Class IntelsatElevenElementsPropagator
- 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.intelsat.IntelsatElevenElementsPropagator
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- All Implemented Interfaces:
Propagator
,PVCoordinatesProvider
public class IntelsatElevenElementsPropagator extends AbstractAnalyticalPropagator
This class provides elements to propagate Intelsat's 11 elements.Intelsat's 11 elements propagation is defined in ITU-R S.1525 standard.
- Since:
- 12.1
- Author:
- Bryan Cazabonne
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Field Summary
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Fields inherited from interface org.orekit.propagation.Propagator
DEFAULT_MASS
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Constructor Summary
Constructors Constructor Description IntelsatElevenElementsPropagator(IntelsatElevenElements elements)
Default constructor.IntelsatElevenElementsPropagator(IntelsatElevenElements elements, Frame inertialFrame, Frame ecefFrame)
Constructor.IntelsatElevenElementsPropagator(IntelsatElevenElements elements, Frame inertialFrame, Frame ecefFrame, AttitudeProvider attitudeProvider, double mass)
Constructor.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description UnivariateDerivative2
getEastLongitudeDegrees()
Get the computed satellite's east longitude.Frame
getFrame()
Get the frame in which the orbit is propagated.UnivariateDerivative2
getGeocentricLatitudeDegrees()
Get the computed satellite's geocentric latitude.IntelsatElevenElements
getIntelsatElevenElements()
Get the Intelsat's 11 elements used by the propagator.protected double
getMass(AbsoluteDate date)
Get the mass.UnivariateDerivative2
getOrbitRadius()
Get the computed satellite's orbit.PVCoordinates
propagateInEcef(AbsoluteDate date)
Converts the Intelsat's 11 elements into Position/Velocity coordinates in ECEF.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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Constructor Detail
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IntelsatElevenElementsPropagator
@DefaultDataContext public IntelsatElevenElementsPropagator(IntelsatElevenElements elements)
Default constructor.This constructor uses the
default data context
.The attitude provider is set by default to be aligned with the inertial frame.
The mass is set by default to theDEFAULT_MASS
.
The inertial frame is set by default to theTOD frame
in the default data context.
The ECEF frame is set by default to theCIO/2010-based ITRF simple EOP
in the default data context.- Parameters:
elements
- Intelsat's 11 elements
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IntelsatElevenElementsPropagator
public IntelsatElevenElementsPropagator(IntelsatElevenElements elements, Frame inertialFrame, Frame ecefFrame)
Constructor.The attitude provider is set by default to be aligned with the inertial frame.
The mass is set by default to theDEFAULT_MASS
.
- Parameters:
elements
- Intelsat's 11 elementsinertialFrame
- inertial frame for the output orbitecefFrame
- ECEF frame related to the Intelsat's 11 elements
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IntelsatElevenElementsPropagator
public IntelsatElevenElementsPropagator(IntelsatElevenElements elements, Frame inertialFrame, Frame ecefFrame, AttitudeProvider attitudeProvider, double mass)
Constructor.- Parameters:
elements
- Intelsat's 11 elementsinertialFrame
- inertial frame for the output orbitecefFrame
- ECEF frame related to the Intelsat's 11 elementsattitudeProvider
- attitude providermass
- spacecraft mass
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Method Detail
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propagateInEcef
public PVCoordinates propagateInEcef(AbsoluteDate date)
Converts the Intelsat's 11 elements into Position/Velocity coordinates in ECEF.- Parameters:
date
- computation epoch- Returns:
- Position/Velocity coordinates in ECEF
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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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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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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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getEastLongitudeDegrees
public UnivariateDerivative2 getEastLongitudeDegrees()
Get the computed satellite's east longitude.- Returns:
- the satellite's east longitude in degrees
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getGeocentricLatitudeDegrees
public UnivariateDerivative2 getGeocentricLatitudeDegrees()
Get the computed satellite's geocentric latitude.- Returns:
- the satellite's geocentric latitude in degrees
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getOrbitRadius
public UnivariateDerivative2 getOrbitRadius()
Get the computed satellite's orbit.- Returns:
- satellite's orbit radius in meters
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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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getIntelsatElevenElements
public IntelsatElevenElements getIntelsatElevenElements()
Get the Intelsat's 11 elements used by the propagator.- Returns:
- the Intelsat's 11 elements used by the propagator
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