Design and implementation of fixed-wing MAV controllers

This paper deals with the experimental validation of a linear controller and two non linear controllers for a fixed-wing Miniature Air Vehicle (MAV). We are interested to realize an experimental analysis of these control techniques in order to validate the robustness and the performance of these controllers in presence of perturbations due to wind gusts using a reduced aerodynamic model. The controllers implemented are: Proportional Integral Derivative (PID) and backstepping. The results obtained by the sliding mode control (SMC) have been presented on simulations, each controller has been applied to the movement of altitude, yaw angle and roll angle of the fixed-wing MAV.