Tri-Tilting Rotor Fixed-Wing VTOL UAV: Dynamic Modelling and Transition Flight Control

This paper gives the dynamic modeling and design of a controller for autonomous Vertical take-off and landing (VTOL) Tri-Tilt rotor hybrid Unmanned Aerial Vehicle (UAV). Nowadays, UAVs have experienced remarkable progress and mainly categorized into fixed-wing UAVs and rotary-wing UAVs. The Tri Tiltrotor UAV models are derived mathematically using Euler's force and moment equations for VTOL to horizontal flight and vice-versa using MATLAB. The development of fully autonomous and self-guided UAVs would reduce the risk to human life. The applications consist of inspection of coasts, terrain, border, patrol buildings, rescue teams, police, and pipelines. A Proportional-Integral-Derivative control method is proposed for UAVs attitude and altitude stabilization. The results reveal that the controller accomplishes adaptability, robust performance and stability in the transition mode.