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

Class SBASNavigationMessage

java.lang.Object

org.orekit.propagation.analytical.gnss.data.AbstractEphemerisMessage

org.orekit.propagation.analytical.gnss.data.SBASNavigationMessage

All Implemented Interfaces:

NavigationMessage, SBASOrbitalElements, TimeStamped

public class SBASNavigationMessage
extends AbstractEphemerisMessage
implements SBASOrbitalElements

Container for data contained in a SBAS navigation message.

Since:

11.0

Author:

Bryan Cazabonne

Field Summary

Fields

Modifier and Type	Field	Description
static String	SBAS	Message type.

Constructor Summary

Constructors

Constructor	Description
SBASNavigationMessage()	Constructor.

Method Summary

Modifier and Type	Method	Description
double	getAGf0()	Gets the Zeroth Order Clock Correction.
double	getAGf1()	Gets the First Order Clock Correction.
int	getIODN()	Gets the Issue Of Data Navigation (IODN).
String	getNavigationMessageSubType()	Get navigation message subtype.
String	getNavigationMessageType()	Get navigation message type.
SBASPropagator	getPropagator()	Get the propagator corresponding to the navigation message.
SBASPropagator	getPropagator(Frames frames)	Get the propagator corresponding to the navigation message.
SBASPropagator	getPropagator(Frames frames, AttitudeProvider provider, Frame inertial, Frame bodyFixed, double mass, double mu)	Get the propagator corresponding to the navigation message.
double	getTime()	Gets the Reference Time of the SBAS orbit in GPS seconds of the week.
double	getURA()	Getter for the user range accuray (meters).
int	getWeek()	Gets the Reference Week of the SBAS orbit.
void	setAGf0(double a0)	Setter for the SV clock bias.
void	setAGf1(double a1)	Setter for the SV relative frequency.
void	setIODN(double iod)	Setter for the issue of data navigation.
void	setTime(double time)	Setter for the reference time of the SBAS orbit in GPS seconds of the week.
void	setURA(double accuracy)	Setter for the user range accuracy.

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

getDate, getEpochToc, getHealth, getPRN, getX, getXDot, getXDotDot, getY, getYDot, getYDotDot, getZ, getZDot, getZDotDot, setDate, setEpochToc, setHealth, setPRN, setX, setXDot, setXDotDot, setY, setYDot, setYDotDot, setZ, setZDot, setZDotDot

Methods inherited from class java.lang.Object

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

Methods inherited from interface org.orekit.propagation.analytical.gnss.data.SBASOrbitalElements

getPRN, getToc, getX, getXDot, getXDotDot, getY, getYDot, getYDotDot, getZ, getZDot, getZDotDot

Methods inherited from interface org.orekit.time.TimeStamped

durationFrom, getDate

Field Detail

SBAS

public static final String SBAS

Message type.

Since:

14.0

See Also:

Constant Field Values

Constructor Detail

SBASNavigationMessage

public SBASNavigationMessage()

Constructor.

Method Detail

getNavigationMessageType

public String getNavigationMessageType()

Get navigation message type.

Specified by:

getNavigationMessageType in interface NavigationMessage

Returns:

the navigation message type

getNavigationMessageSubType

public String getNavigationMessageSubType()

Get navigation message subtype.

Specified by:

getNavigationMessageSubType in interface NavigationMessage

Returns:

the navigation message type

getPropagator

@DefaultDataContext
public SBASPropagator getPropagator()

Get the propagator corresponding to the navigation message.

The attitude provider is set by default be aligned with the EME2000 frame.
The Earth gravity coefficient is set by default to the SBAS_MU.
The mass is set by default to the DEFAULT_MASS.
The ECI frame is set by default to the EME2000 frame.
The ECEF frame is set by default to the CIO/2010-based ITRF simple EOP.

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, double)

getPropagator

public SBASPropagator getPropagator(Frames frames)

Get the propagator corresponding to the navigation message.

The attitude provider is set by default be aligned with the EME2000 frame.
The Earth gravity coefficient is set by default to the SBAS_MU.
The mass is set by default to the DEFAULT_MASS.
The ECI frame is set by default to the EME2000 frame.
The ECEF frame is set by default to the CIO/2010-based ITRF simple EOP.

Parameters:

frames - set of frames to use

Returns:

the propagator corresponding to the navigation message

Since:

12.0

See Also:

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

getPropagator

public SBASPropagator getPropagator(Frames frames,
                                    AttitudeProvider provider,
                                    Frame inertial,
                                    Frame bodyFixed,
                                    double mass,
                                    double mu)

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

mu - central attraction coefficient

Returns:

the propagator corresponding to the navigation message

Since:

12.0

See Also:

getPropagator(), getPropagator(Frames)

getWeek

public int getWeek()

Gets the Reference Week of the SBAS orbit.

Specified by:

getWeek in interface SBASOrbitalElements

Returns:

the Reference Week of the SBAS orbit

getTime

public double getTime()

Gets the Reference Time of the SBAS orbit in GPS seconds of the week.

Specified by:

getTime in interface SBASOrbitalElements

Returns:

the Reference Time of the SBAS orbit (s)

setTime

public void setTime(double time)

Setter for the reference time of the SBAS orbit in GPS seconds of the week.

Parameters:

time - the time to set

getIODN

public int getIODN()

Gets the Issue Of Data Navigation (IODN).

Specified by:

getIODN in interface SBASOrbitalElements

Returns:

the IODN

setIODN

public void setIODN(double iod)

Setter for the issue of data navigation.

Parameters:

iod - the issue of data to set

getAGf0

public double getAGf0()

Gets the Zeroth Order Clock Correction.

Specified by:

getAGf0 in interface SBASOrbitalElements

Returns:

the Zeroth Order Clock Correction (s)

setAGf0

public void setAGf0(double a0)

Setter for the SV clock bias.

Parameters:

a0 - the SV clock bias to set in seconds

getAGf1

public double getAGf1()

Gets the First Order Clock Correction.

Specified by:

getAGf1 in interface SBASOrbitalElements

Returns:

the First Order Clock Correction (s/s)

setAGf1

public void setAGf1(double a1)

Setter for the SV relative frequency.

Parameters:

a1 - the SV relative frequency to set

getURA

public double getURA()

Getter for the user range accuray (meters).

Returns:

the user range accuracy

setURA

public void setURA(double accuracy)

Setter for the user range accuracy.

Parameters:

accuracy - the value to set