Number of approaches were applied to final satellite decay problem, but only few theories were developed for case of predicting ahead fraction or few revolutions; latter problem is attacked for orbits of small eccentricity taking into account not only reference density but also scale height; by linearization of dynamical equations analytical expressions are developed for perturbation due to drag; being in closed form, expressions can be used in various ways to study influence of small eccentricity and drag on other quantities.
Linearized drag analysis and orbit determination
Progress Astronautics Aeronautics -- Celestial Mechanics Astrodynamics
1964
16 pages
Aufsatz (Zeitschrift)
Englisch
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