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Engine Model: LE-5. Designer: Mitsubishi. Propellants: Lox/LH2. Thrust(vac): 103.000 kN (23,155 lbf). Isp: 450 sec. Burn time: 370 sec. Mass Engine: 245 kg (540 lb). Diameter: 2.49 m (8.16 ft). Length: 2.67 m (8.75 ft). Chambers: 1. Chamber Pressure: 36.00 bar. Area Ratio: 140.00. Oxidizer to Fuel Ratio: 5.50. Thrust to Weight Ratio: 50.00. Country: Japan. First Flight: 1986. Last Flight: 1992. Flown: 9.00.

Engine Model: LE-5A. Other Designations: LE-5EC. Designer: Mitsubishi. Propellants: Lox/LH2. Thrust(vac): 121.500 kN (27,314 lbf). Isp: 452 sec. Burn time: 609 sec. Mass Engine: 242 kg (533 lb). Diameter: 4.00 m (13.10 ft). Length: 2.67 m (8.75 ft). Chambers: 1. Chamber Pressure: 40.00 bar. Area Ratio: 130.00. Oxidizer to Fuel Ratio: 5.00. Thrust to Weight Ratio: 51.20. Country: Japan. First Flight: 1994. Last Flight: 1999. Flown: 7.00.

Engine Model: LE-5B. Designer: Mitsubishi. Developed in: 1995-2001. Propellants: Lox/LH2. Thrust(vac): 137.000 kN (30,798 lbf). Isp: 447 sec. Burn time: 534 sec. Mass Engine: 269 kg (593 lb). Length: 2.78 m (9.13 ft). Chambers: 1. Chamber Pressure: 36.00 bar. Area Ratio: 110.00. Oxidizer to Fuel Ratio: 5.00. Country: Japan. Status: In production. First Flight: 2001. Last Flight: 2006. Flown: 10.

The LE-5B rocket engine, developed for the second stage of the H-II rocket, was an improved model of the LE-5A. It used hydrogen for the cooling of the thrust chamber, then as the gas to drive the turbine. 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.

LE-5 used on Rocket Stages
  • Used on stage: H-2. on launch vehicle: H-2.
Bibliography:

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