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undergraduate thesis
Umjeravanje termometra zrakoplova Pilatus PC-9 M
Zagreb: University of Zagreb, Faculty of Transport and Traffic Sciences, 2020. urn:nbn:hr:119:948376
Bukvić, Marino
University of Zagreb
Faculty of Transport and Traffic Sciences
Division of Aeronautics
Department of Aeronautics

Institutional repository: Faculty of Transport and Traffic Sciences

Cite this document

Bukvić, M. (2020). Umjeravanje termometra zrakoplova Pilatus PC-9 M (Undergraduate thesis). Zagreb: University of Zagreb, Faculty of Transport and Traffic Sciences. Retrieved from https://urn.nsk.hr/urn:nbn:hr:119:948376

Bukvić, Marino. "Umjeravanje termometra zrakoplova Pilatus PC-9 M." Undergraduate thesis, University of Zagreb, Faculty of Transport and Traffic Sciences, 2020. https://urn.nsk.hr/urn:nbn:hr:119:948376

Bukvić, Marino. "Umjeravanje termometra zrakoplova Pilatus PC-9 M." Undergraduate thesis, University of Zagreb, Faculty of Transport and Traffic Sciences, 2020. https://urn.nsk.hr/urn:nbn:hr:119:948376

Bukvić, M. (2020). 'Umjeravanje termometra zrakoplova Pilatus PC-9 M', Undergraduate thesis, University of Zagreb, Faculty of Transport and Traffic Sciences, accessed 28 December 2024, https://urn.nsk.hr/urn:nbn:hr:119:948376

Bukvić M. Umjeravanje termometra zrakoplova Pilatus PC-9 M [Undergraduate thesis]. Zagreb: University of Zagreb, Faculty of Transport and Traffic Sciences; 2020 [cited 2024 December 28] Available at: https://urn.nsk.hr/urn:nbn:hr:119:948376

M. Bukvić, "Umjeravanje termometra zrakoplova Pilatus PC-9 M", Undergraduate thesis, University of Zagreb, Faculty of Transport and Traffic Sciences, Zagreb, 2020. Available at: https://urn.nsk.hr/urn:nbn:hr:119:948376

Metadata
TitleUmjeravanje termometra zrakoplova Pilatus PC-9 M
Title (english)Pilatus PC-9 M Thermometer Calibration
AuthorMarino Bukvić
MentorJurica Ivošević (mentor)
Committee memberTino Bucak (predsjednik povjerenstva)
Committee memberDoris Novak (član povjerenstva)
Committee memberTomislav Radišić (član povjerenstva)
GranterUniversity of Zagreb
Faculty of Transport and Traffic Sciences
(Division of Aeronautics)
(Department of Aeronautics)
Zagreb
Defense date and country2020-09-15, Croatia
Scientific / art field,
discipline and subdiscipline		TECHNICAL SCIENCES
Traffic and Transport Technology
Air Traffic
Abstract
Sustavi praćenja temperature u zrakoplovu sastoje se od termometara vanjske temperature i termometara temperature motora. Najzastupljeniji termometri vanjskog zraka su otporski, dok su u motoru najčešće termočlanci. U zrakoplovu modela Pilatus PC-9 (M) u uporabi je više sustava praćenja temperature. Na desnom krilu letjelice nalazi se senzor za vanjsku temperaturu, odnosno otporski termometar, a termometri u motoru su paralelno spojeni termočlanci „K-tipa“. Oba sustava su potrebna za regulaciju radne temperature te s obzirom na trošljivost materijala i drugih parametara poput promjene tlaka postoji opasnost od gubljenja funkcije ili kakvih drugih neispravnosti. Stoga je potrebno redovito provoditi test ispravnosti, točnije izlagati senzor ledu i približno dvije minute provjeravati smanjivanje temperature na prikazniku. Ako sve radi ispravno, temperatura će opadati prema logaritamskoj funkciji te će se na temperaturi ispod +4 °C uključiti indikator koji upozorava pilota na potrebu za odgovarajućim prilagodbama rada motora i drugih sustava. Ovakav praktični postupak proveden je u ovome radu.
Abstract (english)
The systems of tracking temperature in an aircraft are composed of outside temperature thermometers and engine temperature thermometers. Resistance thermometers are the most common outside temperature thermometers, while most common engine thermometer is a thermocouple. The aircraft Pilatus PC-9 (M) is equipped with several temperature tracking systems. The outside air temperature sensor is a resistence thermometer situated on the right wing of the craft, while the engine thermometers are composed of a parallel connected “K-type” thermocouples. Both of the systems are crucial for operating temperature regulation and due to the specific wear of the material and similar parameters like change of pressure, there is a risk od loss of function or any other possible malfunction. Therefore, it’s necessary to regulary perform a test of functionallity exposing the sensor to ice and observe as the temperature drops for approximately two minutes. If it works properly, the temperature will decrease logarithmically. As the temperature drops below +4 °C an indicator should activate as a warning to the pilot of the need for appropriate adjustments. Such a practical procedure was carried out in this paper.
Keywords
Keywords (english)
Languagecroatian
URN:NBNurn:nbn:hr:119:948376
Study programmeTitle: Aeronautics
Study programme type: university
Study level: undergraduate
Academic / professional title: sveučilišni/a prvostupnik/prvostupnica (baccalaureus/baccalaurea) inženjer/inženjerka aeronautike (sveučilišni/a prvostupnik/prvostupnica (baccalaureus/baccalaurea) inženjer/inženjerka aeronautike)
Type of resourceText
File originBorn digital
Access conditionsOpen access
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Created on2020-10-22 14:08:58