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The F-1 is a rocket engine developed by Rocketdyne.The engine uses a gas-generator cycle developed in the United States in the late 1950s and was used in the Saturn V rocket in the 1960s and early 1970s.
The F-1B is to have better specific impulse and be cheaper than the F-1, with a simplified combustion chamber and fewer engine parts, while producing 1,800,000 lbf (8.0 MN) of thrust at sea level, an increase over the approximate 1,550,000 lbf (6.9 MN) achieved by the mature Apollo 15 F-1 engine, [104]
Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio
S-IC-T, like all following Saturn V's S-IC rockets used five Rocketdyne F-1 engines. The Rocketdyne F-1 engine was first tested in March 1959 and delivered to NASA in October 1963. S-IC-T was built starting in 1963 and complete in 1965. The S-IC-T tests were to verify that the S-IC stage could support the firing of all five Rocketdyne F-1 ...
F-1 rocket engine used in the Saturn program, Rocketdyne former main production facility, Canoga Park, Los Angeles. After World War II, North American Aviation (NAA) was contracted by the Defense Department to study the German V-2 missile and adapt its engine to Society of Automotive Engineers (SAE) measurements and U.S. construction details.
The Air Force had recently expressed an interest in such an engine, which would develop into the famed F-1, but at the time they were aiming for 1,000,000 lbf (4,400 kN) and the engines would not be ready until the mid-1960s. The engine-cluster appeared to be the only way to meet the requirements on time and budget.
The S-IC (pronounced S-one-C [3] [4]) was the first stage of the American Saturn V rocket. The S-IC stage was manufactured by the Boeing Company. Like the first stages of most rockets, more than 90% of the mass at launch was propellant, in this case RP-1 rocket fuel and liquid oxygen (LOX) oxidizer.
Rocketdyne F-1 (RP-1/LOX) – The main engine of the first stage of the Saturn V rocket used in the Apollo program. The most powerful single combustion chamber liquid-propellant rocket engine ever developed. [34] Rocketdyne J-2 (LH 2 /LOX) – Used on the upper stage of the Saturn IB and second and upper stages of Saturn V.