Lox/Kerosene propellant rocket stage. Loaded/empty mass 3,050/3,050 kg. Thrust 1,517.42 kN. Vacuum specific impulse 282 seconds.
No Engines: 2.
Status: Out of production.
More... - Chronology...
Gross mass: 3,050 kg (6,720 lb).
Unfuelled mass: 3,050 kg (6,720 lb).
Diameter: 4.90 m (16.00 ft).
Span: 4.90 m (16.00 ft).
Thrust: 1,517.42 kN (341,130 lbf).
Specific impulse: 282 s.
Specific impulse sea level: 248 s.
Burn time: 135 s.
Number: 275 .
XLR89-5 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Atlas D. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Isp=282s. First flight 1958. More...
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 C Able American orbital launch vehicle. Version with Atlas C first stage, Able AJ10-101A second stage, Altair solid third stage. More...
Atlas Able American orbital launch vehicle. Atlas with upper stage based on Vanguard second stage. More...
Atlas D Able American orbital launch vehicle. Version with Atlas D first stage, Able AJ10-101A second stage, Altair solid third 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...
Atlas Centaur American orbital launch vehicle. First test version of Atlas with Centaur upper stage. More...
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...
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