A feasibility study of SMC-MIMO based control architecture for longitudinal high angle of attack flight

摘要

Aircraft is a highly non-linear vehicle especially when it flies at high angles of attack due to flow separations which cause non-linear aerodynamic characteristics in that region. To deal with the non-linearity of the aircraft in this region, a robust control method for a multi-input multi-output or MIMO problem is considered in this feasibility review. Sliding mode control (SMC) approach was selected as it is one of the robust and nonlinear control methods. In this paper, the controller objective is to track the angles of attack and the pitch angle throughout the high angles of attack envelope itself. Numerical simulations are carried out with respect to high angles of attack maneuver; and the novel integrated SMC-MIMO system performances were studied accordingly based on their transient responses. The results show the feasibility of the proposed control architecture for the high angles of attack within the flight envelopes.