This paper presents the attitude control of miniature spacecraft using a micro-actuator. A nonlinear mathematical model for the spacecraft coupled by the micro-actuator is developed. The proposed model includes not only the inverse piezoelectric effect of the micro-actuator but also
the gravitational effect. This paper also presents three controller designs, the pole assignment method, the linear quadratic regulator, and the time-delay control, which demonstrate the feasibility of spacecraft attitude control using the hub-bimorph mechanism.
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