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スプリットエレボンを用いた有翼宇宙往還機の横/方向制御の検討
https://jaxa.repo.nii.ac.jp/records/40569
https://jaxa.repo.nii.ac.jp/records/405691f244023-95b9-4c9d-8232-524b58f4e26d
名前 / ファイル | ライセンス | アクション |
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naltr0001379.pdf (420.2 kB)
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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 | スプリットエレボンを用いた有翼宇宙往還機の横/方向制御の検討 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | スプリットエレボン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 有翼宇宙往還機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 飛行制御 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ティップフィン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 飛行安定性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 風洞実験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | HOPE | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 宇宙往還技術試験機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 垂直尾翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 制御系設計 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 計算機シミュレーション | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力特性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 姿勢制御 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 姿勢安定性 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | split elevon | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | winged reentry vehicle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flight control | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | tip fin | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flight stability | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wind tunnel experiment | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | HOPE | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | H 2 Orbiting Plane Experimental | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | vertical tail | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | control system design | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computer simulation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic characteristics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | attitude control | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | attitude stability | |||||
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 | Feasibility study of lateral/directional control of winged re-entry vehicle with split elevons | |||||
著者 |
塚本, 太郎
× 塚本, 太郎× 柳原, 正明× 水藤, 貴靖× Tsukamoto, Taro× Yanagihara, Masaaki× Suito, Takanobu |
|||||
著者所属 | ||||||
航空宇宙技術研究所 制御部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 制御部 | ||||||
著者所属 | ||||||
宇宙開発事業団 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Control Systems Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Control Systems Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Space Development Agency of Japan | ||||||
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 巻 1379, p. 1-24, 発行日 1999-03 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 最近のいくつかの航空機では、垂直尾翼をなくし、ドラッグラダーなどを用いた能動的制御によって方向安定を得る試みがなされている。宇宙往還機でもこのような形態にすれば、特に構造上有利である。ここでは、宇宙開発事業団と航空宇宙技術研究所が共同研究している無人有翼往還機からティップフィンを除き、スプリットエレボンを付加した形態での風洞試験結果を用いてMDM/MDP(多数遅れモデル/多数設計点)法によって横/方向の飛行制御則を設計し、その評価を行う。ティップフィンをなくすことにより、機体の方向安定は悪化するが、スプリットエレボンを用いた制御によりある程度の安定性、制御性を得ることができる。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Recently, several aircraft which lack vertical tails have been developed, the so-called 'tailless aircraft'. For directional stability, these aircraft are actively controlled using devices such as drag rudders. In the case of winged reentry vehicles, it will be useful to apply this technology, especially from the structural viewpoint. In this paper, a tailless configuration of the HOPE-X (H-2 Orbiting Plane Experimental), a winged reentry vehicle being developed by the National Aerospace Laboratory and National Space Development Agency of Japan, was analyzed. Lateral/directional control laws were designed for this configuration using the MDM (Multiple Delay Model)/MDP (Multiple Design Point) approach. Though directional stability degenerated without fins, the vehicle was stabilized and controlled to a certain degree using split elevons. | |||||
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: AA0001804000 | |||||
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-1379 |