Integracija sistema gorivnih celic v akrobatsko letalo

magistrsko delo magistrskega študijskega programa II. stopnje Strojništvo

Rok Markovič (Author), Mitja Mori (Mentor)

Abstract

V zaključnem delu smo raziskali uporabo vodika v letalstvu, natančneje aplikaciji gorivnih celic in shranjevanja vodika v akrobatskem letalu. Na podlagi pridobljenih podatkov, za sklad gorivnih celic in ostalih pomožnih komponent, smo postavili enostaven numerični model za preračun masnih in energijskih tokov. Pri tem se je upoštevala začetna zahteva po vsaj 300 kW moči na gredi elektromotorja in trajanju leta 5 min. Z uporabo 3D modelirnika smo v obstoječ okvir akrobatskega letala z motorjem na notranje zgorevanje umestili vse komponente potrebne za predelavo akrobatskega letala. Dimenzije in mase predvidenih komponent so povzete iz specifikacij komercialno dosegljivih produktov. Na podlagi izdelanega modela smo ocenili končno maso in določili težišče obravnavanega sistema. Na koncu smo podali še predloge možnih izboljšav.

Keywords

magistrske naloge;vodik v letalstvu;gorivne celice s protonsko izmenjevalno membrano;skladiščenje vodika;pomožni sistemi;akrobatsko letalo;integracija sistema gorivnih celic;

Data

Language:	Slovenian
Year of publishing:	2024
Typology:	2.09 - Master's Thesis
Organization:	UL FS - Faculty of Mechanical Engineering
Publisher:	[R. Markovič]
UDC:	629.7:62-611-546.11(043.2)
COBISS:	219653891
Views:	187
Downloads:	281
Average score:	0 (0 votes)
Metadata:

Other data

Secondary language:	English
Secondary title:	Integration of a fuel cell system in an acrobatic aeroplane
Secondary abstract:	In the master thesis, we investigated the use of hydrogen in aviation, specifically the application of fuel cells and hydrogen storage in aerobatic aircraft. Based on the data obtained for the fuel cell stack and other auxiliary components, a simple numerical model was built to calculate the mass and energy fluxes. We considered the initial requirement of at least 300 kW of power at the electric motor shaft and a flight duration of 5 min. Using a 3D modeler, all the components required to convert the airplane were fitted into the frame. The dimensions and masses of the intended components are taken from the specifications of commercially available products. Based on the model, the final mass was estimated and the center of gravity of the system was determined. Finally, suggestions for possible improvements are given.
Secondary keywords:	master thesis;hydrogen in aviation;proton exchange membrane fuel cells;hydrogen storage;auxiliary systems;acrobatic aircraft;fuel cell system integration;
Type (COBISS):	Master's thesis/paper
Study programme:	0
Embargo end date (OpenAIRE):	1970-01-01
Thesis comment:	Univ. Ljubljana, Fak. za strojništvo
Pages:	XX, 50 str.
ID:	25059963