org.orekit.propagation.analytical.gnss.data

Interface GNSSOrbitalElements

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 the GNSSPropagator.

Author:

Pascal Parraud

Method Summary

Modifier and Type	Method and 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

Method Detail

getPRN

int getPRN()

Gets the PRN number of the GNSS satellite.

Returns:

the PRN number of the GNSS satellite

getWeek

int getWeek()

Gets the Reference Week of the GNSS orbit.

Returns:

the Reference Week of the GNSS orbit within [0, 1024[

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)

getSma

double getSma()

Gets the Semi-Major Axis.

Returns:

the Semi-Major Axis (m)

getMeanMotion

double getMeanMotion()

Gets the Mean Motion.

Returns:

the Mean Motion (rad/s)

getE

double getE()

Gets the Eccentricity.

Returns:

the Eccentricity

getI0

double getI0()

Gets the Inclination Angle at Reference Time.

Returns:

the Inclination Angle at Reference Time (rad)

getIDot

double getIDot()

Gets the Rate of Inclination Angle.

Returns:

the Rate of Inclination Angle (rad/s)

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)

getOmegaDot

double getOmegaDot()

Gets the Rate of Right Ascension.

Returns:

the Rate of Right Ascension (rad/s)

getPa

double getPa()

Gets the Argument of Perigee.

Returns:

the Argument of Perigee (rad)

getM0

double getM0()

Gets the Mean Anomaly at Reference Time.

Returns:

the Mean Anomaly at Reference Time (rad)

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)

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)

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)

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)

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)

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)

getMu

double getMu()

Gets the Earth's universal gravitational parameter.

Returns:

the Earth's universal gravitational parameter

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

getCycleDuration

double getCycleDuration()

Gets the duration of the GNSS cycle in seconds.

Returns:

the duration of the GNSS cycle in seconds

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 the DEFAULT_MASS.
The ECI frame is set by default to the EME2000 frame in the default data context.
The ECEF frame is set by default to the CIO/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)

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 the DEFAULT_MASS.
The ECI frame is set by default to the EME2000 frame in the default data context.
The ECEF frame is set by default to the CIO/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)

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 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

Returns:

the propagator corresponding to the navigation message

Since:

12.0

See Also:

getPropagator(), getPropagator(Frames)