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.
Reference27 articles.
1. Cook G. E . 1959 T h e aerodynam ic drag o f near earth sa tellites. M in istry of S u pply J
2. Cook G. E . i 960 E ffect o f an o b late ro ta tin g atm osp here on th e orien ta tio n o f a sa tellite orbit. M in istry of A viation report.
3. Cook G. E . & Plim m er R . N . A . i 960 T he effect o f atm ospheric r o ta tio n on th e orb ital plane o f a near earth satellite. Proc. Roy. Soc. A (in th e Press).
4. Proc. Roy;Soc. A,1959
5. Jacchia L. G. 1959 a Nature Lond. 183 526-527.
Cited by
46 articles.
订阅此论文施引文献
订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献