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

---

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.

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.

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.