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形状記憶合金を用いたパネル展開方式の研究
https://jaxa.repo.nii.ac.jp/records/8098
https://jaxa.repo.nii.ac.jp/records/8098236b4c92-b8c9-48c5-8270-d73324ef9d08
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 | 形状記憶合金を用いたパネル展開方式の研究 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 形状記憶合金 | |||||
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 | テザー衛星 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | アクチュエータ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 展開 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 太陽電池パネル | |||||
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 | 変形 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱膨張 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | shape memory alloy | |||||
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 | tethered satellite | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | actuator | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | deployment | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | solar cell panel | |||||
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 | deformation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | thermal expansion | |||||
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 | Research of the panel deployment system using the shape memory alloy | |||||
著者 |
野神, 誠一郎
× 野神, 誠一郎× 森田, 博和× 樋口, 健× 奥泉, 信克× 田中, 孝治× 佐々木, 進× Nogami, Seiichiro× Morita, Hirokazu× Higuchi, Ken× Okuizumi, Nobukatsu× Tanaka, Koji× Sasaki, Susumu |
|||||
著者所属 | ||||||
帝京平成大学 大学院 | ||||||
著者所属 | ||||||
東京大学 大学院 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 宇宙科学研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 宇宙科学研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 宇宙科学研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 宇宙科学研究本部 | ||||||
著者所属(英) | ||||||
en | ||||||
Teikyo Heisei University Graduate School | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo Graduate School | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science | ||||||
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. 57-61, 発行日 2005-06 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | In the tethered-type solar power satellite, a large panel structure for the power generation and transmission is adopted. A huge number of actuators are required to deploy the large panel in orbit. In our research, a deployment mechanism using coils of shape memory alloy (SMA) has been studied. When the SMA coil is heated by applying an electric current, it works to deploy the folded panels if the coil has a memory for rotation. This mechanism has several advantages as: (1) Simple and light-weight as compared with motor activation, (2) Deployment speed is well controlled to minimize the effect on the attitude of the system during deployment and to suppress the shock when the panel is fully deployed, (3) The shape of the unfolded panels can be controlled using two types of SMA coils (this function can be used to compensate the thermal deformation of the panels), and (4) The oscillation of the panels can be suppressed by heating the SMA coils to the super-elastic state. We have fabricated the hinges containing the SMA coils as shown in this report and integrated them to a test panel composed of 4 x 8 sub-panels. The size of the sub-panel is 12 x 24 cm. The test model is equipped with a latch mechanism using the permanent magnet. In the laboratory test, it is confirmed that the hinge with the SMA coils work well as expected, but it is found that the life of the SMA coils is unexpectedly limited by the metal fatigue. Further study is required to redesign the SMA coils to eliminate the fatigue effect. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0049120012 |