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A variety of control systems have been proposed for aircraft autopilotsystems. Traditional approaches such as proportional controller andconventional PID (CPID) controller are widely used. PID controller has a goodstatic performance especially for linear and time-invariant systems, but a weakdynamic performance and discouraging function on nonlinear, time-varying, anduncertain systems. Fuzzy control theory can improve dynamic response in variousconditions of system performance. This paper designs fuzzy self-tuning PID(FSPID) controller to improve disadvantages of conventional PID in aircraftautopilots. We apply proposed controller to pitch angle of aircraft then theabilities of proposed controller will be compared to the conventional PID andproportional controller. Inner feedback loop acts as oscillation damper intraditional schemes, but here is removed to compare the capabilities of Fuzzyself-tuning PID, conventional PID, and proportional controller. Based on thesimulations, both of Conventional and Fuzzy self-tuning PID controllers canproperly damp oscillations in lack of the inner feedback loop, but proportionalcontroller cannot do. Then short-period approximation is assumed to assess thefunction of FSPID and CPID controllers in confront with abrupt and continuousdisturbances, in addition to inappropriate tuning of parameters. Simulationresults of short-period approximation show a better anti-disturbance functionfor Fuzzy self-tuning PID compare to the conventional type. Fuzzy self-tuningPID can tune the PID parameters for achieving the optimal response in view ofspeed, overshoot, and steady-state error in conditions of inappropriate tuningof PID parameters, based on the results of simulation in short-periodapproximation, the proposed controller can adaptively improve the systemresponse by on-line setting of PID parameters.

Design of Fuzzy self-tuning PID controller for pitch control system of aircraft autopilot