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    Wyświetlanie 1-4 z 4
    Tytuł:
    The Elaboration of the Method of Fatigue Testing of the Rotor of the Mosups Plane Propulsion System
    Autorzy:
    Głowacki, D.
    Rodzewicz, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/97933.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    UAV
    propulsion system
    stress analysis
    fatigue tests
    Opis:
    This paper concerns fatigue testing of the rotor of the propulsion system for the MOSUPS – an unmanned aircraft designed in a joint wing configuration, and equipped with a ducted propeller. The work presents the analysis of the stresses and deformations of the rotor structure as well as the form of the loading cycle. The aim of the paper is to introduce the concept of a simplified method of fatigue testing of multi-blade rotors. With the sophisticated geometry of the rotor in mind – the authors applied the FEM tools and implemented the ANSYS and nCode programs. The prototype of the fatigue stand built by the authors is also presented in the paper.
    Źródło:
    Fatigue of Aircraft Structures; 2016, 8; 97-103
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Prediction of Fatigue Cracks Using Gamma Function
    Autorzy:
    Moussouni, Abdelfetah
    Benachour, Mustapha
    Benachour, Nadjia
    Powiązania:
    https://bibliotekanauki.pl/articles/24201171.pdf
    Data publikacji:
    2022
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    fatigue crack growth
    stress ratio
    fatigue
    2024 T351 Al-alloy
    Gamma function
    Opis:
    In the present study it has been endeavored to estimate the fatigue crack propagation in V-notch Charpy specimens of 2024 T351 Al-alloy. For this purpose, a new application of fatigue crack growth (FCG) is developed based on the “Gamma function.” Experimental fatigue tests are conducted for stress ratios from 0.1 to 0.5 under constant amplitude loading. The empiric model depends principally on physical parameters and materials’ properties in non-dimensional form. Deviation percentage, prediction ratio, and band error are used for validation of the performance of the fatigue life. The results determined from Gamma application are in good agreement with experimental FCG rates and those obtained from using Paris law.
    Źródło:
    Fatigue of Aircraft Structures; 2022, 14; 29--46
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Stress Intensity Factor Analysis and Fatigue Behavior of A Crack in The Residual Stress Field of Welding
    Autorzy:
    Terada, H.
    Powiązania:
    https://bibliotekanauki.pl/articles/97909.pdf
    Data publikacji:
    2011
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    stress intensity factor analysis
    crack
    residual stress field
    butt weld
    stress redistribution
    fatigue crack
    crack propagation
    Opis:
    This paper deals with the behavior of a crack in the residual stress field induced by the butt weld in a wide plate. It is known that the distribution form of residual stress has similarities regardless of the welding process, although the size and the magnitude of the residual stress depend largely on the welding process. Stress intensity factor and stress redistribution induced by the crack extension were calculated for a crack with arbitrary length and location. The stress redistributions caused by crack extension obtained by the present analysis showed good agreement with the experimental data. Fatigue crack propagation behavior in the residual stress field reported by Glinka was also examined from ΔK point of view. The effect of residual stress on the fatigue crack propagation rate is considered to be the effect of varying mean stress. It was shown that fatigue crack propagation rate is estimated by the following equation with reasonable accuracy.
    da/dn=CΔFα(1+ σ0/Δσ Fres)
    In the above equation, material constants C and α of Paris’s law are experimentally obtained by using specimens without the weld joint.
    Źródło:
    Fatigue of Aircraft Structures; 2011, 3; 5-15
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Local Phenomena During Riveting Process
    Autorzy:
    Kaniowski, J.
    Wronicz, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/97899.pdf
    Data publikacji:
    2013
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    riveting
    fatigue
    strain gauge
    FE model
    residual stress
    airframes
    Opis:
    The paper presents experimental and numerical study of the local phenomena during the riveting process. It is commonly accepted that technological factors of the riveting process has a strong influence on the fatigue life of riveted joints. The authors analysed the papers concerned the experimental researches of the riveting force influence on fatigue life. The magnitude of the life increase caused by the riveting force increase suggests the authors that this is not only the result of beneficial stress system but the change of the joint formation mechanism has taken place. This was an inspiration to undertake more detailed researches of the riveting process. The strain progress during the riveting process has been experimentally investigated for four types of aluminium rivets used in airframes. Measurements confirm very high strains near the driven head. For some types of rivets the reversal strain signal has been recorded. Several FE model has been use to investigate the riveting process. The axisymmetric and solid models were used. The agreement of experimental and numerical results in some cases were good, in other cases the numerical models demand further development. In any calculations, the reversal strain effect has not been obtained, This suggest that it is result of the phenomenon which has not been taken into account in numerical modelling. The working hypothesis has been assumed that during the riveting process adhesive joints (called cold welding) were formed and destroyed during the process, what was the reason of the observed reversal strain signal. The authors are going to continue this investigation.
    Źródło:
    Fatigue of Aircraft Structures; 2013, 5; 66-78
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-4 z 4

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