Modelling and simulation of an aeroelastic airfoil using LQR, LQG/LTR, H2 and H∞ controllers

The recent development in the aeronautic domain is characterized by a high flexibility aircraft which results in a stronger interaction between the flight control system, structural and aerodynamic. The robust control is needed to meet the desired performance specification. This paper presents a robust control of flexible aircraft wing using LQR, LQG/LTR and H
₂
/ H
_∞
techniques. In the first step a linearized model of an aeroelastic wing is presented and a theory of robust control is developed. At the end an application of simulation show the closed loop system is guarantied to be stable and meet the performance requirements.