Design and aerodynamic analysis of a VTOL tilt-wing UAV

The aerodynamic design and analysis of an Unmanned Air Vehicle, capable vertical take-off landing by employing fixed four rotors on the tilt-wing two tilt-tail, will be presented in this study. Both main wing horizontal tail can tilted 90°. During VTOL, transition forward flight, thrust forces have been employed. Different flight conditions, including effects angle attack, side slip, tilt control surfaces deflection changes, studied with CFD analysis. For a Tilt-Wing UAV, there are challenges like high non-linearity, vulnerability to disturbances during hover transition, cross-coupling between three axes, very low time double amplitude open-loop system. Therefore, has done detail considering especially phase envelope.