A new IFNTSM controller design for the BWB aircraft with parameter uncertainties

Aiming at attitude control of the advanced Blendwing-body (BWB) layout aircraft with aerodynamic, center of gravity and inertial parameters' uncertainties, a new improved fast non-singular terminal sliding mode control (IFNTSM) method is proposed in this paper. Compared to the conventional terminal sliding mode (TSM) control method, IFNTSM guarantees to reach the equilibrium in an improved finite time for any initial state and also effectively deals with system uncertainties. Moreover, the proposed method addresses the singularity problem in the conventional TSM controller design. Simulation results verify the ability and effectiveness of the IFNTSM controller to improve the convergence rate and cope with strong uncertainties.