Class KeplerianElements

  • All Implemented Interfaces:
    Data, Section

    public class KeplerianElements
    extends CommentsContainer
    implements Data
    Container for Keplerian elements.
    Since:
    6.1
    Author:
    sports
    • 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 PositionAngleType getAnomalyType()
        Get the type of anomaly (true or mean).
        Returns:
        the type of anomaly
      • setAnomalyType

        public void setAnomalyType​(PositionAngleType 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