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

Class FieldAbstractAlmanac<T extends CalculusFieldElement<T>,O extends AbstractAlmanac<O>>

java.lang.Object

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

org.orekit.propagation.analytical.gnss.data.FieldGnssOrbitalElements<T,O>

org.orekit.propagation.analytical.gnss.data.FieldCommonGnssData<T,O>

org.orekit.propagation.analytical.gnss.data.FieldAbstractAlmanac<T,O>

Type Parameters:

T - type of the field elements

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

All Implemented Interfaces:

FieldGNSSClockElements<T>, FieldTimeStamped<T>, ParameterDriversProvider

Direct Known Subclasses:

FieldAbstractNavigationMessage, FieldBeidouAlmanac, FieldGalileoAlmanac, FieldGPSAlmanac, FieldNavICAlmanac, FieldQZSSAlmanac

public abstract class FieldAbstractAlmanac<T extends CalculusFieldElement<T>,O extends AbstractAlmanac<O>>
extends FieldCommonGnssData<T,O>

Base class for GNSS almanacs.

Since:

13.0

Author:

Luc Maisonobe

Field Summary

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
protected	FieldAbstractAlmanac(Function<V,T> converter, FieldAbstractAlmanac<V,O> original)	Constructor from different field instance.
protected	FieldAbstractAlmanac(Field<T> field, O original)	Constructor from non-field instance.

Method Summary

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

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

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

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

changeField, getADot, getDate, getDeltaN0, getDeltaN0Dot, getE, getI0, getM0, getMeanMotion0, getMu, getOmega0, getPa, getSma, setE, setGnssDate, setI0, setM0, setOmega0, setPa, setSma, toNonField

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.time.FieldTimeStamped

durationFrom, getDate

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

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

Constructor Detail

FieldAbstractAlmanac

protected FieldAbstractAlmanac(Field<T> field,
                               O original)

Constructor from non-field instance.

Parameters:

field - field to which elements belong

original - regular non-field instance

FieldAbstractAlmanac

protected FieldAbstractAlmanac(Function<V,T> converter,
                               FieldAbstractAlmanac<V,O> original)

Constructor from different field instance.

Type Parameters:

V - type of the old field elements

Parameters:

original - regular non-field instance

converter - for field elements

Method Detail

getPropagator

@DefaultDataContext
public FieldGnssPropagator<T> 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

See Also:

getPropagator(Frames), getPropagator(Frames, AttitudeProvider, Frame, Frame, CalculusFieldElement)

getPropagator

public FieldGnssPropagator<T> 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

See Also:

getPropagator(), getPropagator(Frames, AttitudeProvider, Frame, Frame, CalculusFieldElement)

getPropagator

public FieldGnssPropagator<T> getPropagator(Frames frames,
                                            AttitudeProvider provider,
                                            Frame inertial,
                                            Frame bodyFixed,
                                            T 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

See Also:

getPropagator(), getPropagator(Frames)