Interface GLONASSOrbitalElements
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- 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 theGLONASSAnalyticalPropagator
and theGLONASSNumericalPropagator
.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 aGLONASSAnalyticalPropagator
he can create an instance of aGLONASSEphemeris
orGLONASSAlmanac
.- Since:
- 10.0
- Author:
- Bryan Cazabonne
- See Also:
- GLONASS Interface Control Document
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Method Summary
All Methods Instance Methods Default Methods 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
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Method Detail
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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
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getN4
default int getN4()
Get the number of the current four year interval.- Returns:
- the number of the current four year interval
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getTime
default double getTime()
Get the Reference Time.- Returns:
- the Reference Time (s)
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getLambda
default double getLambda()
Get the longitude of ascending node of orbit.- Returns:
- the longitude of ascending node of orbit (rad)
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getE
default double getE()
Get the Eccentricity.- Returns:
- the Eccentricity
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getPa
default double getPa()
Get the Argument of Perigee.- Returns:
- the Argument of Perigee (rad)
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getDeltaI
default double getDeltaI()
Get the correction to the mean value of inclination.- Returns:
- the correction to the mean value of inclination (rad)
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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)
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getDeltaTDot
default double getDeltaTDot()
Get the rate of change of Draconian period.- Returns:
- the rate of change of Draconian period
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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
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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)
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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)
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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)
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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)
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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)
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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)
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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)
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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)
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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)
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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)
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getIOD
default int getIOD()
Gets the GLONASS Issue Of Data (IOD).- Returns:
- the IOD
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