The attitude of the aircraft is controlled based on the theory of fault-tolerant control and integral sliding mode control to make it fault-tolerant.Taking a class of nonlinear system with uncertainties and possibility of actuator faults as the aircraft model, an integral sliding mode controller was designed for the system, which can keep an ideal control performance even in the case of actuator faults.For comparison, the controller was also designed for the system based on Lyapunov′s direct method and sliding mode control theory respectively.Simulation was made in the presence or absence of actuator faults, to observe the effects of the three kinds of control methods on the state variables, and to compare the chattering condition under normal sliding mode control and integral sliding mode control.The results show that integral sliding mode control performs better in control effect and chattering reduction.