Abstract
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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Dedicated to V. Szebehely on the occasion of his 60th birthday
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Roth, E.A. Construction of a consistent semianalytic theory of a planetary or moon orbiter perturbed by a third body. Celestial Mechanics 28, 155–169 (1982). https://doi.org/10.1007/BF01230668
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DOI: https://doi.org/10.1007/BF01230668