Folding wing morphing aircraft can alter their shape largely which causes the aerodynamic parameters change significantly. So the aerodynamic effects caused by the asymmetric morphing can be used for aircraft maneuver control as an assist to the conventional control, which can enhance maneuvering flight ability. The purpose of this paper is studying the asymmetric morphing control efficiency of a folding wing morphing aircraft. Firstly, the nonlinear dynamic equations and aerodynamic model that can depict the full morphing process are derived. Then, an asymmetric morphing control model is proposed based on the asymmetric morphing control method. Finally, by comparing with the efficiency of conventional control and the dynamic response of simulation, we find the maximum effective interval of the asymmetric morphing control. The results show that the efficiency of asymmetric morphing control is higher at lower flight speeds, and the asymmetric morphing control can provide the highest roll handling efficiency near the reference folding angle of 90°.