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

Class GNSSOrbitalElements<O extends GNSSOrbitalElements<O>>

java.lang.Object

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

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

Type Parameters:

O - type of the orbital elements

All Implemented Interfaces:

TimeStamped, ParameterDriversProvider

Direct Known Subclasses:

CommonGnssData

public abstract class GNSSOrbitalElements<O extends GNSSOrbitalElements<O>>
extends GNSSOrbitalElementsDriversProvider
implements TimeStamped

This class provides the minimal set of orbital elements needed by the GNSSPropagator.

The parameters are split in two groups: Keplerian orbital parameters and non-Keplerian evolution parameters. All parameters can be updated as they are all instances of ParameterDriver. Only the non-Keplerian parameters are returned in the GNSSOrbitalElementsDriversProvider.getParametersDrivers() method, the Keplerian orbital parameters must be accessed independently. These groups ensure proper separate computation of state transition matrix and Jacobian matrix by GNSSPropagator.

Since:

13.0

Author:

Pascal Parraud, Luc Maisonobe

Field Summary

Fields

Modifier and Type	Field	Description
static final String	ARGUMENT_OF_PERIGEE	Name for argument of perigee parameter.
static final String	ECCENTRICITY	Name for eccentricity parameter.
static final String	INCLINATION	Name for inclination at reference time parameter.
static final String	MEAN_ANOMALY	Name for mean anomaly at reference time parameter.
static final String	NODE_LONGITUDE	Name for longitude of ascending node at weekly epoch parameter.
static final String	SEMI_MAJOR_AXIS	Name for semi major axis parameter.

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

A_DOT, A_DOT_INDEX, CIC_INDEX, CIS_INDEX, CRC_INDEX, CRS_INDEX, CUC_INDEX, CUS_INDEX, DELTA_N0, DELTA_N0_DOT, DELTA_N0_DOT_INDEX, DELTA_N0_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	GNSSOrbitalElements(double mu, double angularVelocity, int weeksInCycle, TimeScales timeScales, SatelliteSystem system)	Constructor.
protected	GNSSOrbitalElements(FieldGnssOrbitalElements<T,A> original)	Constructor from field instance.

Method Summary

Modifier and Type	Method	Description
AbsoluteDate	getDate()	Get the date.
double	getE()	Get eccentricity.
ParameterDriver	getEDriver()	Get the driver for the eccentricity.
double	getI0()	Get the inclination angle at reference time.
ParameterDriver	getI0Driver()	Get the driver for the inclination angle at reference time.
double	getM0()	Get mean anomaly at reference time.
ParameterDriver	getM0Driver()	Get the driver for the mean anomaly at reference time.
double	getMeanMotion0()	Get the computed mean motion n₀.
double	getMu()	Get the Earth's universal gravitational parameter.
double	getOmega0()	Get longitude of ascending node of orbit plane at weekly epoch.
ParameterDriver	getOmega0Driver()	Get the driver for the longitude of ascending node of orbit plane at weekly epoch.
double	getPa()	Get argument of perigee.
ParameterDriver	getPaDriver()	Get the driver for the argument of perigee.
double	getSma()	Get semi-major axis.
ParameterDriver	getSmaDriver()	Get semi-major axis.
void	setE(double e)	Set eccentricity.
protected void	setGnssDate(GNSSDate gnssDate)	Set GNSS date.
void	setI0(double i0)	Set inclination angle at reference time.
void	setM0(double anom)	Set mean anomaly at reference time.
void	setOmega0(double om0)	Set longitude of ascending node of orbit plane at weekly epoch.
void	setPa(double aop)	Set argument of perigee.
void	setSma(double sma)	Set semi-major axis.
abstract <T extends CalculusFieldElement<T>, F extends FieldGnssOrbitalElements<T, O>> F	toField(Field<T> field)	Create a field version of the instance.

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

copyNonKeplerian, copySelectionSettings, createDriver, getADot, getADotDriver, getAngularVelocity, getCic, getCicDriver, getCis, getCisDriver, getCrc, getCrcDriver, getCrs, getCrsDriver, getCuc, getCucDriver, getCus, getCusDriver, getCycleDuration, getDeltaN0, getDeltaN0Dot, getDeltaN0DotDriver, getDeltaN0Driver, getIDot, getIDotDriver, getOmegaDot, getOmegaDotDriver, getParametersDrivers, getPRN, getSystem, getTime, getTimeDriver, getTimeScales, getWeek, getWeeksInCycle, isCivilianMessage, setADot, setCic, setCis, setCrc, setCrs, setCuc, setCus, setDeltaN0, setDeltaN0Dot, 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

Field Details

SEMI_MAJOR_AXIS

public static final String SEMI_MAJOR_AXIS

Name for semi major axis parameter.

