Aircraft pitch control design using LQG controller based on genetic algorithm

Designing a robust aircraft control system used to achieve good tracking performance and stable dynamic behavior against working disturbances problem has attracted attention of engineers. In this paper, pitch angle for is designed utilizing liner quadratic Gaussian (LQG) optimal controller technique with numerical tuning algorithm method in the longitudinal plane through cruising stage. Main design approach LQG includes obtaining best weighting matrices values using trial error that consumes effort takes more time, addition, there no guarantees obtain optimum elements. research, genetic (GA) optimize state determine their The proposed traditional optimized schemes are implemented Matlab simulation tool presented compared based on transient steady parameters. results reveal ability GA_LQG reject effect noises conventional system.