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剛体ダイナミクスを考慮した宇宙往還機の上昇飛行経路最適化
https://jaxa.repo.nii.ac.jp/records/17449
https://jaxa.repo.nii.ac.jp/records/174498274ae9f-1e40-4904-b621-f2118eac09e5
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 剛体ダイナミクスを考慮した宇宙往還機の上昇飛行経路最適化 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 上昇飛行経路 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 飛行経路最適化 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | スペースプレーン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | SSTO | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 剛体ダイナミクス | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | ascent trajectory | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | trajectory optimization | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | spaceplane | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | SSTO | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | rigid body dynamics | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Ascent trajectory optimization of a space plane considering rigid body dynamics | |||||
著者 |
横山, 信宏
× 横山, 信宏× 鈴木, 真二× Yokoyama, Nobuhiro× Suzuki, Shinji |
|||||
著者所属 | ||||||
東京大学 大学院工学系研究科 | ||||||
著者所属 | ||||||
東京大学 工学部 | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo Graduate School of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo Faculty of Engineering | ||||||
出版者 | ||||||
出版者 | 宇宙科学研究所 | |||||
出版者(英) | ||||||
出版者 | The Institute of Space and Astronautical Science (ISAS) | |||||
書誌情報 |
宇宙輸送シンポジウム 平成13年度 en : Proceedings of Space Transportation Symposium FY2001 p. 83-86, 発行日 2002-04 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | In the past studies on the ascent trajectory optimization of a space plane, mass point approximation is usually used to simplify the problem. However, the validity of those obtained trajectory must be verified under the more precise dynamics model. Especially; if the rigid body dynamics is considered, the attitude control system and vehicle's flight trajectory usually have a strong coupling. Therefore, this study considers the trajectory optimization of a SSTO with the rigid body dynamics. New proposed method, in which the guidance law and the attitude control system are optimized simultaneously, is compared with the conventional method, in which the guidance law and the attitude control system are optimized sequentially, and the advantages of the new method are demonstrated. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0033392021 |