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Abstract
The effect of air drag on satellite orbits of small eccentricity e (< 0.2) is studied analytically by a perturbation method, on the assumption that the atmosphere is spherically symmetrical. Equations are derived which show (1) how perigee distance and orbital period vary with eccentricity as the orbit contracts, and (2) how each of these quantities varies with time. The equations of type (1) are nearly independent of the oblateness of the atmosphere. In all the equations, terms of order e 4 and higher are usually neglected. The results are also presented graphically, in a manner designed for practical use. The theory will be extended to an oblate atmosphere in part II, and will later be compared with observation.
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Schedule a callMore From: Proceedings of the Royal Society of London. Series A. Mathematical and Physical Sciences
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