| アイテムタイプ |
itemtype_ver1(1) |
| 公開日 |
2024-10-21 |
| タイトル |
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|
タイトル |
Nitrous Oxide/Ethanol Cylindrical Rotating Detonation Engine for Sounding Rocket Space Flight |
|
言語 |
en |
| 著者 |
Ishihara, Kazuki
Sato, Tomoki
Kimura, Tomoaki
Nakajima, Kosuke
Nakata, Kotaro
Itouyama, Noboru
Kawasaki, Akira
Matsuoka, Ken
Matsuyama, Koichi
Kasahara, Jiro
Eguchi, Hikaru
Nakata, Daisuke
Uchiumi, Masaharu
Matsuo, Akiko
Funaki, Ikkoh
|
| アクセス権 |
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|
アクセス権 |
open access |
|
アクセス権URI |
http://purl.org/coar/access_right/c_abf2 |
| 内容記述 |
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|
内容記述タイプ |
Abstract |
|
内容記述 |
There are few experimental studies on rotating detonation engines (RDEs) with liquid propellants. This study reveals the static thrust performance of a cylindrical RDE with ethanol and liquid nitrous oxide as propellants under atmospheric pressure. This RDE had an inner diameter of 40 mm, a maximum combustor length of 230 mm, a nozzle contraction ratio of 1.7, and a nozzle expansion ratio of 9.1. Nineteen experiments were conducted at total mass flow rates of 184–210 g/s, mixture ratios of 3.6–5.9, and combustion pressures of 0.35–0.46 MPa, resulting in a maximum detonation velocity of 1840 m/s (approximately 80% of the theoretical detonation velocity, 2251 m/s), maximum thrust at sea level of 294 N, and maximum specific impulse at sea level of 148 s. In addition, the maximum characteristic exhaust velocity, 𝑐*, was 1716 m/s, which was 99% of the theoretical value. The characteristic length of the combustion chamber at this time was 0.15 m. Since conventional rocket combustion requires 1.57 m to achieve the same 𝑐* efficiency, this study shows that detonation combustion can reduce the combustor size by 88%. |
|
言語 |
en |
| 内容記述 |
|
|
内容記述タイプ |
Other |
|
内容記述 |
Published Online:28 May 2024 |
|
言語 |
en |
| 出版者 |
|
|
出版者 |
American Institute of Aeronautics and Astronautics |
|
言語 |
en |
| 言語 |
|
|
言語 |
eng |
| 資源タイプ |
|
|
資源タイプresource |
http://purl.org/coar/resource_type/c_6501 |
|
タイプ |
journal article |
| 出版タイプ |
|
|
出版タイプ |
AM |
|
出版タイプResource |
http://purl.org/coar/version/c_ab4af688f83e57aa |
| 関連情報 |
|
|
関連タイプ |
isVersionOf |
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|
識別子タイプ |
DOI |
|
|
関連識別子 |
https://doi.org/10.2514/1.A35824 |
| 収録物識別子 |
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|
収録物識別子タイプ |
PISSN |
|
収録物識別子 |
0022-4650 |
| 書誌情報 |
en : Journal of Spacecraft and Rockets
巻 62,
号 1,
p. 44-54,
発行日 2025-01
|
JSR2023-07-A35824_R1_Revised_Edition_EN_r02_forRepository.pdf (1.6 MB)
