Encyclopedia Astronautica
LE-5


Mitsubishi lox/lh2 rocket engine. 103 kN. Isp=450s. Used on H-1 launch vehicle. First flight 1986.

Engine: 245 kg (540 lb). Chamber Pressure: 36.00 bar. Area Ratio: 140. Thrust to Weight Ratio: 50. Oxidizer to Fuel Ratio: 5.5.

Unfuelled mass: 245 kg (540 lb).
Height: 2.67 m (8.75 ft).
Diameter: 2.49 m (8.16 ft).
Thrust: 103.00 kN (23,155 lbf).
Specific impulse: 450 s.
Burn time: 370 s.
Number: 9 .

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Associated Countries
See also
Associated Launch Vehicles
  • H-1 Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages. 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...

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

Associated Stages
  • LE-5 Lox/LH2 propellant rocket stage. Loaded/empty mass 10,600/1,800 kg. Thrust 102.90 kN. Vacuum specific impulse 450 seconds. More...

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