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LE-7
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 | LE-7
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Designer: Mitsubishi. Propellants: Lox/LH2. Thrust(vac): 1,078.000 kN (242,344 lbf). Thrust(sl): 843.500 kN (189,626 lbf). Isp: 446 sec. Isp (sea level): 349 sec. Burn time: 346 sec. Mass Engine: 1,714 kg (3,778 lb). Diameter: 4.00 m (13.10 ft). Length: 3.40 m (11.10 ft). Chambers: 1. Chamber Pressure: 127.00 bar. Area Ratio: 52.00. Oxidizer to Fuel Ratio: 5.90. Thrust to Weight Ratio: 64.13. Country: Japan. First Flight: 1994. Last Flight: 1999. Flown: 7.00. Staged combustion turbopump. No throttle capability.
LE-7 used on Rocket Stages - Used on stage: H-2-1. on launch vehicle: H-2.
Bibliography and Further Reading - Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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