LE-7
Type: Lower Stage Engine
Country of Origin: Japan
Manufacturer: Mitsubishi Heavy Industries
First Flight: February 3, 1994
Status: Retired
Propellant (O/F): Liquid Oxygen/Liquid Hydrogen
Mixture Ratio (O/F by mass): 5.9
Cycle: Staged Combustion
Chambers: 1
Thrust (vac.): 1078 kN; 1098 kN (LE-7A)
Thrust (s.l.): 843.5 kN; 870 kN (LE-7A)
Throttle: 72% to 100%
ISP (vac.): 446 s; 440 s (LE-7A)
ISP (s.l.): 349 s; 338 s (LE-7A)
Chamber Pressure: 1840 psi; 1740 psi (LE-7A)
Nozzle Ratio: 52:1
Burn time:
Ignitions: 1
Mass: 1714 kg
Length: 3.4 m
Diameter:
Used in: H-IIA (LE-7), H-IIB (LE-7A)
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