Abstract: The design of the flight control system with the vectored thrust is discussed. The flight state variables are separated into the fast and the slow state variables based on their transient responses. Nonlinear dynamic inversion is adopted to design them separately. The simulations of the flight of the fighter at high angle-of-attack and the attacking process of the designed flight control law combined with the integrated flight/fire control system on the 6-DOF aircraft equation are made. The results prove that the integrated flight/vectored thrust control system can implement the flight at high angle-of-attack and meet the requirement of the integrated flight/fire control system. The adopted method is promising in the engineering application.