public class FieldKeplerianPropagator<T extends RealFieldElement<T>> extends FieldAbstractAnalyticalPropagator<T>
FieldOrbitDEFAULT_LAW, DEFAULT_MASS, EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE| Constructor and 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.
|
| Modifier and Type | Method and 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, propagateaddAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getField, getFixedStepSize, getFrame, getInitialState, getManagedAdditionalStates, getMode, getPVCoordinates, getStartDate, getStepHandler, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, setEphemerisMode, setMasterMode, setMasterMode, setSlaveMode, setStartDate, stateChanged, updateAdditionalStates@DefaultDataContext 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.
This constructor uses the default data context.
initialFieldOrbit - initial orbitFieldKeplerianPropagator(FieldOrbit, AttitudeProvider)@DefaultDataContext public FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, T mu)
Mass and attitude provider are set to unspecified non-null arbitrary values.
This constructor uses the default data context.
initialFieldOrbit - initial orbitmu - central attraction coefficient (m³/s²)FieldKeplerianPropagator(FieldOrbit, AttitudeProvider, RealFieldElement)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 RealFieldElement<T>>resetInitialState in class FieldAbstractPropagator<T extends RealFieldElement<T>>state - new initial state to considerprotected void resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
resetIntermediateState in class FieldAbstractAnalyticalPropagator<T extends 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 RealFieldElement<T>>date - target date for the orbitprotected T getMass(FieldAbsoluteDate<T> date)
getMass in class FieldAbstractAnalyticalPropagator<T extends RealFieldElement<T>>date - target date for the orbitCopyright © 2002-2020 CS Group. All rights reserved.