| Item type |
学術雑誌論文 / Journal Article.(1) |
| 公開日 |
2019-06-26 |
| 書誌情報 |
en : Journal of Propulsion and Power
巻 35,
号 1,
p. 213-223,
発行日 2019-01
|
| タイトル |
|
|
タイトル |
Propulsive Performance and Heating Environment of Rotating Detonation Engine with Various Nozzles |
|
言語 |
en |
| 言語 |
|
|
言語 |
eng |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
|
資源タイプ |
journal article |
| アクセス権 |
|
|
アクセス権 |
open access |
|
アクセス権URI |
http://purl.org/coar/access_right/c_abf2 |
| 著者 |
後藤, 啓介
西村, 純平
川崎, 央
松岡, 健
笠原, 次郎
松尾, 亜紀子
船木, 一幸
中田, 大将
内海, 政春
東野, 和幸
|
| 室蘭工業大学研究者データベースへのリンク |
|
|
表示名 |
中田 大将(NAKATA Daisuke) |
|
URL |
http://rdsoran.muroran-it.ac.jp/html/100000232_ja.html |
| 室蘭工業大学研究者データベースへのリンク |
|
|
表示名 |
内海 政春(UCHIUMI Masaharu) |
|
URL |
http://rdsoran.muroran-it.ac.jp/html/200000040_ja.html |
| 抄録 |
|
|
内容記述タイプ |
Abstract |
|
内容記述 |
Geometric throats are commonly applied to rocket combustors to increase pressure and specific impulse. This paper presents the results from thrust measurements of an ethylene/gas-oxygen rotating detonation engine with various throat geometries in a vacuum chamber to simulate varied backpressure conditions in a range of 1.1–104 kPa. For the throatless case, the detonation channel area was regarded to be equivalent the throat area, and three throat-contraction ratios were tested: 1, 2.5, and 8. Results revealed that combustor pressure was approximately proportional to equivalent throat mass flux for all test cases. Specific impulse was measured for a wide range of pressure ratios, defined as the ratio of the combustor pressure to the backpressure in the vacuum chamber. The rotating detonation engine could achieve almost the same level of optimum specific impulse for each backpressure, whether or not flow was squeezed by a geometric throat. In addition, heat-flux measurements using heat-resistant material are summarized. Temporally and spatially averaged heat flux in the engine were roughly proportional to channel mass flux. Heat-resistant material wall compatibility with two injector shapes of doublet and triplet injection is also discussed. |
|
言語 |
en |
| 出版者 |
|
|
出版者 |
American Institute of Aeronautics and Astronautics (AIAA) |
|
言語 |
en |
| 出版者版へのリンク |
|
|
表示名 |
10.2514/1.B37196 |
|
URL |
https://doi.org/10.2514/1.B37196 |
| DOI |
|
|
関連タイプ |
isVersionOf |
|
|
識別子タイプ |
DOI |
|
|
関連識別子 |
10.2514/1.B37196 |
| 日本十進分類法 |
|
|
主題Scheme |
NDC |
|
主題 |
538 |
| ISSN |
|
|
収録物識別子タイプ |
PISSN |
|
収録物識別子 |
0748-4658 |
| 権利 |
|
|
言語 |
en |
|
権利情報 |
© 2019 American Institute of Aeronautics and Astronautics (AIAA) |
| 参考URL |
|
|
|
識別子タイプ |
URI |
|
|
関連識別子 |
https://arc.aiaa.org/ |
|
|
言語 |
en |
|
|
関連名称 |
AIAA Aerospace Research Central |
| 著者版フラグ |
|
|
出版タイプ |
AM |
|
出版タイプResource |
http://purl.org/coar/version/c_ab4af688f83e57aa |
| フォーマット |
|
|
内容記述タイプ |
Other |
|
内容記述 |
application/pdf |
JPP_35_1_213_223 (1.3 MB)
