org.orekit.propagation.analytical.gnss.data

Interface SBASOrbitalElements

All Superinterfaces:

TimeStamped

All Known Implementing Classes:

SBASNavigationMessage

public interface SBASOrbitalElements
extends TimeStamped

This interface provides the minimal set of orbital elements needed by the SBASPropagator.

Since:

10.1

Author:

Bryan Cazabonne

Method Summary

Modifier and Type	Method and Description
default double	getAGf0() Gets the Zeroth Order Clock Correction.
default double	getAGf1() Gets the First Order Clock Correction.
default int	getIODN() Gets the Issue Of Data Navigation (IODN).
int	getPRN() Gets the PRN number of the SBAS satellite.
double	getTime() Gets the Reference Time of the SBAS orbit in GPS seconds of the week.
default double	getToc() Gets the clock correction reference time toc.
int	getWeek() Gets the Reference Week of the SBAS orbit.
double	getX() Get the ECEF-X component of satellite coordinates.
double	getXDot() Get the ECEF-X component of satellite velocity vector.
double	getXDotDot() Get the ECEF-X component of satellite acceleration vector.
double	getY() Get the ECEF-Y component of satellite coordinates.
double	getYDot() Get the ECEF-Y component of satellite velocity vector.
double	getYDotDot() Get the ECEF-Y component of satellite acceleration vector.
double	getZ() Get the ECEF-Z component of satellite coordinates.
double	getZDot() Get the ECEF-Z component of satellite velocity vector.
double	getZDotDot() Get the ECEF-Z component of satellite acceleration vector.

Methods inherited from interface org.orekit.time.TimeStamped

getDate

Method Detail

getPRN

int getPRN()

Gets the PRN number of the SBAS satellite.

Returns:

the PRN number of the SBAS satellite

getWeek

int getWeek()

Gets the Reference Week of the SBAS orbit.

Returns:

the Reference Week of the SBAS orbit

getTime

double getTime()

Gets the Reference Time of the SBAS orbit in GPS seconds of the week.

Returns:

the Reference Time of the SBAS orbit (s)

getX

double getX()

Get the ECEF-X component of satellite coordinates.

Returns:

the ECEF-X component of satellite coordinates (m)

getXDot

double getXDot()

Get the ECEF-X component of satellite velocity vector.

Returns:

the the ECEF-X component of satellite velocity vector (m/s)

getXDotDot

double getXDotDot()

Get the ECEF-X component of satellite acceleration vector.

Returns:

the GLONASS ECEF-X component of satellite acceleration vector (m/s²)

getY

double getY()

Get the ECEF-Y component of satellite coordinates.

Returns:

the ECEF-Y component of satellite coordinates (m)

getYDot

double getYDot()

Get the ECEF-Y component of satellite velocity vector.

Returns:

the ECEF-Y component of satellite velocity vector (m/s)

getYDotDot

double getYDotDot()

Get the ECEF-Y component of satellite acceleration vector.

Returns:

the ECEF-Y component of satellite acceleration vector (m/s²)

getZ

double getZ()

Get the ECEF-Z component of satellite coordinates.

Returns:

the ECEF-Z component of satellite coordinates (m)

getZDot

double getZDot()

Get the ECEF-Z component of satellite velocity vector.

Returns:

the the ECEF-Z component of satellite velocity vector (m/s)

getZDotDot

double getZDotDot()

Get the ECEF-Z component of satellite acceleration vector.

Returns:

the ECEF-Z component of satellite acceleration vector (m/s²)

getIODN

default int getIODN()

Gets the Issue Of Data Navigation (IODN).

Returns:

the IODN

getAGf0

default double getAGf0()

Gets the Zeroth Order Clock Correction.

Returns:

the Zeroth Order Clock Correction (s)

getAGf1

default double getAGf1()

Gets the First Order Clock Correction.

Returns:

the First Order Clock Correction (s/s)

getToc

default double getToc()

Gets the clock correction reference time toc.

Returns:

the clock correction reference time (s)