@inproceedings{oai:jaxa.repo.nii.ac.jp:00007644,
 author = {山本, 昌幸 and 武市, 昇 and 上野, 浩史 and 小田, 光茂 and 関口, 毅 and Yamamoto, Masayuki and Takeichi, Noboru and Ueno, Hiroshi and Oda, Mitsushige and Sekiguchi, Takeshi},
 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 = {編隊飛行する太陽発電衛星システム(FF-SSPS)は、静止軌道上にあって地球指向する発送電部と、太陽輻射圧を揚力として利用して赤道面から一定の距離に保たれつつ太陽指向する反射鏡によって構成される。本稿では、まず、円軌道近傍におけるHill方程式で表される系に対してLQRを適用し、反射鏡の発送電部に対する相対軌道制御則を導く。続いて、静止軌道上で想定される摂動源を組み込んだ軌道制御シミュレーションを実施し、制御則の有効性を検証する。, A space solar power satellite system using a formation-flying reflector (FF-SSPS) consists of the main body and two formation-flying reflectors. The main body is located on geostationary orbit. Two reflectors are located north and south of the main body. Their orbital planes are parallel to the main body's orbital plane. First set is the control law to maintain the relative position of the reflector for the main body, which is an applied linear quadratic regulator (LQR) for the system expressed in Hill's equation around a circular orbit. Then the efficiency of the control law is confirmed using an orbit control simulation that incorporates the perturbations that are assumed on geostationary orbit., 資料番号: AA0047897011},
 pages = {61--66},
 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 = {Relative position control for solar power satellites using a formation flying reflector},
 year = {2005}
}