Encyclopedia Astronautica

Mitsubishi lox/lh2 rocket engine for H-2 upper stage. 1078 kN. Staged combustion turbopump. No throttle capability. Isp=446s. First flight 1994.

Thrust (sl): 843.500 kN (189,626 lbf). Thrust (sl): 86,018 kgf. Engine: 1,714 kg (3,778 lb). Chamber Pressure: 127.00 bar. Area Ratio: 52. Thrust to Weight Ratio: 64.1338435000121. Oxidizer to Fuel Ratio: 5.9. Coefficient of Thrust vacuum: 1.73739021790307. Coefficient of Thrust sea level: 1.32200560251845.

Unfuelled mass: 1,714 kg (3,778 lb).
Height: 3.40 m (11.10 ft).
Diameter: 4.00 m (13.10 ft).
Thrust: 1,078.00 kN (242,344 lbf).
Specific impulse: 446 s.
Specific impulse sea level: 349 s.
Burn time: 346 s.
Number: 7 .

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Associated Countries
See also
Associated Launch Vehicles
  • H-2 Heavy lift Japanese indigenous launch vehicle. The original H-2 version was cancelled due to high costs and poor reliability and replaced by the substantially redesigned H-2A. More...
  • H-2 HIMES Japanese orbital launch vehicle. Concept of H-2 augmented with Liquid-Air Cycle Engine boosters and advanced HIMES upper stage. More...

Associated Manufacturers and Agencies
  • Mitsubishi Japanese manufacturer of rockets, spacecraft, and rocket engines. Mitsubishi Electric Corp, Japan. 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...

  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.

Associated Stages
  • H-2-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 98,100/11,900 kg. Thrust 1,078.00 kN. Vacuum specific impulse 446 seconds. More...

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