| Item type |
紀要論文 / Departmental Bulletin Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
ATREXエンジンの燃焼試験による地上システム実証 |
| 言語 |
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言語 |
jpn |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
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資源タイプ |
departmental bulletin paper |
| その他のタイトル（英） |
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その他のタイトル |
Development Study of the ATREX Engine System by Ground Firing Tests |
| 著者 |
佐藤, 哲也
棚次, 亘弘
小林, 弘明
成尾, 芳博
Sato, Tetsuya
Tanatsugu, Nobuhiro
Kobayashi, Hiroaki
Naruo, Yoshihiro
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| 著者所属 |
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宇宙科学研究所 |
| 著者所属 |
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宇宙科学研究所 |
| 著者所属 |
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宇宙科学研究所 |
| 著者所属 |
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宇宙科学研究所 |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science (ISAS) |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science (ISAS) |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science (ISAS) |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science (ISAS) |
| 出版者 |
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出版者 |
宇宙科学研究所 |
| 出版者（英） |
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出版者 |
Institute of Space and Astronautical Science |
| 書誌情報 |
宇宙科学研究所報告. 特集: ATREXエンジンの研究開発
巻 46,
p. 63-80,
発行日 2003-03
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
The present paper addresses the development study of the air turbo ramjet engine with expander cycle (ATREX) being conducted since 1986 in the Institute of Space and Astronautical Science in cooperation with the industries (IHI, KHI, MHI and SHI). The ATREX is expected as one of the most promising candidates for the propulsion system of a future space plane. The ATREX is the combined cycle engine performing like a turbojet at lower flight speed and a fan-boosted ramjet at higher flight speed beyond Mach 3 to 6. The 1/4-scaled model of ATREX whose fan inlet diameter of 300mm was built for system verification under sea level static conditions. Carious components such as turbo-fan, precooler, mixer, regeneratively cooled combustor and heat exchanger as well as the expander cycle have been developed and verified in the firing test. Number of 63 tests with 3,300 sec of the total duration have been conducted step by step since 1990 at Noshiro Testing Center of ISAS. The recent study focused on the precooler. The latest model (Type-III) was designed taking into consideration the reduction of size and weight as well as the heat-dynamic performance aiming at the flight model/ Engine performance is improved such that the Thrust and specific impulse are increased 1.8 and 1.2 times respectively by reducing the fan inlet temperature to 180K. The heat exchange performance of precooler was 80-90 % of the design value and the large pressure losses of the air flow occurred due to the frost formation on the tube surfaces. This frost formation phenomenon has been made clear analytically and experimentally and several methods eliminating it have been devised and tested. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0285-9920 |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
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収録物識別子 |
AN00354485 |
| 資料番号 |
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内容記述タイプ |
Other |
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内容記述 |
資料番号: SA0200115000 |
SA0200115.pdf (1.6 MB)
