T
- type of the field elementspublic class FieldKeplerianPropagator<T extends org.hipparchus.CalculusFieldElement<T>> extends FieldAbstractAnalyticalPropagator<T>
FieldOrbit
DEFAULT_MASS
Constructor and Description |
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FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit)
Build a propagator from orbit only.
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FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
AttitudeProvider attitudeProv)
Build a propagator from orbit and attitude provider.
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FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
AttitudeProvider attitudeProv,
T mu)
Build a propagator from orbit, attitude provider and central attraction
coefficient μ.
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FieldKeplerianPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
T mu,
T mass)
Build propagator from orbit, attitude provider, central attraction
coefficient μ and mass.
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FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
T mu)
Build a propagator from orbit and central attraction coefficient μ.
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Modifier and Type | Method and Description |
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protected T |
getMass(FieldAbsoluteDate<T> date)
Get the mass.
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List<ParameterDriver> |
getParametersDrivers()
Get the drivers for parameters.
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protected FieldOrbit<T> |
propagateOrbit(FieldAbsoluteDate<T> date,
T[] parameters)
Extrapolate an orbit up to a specific target date.
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void |
resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.
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protected void |
resetIntermediateState(FieldSpacecraftState<T> state,
boolean forward)
Reset an intermediate state.
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acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEphemerisGenerator, getEventsDetectors, getPvProvider, propagate
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getField, getFrame, getInitialState, getManagedAdditionalStates, getMultiplexer, getPVCoordinates, getStartDate, initializeAdditionalStates, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, setStartDate, stateChanged, updateAdditionalStates, updateUnmanagedStates
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported
clearStepHandlers, setStepHandler, setStepHandler
getPosition
public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit)
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.
initialFieldOrbit
- initial orbitFieldKeplerianPropagator(FieldOrbit, AttitudeProvider)
public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, T mu)
Mass and attitude provider are set to unspecified non-null arbitrary values.
initialFieldOrbit
- initial orbitmu
- central attraction coefficient (m³/s²)FieldKeplerianPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement)
public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, AttitudeProvider attitudeProv)
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.
initialFieldOrbit
- initial orbitattitudeProv
- attitude providerpublic FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, AttitudeProvider attitudeProv, T mu)
Mass is set to an unspecified non-null arbitrary value.
initialFieldOrbit
- initial orbitattitudeProv
- attitude providermu
- central attraction coefficient (m³/s²)public FieldKeplerianPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mu, T mass)
initialOrbit
- initial orbitattitudeProv
- attitude providermu
- central attraction coefficient (m³/s²)mass
- spacecraft mass (kg)public void resetInitialState(FieldSpacecraftState<T> state)
resetInitialState
in interface FieldPropagator<T extends org.hipparchus.CalculusFieldElement<T>>
resetInitialState
in class FieldAbstractPropagator<T extends org.hipparchus.CalculusFieldElement<T>>
state
- new initial state to considerprotected void resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
resetIntermediateState
in class FieldAbstractAnalyticalPropagator<T extends org.hipparchus.CalculusFieldElement<T>>
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for
propagations after itselfprotected FieldOrbit<T> propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)
propagateOrbit
in class FieldAbstractAnalyticalPropagator<T extends org.hipparchus.CalculusFieldElement<T>>
date
- target date for the orbitparameters
- model parametersprotected T getMass(FieldAbsoluteDate<T> date)
getMass
in class FieldAbstractAnalyticalPropagator<T extends org.hipparchus.CalculusFieldElement<T>>
date
- target date for the orbitpublic List<ParameterDriver> getParametersDrivers()
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