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

Class GPSLegacyNavigationMessage

java.lang.Object

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

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

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

org.orekit.propagation.analytical.gnss.data.GPSLegacyNavigationMessage

All Implemented Interfaces:

OrbitalParameters, GNSSClockElements, NavigationMessage, TimeStamped

public class GPSLegacyNavigationMessage
extends LegacyNavigationMessage<GPSLegacyNavigationMessage>

Container for data contained in a GPS navigation message.

Since:

11.0

Author:

Bryan Cazabonne

Field Summary

Fields

Modifier and Type	Field	Description
static final String	LNAV	Message type.

Constructor Summary

Constructors

Constructor	Description
GPSLegacyNavigationMessage(FieldGPSLegacyNavigationMessage<T> original)	Constructor from field instance.
GPSLegacyNavigationMessage(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.

Method Summary

Modifier and Type	Method	Description
GPSLegacyNavigationMessageFactory	baseFactory(Frame inertial, Frame bodyFixed)	Factory for the orbital elements.
<T extends CalculusFieldElement<T>> FieldGPSLegacyNavigationMessage<T>	toField(FieldKeplerianOrbit<T> orbit, T[] nonKeplerian, DoubleFunction<T> converter)	Create another field version of the instance.

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

getFitInterval, getIODC, getIODE, getL2Codes, getL2PFlags, getSvAccuracy, getSvHealth

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

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

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

Field Details

LNAV

public static final String LNAV

Message type.

Since:

14.0

See Also:

• Constant Field Values

Constructor Details

GPSLegacyNavigationMessage

public GPSLegacyNavigationMessage(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:

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.

GPSLegacyNavigationMessage

public GPSLegacyNavigationMessage(FieldGPSLegacyNavigationMessage<T> original)

Constructor from field instance.

Type Parameters:

T - type of the field elements

Parameters:

original - regular field instance

Method Details

toField

public <T extends CalculusFieldElement<T>>
FieldGPSLegacyNavigationMessage<T> toField(FieldKeplerianOrbit<T> orbit,
 T[] nonKeplerian,
 DoubleFunction<T> converter)

Create another field version of the instance.

Specified by:

toField in class GNSSOrbitalElements<GPSLegacyNavigationMessage>

Type Parameters:

T - type of the field elements

Parameters:

orbit - orbit in the correct gradient field

nonKeplerian - non-Keplerian parameters

converter - converter for remaining elements

Returns:

gradient version of the instance

baseFactory

public GPSLegacyNavigationMessageFactory baseFactory(Frame inertial,
 Frame bodyFixed)

Factory for the orbital elements.

Specified by:

baseFactory in class GNSSOrbitalElements<GPSLegacyNavigationMessage>

Parameters:

inertial - reference inertial frame

bodyFixed - body fixed frame (will be frozen at date to build the orbital elements

Returns:

factory for the orbital elements