Abstract Atmospheric perturbations of the elements of the artificial satellites orbits are determined using a special model of distribution and variations of the total density of the upper atmosphere between 200–500 km. The model includes diurnal and semi-annual density variations, variations with solar activity and geomagnetic index and latitudinal changes. The height profile is expressed by multiple exponential functions. The equations of motion are solved analytically.


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    Titel :

    Determination of orbital drag perturbations caused by atmospheric effects


    Beteiligte:
    Sehnal, L. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.01.1986


    Format / Umfang :

    6 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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