Abstract: To address such challenges as strong uncertainties, nonlinearities, and rapidly changing dynamics faced by the attitude control system during the dive phase of high-speed flight vehicles, an adaptive disturbance rejection control（AADRC）method for attitude control is proposed. Unlike traditional ADRC methods, the proposed approach employs an extended Kalman filtering algorithm to identify key aerodynamic parameters. Different from the traditional adaptive disturbance rejection control method, the proposed method utilizes the extended Kalman filtering algorithm to identify the key pneumatic parameters so that the more accurate model information can be provided for the design of the extended state observer and rudder-trimming deflection, the design of adaptive feedforward control is achieved. Meanwhile, the adaptive augmentation control method and the gain schedule method are designed based on identification values of key aerodynamic parameters to realize the feedback control design based on online estimation of steerage. Finally, strong robustness, high accuracy, and adaptability of the proposed method under various aerodynamic parameter deviations are verified by the simulation analysis of flight mission scenarios of a dive phase for a typical high-speed flight vehicle.