Naslov
Modelling and control of hybrid propulsion systems for multirotor unmanned aerial vehicles

Autori
Krznar, Matija

Vrsta, podvrsta i kategorija rada
Ocjenski radovi, doktorska disertacija

Fakultet
Fakultet strojarstva i brodogradnje

Mjesto
Zagreb

Datum
30.10

Godina
2020

Stranica
183

Mentor
Pavković, Danijel

Ključne riječi
Multirotor Unmanned Aerial Vehicle ; Hybrid Multirotor Propulsion ; Hybrid–electric power unit ; Identification and Modelling of multirotor propulsion ; Internal combustion engine - electrical generator set, DC–DC converter ; Lithium–Polymer battery

Sažetak
Unmanned Aerial Vehicles (UAV) are categorized as autonomous or remotely con- trolled aircraft that hold a many favourable features allowing them a wide range of useful applications. In order to successfully complete a flight mission, the aircraft must com- ply with the required flight performance indices. Aircraft performance depends strongly on the propulsion system and therefore different flight characteristics require different propulsion implementations. In contrast to well–known benefits of UAVs utilisation, in particular multirotor type of UAV, there is one major drawback regarding the on–board available energy. Most common electrically powered aircraft can last in the air for 15 to 30 minutes, while the best ones may last up to 60 minutes. Therefore, to overcome the aforementioned drawbacks of purely– electric energy source in multirotor aircraft, alternative propulsion systems combining two different energy sources (hybrid power systems) are considered. In this work, a methodological approach to the design of a hybrid propulsion unit for multirotor aircraft consisting of an internal combustion engine, electricity generator and electrochemical battery is described. For this purpose, analysis and modelling of individual components of the propulsion system have been carried out. Physical parameters of dynamic models are identified by means of experimental measurements. Based on the obtained data, a detailed model of a hybrid electrical propulsion configuration was proposed and suitable control strategies for the hybrid power system have been designed. The proposed control system design methodology has been verified by exhaustive computer simulations and experimentally by using different experimental setups.

Izvorni jezik
Engleski

Znanstvena područja
Strojarstvo, Zrakoplovstvo, raketna i svemirska tehnika

POVEZANOST RADA