From Wikipedia, the free encyclopedia
Japanese hydrolox expander rocket engine
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
H3 launch vehicle.
[1]
[2]
[5]
The newly developed LE-9 engine is the most important factor in achieving cost reduction, improved safety and increased thrust. The
expander bleed cycle used in the LE-9 engine is a highly reliable combustion method that Japan has put into practical use for the
LE-5A /
B engine. However, it is physically difficult for an expander bleed cycle engine to generate large thrust, so the development of the LE-9 engine with a thrust of 1,471 kN (331,000 lbf ) is the most challenging and important development element.
[6]
Firing tests of the LE-9 first-stage engine began in April 2017.
[7]
On 21 January 2022, the launch of the first H3 was rescheduled to
FY 2022 or later, citing technical problems regarding the first stage LE-9 engine.
[8]
The LE-9 was operated successfully for the first time, on March 7, 2023. The second stage of that rocket, did not ignite and the mission was a failure.
[9] On February 17, 2024, the second launch of H3 was successful and LE-9 operations were successful for the second consecutive time.
[10]
See also
References
^
a
b Atsumi, Masahiro; Yoshikawa, Kimito; Ogawara, Akira; Onga, Tadaoki (December 2011).
"Development of the LE-X Engine" (PDF) . MHI Technical Review . 48 (4): 36–43. Archived from
the original (PDF) on 2015-12-24. Retrieved 2015-07-08 .
^
a
b 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).
doi :
10.2514/6.2010-6853 .
ISBN
978-1-60086-958-7 .
S2CID
110462567 . Archived from
the original (PDF) on 2015-06-12. 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).
doi :
10.2514/6.2011-5930 .
ISBN
978-1-60086-949-5 . Archived from
the original (PDF) on 2015-06-10. Retrieved 2015-07-08 .
^ Daiki, Watanabe; Manako, Hiroyasu; Onga, Tadaoki; Tamura, Takashi; Ikeda, Kazufumi; Isono, Mitsunori (December 2016).
"Combustion Stability Improvement of LE-9 Engine for Booster Stage of H3 Launch Vehicle" (PDF) . MHI Technical Review . 53 (4): 28–35. Archived from
the original (PDF) on 2018-03-03. Retrieved 2017-06-29 .
^
"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 .
^ Shinya Torishima (24 September 2020).
"H3ロケット開発を襲った"魔物"とは?、エンジンに見つかった技術的課題" (in Japanese). Mynavi news. Archived from
the original on 1 October 2020.
^
LE-9 燃焼試験 (in Japanese). JAXA. Archived from
the original on 1 March 2020. Retrieved 21 January 2020 .
^
"H3ロケットの試験機1号機の打上げについて" (in Japanese). JAXA. January 21, 2022. Retrieved January 21, 2022 .
^
"Japan's new H3 rocket fails to reach orbit, self-destruct command issued ;Spacedaily" .
^
打ち上げ成功 前回の失敗乗り越える.
NHK . 17 February 2024
External links
Liquid fuel
Cryogenic
Hydrolox (
LH2 /
LOX )
China
Europe
India
Japan
Russia
USA
Methalox (
CH4 /
LOX )
Semi- cryogenic
Kerolox (
RP-1 /
LOX )
China
India
Russia
NK-15
NK-33, 44
RD-58
RD-0105, 0109
RD-0107, 0108, 0110
RD-0110R
RD-0124
RD-107, 108, 117, 118
RD-120
RD-170, 171
RD-180
RD-191, 151, 181
RD-193
S1.5400
Spain
Ukraine
USA
Storable
Hypergolic (
Aerozine ,
UH 25 ,
MMH , or
UDMH /
N2 O4 ,
MON , or
HNO3 )
China
Europe
India
Israel
North Korea
Russia
17D61
RD-0202 to 0206, 0208 to 0213
RD-0207, 0214
RD-0216, 0217, 0235
RD-0233, 0234
RD-0236
RD-0237
RD-0243 to 0245
RD-0255 to 0257
RD-215 to 219
RD-250 to 252, 261, 262
RD-253, 275
RD-263, 268, 273
RD-270
S5.92
S5.98M
Ukraine
USA
Other
Solid fuel
China
Europe
India
Iran
Israel
Japan
USA
* Different versions of the engine use different propellant combinations
Engines in italics are under development