org.orekit.files.ccsds

Class OEMFile.OemSatelliteEphemeris

java.lang.Object

org.orekit.files.ccsds.OEMFile.OemSatelliteEphemeris

All Implemented Interfaces:

EphemerisFile.SatelliteEphemeris

Enclosing class:

OEMFile

public static class OEMFile.OemSatelliteEphemeris
extends Object
implements EphemerisFile.SatelliteEphemeris

OEM ephemeris blocks for a single satellite.

Constructor Summary

Constructors

Constructor and Description
OemSatelliteEphemeris(String id, double mu, List<OEMFile.EphemeridesBlock> 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 and Description
String	getId() Get the satellite ID.
double	getMu() Get the standard gravitational parameter for the satellite.
List<OEMFile.EphemeridesBlock>	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

Constructor Detail

OemSatelliteEphemeris

public OemSatelliteEphemeris(String id,
                             double mu,
                             List<OEMFile.EphemeridesBlock> blocks)

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

Parameters:

id - of the satellite.

mu - standard gravitational parameter used to create orbits for the satellite, in m^3 / s^2.

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

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

Returns:

the gravitational parameter use in EphemerisFile.SatelliteEphemeris.getPropagator(), in m^3 / s^2.

getSegments

public List<OEMFile.EphemeridesBlock> 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

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

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

Returns:

ephemeris end date.