Class GLONASSAnalyticalPropagator
- java.lang.Object
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- org.orekit.propagation.AbstractPropagator
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- org.orekit.propagation.analytical.AbstractAnalyticalPropagator
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- org.orekit.propagation.analytical.gnss.GLONASSAnalyticalPropagator
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- All Implemented Interfaces:
Propagator
,PVCoordinatesProvider
public class GLONASSAnalyticalPropagator extends AbstractAnalyticalPropagator
This class aims at propagating a GLONASS orbit fromGLONASSOrbitalElements
.Caution: The Glonass analytical propagator can only be used with
GLONASSAlmanac
. Using this propagator with aGLONASSNavigationMessage
is prone to error.- Since:
- 10.0
- Author:
- Bryan Cazabonne
- See Also:
- GLONASS Interface Control Document
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Field Summary
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Fields inherited from interface org.orekit.propagation.Propagator
DEFAULT_MASS
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Method Summary
All Methods Static Methods Instance Methods Concrete Methods Modifier and Type Method Description Frame
getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GLONASS orbits.Frame
getECI()
Gets the Earth Centered Inertial frame used to propagate the orbit.Frame
getFrame()
Get the frame in which the orbit is propagated.GLONASSOrbitalElements
getGLONASSOrbitalElements()
Gets the underlying GLONASS orbital elements.protected double
getMass(AbsoluteDate date)
Get the mass.static double
getMU()
Get the Earth gravity coefficient used for GLONASS propagation.PVCoordinates
propagateInEcef(AbsoluteDate date)
Gets the PVCoordinates of the GLONASS SV inECEF frame
.protected Orbit
propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.void
resetInitialState(SpacecraftState state)
Reset the propagator initial state.protected void
resetIntermediateState(SpacecraftState state, boolean forward)
Reset an intermediate state.-
Methods inherited from class org.orekit.propagation.analytical.AbstractAnalyticalPropagator
acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEphemerisGenerator, getEventsDetectors, getJacobiansColumnsNames, getPvProvider, propagate
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Methods inherited from class org.orekit.propagation.AbstractPropagator
addAdditionalStateProvider, createHarvester, getAdditionalStateProviders, getAttitudeProvider, getHarvester, getInitialState, getManagedAdditionalStates, getMultiplexer, getStartDate, initializeAdditionalStates, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, setStartDate, setupMatricesComputation, stateChanged, updateAdditionalStates, updateUnmanagedStates
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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.Propagator
clearStepHandlers, getPosition, getPVCoordinates, setStepHandler, setStepHandler
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Method Detail
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propagateInEcef
public PVCoordinates propagateInEcef(AbsoluteDate date)
Gets the PVCoordinates of the GLONASS SV inECEF frame
.The algorithm is defined at Appendix M.1 from GLONASS Interface Control Document, with automatic differentiation added to compute velocity and acceleration.
- Parameters:
date
- the computation date- Returns:
- the GLONASS SV PVCoordinates in
ECEF frame
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getMass
protected double getMass(AbsoluteDate date)
Get the mass.- Specified by:
getMass
in classAbstractAnalyticalPropagator
- Parameters:
date
- target date for the orbit- Returns:
- mass mass
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getMU
public static double getMU()
Get the Earth gravity coefficient used for GLONASS propagation.- Returns:
- the Earth gravity coefficient.
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getGLONASSOrbitalElements
public GLONASSOrbitalElements getGLONASSOrbitalElements()
Gets the underlying GLONASS orbital elements.- Returns:
- the underlying GLONASS orbital elements
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getECI
public Frame getECI()
Gets the Earth Centered Inertial frame used to propagate the orbit.- Returns:
- the ECI frame
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getECEF
public Frame getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GLONASS orbits.- Returns:
- the ECEF frame
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getFrame
public Frame getFrame()
Get the frame in which the orbit is propagated.The propagation frame is the definition frame of the initial state, so this method should be called after this state has been set, otherwise it may return null.
- Specified by:
getFrame
in interfacePropagator
- Overrides:
getFrame
in classAbstractPropagator
- Returns:
- frame in which the orbit is propagated
- See Also:
Propagator.resetInitialState(SpacecraftState)
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resetInitialState
public void resetInitialState(SpacecraftState state)
Reset the propagator initial state.- Specified by:
resetInitialState
in interfacePropagator
- Overrides:
resetInitialState
in classAbstractPropagator
- Parameters:
state
- new initial state to consider
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resetIntermediateState
protected void resetIntermediateState(SpacecraftState state, boolean forward)
Reset an intermediate state.- Specified by:
resetIntermediateState
in classAbstractAnalyticalPropagator
- Parameters:
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for propagations after itself
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propagateOrbit
protected Orbit propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.- Specified by:
propagateOrbit
in classAbstractAnalyticalPropagator
- Parameters:
date
- target date for the orbit- Returns:
- extrapolated parameters
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