Package org.orekit.files.ccsds.ndm.odm.ocm

Enum Class OrbitElementsType

java.lang.Object
java.lang.Enum<OrbitElementsType>
org.orekit.files.ccsds.ndm.odm.ocm.OrbitElementsType
All Implemented Interfaces:
Serializable, Comparable<OrbitElementsType>, Constable
public enum OrbitElementsType extends Enum<OrbitElementsType>
Orbit element set type used in CCSDS Orbit Comprehensive Messages.
Since:
11.0
Author:
Luc Maisonobe
See Also:

  • Enum Constant Details

    • ADBARV

      public static final OrbitElementsType ADBARV
      Spherical 6-element set (α,δ,β,A,r,v).

    • CARTP

      public static final OrbitElementsType CARTP
      Cartesian 3-element position (X, Y, Z).

    • CARTPV

      public static final OrbitElementsType CARTPV
      Cartesian 6-element position and velocity (X, Y, Z, XD, YD, ZD).

    • CARTPVA

      public static final OrbitElementsType CARTPVA
      Cartesian 9-element position, velocity and acceleration (X, Y, Z, XD, YD, ZD, XDD, YDD, ZDD).

    • DELAUNAY

      public static final OrbitElementsType DELAUNAY
      Delaunay elements (L, G, H, l, g, h).

    • DELAUNAYMOD

      public static final OrbitElementsType DELAUNAYMOD
      Modified Delaunay elements (Lm, Gm, Hm, lm, gm, hm).

    • EIGVAL3EIGVEC3

      public static final OrbitElementsType EIGVAL3EIGVEC3
      12 elements eigenvalue/eigenvectors (EigMaj, EigMed, EigMin, EigVecMaj, EigVecMed, EigVecMin).

    • EQUINOCTIAL

      public static final OrbitElementsType EQUINOCTIAL
      Equinoctial elements (a, af, ag, L=M+ω+frΩ, χ, ψ, fr).

    • EQUINOCTIALMOD

      public static final OrbitElementsType EQUINOCTIALMOD
      Modified equinoctial elements (p=a(1−e²), af, ag, L'=υ+ω+frΩ, χ, ψ, fr).

    • GEODETIC

      public static final OrbitElementsType GEODETIC
      Geodetic elements (λ, ΦGD, β, A, h, vre).

    • KEPLERIAN

      public static final OrbitElementsType KEPLERIAN
      Keplerian 6-element classical set (a, e, i, Ω, ω, ν).

    • KEPLERIANMEAN

      public static final OrbitElementsType KEPLERIANMEAN
      Keplerian 6-element classical set (a, e, i, Ω, ω, M).

    • LDBARV

      public static final OrbitElementsType LDBARV
      Modified spherical 6-element set (λ, δ, β, A, r, v).

    • ONSTATION

      public static final OrbitElementsType ONSTATION
      Geosynchronous on-station tailored set (a, ex, ey, ix, iy, λ).

    • POINCARE

      public static final OrbitElementsType POINCARE
      Canonical counterpart of equinoctial 6-element set (λM=M+ω+Ω, gp, hp, Lp, Gp, Hp).

  • Method Details

    • values

      public static OrbitElementsType[] values()
      Returns an array containing the constants of this enum class, in the order they are declared.
      Returns:
      an array containing the constants of this enum class, in the order they are declared

    • valueOf

      public static OrbitElementsType valueOf(String name)
      Returns the enum constant of this class with the specified name. The string must match exactly an identifier used to declare an enum constant in this class. (Extraneous whitespace characters are not permitted.)
      Parameters:
      name - the name of the enum constant to be returned.
      Returns:
      the enum constant with the specified name
      Throws:
      IllegalArgumentException - if this enum class has no constant with the specified name
      NullPointerException - if the argument is null

    • getUnits

      public List<Unit> getUnits()
      Get the elements units.
      Returns:
      elements units

    • toCartesian

      public TimeStampedPVCoordinates toCartesian(AbsoluteDate date, double[] elements, OneAxisEllipsoid body, double mu)
      Convert to Cartesian coordinates.
      Parameters:
      date - elements date
      elements - elements values in SI units
      body - central body (may be null if type is not GEODETIC)
      mu - gravitational parameter in m³/s²
      Returns:
      Cartesian coordinates

    • toRawElements

      public double[] toRawElements(TimeStampedPVCoordinates pv, Frame frame, OneAxisEllipsoid body, double mu)
      Convert to raw elements array.
      Parameters:
      pv - Cartesian coordinates
      frame - inertial frame where elements are defined
      body - central body (may be null if type is not GEODETIC)
      mu - gravitational parameter in m³/s²
      Returns:
      elements elements values in SI units
      Since:
      12.0

    • toString

      public String toString()
      Overrides:
      toString in class Enum<OrbitElementsType>