F-1
F-1 engine
Credit - © Mark Wade
Manufacturer Name: F-1. Designer: Rocketdyne. Developed in: 1959. Propellants: Lox/Kerosene. Thrust(vac): 7,740.500 kN (1,740,134 lbf). Thrust(sl): 6,747.500 kN (1,516,898 lbf). Isp: 304 sec. Isp (sea level): 265 sec. Burn time: 161 sec. Mass Engine: 8,391 kg (18,498 lb). Diameter: 3.72 m (12.20 ft). Length: 5.64 m (18.50 ft). Chambers: 1. Chamber Pressure: 70.00 bar. Area Ratio: 16.00. Oxidizer to Fuel Ratio: 2.27. Thrust to Weight Ratio: 94.07. Country: USA. First Flight: 1967. Last Flight: 1973. Flown: 65.

Used in Saturn IC. The largest liquid engine rocket motor ever developed, it represented an incredible order-of-magnitude development from the 150,000 lb thrust class motor developed for Navaho, Jupiter, Thor, Atlas, Titan I, and Saturn I. Severe combustion stability problems were solved during development and it never failed in flight. Proposed for use on Nova NASA-1; Nova A-1; Nova NASA-2; Jarvis-1; Nova B-1; Nova 59-4-2; Saturn MLV 5-23L-0; Saturn S-IB-2; Nova 59-4-1; Nova 60-8-1; Saturn S-ID; Saturn S-IB-4. Saturn V S-1C Stage. Designed for booster applications. Gas generator, pump-fed.


F-1 used on Rocket Stages


Bibliography and Further Reading
  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
 
 
 
 
 
 
 
 
 

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