Package org.orekit.propagation.analytical.gnss.data

Class LegacyNavigationMessage<O extends LegacyNavigationMessage<O>>

java.lang.Object

org.orekit.propagation.analytical.gnss.data.GNSSOrbitalElements<O>

org.orekit.propagation.analytical.gnss.data.AbstractNavigationMessage<O>

org.orekit.propagation.analytical.gnss.data.LegacyNavigationMessage<O>

Type Parameters:

O - type of the orbital elements

All Implemented Interfaces:

OrbitalParameters, GNSSClockElements, NavigationMessage, TimeStamped

Direct Known Subclasses:

GPSLegacyNavigationMessage, NavICLegacyNavigationMessage, QZSSLegacyNavigationMessage

public abstract class LegacyNavigationMessage<O extends LegacyNavigationMessage<O>>
extends AbstractNavigationMessage<O>

Container for data contained in a GPS/QZNSS legacy navigation message.

Since:

11.0

Author:

Bryan Cazabonne

Constructor Summary

Constructors

Modifier	Constructor	Description
protected	LegacyNavigationMessage(double angularVelocity, int weeksInCycle, TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, int iode, int iodc, double svAccuracy, int svHealth, int fitInterval, int l2Codes, int l2PFlags)	Constructor.
protected	LegacyNavigationMessage(FieldLegacyNavigationMessage<T,A> original)	Constructor from field instance.

Method Summary

Modifier and Type	Method	Description
int	getFitInterval()	Get the fit interval.
int	getIODC()	Get the Issue Of Data Clock (IODC).
int	getIODE()	Get the Issue Of Data Ephemeris (IODE).
int	getL2Codes()	Get the codes on L2 channel.
int	getL2PFlags()	Get the L2 P data flags.
double	getSvAccuracy()	Get the user SV accuray (meters).
int	getSvHealth()	Get the satellite health status.

Methods inherited from class org.orekit.propagation.analytical.gnss.data.AbstractNavigationMessage

getNavigationMessageSubType, getNavigationMessageType, getTransmissionTime

Methods inherited from class org.orekit.propagation.analytical.gnss.data.GNSSOrbitalElements

baseFactory, factory, getADot, getAf0, getAf1, getAf2, getAngularVelocity, getCic, getCis, getCrc, getCrs, getCuc, getCus, getCycleDuration, getDate, getDeltaN0, getDeltaN0Dot, getIDot, getOmegaDot, getOrbit, getPrn, getTgd, getTimeOfClock, getTimeOfEphemeris, getTimeScales, getType, getWeeksInCycle, isCivilianMessage, toField, toField

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from interface org.orekit.time.TimeStamped

durationFrom, getDate

Constructor Details

LegacyNavigationMessage

protected LegacyNavigationMessage(double angularVelocity,
 int weeksInCycle,
 TimeScales timeScales,
 String type,
 int prn,
 GNSSDate toe,
 KeplerianOrbit orbit,
 double aDot,
 double deltaN0,
 double deltaN0Dot,
 double iDot,
 double omegaDot,
 double cuc,
 double cus,
 double crc,
 double crs,
 double cic,
 double cis,
 double af0,
 double af1,
 double af2,
 double tgd,
 GNSSDate toc,
 GNSSDate transmissionTime,
 int iode,
 int iodc,
 double svAccuracy,
 int svHealth,
 int fitInterval,
 int l2Codes,
 int l2PFlags)

Constructor.

Parameters:

angularVelocity - mean angular velocity of the Earth for the GNSS model

weeksInCycle - number of weeks in the GNSS cycle

timeScales - known time scales

type - message type

prn - PRN number of the satellite

toe - time of ephemeris (must be consistent with orbit)

orbit - Keplerian orbit in Earth-frozen frame

aDot - change rate in semi-major axis (m/s)

deltaN0 - delta of satellite mean motion

deltaN0Dot - change rate in Δn₀

iDot - inclination rate (rad/s)

omegaDot - rate of right ascension (rad/s)

cuc - amplitude of the cosine harmonic correction term to the argument of latitude

cus - amplitude of the sine harmonic correction term to the argument of latitude

crc - amplitude of the cosine harmonic correction term to the orbit radius

crs - amplitude of the sine harmonic correction term to the orbit radius

cic - amplitude of the cosine harmonic correction term to the inclination

cis - amplitude of the sine harmonic correction term to the inclination

af0 - zero-th order clock correction (s)

af1 - first order clock correction (s/s)

af2 - second order clock correction (s/s²)

tgd - group delay differential TGD for L1-L2 correction

toc - time of clock

transmissionTime - transmission time

iode - issue of data, ephemeris

iodc - issue of data, clock

svAccuracy - user SV accuracy (m)

svHealth - satellite health status

fitInterval - fit interval

l2Codes - codes on L2 channel

l2PFlags - L2 P data flags.

LegacyNavigationMessage

protected LegacyNavigationMessage(FieldLegacyNavigationMessage<T,A> original)

Constructor from field instance.

Type Parameters:

T - type of the field elements

A - type of the orbital elements (non-field version)

Parameters:

original - regular field instance

Method Details

getIODE

public int getIODE()

Get the Issue Of Data Ephemeris (IODE).

Returns:

the Issue Of Data Ephemeris (IODE)

getIODC

public int getIODC()

Get the Issue Of Data Clock (IODC).

Returns:

the Issue Of Data Clock (IODC)

getSvAccuracy

public double getSvAccuracy()

Get the user SV accuray (meters).

Returns:

the user SV accuracy

getSvHealth

public int getSvHealth()

Get the satellite health status.

Returns:

the satellite health status

getFitInterval

public int getFitInterval()

Get the fit interval.

Returns:

the fit interval

Since:

12.0

getL2Codes

public int getL2Codes()

Get the codes on L2 channel.

Returns:

codes on L2 channel

Since:

14.0

getL2PFlags

public int getL2PFlags()

Get the L2 P data flags.

Returns:

L2 P data flags

Since:

14.0