Credit: Boeing / Rocketdyne
Rocketdyne Lox/Kerosene rocket engine. 363.2 kN. Atlas D. Atlas Sustainer. Gas generator, pump-fed. Shared turbopumps for booster engines. Isp=309s. First flight 1958.
Application: Atlas D.
Thrust (sl): 252.700 kN (56,809 lbf). Thrust (sl): 25,771 kgf. Engine: 460 kg (1,010 lb). Chamber Pressure: 48.00 bar. Area Ratio: 25. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 80.5173913043478. Coefficient of Thrust vacuum: 1.73727457790893. Coefficient of Thrust sea level: 1.21644124457559.
Diameter: 3.05 m (10.00 ft).
More... - Chronology...
Thrust: 363.20 kN (81,651 lbf).
Specific impulse: 309 s.
Specific impulse sea level: 215 s.
Burn time: 335 s.
First Launch: 1958.
Number: 172 .
Associated Launch Vehicles
Atlas B American test vehicle. First all-up test version of the Atlas ICBM, with jettisonable booster engines and a single engine sustainer on core - a '1 1/2' stage launch vehicle. More...
Atlas C American test vehicle. Last development version of Atlas. Never deployed operationally or used for space launches. More...
Atlas D American intercontinental ballistic missile. Rocket used both as a space launcher and ICBM. More...
Atlas Able American orbital launch vehicle. Atlas with upper stage based on Vanguard second stage. More...
Atlas Agena A American orbital launch vehicle. Atlas D + 1 x Agena A upper stage. Agena originally called 'Hustler', based on engine for cancelled rocket-propelled nuclear warhead pod for B-58 Hustler bomber. 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 Able Lox/Kerosene propellant rocket stage. Loaded/empty mass 114,495/4,200 kg. Thrust 363.22 kN. Vacuum specific impulse 309 seconds. More...
Atlas Agena LV-3A Lox/Kerosene propellant rocket stage. Loaded/empty mass 117,150/2,390 kg. Thrust 363.22 kN. Vacuum specific impulse 309 seconds. More...
Atlas B Lox/Kerosene propellant rocket stage. Loaded/empty mass 107,610/3,980 kg. Thrust 363.22 kN. Vacuum specific impulse 309 seconds. More...
Atlas Centaur LV-3C Lox/Kerosene propellant rocket stage. Loaded/empty mass 117,350/3,700 kg. Thrust 363.22 kN. Vacuum specific impulse 309 seconds. More...
Atlas D Lox/Kerosene propellant rocket stage. Loaded/empty mass 113,050/2,347 kg. Thrust 363.22 kN. Vacuum specific impulse 309 seconds. More...
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