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This paper presents a Takagi-Sugeno (T-S) model based fuzzy control design approach for rigid satellite attitude maneuver. The T-S fuzzy model is first applied to represent the rigid satellite model consists of dynamic and kinematics equation. Then, a fuzzy state feedback controller is designed for the obtained T-S fuzzy model with considering the decay rate by using the parallel distributed compensation scheme. Then, sufficient conditions for the existence of such a controller are derived in terms of linear matrix inequalities (LMIs) and the controller design is cast into a convex optimization problem subject to LMI constraints, which can be readily solved by Matlab. The mathematical simulation results of example show that the time of satellite maneuver is shortened.