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.


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    Title :

    Lunar vehicle orbit determination


    Additional title:

    ARS J


    Contributors:
    Tross, C. (author)

    Published in:

    ARS Journal ; 32 , n 4 ; p 582-588


    Publication date :

    1962


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Lunar vehicle orbit determination

    Tross, C. | NTRS | 1960


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