Compared with the conventional aerodynamic control, the aerodynamic resistance and heating can be reduced if a flight vehicle is controlled by adopting mass moving control under condition of flying at a high speed. By so doing the maneuverability and agility of vehcles can be enhanced greatly to provide qualifications for the improvement of the control efficiency and precision of the vehicles. In this paper, taking an interception missile flying at the last stage as a control target, based on the coupled nonlinear system of the missile constructed math model, in view of the influefnce of the aerodynamic parameters and that of the indeterminate factors of the collectivity parameters, and the chattering of the system in the control process , a quick terminal sliding mode control system is developed via backstepping and integral. Through the stability analysis and the simulation of the masses locomotion, the results show that the method is effective and feasible.