LE-9
| 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
- 1 2 Atsumi, Masahiro; Yoshikawa, Kimito; Ogawara, Akira; Onga, Tadaoki (December 2011). "Development of the LE-X Engine" (pdf). MHI Technical Review. 48 (4): 36–43. Retrieved 2015-07-08.
- 1 2 Kumada, Nobuhiko; Ogawara, Akira; Manako, Hiroyasu; Onga, Tadaoki; Sunakawa, Hideo; Kurosu, Akihide; Iizuka, Nobuyuki; Noda, Keiichiro; Okita, Koichi (2010-07-26). "Highly Reliable Design Approaches for Next Booster Engine LE-X" (pdf). 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 46 (AIAA 2010-6853). Retrieved 2015-07-08.
- ↑ Watanabe, Daiki; Imai, Kazuhiro; Ogawara, Akira; Yamanishi, Nobuhiro; Neghishi, Hideyo; Kawatsu, Kaname; Kurosu, Akihide; Noda, Keiichiro (2011-07-31). "Application of High Fidelity Simulation to LE-X Engine Development" (pdf). 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 47 (AIAA 2011-5930). Retrieved 2015-07-08.
- ↑ "2020年：H3ロケットの目指す姿" [2020: H3 projected debut date] (pdf) (in Japanese). JAXA. 2015-07-08. Retrieved 2015-07-08.
External links
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