Abstract

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 present to rebuild the velocity information of the satellite in finite time. With this estimation of velocity, a finite time attitude controller is designed based on nonsingular fast terminal sliding mode theory. In the end, simulations are presented to shown the effectiveness of the proposed control scheme with high accuracy and fast convergence.

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