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    Wyświetlanie 1-6 z 6
    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:
    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:
    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:
    Introduction of Fatigue Markers in Full Scale Fatigue Test of an Aircraft Structure
    Autorzy:
    Leski, A.
    Kłysz, S.
    Lisiecki, J.
    Gmurczyk, G.
    Reymer, P.
    Bochenek, D.
    Zasada, D.
    Powiązania:
    https://bibliotekanauki.pl/articles/97777.pdf
    Data publikacji:
    2012
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    full scale fatigue test
    fatigue markers
    load block rearrangement
    Opis:
    Air Force Institute of Technology participates in the service life assessment programme SEWST. The aim of this programme, funded by the Polish Ministry of Defense, is to modify the operation system of PZL-130 "Orlik" TC-II turbo propelled trainer aircraft. The structural part of the programme is focused on the Full Scale Fatigue Test of the whole airframe to be conducted at the VZLU in the Czech Republic. The load spectrum for the test was developed by the AFIT based on the flight test results. The basic load block represents 200 simulated flight hours and consists of 194 flights showing different levels of severity. At the end of the Full Scale Fatigue Test a teardown inspection is planned during which it would be most beneficial to be able to determine crack propagation rate by means of a crack surface inspection. Markers are usually visible on most fatigue crack surfaces, however they occur randomly therefore it is almost impossible to conclude anything about the crack history. Since the preliminary load block consisted of separate flights (flight loads together with landing and taxing loads) showing significantly different levels of severity, the easiest way to modify the load block was to change the order of flights within the block. Hence a pilot programme was started at the AFIT which was focused on the determination of the influence of flight sequence on crack appearance. Several load blocks were determined using various techniques of rearranging the order of flights within the preliminary load spectrum. This approach ensured the preservation of the initial severity of the load block and simultaneously enabled a significant increase in the probability of the markers occurrence introducing neither artificial underloads nor overloads that would most probably affect the crack propagation rate. Fatigue crack surfaces were inspected using Scanning Electron Microscope. As a result of the investigations a series of images were obtained showing the specimen microstructure with visible markers arranged in the desired sequences. Based on the obtained pictures the most promising load block arrangements were chosen for the Full Scale Fatigue Test.
    Źródło:
    Fatigue of Aircraft Structures; 2012, 4; 29-37
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Crack Growth Analysis of the Landing Gear Pull Rod of the Fighter Jet Aircraft
    Autorzy:
    Kurdelski, M.
    Leski, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/97773.pdf
    Data publikacji:
    2011
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    crack growth
    fatigue
    flight tests
    landing gear
    Opis:
    This paper describes the problem of searching for the causes of damage in the form of rupture of a strength member of the main landing gear. There have been two incidents noted which both occurred during hangar storage. It should be pointed out that the two occurrences mentioned concern a particular aircraft currently in operation, and that these incidents occurred a few days after the last flight. This article presents part of the investigation process needed to determine the causes of cracks in the test item. The crack growth analysis of the pull rod was performed using the NASGRO software. In order to perform the calculations, the information was gathered during previously conducted material studies and flight tests.
    Źródło:
    Fatigue of Aircraft Structures; 2011, 3; 64-73
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    An Approach to Damage Detection in the Aircraft Structure with the Use of Integrated Sensors – The Symost Project
    Autorzy:
    Dragan, K.
    Dziendzikowski, M.
    Leski, A.
    Dworakowski, Z.
    Uhl, T.
    Powiązania:
    https://bibliotekanauki.pl/articles/97801.pdf
    Data publikacji:
    2012
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    averaged damage index
    full scale fatigue test
    damage growth monitoring
    Opis:
    This paper presents an approach to damage growth monitoring and early damage detection in the structure of PZL – 130 ORLIK TC II turbo-prop military trainer aft using the statistical models elaborated by the Polish Air Force Institute of Technology (AFIT) and the network of the sensors attached to the structure. Drawing on the previous experiences of the AFIT and AGH in structural health monitoring, the present research will deploy an array of the PZT sensors in the structure of the PZL -130 Orlik TC II aircraft. The aircraft has just started Full Scale Fatigue Test (FSFT) that will continue up to 2013. The FSFT of the structure is necessary as a consequence of the structure modification and the change of the maintenance system - the transition to Condition Based Maintenance. In this paper, a novel approach to the monitoring of the aircraft hot-spots will be presented. Special attention will be paid to the preliminary results of the statistical models that provide an automated tool to infer about the presence of damage and its size. In particular, the effectiveness of the selected signal characteristics will be assessed using dimensional reduction methods (PCA) and the so-called averaged damage indices will be delivered. Moreover, the results of the signal classification based on the neural network will be presented alongside the numerical model of the wave propagation. The work contains selected information about the project scope and the results achieved at the preliminary stage of the project.
    Źródło:
    Fatigue of Aircraft Structures; 2012, 4; 10-16
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-6 z 6

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