Class GNSSPropagator
- 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.GNSSPropagator
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- All Implemented Interfaces:
Propagator
,PVCoordinatesProvider
public class GNSSPropagator extends AbstractAnalyticalPropagator
Common handling ofAbstractAnalyticalPropagator
methods for GNSS propagators.This class allows to provide easily a subset of
AbstractAnalyticalPropagator
methods for specific GNSS propagators.- Author:
- Pascal Parraud
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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 Instance Methods Concrete Methods Modifier and Type Method Description Frame
getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits according to the Interface Control Document.Frame
getECI()
Gets the Earth Centered Inertial frame used to propagate the orbit.Frame
getFrame()
Get the frame in which the orbit is propagated.protected double
getMass(AbsoluteDate date)
Get the mass.double
getMU()
Gets the Earth gravity coefficient used for GNSS propagation.GNSSOrbitalElements
getOrbitalElements()
Get the underlying GNSS orbital elements.PVCoordinates
propagateInEcef(AbsoluteDate date)
Gets the PVCoordinates of the GNSS 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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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 GNSS orbits according to the Interface Control Document.- Returns:
- the ECEF frame
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getMU
public double getMU()
Gets the Earth gravity coefficient used for GNSS propagation.- Returns:
- the Earth gravity coefficient.
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getOrbitalElements
public GNSSOrbitalElements getOrbitalElements()
Get the underlying GNSS orbital elements.- Returns:
- the underlying GNSS orbital elements
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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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propagateInEcef
public PVCoordinates propagateInEcef(AbsoluteDate date)
Gets the PVCoordinates of the GNSS SV inECEF frame
.The algorithm uses automatic differentiation to compute velocity and acceleration.
- Parameters:
date
- the computation date- Returns:
- the GNSS SV PVCoordinates in
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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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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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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