Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
LE-5 engine
Mitsubishi LOx/LH2 rocket engine. Used on H-1 launch vehicle. First flight 1986.

AKA: LE-5. Number: 9 . Thrust: 103.00 kN (23,155 lbf). Unfuelled mass: 245 kg (540 lb). Specific impulse: 450 s. Burn time: 370 s. Height: 2.67 m (8.75 ft). Diameter: 2.49 m (8.16 ft).

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



Subtopics

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

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

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

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

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.

Country: Japan. Launch Vehicles: H-1. Propellants: Lox/LH2. Stages: LE-5. Agency: Mitsubishi. Bibliography: 225.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2017 Mark Wade - Contact
© / Conditions for Use