Optimizing Electric Propulsion Systems for Unmanned Aerial Vehicles

Abstract

Design of an electric propulsion system for an unmanned aerial vehicle incorporates various disciplines such as the propeller's aerodynamic and structural properties, characteristics of the electric system, and characteristics of the vehicle itself. This makes the design of this propulsion system a multidisciplinary design optimization task. Although the present propeller model is based on previous derivations that are described very briefly, new models of the electric motor and battery pack, which are based on examining existing products on the market, are described in more detail. The propeller model and a model of the electric system, together with various optimization schemes, are used to design optimal propulsion systems for a mini unmanned aerial vehicle for various goals and under various constraints. Important design trends are presented, discussed, and explained. Although the first part of the investigation is based on typical characteristics of the electric system, the second part includes a sensitivity study of the influence of variations of these characteristics on the optimal system design. = vehicle mass without the propulsion system P in = electric system input power P out = motor output power P out-max = maximum motor output power R = propeller radius R a = motor resistance r = radial coordinate S W = wing area= driver efficiency P = propeller efficiency P-ideal = ideal propeller efficiency S = electric system efficiency a = air density = maximal von Mises stress = rotational speed

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