      double getIDot()
      Gets the Rate of Inclination Angle.
      double getM0()
      Gets the Mean Anomaly at Reference Time.
      double getMeanMotion()
      Gets the Mean Motion.
      double getMu()
      Gets the Earth's universal gravitational parameter.
      double getOmega0()
      Gets the Longitude of Ascending Node of Orbit Plane at Weekly Epoch.
      double getOmegaDot()
      Gets the Rate of Right Ascension.
      double getPa()
      Gets the Argument of Perigee.
      int getPRN()
      Gets the PRN number of the GNSS satellite.
      default GNSSPropagator getPropagator()
      Get the propagator corresponding to the navigation message.
      default GNSSPropagator getPropagator​(Frames frames)
      Get the propagator corresponding to the navigation message.
      default GNSSPropagator getPropagator​(Frames frames, AttitudeProvider provider, Frame inertial, Frame bodyFixed, double mass)
      Get the propagator corresponding to the navigation message.
      double getSma()
      Gets the Semi-Major Axis.
      double getTime()
      Gets the Reference Time of the GNSS orbit as a duration from week start.
      int getWeek()
      Gets the Reference Week of the GNSS orbit.
    • Method Detail

      • getPRN

        int getPRN()
        Gets the PRN number of the GNSS satellite.
        Returns:
        the PRN number of the GNSS satellite
      • getWeek

        int getWeek()
        Gets the Reference Week of the GNSS orbit.
        Returns:
        the Reference Week of the GNSS orbit within [0, 1024[
      • getTime

        double getTime()
        Gets the Reference Time of the GNSS orbit as a duration from week start.
        Returns:
        the Reference Time of the GNSS orbit (s)
      • getSma

        double getSma()
        Gets the Semi-Major Axis.
        Returns:
        the Semi-Major Axis (m)
      • getMeanMotion

        double getMeanMotion()
        Gets the Mean Motion.
        Returns:
        the Mean Motion (rad/s)
      • getE

        double getE()
        Gets the Eccentricity.
        Returns:
        the Eccentricity
      • getI0

        double getI0()
        Gets the Inclination Angle at Reference Time.
        Returns:
        the Inclination Angle at Reference Time (rad)
      • getIDot

        double getIDot()
        Gets the Rate of Inclination Angle.
        Returns:
        the Rate of Inclination Angle (rad/s)
      • getOmega0

        double getOmega0()
        Gets the Longitude of Ascending Node of Orbit Plane at Weekly Epoch.
        Returns:
        the Longitude of Ascending Node of Orbit Plane at Weekly Epoch (rad)
      • getOmegaDot

        double getOmegaDot()
        Gets the Rate of Right Ascension.
        Returns:
        the Rate of Right Ascension (rad/s)
      • getPa

        double getPa()
        Gets the Argument of Perigee.
        Returns:
        the Argument of Perigee (rad)
      • getM0

        double getM0()
        Gets the Mean Anomaly at Reference Time.
        Returns:
        the Mean Anomaly at Reference Time (rad)
      • getCuc

        double getCuc()
        Gets the Amplitude of the Cosine Harmonic Correction Term to the Argument of Latitude.
        Returns:
        the Amplitude of the Cosine Harmonic Correction Term to the Argument of Latitude (rad)
      • getCus

        double getCus()
        Gets the Amplitude of the Sine Harmonic Correction Term to the Argument of Latitude.
        Returns:
        the Amplitude of the Sine Harmonic Correction Term to the Argument of Latitude (rad)
      • getCrc

        double getCrc()
        Gets the Amplitude of the Cosine Harmonic Correction Term to the Orbit Radius.
        Returns:
        the Amplitude of the Cosine Harmonic Correction Term to the Orbit Radius (m)
      • getCrs

        double getCrs()
        Gets the Amplitude of the Sine Harmonic Correction Term to the Orbit Radius.
        Returns:
        the Amplitude of the Sine Harmonic Correction Term to the Orbit Radius (m)
      • getCic

        double getCic()
        Gets the Amplitude of the Cosine Harmonic Correction Term to the Angle of Inclination.
        Returns:
        the Amplitude of the Cosine Harmonic Correction Term to the Angle of Inclination (rad)
      • getCis

        double getCis()
        Gets the Amplitude of the Sine Harmonic Correction Term to the Angle of Inclination.
        Returns:
        the Amplitude of the Sine Harmonic Correction Term to the Angle of Inclination (rad)
      • getMu

        double getMu()
        Gets the Earth's universal gravitational parameter.
        Returns:
        the Earth's universal gravitational parameter
      • getAngularVelocity

        double getAngularVelocity()
        Gets the mean angular velocity of the Earth of the GNSS model.
        Returns:
        the mean angular velocity of the Earth of the GNSS model
      • getCycleDuration

        double getCycleDuration()
        Gets the duration of the GNSS cycle in seconds.
        Returns:
        the duration of the GNSS cycle in seconds
      • getPropagator

        default GNSSPropagator getPropagator​(Frames frames,
                                             AttitudeProvider provider,
                                             Frame inertial,
                                             Frame bodyFixed,
                                             double mass)
        Get the propagator corresponding to the navigation message.
        Parameters:
        frames - set of frames to use
        provider - attitude provider
        inertial - inertial frame, use to provide the propagated orbit
        bodyFixed - body fixed frame, corresponding to the navigation message
        mass - spacecraft mass in kg
        Returns:
        the propagator corresponding to the navigation message
        Since:
        12.0
        See Also:
        getPropagator(), getPropagator(Frames)