Serializable
, Propagator
, PVCoordinatesProvider
public class KeplerianPropagator extends AbstractAnalyticalPropagator implements Serializable
Orbit
,
Serialized FormDEFAULT_LAW, DEFAULT_MASS, EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE
Constructor | Description |
---|---|
KeplerianPropagator(Orbit initialOrbit) |
Build a propagator from orbit only.
|
KeplerianPropagator(Orbit initialOrbit,
double mu) |
Build a propagator from orbit and central attraction coefficient μ.
|
KeplerianPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv) |
Build a propagator from orbit and attitude provider.
|
KeplerianPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mu) |
Build a propagator from orbit, attitude provider and central attraction
coefficient μ.
|
KeplerianPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mu,
double mass) |
Build propagator from orbit, attitude provider, central attraction
coefficient μ and mass.
|
Modifier and Type | Method | Description |
---|---|---|
protected double |
getMass(AbsoluteDate date) |
Get the mass.
|
protected Orbit |
propagateOrbit(AbsoluteDate date) |
Extrapolate an orbit up to a specific target date.
|
void |
resetInitialState(SpacecraftState state) |
Reset the propagator initial state.
|
protected void |
resetIntermediateState(SpacecraftState state,
boolean forward) |
Reset an intermediate state.
|
acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEventsDetectors, getGeneratedEphemeris, getPvProvider, propagate
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getFixedStepSize, getFrame, getInitialState, getManagedAdditionalStates, getMode, getPVCoordinates, getStartDate, getStepHandler, isAdditionalStateManaged, propagate, setAttitudeProvider, setEphemerisMode, setEphemerisMode, setMasterMode, setMasterMode, setSlaveMode, setStartDate, updateAdditionalStates
public KeplerianPropagator(Orbit initialOrbit)
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.
initialOrbit
- initial orbitpublic KeplerianPropagator(Orbit initialOrbit, double mu)
Mass and attitude provider are set to unspecified non-null arbitrary values.
initialOrbit
- initial orbitmu
- central attraction coefficient (m³/s²)public KeplerianPropagator(Orbit initialOrbit, 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.
initialOrbit
- initial orbitattitudeProv
- attitude providerpublic KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu)
Mass is set to an unspecified non-null arbitrary value.
initialOrbit
- initial orbitattitudeProv
- attitude providermu
- central attraction coefficient (m³/s²)public KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu, double mass)
initialOrbit
- initial orbitattitudeProv
- attitude providermu
- central attraction coefficient (m³/s²)mass
- spacecraft mass (kg)public void resetInitialState(SpacecraftState state)
resetInitialState
in interface Propagator
resetInitialState
in class AbstractPropagator
state
- new initial state to considerprotected void resetIntermediateState(SpacecraftState state, boolean forward)
resetIntermediateState
in class AbstractAnalyticalPropagator
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for
propagations after itselfprotected Orbit propagateOrbit(AbsoluteDate date)
propagateOrbit
in class AbstractAnalyticalPropagator
date
- target date for the orbitprotected double getMass(AbsoluteDate date)
getMass
in class AbstractAnalyticalPropagator
date
- target date for the orbitCopyright © 2002-2019 CS Systèmes d'information. All rights reserved.