LE-9
| Country of origin | Japan |
|---|---|
| Designer | JAXA |
| Manufacturer | Mitsubishi Heavy Industries |
| Application | sustainer engine |
| Associated L/V | H3 Launch Vehicle |
| Predecessor | LE-7A |
| 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.) | 1,471 kN (331,000 lbf) |
| Thrust-to-weight ratio | 62.50 |
| Chamber pressure | 10.0 MPa (1,450 psi) |
| Isp (vac.) | 426 s (4.18 km/s) |
| Dimensions | |
| Length | 3.8 m |
| Dry weight | 2.4 t (5,300 lb) |
| Used in | |
| H3 Launch Vehicle core stage. | |
| References | |
| References | |
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.
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Wikipedia