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Tytuł:
Automation of Aircraft Fatigue Life Estimation
Autorzy:
Gajek, Stanisław
Powiązania:
https://bibliotekanauki.pl/articles/24201179.pdf
Data publikacji:
2022
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
Aircraft Fatigue
Rainflow Cycle Counting
Load Spectra
UAV
Opis:
The fatigue is an important factor in aircraft operation. A correct estimation of structure fatigue life is crucial for user and payload safety. However, due to high amount of data gathered during a typical recording of load spectra for different types of flights, the overall results become prone to human error. The paper describes development of a software able to perform an automated, in-depth analysis of data recorded with onboard accelerometers. Using the Rainflow Cycle Counting method, it transforms received data points into a Markov matrix. The prepared array is then recalculated into a half-cycle matrix, which can be collapsed into scalar value of fatigue level using the Palmgren-Miner rule. The method was tested with loads recorded during a typical flight conducted according to the Polish NSTS-06 flight scenario and simulated camera mounting fixed to a multirotor.
Źródło:
Fatigue of Aircraft Structures; 2022, 14; 83--103
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Review of Aeronautical Fatigue Investigations in Poland (2013-2014)
Autorzy:
Niepokólczycki, A.
Leski, A.
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/97803.pdf
Data publikacji:
2016
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
fatigue of aircraft structures
Opis:
This review was presented on the 34 Conference of the International Committee on Aeronautical Fatigue and Structural Integrity, Helsinki, Finland, June 1-2, 2015. It contains description of main works and investigations in fatigue of aircraft structures performed in Poland during the years 2013 and 2014.
Źródło:
Fatigue of Aircraft Structures; 2016, 8; 5-48
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Estimation of Loads Acting on Flaps of the Su-22 Aircraft for Fatigue Tests
Oszacowanie obciążenia klap samolotu Su-22 na potrzeby prób zmęczeniowych
Autorzy:
Kowaleczko, G.
Leski, A.
Zieliński, W.
Powiązania:
https://bibliotekanauki.pl/articles/403695.pdf
Data publikacji:
2016
Wydawca:
Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:
mechanics
aircraft fatigue tests
aerodynamic loads
aircraft flap
mechanika
badania zmęczeniowe samolotów
obciążenia aerodynamiczne
klapy samolotu
Opis:
The paper presents the results of the calculation of forces acting on the flaps of the Su-22 aircraft during take-off and landing. Four different analytic and experimental calculation methods were used to increase the reliability of the obtained results. The results will be the basis for performance of fatigue testing of the flaps which are structural components of the aircraft wings. The tests will be performed as part of a wider research program aimed at the extension of the Su-22 aircraft service life.
W pracy przedstawiono wyniki obliczeń sił działających na klapy samolotu Su-22 podczas startu i lądowania. Wykorzystano cztery rożne analityczno-eksperymentalne metody obliczeniowe w celu zwiększenia wiarygodności otrzymanych rezultatow. Będą one stanowić podstawę do przeprowadzenia prob zmęczeniowych tych elementow konstrukcyjnych skrzydła samolotu. Proby te wykonane będą w ramach szerszego programu badań, mających na celu wydłużenie procesu eksploatacji samolotu Su-22.
Źródło:
Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa; 2016, 7, 3 (25); 87-112
2081-5891
Pojawia się w:
Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The Fatigue Life Assessment of PZL-130 Orlik Structures Based on Historical Usage Data
Autorzy:
Leski, A.
Klimaszewski, S.
Kurdelski, M.
