Abstract: To enhance the flying quality of aircraft post-stall maneuver in a model flight test, an improved dynamic surface flight control law was proposed in consideration of the unsteady aerodynamics effect and the actuator model. The controller designing procedure was established for general affine models. In the procedure, the dynamic surface controller for the sub-system was first developed. Then the slide mode control technique was employed to synthesize the whole system with the control limitation. The closed system was proved to be input-to-state stable under certain conditions. To accurately predict the unsteady aerodynamics in the post-stall maneuver controller designing, the overload measurement was used to solve the aircraft aerodynamic force, and the differential equation model was developed to compute the unsteady aerodynamic moment. The control effect of the proposed controller is nearly independent of the actuator bandwidth due to the inclusion of actuator model, and the lag effect from the dynamic response of the actuator is effectively attenuated. The valid prediction of the unsteady aerodynamics is also helpful to improve the quality of the post-stall maneuver.