Package org.orekit.files.stk

Class STKEphemerisFile.STKEphemeris

java.lang.Object

org.orekit.files.stk.STKEphemerisFile.STKEphemeris

All Implemented Interfaces:

EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,STKEphemerisFile.STKEphemerisSegment>

Enclosing class:

STKEphemerisFile

public static class STKEphemerisFile.STKEphemeris
extends Object
implements EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,STKEphemerisFile.STKEphemerisSegment>

Ephemeris from an STK ephemeris file.

Constructor Summary

Constructors

Constructor	Description
STKEphemeris(String satelliteId, double mu, List<STKEphemerisFile.STKEphemerisSegment> segments)	Constructs a STKEphemerisFile.STKEphemeris instance.

Method Summary

Modifier and Type	Method	Description
String	getId()	Get the satellite ID.
double	getMu()	Get the standard gravitational parameter for the satellite.
List<STKEphemerisFile.STKEphemerisSegment>	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 Details

STKEphemeris

public STKEphemeris(String satelliteId,
 double mu,
 List<STKEphemerisFile.STKEphemerisSegment> segments)

Constructs a STKEphemerisFile.STKEphemeris instance. This constructor shallowly copies the list of segments provided.

Parameters:

satelliteId - satellite id

mu - gravitational parameter (m^3/s^2)

segments - ephemeris segments

Method Details

getId

public String getId()

Description copied from interface: EphemerisFile.SatelliteEphemeris

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

Specified by:

getId in interface EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,STKEphemerisFile.STKEphemerisSegment>

Returns:

the satellite's ID, never null.

getMu

public double getMu()

Description copied from interface: EphemerisFile.SatelliteEphemeris

Get the standard gravitational parameter for the satellite.

Specified by:

getMu in interface EphemerisFile.SatelliteEphemeris<TimeStampedPVCoordinates,STKEphemerisFile.STKEphemerisSegment>

Returns:

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

getSegments

public List<STKEphemerisFile.STKEphemerisSegment> getSegments()

Description copied from interface: EphemerisFile.SatelliteEphemeris

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,STKEphemerisFile.STKEphemerisSegment>

Returns:

the segments contained in the ephemeris file for this satellite.

getStart

public AbsoluteDate getStart()

Description copied from interface: EphemerisFile.SatelliteEphemeris

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,STKEphemerisFile.STKEphemerisSegment>

Returns:

ephemeris start date.

getStop

public AbsoluteDate getStop()

Description copied from interface: EphemerisFile.SatelliteEphemeris

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,STKEphemerisFile.STKEphemerisSegment>

Returns:

ephemeris end date.