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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    Titel :

    Lunar vehicle orbit determination


    Weitere Titelangaben:

    ARS J


    Beteiligte:
    Tross, C. (Autor:in)

    Erschienen in:

    ARS Journal ; 32 , n 4


    Erscheinungsdatum :

    1962


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Lunar vehicle orbit determination

    Tross, C. | NTRS | 1960



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