Powiązania:
https://bibliotekanauki.pl/articles/97857.pdf
Data publikacji:
2009
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
aircraft structure
fatigue
usage profile
Opis:
Material fatigue is the basic factor limiting aircraft's durability. It comes from the fact that changing loads affect aircraft structure as well as from the fact that aircraft’s mass restrictions do not allow for diminishing stress to the level when material fatigue does not occur. Estimating fatigue durability of a particular structure as well as its actual fatigue damage degree is possible when the history of loads affecting the structure is known. Accuracy of loads monitoring influences the accuracy of indicated fatigue wear. In case of older structures, which have been maintained according to safe life principle, the number of hours have been commonly used as a fatigue wear indicator. After aircraft structure reaches flying time estimated by the produces, it is considered as fatigue wear and it is no longer in service. In case of a lack of results of loads spectrum measurements, results of tests conducted for other aircraft (of similar structure and assignment) can be used. For this purpose, average loads spectrum has been elaborated for particular aircraft groups, for example, HELIX, FELIX, FALSTAFF, ENSTAFF, TWIST(10). In the case of small aircraft, the data from FAA (2) report have been often used. This article describes the way of fatigue wear estimation for PZL-130 Orlik aircraft on the basis of historical data from flight recorders.
Źródło:
Fatigue of Aircraft Structures; 2009, 1; 131-139
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Full Scale Fatigue Test of New Undercarriage for Commuter Aircraft
Autorzy:
Brzęczek, J.
Gruszecki, H.
Pieróg, L.
Pietruszka, J.
Powiązania:
https://bibliotekanauki.pl/articles/97943.pdf
Data publikacji:
2012
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
fatigue testing
commuter aircraft
undercarriage
Opis:
Fatigue testing of the new main landing gear for the PZL M28 aircraft was conducted in Polskie Zakłady Lotnicze Sp. z o.o. in Mielec using MTS Aero 90-LT system. The test was conducted in a flight-by-flight manner with loads resulting from landing, taxiing, maneuvering and braking. The undercarriage structure is made of high tensile strength low alloy steel. FEM analyses were performed before the tests in order to find critical points and to obtain information about loads which may be neglected. During the test fatigue damage was observed, which led to splitting the test into two separate tests performed in independent rigs: the test of the undercarriage leg and the test of the shock absorber.
Źródło:
Fatigue of Aircraft Structures; 2012, 4; 70-75
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Comparative Analysis of the Load Spectra Recorded During Photogrammetric Missions of Lightweight Uavs in Tailless and Conventional Configurations
Autorzy:
Rodzewicz, Mirosław
Głowacki, Dominik
Hajduk, Jaroslaw
Powiązania:
https://bibliotekanauki.pl/articles/24201177.pdf
Data publikacji:
2022
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
load spectra
fatigue life
unmanned aircraft
photogrammetry mission
Opis:
The purpose of this article is to present the results of the investigation regarding the differences of the load spectra of two unmanned fixed-wing aircraft performing photogrammetry missions: X-8 (flying wing) and PW-ZOOM (conventional configuration). The focus was on the analysis of a number of load cycles for various load increments within the range of the operational loads. The load spectra were determined using the acceleration signal recorded in the autopilot logs as an input. This signal was transferred to the chain of local extreme values scaled in the form of discrete load levels, and then the transfer arrays were derived with use of the rainflow counting algorithm. On this basis, the incremental load spectra were determined for each flight. These load spectra were subjected to statistical analyses to determine the load spectra representative of the flight sessions in a few ways between non-conservative (i.e., focused on average load histories) and conservative (i.e., focused on the worst load histories observed during the flight session). Finally, the fatigue life was calculated by having the structural element of the assumed fatigue properties subjected to the load spectra of both airplanes. A large (exceeding one order of magnitude) difference in the number of load cycles for larger load increments in the analyzed load spectra was shown. This difference is related to the different dynamic characteristics of the two aircraft, in particular the gust response. As a result, there is a several-fold difference in fatigue life.
