Encyclopedia Astronautica

Mitsubishi lox/lh2 rocket engine. 137 kN. In production. Isp=447s. Improved model of the LE-5A for second stage of the H-II rocket; used hydrogen for the cooling of the thrust chamber, then as the gas to drive the turbine. First flight 2001.

The result was a simplified, lower cost version of the LE-5A using an expander bleed cycle turbopump. The engine could be throttled to 5% idle mode.

Engine: 269 kg (593 lb). Chamber Pressure: 36.00 bar. Area Ratio: 110. Oxidizer to Fuel Ratio: 5.

Status: In production.
Unfuelled mass: 269 kg (593 lb).
Height: 2.78 m (9.13 ft).
Thrust: 137.00 kN (30,798 lbf).
Specific impulse: 447 s.
Burn time: 534 s.
First Launch: 1995-2001.
Number: 10 .

More... - Chronology...

Associated Countries
See also
Associated Launch Vehicles
  • H-2A 212 Japanese orbital launch vehicle. This version uses two core stages side-by-side in an asymmetric configuration, supplemented by two SRB-A solid rocket boosters. More...
  • H-IIA 2024 Japanese orbital launch vehicle. Three stage vehicle consisting of 4 x Castor 4XL + 2 x H-II SRB-A boosters + two-stage core vehicle. 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
  • LE-5B Lox/LH2 propellant rocket stage. Loaded/empty mass 19,600/3,000 kg. Thrust 137.00 kN. Vacuum specific impulse 447 seconds. Lower cost version of H-2 second stage. More...

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