Credit: Boeing / Rocketdyne
Rocketdyne Lox/Kerosene rocket engine. 822.5 kN. Atlas E, F. Designed for booster applications. Gas generator, pump-fed. Separate turbopumps for each booster engine. Isp=290s. First flight 1960.
Application: Atlas E, F.
Thrust (sl): 726.000 kN (163,211 lbf). Thrust (sl): 74,037 kgf. Engine: 720 kg (1,580 lb). Chamber Pressure: 41.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 116.486111111111. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.42466495026104. Coefficient of Thrust sea level: 1.22954299904152.
Height: 3.40 m (11.10 ft).
More... - Chronology...
Diameter: 1.53 m (5.00 ft).
Thrust: 822.50 kN (184,905 lbf).
Specific impulse: 290 s.
Specific impulse sea level: 256 s.
Burn time: 120 s.
First Launch: 1958.
Number: 504 .
Ames Mach 10 Demonstrator American manned spaceplane. Study 1957. Ames proposed in 1957 to air-launch a high-wing designed hypersonic glider from a B-36 bomber. Early versions would use an XLR-99-powered booster stage and be capable of reaching Mach 6. More...
Associated Launch Vehicles
Saturn B-1 American orbital launch vehicle. Most powerful version of Saturn I considered. New low energy second stage with four H-1 engines, S-IV third stage, Centaur fourth stage. Masses, payload estimated. More...
Atlas E American intercontinental ballistic missile. Initial fully operational version of Atlas ICBM. Differed in guidance system from Atlas F. Deployed as missiles from 1960 to 1966. After retirement, the ICBM's were refurbished and used over twenty years as space launch vehicles. More...
Atlas Agena B American orbital launch vehicle. Atlas D with improved, enlarged Agena upper stage. More...
Atlas F American intercontinental ballistic missile. Final operational version of Atlas ICBM. Differed in guidance systems. Deployed as missiles from 1961 to 1966. After retirement, the ICBM's were refurbished and used for over thirty years as space launch vehicles. More...
Atlas Agena D American orbital launch vehicle. Atlas D with further improved and lightened Agena upper stage. More...
Atlas SLV-3 American orbital launch vehicle. Standardized Atlas booster with no or small solid upper stage. 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...
Atlas MA-3 Lox/Kerosene propellant rocket stage. Loaded/empty mass 3,174/3,174 kg. Thrust 1,644.96 kN. Vacuum specific impulse 290 seconds. More...
Titan Cluster Lox/Kerosene propellant rocket stage. Loaded/empty mass 150,000/10,000 kg. Thrust 2,940.00 kN. Vacuum specific impulse 130 seconds. Masses estimated (cluster of four Titan I first stages) More...
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