Performanse ultralakog zrakoplova s hibridno-električnim pogonskim sustavom

undergraduate thesis

• Title: Performanse ultralakog zrakoplova s hibridno-električnim pogonskim sustavom : HIBRIDNO ELEKTRIČNI POGON ZRAKOPLOVA : HIBRIDNO ELEKTRIČNI POGONSKI SUSTAV KOD ULTRALAKOG ZRAKOPLOVA : PRIMJENA HEP SUSTAVA : ZAKLJUČAK
• Title (english): Performance of the ultralight aircraft with hybrid-electric propulsion system
• Author: Petar Šagud
• Mentor: Milan Vrdoljak (mentor)
• Committee member: Milan Vrdoljak (predsjednik povjerenstva)
• Committee member: Ivica Smojver (član povjerenstva)
• Committee member: Darko Ivančević (član povjerenstva)
• Granter: University of Zagreb; Faculty of Mechanical Engineering and Naval Architecture; Zagreb
• Defense date and country: 2020-02-26, Croatia
• Scientific / art field, discipline and subdiscipline: TECHNICAL SCIENCES; Aviation, Rocket and Space Technology

Abstract

Ovaj rad se zasniva na razmatranju ultralakog zrakoplova sa implementiranim hibridno
električnim pogonskim sustavom. Radu se pristupilo na način da se na početku objasnila
tehnologija hibridnog pogona i njeni ključni elementi. Opisivanjem raznih konfiguracija
pogona objasnili smo zašto je za zrakoplovstvo povoljna paralelna hibridna konfiguracija.
Daljnja analiza se sastojala od prikupljanja podataka iz analize leta zrakoplova. Slijedio je
izračuna doleta zrakoplova sa različitom količinom goriva. Rezultati doleta nam govore da je i
manje goriva dovoljno za potrebe ultralakog zrakoplova na hibridni pogon. Usporedbom leta
sa tri različite brzine vidjeli smo kako nam pri manjoj brzini višak snage omogućuje brže
punjenje baterija no uzrokuje i veću potrošnju. Rezultati nam također pokazuju da punjenje
baterija nema značajan utjecaj na potrošnju te se opravdava punjenje baterija klipnim motorom
koje ćemo koristiti u drugim fazama leta, poput leta većom brzinom ili za potrebe penjanja.
Dodatno smo izračunali dolet koji bi se mogao prijeći koristeći samo elektromotor nakon
potrošnje goriva i vidjeli značajno povećanje doleta.

Abstract (english)

This paper analyses an ultralight aircraft with an implemented hybrid electric propulsion
system. The first step in our approach was explaining the technology behind hybrid electric
propulsion and its key elements. During this explanation we validated the use of parallel electric
systems in aerospace applications. Further analysis began with the gathering of data on the
selected aircraft collected from the analysis of the flight. Next came the range calculations
comparing different fuel amounts, from which we concluded that the less amount of fuel was
sufficient for the needs of an ultralight hybrid aircraft. We then compared the flight with three
different speeds and saw an increase in specific fuel consumption on lower speed flights, but
the recharge rate was higher. The charging of the batteries hasn’t shown a significant increase
in fuel consumption, so we justified the use of an internal combustion engine for this purpose.
The batteries will be discharged in other fazes of flight, such as climb out or flying at a higher
velocity. We additionally calculated the range increase in a situation where we continue flying
after using all of the fuel, using only an electric motor and saw a significant increase in range.

• Keywords: hibridno električni pogon; ultralaki zrakoplov; dolet
• Keywords (english): hybrid electric propulsion system; ultralight aircraft; range
• Language: croatian
• URN:NBN: urn:nbn:hr:235:989836
• Study programme: Title: Aeronautical Studies; Study programme type: university; Study level: undergraduate; Academic / professional title: sveučilišni/a prvostupnik/ prvostupnica (baccalaureus/baccalaurea) inženjer/inženjerka zrakoplovnog inženjerstva (sveučilišni/a prvostupnik/ prvostupnica (baccalaureus/baccalaurea) inženjer/inženjerka zrakoplovnog inženjerstva)
• Type of resource: Text
• File origin: Born digital
• Access conditions: Open access
• Created on: 2020-02-24 11:51:26