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

Class AbstractAlmanac<O extends AbstractAlmanac<O>>

java.lang.Object

org.orekit.propagation.analytical.gnss.data.GNSSOrbitalElementsDriversProvider

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

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

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

Type Parameters:

O - type of the orbital elements

All Implemented Interfaces:

GNSSClockElements, TimeStamped, ParameterDriversProvider

Direct Known Subclasses:

AbstractNavigationMessage, BeidouAlmanac, GalileoAlmanac, GPSAlmanac, NavICAlmanac, QZSSAlmanac

public abstract class AbstractAlmanac<O extends AbstractAlmanac<O>>
extends CommonGnssData<O>

Base class for GNSS almanacs.

Since:

11.0

Author:

Pascal Parraud

Field Summary

Fields inherited from class org.orekit.propagation.analytical.gnss.data.CommonGnssData

AF0, AF1, AF2

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

ARGUMENT_OF_PERIGEE, ECCENTRICITY, INCLINATION, MEAN_ANOMALY, NODE_LONGITUDE, SEMI_MAJOR_AXIS

Fields inherited from class org.orekit.propagation.analytical.gnss.data.GNSSOrbitalElementsDriversProvider

CIC_INDEX, CIS_INDEX, CRC_INDEX, CRS_INDEX, CUC_INDEX, CUS_INDEX, I_DOT_INDEX, INCLINATION_COSINE, INCLINATION_RATE, INCLINATION_SINE, LATITUDE_COSINE, LATITUDE_SINE, LONGITUDE_RATE, OMEGA_DOT_INDEX, RADIUS_COSINE, RADIUS_SINE, SIZE, TIME, TIME_INDEX

Constructor Summary

Constructors

Modifier	Constructor	Description
	AbstractAlmanac(double mu, double angularVelocity, int weeksInCycle, TimeScales timeScales, SatelliteSystem system)	Constructor.
protected	AbstractAlmanac(FieldAbstractAlmanac<T,A> original)	Constructor from field instance.

Method Summary

Modifier and Type	Method	Description
GNSSPropagator	getPropagator()	Get the propagator corresponding to the navigation message.
GNSSPropagator	getPropagator(Frames frames)	Get the propagator corresponding to the navigation message.
GNSSPropagator	getPropagator(Frames frames, AttitudeProvider provider, Frame inertial, Frame bodyFixed, double mass)	Get the propagator corresponding to the navigation message.

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

getAf0, getAf1, getAf2, getTGD, getToc, setAf0, setAf1, setAf2, setTGD, setToc

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

getADot, getDate, getDeltaN0, getDeltaN0Dot, getE, getEDriver, getI0, getI0Driver, getM0, getM0Driver, getMeanMotion0, getMu, getOmega0, getOmega0Driver, getPa, getPaDriver, getSma, getSmaDriver, setE, setGnssDate, setI0, setM0, setOmega0, setPa, setSma, toField

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

copySelectionSettings, createDriver, getAngularVelocity, getCic, getCicDriver, getCis, getCisDriver, getCrc, getCrcDriver, getCrs, getCrsDriver, getCuc, getCucDriver, getCus, getCusDriver, getCycleDuration, getIDot, getIDotDriver, getOmegaDot, getOmegaDotDriver, getParametersDrivers, getPRN, getSystem, getTime, getTimeDriver, getTimeScales, getWeek, getWeeksInCycle, setCic, setCis, setCrc, setCrs, setCuc, setCus, setIDot, setOmegaDot, setPRN, setTime, setWeek

Methods inherited from class java.lang.Object

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

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported

Methods inherited from interface org.orekit.time.TimeStamped

durationFrom, getDate

Constructor Detail

AbstractAlmanac

public AbstractAlmanac(double mu,
                       double angularVelocity,
                       int weeksInCycle,
                       TimeScales timeScales,
                       SatelliteSystem system)

Constructor.

Parameters:

mu - Earth's universal gravitational parameter

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

weeksInCycle - number of weeks in the GNSS cycle

timeScales - known time scales

system - satellite system to consider for interpreting week number (may be different from real system, for example in Rinex nav, weeks are always according to GPS)

AbstractAlmanac

protected AbstractAlmanac(FieldAbstractAlmanac<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 Detail

getPropagator

@DefaultDataContext
public 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

public 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:

13.0

See Also:

getPropagator(), getPropagator(Frames, AttitudeProvider, Frame, Frame, double)

getPropagator

public 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:

13.0

See Also:

getPropagator(), getPropagator(Frames)