In this paper, a FTFC system is designed to handle a cosmic rays fault affecting actuator control signal. The geometric approach is used to design the fault diagnosis module. This module determines the gravity of the fault and calculates its parameters. Based thereon, a new reconfigurable Sliding Mode Control law is designed and applied on the longitudinal linear model of the F-16 aircraft. Simulations are performed using Matlab®/Simulink® to show the effectiveness of the proposed approach.

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