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The Saturn V-3 was studied by the NASA Marshall Space Flight Center in 1965. [ 2 ] The first stage, called MS-IC-1, was to have used new F-1 engines designated F-1A which utilized a pump-fed design, an anticipated 20% additional thrust, and a six-second improvement in specific impulse on an F-1, with the first stage stretched 20 feet.
The streamlined design is due to the reduced parts visible above the engine nozzles. Raptor 2 is a complete redesign of the Raptor 1 engine. [79] The turbomachinery, chamber, nozzle, and electronics were all redesigned. Many flanges were converted to welds, while other parts were deleted. [80] Simplifications continued after production began.
The J-2, commonly known as Rocketdyne J-2, was a liquid-fuel cryogenic rocket engine used on NASA's Saturn IB and Saturn V launch vehicles. Built in the United States by Rocketdyne, the J-2 burned cryogenic liquid hydrogen (LH 2) and liquid oxygen (LOX) propellants, with each engine producing 1,033.1 kN (232,250 lb f) of thrust in vacuum.
Engine Origin Designer Vehicle Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [e] Oxidiser: fuel ratio ...
After the United Auto Workers ratified a new contract in March 2004, the plant became part of General Motors, but Saturn-only manufacturing lines continued until March 2007. The facility includes a four-cylinder engine assembly plant, auto assembly plant, paint and plastics plant, a Saturn parts warehouse, and a visitors center.
The reduction in parts costs is aided by using selective laser melting in the production of some metallic parts. [ 13 ] [ 18 ] The resulting F-1B engine is intended to produce 1,800,000 lbf (8.0 MN) of thrust at sea level, a 15% increase over the approximate 1,550,000 lbf (6.9 MN) of thrust that the mature Apollo 15 F-1 engines produced.