The method of osculating parameters is used to obtain the integral orbit restrictedness condition around the colinear libration center in the restricted elliptical three body problem. It is shown that, if a restricted orbit exists, it can be found by solving the equations of spacecraft motion under the above mentioned conditions.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Limitation of Spacecraft Orbit Near Colinear Libration Center of Limited Elliptical Three Body Problem (Abstract Only)


    Beteiligte:
    P. Y. Elyasberg (Autor:in) / T. A. Timokhova (Autor:in)

    Erscheinungsdatum :

    1987


    Format / Umfang :

    1 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch