Encyclopedia Astronautica

Lox/LH2 propellant rocket stage. Loaded/empty mass 10,898,000/608,000 kg. Thrust 165,447.00 kN. Vacuum specific impulse 410 seconds.

No Engines: 4.

Status: Study 1963.
Gross mass: 10,898,000 kg (24,025,000 lb).
Unfuelled mass: 608,000 kg (1,340,000 lb).
Height: 106.70 m (350.00 ft).
Diameter: 21.30 m (69.80 ft).
Span: 21.30 m (69.80 ft).
Thrust: 165,447.00 kN (37,193,965 lbf).
Specific impulse: 410 s.
Specific impulse sea level: 345 s.
Burn time: 246 s.

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Associated Countries
Associated Engines
  • 5 mlbf Notional lox/lh2 rocket engine. 41,361 kN. OOST, ROOST studies 1963. Isp=410s. First flight 1977. More...

Associated Launch Vehicles
  • ROOST American SSTO orbital launch vehicle. Bono's first design for a reusable single stage to orbit LH2/Lox booster, using conventional engines. More...

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...

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