org.orekit.propagation.analytical.gnss.data

Interface GLONASSOrbitalElements

All Superinterfaces:

TimeStamped

All Known Implementing Classes:

GLONASSAlmanac, GLONASSEphemeris, GLONASSNavigationMessage

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:

GLONASS Interface Control Document

Method Summary

Modifier and Type	Method and 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

getDate

Method Detail

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