This work investigates end-of-life trajectories for spacecraft in orbit about the sun-Earth L1 and L2 libration points. A decommission plan is often required during the mission design process. The spacecraft's natural departure dynamics are studied in both the circular restricted three-body problem and an ephemeris model. In particular, the roles of the unstable manifold and forbidden regions in determining disposal outcomes are considered. A close correspondence is observed between the models when computing the probabilities of return to the Earth neighborhood. A simple maneuver scheme, which uses regions partitioned by the zero-velocity surfaces to prevent returns to the Earth vicinity, is also analyzed. Disposal maneuver costs less than 50 m/s are possible for many initial libration point orbits during a decommissioning phase lasting less than one year.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Dynamic Mechanisms for Spacecraft Disposal from Sun-Earth Libration Points




    Erscheinungsdatum :

    2015




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    55.54 Flugführung
    Lokalklassifikation TIB:    770/7040



    Dynamic Mechanisms for Spacecraft Disposal from Sun–Earth Libration Points

    Olikara, Zubin P. / Gómez, Gerard / Masdemont, Josep J. | AIAA | 2015


    Spacecraft Formation Flight About Libration Points

    Carlson, Brian / Pernicka, Henry / Balakrishnan, S.N. | AIAA | 2004




    Earth-Moon Triangular Libration Point Spacecraft Formations

    Kathryn Catlin / Craig McLaughlin | AIAA | 2007