The output feedback fault tolerant control strategy was proposed for aero-engine distributed control system with network induced time delay and disturbance in occurrence of actuator partial fault. The areo-engine distributed control system model parameters were described quantitatively

and the closed-loop system was established based on dynamic output feedback controller. The stability analysis under the constraint of H∞ performance was given for the augmented closed-loop system

based on which the design approach of output feedback H∞ fault-tolerant controller was designed by means of linear matrix inequality. Simulation results showed that the system was asymptotically stable with the devised controller when actuator attenuation faults were 80% and 50%

respectively

and had a certain H∞ performance index 0.63. Similarly

then system had a good fault tolerant performance when actuator attenuation faults occurred.