Package org.orekit.files.ccsds

Class OPMFile

java.lang.Object

org.orekit.files.ccsds.ODMFile

org.orekit.files.ccsds.OGMFile

org.orekit.files.ccsds.OPMFile

public class OPMFile
extends OGMFile

This class gathers the informations present in the Orbital Parameter Message (OPM), and contains methods to generate CartesianOrbit, KeplerianOrbit or SpacecraftState.

Since:

6.1

Author:

sports

Nested Class Summary

Nested Classes

Modifier and Type	Class	Description
static class	OPMFile.Maneuver	Maneuver in an OPM file.

Method Summary

Modifier and Type	Method	Description
CartesianOrbit	generateCartesianOrbit()	Generate a CartesianOrbit from the OPM state vector data.
KeplerianOrbit	generateKeplerianOrbit()	Generate a KeplerianOrbit from the OPM Keplerian elements if hasKeplerianElements is true, or from the state vector data otherwise.
SpacecraftState	generateSpacecraftState()	Generate spacecraft state from the CartesianOrbit generated by generateCartesianOrbit.
boolean	getHasManeuver()	Get boolean testing whether the OPM contains at least one maneuver.
OPMFile.Maneuver	getManeuver(int index)	Get a maneuver.
List<OPMFile.Maneuver>	getManeuvers()	Get a list of all maneuvers.
ODMMetaData	getMetaData()	Get the meta data.
List<String>	getMetaDataComment()	Get the comment for meta-data.
int	getNbManeuvers()	Get the number of maneuvers present in the OPM.
org.hipparchus.geometry.euclidean.threed.Vector3D	getPosition()	Get position vector.
PVCoordinates	getPVCoordinates()	Get the position/velocity coordinates contained in the OPM.
org.hipparchus.geometry.euclidean.threed.Vector3D	getVelocity()	Get velocity vector.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from class org.orekit.files.ccsds.ODMFile

getConventions, getCreationDate, getFormatVersion, getHeaderComment, getMissionReferenceDate, getMuCreated, getMuParsed, getMuSet, getMuUsed, getOriginator, setMuUsed

Methods inherited from class org.orekit.files.ccsds.OGMFile

getA, getAnomaly, getAnomalyType, getCovarianceComment, getCovarianceMatrix, getCovRefFrame, getCovRefLofType, getDragArea, getDragCoeff, getE, getEpoch, getEpochComment, getI, getKeplerianElementsComment, getMass, getPa, getRaan, getSolarRadArea, getSolarRadCoeff, getSpacecraftComment, getUserDefinedParameters, hasCovarianceMatrix, hasKeplerianElements

Method Detail

getMetaData

public ODMMetaData getMetaData()

Get the meta data.

Specified by:

getMetaData in class OGMFile

Returns:

meta data

getPosition

public org.hipparchus.geometry.euclidean.threed.Vector3D getPosition()

Get position vector.

Returns:

the position vector

getVelocity

public org.hipparchus.geometry.euclidean.threed.Vector3D getVelocity()

Get velocity vector.

Returns:

the velocity vector

getNbManeuvers

public int getNbManeuvers()

Get the number of maneuvers present in the OPM.

Returns:

the number of maneuvers

getManeuvers

public List<OPMFile.Maneuver> getManeuvers()

Get a list of all maneuvers.

Returns:

unmodifiable list of all maneuvers.

getManeuver

public OPMFile.Maneuver getManeuver(int index)

Get a maneuver.

Parameters:

index - maneuver index, counting from 0

Returns:

maneuver

getHasManeuver

public boolean getHasManeuver()

Get boolean testing whether the OPM contains at least one maneuver.

Returns:

true if OPM contains at least one maneuver false otherwise

getMetaDataComment

public List<String> getMetaDataComment()

Get the comment for meta-data.

Returns:

comment for meta-data

getPVCoordinates

public PVCoordinates getPVCoordinates()

Get the position/velocity coordinates contained in the OPM.

Returns:

the position/velocity coordinates contained in the OPM

generateCartesianOrbit

public CartesianOrbit generateCartesianOrbit()

Generate a CartesianOrbit from the OPM state vector data. If the reference frame is not pseudo-inertial, an exception is raised.

Returns:

the CartesianOrbit generated from the OPM information

generateKeplerianOrbit

public KeplerianOrbit generateKeplerianOrbit()

Generate a KeplerianOrbit from the OPM Keplerian elements if hasKeplerianElements is true, or from the state vector data otherwise. If the reference frame is not pseudo-inertial, an exception is raised.

Returns:

the KeplerianOrbit generated from the OPM information

generateSpacecraftState

public SpacecraftState generateSpacecraftState()

Generate spacecraft state from the CartesianOrbit generated by generateCartesianOrbit. Raises an exception if OPM doesn't contain spacecraft mass information.

Returns:

the spacecraft state of the OPM