Encyclopedia Astronautica

Pratt and Whitney lox/lh2 rocket engine. 110.8 kN. Design concept 1994. Isp=450s.

Engine: 317 kg (700 lb). Chamber Pressure: 102.00 bar. Area Ratio: 190. Thrust to Weight Ratio: 50. Coefficient of Thrust vacuum: 1.12481904138203.

Status: Design concept 1994.
Unfuelled mass: 317 kg (698 lb).
Diameter: 2.44 m (8.00 ft).
Thrust: 110.80 kN (24,909 lbf).
Specific impulse: 450 s.
Burn time: 630 s.

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Associated Propellants
  • Lox/LH2 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. Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today. More...

Associated Stages
  • Centaur C-X Lox/LH2 propellant rocket stage. Loaded/empty mass 19,138/2,358 kg. Thrust 110.80 kN. Vacuum specific impulse 450 seconds. Conceptual design. Not put into production. More...

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