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

Class SBASNavigationMessage

java.lang.Object
org.orekit.propagation.analytical.gnss.data.AbstractEphemerisMessage
org.orekit.propagation.analytical.gnss.data.SBASNavigationMessage
All Implemented Interfaces:
NavigationMessage, SBASOrbitalElements, TimeStamped
public class SBASNavigationMessage extends AbstractEphemerisMessage implements SBASOrbitalElements
Container for data contained in a SBAS navigation message.
Since:
11.0
Author:
Bryan Cazabonne

  • Field Details

  • Constructor Details

    • SBASNavigationMessage

      public SBASNavigationMessage()
      Constructor.

  • Method Details

    • getNavigationMessageType

      public String getNavigationMessageType()
      Get navigation message type.
      Specified by:
      getNavigationMessageType in interface NavigationMessage
      Returns:
      the navigation message type

    • getNavigationMessageSubType

      public String getNavigationMessageSubType()
      Get navigation message subtype.
      Specified by:
      getNavigationMessageSubType in interface NavigationMessage
      Returns:
      the navigation message type

    • getPropagator

      @DefaultDataContext public SBASPropagator getPropagator()
      Get the propagator corresponding to the navigation message.

      The attitude provider is set by default be aligned with the EME2000 frame.
      The Earth gravity coefficient is set by default to the SBAS_MU.
      The mass is set by default to the DEFAULT_MASS.
      The ECI frame is set by default to the EME2000 frame.
      The ECEF frame is set by default to the CIO/2010-based ITRF simple EOP.

      This constructor uses the default data context

      Returns:
      the propagator corresponding to the navigation message
      Since:
      12.0
      See Also:

    • getPropagator

      public SBASPropagator getPropagator(Frames frames)
      Get the propagator corresponding to the navigation message.

      The attitude provider is set by default be aligned with the EME2000 frame.
      The Earth gravity coefficient is set by default to the SBAS_MU.
      The mass is set by default to the DEFAULT_MASS.
      The ECI frame is set by default to the EME2000 frame.
      The ECEF frame is set by default to the CIO/2010-based ITRF simple EOP.

      Parameters:
      frames - set of frames to use
      Returns:
      the propagator corresponding to the navigation message
      Since:
      12.0
      See Also:

    • getPropagator

      public SBASPropagator getPropagator(Frames frames, AttitudeProvider provider, Frame inertial, Frame bodyFixed, double mass, double mu)
      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
      mu - central attraction coefficient
      Returns:
      the propagator corresponding to the navigation message
      Since:
      12.0
      See Also:

    • getWeek

      public int getWeek()
      Gets the Reference Week of the SBAS orbit.
      Specified by:
      getWeek in interface SBASOrbitalElements
      Returns:
      the Reference Week of the SBAS orbit

    • getTime

      public double getTime()
      Gets the Reference Time of the SBAS orbit in GPS seconds of the week.
      Specified by:
      getTime in interface SBASOrbitalElements
      Returns:
      the Reference Time of the SBAS orbit (s)

    • setTime

      public void setTime(double time)
      Setter for the reference time of the SBAS orbit in GPS seconds of the week.
      Parameters:
      time - the time to set

    • getIODN

      public int getIODN()
      Gets the Issue Of Data Navigation (IODN).
      Specified by:
      getIODN in interface SBASOrbitalElements
      Returns:
      the IODN

    • setIODN

      public void setIODN(double iod)
      Setter for the issue of data navigation.
      Parameters:
      iod - the issue of data to set

    • getAGf0

      public double getAGf0()
      Gets the Zeroth Order Clock Correction.
      Specified by:
      getAGf0 in interface SBASOrbitalElements
      Returns:
      the Zeroth Order Clock Correction (s)

    • setAGf0

      public void setAGf0(double a0)
      Setter for the SV clock bias.
      Parameters:
      a0 - the SV clock bias to set in seconds

    • getAGf1

      public double getAGf1()
      Gets the First Order Clock Correction.
      Specified by:
      getAGf1 in interface SBASOrbitalElements
      Returns:
      the First Order Clock Correction (s/s)

    • setAGf1

      public void setAGf1(double a1)
      Setter for the SV relative frequency.
      Parameters:
      a1 - the SV relative frequency to set

    • getURA

      public double getURA()
      Getter for the user range accuray (meters).
      Returns:
      the user range accuracy

    • setURA

      public void setURA(double accuracy)
      Setter for the user range accuracy.
      Parameters:
      accuracy - the value to set