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Body Divergence of a Multi-Stage Rocket
https://jaxa.repo.nii.ac.jp/records/34392
https://jaxa.repo.nii.ac.jp/records/34392efc3f66f-dc26-4984-adff-8ea531224016
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA2400548.pdf (490.9 kB)
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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 | ||||||||||
| タイトル | Body Divergence of a Multi-Stage Rocket | |||||||||
| 言語 | en | |||||||||
| 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 |
IKEDA, Ken
× IKEDA, Ken
× HIRANO, Yoichi
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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 32, 号 4, p. 65-73, 発行日 1967-03 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | The body of a rocket is designed to satisfy the static stability criteria. The body should not be considered rigid but elastic, especially when the body is slender. Even if the body is statically stable for a rigid one, the critical speed exists for an elastic body. This speed is known as the divergence speed. For a single-stage rocket, this divergence speed is already obtained by one of the authors [1]. The method of deriving this speed is given in the following. The lift of the single-stage rocket operates mainly on around the nose and the fin. It dose not seem much errorneous to consider the total lift concentrated on the nose and the fin [2]. So the deformation of the body can be determined in such a way that the inertia force of the body corresponding to some flight speed is supported at the nose and the fin. The angle of attack of the nose and of the fin are now obtained and the lift of each point can be calculated. The divergence speed is derived by equating the restoring moment due to the lift zero. In calculating the divergence speed for an actual rocket, the values for the lift coefficient can be obtained by the wind-tunnel test and the values for the deformation can be obtained by the bending test of the actual rocket or the simple calculation. This method is very clear and simple in calculating the divergence speed. In 1965 National Aerospace Laboratory fired NAL-7 rockets. The area of the fin and the center of the gravity of these rockets were varied, and the stability of the flight was examined. From these experimental results the above mentioned analysis has been found very useful. In this paper, this method of analysis is extended to the multi-stage rocket. It does not seem much errorneous to consider the lift of a multi-stage rocket concentrated on the several points, and so the analysis for a single-stage rocket concentrated on the several points, and so the analysis for a single-stage rocket can be extended. | |||||||||
| 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: SA2400548000 | |||||||||
