Abstract: The design of a flight control system for a supermaneuverable aircraft by means of nonlinear dynamic inversion was discussed in detail. First, the dynamics to be controlled are separated into fast and slow variables in terms of singular perturbation theory. The fast variables are the three angular rates and the slow variables are the angle of attack, sideslip angle, and bank angle. Then two dynamic inversion control laws are designed for the fast and slow variables respectively, the outputs of outer loops are used as the inputs of inner loops. The resulting control system is demonstrated using post-stall maneuver simulation, the simulation results show that the dynamic inversion control law achieves a high level performance in post-stall maneuver conditions.