Package org.orekit.propagation.semianalytical.dsst.utilities

Class AuxiliaryElements

  • public class AuxiliaryElements
extends Object
    Container class for common parameters used by all DSST forces.

    Most of them are defined in Danielson paper at § 2.1.

    Author:
    Pascal Parraud

    • Constructor Summary

      Constructors 
      Constructor Description
      AuxiliaryElements​(Orbit orbit, int retrogradeFactor)
      Simple constructor.

    • Method Summary

      All Methods Instance Methods Concrete Methods 
      Modifier and Type Method Description
      double getA()
      Get A = sqrt(μ * a).
      double getAlpha()
      Get direction cosine α for central body.
      double getB()
      Get B = sqrt(1 - e²).
      double getBeta()
      Get direction cosine β for central body.
      double getC()
      Get C = 1 + p² + q².
      AbsoluteDate getDate()
      Get the date of the orbit.
      double getEcc()
      Get the eccentricity.
      Frame getFrame()
      Get the definition frame of the orbit.
      double getGamma()
      Get direction cosine γ for central body.
      double getH()
      Get the y component of eccentricity vector.
      double getK()
      Get the x component of eccentricity vector.
      double getKeplerianPeriod()
      Get the Keplerian period.
      double getLf()
      Get the eccentric longitude.
      double getLM()
      Get the mean longitude.
      double getLv()
      Get the true longitude.
      double getMeanMotion()
      Get the Keplerian mean motion.
      double getMu()
      Get the central body attraction coefficient.
      double getP()
      Get the y component of inclination vector.
      double getQ()
      Get the x component of inclination vector.
      int getRetrogradeFactor()
      Get the retrograde factor.
      double getSma()
      Get the semi-major axis.
      org.hipparchus.geometry.euclidean.threed.Vector3D getVectorF()
      Get equinoctial frame vector f.
      org.hipparchus.geometry.euclidean.threed.Vector3D getVectorG()
      Get equinoctial frame vector g.
      org.hipparchus.geometry.euclidean.threed.Vector3D getVectorW()
      Get equinoctial frame vector w.

    • Constructor Detail

      • AuxiliaryElements

        public AuxiliaryElements​(Orbit orbit,
                         int retrogradeFactor)
        Simple constructor.
        Parameters:
        orbit - related mean orbit for auxiliary elements
        retrogradeFactor - retrograde factor I [Eq. 2.1.2-(2)]

    • Method Detail

      • getDate

        public AbsoluteDate getDate()
        Get the date of the orbit.
        Returns:
        the date

      • getFrame

        public Frame getFrame()
        Get the definition frame of the orbit.
        Returns:
        the definition frame

      • getMu

        public double getMu()
        Get the central body attraction coefficient.
        Returns:
        μ

      • getEcc

        public double getEcc()
        Get the eccentricity.
        Returns:
        ecc

      • getMeanMotion

        public double getMeanMotion()
        Get the Keplerian mean motion.
        Returns:
        n

      • getKeplerianPeriod

        public double getKeplerianPeriod()
        Get the Keplerian period.
        Returns:
        period

      • getSma

        public double getSma()
        Get the semi-major axis.
        Returns:
        the semi-major axis a

      • getK

        public double getK()
        Get the x component of eccentricity vector.

        This element called k in DSST corresponds to ex for the EquinoctialOrbit

        Returns:
        k

      • getH

        public double getH()
        Get the y component of eccentricity vector.

        This element called h in DSST corresponds to ey for the EquinoctialOrbit

        Returns:
        h

      • getQ

        public double getQ()
        Get the x component of inclination vector.

        This element called q in DSST corresponds to hx for the EquinoctialOrbit

        Returns:
        q

      • getP

        public double getP()
        Get the y component of inclination vector.

        This element called p in DSST corresponds to hy for the EquinoctialOrbit

        Returns:
        p

      • getLM

        public double getLM()
        Get the mean longitude.
        Returns:
        lm

      • getLv

        public double getLv()
        Get the true longitude.
        Returns:
        lv

      • getLf

        public double getLf()
        Get the eccentric longitude.
        Returns:
        lf

      • getRetrogradeFactor

        public int getRetrogradeFactor()
        Get the retrograde factor.
        Returns:
        the retrograde factor I

      • getA

        public double getA()
        Get A = sqrt(μ * a).
        Returns:
        A

      • getB

        public double getB()
        Get B = sqrt(1 - e²).
        Returns:
        B

      • getC

        public double getC()
        Get C = 1 + p² + q².
        Returns:
        C

      • getVectorF

        public org.hipparchus.geometry.euclidean.threed.Vector3D getVectorF()
        Get equinoctial frame vector f.
        Returns:
        f vector

      • getVectorG

        public org.hipparchus.geometry.euclidean.threed.Vector3D getVectorG()
        Get equinoctial frame vector g.
        Returns:
        g vector

      • getVectorW

        public org.hipparchus.geometry.euclidean.threed.Vector3D getVectorW()
        Get equinoctial frame vector w.
        Returns:
        w vector

      • getAlpha

        public double getAlpha()
        Get direction cosine α for central body.
        Returns:
        α

      • getBeta

        public double getBeta()
        Get direction cosine β for central body.
        Returns:
        β

      • getGamma

        public double getGamma()
        Get direction cosine γ for central body.
        Returns:
        γ