@inproceedings{oai:jaxa.repo.nii.ac.jp:00007643,
 author = {松永, 三郎 and 矢部, 秀幸 and 中谷, 幸司 and 居相, 政史 and 尾曲, 邦之 and 森, 治 and Matsunaga, Saburo and Yabe, Hideyuki and Nakaya, Koji and Iai, Masafumi and Omagari, Kuniyuki and Mori, Osamu},
 book = {平成16年度アストロダイナミクスシンポジウム:講演後刷り集, ISAS proceedings of 14th Workshop on Astrodynamics and Flight Mechanics 2004: A Collection of Technical Papers},
 month = {Mar},
 note = {In the paper, a new type membrane deployment method is proposed, and locally full-deployment state can be achieved in the deployment from folded state. Fundamental ground experiments of the proposed membrane deployment are conducted using an experimental set-up system including two-dimensional micro-gravity simulators, and tether and membrane control mechanisms developed at Tokyo Institute of Technology. The simulator system is composed of a 3 m x 5 m flat-floor glass and floating satellite simulators with gas-thruster. Here, used are three satellite simulators, triangular membranes, the tether control system and newly developed drum mechanisms for membrane control. The drum mechanism can control membrane extension speed. A virtual structure control method is applied to control the three satellites for formation flight, and PID type control is adopted to control the membrane control. From the experiment obtained is two-dimentional deployment behavior and the feasibility of the proposed method is discussed comparing with corresponding numerical simulation results., 資料番号: AA0047897010},
 pages = {55--60},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)},
 title = {Membrane deployment for spinning formation-flight solar sail},
 year = {2005}
}