Encyclopedia Astronautica
L-5.25H


Notional lox/lh2 rocket engine. 27,350 kN. Study 1963. Isp=410s. Engines for recoverable booster engine package 'half stage' of a 1 1/2 stage arrangement. Used on Nova GD-H launch vehicle.

Separation at 2,980 m/s at 87,800 m altitude; splashdown under 4 46 m diameter parachutes 1,000 km downrange.

Status: Study 1963.
Thrust: 27,350.00 kN (6,148,520 lbf).
Specific impulse: 410 s.
Specific impulse sea level: 350 s.
Burn time: 190 s.

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Associated Countries
See also
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...

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
  • Nova GD-H-0 Lox/LH2 propellant rocket stage. Loaded/empty mass 295,000/295,000 kg. Thrust 109,402.00 kN. Vacuum specific impulse 410 seconds. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. Recoverable booster engine package 'half stage' of a 1 1/2 stage arrangement. Separation at 2,980 m/s at 87,800 m altitude; splashdown under 4 46 m diameter parachutes 1,000 km downrange. More...

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