L1 Fault Tolerant Control with Sliding-Mode Based Adaptive Law for Aircraft Actuator Fault

摘要

This paper present a method for the aircraft fault control system, which is based on an Ll adaptive controller with sliding-mode based adaptive law. In particular, the actuator fault is analyzed and considered as matched uncertainties. To compensate the uncertainties, Ll adaptive control which provides good tracking performance as well as robustness is applied into the flight control system. Sliding-mode control is used as an adaptive law to estimate the uncertainties and be considered as a virtual control of error dynamics in the Ll adaptive control architecture. By introducing the low-pass filter, performance and robustness are decoupled, which allows for a fast and reliable compensation of uncertainties. By introducing a reference system, the stability of Ll-SMC control system is proved. Finally, The simulation results demonstrate the performance of the presented Ll-SMC adaptive controller.