A space launcher that is recoverable was studied. Possible configurations were investigated and dimensioning parameters were identified. Analysis centered on design of a two-stage vehicle in a winged or ballistic configuration. The launch vehicle mission was defined as injection into low Earth orbit of a 10,000 kg payload. Results concern choice of propulsion system as well as ascent and descent trajectories (including implications for thermal protection).


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Future Launching Systems


    Beteiligte:
    M. Villain (Autor:in)

    Erscheinungsdatum :

    1981


    Format / Umfang :

    71 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Launching Systems-

    Kozlov, D. / Novikov, V. / Smirnov, I. et al. | British Library Conference Proceedings | 1998



    Launching the Future of Science and Exploration

    Shivers, Charles H. | NTRS | 2009



    LAUNCHING DEVICE AND LAUNCHING METHOD

    KIN HIROAKI / TAKAHASHI MASAMI / ISHIKAWA RYO et al. | Europäisches Patentamt | 2022

    Freier Zugriff