Encyclopedia Astronautica

Notional lox/lh2 rocket engine. 1280 kN. Study 1985. Isp=490s. Used on Sanger II launch vehicle.

Thrust (sl): 1,068.400 kN (240,186 lbf). Thrust (sl): 108,948 kgf. Chamber Pressure: 282.00 bar.

Status: Study 1985.
Thrust: 1,280.00 kN (287,750 lbf).
Specific impulse: 490 s.
Specific impulse sea level: 409 s.
Burn time: 298 s.

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Associated Countries
See also
Associated Launch Vehicles
  • Saenger II Proposed two stage to orbit vehicle. Air-breathing hypersonic first stage and delta wing second stage. The German Hypersonics Programme and its Saenger II reference vehicle received most of the domestic funding for spaceplane development in the late 1980s and early 1990s. 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
  • Sanger II-2 Lox/LH2 propellant rocket stage. Loaded/empty mass 112,000/32,600 kg. Thrust 1,280.00 kN. Vacuum specific impulse 490 seconds. 6000 kg to LEO More...

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