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片持矩形弾性翼の突風荷重軽減の風洞試験と解析
https://jaxa.repo.nii.ac.jp/records/45104
https://jaxa.repo.nii.ac.jp/records/451047d429e6a-a062-49f7-918a-58d38d0da2c7
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00846.pdf (2.6 MB)
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| 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 | 片持矩形弾性翼の突風荷重軽減の風洞試験と解析 | |||||||||
| 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 | Gust Load Alleviation of a Cantilevered Rectangular Elastic Wing. Wind Tunnel Experiment and Analysis | |||||||||
| 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-846 巻 846, p. 32, 発行日 1984-12 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | This paper describes an experimental and theoretical study on gust load alleviation (GLA) of a cantilevered rectangular elastic wing with an active aileron. The beneficial effects predicted by the theoretical analysis were verified by the experiment performed in a low subsonic wind tunnel. The root-mean-square value of the wing motion to random gust decreased by 45-50％ when the GLA system was turned on. The aileron was actuated according to the first-order control law. The law used was obtained by modifying an optimal control law of seventh order which was originally formulated with the aid of an LQG approach. In the mathematical wing model, only the first bending mode and aileron motions were taken into account because the frequencies of the second and higher modes of the wing were much higher than the frequency spectrum contained in the gust generated. The unsteady aerodynamic prediction incorporated in the GLA system was corrected by test data for steady flow so that the response due to the aileron motion as estimated with good accuracy. | |||||||||
| 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: NALTR0846000 | |||||||||
| 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-846 | |||||||||
