agi.foundation.propagators

(agi.foundation.navigation-2024r2.jar)

Interface IGpsElements

All Known Implementing Classes:

RinexNavigationEphemeris, SemAlmanacRecord, YumaAlmanacRecord

public interface IGpsElements

An interface to a GPS element set that contains data items needed for GPS ephemeris propagation. This interface provides data for one GPS satellite.

Definitions from IS-GPS-200D pages 94, 96, and 107.

Method Summary

Modifier and Type	Method and Description
double	getArgumentOfPerigee() Gets the inclination angle.
double	getCosineCorrectionToArgumentOfLatitude() Gets the amplitude of the cosine harmonic correction term to the Argument of Latitude.
double	getCosineCorrectionToInclination() Gets the amplitude of the cosine harmonic correction term to the angle of inclination.
double	getCosineCorrectionToOrbitRadius() Gets the amplitude of the sine harmonic correction term to the orbit radius.
double	getEccentricity() Gets eccentricity.
GlobalPositioningSystemDate	getEpoch() Gets the epoch at which these elements are specified.
double	getInclinationAngle() Gets the inclination angle.
double	getIssueOfData() Gets the issue of data ephemeris (IODE).
double	getLongitudeOfAscendingNode() Gets the longitude of ascending node of orbit plane at weekly epoch.
double	getMeanAnomaly() Gets the mean anomaly.
double	getMeanMotionDifference() Gets the mean motion difference from computed value.
double	getRateOfInclinationAngle() Gets the rate of inclination angle (IDOT).
double	getRateOfRightAscension() Gets the rate of right ascension.
double	getSineCorrectionToArgumentOfLatitude() Gets the amplitude of the sine harmonic correction term to the Argument of Latitude.
double	getSineCorrectionToInclination() Gets the amplitude of the sine harmonic correction term to the angle of inclination.
double	getSineCorrectionToOrbitRadius() Gets the amplitude of the sine harmonic correction term to the orbit radius.
double	getSquareRootOfSemimajorAxis() Gets the square root of the semi-major axis (sqrt(meters)).

Method Detail

getArgumentOfPerigee

double getArgumentOfPerigee()

Gets the inclination angle. Units: rad

getCosineCorrectionToArgumentOfLatitude

double getCosineCorrectionToArgumentOfLatitude()

Gets the amplitude of the cosine harmonic correction term to the Argument of Latitude. Units: rad

getCosineCorrectionToInclination

double getCosineCorrectionToInclination()

Gets the amplitude of the cosine harmonic correction term to the angle of inclination. Units: rad

getCosineCorrectionToOrbitRadius

double getCosineCorrectionToOrbitRadius()

Gets the amplitude of the sine harmonic correction term to the orbit radius. Units: m

getEccentricity

double getEccentricity()

Gets eccentricity. Units: unitless

getEpoch

@Nonnull
GlobalPositioningSystemDate getEpoch()

Gets the epoch at which these elements are specified.

getInclinationAngle

double getInclinationAngle()

Gets the inclination angle. Units: rad

getIssueOfData

double getIssueOfData()

Gets the issue of data ephemeris (IODE).

getLongitudeOfAscendingNode

double getLongitudeOfAscendingNode()

Gets the longitude of ascending node of orbit plane at weekly epoch. Units: rad

getMeanAnomaly

double getMeanAnomaly()

Gets the mean anomaly. Units: rad

getMeanMotionDifference

double getMeanMotionDifference()

Gets the mean motion difference from computed value. Units: rad / s

getRateOfInclinationAngle

double getRateOfInclinationAngle()

Gets the rate of inclination angle (IDOT). Units: rad / s

getRateOfRightAscension

double getRateOfRightAscension()

Gets the rate of right ascension. Units: rad / s

getSineCorrectionToArgumentOfLatitude

double getSineCorrectionToArgumentOfLatitude()

Gets the amplitude of the sine harmonic correction term to the Argument of Latitude. Units: rad

getSineCorrectionToInclination

double getSineCorrectionToInclination()

Gets the amplitude of the sine harmonic correction term to the angle of inclination. Units: rad

getSineCorrectionToOrbitRadius

double getSineCorrectionToOrbitRadius()

Gets the amplitude of the sine harmonic correction term to the orbit radius. Units: m

getSquareRootOfSemimajorAxis

double getSquareRootOfSemimajorAxis()

Gets the square root of the semi-major axis (sqrt(meters)). Units: sqrt(m)