Zobrazeno 1 - 10 of 156 pro vyhledávání: '"Masaharu UCHIUMI"'
1
Akademický článek
Overspeeding characteristics of turbomachinery for gas generator cycle air turbo ramjet engine
Autor: Ryojiro Minato, Daisuke Nakata, Masaharu Uchiumi, Ryoji Imai, Kazuyuki Higashino
Publikováno v: Propulsion and Power Research, Vol 11, Iss 4, Pp 444-456 (2022)
The main interest in the current study focuses on the possibility of overspeeding for the gas-generator cycle air turbo ramjet (GG-ATR) engine. The authors developed the air turbo ramjet engine and investigated its compressor performance. Based on th
Externí odkaz: https://doaj.org/article/c740cd31959b43dbad89050c7235d035
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2
Akademický článek
Morphological design considering layout and permutation of the components for rocket turbopump
Autor: Satoshi KAWASAKI, Mitsuru SHIMAGAKI, Masaharu UCHIUMI, Kazuhiko ADACHI
Publikováno v: Nihon Kikai Gakkai ronbunshu, Vol 82, Iss 842, Pp 16-00134-16-00134 (2016)
The rocket engine turbopump is the high-rotational speed and high-power turbomachinery to feed the propellant from the tank to the combustion chamber. Lateral vibration of turbopump rotor is a very serious problem and it has brought about the unplann
Externí odkaz: https://doaj.org/article/ade2192c64584a058be266bbd3eecbf7
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3
Akademický článek
One-dimensional multidomain analysis of rotating cavitation
Autor: Takashi SHIMURA, Satoshi KAWASAKI, Masaharu UCHIUMI
Publikováno v: Nihon Kikai Gakkai ronbunshu, Vol 81, Iss 829, Pp 15-00125-15-00125 (2015)
A method to analyze pump dynamic characteristics by cavitation compliance, mass-flow gain factor and dynamic gain was evolved to analyze rotating cavitation, using one-dimensional multi-domain system analysis software. This analysis method was used t
Externí odkaz: https://doaj.org/article/7208a7c8045c4573ac652520a906196c
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4
Space Flight Demonstration of Rotating Detonation Engine Using Sounding Rocket S-520-31
Autor: Keisuke Goto, Ken Matsuoka, Koichi Matsuyama, Akira Kawasaki, Hiroaki Watanabe, Noboru Itouyama, Kazuki Ishihara, Valentin Buyakofu, Tomoyuki Noda, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki, Daisuke Nakata, Masaharu Uchiumi, Hiroto Habu, Shinsuke Takeuchi, Satoshi Arakawa, Junichi Masuda, Kenji Maehara, Tatsuro Nakao, Kazuhiko Yamada
Publikováno v: Journal of Spacecraft and Rockets. 60:273-285
To create a new flyable detonation propulsion system, a detonation engine system (DES) that can be stowed in sounding rocket S-520-31 has been developed. This paper focused on the first flight demonstration in the space environment of a DES-integrate
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::aaf525ad2eda24688794d2af7015e1cf
https://doi.org/10.2514/1.a35401
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5
Flight Demonstration of Pulse Detonation Engine Using Sounding Rocket S-520-31 in Space
Autor: Valentin Buyakofu, Ken Matsuoka, Koichi Matsuyama, Akira Kawasaki, Hiroaki Watanabe, Noboru Itouyama, Keisuke Goto, Kazuki Ishihara, Tomoyuki Noda, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki, Daisuke Nakata, Masaharu Uchiumi, Hiroto Habu, Shinsuke Takeuchi, Satoshi Arakawa, Junichi Masuda, Kenji Maehara, Tatsuro Nakao, Kazuhiko Yamada
Publikováno v: Journal of Spacecraft and Rockets. 60:181-189
A detonation engine system is successfully demonstrated for the first time in space using sounding rocket S-520-31 of the Japan Aerospace Exploration Agency/Institute of Space Astronautical Science. Detailed flight results of an S-shaped pulse detona
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::922a3ef21999266da51e354450c00177
https://doi.org/10.2514/1.a35394
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