Most powerful engine in Saturn V launch vehicle is first stage F-1, developed by Rocket-dyne Div of North American Aviation; it is rated at 1,500,000 lb of thrust at sea level and operates at chamber pressure of 1000 psi, has maximum diameter of 12 ft and weighs about 18,000 lb; LOX and kerosene is used as propellants; turbopump is single-unit design with both pumps and turbine mounted on single shaft, which eliminates gearing; two significant achievements in over-coming problem of random combustion instability are discussed and propulsion requirements for rocket engines of future are examined. Extracts of paper before Royal Aeronautical Soc, London, Apr 14 1966.


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    Titel :

    Spacecraft propulsion -- Present and future


    Weitere Titelangaben:

    Flight


    Beteiligte:
    Hoffman, S.K. (Autor:in)

    Erschienen in:

    Flight ; 89 , n 2981


    Erscheinungsdatum :

    1966


    Format / Umfang :

    2 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Future spacecraft propulsion

    GARRISON, P. W. / STOCKY, J. F. | AIAA | 1988


    Future spacecraft propulsion

    Garrison, P. W. / Stocky, J. F. | NTRS | 1988



    Spacecraft Propulsion: Future Needs and Challenges

    Berry, W. | British Library Conference Proceedings | 1997