The invention provides a hypersonic flight vehicle attitude control method considering input saturation, which comprises the following steps of: 1, combining uncertainty of parameters, unmodeled dynamics and external disturbance in an unpowered reentry process mathematical model of a hypersonic flight vehicle to serve as total disturbance, and establishing models of an attitude loop and an angularrate loop, 2, designing a performance function to constrain steady-state and transient-state performances of state variable tracking errors of the attitude loop and the angular rate loop of the flight vehicle, 3, converting the inequality constraints obtained in the step 2 into equality constraints so as to facilitate controller design, 4, designing a linear extended state observer, and obtainingan output estimation value and a total disturbance estimation value of each loop, and step 5, designing a controller, so that the tracking error of the system can be converged to a preset area underthe condition of facing input saturation constraints. According to the method, the design and parameter optimization of the linear active disturbance rejection controller of the hypersonic flight vehicle are realized, and the dynamic performance, the robust performance and the anti-interference performance of the hypersonic flight vehicle are improved.