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.
Spacecraft propulsion -- Present and future
Flight
Flight ; 89 , n 2981
1966
2 pages
Article (Journal)
English
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