org.orekit.files.general

Class OrekitEphemerisFile.OrekitSatelliteEphemeris

java.lang.Object

org.orekit.files.general.OrekitEphemerisFile.OrekitSatelliteEphemeris

All Implemented Interfaces:

EphemerisFile.SatelliteEphemeris

Enclosing class:

OrekitEphemerisFile

public static class OrekitEphemerisFile.OrekitSatelliteEphemeris
extends Object
implements EphemerisFile.SatelliteEphemeris

Inner class of OrekitEphemerisFile that defines the OrekitEphemerisFile.OrekitSatelliteEphemeris corresponding object for this ephemeris type.

Field Summary

Fields

Modifier and Type	Field and Description
static int	DEFAULT_INTERPOLATION_SIZE Defines the default interpolation sample size if it is not specified on a segment.

Constructor Summary

Constructors

Constructor and Description
OrekitSatelliteEphemeris(String id) Standard constructor for building the satellite Ephemeris object.

Method Summary

Modifier and Type	Method and Description
OrekitEphemerisFile.OrekitEphemerisSegment	addNewSegment(List<SpacecraftState> states) Injects pre-computed satellite states into this ephemeris file object, returning the generated OrekitEphemerisFile.OrekitEphemerisSegment that has been stored internally.
OrekitEphemerisFile.OrekitEphemerisSegment	addNewSegment(List<SpacecraftState> states, CelestialBody body, int interpolationSampleSize) Injects pre-computed satellite states into this ephemeris file object, returning the generated OrekitEphemerisFile.OrekitEphemerisSegment that has been stored internally.
OrekitEphemerisFile.OrekitEphemerisSegment	addNewSegment(List<SpacecraftState> states, int interpolationSampleSize) Injects pre-computed satellite states into this ephemeris file object, returning the generated OrekitEphemerisFile.OrekitEphemerisSegment that has been stored internally.
String	getId() Get the satellite ID.
double	getMu() Get the standard gravitational parameter for the satellite.
List<? extends EphemerisFile.EphemerisSegment>	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

Field Detail

DEFAULT_INTERPOLATION_SIZE

public static final int DEFAULT_INTERPOLATION_SIZE

Defines the default interpolation sample size if it is not specified on a segment.

See Also:

Constant Field Values

Constructor Detail

OrekitSatelliteEphemeris

public OrekitSatelliteEphemeris(String id)

Standard constructor for building the satellite Ephemeris object.

Parameters:

id - the ID of the space object for this data

Method Detail

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

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

Returns:

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

getSegments

public List<? extends EphemerisFile.EphemerisSegment> 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

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

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

Returns:

ephemeris end date.

addNewSegment

public OrekitEphemerisFile.OrekitEphemerisSegment addNewSegment(List<SpacecraftState> states)
                                                         throws OrekitException

Injects pre-computed satellite states into this ephemeris file object, returning the generated OrekitEphemerisFile.OrekitEphemerisSegment that has been stored internally. Defaults the celestial body to earth and the interpolation size to the default.

Parameters:

states - a list of SpacecraftState that will comprise this new unit.

Returns:

the generated OrekitEphemerisFile.OrekitEphemerisSegment

Throws:

OrekitException - if there is an exception in time or frame transformations

addNewSegment

public OrekitEphemerisFile.OrekitEphemerisSegment addNewSegment(List<SpacecraftState> states,
                                                                int interpolationSampleSize)
                                                         throws OrekitException

Injects pre-computed satellite states into this ephemeris file object, returning the generated OrekitEphemerisFile.OrekitEphemerisSegment that has been stored internally. Defaults the Celestial Body to be Earths

Parameters:

states - a list of SpacecraftState that will comprise this new unit.

interpolationSampleSize - the number of interpolation samples that should be used when processed by another system

Returns:

the generated OrekitEphemerisFile.OrekitEphemerisSegment

Throws:

OrekitException - if there is an exception in time or frame transformations

addNewSegment

public OrekitEphemerisFile.OrekitEphemerisSegment addNewSegment(List<SpacecraftState> states,
                                                                CelestialBody body,
                                                                int interpolationSampleSize)
                                                         throws OrekitException

Injects pre-computed satellite states into this ephemeris file object, returning the generated OrekitEphemerisFile.OrekitEphemerisSegment that has been stored internally.

Parameters:

states - a list of SpacecraftState that will comprise this new unit.

body - the celestial body the state's frames are with respect to

interpolationSampleSize - the number of interpolation samples that should be used when processed by another system

Returns:

the generated OrekitEphemerisFile.OrekitEphemerisSegment

Throws:

OrekitException - if there is an exception in time or frame transformations