Źródło:
Fatigue of Aircraft Structures; 2022, 14; 114--134
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Influence of the cyclic hardening model on the results of the numerical analysis of fatigue life on example of the compressor blade
Autorzy:
Bednarz, Arkadiusz
Powiązania:
https://bibliotekanauki.pl/articles/245046.pdf
Data publikacji:
2019
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
fatigue life
compressor blade
aircraft engine
cyclic hardening
numerical analysis
Opis:
The main goal of the presented work is to determine the impact of the cyclic hardening model on the numerical results of the ε-N fatigue test. As an object of study, compressor blade (from PZL-10W helicopter engine) was used. The examined blade was made of EI-961 alloy. In numerical analysis, a geometrical model of the blade with a preliminary defect was created. Geometrical defect – V-notch was created on the leading edge. This defect was introduced in order to weaken the structure of the element and the possibility of observing the crack initiation process (in experimental tests). Material data to ε-N analysis, based on Manson-Coffin-Basquin equation, were estimated for Mitchell’s model. This model was built based on strength data provided by the steel producer. Based on three different models of cyclic hardening (Manson, Fatemi, and Xianxin), a number of load cycles were calculated. Load cycle during numerical analysis was represented as resonance bending with an amplitude of displacement equal to A = 1.8 mm. Obtained results were compared with experimental data. Additionally, the analytical model of ε-N fatigue (depending on the cyclic hardening) was prepared. All the work carried out has been summarized by a comprehensive comparative analysis of the results. Obtained results and dependencies can be used in the selection of an appropriate model of cyclic hardening in further fatigue tests of many aerospace elements.
Źródło:
Journal of KONES; 2019, 26, 2; 7-14
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Numerical Simulation of Fatigue Fracture of the Turbine Disc
Autorzy:
Witek, L.
Powiązania:
https://bibliotekanauki.pl/articles/97889.pdf
Data publikacji:
2012
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
aircraft engine
crack propagation analysis
finite element method
fatigue fracture
Opis:
This paper presents the results of the crack propagation analysis of an aircraft engine turbine disc. In the first part of the work the finite element method was used for calculation of the stress state and the stress intensity factor (SIF, KI, K-factor) in the turbine disc with an embedded quarter-elliptical corner crack, subjected to low-cycle thermo-mechanical fatigue. To refine the K-factor calculation, specially degenerated finite elements were used. These elements provide stress singularity suitable for the linear-elastic material of the disc. The performed calculations yielded the stress intensity factor KI for different crack sizes. Subsequently, ΔK parameter was determined as a difference of the KI values calculated for the turbine’s speeds equal to 6373 and 14200 RPM. Based on the Paris-Erdogan equation and the obtained ΔK values, the fatigue crack growth plot for the turbine disc subjected to complex thermo-mechanical loads was determined.
Źródło:
Fatigue of Aircraft Structures; 2012, 4; 114-122
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The study on algorithm for identification the fatigue crack length of compressor blade based on amplitude-frequency resonant characteristics
Autorzy:
Lichoń, D.
Bednarz, A.
Powiązania:
https://bibliotekanauki.pl/articles/243684.pdf
Data publikacji:
2017
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
fatigue failure
crack length
compressor blade
aircraft engine
failure identification algorithm
Opis:
The article is focused on building the algorithm for identification the fatigue crack length in the first stage of compressor blade of the helicopter PZL-10W turbo-shaft engine. The fatigue wear of compressor blade is a process in which the fatigue crack begins at the structural notch of the working part. For compressor blade, the crack starts at the leading edge and progress along the blade chord. Due to working conditions, the compressor blades are referred to as critical components. The helicopter rotor downwash can easily lift particles form the ground that may cause damages in the compressor section. Aircraft engines are designed so that the rotational speed of impeller remains below the resonant frequency. However, the pulsation of working medium or mechanical vibrations may cause temporary increase of vibration frequency. The appearance of structural notch combined with temporary increase of vibrations may initiate the fatigue failure. The works undertaken at the Department of Aircraft and Aircraft Engines, Rzeszow University of Technology provided a wide spectrum of research data of amplitude-frequency (A-F) characteristics of 1st stage of compressor blade. For different crack lengths, the fatigue tests of resonant frequency and asymmetry of A-F characteristics were acquired. The crack lengths were measured by fluorescent or infrared mapping method. The aim of the article is to develop the numerical method for identification of crack length of compressor blade basing on A-F characteristics. The studies on A-F characteristics in order to find correlations between crack length, resonant frequency and characteristics asymmetry were performed. The next step was to build the algorithm for identification the crack length when only A-F characteristic is known. The article contains the description of researches background, A-F characteristics unique features, algorithm detailed methods of work and sample use of algorithm in identification the crack length.