See Also:

• Constant Field Values

ECCENTRICITY

public static final String ECCENTRICITY

Name for eccentricity parameter.

See Also:

• Constant Field Values

INCLINATION

public static final String INCLINATION

Name for inclination at reference time parameter.

See Also:

• Constant Field Values

ARGUMENT_OF_PERIGEE

public static final String ARGUMENT_OF_PERIGEE

Name for argument of perigee parameter.

See Also:

• Constant Field Values

NODE_LONGITUDE

public static final String NODE_LONGITUDE

Name for longitude of ascending node at weekly epoch parameter.

See Also:

• Constant Field Values

MEAN_ANOMALY

public static final String MEAN_ANOMALY

Name for mean anomaly at reference time parameter.

See Also:

• Constant Field Values

Constructor Details

GNSSOrbitalElements

protected GNSSOrbitalElements(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)

GNSSOrbitalElements

protected GNSSOrbitalElements(FieldGnssOrbitalElements<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

toField

public abstract <T extends CalculusFieldElement<T>,
F extends FieldGnssOrbitalElements<T,
O>>
F toField(Field<T> field)

Create a field version of the instance.

Type Parameters:

T - type of the field elements

F - type of the orbital elements (field version)

Parameters:

field - field to which elements belong

Returns:

field version of the instance

setGnssDate

protected void setGnssDate(GNSSDate gnssDate)

Set GNSS date.

Specified by:

setGnssDate in class GNSSOrbitalElementsDriversProvider

Parameters:

gnssDate - GNSS date

getDate

public AbsoluteDate getDate()

Get the date.

Specified by:

getDate in interface TimeStamped

Returns:

date attached to the object

getMu

public double getMu()

Get the Earth's universal gravitational parameter.

Returns:

the Earth's universal gravitational parameter

getSmaDriver

public ParameterDriver getSmaDriver()

Get semi-major axis.

Returns:

driver for the semi-major axis (m)

getSma

public double getSma()

Get semi-major axis.

Returns:

semi-major axis (m)

setSma

public void setSma(double sma)

Set semi-major axis.

Parameters:

sma - demi-major axis (m)

getMeanMotion0

public double getMeanMotion0()

Get the computed mean motion n₀.

Returns:

the computed mean motion n₀ (rad/s)

Since:

13.0

getEDriver

public ParameterDriver getEDriver()

Get the driver for the eccentricity.

Returns:

driver for the eccentricity

getE

public double getE()

Get eccentricity.

Returns:

eccentricity

setE

public void setE(double e)

Set eccentricity.

Parameters:

e - eccentricity

getI0Driver

public ParameterDriver getI0Driver()

Get the driver for the inclination angle at reference time.

Returns:

driver for the inclination angle at reference time (rad)

getI0

public double getI0()

Get the inclination angle at reference time.

Returns:

inclination angle at reference time (rad)

setI0

public void setI0(double i0)

Set inclination angle at reference time.

Parameters:

i0 - inclination angle at reference time (rad)

getOmega0Driver

public ParameterDriver getOmega0Driver()

Get the driver for the longitude of ascending node of orbit plane at weekly epoch.

Returns:

driver for the longitude of ascending node of orbit plane at weekly epoch (rad)

getOmega0

public double getOmega0()

Get longitude of ascending node of orbit plane at weekly epoch.

Returns:

longitude of ascending node of orbit plane at weekly epoch (rad)

setOmega0

public void setOmega0(double om0)

Set longitude of ascending node of orbit plane at weekly epoch.

Parameters:

om0 - longitude of ascending node of orbit plane at weekly epoch (rad)

getPaDriver

public ParameterDriver getPaDriver()

Get the driver for the argument of perigee.

Returns:

driver for the argument of perigee (rad)

getPa

public double getPa()

Get argument of perigee.

Returns:

argument of perigee (rad)

setPa

public void setPa(double aop)

Set argument of perigee.

Parameters:

aop - argument of perigee (rad)

getM0Driver

public ParameterDriver getM0Driver()

Get the driver for the mean anomaly at reference time.

Returns:

driver for the mean anomaly at reference time (rad)

getM0

public double getM0()

Get mean anomaly at reference time.

Returns:

mean anomaly at reference time (rad)

setM0

public void setM0(double anom)

Set mean anomaly at reference time.

Parameters:

anom - mean anomaly at reference time (rad)