Class SBASNavigationMessage
- java.lang.Object
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- org.orekit.propagation.analytical.gnss.data.AbstractEphemerisMessage
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- org.orekit.propagation.analytical.gnss.data.SBASNavigationMessage
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- All Implemented Interfaces:
SBASOrbitalElements
,TimeStamped
public class SBASNavigationMessage extends AbstractEphemerisMessage implements SBASOrbitalElements
Container for data contained in a SBAS navigation message.- Since:
- 11.0
- Author:
- Bryan Cazabonne
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Constructor Summary
Constructors Constructor Description SBASNavigationMessage()
Constructor.
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Method Summary
All Methods Instance Methods Concrete Methods 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).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
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Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
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Methods inherited from interface org.orekit.propagation.analytical.gnss.data.SBASOrbitalElements
getPRN, getToc, getX, getXDot, getXDotDot, getY, getYDot, getYDotDot, getZ, getZDot, getZDotDot
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Methods inherited from interface org.orekit.time.TimeStamped
durationFrom, getDate
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Method Detail
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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 theSBAS_MU
.
The mass is set by default to theDEFAULT_MASS
.
The ECI frame is set by default to theEME2000 frame
.
The ECEF frame is set by default to theCIO/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)
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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 theSBAS_MU
.
The mass is set by default to theDEFAULT_MASS
.
The ECI frame is set by default to theEME2000 frame
.
The ECEF frame is set by default to theCIO/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)
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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 useprovider
- attitude providerinertial
- inertial frame, use to provide the propagated orbitbodyFixed
- body fixed frame, corresponding to the navigation messagemass
- spacecraft mass in kgmu
- central attraction coefficient- Returns:
- the propagator corresponding to the navigation message
- Since:
- 12.0
- See Also:
getPropagator()
,getPropagator(Frames)
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getWeek
public int getWeek()
Gets the Reference Week of the SBAS orbit.- Specified by:
getWeek
in interfaceSBASOrbitalElements
- Returns:
- the Reference Week of the SBAS orbit
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getTime
public double getTime()
Gets the Reference Time of the SBAS orbit in GPS seconds of the week.- Specified by:
getTime
in interfaceSBASOrbitalElements
- Returns:
- the Reference Time of the SBAS orbit (s)
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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
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getIODN
public int getIODN()
Gets the Issue Of Data Navigation (IODN).- Specified by:
getIODN
in interfaceSBASOrbitalElements
- Returns:
- the IODN
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setIODN
public void setIODN(double iod)
Setter for the issue of data navigation.- Parameters:
iod
- the issue of data to set
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getAGf0
public double getAGf0()
Gets the Zeroth Order Clock Correction.- Specified by:
getAGf0
in interfaceSBASOrbitalElements
- Returns:
- the Zeroth Order Clock Correction (s)
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setAGf0
public void setAGf0(double a0)
Setter for the SV clock bias.- Parameters:
a0
- the SV clock bias to set in seconds
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getAGf1
public double getAGf1()
Gets the First Order Clock Correction.- Specified by:
getAGf1
in interfaceSBASOrbitalElements
- Returns:
- the First Order Clock Correction (s/s)
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setAGf1
public void setAGf1(double a1)
Setter for the SV relative frequency.- Parameters:
a1
- the SV relative frequency to set
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getURA
public double getURA()
Getter for the user range accuray (meters).- Returns:
- the user range accuracy
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setURA
public void setURA(double accuracy)
Setter for the user range accuracy.- Parameters:
accuracy
- the value to set
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