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java.lang.Objectorg.orekit.propagation.AbstractPropagator
org.orekit.propagation.AnalyticalIntegratedEphemeris
public class AnalyticalIntegratedEphemeris
This class stores sequentially generated orbital parameters for later retrieval.
Instances of this class are built and then must be fed with the results
provided by Propagator
objects
configured in ephemeris generation mode
. Once propagation is o, random access to any
intermediate state of the orbit throughout the propagation range is possible.
Field Summary |
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Fields inherited from class org.orekit.propagation.AbstractPropagator |
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MASS |
Fields inherited from interface org.orekit.propagation.Propagator |
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EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE |
Constructor Summary | |
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AnalyticalIntegratedEphemeris(List<AbsoluteDate> initialDates,
List<AbsoluteDate> finalDates,
List<SpacecraftState> initialStates,
AbstractPropagator propagator,
AttitudeProvider attForcesProvider,
AttitudeProvider attEventsProvider,
boolean isForward)
Constructor. |
Method Summary | |
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Frame |
getFrame()
Get the frame in which the orbit is propagated. |
AbsoluteDate |
getMaxDate()
Get the last date of the range. |
AbsoluteDate |
getMinDate()
Get the first date of the range. |
SpacecraftState |
propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
protected Orbit |
propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
Methods inherited from class java.lang.Object |
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clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait |
Methods inherited from interface org.orekit.propagation.Propagator |
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addEventDetector, clearEventsDetectors, getAttitudeProvider, getAttitudeProviderEvents, getAttitudeProviderForces, getEventsDetectors, getGeneratedEphemeris, getInitialState, getMode, resetInitialState, setAttitudeProvider, setAttitudeProviderEvents, setAttitudeProviderForces, setEphemerisMode, setMasterMode, setMasterMode, setOrbitFrame, setSlaveMode |
Methods inherited from interface org.orekit.utils.PVCoordinatesProvider |
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getPVCoordinates |
Constructor Detail |
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public AnalyticalIntegratedEphemeris(List<AbsoluteDate> initialDates, List<AbsoluteDate> finalDates, List<SpacecraftState> initialStates, AbstractPropagator propagator, AttitudeProvider attForcesProvider, AttitudeProvider attEventsProvider, boolean isForward)
initialDates
- list of initial datesfinalDates
- list of final datesinitialStates
- list of initial states at initial datespropagator
- propagatorattForcesProvider
- attitude provider for force computationattEventsProvider
- attitude provider for events computationisForward
- true if propagation is forward, false if propagation is backwardMethod Detail |
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public SpacecraftState propagate(AbsoluteDate target) throws PropagationException
Simple propagators use only the target date as the specification for computing the propagated state. More feature rich propagators can consider other information and provide different operating modes or G-stop facilities to stop at pinpointed events occurrences. In these cases, the target date is only a hint, not a mandatory objective.
propagate
in interface Propagator
propagate
in class AbstractPropagator
target
- target date towards which orbit state should be propagated
PropagationException
- if state cannot be propagatedpublic SpacecraftState propagate(AbsoluteDate start, AbsoluteDate target) throws PropagationException
Those propagators use a start date and a target date to compute the propagated state. For propagators using event detection mechanism, if the provided start date is different from the initial state date, a first, simple propagation is performed, without processing any event computation. Then complete propagation is performed from start date to target date.
propagate
in interface Propagator
propagate
in class AbstractPropagator
start
- start date from which orbit state should be propagatedtarget
- target date to which orbit state should be propagated
PropagationException
- if state cannot be propagatedprotected Orbit propagateOrbit(AbsoluteDate date) throws PropagationException
propagateOrbit
in class AbstractPropagator
date
- target date for the orbit
PropagationException
- if some parameters are out of boundspublic AbsoluteDate getMinDate()
getMinDate
in interface BoundedPropagator
public AbsoluteDate getMaxDate()
getMaxDate
in interface BoundedPropagator
public Frame getFrame()
4 cases are possible:
Propagator.setOrbitFrame(Frame)
): it is returned.
getFrame
in interface Propagator
getFrame
in class AbstractPropagator
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