Optimal Control of Roll Axis of Aircraft Using PID Controller

Abstract

In this paper, the Proportional Integral Derivative (PID) controller is tuned using genetic algorithm. The optimally tuned controller is implemented in order to increase the stability and the performance of aircraft. The safety feature of flight system could be enhanced with the tuning of PID parameters of the controller for roll axis of any flight. The design of a mathematical model is necessary for describing the latitudinal roll axis of an aviation aircraft. The PID controller can be employed based on the dynamic as well as mathematical modelling of the aircraft system. The Zeigler Nichols (ZN) Method and Genetic Algorithm (GA) optimization technique are considered to tune the PID controller parameters. The fitness function considered for the optimization algorithm is an Integral Absolute Error (IAE) criterion. The MATLAB simulation result shows that the PID controller tuned by the GA method for aviation aircraft dynamics gives better results.