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How NASA brought the monstrous F-1 “moon rocket” engine back to life; New F-1B rocket engine upgrades Apollo-era design with 1.8M lbs of thrust; MSFC History office F-1 Fact sheet; Anthony Young Collection, The University of Alabama in Huntsville Archives and Special Collections Research material on the development of the F-1 engine.
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
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 F1 Rocket is a tandem two-seat low-wing cantilever monoplane built mainly in aluminum. [1] The Rocket has a titanium fixed conventional landing gear with a tailwheel. . Designed to be built with a range of nose-mounted engines between 235 and 350 hp (175 and 224 kW) the prototype has a Lycoming IO-540 with a three-bladed propelle
'Rocket Engine-180') is a rocket engine that was designed and built in Russia. It features a dual combustion chamber, dual-nozzle design and is fueled by a RP-1/LOX mixture. The RD-180 is derived from the RD-170 line of rocket engines, which were used in the Soviet Energia launch vehicle.
RS-68 being tested at NASA's Stennis Space Center Viking 5C rocket engine used on Ariane 1 through Ariane 4. A rocket engine is a reaction engine, producing thrust in accordance with Newton's third law by ejecting reaction mass rearward, usually a high-speed jet of high-temperature gas produced by the combustion of rocket propellants stored inside the rocket.
The bell-shaped or contour nozzle is probably the most commonly used shaped rocket engine nozzle. It has a high angle expansion section (20 to 50 degrees) right behind the nozzle throat; this is followed by a gradual reversal of nozzle contour slope so that at the nozzle exit the divergence angle is small, usually less than a 10 degree half angle.
Merlin 1 is a family of LOX/RP-1 rocket engines developed 2003–2012. Merlin 1A and Merlin 1B utilized an ablatively-cooled carbon-fiber composite nozzle. Merlin 1A produced 340 kilonewtons (76,000 lb f) of thrust and was used to power the first stage of the first two Falcon 1 flights in 2006 and 2007.