fr.cnes.sirius.patrius.propagation

Class AnalyticalIntegratedEphemeris

java.lang.Object

fr.cnes.sirius.patrius.propagation.AbstractPropagator

fr.cnes.sirius.patrius.propagation.AnalyticalIntegratedEphemeris

All Implemented Interfaces:

PVCoordinatesProvider, BoundedPropagator, Propagator, Serializable

public class AnalyticalIntegratedEphemeris
extends AbstractPropagator
implements BoundedPropagator

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.

See Also:

Serialized Form

Field Summary

Fields inherited from class fr.cnes.sirius.patrius.propagation.AbstractPropagator

MASS

Fields inherited from interface fr.cnes.sirius.patrius.propagation.Propagator

EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE

Constructor Summary

Constructors

Constructor and Description
AnalyticalIntegratedEphemeris(List<AbsoluteDate> initialDatesIn, List<AbsoluteDate> finalDatesIn, List<SpacecraftState> initialStatesIn, Propagator propagatorIn, AttitudeProvider attForcesProvider, AttitudeProvider attEventsProvider, boolean isForwardIn) Constructor.

Method Summary

Modifier and Type	Method and Description
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 fr.cnes.sirius.patrius.propagation.AbstractPropagator

acceptStep, addAdditionalStateProvider, addAdditionalStateProvider, addEventDetector, basicPropagate, clearEventsDetectors, getAttitudeProvider, getAttitudeProviderEvents, getAttitudeProviderForces, getEventsDetectors, getGeneratedEphemeris, getInitialState, getMode, getPVCoordinates, getPvProvider, manageStateFrame, resetInitialState, setAttitudeProvider, setAttitudeProviderEvents, setAttitudeProviderForces, setEphemerisMode, setMasterMode, setMasterMode, setOrbitFrame, setSlaveMode, setStartDate

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from interface fr.cnes.sirius.patrius.propagation.Propagator

addEventDetector, clearEventsDetectors, getAttitudeProvider, getAttitudeProviderEvents, getAttitudeProviderForces, getEventsDetectors, getGeneratedEphemeris, getInitialState, getMode, resetInitialState, setAttitudeProvider, setAttitudeProviderEvents, setAttitudeProviderForces, setEphemerisMode, setMasterMode, setMasterMode, setOrbitFrame, setSlaveMode

Methods inherited from interface fr.cnes.sirius.patrius.orbits.pvcoordinates.PVCoordinatesProvider

getPVCoordinates

Constructor Detail

AnalyticalIntegratedEphemeris

public AnalyticalIntegratedEphemeris(List<AbsoluteDate> initialDatesIn,
                                     List<AbsoluteDate> finalDatesIn,
                                     List<SpacecraftState> initialStatesIn,
                                     Propagator propagatorIn,
                                     AttitudeProvider attForcesProvider,
                                     AttitudeProvider attEventsProvider,
                                     boolean isForwardIn)

Constructor.

Parameters:

initialDatesIn - list of initial dates

finalDatesIn - list of final dates

initialStatesIn - list of initial states at initial dates

propagatorIn - propagator

attForcesProvider - attitude provider for force computation

attEventsProvider - attitude provider for events computation

isForwardIn - true if propagation is forward, false if propagation is backward

Method Detail

propagate

public SpacecraftState propagate(AbsoluteDate target)
                          throws PropagationException

Propagate towards a target date.

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.

Specified by:

propagate in interface Propagator

Overrides:

propagate in class AbstractPropagator

Parameters:

target - target date towards which orbit state should be propagated

Returns:

propagated state

Throws:

PropagationException - if state cannot be propagated

propagate

public SpacecraftState propagate(AbsoluteDate start,
                                 AbsoluteDate target)
                          throws PropagationException

Propagate from a start date towards a target date.

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.

Specified by:

propagate in interface Propagator

Overrides:

propagate in class AbstractPropagator

Parameters:

start - start date from which orbit state should be propagated

target - target date to which orbit state should be propagated

Returns:

propagated state

Throws:

PropagationException - if state cannot be propagated

propagateOrbit

protected Orbit propagateOrbit(AbsoluteDate date)
                        throws PropagationException

Extrapolate an orbit up to a specific target date.

Specified by:

propagateOrbit in class AbstractPropagator

Parameters:

date - target date for the orbit

Returns:

extrapolated parameters

Throws:

PropagationException - if some parameters are out of bounds

getMinDate

public AbsoluteDate getMinDate()

Get the first date of the range.

Specified by:

getMinDate in interface BoundedPropagator

Returns:

the first date of the range

getMaxDate

public AbsoluteDate getMaxDate()

Get the last date of the range.

Specified by:

getMaxDate in interface BoundedPropagator

Returns:

the last date of the range

getFrame

public Frame getFrame()

Get the frame in which the orbit is propagated.

4 cases are possible:

• The propagation frame has been defined (using Propagator.setOrbitFrame(Frame)): it is returned.
• The propagation frame has not been defined and the initial state has been provided and is expressed in a pseudo-inertial frame: the initial state frame is returned.
• The propagation frame has not been defined and the initial state has been provided and is not expressed in a pseudo-inertial frame: null is returned.
• The propagation frame has not been defined and the initial state has not been provided: null is returned.

Specified by:

getFrame in interface Propagator

Overrides:

getFrame in class AbstractPropagator

Returns:

frame in which the orbit is propagated