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Linear Dynamic Analysis of the Spinning Axisymmetrical Rocket or Vehicle
https://jaxa.repo.nii.ac.jp/records/34380
https://jaxa.repo.nii.ac.jp/records/3438034718d06-bd2e-4ff4-b415-3d3906033beb
名前 / ファイル | ライセンス | アクション |
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SA2400510.pdf (2.9 MB)
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Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Linear Dynamic Analysis of the Spinning Axisymmetrical Rocket or 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 | departmental bulletin paper | |||||
著者 |
AZUMA, Akira
× AZUMA, Akira |
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出版者 | ||||||
出版者 | 東京大学宇宙航空研究所 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Aeronautical Science,University of Tokyo | |||||
書誌情報 |
en : ISAS report/Institute of Space and Aeronautical Science,University of Tokyo 巻 30, 号 8, p. 217-273, 発行日 1965-12 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | This report contains a dynamic analysis of the angular behavior of a spinning body flying either in vacuum or in atmosphere. The study is mainly concerned with the angular motion of a rigid axisymmetrical body having a thrust malalignment and another moment due to the deflection of control surfaces or control jets. In linear feedback system which is used in the control of spin-stabilized space vehicle, preferable combinations of the control parameters, such as feedback gain, spin rate, feedback phase difference and damping of the system, are obtained to optimize the stability and control of the vehicle. In the case of asymmetrical feedback system the linear approximate solution has been obtained. The analysis of the feedback system will be applied to the motion of either launching or re-entry vehicle within atmosphere. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0372-1418 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA00675986 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA2400510000 |