This paper investigates the fault-tolerant control for the large launch vehicle(LLV) attitude tracking system considering the influence of interference, actuator fault and model uncertainty. First, the attitude control system model of the launch vehicle is established under actuator loss of effectiveness and bias fault. Then, a novel Takagi-Sugeno fuzzy extended state observer is designed to estimate the uncertain items including launch vehicle fault and disturbance. Finally, a terminal sliding mode fault tolerant control scheme is proposed for the attitude control system. The convergence and global stability of the closed-loop system are proved by the Lyapunov’ s analysis method. Using numerical simulation, it is verified that the terminal sliding mode control law based on the Takagi-Sugeno fuzzy extended state observer proposed has better tracking performance and accuracy.