Celestial mechanics

, Volume 36, Issue 4, pp 409–419 | Cite as

A set modified equinoctial orbit elements

  • M. J. H. Walker
  • B. Ireland
  • Joyce Owens


Modified equinoctial elements are introduced which are suitable for perturbation analysis of all kinds of orbit. Equations of motion in Lagrangian and Gaussian forms are derived. Identities connecting the partial derivatives of the disturbing function with respect to equinoctial elements are established. Numerical comparisons of the evolution of a perturbed, highly eccentric, elliptic orbit analysed in equinoctial elements and by Cowell's method show satisfactory agreement.


Partial Derivative Method Show Satisfactory Agreement Orbit Element Perturbation Analysis 
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  1. Broucke, R.A. and Cefola, P.J.: 1972,Celes. Mech. 5, 303–310.Google Scholar
  2. Cefola, P.J.: 1972,Equinoctial Orbit Elements-Application to Artificial Satellite Orbits, AIAA preprint 72-937.Google Scholar
  3. Cohen, C.J. and Hubbard, E.C.: 1962,Astron. Journal 67 (1), 10–15.Google Scholar
  4. Cornelisse, J.W., Shöyer, H.F.R., and Wakker, K.F.: 1979,Rocket Propulsion and Spacecraft Dynamics, Pitman.Google Scholar
  5. Giacaglia, G.E.O.: 1977,Celes. Mech. 15, 191–215.Google Scholar
  6. Kaula, W.M.: 1966,Theory of Satellite Geodesy, Blaisdell.Google Scholar
  7. Roth, E.A.: 1970,ZAMP 30 (2), 315–325.Google Scholar

Copyright information

© D. Reidel Publishing Company 1985

Authors and Affiliations

  • M. J. H. Walker
    • 1
  • B. Ireland
    • 2
  • Joyce Owens
    • 3
  1. 1.Marconi Space SystemsPortsmouthUK
  2. 2.University of BathBathUK
  3. 3.Marconi Space SystemsPortsmouthUK

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