Abstract: Aiming at the design of attitude control of hypersonic vehicles, the sliding mode disturbance observer is used to compensate the composite disturbance, meanwhile the dynamic surface control method is used to deal with the design of the nonlinear control system. Considering the input saturation problem, the control input is expanded into a new variable to design the controller, which is different from the direct limit of the rudder deviation. The simulation results show that the dynamic surface control method based on sliding mode observer has stronger robustness than the simple dynamic inversion control method, but the control inputs of both methods are forced to limit the rudder bias, which is bad for the stability of the system. The attitude control of aircraft considering input saturation not only ensures the accurate tracking of attitude, but also ensures the smoother control input and relatively smaller peak value.

Key words: hypersonic vehicle, attitude control, sliding mode disturbance observer, dynamic surface control, input saturation