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

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Other TitleDeployment mechanisms of thick panels with SMA actuators
Author(jpn)樋口 健; 田中 孝治; 佐々木 進; 奥泉 信克; 野神 誠一郎; 森田 博和
Author(eng)Higuchi, Ken; Tanaka, Koji; Sasaki, Susumu; Okuizumi, Nobukatsu; Nogami, Seiichiro; Morita, Hirokazu
Author Affiliation(jpn)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; 帝京平成大学 大学院; 東京大学 大学院工学系研究科
Author Affiliation(eng)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; Teikyo Heisei University Graduate School; University of Tokyo Graduate School of Engineering
Issue Date2004-06
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
Publication title第23回宇宙エネルギーシンポジウム 平成15年度
The 23rd ISAS Space Energy Symposium March 9, 2004
Start page94
End page98
Publication date2004-06
AbstractShape memory alloy (SMA) has attractive characteristics such as shape memory effect, super elasticity and hysteresis of stress-strain relationship. By utilizing SMA for actuators of large deployable panels, it is expected to realize controlled and low-shock deployment, sequential deployment, shape control during deployment, also shape control and vibration absorption after deployment, and so on. Generally, expected functions of actuators for deployment, shape control, and vibration suppression for panel-like huge space structures are small attitude deviation during deployment, low shock at latching, good structural accuracy, controllability of static shape such as thermal deformation compensation, large vibration damping, capability of folding panels with a certain quantity of thickness. A multi-functional actuator utilizing SMA may be able to satisfy the requirements. In this paper, proposed is a conceptual design of a multi-functional SMA actuator, which is applicable to a unified panel of power generation and transmission of a solar power satellite. The basic principles and possibilities of deployment, latch mechanism, shape control and vibration absorption are presented. A hinge for two-way angle control effect can be realized by making a pair of SMA coils, each of which undergoes one-way shape memory treatment at different aperture angle. One of the pair of SMA coils is conducted to heat up to the reverse transformation temperature in order to activate the shape recovery effect one way. In the case that both of the pair of SMA coils are conducted at the same time to heat up, the hysteresis loop of stress-strain relationship at the high temperature phase of SMA can be used to damp the vibration of a large amplitude. The hinge with two-way shape memory effect requires a latching mechanism that can latch and release at any hinge angle between the two panel units. The latch can be designed by combining permanent magnet and electromagnet, and a tongue of magnetic material. Demonstration model of the function has also been made. Instead of thick panel unit with actual thickness, a thin rigid panel represents the mid-surface of the thick panel unit. Spacers with height of half of the thickness of a thick panel unit are attached to the both sides of the mid-surface panel in order to demonstrate the thick panel unit. The SMA hinges and magnetic latches combine 8 x 4 panel units. Some functions of the multi-functional hinge of the panel have been proved.
Keywordssatellite design; deployment mechanism; shape memory alloy; panel; solar power satellite; attitude stability; satellite attitude control; actuator; 衛星設計; 展開機構; 形状記憶合金; パネル; 太陽発電衛星; 姿勢安定性; 衛星姿勢制御; アクチュエータ
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会

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