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    Wyświetlanie 1-11 z 11
    Tytuł:
    Predicting Fatigue Crack Growth and Fatigue Life Under Variable Amplitude Loading
    Autorzy:
    Jasztal, M.
    Kocanda, D.
    Tomaszek, H.
    Powiązania:
    https://bibliotekanauki.pl/articles/97891.pdf
    Data publikacji:
    2010
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Opis:
    A probabilistic approach to the description of fatigue crack growth and fatigue life estimation of a component subjected to variable amplitude loading is presented in the paper. The core of the model is a differential equation originated from the Paris formula. In order to consider the influence of overload-underload cycles existing in an exploitive load spectrum on crack growth rate for an aeronautical aluminum alloy sheet, the modified Willenborg retardation model was applied.
    Źródło:
    Fatigue of Aircraft Structures; 2010, 2; 37-51
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Monitoring of Crack Growth in a Structure Under a Composite Patch
    Autorzy:
    Sałaciński, M.
    Synaszko, P.
    Stefaniuk, M.
    Dragan, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/97971.pdf
    Data publikacji:
    2011
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Opis:
    In civil as well as in military aviation, boron, carbon and aramid fiber reinforced composites are employed for the repair of metal structures. After such composite bonded repairs, the monitoring of the repaired structure along with the composite patch and its bond is necessary. The paper describes the possibilities of utilizing NDT methods for periodical check-ups and examinations. Also, a novel approach to continuous monitoring of the repaired structure is presented.
    Źródło:
    Fatigue of Aircraft Structures; 2011, 3; 103-111
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Strength Testing and Analysis of Fatigue Crack Growth in Selected Aircraft Materials
    Autorzy:
    Kłysz, S.
    Lisiecki, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/97903.pdf
    Data publikacji:
    2009
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Opis:
    The study has been intended to determine the most essential mechanical and fatigue properties as well as impact strength of the 30HGSNA steel, to gain own data on the above-mentioned characteristics of materials to be used further on in numerical analyses of life estimates of aeronautical structural components. The scope of the study comprised the following assignments:
    - determination of the most fundamental mechanical properties and impact strength of materials,
    - low-cycle fatigue testing and evaluation of the Manson-Coffin curves,
    - high-cycle fatigue testing and evaluation of the Wöhler curves,
    - investigation into fatigue crack growth rates at constant and variable load-cycle amplitudes (determination of curves da/dN = f(ΔK, R), coefficients in Paris and NASGRO equations, coefficients in the Wheeler models of delay, the value of Kth(R)),
    - crack toughness testing under the plane-state-of-strain conditions at room temperature (determination of the KIc(R)). The strength/fatigue testing was carried out in the Laboratory for Materials Strength Testing of the AFIT’s Division for Aeronautical Systems Reliability and Safety, the lab being accredited by the Polish Centre for Accreditation (Accreditation Certificate No.: AB 430).
    Źródło:
    Fatigue of Aircraft Structures; 2009, 1; 74-83
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Experimental and Theoretical Investigations of Fatigue Crack Growth in D16 Alloy
    Autorzy:
    Śnieżek, L.
