Problem of ascent or descent from initially Keplerian orbit by constant low thrust is investigated by two-variable expansion procedure; slowly varying elements of Keplerian orbit are explicitly computed, and simple integral relating eccentricity and semimajor axis is derived and used to justify omission of higher order terms in eccentricity for ascent from almost circular initial orbits; present higher order theory that is valid for arbitrary initial eccentricities is shown to contain earlier results for circular starting orbits and gives simple explicit formulas for solution at small eccentricities.
Ascent or descent from satellite orbit by low thrust
AIAA J
AIAA Journal ; 4 , n 12
1966
7 pages
Article (Journal)
English
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