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LE-5
Part of H-1 Family
Mitsubishi LOx/LH2 propellant rocket stage. Upper stage on the H-1 launch vehicle. First flight 1986. The LE-5A, a simplified, lower cost version, used an expander bleed cycle turbopump.

Status: Retired 1992. Thrust: 102.90 kN (23,133 lbf). Gross mass: 10,600 kg (23,300 lb). Unfuelled mass: 1,800 kg (3,900 lb). Specific impulse: 450 s. Burn time: 370 s. Height: 10.32 m (33.85 ft). Diameter: 2.49 m (8.16 ft). Span: 2.49 m (8.16 ft).

Engine: 245 kg (540 lb). Height: 2.49 m. Chamber Pressure: 36.00 bar. Area Ratio: 140. Thrust to Weight Ratio: 50. Oxidizer to Fuel Ratio: 5.5.

Cost $ : 30.000 million.



Subtopics

LE-5B engine Mitsubishi LOx/LH2 rocket engine. In production. 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.

HIMES LOx/LH2 propellant rocket stage. .

LACE/LE-5 Mitsubishi air augmented Liquid Air/LH2 rocket engine. Design 1999. Used on H-2 HIMES launch vehicle.

HIMES engine Mitsubishi LOx/LH2 rocket engine. Design 1999. Used on H-2 HIMES launch vehicle.

LE-5EC LOx/LH2 propellant rocket stage. .

LACE stage Liquid Air/LH2 propellant rocket stage. .

MB-35 Rocketdyne LOx/LH2 rocket engine. Design 2004. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed.

MB-60 Rocketdyne LOx/LH2 rocket engine. Design 2004. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed.

MB-45 Rocketdyne LOx/LH2 rocket engine. Design 2004. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages, announced February 2000.

LE-5 engine Mitsubishi LOx/LH2 rocket engine. Used on H-1 launch vehicle. First flight 1986.

LE-5A Mitsubishi LOx/LH2 rocket engine. Used on H-2 launch vehicle. First flight 1994.

LE-5B LOx/LH2 propellant rocket stage. Lower cost version of H-2 second stage.

Country: Japan. Engines: LE-5 engine. Launch Vehicles: H-1, H-1 (2), H-1 6R. Propellants: Lox/LH2.

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