Package org.orekit.files.ccsds.ndm.odm
Class KeplerianElements
- java.lang.Object
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- org.orekit.files.ccsds.section.CommentsContainer
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- org.orekit.files.ccsds.ndm.odm.KeplerianElements
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public class KeplerianElements extends CommentsContainer implements Data
Container for Keplerian elements.- Since:
- 6.1
- Author:
- sports
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Constructor Summary
Constructors Constructor Description KeplerianElements()
Simple constructor.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description KeplerianOrbit
generateKeplerianOrbit(Frame frame)
Generate a keplerian orbit.double
getA()
Get the orbit semi-major axis.double
getAnomaly()
Get the orbit anomaly.PositionAngleType
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(PositionAngleType 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
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Method Detail
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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 interfaceSection
- Overrides:
validate
in classCommentsContainer
- Parameters:
version
- format version
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getEpoch
public AbsoluteDate getEpoch()
Get epoch of state vector, Keplerian elements and covariance matrix data.- Returns:
- epoch the epoch
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setEpoch
public void setEpoch(AbsoluteDate epoch)
Set epoch of state vector, Keplerian elements and covariance matrix data.- Parameters:
epoch
- the epoch to be set
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getA
public double getA()
Get the orbit semi-major axis.- Returns:
- the orbit semi-major axis
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setA
public void setA(double a)
Set the orbit semi-major axis.- Parameters:
a
- the semi-major axis to be set
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getMeanMotion
public double getMeanMotion()
Get the orbit mean motion.- Returns:
- the orbit mean motion
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setMeanMotion
public void setMeanMotion(double motion)
Set the orbit mean motion.- Parameters:
motion
- the mean motion to be set
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getE
public double getE()
Get the orbit eccentricity.- Returns:
- the orbit eccentricity
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setE
public void setE(double e)
Set the orbit eccentricity.- Parameters:
e
- the eccentricity to be set
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getI
public double getI()
Get the orbit inclination.- Returns:
- the orbit inclination
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setI
public void setI(double i)
Set the orbit inclination.- Parameters:
i
- the inclination to be set
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getRaan
public double getRaan()
Get the orbit right ascension of ascending node.- Returns:
- the orbit right ascension of ascending node
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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
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getPa
public double getPa()
Get the orbit argument of pericenter.- Returns:
- the orbit argument of pericenter
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setPa
public void setPa(double pa)
Set the orbit argument of pericenter.- Parameters:
pa
- the argument of pericenter to be set
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getAnomaly
public double getAnomaly()
Get the orbit anomaly.- Returns:
- the orbit anomaly
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setAnomaly
public void setAnomaly(double anomaly)
Set the orbit anomaly.- Parameters:
anomaly
- the anomaly to be set
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getAnomalyType
public PositionAngleType getAnomalyType()
Get the type of anomaly (true or mean).- Returns:
- the type of anomaly
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setAnomalyType
public void setAnomalyType(PositionAngleType anomalyType)
Set the type of anomaly.- Parameters:
anomalyType
- the type of anomaly to be set
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setMu
public void setMu(double mu)
Set the gravitational coefficient.- Parameters:
mu
- the coefficient to be set
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getMu
public double getMu()
Get the gravitational coefficient.- Returns:
- gravitational coefficient
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generateKeplerianOrbit
public KeplerianOrbit generateKeplerianOrbit(Frame frame)
Generate a keplerian orbit.- Parameters:
frame
- inertial frame for orbit- Returns:
- generated orbit
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