Modelling and numerical analysis of attitude control flaps of a UAV

Quadcopters utilize propellers to generate thrust and propeller RPM is controlled to vary its attitude. The Ducted fan UAVs have a compact and protected design. Ducts provide a much better shield, and control over flight, thrust, and maneuverability and work really well for different specific mission requirements. Thrust vectoring techniques can be applied to the duct to produce side thrust, control maneuverability, and for better control over aircraft. Thrust vectoring can be used as primary means of attitude control. The aim of this research work is to design and perform simulations of a control slot-assisted propulsion system where thrust vectoring techniques are applied to control its attitude. CFD (Computational Fluid Dynamics) analysis was used to show variation in propulsive force with varying AOA (Angle of Attack). Numerical simulations performed help quantify the effectiveness of propulsion-assisted control on the Ducted Propeller model. From the results, the important performance parameters were found and compared. A suitable Airfoil was selected based on our objectives and requirements. Pressure, velocity contours, and lift force at various angles of attack were obtained which help to compare with control forces required to maneuver the drone.