Źródło:
Journal of KONES; 2017, 24, 4; 157-164
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Some Comments on Fatigue Life Tests of Aircraft Cable Control Systems
Autorzy:
Brzęczek, Józef
Powiązania:
https://bibliotekanauki.pl/articles/2105148.pdf
Data publikacji:
2020
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
aircraft’s cable control systems
cable service life
cable fatigue tests
Opis:
Cable control systems are widely used in aircraft and gliders.This paper deals with the problem of collecting real loads acting cable control systems and cable tests preparation (load spectrum) and performance. The author proposes a method for defining real loads acting on control systems, preparing and carrying out fatigue tests of cables revealing symptoms of fretting. The fatigue tests results can be used to predict service life, to plan and prepare periodic and details inspections. This method could be used to increase service life of aircraft control cables and could help to replace the commonly used Time-Based Maintenance (TBM) strategy with the Damage Tolerance (DT).
Źródło:
Fatigue of Aircraft Structures; 2020, 12; 102--112
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Eddy current techniques for detecting hidden subsurface defects in multilayer aircraft structures
Autorzy:
Uchanin, Valentyn
Powiązania:
https://bibliotekanauki.pl/articles/36455560.pdf
Data publikacji:
2022
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
aircraft structure
subsurface defect
eddy current
fatigue crack
corrosion
operational frequency
repair patch
Opis:
In-service non-destructive inspection (NDI) is a very important part of the aircraft maintenance program that minimizes aircraft breakdowns due to the fracture of critical components. The eddy current (EC) NDI method is one of the most applicable methods for this purpose, due to its high sensitivity to fatigue cracks and corrosion damage in the main structural materials. In this paper, selective double differential type EC probes characterized by the enhanced possibility of detecting subsurface cracks initiated by fatigue or stress corrosion phenomena are presented. For different applications, a family of double differential type EC probes was developed with different sizes (from 5 to 33 mm) and different spatial resolutions. These types of probes are characterized by different operational frequencies in a wide frequency range (from 0.2 kHz to 1.0 MHz), high penetration depth and unique sensitivity to subsurface defects of different types (like elongated fatigue cracks or local corrosive pitting), and a high level of specific noise suppression concerned with the scanning inspection procedures. The EC probes proposed were investigated as effective tools for characteristic aircraft applications concerned with subsurface defect detection in multilayer structures, such as the detection of cracks in the second layer of a riveted two-layer structure or cracks initiated on the side surface of a multilayer structure with the suppression of the reinforcing hoop influence; the detection of subsurface defects in arc welding with a rough surface; the detection of cracks through repair patches fabricated from aluminum alloy or carbon fiber reinforced plastic, etc. These techniques create remarkable possibilities for the well-timed detection of dangerous damage without disassembling the aircraft structure or removing protective coating.
Źródło:
Transactions on Aerospace Research; 2022, 2 (267); 69-79
0509-6669
2545-2835
Pojawia się w:
Transactions on Aerospace Research
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Metodyka modelowania widma obciążeń zmęczeniowych dla kompozytowego samolotu AF-129
Methodology for modeling fatigue load spectrum for AF-129 composite aircraft
Autorzy:
Danilecki, S.
Leszczyński, P.
Powiązania:
https://bibliotekanauki.pl/articles/209407.pdf
Data publikacji:
2012
Wydawca:
Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:
lotnictwo
statek powietrzny
bezpieczny okres użytkowania
widmo obciążeń zmęczeniowych
trwałość zmęczeniowa
aviation
aircraft
safe period of use
fatigue loads spectrum
fatigue life
Opis:
W ramach niniejszej pracy opracowano metodykę modelowania widma obciążeń zmęczeniowych dla samolotu kompozytowego, przedstawiono charakterystykę obciążeń zewnętrznych struktury - założenia ogólne. Następnie, bazując na modelu użytkowania samolotu kompozytowego, wyodrębniono poszczególne tak zwane bloki, charakteryzujące kolejne etapy lotu samolotu. Należą do nich: 1. Blok startu-kołowania. 2. Blok wznoszenia. 3. Blok zakrętów o różnych kątach przechylenia. 4. Blok lotu poziomego. 5. Blok opadania-szybowania. 6. Blok lądowania-kołowania. Bloki te zostały szczegółowo omówione w ramach zaprezentowanej metodyki modelowania widma obciążeń zmęczeniowych. Omówienie zakończone zostało zbiorczymi zestawieniami liczby zmian obciążeń (cykli) od wartości współczynnika obciążeń n dla dwóch rozpatrywanych wariantów. Z kolei dokonano oceny uproszczeń sposobu przyjmowania wartości współczynnika zwielokrotnienia próby trwałości zmęczeniowej oraz oceny sposobu przyjmowania wartości obciążenia podstawowego. Na zakończenie opracowano uwagi o sposobie prowadzenia badań.
