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Study on Acoustic Prediction and Reduction of Epsilon Launch Vehicle at Liftoff
https://jaxa.repo.nii.ac.jp/records/22518
https://jaxa.repo.nii.ac.jp/records/2251853ffcd7c-c7d3-4e8a-96bb-171fa5df7648
名前 / ファイル | ライセンス | アクション |
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PA1510016000.pdf (3.2 MB)
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Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2015-05-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Study on Acoustic Prediction and Reduction of Epsilon Launch Vehicle at Liftoff | |||||
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 | |||||
著者 |
Tsutsumi, Seiji
× Tsutsumi, Seiji× Ishii, Tatsuya× Ui, Kyouichi× Tokudome, Shinichiro× Wada, K |
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著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Science Service, Inc. | ||||||
出版者(英) | ||||||
出版者 | American Institute of Aeronautics and Astronautics (AIAA) | |||||
書誌情報 |
en : Journal of Spacecraft and Rockets 巻 52, 号 2, p. 350-361, 発行日 2015-03 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Subscale model tests and a numerical investigation are performed to predict and attenuate the acoustic level of the Epsilon launch vehicle at liftoff. Requirements for the subscale model test to predict a full-scale acoustic environment are investigated, and then the scale size of the model test is set at 1/42. The launch pads employed herein are designed to attenuate reflection of the Mach wave radiated from the free jet and the acoustic wave due to the jet’s impinging on the flame deflector. When comparing the acoustic result taken at the fairing location with that at three different altitudes, 9D(sub e),14D(sub e), and 22D(sub e), where D(sub e)represents the nozzle exit diameter, the acoustic level observed at 14D(sub e)is the highest and exceeds the design requirement at all frequencies. It is revealed from the numerical analysis that the reflection of Mach waves radiating from the free jet within the flame path is the dominant acoustic source. A front cover is attached to the vertical flame path to shield the Mach wave radiation, and 3 dB attenuation in the overall sound pressure level is achieved. The design methods and the knowledge obtained in this study are valid for the design of the launch pad to attenuate liftoff acoustics. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0022-4650 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA00707776 | |||||
DOI | ||||||
関連タイプ | isVersionOf | |||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.2514/1.A33010 | |||||
関連名称 | info:doi/10.2514/1.A33010 | |||||
権利 | ||||||
権利情報 | (C)2015 American Institute of Aeronautics and Astronautics | |||||
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 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: PA1510016000 |