LE-7 |
Number: 7 . Thrust: 1,078.00 kN (242,344 lbf). Unfuelled mass: 1,714 kg (3,778 lb). Specific impulse: 446 s. Specific impulse sea level: 349 s. Burn time: 346 s. Height: 3.40 m (11.10 ft). Diameter: 4.00 m (13.10 ft).
Thrust (sl): 843.500 kN (189,626 lbf). Thrust (sl): 86,018 kgf. Engine: 1,714 kg (3,778 lb). Chamber Pressure: 127.00 bar. Area Ratio: 52. Thrust to Weight Ratio: 64.1338435000121. Oxidizer to Fuel Ratio: 5.9. Coefficient of Thrust vacuum: 1.73739021790307. Coefficient of Thrust sea level: 1.32200560251845.
LE-7A Mitsubishi LOx/LH2 rocket engine. In production. 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. |