As a part of this work, a methodology of modeling fatigue load spectrum for composite aircraft was developed. The characteristic of external loads of the structure - general assumptions was presented. Then, basing on the use of aircraft composite model, so-called, individual blocks, characterizing successive stages of the aircraft flight were separated. These are: 1. Starting block. 2. Take up block. 3. The block of corners with different angles of tilt. 4. Horizontal flight block. 5. Falling-gliding block. 6. Landing block. These blocks were discussed in detail in the presented methodology for modelling the fatigue loads spectrum. Discussion has been completed with summary combinations of the number of load changes (cycles) of the load factor n for the two options under consideration. The simplification of the method was evaluated taking the multiplication factor of the fatigue life test and evaluates how to take the base load. In conclusion, the comments on a way of research conducting are presented.
Źródło:
Biuletyn Wojskowej Akademii Technicznej; 2012, 61, 4; 197-229
1234-5865
Pojawia się w:
Biuletyn Wojskowej Akademii Technicznej
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Aspekty metrologiczne bezdotykowego diagnozowania wirujących łopatek sprężarki
Metrological aspects of non-contact roating blade measurements
Autorzy:
Witoś, M.
Kowalski, M.
Powiązania:
https://bibliotekanauki.pl/articles/209146.pdf
Data publikacji:
2008
Wydawca:
Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:
odstęp czasu
nierównomierne próbkowanie
łopatki
zmęczenie
silniki lotnicze
diagnostyka silników lotniczych
tip timing
nonuniform sampling
blades
fatigue
aircraft engine
diagnosis of aircraft engine
Opis:
Przedstawiono podstawy teoretyczne stosowania elastycznego znacznika fazy - wirującej i drgającej łopatki sprężarki - do kompleksowego diagnozowania turbinowego silnika lotniczego (metoda tip timing). Wskazano na rolę numerycznych metod analizy w rozdzieleniu składowych sygnału pomiarowego (aperiodycznej i oscylacyjnej) oraz potrzebę weryfikacji istniejących algorytmów analizy danych, pochodzących z nierównomiernego próbkowania. Omówiono 15-letnie spostrzeżenia eksploatacyjne stosowania metody na samolotach TS-11 "Iskra".
The paper presents theoretical background of using elastic key phasor-rotating and vibrating compressor blade - for complex jet engine diagnosis (tip timing method). The role of numerical methods of measurement signal decomposition onto parts (aperiodic and oscillation) is pointed. It also shows the need of existing algorithms (from irregular sampling) verification. Fifteen years' service knowledge of using mentioned method aboard T-11 "Iskra" is presented.
Źródło:
Biuletyn Wojskowej Akademii Technicznej; 2008, 57, 2; 289-299
1234-5865
Pojawia się w:
Biuletyn Wojskowej Akademii Technicznej
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Methods of counting aircraft turbine engines operating cycles
Metody zaliczania cykli pracy lotniczych silników turbinowych
Autorzy:
Chachurski, R.
Głowacki, P.
Szczeciński, S.
