Analiza performansi električnog aviona

Haber-Zelanto, David (2018) Analiza performansi električnog aviona. = Performance analysis of electric aircraft. Undergraduate thesis , Sveučilište u Zagrebu, Fakultet strojarstva i brodogradnje, UNSPECIFIED. Mentor: Vrdoljak, Milan.

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Abstract (Croatian)

Tema ovog završnog rada jest analiza performansi potpuno električnog akrobatskog zrakoplova u horizontalnom letu i penjanju kao i usporedba istih s performansama ekvivalentnog aviona sa klipnim motorom. Također se procjenjuje otpor i računaju značajke pogonskog sustava potrebne za samu analizu. Analizirani zrakoplov i njegove karakteristike usvojeni su po uzoru na trenutno vrlo atraktivan i zanimljiv, potpuno električni zrakoplov-Extru 330LE, dok model zrakoplova s kojim se on uspoređuje nalikuje ravnopravnoj Extri 330LX. Nakon prikupljanja dostupnih podataka o performansama i značajkama oba aviona usvojena je polazna geometrija te je s obzirom na nju, procijenjen koeficijent otpora. Zatim su određene značajke pogonskog sustava s obzirom na faktore koji na njih utječu te su dobivene performanse i uspoređene, kako međusobno između dvaju različito pogonjenih aviona tako i sa polaznim performansama i postignućima stvarnih zrakoplova Extre 330LE i Extre 330LX. Performanse zrakoplova izračunate su metodom ukupne energije, za avion u horizontalnom letu te pomoću jednadžbi gibanja za središte mase zrakoplova, za avion u penjanju. Rezultati analiza uključuju ovojnicu leta sa svim pripadajućim ograničenjima te minimalno vrijeme penjanja zrakoplova.

Abstract

Topic of this bachelor thesis is the performance analysis of a fully electric, acrobatic aircraft in horizontal flight and climbing, as well as the comparison of the same with the equivalent aircraft powered by a piston engine. Beside estimation of the drag, features of the propulsion system required for this analysis are also modelled. Analysed aircraft and its characteristics are based upon currently very attractive and interesting, fully electric aircraft-Extra 330LE, which is compared to the model of equally capable aircraft Extra 330LX. After collecting available performance data, achievements, and features of both planes, initial geometry is adopted and drag coefficient is estimated. Then, the features of the propulsion system are determined as well as performance results which are then compared not just between two differently powered planes, but also to the initial performance and achievements of the actual Extra 330LE and Extra 330LX aircraft. Aircraft performance is calculated using the total energy method, for a plane in a horizontal flight, and with use of the equations of motion for the center of gravity of an aircraft in climbing regime. The analysis results include the flight envelope of the aircraft with all relevant limits as well as minimum time to climb performance.

Item Type: Thesis (Undergraduate thesis)
Subjects: TECHNICAL SCIENCE > Aviation, rocket and space technology
Divisions: 1300 Department of Aeronautical Engineering > 1320 Chair of Aircraft Dynamics
Date Deposited: 01 Mar 2018 11:39
Last Modified: 06 Mar 2018 13:54
URI: http://repozitorij.fsb.hr/id/eprint/8492

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