org.orekit.files.ccsds.ndm.odm

Class KeplerianElements

java.lang.Object

org.orekit.files.ccsds.section.CommentsContainer

org.orekit.files.ccsds.ndm.odm.KeplerianElements

All Implemented Interfaces:

Data, Section

public class KeplerianElements
extends CommentsContainer
implements Data

Container for Keplerian elements.

Since:

6.1

Author:

sports

Constructor Summary

Constructors

Constructor and Description
KeplerianElements() Simple constructor.

Method Summary

Modifier and Type	Method and Description
KeplerianOrbit	generateKeplerianOrbit(Frame frame) Generate a keplerian orbit.
double	getA() Get the orbit semi-major axis.
double	getAnomaly() Get the orbit anomaly.
PositionAngle	getAnomalyType() Get the type of anomaly (true or mean).
double	getE() Get the orbit eccentricity.
AbsoluteDate	getEpoch() Get epoch of state vector, Keplerian elements and covariance matrix data.
double	getI() Get the orbit inclination.
double	getMeanMotion() Get the orbit mean motion.
double	getMu() Get the gravitational coefficient.
double	getPa() Get the orbit argument of pericenter.
double	getRaan() Get the orbit right ascension of ascending node.
void	setA(double a) Set the orbit semi-major axis.
void	setAnomaly(double anomaly) Set the orbit anomaly.
void	setAnomalyType(PositionAngle anomalyType) Set the type of anomaly.
void	setE(double e) Set the orbit eccentricity.
void	setEpoch(AbsoluteDate epoch) Set epoch of state vector, Keplerian elements and covariance matrix data.
void	setI(double i) Set the orbit inclination.
void	setMeanMotion(double motion) Set the orbit mean motion.
void	setMu(double mu) Set the gravitational coefficient.
void	setPa(double pa) Set the orbit argument of pericenter.
void	setRaan(double raan) Set the orbit right ascension of ascending node.
void	validate(double version) Check is all mandatory entries have been initialized.

Methods inherited from class org.orekit.files.ccsds.section.CommentsContainer

acceptComments, addComment, checkAllowed, checkNotNaN, checkNotNegative, checkNotNull, getComments, refuseFurtherComments

Methods inherited from class java.lang.Object

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

Constructor Detail

KeplerianElements

public KeplerianElements()

Simple constructor.

Method Detail

validate

public void validate(double version)

Check is all mandatory entries have been initialized.

This method should throw an exception if some mandatory entries are missing or not compatible with version number.

We check neither semi-major axis nor mean motion here, they must be checked separately in OPM and OMM parsers

Specified by:

validate in interface Section

Overrides:

validate in class CommentsContainer

Parameters:

version - format version

getEpoch

public AbsoluteDate getEpoch()

Get epoch of state vector, Keplerian elements and covariance matrix data.

Returns:

epoch the epoch

setEpoch

public void setEpoch(AbsoluteDate epoch)

Set epoch of state vector, Keplerian elements and covariance matrix data.

Parameters:

epoch - the epoch to be set

getA

public double getA()

Get the orbit semi-major axis.

Returns:

the orbit semi-major axis

setA

public void setA(double a)

Set the orbit semi-major axis.

Parameters:

a - the semi-major axis to be set

getMeanMotion

public double getMeanMotion()

Get the orbit mean motion.

Returns:

the orbit mean motion

setMeanMotion

public void setMeanMotion(double motion)

Set the orbit mean motion.

Parameters:

motion - the mean motion to be set

getE

public double getE()

Get the orbit eccentricity.

Returns:

the orbit eccentricity

setE

public void setE(double e)

Set the orbit eccentricity.

Parameters:

e - the eccentricity to be set

getI

public double getI()

Get the orbit inclination.

Returns:

the orbit inclination

setI

public void setI(double i)

Set the orbit inclination.

Parameters:

i - the inclination to be set

getRaan

public double getRaan()

Get the orbit right ascension of ascending node.

Returns:

the orbit right ascension of ascending node

setRaan

public void setRaan(double raan)

Set the orbit right ascension of ascending node.

Parameters:

raan - the right ascension of ascending node to be set

getPa

public double getPa()

Get the orbit argument of pericenter.

Returns:

the orbit argument of pericenter

setPa

public void setPa(double pa)

Set the orbit argument of pericenter.

Parameters:

pa - the argument of pericenter to be set

getAnomaly

public double getAnomaly()

Get the orbit anomaly.

Returns:

the orbit anomaly

setAnomaly

public void setAnomaly(double anomaly)

Set the orbit anomaly.

Parameters:

anomaly - the anomaly to be set

getAnomalyType

public PositionAngle getAnomalyType()

Get the type of anomaly (true or mean).

Returns:

the type of anomaly

setAnomalyType

public void setAnomalyType(PositionAngle anomalyType)

Set the type of anomaly.

Parameters:

anomalyType - the type of anomaly to be set

setMu

public void setMu(double mu)

Set the gravitational coefficient.

Parameters:

mu - the coefficient to be set

getMu

public double getMu()

Get the gravitational coefficient.

Returns:

gravitational coefficient

generateKeplerianOrbit

public KeplerianOrbit generateKeplerianOrbit(Frame frame)

Generate a keplerian orbit.

Parameters:

frame - inertial frame for orbit

Returns:

generated orbit