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This paper presents a novel adaptive mode switching scheme for hypersonic morphing aircraft with retracted winglets based on type-2 Takagi-Sugeno-Kang(TSK) fuzzy sliding mode control. For each of retracting and stretching modes, a specific sliding mode controller has been adopted. Drawing upon input/output linearization to globally linearize the nonlinear model of the hypersonic aircraft at first, a type-2 TSK fuzzy logic system is devised for robust mode switching between these sliding mode controllers. For rapid stabilization of the system, the adaptive law for mode switching is designed using a direct constructive Lyapunov analysis.Simulation results demonstrate the stability and smooth transition using the proposed switched control scheme.
This paper presents a novel adaptive mode switching scheme for hypersonic morphing aircraft with retracted winglets based on type-2 Takagi-Sugeno-Kang (TSK) fuzzy sliding mode control. For each of retracting and stretching modes, a specific sliding mode controller has been . For Drawing the input / output linearization to globally linearize the nonlinear model of the hypersonic aircraft at first, a type-2 TSK fuzzy logic system is devised for robust mode switching between these sliding mode controllers. For rapid stabilization of the system, the adaptive law for mode switching is designed using a direct constructive Lyapunov analysis. Simulation results demonstrate the stability and smooth transition using the proposed switched control scheme.