Lox/LH2 propellant rocket stage. Loaded/empty mass 8,526,000/172,000 kg. Thrust 30,685.00 kN. Vacuum specific impulse 428 seconds.
Status: Study 1963.
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Gross mass: 8,526,000 kg (18,796,000 lb).
Unfuelled mass: 172,000 kg (379,000 lb).
Height: 73.80 m (242.10 ft).
Diameter: 25.90 m (84.90 ft).
Span: 25.90 m (84.90 ft).
Thrust: 30,685.00 kN (6,898,262 lbf).
Specific impulse: 428 s.
Specific impulse sea level: 310 s.
Burn time: 500 s.
L-5.00H Notional lox/lh2 rocket engine. 30,684 kN. Study 1963. Isp=428s. Used on Nova GD-H launch vehicle. More...
Associated Launch Vehicles
Nova GD-H American heavy-lift orbital launch vehicle. General Dynamics Nova design using 1 1/2 stage arrangement and new 2.4 million kgf Lox/LH2 engines. Recoverable booster 4 engine package would separate at 2,980 m/s at 87,800 m altitude; splashdown under 4 46 m diameter parachutes 1,000 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. More...
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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