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Attitude Control of Miniature Spacecraft Using a Micro-Actuator

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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.

Document Type: Research Article


Publication date: July 1, 2012

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  • ADVANCED SCIENCE LETTERS is an international peer-reviewed journal with a very wide-ranging coverage, consolidates research activities in all areas of (1) Physical Sciences, (2) Biological Sciences, (3) Mathematical Sciences, (4) Engineering, (5) Computer and Information Sciences, and (6) Geosciences to publish original short communications, full research papers and timely brief (mini) reviews with authors photo and biography encompassing the basic and applied research and current developments in educational aspects of these scientific areas.
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