Class FieldKeplerianPropagator<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.FieldKeplerianPropagator<T>
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- Type Parameters:
T
- type of the field elements
- All Implemented Interfaces:
FieldPropagator<T>
,FieldPVCoordinatesProvider<T>
,ParameterDriversProvider
public class FieldKeplerianPropagator<T extends CalculusFieldElement<T>> extends FieldAbstractAnalyticalPropagator<T>
Simple Keplerian orbit propagator.- Author:
- Guylaine Prat
- See Also:
FieldOrbit
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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 FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit)
Build a propagator from orbit only.FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, AttitudeProvider attitudeProv)
Build a propagator from orbit and attitude provider.FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, AttitudeProvider attitudeProv, T mu)
Build a propagator from orbit, attitude provider and central attraction coefficient μ.FieldKeplerianPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mu, T mass)
Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, T mu)
Build a propagator from orbit and central attraction coefficient μ.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description protected T
getMass(FieldAbsoluteDate<T> date)
Get the mass.List<ParameterDriver>
getParametersDrivers()
Get the drivers for parameters.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, getFrame, 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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FieldKeplerianPropagator
public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit)
Build a propagator from orbit only.The central attraction coefficient μ is set to the same value used for the initial orbit definition. Mass and attitude provider are set to unspecified non-null arbitrary values.
- Parameters:
initialFieldOrbit
- initial orbit- See Also:
FieldKeplerianPropagator(FieldOrbit, AttitudeProvider)
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FieldKeplerianPropagator
public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, T mu)
Build a propagator from orbit and central attraction coefficient μ.Mass and attitude provider are set to unspecified non-null arbitrary values.
- Parameters:
initialFieldOrbit
- initial orbitmu
- central attraction coefficient (m³/s²)- See Also:
FieldKeplerianPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement)
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FieldKeplerianPropagator
public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, AttitudeProvider attitudeProv)
Build a propagator from orbit and attitude provider.The central attraction coefficient μ is set to the same value used for the initial orbit definition. Mass is set to an unspecified non-null arbitrary value.
- Parameters:
initialFieldOrbit
- initial orbitattitudeProv
- attitude provider
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FieldKeplerianPropagator
public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, AttitudeProvider attitudeProv, T mu)
Build a propagator from orbit, attitude provider and central attraction coefficient μ.Mass is set to an unspecified non-null arbitrary value.
- Parameters:
initialFieldOrbit
- initial orbitattitudeProv
- attitude providermu
- central attraction coefficient (m³/s²)
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FieldKeplerianPropagator
public FieldKeplerianPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mu, T mass)
Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.- Parameters:
initialOrbit
- initial orbitattitudeProv
- attitude providermu
- central attraction coefficient (m³/s²)mass
- spacecraft mass (kg)
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Method Detail
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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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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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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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getParametersDrivers
public List<ParameterDriver> getParametersDrivers()
Get the drivers for parameters.- Returns:
- drivers for parameters
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