LE-9
From Infogalactic: the planetary knowledge core
Country of origin | Japan |
---|---|
Designer | JAXA |
Manufacturer | Mitsubishi Heavy Industries |
Application | sustainer engine |
Associated L/V | H3 Launch Vehicle |
Predecessor | LE-7 |
Status | In Development |
Liquid-fuel engine | |
Propellant | liquid oxygen / liquid hydrogen |
Mixture ratio | 5.9 |
Cycle | Expander Bleed cycle |
Configuration | |
Chamber | 1 |
Nozzle ratio | 37 |
Performance | |
Thrust (vac.) | 1,448 kilonewtons (326,000 lbf) |
Chamber pressure | 12.4 megapascals (1,800 psi) |
Isp (vac.) | 432 s (4.24 km/s) |
Used in | |
H3 Launch Vehicle core stage. | |
References | |
References | [1][2][3] |
The LE-9 is a liquid cryogenic rocket engine burning liquid hydrogen and liquid oxygen in an expander bleed cycle. Two or three will be used to power the core stage of the H-3 launch vehicle.[1][2][4]
See also
References
External links
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