    Powiązania:
    https://bibliotekanauki.pl/articles/97817.pdf
    Data publikacji:
    2009
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Opis:
    In this work the arising and development of fatigue crack in aluminium alloy D16, taking into consideration the influence of notch in the form of hole with incisions which were done on its sides were tested. The process of working out of tests' programme was preceded by numeric analysis of stresses pattern and strains distribution in the zone of notch’s influence which was focused on determination of stresses' face values. To examine stress and strain distributions, the specialised FEM software (MSC.Patran and MSC.Nastran) was applied. Findings have been presented in the form of a statement of σmax and εmax values, and functions of the following factors: aσ, aε, and ak, computed on the grounds of these values for both different distances from the bottom of the notch and assumed levels of loading the specimens. Theoretical analysis has been supplemented with experimental investigation into the microstructure of fatigue-fracture surfaces in the area of crack initiation and that of fatigue of a propagating crack. The paper has been intended to present a model of the probabilistic estimation of fatigue life of structural members. The model has been based on the deterministic description of the cracking. Analyzed were components with notches in the form of centrally located holes with side cuts. In the method of probabilistically approaching the crack propagation, some dependences have been used that take account of the presence of areas showing plastic strains in front of crack tips. It has been assumed that the cracking can be modeled on the grounds of some general-purpose quantity used to describe the energy state in the area of the crack tip, i.e. the Rice's integral (J). The formulated computational model has been used to estimate fatigue life of model components made of D16 alloy. Experimental work was carried out using some flat specimens with centrally positioned holes. They were exposed to flat bending at R = 0. Analytical and experimental results have shown pretty good conformity.
    Źródło:
    Fatigue of Aircraft Structures; 2009, 1; 170-190
    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:
    Simulation of Fatigue Crack Growth in Integrally Stiffened Panels Under the Constant Amplitude and Spectrum Loading
    Autorzy:
    Augustin, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/97771.pdf
    Data publikacji:
    2009
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Opis:
    The paper describes methodology of numerical simulation of fatigue crack growth and its application on integrally stiffened panels made of 2024-T351 aluminium alloy using high speed cutting technique. Presented approach for crack growth simulation starts by the calculation of stress intensity factor function from finite element results obtained using MSC. Patran/Nastran. Subsequent crack growth analysis is done in NASGRO and uses description of crack growth rates either by the Forman-Newman-de Koning relationship or by the table lookup form. Three crack growth models were applied for spectrum loading: non-interaction, Willenborg and Strip Yield model. Relatively large experimental program comprising both the constant amplitude and spectrum tests on integral panels and CCT specimens was undertaken at the Institute of Aerospace Engineering laboratory in order to acquire crack growth rate data and enable verification of simulations. First analyses and verification tests of panels were performed under the constant amplitude loading. For predictions of crack growth using the spectrum loading a load sequence representing service loading of the transport airplane wing was prepared. Applied load spectrum was measured on B737 airplane within the joint FAA/NASA collection program. The load sequence is composed of 10 flight types with different severity analogous to the standardized load sequence TWIST. Before application on the stiffened panels a calculation of crack growth under the spectrum loading was performed for simple CCT specimen geometry. The paper finally presents comparison of simulations of fatigue crack propagation in two-stringer stiffened panel under the spectrum loading with verification test carried out in the IAE lab. The work was performed within the scope of the 6th Framework Programme project DaToN - Innovative Fatigue and Damage Tolerance Methods for the Application of New Structural Concepts.
    Źródło:
    Fatigue of Aircraft Structures; 2009, 1; 5-19
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Deterministic Approach to Predicting the Fatigue Crack Growth in the 2024-T3 Aluminum Alloy Under Variable Amplitude Loading
    Autorzy:
    Kocańda, D.
    Torzewski, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/97779.pdf
    Data publikacji:
    2009
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    aluminum alloy
    fatigue crack growth rate
    microfractographic analysis
    Willenborg retardation model
    Opis:
    The paper presents the attempt to predict fatigue crack growth rate in a component subjected to variable amplitude loading containing overload-underload cycles. For this goal in a deterministic approach the modified Willenborg retardation model was applied. To provide experimental data the research into fatigue crack growth for 2024-T3 aluminum alloy sheet CCT specimens under LHL type block program loading with multiple overload-underload cycles was developed. The microfractographic analysis of fatigue fractures with the use of the transmission electron microscope (TEM) made it possible to trace the effect of block program loading on the crack growth rate. The knowledge of the affection of a particular overloadunderload cycle or a block of these cycles on crack rate on the basis of microfractographic analysis was utilized for assessing the equivalent loading for the LHL block program. The diagrams that presented the crack growth rate both on the surface and inside the aluminum alloy sheet was performed. The crack growth rate inside the sheet was estimated on the basis of the striation spacing analysis.
