Notional lox/lh2 rocket engine. 101,988 kN. Study 1964. Isp=459s. Used on Rombus launch vehicle.
Thrust (sl): 79,768.100 kN (17,932,582 lbf). Thrust (sl): 8,134,205 kgf.
Status: Study 1964.
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Thrust: 101,988.00 kN (22,927,814 lbf).
Specific impulse: 459 s.
Specific impulse sea level: 359 s.
Burn time: 215 s.
Associated Launch Vehicles
Rombus American SSTO VTOVL orbital launch vehicle. Bono original design for ballistic single-stage-to-orbit (not quite - it dropped liquid hydrogen tanks on the way up) heavy lift launch vehicle. The recoverable vehicle would re-enter, using its actively-cooled plug nozzle as a heat shield. 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...
Rombus Lox/LH2 propellant rocket stage. Loaded/empty mass 5,102,041/306,175 kg. Thrust 101,900.00 kN. Vacuum specific impulse 455 seconds. 36 x plug-nozzle engines (20 atm chamber pressure, 7:1 mixture ratio) More...
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