Encyclopedia Astronautica

Mitsubishi lox/lh2 rocket engine. 1098 kN. In production. Isp=438s. Improved model of the original LE-7 for the first stage of the H-II rocket with a two stage combustion cycle system. First flight 2001.

The LE-7A rocket engine, developed for the first stage of the H-II rocket, had a two stage combustion cycle system, and was an improved model of the original LE-7 engine. The improvements were made as a result of the severe competition in the artificial satellite business worldwide, and the resulting need to lower the cost of the H-II vehicle for the H-IIA model. The changes were targeted to increase the reliability, improve the operability, and decrease the cost for the first stage engine for the H-IIA rocket. The result was a simplified, lower cost version of LE-7 with a staged combustion turbopump that could be throttled to 72% of rated thrust.

Engine: 1,800 kg (3,900 lb). Chamber Pressure: 121.00 bar. Area Ratio: 51.9. Oxidizer to Fuel Ratio: 5.9.

Status: In production.
Unfuelled mass: 1,800 kg (3,900 lb).
Height: 3.67 m (12.04 ft).
Thrust: 1,098.00 kN (246,840 lbf).
Specific impulse: 438 s.
Specific impulse sea level: 338 s.
Burn time: 390 s.
First Launch: 1995-2001.
Number: 10 .

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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...

Associated Stages
  • H-2A LRB Lox/LH2 propellant rocket stage. Loaded/empty mass 117,000/17,800 kg. Thrust 2,196.00 kN. Vacuum specific impulse 440 seconds. Two-engine version of H-2A-1 used as strap-on booster. More...
  • H-2A-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 113,600/13,600 kg. Thrust 1,098.00 kN. Vacuum specific impulse 440 seconds. Lower cost version of H-2 first stage. Can be throttled to 72% thrust. More...

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