    Źródło:
    Fatigue of Aircraft Structures; 2009, 1; 102-115
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    A Model for Fatigue Crack Growth in the Paris Regime under the Variability of Cyclic Hardening and Elastic Properties
    Autorzy:
    Kebir, T.
    Benguediab, M.
    Imad, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/97819.pdf
    Data publikacji:
    2017
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    cyclic plastic strain
    elastic properties
    cyclic hardening parameters
    Young's modulus
    variability
    crack tip
    fatigue crack growth
    constants of the Paris law
    Al-alloys
    Opis:
    Over the last 60 years, several models have been developed governing different zones of fatigue crack growth from the threshold zone to final failure. The best known model is the Paris law and a number of its based on mechanical, metallurgical and loading parameters governing the propagation of cracks. This paper presents an analytical model developed to predict the fatigue crack propagation rate in the Paris regime, for different material properties, yield strength (σy), Young’s modulus (E) and cyclic hardening parameters (K’, n’) and their influence by variability. The cyclic plastic deformation at a crack tip or any other cyclic hardening rule may be used to reach this objective, for to investigate this influence, these properties of the model are calibrated using available experimental data in the literature. This FCGR model was validated on Al-alloys specimens under constant amplitude load and shows good agreement with the experimental results.
    Źródło:
    Fatigue of Aircraft Structures; 2017, 9; 117-135
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Capacity of Fractographic Analysis for Load-Time History Reconstruction and Fatigue Crack Growth Rate Estimation for the 2024-T3 Aluminium Alloy
    Autorzy:
    Bogdanowicz, Z.
    Kocańda, D.
    Torzewski, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/97833.pdf
    Data publikacji:
    2009
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Opis:
    The subject of the paper is the considerations for the feasibility of load time history reconstruction on the basis of microfracture analysis for a failed component made of 2024-T3 aluminium alloy that operates under variable amplitude loading. For this goal three different variable amplitude load sequences with single and multiple overloads and underloads were applied to investigate crack growth rate and to examine the images of fatigue striations on the fracture surface of a component. These loads are employed when simulating the fatigue crack behaviour in aeronautical alloys. Microfracture analysis was also used either for learning the interaction of variable amplitude loading for crack growth rate in 2024-T3 alloy or for establishing the relation between surface crack and crack depth growth.
    Źródło:
    Fatigue of Aircraft Structures; 2009, 1; 20-36
    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:
    A FCG Model and the Graphical User Interface Under Matlab for Predicting Fatigue Life: Parametric Studies
    Autorzy:
    Kebir, Tayeb
    Correia, José A.F.O.
    Benguediab, Mohamed
    Imad, Abdellatif
    Powiązania:
    https://bibliotekanauki.pl/articles/2105193.pdf
    Data publikacji:
    2021
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    fatigue life prediction
    Graphical User Interface
    fatigue crack growth
    cyclic hardening
    Paris
    Walker
    Forman
    Opis:
    The focus of this research work was predicting the fatigue life of mechanical components used for industrial and transport systems. To understand how the phenomenon of fatigue occurs in a material, the fatigue crack growth is studied. The purpose of this work was to create a graphical user interface (GUI) under Matlab to allow researchers to conduct the parametric studies of fatigue crack propagation to predict fatigue life. In this work, three models for fatigue crack propagation were used: those of Paris, Walker and Forman in order to study the three parameters: the Paris exponent m, load ratio R and hardness KIC, respectively. In addition, a novel model FCG was developed to study the influence of the hardening parameters (K′, n′) on fatigue crack propagation. The comparison of the simulation results with those in the literature shows good agreement.
    Źródło:
    Fatigue of Aircraft Structures; 2021, 13; 116--139
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
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