A LOX-hydrocarbon engine for the propulsion of a reusable launcher first stage was defined and commonality with the HM60 was analyzed. Engines presented are: LOX-CH4, LOX-C3H8, LOX-UDMH, and LOX-RP1. Engine performances and cooling analysis are summarized. Results suggest that the LOX-methane combination is the most promising.


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    Titel :

    Studies on Rocket Engines for Future European Launchers


    Beteiligte:
    by Etienn (Autor:in) / G. Schmidt (Autor:in)

    Erscheinungsdatum :

    1984


    Format / Umfang :

    58 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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