Flight Control of a Tilt-Duct VTOL UAV

A new tilt-duct VTOL UAV concept is proposed. The main characteristics of this UAV are presented and some results are given. The flight mechanics equations for the tilt-duct VTOL UAV are derived. Trim flight conditions at various flight regimes are obtained. For this purpose a trim program is written which minimizes a cost function. Various trimmed flight conditions for hover, transition and cruise are obtained and the airplane stability at these particular flight conditions is discussed. The automatic flight control system designed for transition flight mode is presented in details. The control method for other flight phases is also given.