ATTITUDE CONTROL OF A MICRO SATELLITE WITH EVENTUAL SLIDING MODE CONTROLLER
Satoshi TAKEZAWA, Tomohiro Ishikawa, Shin Satori · The Proceedings of the International Conference on Motion and Vibration Control · 2002
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^.