Design, construction and test of the propulsion system of a solar UAV

Abstract

[EN] Pollution problems and the need to achieve a lower oil dependency have given solar and electric technologies, an important role in propulsion systems, from automotive to, more recently, aviation industry. This thesis contains the conceptual design of a hybrid propulsion system of an unmanned aerial vehicle (UAV). The solar-powered plant aimed at a small UAV with a wingspan of 4.5 m and an approximate weight of 5 kg, with a specific civil surveillance mission. Its architecture is completely different from the conventional methods of propulsion. From all the different efficiencies of the components that influence the use of energy, the most important factor is the solar irradiance and the ability that the solar panels have to harvest that energy, that is, their efficiency. The design and sizing of the different components of the propulsion system depends on the available energy stored in the battery or the generate power in the solar panels. As solar radiation is different throughout the year, different combinations of batteries, solar panels or hybrid systems are studied. The propulsion system is designed according to the requirements of energy available and energy required, and after appropriate design, the different components of the propulsion system are selected following design criteria. In the end, a road-map to achieve the necessary tests and check the proper functioning of the designed system will be established.