ATTITUDE CONTROL OF A MICRO SATELLITE WITH EVENTUAL SLIDING MODE CONTROLLER
スポンサーリンク
概要
- 論文の詳細を見る
The feasibility study has been investigated to build a small satellite (so called 'nano-satellite'), which has 3-kg mass and less than 30-W power, since October in 1998. The experimental 3-axes attitude control of the nano-satellite under micro-gravity field is conducted at in Japan Micro-gravity Center (JAMIC) in 2001. The small reaction wheel is used as an actuator for the attitude control and enables compensate the small residual deviation of the presume error. This project investigates the validity of the feedback control with sliding mode control because of the correspondence for the non-linearity of the control system and the excellence for robustness^<[1]>.
- 社団法人日本機械学会の論文
著者
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Satori S
Department Of Electric Electronics Engineering Hokkaido Institute Of Technology
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Takezawa Satoshi
Department of Mechanical Engineering, Hokkaido Institute of Technology
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Ishikawa Tomohiro
Graduate School of Mechanical Systems Engineering, Hokkaido Institute of Technology
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Satori Shin
Department of electric electronics Engineering, Hokkaido Institute of Technology
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Ishikawa Tomohiro
Graduate School Of Mechanical Systems Engineering Hokkaido Institute Of Technology
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Takezawa Satoshi
Department Of Mechanical Engineering Hokkaido Institute Of Technology
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Takezawa Satoshi
Mechanical System Engineering Hokkaido Institute Of Technology
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Satori Shin
Department Of Electric Electronics Engineering Hokkaido Institute Of Technology
関連論文
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