Package org.orekit.files.ccsds.ndm.odm.ocm

Class TrajectoryStateHistory

java.lang.Object

org.orekit.files.ccsds.ndm.odm.ocm.TrajectoryStateHistory

All Implemented Interfaces:

EphemerisFile.EphemerisSegment<TimeStampedPVCoordinates>

public class TrajectoryStateHistory
extends Object
implements EphemerisFile.EphemerisSegment<TimeStampedPVCoordinates>

Trajectory state history.

Since:

11.0

Author:

Luc Maisonobe

Constructor Summary

Constructors

Constructor	Description
TrajectoryStateHistory(TrajectoryStateHistoryMetadata metadata, List<TrajectoryState> states, OneAxisEllipsoid body, double mu)	Simple constructor.

Method Summary

Modifier and Type	Method	Description
CartesianDerivativesFilter	getAvailableDerivatives()	Get which derivatives of position are available in this ephemeris segment.
OneAxisEllipsoid	getBody()	Get central body.
List<TimeStampedPVCoordinates>	getCoordinates()	Get the coordinates for this ephemeris segment in EphemerisFile.EphemerisSegment.getFrame().
Frame	getFrame()	Get the reference frame for this ephemeris segment.
int	getInterpolationSamples()	Get the number of samples to use in interpolation.
TrajectoryStateHistoryMetadata	getMetadata()	Get metadata.
double	getMu()	Get the standard gravitational parameter for the satellite.
AbsoluteDate	getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	getStop()	Get the end date of this ephemeris segment.
List<TrajectoryState>	getTrajectoryStates()	Get the trajectory states.

Methods inherited from class java.lang.Object

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

Methods inherited from interface org.orekit.files.general.EphemerisFile.EphemerisSegment

getInertialFrame, getPropagator, getPropagator

Constructor Detail

TrajectoryStateHistory

public TrajectoryStateHistory(TrajectoryStateHistoryMetadata metadata,
                              List<TrajectoryState> states,
                              OneAxisEllipsoid body,
                              double mu)

Simple constructor.

Parameters:

metadata - metadata

states - orbital states

body - central body (may be null if type is not OrbitElementsType.GEODETIC)

mu - gravitational parameter in m³/s²

Method Detail

getMetadata

public TrajectoryStateHistoryMetadata getMetadata()

Get metadata.

Returns:

metadata

getTrajectoryStates

public List<TrajectoryState> getTrajectoryStates()

Get the trajectory states.

Returns:

trajectory states

getMu

public double getMu()

Get the standard gravitational parameter for the satellite.

Specified by:

getMu in interface EphemerisFile.EphemerisSegment<TimeStampedPVCoordinates>

Returns:

the gravitational parameter used in EphemerisFile.EphemerisSegment.getPropagator(AttitudeProvider), in m³/s².

getBody

public OneAxisEllipsoid getBody()

Get central body.

Returns:

central body

Since:

12.0

getFrame

public Frame getFrame()

Get the reference frame for this ephemeris segment. The defining frame for EphemerisFile.EphemerisSegment.getCoordinates().

Specified by:

getFrame in interface EphemerisFile.EphemerisSegment<TimeStampedPVCoordinates>

Returns:

the reference frame for this segment. Never null.

getInterpolationSamples

public int getInterpolationSamples()

Get the number of samples to use in interpolation.

Specified by:

getInterpolationSamples in interface EphemerisFile.EphemerisSegment<TimeStampedPVCoordinates>

Returns:

the number of points to use for interpolation.

getAvailableDerivatives

public CartesianDerivativesFilter getAvailableDerivatives()

Get which derivatives of position are available in this ephemeris segment.

While EphemerisFile.EphemerisSegment.getCoordinates() always returns position, velocity, and acceleration the return value from this method indicates which of those are in the ephemeris file and are actually valid.

Specified by:

getAvailableDerivatives in interface EphemerisFile.EphemerisSegment<TimeStampedPVCoordinates>

Returns:

a value indicating if the file contains velocity and/or acceleration data.

getStart

public AbsoluteDate getStart()

Get the start date of this ephemeris segment.

The date returned by this method is equivalent to getPropagator().getMinDate().

Specified by:

getStart in interface EphemerisFile.EphemerisSegment<TimeStampedPVCoordinates>

Returns:

ephemeris segment start date.

getStop

public AbsoluteDate getStop()

Get the end date of this ephemeris segment.

The date returned by this method is equivalent to getPropagator().getMaxDate().

Specified by:

getStop in interface EphemerisFile.EphemerisSegment<TimeStampedPVCoordinates>

Returns:

ephemeris segment end date.

getCoordinates

public List<TimeStampedPVCoordinates> getCoordinates()

Get the coordinates for this ephemeris segment in EphemerisFile.EphemerisSegment.getFrame().

Specified by:

getCoordinates in interface EphemerisFile.EphemerisSegment<TimeStampedPVCoordinates>

Returns:

a list of state vectors in chronological order. The coordinates are not necessarily evenly spaced in time. The value of EphemerisFile.EphemerisSegment.getAvailableDerivatives() indicates if the velocity or accelerations were specified in the file. Any position, velocity, or acceleration coordinates that are not specified in the ephemeris file are zero in the returned values.