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    Wyświetlanie 1-3 z 3
    Tytuł:
    The Analysis of Fatigue Crack Propagation in the Elements of Aluminum Alloy D16CZATW with a Notch in the Formof A Cylindrical Hole
    Autorzy:
    Hutsaylyuk, V.
    Mierzyński, J.
    Zasada, D.
    Powiązania:
    https://bibliotekanauki.pl/articles/97793.pdf
    Data publikacji:
    2011
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Opis:
    In this work, the fatigue life of specimens made from the aluminum alloy D16CzATW has been determined. To this aim, flat specimens with notches in the form of cylindrical holes made by drilling and reaming have been investigated. The research was carried out under the conditions of constant-amplitude bending at the stress ratio of R = -1. The results obtained were compared with the fatigue life of specimens with calibrated holes and specimens without notches. Fatigue life was determined for specimens plated on both sides and those without this protecting layer. Very large differences in fatigue resistance were observed. These differences can be explained by the negative effect of the brittle protecting layer on the fatigue crack initiation process. A complex fracture mechanism was observed, in which micro-mechanisms of brittle and ductile fracture were appearing at different stages of fatigue crack propagation.
    Źródło:
    Fatigue of Aircraft Structures; 2011, 3; 28-41
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    ZL-130TCII Fracture Markers Solution for Full-Scale Fatigue Test
    Autorzy:
    Kłysz, S.
    Lisiecki, J.
    Zasada, D.
    Gmurczyk, G.
    Leski, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/97988.pdf
    Data publikacji:
    2011
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    full scale fatigue test
    fracture surface marking
    quantitative fractography
    Opis:
    In the context of PZL-130TC-II full-scale fatigue test, several strategies of fatigue loadings that create fracture surface markings were considered. One block of spectrum is made of 200 flights. By reordering those flights, a block which should create a fracture marker, was developed. It was very important that reordering the load spectrum or adding overloads or underloads did not change spectrum severity. Pilot tests of aluminium alloys specimens were carried out to finalise appropriate marker intervals before commencing full-scale tests. The experiment was conducted with the MTS machine with 810.23 system. The results and conclusions are presented within this paper.
    Źródło:
    Fatigue of Aircraft Structures; 2011, 3; 22-27
    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
      Wyświetlanie 1-3 z 3

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