Search results
Results from the WOW.Com Content Network
During their two and a half minutes of operation, the five F-1s propelled the Saturn V vehicle to a height of 42 miles (222,000 ft; 68 km) and a speed of 6,164 mph (9,920 km/h). The combined flow rate of the five F-1s in the Saturn V was 3,357 US gal (12,710 L) [5] or 28,415 lb (12,890 kg) per second.
The Saturn family used liquid hydrogen as fuel in the upper stages. Originally proposed as a military satellite launcher, they were adopted as the launch vehicles for the Apollo Moon program . Three versions were built and flown: the medium-lift Saturn I , the heavy-lift Saturn IB , and the super heavy-lift Saturn V .
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 Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio
The S-II (pronounced "S-two") was the second stage of the Saturn V rocket. It was built by North American Aviation. Using liquid hydrogen (LH2) and liquid oxygen (LOX) it had five J-2 engines in a quincunx pattern. The second stage accelerated the Saturn V through the upper atmosphere with 1,000,000 pounds-force (4.4 MN) of thrust.
Apollo 8, Saturn V with 810,700 litres of RP-1 and 1,311,100 liters of LOX in the S-IC first stage [1] RP-1 is a fuel in the first-stage boosters of the Electron, Soyuz, Zenit, Delta I-III, Atlas, Falcon, Antares, and Tronador II rockets. It also powered the first stages of the Energia, Titan I, Saturn I and IB, and Saturn V.
The RS-25 engine consists of pumps, valves, and other components working in concert to produce thrust. Fuel (liquid hydrogen) and oxidizer (liquid oxygen) from the Space Shuttle's external tank entered the orbiter at the umbilical disconnect valves and from there flowed through the orbiter's main propulsion system (MPS) feed lines; whereas in the Space Launch System (SLS), fuel and oxidizer ...
S-IC-T was planned as a test rocket only and not to be used in the later Apollo program. The Saturn V rocket was used in the Apollo program to depart Earth's gravity. 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.