Package org.orekit.files.ccsds

Class OMMFile

java.lang.Object

org.orekit.files.ccsds.ODMFile

org.orekit.files.ccsds.OGMFile

org.orekit.files.ccsds.OMMFile

public class OMMFile
extends OGMFile

This class gathers the informations present in the Orbital Mean-Elements Message (OMM), and contains methods to generate a CartesianOrbit, a KeplerianOrbit, a SpacecraftState and, eventually, a TLE.

Since:

6.1

Author:

sports

Nested Class Summary

Nested Classes

Modifier and Type	Class	Description
static class	OMMFile.OMMMetaData

Method Summary

Modifier and Type	Method	Description
CartesianOrbit	generateCartesianOrbit()	Generate a CartesianOrbit from the KeplerianOrbit.
KeplerianOrbit	generateKeplerianOrbit()	Generate a KeplerianOrbit based on the OMM mean Keplerian elements.
SpacecraftState	generateSpacecraftState()	Generate spacecraft state from the KeplerianOrbit generated by generateKeplerianOrbit.
TLE	generateTLE()	Generate TLE from OMM file.
double	getBStar()	Get the SGP/SGP4 drag-like coefficient.
char	getClassificationType()	Get the classification type.
String	getElementSetNumber()	Get the element set number for this satellite.
int	getEphemerisType()	Get the ephemeris type.
double	getMeanMotion()	Get the orbit mean motion.
double	getMeanMotionDot()	Get the first time derivative of the mean motion.
double	getMeanMotionDotDot()	Get the second time derivative of the mean motion.
OMMFile.OMMMetaData	getMetaData()	Get the meta data.
Integer	getNoradID()	Get the NORAD Catalog Number ("Satellite Number").
int	getRevAtEpoch()	Get the revolution rumber.
List<String>	getTLERelatedParametersComment()	Get the comment for TLE related parameters.

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 OMMFile.OMMMetaData getMetaData()

Get the meta data.

Specified by:

getMetaData in class OGMFile

Returns:

meta data

getMeanMotion

public double getMeanMotion()

Get the orbit mean motion.

Returns:

the orbit mean motion

getEphemerisType

public int getEphemerisType()

Get the ephemeris type.

Returns:

the ephemerisType

getClassificationType

public char getClassificationType()

Get the classification type.

Returns:

the classificationType

getNoradID

public Integer getNoradID()

Get the NORAD Catalog Number ("Satellite Number").

Returns:

the NORAD Catalog Number

getElementSetNumber

public String getElementSetNumber()

Get the element set number for this satellite.

Returns:

the element set number for this satellite

getRevAtEpoch

public int getRevAtEpoch()

Get the revolution rumber.

Returns:

the revolution rumber

getBStar

public double getBStar()

Get the SGP/SGP4 drag-like coefficient.

Returns:

the SGP/SGP4 drag-like coefficient

getMeanMotionDot

public double getMeanMotionDot()

Get the first time derivative of the mean motion.

Returns:

the first time derivative of the mean motion

getMeanMotionDotDot

public double getMeanMotionDotDot()

Get the second time derivative of the mean motion.

Returns:

the second time derivative of the mean motion

getTLERelatedParametersComment

public List<String> getTLERelatedParametersComment()

Get the comment for TLE related parameters.

Returns:

comment for TLE related parameters

generateKeplerianOrbit

public KeplerianOrbit generateKeplerianOrbit()
                                      throws OrekitException

Generate a KeplerianOrbit based on the OMM mean Keplerian elements. If the reference frame is not pseudo-inertial, an exception is raised.

Returns:

the KeplerianOrbit generated from the OMM information

Throws:

OrekitException - if the reference frame is not pseudo-inertial or if the central body gravitational coefficient cannot be retrieved from the OMM

generateCartesianOrbit

public CartesianOrbit generateCartesianOrbit()
                                      throws OrekitException

Generate a CartesianOrbit from the KeplerianOrbit.

Returns:

the CartesianOrbit generated from the OPM information

Throws:

OrekitException - if the Keplerian Orbit cannot be generated

generateSpacecraftState

public SpacecraftState generateSpacecraftState()
                                        throws OrekitException

Generate spacecraft state from the KeplerianOrbit generated by generateKeplerianOrbit. Raises an exception if OMM doesn't contain spacecraft mass information.

Returns:

the spacecraft state of the OMM

Throws:

OrekitException - if there is no spacecraft mass associated with the OMM

generateTLE

public TLE generateTLE()

Generate TLE from OMM file. Launch Year, Launch Day and Launch Piece are not present in the OMM file, they have to be set manually by the user with the AdditionalData static class.

Returns:

the tle