Bumpless Switching Control for Aircraft Engine Control Systems With Actuator Fault Based on Switched LPV Models

In this article, a bump restriction dependent switching command design strategy is proposed for the aircraft engine control system which is characterized by a switched LPV (SLPV) model. A novel bump restraint description is introduced, quantifying the bump restraint level just by the magnitude of the state at switching points. Unlike the existing description of the bumpless switching performance, this description better reflects the original ideal of bumpless switching. By co-designing the bump restriction dependent switching command and control law, the robust stability condition is developed with the actuator fault addressed. An effective simulation verification performed on an aircraft engine semi-physical experiment test bed is provided on the established bumpless switching control approach.