Class FieldIntelsatElevenElementsPropagator<T extends CalculusFieldElement<T>>
- java.lang.Object
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- org.orekit.propagation.FieldAbstractPropagator<T>
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- org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator<T>
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- org.orekit.propagation.analytical.intelsat.FieldIntelsatElevenElementsPropagator<T>
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- All Implemented Interfaces:
FieldPropagator<T>
,FieldPVCoordinatesProvider<T>
,ParameterDriversProvider
public class FieldIntelsatElevenElementsPropagator<T extends CalculusFieldElement<T>> extends FieldAbstractAnalyticalPropagator<T>
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.FieldPropagator
DEFAULT_MASS
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Constructor Summary
Constructors Constructor Description FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements)
Default constructor.FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements, Frame inertialFrame, Frame ecefFrame)
Constructor.FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements, Frame inertialFrame, Frame ecefFrame, AttitudeProvider attitudeProvider, T mass)
Constructor.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description FieldUnivariateDerivative2<T>
getEastLongitudeDegrees()
Get the computed satellite's east longitude.Frame
getFrame()
Get the frame in which the orbit is propagated.FieldUnivariateDerivative2<T>
getGeocentricLatitudeDegrees()
Get the computed satellite's geocentric latitude.FieldIntelsatElevenElements<T>
getIntelsatElevenElements()
Get the Intelsat's 11 elements used by the propagator.protected T
getMass(FieldAbsoluteDate<T> date)
Get the mass.FieldUnivariateDerivative2<T>
getOrbitRadius()
Get the computed satellite's orbit.List<ParameterDriver>
getParametersDrivers()
Get the drivers for parameters.FieldPVCoordinates<T>
propagateInEcef(FieldAbsoluteDate<T> date)
Converts the Intelsat's 11 elements into Position/Velocity coordinates in ECEF.protected FieldOrbit<T>
propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)
Extrapolate an orbit up to a specific target date.void
resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.protected void
resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
Reset an intermediate state.-
Methods inherited from class org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator
acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEphemerisGenerator, getEventsDetectors, getPvProvider, propagate
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Methods inherited from class org.orekit.propagation.FieldAbstractPropagator
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getField, getInitialState, getManagedAdditionalStates, getMultiplexer, getStartDate, initializeAdditionalStates, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, setStartDate, 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.FieldPropagator
clearStepHandlers, getPosition, getPVCoordinates, setStepHandler, setStepHandler
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Methods inherited from interface org.orekit.utils.ParameterDriversProvider
getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported
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Constructor Detail
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FieldIntelsatElevenElementsPropagator
@DefaultDataContext public FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> 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
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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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FieldIntelsatElevenElementsPropagator
public FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> 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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FieldIntelsatElevenElementsPropagator
public FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements, Frame inertialFrame, Frame ecefFrame, AttitudeProvider attitudeProvider, T 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 FieldPVCoordinates<T> propagateInEcef(FieldAbsoluteDate<T> 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(FieldSpacecraftState<T> state)
Reset the propagator initial state..- Specified by:
resetInitialState
in interfaceFieldPropagator<T extends CalculusFieldElement<T>>
- Overrides:
resetInitialState
in classFieldAbstractPropagator<T extends CalculusFieldElement<T>>
- Parameters:
state
- new initial state to consider
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getMass
protected T getMass(FieldAbsoluteDate<T> date)
Get the mass..- Specified by:
getMass
in classFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>
- Parameters:
date
- target date for the orbit- Returns:
- mass mass
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resetIntermediateState
protected void resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
Reset an intermediate state..- Specified by:
resetIntermediateState
in classFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>
- Parameters:
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for propagations after itself
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propagateOrbit
protected FieldOrbit<T> propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)
Extrapolate an orbit up to a specific target date..- Specified by:
propagateOrbit
in classFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>
- Parameters:
date
- target date for the orbitparameters
- model parameters- Returns:
- extrapolated parameters
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getEastLongitudeDegrees
public FieldUnivariateDerivative2<T> getEastLongitudeDegrees()
Get the computed satellite's east longitude.- Returns:
- the satellite's east longitude in degrees
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getGeocentricLatitudeDegrees
public FieldUnivariateDerivative2<T> getGeocentricLatitudeDegrees()
Get the computed satellite's geocentric latitude.- Returns:
- the satellite's geocentric latitude in degrees
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getOrbitRadius
public FieldUnivariateDerivative2<T> 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 interfaceFieldPropagator<T extends CalculusFieldElement<T>>
- Overrides:
getFrame
in classFieldAbstractPropagator<T extends CalculusFieldElement<T>>
- Returns:
- frame in which the orbit is propagated
- See Also:
FieldPropagator.resetInitialState(FieldSpacecraftState)
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getParametersDrivers
public List<ParameterDriver> getParametersDrivers()
Get the drivers for parameters..- Returns:
- drivers for parameters
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getIntelsatElevenElements
public FieldIntelsatElevenElements<T> 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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