Package org.orekit.files.general

Class EphemerisSegmentPropagator<C extends TimeStampedPVCoordinates>

java.lang.Object

org.orekit.propagation.AbstractPropagator

org.orekit.propagation.analytical.AbstractAnalyticalPropagator

org.orekit.files.general.EphemerisSegmentPropagator<C>

Type Parameters:

C - type of the Cartesian coordinates

All Implemented Interfaces:

BoundedPropagator, Propagator, BoundedPVCoordinatesProvider, PVCoordinatesProvider

public class EphemerisSegmentPropagator<C extends TimeStampedPVCoordinates>
extends AbstractAnalyticalPropagator
implements BoundedPropagator

A Propagator based on a EphemerisFile.EphemerisSegment.

The getPVCoordinates(AbsoluteDate, Frame) is implemented without using the AbstractPropagator.propagate(AbsoluteDate) methods so using this class as a PVCoordinatesProvider still behaves as expected when the ephemeris file did not have a valid gravitational parameter.

Author:

Evan Ward

Field Summary

Fields inherited from interface org.orekit.propagation.Propagator

DEFAULT_MASS

Constructor Summary

Constructors

Constructor	Description
EphemerisSegmentPropagator(EphemerisFile.EphemerisSegment<C> ephemeris, AttitudeProvider attitudeProvider)	Create a Propagator from an ephemeris segment.

Method Summary

Modifier and Type	Method	Description
SpacecraftState	getInitialState()	Get the propagator initial state.
protected double	getMass(AbsoluteDate date)	Get the mass.
AbsoluteDate	getMaxDate()	Get the last date of the range.
AbsoluteDate	getMinDate()	Get the first date of the range.
Vector3D	getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
TimeStampedPVCoordinates	getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
Vector3D	getVelocity(AbsoluteDate date, Frame frame)	Get the velocity of the body in the selected frame.
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.

Methods inherited from class org.orekit.propagation.analytical.AbstractAnalyticalPropagator

acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, clearMatricesComputation, getEphemerisGenerator, getEventDetectors, getJacobiansColumnsNames, getPvProvider, propagate

Methods inherited from class org.orekit.propagation.AbstractPropagator

addAdditionalDataProvider, createHarvester, getAdditionalDataProviders, getAttitudeProvider, getFrame, getHarvester, getManagedAdditionalData, getMultiplexer, getStartDate, initializeAdditionalData, initializePropagation, isAdditionalDataManaged, propagate, removeAdditionalDataProvider, setAttitudeProvider, setStartDate, setupMatricesComputation, stateChanged, updateAdditionalData, updateUnmanagedData

Methods inherited from class java.lang.Object

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

Methods inherited from interface org.orekit.propagation.Propagator

addAdditionalDataProvider, addEventDetector, clearEventsDetectors, clearStepHandlers, getAdditionalDataProviders, getAttitudeProvider, getEphemerisGenerator, getEventDetectors, getFrame, getManagedAdditionalData, getMultiplexer, isAdditionalDataManaged, propagate, propagate, setAttitudeProvider, setStepHandler, setStepHandler, setupMatricesComputation

Constructor Details

EphemerisSegmentPropagator

public EphemerisSegmentPropagator(EphemerisFile.EphemerisSegment<C> ephemeris,
 AttitudeProvider attitudeProvider)

Create a Propagator from an ephemeris segment.

Parameters:

ephemeris - segment containing the data for this propagator.

attitudeProvider - provider for attitude computation

Method Details

getPVCoordinates

public TimeStampedPVCoordinates getPVCoordinates(AbsoluteDate date,
 Frame frame)

Description copied from interface: Propagator

Get the PVCoordinates of the body in the selected frame.

Specified by:

getPVCoordinates in interface Propagator

Specified by:

getPVCoordinates in interface PVCoordinatesProvider

Parameters:

date - current date

frame - the frame where to define the position

Returns:

time-stamped position/velocity of the body (m and m/s)

getVelocity

public Vector3D getVelocity(AbsoluteDate date,
 Frame frame)

Description copied from interface: Propagator

Get the velocity of the body in the selected frame.

Specified by:

getVelocity in interface Propagator

Specified by:

getVelocity in interface PVCoordinatesProvider

Parameters:

date - current date

frame - the frame where to define the velocity

Returns:

velocity of the body (m/s)

getPosition

public Vector3D getPosition(AbsoluteDate date,
 Frame frame)

Description copied from interface: Propagator

Get the position of the body in the selected frame.

Specified by:

getPosition in interface Propagator

Specified by:

getPosition in interface PVCoordinatesProvider

Parameters:

date - current date

frame - the frame where to define the position

Returns:

position of the body (m and)

propagateOrbit

public Orbit propagateOrbit(AbsoluteDate date)

Description copied from class: AbstractAnalyticalPropagator

Extrapolate an orbit up to a specific target date.

Specified by:

propagateOrbit in class AbstractAnalyticalPropagator

Parameters:

date - target date for the orbit

Returns:

extrapolated parameters

getMinDate

public AbsoluteDate getMinDate()

Description copied from interface: BoundedPVCoordinatesProvider

Get the first date of the range.

Specified by:

getMinDate in interface BoundedPVCoordinatesProvider

Returns:

the first date of the range

getMaxDate

public AbsoluteDate getMaxDate()

Description copied from interface: BoundedPVCoordinatesProvider

Get the last date of the range.

Specified by:

getMaxDate in interface BoundedPVCoordinatesProvider

Returns:

the last date of the range

getMass

protected double getMass(AbsoluteDate date)

Description copied from class: AbstractAnalyticalPropagator

Get the mass.

Specified by:

getMass in class AbstractAnalyticalPropagator

Parameters:

date - target date for the orbit

Returns:

mass mass

getInitialState

public SpacecraftState getInitialState()

Description copied from class: AbstractPropagator

Get the propagator initial state.

Specified by:

getInitialState in interface Propagator

Overrides:

getInitialState in class AbstractPropagator

Returns:

initial state

resetIntermediateState

protected void resetIntermediateState(SpacecraftState state,
 boolean forward)

Description copied from class: AbstractAnalyticalPropagator

Reset an intermediate state.

Specified by:

resetIntermediateState in class AbstractAnalyticalPropagator

Parameters:

state - new intermediate state to consider

forward - if true, the intermediate state is valid for propagations after itself

resetInitialState

public void resetInitialState(SpacecraftState state)

Description copied from class: AbstractPropagator

Reset the propagator initial state.

Specified by:

resetInitialState in interface Propagator

Overrides:

resetInitialState in class AbstractPropagator

Parameters:

state - new initial state to consider