Powiązania:
https://bibliotekanauki.pl/articles/212469.pdf
Data publikacji:
2011
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
zmęczenie silników turbinowych
zaliczanie cykli pracy silników lotniczych
lotnicze silniki turbinowe
turbine engine fatigue
aircraft engine
turbine engine
low-cycle fatigue
cycles number
Opis:
The issue of low-cycle fatigue is very important in terms of operational safety of aircraft turbine engines. This paper discusses methods, which are used in US aviation industry to determine boundary cycle counts, as well as methods of counting turbine engine operating cycles allowing to determine the residual safe operation time (hard time), expressed in cycles. Methods are discussed, which are used for both older types of engines as well as for present-day ones. In the paper titled „Zmęczenie niskocyklowe konstrukcji i jego minimalizacja” (Low-cycle structural fatigue and its minimization), published in volume no. 199/2009 of Prace Instytutu Lotnictwa (Proceedings of the Institute of Aviation) contains a schematic presentation of loads acting on components in the „hot section” of an aircraft turbine engine, as well as loads’ operational dependencies on engines’ operating conditions and operating ranges affecting their lowcycle structural fatigue. The paper pointed out that findings related to this type of loads had caused engine safe operation times to be expressed both in hours as well as in cycles. Methods for determining the number of cycles „utilized” by main engine modules and their important parts affecting operational safety, as well as maximum limits of operational cycle which if exceeded should require replacement of respective modules or individual parts had been imposed on operators by engine manufacturers. They are initially determined basing on fatigue tests performed on standard specimens of structural material and then based on fatigue tests of production parts and tests of complete engines. This paper is a further development of these previously discussed topics.
Zagadnienie zmęczenia niskocyklowego jest bardzo istotne z punktu widzenia bezpieczeństwa eksploatacji lotniczych silników turbinowych. W artykule przedstawiono sposoby wyznaczania granicznej liczby cykli stosowane w lotnictwie USA, a także metody zliczania cykli pracy silnika turbinowego w celu określenia pozostałości czasu jego bezpiecznej eksploatacji (resursu) wyrażonego w cyklach. Opisano metody wykorzystywane podczas użytkowania zarówno silników starszych typów, jak i współczesnych.
Źródło:
Prace Instytutu Lotnictwa; 2011, 8 (217); 5-13
0509-6669
2300-5408
Pojawia się w:
Prace Instytutu Lotnictwa
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The analysis of work shift patterns and risk of fatigue in aircraft maintenance personnel: a case study
Autorzy:
Basaria, Fransisca Tiur
Powiązania:
https://bibliotekanauki.pl/articles/27311329.pdf
Data publikacji:
2023
Wydawca:
Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:
fatigue
work shift pattern
aircraft maintenance
risk analysis
zmęczenie
schemat zmiany pracy
konserwacja statków powietrznych
analiza ryzyka
Opis:
In response to the COVID-19 pandemic in 2020, PT. XYZ, the biggest aircraft maintenance, repair, and overhaul (MRO) company in Indonesia, implemented a new shift pattern for line-maintenance personnel. The new shift pattern allows maintenance personnel to have fewer working hours per day (7-hour shifts) in more shift varieties for 5 consecutive days. Maintenance personnel will have 2-morning shifts, 1-noon shift, and 2-night shifts followed by 3 rest days. This study aims to explore the risk of fatigue caused by the newly implemented shift pattern. Data were collected through electronic questionnaires from a total of 303 respondents. This study found that at the time of the survey, many respondents (78 of 303, 26%) felt tired and had difficulty concentrating, regardless of the shift they were in. Based on the duty time, the highest scores of level 6 (tired, difficult to concentrate) were discovered on night shift day 5. This result shows that although the organization had provided the maintenance personnel with the opportunity to obtain sleep during rest days, tiredness and fatigue were still experienced by the aircraft maintenance personnel. This study recommends necessary actions to be taken to prevent fatigue, especially from the noon shift afterwards, where fatigue level is increasing, and alertness level is decreasing.
Źródło:
Zeszyty Naukowe. Transport / Politechnika Śląska; 2023, 118; 5--16
0209-3324
2450-1549
Pojawia się w:
Zeszyty Naukowe. Transport / Politechnika Śląska
Dostawca treści:
Biblioteka Nauki
Artykuł
Wyświetlanie 1-15 z 18

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