Class OemSatelliteEphemeris
- java.lang.Object
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- org.orekit.files.ccsds.ndm.odm.oem.OemSatelliteEphemeris
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- All Implemented Interfaces:
EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,OemSegment>
public class OemSatelliteEphemeris extends Object implements EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,OemSegment>
OEM ephemeris blocks for a single satellite.- Since:
- 11.0
- Author:
- Luc Maisonobe
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Constructor Summary
Constructors Constructor Description OemSatelliteEphemeris(String id, double mu, List<OemSegment> blocks)
Create a container for the set of ephemeris blocks in the file that pertain to a single satellite.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description String
getId()
Get the satellite ID.double
getMu()
Get the standard gravitational parameter for the satellite.List<OemSegment>
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
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Methods inherited from interface org.orekit.files.general.EphemerisFile.SatelliteEphemeris
getPropagator, getPropagator
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Constructor Detail
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OemSatelliteEphemeris
public OemSatelliteEphemeris(String id, double mu, List<OemSegment> blocks)
Create a container for the set of ephemeris blocks in the file that pertain to a single satellite.- Parameters:
id
- id of the satellite.mu
- gravitational coefficient to use for building Cartesian/Keplerian orbitsblocks
- containing ephemeris data for the satellite.
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Method Detail
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getId
public String getId()
Get the satellite ID. The satellite ID is unique only within the same ephemeris file.- Specified by:
getId
in interfaceEphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,OemSegment>
- Returns:
- the satellite's ID, never
null
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getMu
public double getMu()
Get the standard gravitational parameter for the satellite.- Specified by:
getMu
in interfaceEphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,OemSegment>
- Returns:
- the gravitational parameter used in
EphemerisFile.SatelliteEphemeris.getPropagator(AttitudeProvider)
, in m³/s².
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getSegments
public List<OemSegment> 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 interfaceEphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,OemSegment>
- Returns:
- the segments contained in the ephemeris file for this satellite.
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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 interfaceEphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,OemSegment>
- Returns:
- ephemeris start date.
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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 interfaceEphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,OemSegment>
- Returns:
- ephemeris end date.
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