LE-9

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. 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.
  2. 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.
  3. ↑ 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.
  4. ↑ "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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