Robust Attitude Stabilization of Spacecraft Using Minimal Kinematic Parameters
نویسندگان
چکیده
In this paper, we consider the problem of three-axis robust attitude stabilization of a rigid spacecraft using minimal, three-dimensional kinematic parameters. New nonlinear control laws having a class of relaxed feedback gain structures are proposed, and are shown to provide a robustness with respect to inertia uncertainties of a rigid body. A numerical example is given to illustrate the theoretical results.
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تاریخ انتشار 2001