Encyclopedia Astronautica
Atlas G/H/I


Lox/Kerosene propellant rocket stage. Loaded/empty mass 142,536/4,236 kg. Thrust 386.30 kN. Vacuum specific impulse 316 seconds.

Cost $ : 50.000 million.

Status: Out of production.
Gross mass: 142,536 kg (314,238 lb).
Unfuelled mass: 4,236 kg (9,338 lb).
Height: 22.20 m (72.80 ft).
Diameter: 3.05 m (10.00 ft).
Span: 4.90 m (16.00 ft).
Thrust: 386.30 kN (86,844 lbf).
Specific impulse: 316 s.
Specific impulse sea level: 220 s.
Burn time: 266 s.
Number: 42 .

More... - Chronology...


Associated Countries
Associated Engines
  • LR105-7 Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Atlas space launchers. Out of production. Atlas Sustainer. Gas generator, pump-fed. Evolved from MA-2 ICBM system. Isp=316s. First flight 1963. More...

Associated Launch Vehicles
  • Atlas H American orbital launch vehicle. Atlas H used the Atlas first stage developed for the Atlas G vehicle. It was flown without the Centaur upper stage. More...
  • Atlas I American orbital launch vehicle. The Atlas I launch vehicle was derived from the Atlas G, and included the same basic vehicle components (Atlas booster and Centaur upper stage). Significant improvements in the guidance and control system were made with an emphasis on replacing analog flight control components with digital units interconnected with a digital data bus. More...

Associated Propellants
  • 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...

Home - Browse - Contact
© / Conditions for Use