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This paper studies the finite time attitude control of a satellite with flexible appendages when the velocity measurements are not available in the condition of external disturbances and model uncertainties. First a dynamic model which considers the coupling effect between the motion of the rigid hub and the deformation of the flexible appendages is build. Then a terminal sliding mode observer is...
The problem of attitude tracking control for rigid satellite is studied in this paper. Based on the dynamic equation and kinematics equation using error quaternion and error angular velocity, a sliding mode controller is initially designed to solve this problem. In order to avoid inherent chattering of sliding mode control and then improve control effect, a disturbance observer is introduced and included...
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