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

Class OcmSatelliteEphemeris

java.lang.Object

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

All Implemented Interfaces:

EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,TrajectoryStateHistory>

public class OcmSatelliteEphemeris
extends Object
implements EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,TrajectoryStateHistory>

OCM ephemeris blocks for a single satellite.

Since:

11.0

Author:

Luc Maisonobe

Constructor Summary

Constructors

Constructor	Description
OcmSatelliteEphemeris(String name, double mu, List<TrajectoryStateHistory> blocks)	Create a container for the set of ephemeris blocks in the file that pertain to a single satellite.

Method Summary

Modifier and Type	Method	Description
String	getId()	Get the satellite ID.
double	getMu()	Get the standard gravitational parameter for the satellite.
List<TrajectoryStateHistory>	getSegments()	Get the segments of the ephemeris.
AbsoluteDate	getStart()	Get the start date of the ephemeris.
AbsoluteDate	getStop()	Get the end date of the ephemeris.

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.SatelliteEphemeris

getPropagator, getPropagator

Constructor Detail

OcmSatelliteEphemeris

public OcmSatelliteEphemeris(String name,
                             double mu,
                             List<TrajectoryStateHistory> blocks)

Create a container for the set of ephemeris blocks in the file that pertain to a single satellite.

Parameters:

name - name of the object.

mu - gravitational coefficient to use for building Cartesian/Keplerian orbits

blocks - containing ephemeris data for the satellite.

Method Detail

getId

public String getId()

Get the satellite ID. The satellite ID is unique only within the same ephemeris file.

Specified by:

getId in interface EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,TrajectoryStateHistory>

Returns:

the satellite's ID, never null.

getMu

public double getMu()

Get the standard gravitational parameter for the satellite.

Specified by:

getMu in interface EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,TrajectoryStateHistory>

Returns:

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

getSegments

public List<TrajectoryStateHistory> getSegments()

Get the segments of the ephemeris.

Ephemeris segments are typically used to split an ephemeris around discontinuous events, such as maneuvers.

Specified by:

getSegments in interface EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,TrajectoryStateHistory>

Returns:

the segments contained in the ephemeris file for this satellite.

getStart

public AbsoluteDate getStart()

Get the start date of the ephemeris.

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

Specified by:

getStart in interface EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,TrajectoryStateHistory>

Returns:

ephemeris start date.

getStop

public AbsoluteDate getStop()

Get the end date of the ephemeris.

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

Specified by:

getStop in interface EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,TrajectoryStateHistory>

Returns:

ephemeris end date.