FieldPropagator<T>
, FieldPVCoordinatesProvider<T>
public class FieldKeplerianPropagator<T extends org.hipparchus.RealFieldElement<T>> extends FieldAbstractAnalyticalPropagator<T>
FieldOrbit
DEFAULT_LAW, DEFAULT_MASS, EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE
Constructor | Description |
---|---|
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit) |
Build a propagator from orbit only.
|
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
double mu) |
Build a propagator from orbit and central attraction coefficient μ.
|
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
AttitudeProvider attitudeProv) |
Build a propagator from orbit and attitude provider.
|
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
AttitudeProvider attitudeProv,
double mu) |
Build a propagator from orbit, attitude provider and central attraction
coefficient μ.
|
FieldKeplerianPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
double mu,
T mass) |
Build propagator from orbit, attitude provider, central attraction
coefficient μ and mass.
|
Modifier and Type | Method | Description |
---|---|---|
protected T |
getMass(FieldAbsoluteDate<T> date) |
Get the mass.
|
protected FieldOrbit<T> |
propagateOrbit(FieldAbsoluteDate<T> date) |
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.
|
acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEventsDetectors, getGeneratedEphemeris, getPvProvider, propagate
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getField, getFixedStepSize, getFrame, getInitialState, getManagedAdditionalStates, getMode, getPVCoordinates, getStartDate, getStepHandler, isAdditionalStateManaged, propagate, setAttitudeProvider, setEphemerisMode, setMasterMode, setMasterMode, setSlaveMode, setStartDate, updateAdditionalStates
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 orbitpublic FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, double mu)
Mass and attitude provider are set to unspecified non-null arbitrary values.
initialFieldOrbit
- initial orbitmu
- central attraction coefficient (m³/s²)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, double 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, double 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.RealFieldElement<T>>
resetInitialState
in class FieldAbstractPropagator<T extends org.hipparchus.RealFieldElement<T>>
state
- new initial state to considerprotected void resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
resetIntermediateState
in class FieldAbstractAnalyticalPropagator<T extends org.hipparchus.RealFieldElement<T>>
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for
propagations after itselfprotected FieldOrbit<T> propagateOrbit(FieldAbsoluteDate<T> date)
propagateOrbit
in class FieldAbstractAnalyticalPropagator<T extends org.hipparchus.RealFieldElement<T>>
date
- target date for the orbitprotected T getMass(FieldAbsoluteDate<T> date)
getMass
in class FieldAbstractAnalyticalPropagator<T extends org.hipparchus.RealFieldElement<T>>
date
- target date for the orbitCopyright © 2002-2019 CS Systèmes d'information. All rights reserved.