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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    Title :

    Spacecraft propulsion -- Present and future


    Additional title:

    Flight


    Contributors:

    Published in:

    Flight ; 89 , n 2981


    Publication date :

    1966


    Size :

    2 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


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