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The problem of attitude control for a spacecraft model which is nonlinear in dynamics with inertia uncertainty and external disturbance is investigated in this paper. The extended state observer is applied to estimate the disturbance, by which a sliding mode controller is designed to force the state variables of the closed loop system to converge to the reference attitude states. Also, simulation...
A novel approach combining the sliding mode control and extended state observer is proposed for attitude control of a quaternion missile model which is nonlinear in aerodynamics. Combining the back-stepping technique, the corresponding sliding mode controller is designed to guarantee the state variables of the closed loop system to converge to the reference state with the help of the extended state...
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