Aircraft Dynamics Using Fuzzy-PID Controller Design

During abnormal flight conditions, performance of aircraft depends upon design of flight control systems. This work deals with developing an intelligent control technique for aircraft dynamics during abnormal flight conditions. Fuzzy logic based PID (proportional-integral-derivative) control technique is developed for aircraft dynamics. Mathematical modeling is carried out for longitudinal and lateral dynamics of an aircraft. Fuzzy logic rules are developed for tuning gains of PID controller. Simulation is carried out for flight condition of supersonic cruise level flight. The performance of self-tuned fuzzy-PID and PID controller is studied in comparison for both longitudinal and lateral models of the aircraft.