Encyclopedia Astronautica

Lox/LH2 propellant rocket stage. Loaded/empty mass 5,352,400/317,400 kg. Thrust 71,171.70 kN. Vacuum specific impulse 455 seconds. Boeing study, 1969.

No Engines: 12.

Status: Study 1969.
Gross mass: 5,352,400 kg (11,800,000 lb).
Unfuelled mass: 317,400 kg (699,700 lb).
Height: 78.63 m (257.97 ft).
Diameter: 21.86 m (71.71 ft).
Span: 21.86 m (71.71 ft).
Thrust: 71,171.70 kN (16,000,035 lbf).
Specific impulse: 455 s.
Specific impulse sea level: 367 s.
Burn time: 310 s.

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Associated Countries
Associated Engines
  • CD Module Notional lox/lh2 rocket engine. 7361 kN. Study 1969. Isp=420s. CD Modules - conceptual engines of various thrusts, according to design - were clustered in Martin Marietta Nova designs More...

Associated Launch Vehicles
  • MLLV American SSTO VTOVL orbital launch vehicle. Boeing study, 1969, for Saturn follow-on. Plug nozzle, single-stage-to-orbit launch vehicle could itself put 1 million pounds payload into orbit. By addition of up to 12 260 inch solid motors up to 3.5 million pounds payload into orbit with a single launch. 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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