Credit: Boeing / Rocketdyne
Rocketdyne Lox/Kerosene rocket engine. 947.7 kN. Saturn l/lB. Designed for booster applications. Gas generator, pump-fed. Isp=289s. First flight 1961.
Thrust (sl): 836.200 kN (187,985 lbf). Thrust (sl): 85,275 kgf. Engine: 635 kg (1,399 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 152.196850393701. Oxidizer to Fuel Ratio: 2.23. Coefficient of Thrust vacuum: 1.74073055260789. Coefficient of Thrust sea level: 1.54073055260789.
Unfuelled mass: 635 kg (1,399 lb).
More... - Chronology...
Height: 2.13 m (6.98 ft).
Diameter: 0.82 m (2.67 ft).
Thrust: 947.70 kN (213,051 lbf).
Specific impulse: 289 s.
Specific impulse sea level: 255 s.
Burn time: 150 s.
First Launch: 1958.
Number: 80 .
Associated Launch Vehicles
Juno V-A American orbital launch vehicle. By 1958 the Super-Jupiter was called Juno V and the 4 E-1 engines were abandoned in favor of clustering 8 Jupiter IRBM engines below existing Redstone/Jupiter tankage. The A version had a Titan I ICBM as the upper stages. Masses, payload estimated. More...
Juno V-B American orbital launch vehicle. A proposed version of the Juno V for lunar and planetary missions used a Titan I ICBM first stage and a Centaur high-energy third stage atop the basic Juno V cluster. Masses, payload estimated. More...
Saturn A-1 American orbital launch vehicle. Projected first version of Saturn I, to be used if necessary before S-IV liquid hydrogen second stage became available. Titan 1 first stage used as second stage, Centaur third stage. Masses, payload estimated. More...
Saturn C-2 American orbital launch vehicle. The launch vehicle initially considered for realizing the Apollo lunar landing at the earliest possible date. 15 launches and rendezvous required to assemble direct landing spacecraft in earth orbit. More...
Saturn I American orbital launch vehicle. Von Braun launch vehicle known as 'Cluster's Last Stand' - 8 Redstone tanks around a Jupiter tank core,powered by eight Jupiter engines. Originally intended as the launch vehicle for Apollo manned circumlunar flights. However it was developed so early, no payloads were available for it. More...
Associated Manufacturers and Agencies
Lox/Kerosene Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...
Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
Saturn I Lox/Kerosene propellant rocket stage. Loaded/empty mass 432,681/45,267 kg. Thrust 7,582.10 kN. Vacuum specific impulse 289 seconds. Configuration as flown, Saturn I. More...
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