Math model of UAV multi rotor prototype with fixed wing aerodynamic structure for a flight simulator

Abstract

This article presents the math modeling of a fixed wing Unmanned Aerial Vehicle (UAV) for a flight simulator, using a numerical method. The UAV is controlled through radio control or mission plan. The mathematical model contains a numerical approximation considering multiple Single Input Single Output (SISO) systems that related altitude, pitch, roll and yaw angle as an input parameters and yaw speed, x, y, z axis speed as output parameters. The signal analysis shows unpredictable behavior during manual controlled flight, but an acceptable stable group of data in controlled mission.