WEKO3
アイテム
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太陽発電衛星の展開シーケンス最適化
https://jaxa.repo.nii.ac.jp/records/8096
https://jaxa.repo.nii.ac.jp/records/8096c6236558-26a5-429d-9fb6-e1a17e08a25a
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 | 太陽発電衛星の展開シーケンス最適化 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 太陽発電衛星 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 展開シーケンス | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 最適化 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 姿勢安定性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 宇宙機安定性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 非線形システム | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 慣性モーメント | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 加速度 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | solar power satellite | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | deployment sequence | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | optimization | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | attitude stability | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | spacecraft stability | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | nonlinear system | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | moment of inertia | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | acceleration | |||||
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 | Optimization of the deployment sequence of solar power satellite | |||||
著者 |
石村, 康生
× 石村, 康生× 高井, 伸明× Ishimura, Kosei× Takai, Nobuaki |
|||||
著者所属 | ||||||
北海道大学 大学院工学研究科 | ||||||
著者所属 | ||||||
北海道大学 大学院工学研究科 | ||||||
著者所属(英) | ||||||
en | ||||||
Hokkaido University Graduate School of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Hokkaido University Graduate School of Engineering | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構宇宙科学研究本部 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS) | |||||
書誌情報 |
第24回宇宙エネルギーシンポジウム 平成16年度 en : The Twenty-fourth Space Energy Symposium March 7, 2005 p. 47-51, 発行日 2005-06 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | For the demonstration and verification of solar power satellite's functions, a small demonstration solar power satellite has been examined by USEF and ISAS/JAXA. Structural characteristics and attitude motion in steady operation have already been studied. In this paper, deployment sequence for the stable and fast deployment is investigated. The deployment sequence consists of two-stage truss extension and two-stage panel deployment. At first, attitude motion in the deployment is analyzed through numerical simulations. From the result, it is shown that nonlinear effect can not be negligible when pitch angle exceeds about 0.6 rad. In such a case, because independency of the pitch angle does not hold true for the nonlinearity, pitch motion leads to the large roll and yaw motions. Next, to realize stable and fast deployment, optimization of the deployment is carried out by changing each deployment time, interval and acceleration of the deployment. As an objective function, weighted sum of deployment times, maximum amplitudes of attitude angles and residual amplitudes of attitude angles is used. The optimization is carried out by Powell's method. From the result it is shown that maximum amplitudes of attitude angles are kept within 0.08 rad, and residual amplitudes of attitude angles are kept within 0.01 rad without any active control if about five orbital periods (about eight hours) can be spent for the total deployment. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0049120010 |