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java.lang.Objectorg.orekit.propagation.AbstractPropagator
org.orekit.propagation.precomputed.IntegratedEphemeris
public class IntegratedEphemeris
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.
A typical use case is for numerically integrated orbits, which can be used by algorithms that need to wander around according to their own algorithm without cumbersome tight links with the integrator.
Another use case is for persistence, as this class is serializable.
As this class implements the Propagator
interface, it can itself be used in batch mode to build another instance of the
same type. This is however not recommended since it would be a waste of resources.
Note that this class stores all intermediate states along with interpolation models, so it may be memory intensive.
NumericalPropagator
,
Serialized FormField 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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IntegratedEphemeris(List<AbsoluteDate> startDates,
List<AbsoluteDate> minDates,
List<AbsoluteDate> maxDates,
OrbitType orbitType,
PositionAngle angleType,
AttitudeProvider attitudeForcesProvider,
AttitudeProvider attitudeEventsProvider,
Map<String,AdditionalStateInfo> additionalStateInfos,
List<ContinuousOutputModel> models,
Frame referenceFrame,
double mu)
Creates a new instance of IntegratedEphemeris. |
Method Summary | |
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protected SpacecraftState |
basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features. |
SpacecraftState |
getInitialState()
Get the propagator initial state. |
AbsoluteDate |
getMaxDate()
Get the last date of the range. |
AbsoluteDate |
getMinDate()
Get the first date of the range. |
PVCoordinates |
getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the PVCoordinates of the body in the selected frame. |
void |
manageStateFrame()
In this class, nothing as to be done in the frame managing before propagation because propagation will be performed in Frame referenceFrame It just throws an OrekitException if this frame is non inertial or pseudo-inertial. |
protected Orbit |
propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
void |
resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
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, getFrame, getGeneratedEphemeris, getMode, propagate, propagate, setAttitudeProvider, setAttitudeProviderEvents, setAttitudeProviderForces, setEphemerisMode, setMasterMode, setMasterMode, setOrbitFrame, setSlaveMode |
Constructor Detail |
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public IntegratedEphemeris(List<AbsoluteDate> startDates, List<AbsoluteDate> minDates, List<AbsoluteDate> maxDates, OrbitType orbitType, PositionAngle angleType, AttitudeProvider attitudeForcesProvider, AttitudeProvider attitudeEventsProvider, Map<String,AdditionalStateInfo> additionalStateInfos, List<ContinuousOutputModel> models, Frame referenceFrame, double mu) throws OrekitException
startDates
- list of start dates of the integration (can be minDate or maxDate)minDates
- list of first dates of the rangesmaxDates
- list of last dates of the rangesorbitType
- orbit typeangleType
- position angle typeattitudeForcesProvider
- attitude provider for forces computationattitudeEventsProvider
- attitude provider for events computationadditionalStateInfos
- additional states informationsmodels
- list of underlying raw mathematical modelsreferenceFrame
- reference referenceFramemu
- central body attraction coefficient
OrekitException
- if several providers have the same nameMethod Detail |
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protected SpacecraftState basicPropagate(AbsoluteDate date) throws PropagationException
This method is similar in spirit to the AbstractPropagator.propagate(org.orekit.time.AbsoluteDate)
method,
except that it does not call any handler during
propagation, nor any discrete events. It always stop exactly at
the specified date.
basicPropagate
in class AbstractPropagator
date
- target date for propagation
PropagationException
- if propagation cannot reach specified datepublic void manageStateFrame() throws OrekitException
manageStateFrame
in class AbstractPropagator
OrekitException
- if the frame is non inertial or pseudo-inertialprotected Orbit propagateOrbit(AbsoluteDate date) throws PropagationException
propagateOrbit
in class AbstractPropagator
date
- target date for the orbit
PropagationException
- if some parameters are out of boundspublic PVCoordinates getPVCoordinates(AbsoluteDate date, Frame frame) throws OrekitException
PVCoordinates
of the body in the selected frame.
getPVCoordinates
in interface PVCoordinatesProvider
getPVCoordinates
in class AbstractPropagator
date
- current dateframe
- the frame where to define the position
OrekitException
- if position cannot be computed in given framepublic AbsoluteDate getMinDate()
getMinDate
in interface BoundedPropagator
public AbsoluteDate getMaxDate()
getMaxDate
in interface BoundedPropagator
public void resetInitialState(SpacecraftState state) throws PropagationException
resetInitialState
in interface Propagator
resetInitialState
in class AbstractPropagator
state
- new initial state to consider
PropagationException
- if initial state cannot be resetpublic SpacecraftState getInitialState() throws OrekitException
getInitialState
in interface Propagator
getInitialState
in class AbstractPropagator
OrekitException
- if state cannot be retrieved
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