Based on the sliding mode control strategy, the morphing-aided maneuver problem of the folding-wing aircraft is studied. The relationship between the aircraft folding angle and the aerodynamic parameters is analyzed. The wing folding angle is viewed as an extra control input and the dynamic model of the morphing-aided maneuver is constructed. For the nonlinearity and the hybrid disturbances of the system, a novel feedback linearization-based non-singular dynamic terminal sliding mode control (NDTSMC) approach is proposed. NDTSMC can restrain the uncertainty of the foldingwing aircraft and complete the attitude tracking control. Simulation results show that the control precision and the robustness of the morphing aircraft are improved by NDTSMC, with a better chattering elimination. It is also shown that the folding-wing aircraft with morphing-aided maneuver has higher maneuverability and disturbance rejection capability when compared to the traditional aircraft.