Highly efficient special perturbation procedure for lunar vehicle ephemeris prediction is developed; Encke's method is employed by means of which it is possible to calculate ephemeris for ballistic Earth-moon trajectory with only 15 integration steps and to maintain precision everywhere along orbit to within 1/2 mi, while considering pertinent perturbation effects such as terrestrial bulge, sun and moon attraction, and atmosphere drag.
Lunar vehicle orbit determination
ARS J
ARS Journal ; 32 , n 4 ; p 582-588
1962
7 pages
Article (Journal)
English
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Lunar vehicle orbit determination
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