A control method used to design the flight control system for a supermaneuverable aircraft is presented, which involves the dynamic inversion and Fuzzy PD theories. The nonlinear model of a super- maneuverable aircraft with thrust vector control (TVC) is established; The singular perturbation theory is used to separate the dynamics into fast and slow sub-systems; The nonlinear dynamic inversion is applied to design the control laws of the two sub-systems separately; Fuzzy PD control is used to compensate the system inversion error. To evaluate the control performance, the maneuver generator is designed to simulate the pilot inputs. The simulation results show that the control law can ensure the stability of the closed-loop system, and tracks the inputs well under the conditions of high angle of attack.
['Xinmin Wang', 'Rong Xie', 'Yan Li']
Nonlinear Controller Design for a Supermaneuverable Aircraft