Introducing and evaluation of a new propulsion system composed of solid oxide fuel cell and downstream cycles; usage in Unmanned Aerial Vehicles

Abstract

Recently, Unmanned Aerial Vehicles (UAVs) with propulsion systems based on fuel cells have led to increased flight endurance and fuel economy. However, due to the limited operation of propulsion systems designed with alone fuel cells, the integration of fuel cells with other power generators can be used. This article attempts to provide a conceptual model of a new solid oxide fuel cell based-propulsion system that is cascaded with thermionic and thermoelectric generators. The fuel cell produces power and heat by receiving hydrogen fuel and oxidant. The required heat of thermionic and thermoelectric generators is supplied by the dissipative heat of the fuel cell and the dissipated heat of thermionic, respectively. The objective of this article is to determine the necessary electricity of a small UAV under mission profile. The conceptual design and structure of the proposed propulsion system (for use in a small drone) is new. In addition, the results presented do not correspond to the same literature. Results showed that the proposed propulsion system is capable of producing 481.3 W of power with an overall efficiency of 46.7%. In addition, UAV needs 1110.3 W of electricity under the desired mission profile. Five various sizing of the propulsion system to provide the necessary electricity of an UAV are discussed.