Package 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.

Beware that the Orekit getters and setters all rely on SI units. The parsers and writers take care of converting these SI units into CCSDS mandatory units. The Unit class provides useful fromSi and toSI methods in case the callers already use CCSDS units instead of the API SI units. The general-purpose Unit class (without an 's') and the CCSDS-specific Units class (with an 's') also provide some predefined units. These predefined units and the fromSi and toSI conversion methods are indeed what the parsers and writers use for the conversions.

Since:
6.1
Author:
sports

  • Constructor Details

    • KeplerianElements

      public KeplerianElements()
      Simple constructor.

  • Method Details

    • 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