Abstract
This paper considers the restricted two-body problem with atmospheric drag, and its results apply to arcs of orbits in which the tangential speed is much greater than the radial speed. In principle this treatment applies to certain arcs of any near-Keplerian orbit but its usefulness is primarily restricted to near-circular orbits. The atmospheric density is approximated by a model that enables us to derive closed-form solutions for the radial distance of a satellite in orbit that are more accurate than other closed-form solutions found in previous works. However, these new formulas for the orbit do not retain the similarity to those of the two-body problem without drag as much as the previous ones, and require the determination of two additional parameters. Nevertheless, the increase in accuracy is significant.
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