Determination of external power factors influencing un-manned aerial vehicle of 'flying wing' type

This article touches upon the issue of determination of external force factors influencing an unmanned aerial vehicle or drone in critical flight modes for further transition to the full-scale engineering development. A brief review of the design of the developing vehicle is given. A simplified three-dimensional model is created. On the basis of the 3d model and with the help of the FloEFD computer complex, the aerodynamic analysis of the chosen design of the developed unmanned aerial vehicle is carried out. The dependences of the available speed and disposable tangential overloads of flight acceleration are obtained. The minimum permissible horizontal flight acceleration is calculated. The aerodynamic coefficients of the used wing profile are given. The value of the available tangential overload for different flight speeds is defined. The relation of the maximum trajectory angle of inclination against the flight speed when flying above the ground is calculated. The minimum allowable catapulted take-off speed is calculated. This speed allows determining an allowable trajectory angle of the incline for the rectilinear altitude gain. The pressure distribution over the outer surface of the fuselage and the wing consoles of an unmanned aerial vehicle is obtained. The value of the acting axial force is calculated for take-off modes with different angles of inclination of the trajectory and for a horizontal straight-line flight at a constant speed.