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高アスペクト比翼の突風荷重軽減風洞実験と解析
https://jaxa.repo.nii.ac.jp/records/45148
https://jaxa.repo.nii.ac.jp/records/451485ceb2328-eb20-463e-b03c-e90895235c12
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00890.pdf (4.5 MB)
|
|
| Item type | テクニカルレポート / Technical Report(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | 高アスペクト比翼の突風荷重軽減風洞実験と解析 | |||||||||
| 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 | Wind Tunnel Tests and Analysis on Gust Load Alleviation of a High-Aspect-Ratio Wing | |||||||||
| 著者 |
ACT研究会
× ACT研究会
× ACT Study Group
|
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| National Aerospace Laboratory(NAL) | ||||||||||
| 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-890 巻 890, p. 57, 発行日 1985-11 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | Application of the active control technology to gust load alleviation problems was investigated both experimentally and analytically. Wind tunnel tests were conducted for a high-aspect-ratio wing that assumes an energy efficient type of future transport. For these tests, NAL’s low speed wind tunnel was equipped with a gust generator with hydraulic servo system. This generator generates turbulence by utilizing the tip vortices from the cantilevered double wings. Atomospheric turbulence was simulated in the tunnel according to the Dryden math-model. Control surfaces of the flexible wing model were actuated by a small DC electric motor embedded in the airfoil. A handy analog computer played the role of controller to drive control surfaces by the signals from two accelerometers and a strain gauge which were installed in the model as feedback sensors. Control laws were obtained by the optimal control theory with its performance index selected as the total energy of the system. Simple control laws based on the LQG thory demonstrated their effectiveness against realistic random gusts. At the end of the test, the flutter boundary of this model was determined for the configuration without active control. | |||||||||
| 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: NALTR0890000 | |||||||||
| 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-890 | |||||||||
