Notional lox/lh2 rocket engine. 23,928 kN. Study 1966. Isp=459s. Used on Pegasus VTOVL launch vehicle.
Thrust (sl): 18,714.800 kN (4,207,254 lbf). Thrust (sl): 1,908,410 kgf.
Status: Study 1966.
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Thrust: 23,928.00 kN (5,379,228 lbf).
Specific impulse: 459 s.
Specific impulse sea level: 359 s.
Burn time: 232 s.
Associated Launch Vehicles
Pegasus VTOVL American SSTO VTOVL orbital launch vehicle. Bono design for semi-single-stage-to-orbit ballistic VTOVL launch vehicle. Drop tanks were shed on the way to orbit. Pegasus could deliver either a Satun V-size payload to LEO or 172 passengers and their luggage the 12,000 km from Vandenberg to Singapore in 39 minutes. 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...
Pegasus VTOVL Lox/LH2 propellant rocket stage. Loaded/empty mass 1,250,000/148,000 kg. Thrust 23,947.00 kN. Vacuum specific impulse 459 seconds. Empty mass includes 29,600 kg of propellants used for re-entry cooling of plug nozzle and rocket soft landing at landing field. More...
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