yasutaka satou

A varaety of satellites are presently utilizing deployable large area structures in orbit. As a novel deployment method for these structures, this study proposes a deployment and retracting method using an electromagnetic force for extensible panels on satellites. Using the proposed method, panels can be deployed quasi-statically to reduce the impulsive force exerted on fragile panels in the deployment. Furthermore, a satellite can also retract panels to a much smaller volume to avoid damage from space debris and achieve agile attitude maneuvers in small moment of inertia. Finally, to assess the proposed method, numerical simulations using multibody dynamics were conducted.

大気球シンポジウム 平成26年度（2014年11月6-7日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)）, 相模原市, 神奈川県 Balloon Symposium 2014 (November 6-7, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan 著者人数: 26名 資料番号: SA6000021016 レポート番号: isas14-sbs-016

Mechanical properties of wrinkles induced by wrapping fold of large space membranes are examined to determine the wrinkle condition in the wrapping fold process. Wrapping fold experiments are performed to investigate the effects of the wrapping tensile force, the crease, and the membrane thickness on the wrinkles. Using the experimental results, the wrinkle condition is examined. To examine the stress around the wrinkles and to confirm the validity of the experimental results, FEM analyses are demonstrated.