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Numerical Analysis of Ignition Overpressure Effect on H-IIB Launch Vehicle
https://jaxa.repo.nii.ac.jp/records/22374
https://jaxa.repo.nii.ac.jp/records/223747f21bcf4-5708-422d-817d-07eb6be7c11c
名前 / ファイル | ライセンス | アクション |
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PA1410005.pdf (2.3 MB)
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Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Numerical Analysis of Ignition Overpressure Effect on H-IIB Launch Vehicle | |||||
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 |
堤, 誠司
× 堤, 誠司× 高木, 亮治× 原, 利顕× 上田, 広幸× 長田, 弘幸× Tsutsumi, Seiji× Takaki, Ryoji× Hara, Toshiaki× Ueda, Hiroyuki× Nagata, Hiroyuki |
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著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(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 | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
出版者(英) | ||||||
出版者 | American Institute of Aeronautics and Astronautics | |||||
書誌情報 |
en : Journal of Spacecraft and Rockets 発行日 2014-02 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A numerical simulation was conducted to investigate the ignition overpressure mechanism generated by theJapanese H-IIB launch vehicle. A simplified benchmark problem and analysis of a free jet exhausted from a singlesolid booster were used to verify the present numerical method; the unsteady Reynolds-averaged Navier-Stokessimulation was found to be essential for determining the typical features of ignition overpressure, such as the shockwave generated in front of the plume and following starting vortex. Comparing with the measured pressure history atthe launch complex, the numerical result agreed reasonably. The correlation between the wave pattern measured atthe launch complex and the ignition overpressure mechanism was clarified. The effect of ignition overpressure on thelaunch vehicle can be reduced by shielding the inlet of the flame duct with a mobile launcher; however, severe impacton the launch complex is unavoidable. The numerical technique and knowledge obtained in this study are applicablein the preliminary design of a launch pad to mitigate the impact of ignition overpressure. | |||||
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.A32700 | |||||
関連名称 | info:doi/10.2514/1.A32700 | |||||
権利 | ||||||
権利情報 | (C)2013 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: PA1410005000 |