Construction of a consistent semianalytic theory of a planetary or moon orbiter perturbed by a third body

Details Construction of a consistent semianalytic theory of a planetary or moon orbiter perturbed by a third body Construction of a consistent semianalytic theory of a planetary or moon orbiter perturbed by a third body

Oct 1982

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1982cemec..28..155r&link_type=abstract

(Conference on Mathematical Methods in Celestial Mechanics, 7th, Oberwolfach, West Germany, Aug. 24-28, 1981.) Celestial Mechani

Mathematics

1

Lunar Orbiter, Orbit Perturbation, Perturbation Theory, Planetary Orbits, Three Body Problem, Approximation, Disturbing Functions, Euler-Lagrange Equation, Orbital Elements, Satellite Orbits

Scientific paper

The third body perturbation of an orbiter of a planet or moon is considered. A very convenient form of the Lagrange equations is given allowing an easy derivation of the various terms of the expansion of the perturbed elements. A careful analysis of the order of magnitude of these terms indicates which ones are required for a consistent theory. It follows that in many practical cases the main term of the disturbing function has to be carried to the second order of the perturbation theory.

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