Aerodynamic envelope protection using hybrid control

This paper presents the application of controller synthesis for hybrid systems to aerodynamic envelope protection and safe switching between flight modes. Each flight mode, which describes a configuration of the dynamic equations describing the motion of the aircraft, is treated as a discrete state with associated continuous, nonlinear dynamics and the safe subset of the state space (that which ensures aerodynamic envelope protection) is calculated for each discrete state. The methodology is applied to a longitudinal axis model of a CTOL aircraft.