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小型二段式ロケットの前後翼のロール干渉とロール制御に関する研究
https://jaxa.repo.nii.ac.jp/records/45051
https://jaxa.repo.nii.ac.jp/records/4505160e93f74-ebc5-46c8-b30c-f8647d0da0cd
名前 / ファイル | ライセンス | アクション |
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naltr00793.pdf (2.7 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 小型二段式ロケットの前後翼のロール干渉とロール制御に関する研究 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル(英) | ||||||
その他のタイトル | An Experimental Study on the Induced Rolling Moment due to Wing-Tail Interference and a Roll-Controllable Two-Stage Rocket | |||||
著者 |
白水, 正男
× 白水, 正男× 曽我, 国男× 山崎, 喬× 柴藤, 羊二× 秋元, 敏男× SHIROUZU, Masao× SOGA, Kunio× YAMAZAKI, Takashi× SHIBATO, Yoji× AKIMOTO, Toshio |
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著者所属 | ||||||
航空宇宙技術研究所空気力学第一部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所空気力学第一部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所空気力学第一部 | ||||||
著者所属 | ||||||
宇宙開発事業団 | ||||||
著者所属 | ||||||
宇宙開発事業団 | ||||||
著者所属(英) | ||||||
en | ||||||
First Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
First Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
First Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
National Space Development Agency of Japan(NASDA) | ||||||
著者所属(英) | ||||||
en | ||||||
National Space Development Agency of Japan(NASDA) | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory(NAL) | |||||
書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-793 巻 793, p. 48, 発行日 1983-12 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A wind tunnel investigation of a roll-controllable two-stage rocket model was made at free-stream Mach numbers from 0.5 to 2.5. The model has ailerons on front-fins to generate rolling moment and free-rolling tail-fins to eliminate the effect of the induced rolling moment on tail-fins. The results confirmed the feasibility of this type of roll-controllable rocket. The characteristics of the induced rolling moment were investigated by tests of a model with fixed tail-fins. The characteristics were compared with theoretical results based on the strip-theory. Values of roll-damping coefficient of the tail-fins were obtained by analysing their rolling rate. The effect of the free-rolling tail-fins on other aerodynamic characteristics, such as normal force coefficient, center of pressure and axial force coefficient, were also evaluated. A computer simulation of the rolling motion of the TT-500A rocket, which has a similar configuration to the present model, was made based on the results of the present study, whose results agreed well with the flight-data. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0389-4010 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: NALTR0793000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL TR-793 |