The launch of a spacecraft into the stable, high polar orbits of a Moon artificial satellite is considered. These orbits can be used to construct a lunar multifunctional satellite system, as well as a near-Moon orbital spaceport. Analysis and comparison of three schemes of direct spacecraft transfer from the Earth to the Moon—with a one-, two-. and three-impulse maneuver of transition into the final orbit—are performed. In particular, the energy, geometrical, and temporal characteristics of a two-impulse transfer obtained under significant influence of gravitational perturbations are compared with their one- and three-impulse analogues.


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    Titel :

    Analysis of Trajectories of Spacecraft Launching into High Circular Orbits of the Moon Artificial Satellite


    Weitere Titelangaben:

    Cosmic Res


    Beteiligte:
    Gordienko, E. S. (Autor:in) / Ivashkin, V. V. (Autor:in) / Simonov, A. V. (Autor:in) / Rozin, P. E. (Autor:in)

    Erschienen in:

    Cosmic Research ; 60 , 3 ; 202-212


    Erscheinungsdatum :

    2022-06-01


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch