JAXA Repository / AIREX 未来へ続く、宙(そら)への英知

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title形状記憶合金を用いたパネル展開方式の研究
Other TitleResearch of the panel deployment system using the shape memory alloy
Author(jpn)野神 誠一郎; 森田 博和; 樋口 健; 奥泉 信克; 田中 孝治; 佐々木 進
Author(eng)Nogami, Seiichiro; Morita, Hirokazu; Higuchi, Ken; Okuizumi, Nobukatsu; Tanaka, Koji; Sasaki, Susumu
Author Affiliation(jpn)帝京平成大学 大学院; 東京大学 大学院; 宇宙航空研究開発機構 宇宙科学研究本部; 宇宙航空研究開発機構 宇宙科学研究本部; 宇宙航空研究開発機構 宇宙科学研究本部; 宇宙航空研究開発機構 宇宙科学研究本部
Author Affiliation(eng)Teikyo Heisei University Graduate School; University of Tokyo Graduate School; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
Issue Date2005-06
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
宇宙航空研究開発機構宇宙科学研究本部
Publication title第24回宇宙エネルギーシンポジウム 平成16年度
The Twenty-fourth Space Energy Symposium March 7, 2005
Start page57
End page61
Publication date2005-06
Languagejpn
AbstractIn 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.
Keywordsshape memory alloy; solar power satellite; tethered satellite; actuator; deployment; solar cell panel; attitude stability; spacecraft stability; deformation; thermal expansion; 形状記憶合金; 太陽発電衛星; テザー衛星; アクチュエータ; 展開; 太陽電池パネル; 姿勢安定性; 宇宙機安定性; 変形; 熱膨張
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会
SHI-NOAA0049120012
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/53085


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