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VSRA/DLCフラップ系の安定・操縦微係数の同定
https://jaxa.repo.nii.ac.jp/records/45375
https://jaxa.repo.nii.ac.jp/records/45375103871bd-5fae-402c-b8df-cdba8529255f
名前 / ファイル | ライセンス | アクション |
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naltr01116.pdf (1.2 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 | VSRA/DLCフラップ系の安定・操縦微係数の同定 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Stability/Control derivatives; Flight Tests; Frequency Response Method; DLC-flaps; In-flight simulator | |||||
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 | Identification of the Stability and Control Derivatives of a DLC-Flap System for VSRA. | |||||
著者 |
塚野, 雄吉
× 塚野, 雄吉× 小野, 孝次× 石川, 和敏× TSUKANO, Yukichi× ONO, Takatsugu× ISHIKAWA, Kazutoshi |
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著者所属 | ||||||
航空宇宙技術研究所飛行実験部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所飛行実験部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所飛行実験部 | ||||||
著者所属(英) | ||||||
en | ||||||
Flight Research Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Flight Research Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Flight Research Division, 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-1116 巻 1116, p. 16, 発行日 1991-07 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | DLCフラップを装着した可変安定応答実験機(VSRA)のシステム・パラメータを知るために強制振動法による飛行実験を行った。水平定常飛行状態のトリムまわりで,DLCフラップを種々の周波数で持続的に加振し,その機体応答の周波数特性データからVSRAシステムの安定・操縦微係数を同定した。さらに,その操縦微係数からDLCフラップの揚力,抗力そして縦揺れモーメントを推定し,風洞試験結果とも比較した。その実験方法並びにデータ解析手法について述べる。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Flight tests were conducted using the Variable Stability and Response Airplane (VSRA) in order to identify the stability and control derivatives for a Direct Lift Control (DLC) flap system. The frequency response method was selected, with a pure sinusoidal input being applied to the DLC-flaps. Response from a linear system model consisting of the stability and control derivatives were compared with other flight test response data to determine general-inputs and resulting derivatives were subsequently verified. In addition, the control capability of the DLC-flaps was estimated by the control derivatives, and their compared with wind tunnel test 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: NALTR1116000 | |||||
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-1116 |