Interface GNSSOrbitalElements
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- All Superinterfaces:
TimeStamped
- All Known Implementing Classes:
AbstractAlmanac
,AbstractNavigationMessage
,BeidouAlmanac
,BeidouCivilianNavigationMessage
,BeidouLegacyNavigationMessage
,CivilianNavigationMessage
,GalileoAlmanac
,GalileoNavigationMessage
,GPSAlmanac
,GPSCivilianNavigationMessage
,GPSLegacyNavigationMessage
,IRNSSAlmanac
,IRNSSNavigationMessage
,LegacyNavigationMessage
,QZSSAlmanac
,QZSSCivilianNavigationMessage
,QZSSLegacyNavigationMessage
public interface GNSSOrbitalElements extends TimeStamped
This interface provides the minimal set of orbital elements needed by theGNSSPropagator
.- Author:
- Pascal Parraud
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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.-
Methods inherited from interface org.orekit.time.TimeStamped
durationFrom, getDate
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Method Detail
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getPRN
int getPRN()
Gets the PRN number of the GNSS satellite.- Returns:
- the PRN number of the GNSS satellite
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getWeek
int getWeek()
Gets the Reference Week of the GNSS orbit.- Returns:
- the Reference Week of the GNSS orbit within [0, 1024[
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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)
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getSma
double getSma()
Gets the Semi-Major Axis.- Returns:
- the Semi-Major Axis (m)
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getMeanMotion
double getMeanMotion()
Gets the Mean Motion.- Returns:
- the Mean Motion (rad/s)
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getE
double getE()
Gets the Eccentricity.- Returns:
- the Eccentricity
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getI0
double getI0()
Gets the Inclination Angle at Reference Time.- Returns:
- the Inclination Angle at Reference Time (rad)
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getIDot
double getIDot()
Gets the Rate of Inclination Angle.- Returns:
- the Rate of Inclination Angle (rad/s)
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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)
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getOmegaDot
double getOmegaDot()
Gets the Rate of Right Ascension.- Returns:
- the Rate of Right Ascension (rad/s)
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getPa
double getPa()
Gets the Argument of Perigee.- Returns:
- the Argument of Perigee (rad)
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getM0
double getM0()
Gets the Mean Anomaly at Reference Time.- Returns:
- the Mean Anomaly at Reference Time (rad)
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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)
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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)
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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)
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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)
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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)
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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)
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getMu
double getMu()
Gets the Earth's universal gravitational parameter.- Returns:
- the Earth's universal gravitational parameter
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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
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getCycleDuration
double getCycleDuration()
Gets the duration of the GNSS cycle in seconds.- Returns:
- the duration of the GNSS cycle in seconds
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getPropagator
@DefaultDataContext default GNSSPropagator getPropagator()
Get the propagator corresponding to the navigation message.The attitude provider is set by default to be aligned with the EME2000 frame.
The mass is set by default to theDEFAULT_MASS
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The ECI frame is set by default to theEME2000 frame
in the default data context.
The ECEF frame is set by default to theCIO/2010-based ITRF simple EOP
in the default data context.This constructor uses the
default data context
- Returns:
- the propagator corresponding to the navigation message
- Since:
- 12.0
- See Also:
getPropagator(Frames)
,getPropagator(Frames, AttitudeProvider, Frame, Frame, double)
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getPropagator
default GNSSPropagator getPropagator(Frames frames)
Get the propagator corresponding to the navigation message.The attitude provider is set by default to be aligned with the EME2000 frame.
The mass is set by default to theDEFAULT_MASS
.
The ECI frame is set by default to theEME2000 frame
in the default data context.
The ECEF frame is set by default to theCIO/2010-based ITRF simple EOP
in the default data context.- Parameters:
frames
- set of frames to use- Returns:
- the propagator corresponding to the navigation message
- Since:
- 12.0
- See Also:
getPropagator()
,getPropagator(Frames, AttitudeProvider, Frame, Frame, double)
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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 useprovider
- attitude providerinertial
- inertial frame, use to provide the propagated orbitbodyFixed
- body fixed frame, corresponding to the navigation messagemass
- spacecraft mass in kg- Returns:
- the propagator corresponding to the navigation message
- Since:
- 12.0
- See Also:
getPropagator()
,getPropagator(Frames)
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