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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    Title :

    Studies on Rocket Engines for Future European Launchers


    Contributors:
    by Etienn (author) / G. Schmidt (author)

    Publication date :

    1984


    Size :

    58 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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