LE-5A
Type: Upper 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
Cycle: Expander Bleed
Chambers: 1
Thrust (vac.): 121.5 kN
Thrust (s.l.):
Throttle: Fixed
ISP (vac.): 452 s
ISP (s.l.):
Chamber Pressure: 577 psi (39.8 bar)
Nozzle Ratio: 130:1
Burn time:
Ignitions:
Mass: 248 kg
Length: 2.69 m
Diameter:
Used in: H-II
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