Attitude Control of an Underactuated
نویسنده
چکیده
A continuous feedback controller with a periodic time varying term for the attitude control of an un-deractuated rigid spacecraft is derived. The attitude is described with the Euler parameter vector. Due to the nondiierentiable nature of exponential stabilizers , sampling of some measurements is used. Global exponential convergence is indicated with analysis and simulations.
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تاریخ انتشار 2008