Design and Modeling of VTOL Tri Tilt-rotor Aircraft

Abstract

Rotary wing aerial vehicles have the capability to vertically take-off and land (VTOL); they have better stability while hovering. On the other hand, conventional fixed wing aircrafts offer greater endurance and higher speed. This article focuses on the development of hover model of a VTOL tri- rotor aerial vehicle, with front rotors having tilting mechanism; combining the aforementioned characteristics of rotary wing and conventional aerial vehicles. This dynamic model of a tri tilt-rotor VTOL aerial vehicle has been developed using force and moment equations, with throttles and tilt angles as input. The response of the Unmanned Aerial Vehicle (UAV), in hover mode, is presented with the help of Matrix Laboratory (MATLAB) simulations and responses of angular velocity with and without linear control are compared in MATLAB simulations.