Fatigue failure in aircraft structural components

Gürgen, Selim; Kuşhan, Melih Cemal; Diltemiz, Seyid Fehmi

doi:10.1016/b978-0-12-800950-5.00013-2

Cited by 9 publications

(8 citation statements)

References 5 publications

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“…Under different stress amplitudes, the relative entropy method has different performances. 4. The relative entropy can be considered the first step to determine the candidates of the fatigue distribution and is feasible to select the suitable fatigue distribution of the fatigue life, which does not follow the exponential distribution.…”

Section: Discussionmentioning

confidence: 99%

“…Study on the fatigue of materials has become more and more significant since Wilhelm Albert published the first article on fatigue in 1837 [ 1 , 2 ]. At the same time, engineering application needs more diverse materials, especially composite materials, and requires some materials working under extreme conditions, such as high-speed railways and aerospace [ 3 , 4 ]. Thus, the importance of the fatigue of a material is beyond just an academic interest and comes into the field of real practice.…”

Section: Introductionmentioning

confidence: 99%

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Relative Entropy Method Applied for the Fatigue Life Distribution of Carbon Fiber/Epoxy Composites

Yuan

Liang

2021

Entropy

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This paper verifies the feasibility of the relative entropy method in selecting the most suitable statistical distribution for the experimental data, which do not follow an exponential distribution. The efficiency of the relative entropy method is tested through the fractional order moment and the logarithmic moment in terms of the experimental data of carbon fiber/epoxy composites with different stress amplitudes. For better usage of the relative entropy method, the efficient range of its application is also studied. The application results show that the relative entropy method is not very fit for choosing the proper distribution for non-exponential random data when the heavy tail trait of the experimental data is emphasized. It is not consistent with the Kolmogorov–Smirnov test but is consistent with the residual sum of squares in the least squares method whenever it is calculated by the fractional moment or the logarithmic moment. Under different stress amplitudes, the relative entropy method has different performances.

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Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Relative Entropy Method Applied for the Fatigue Life Distribution of Carbon Fiber/Epoxy Composites

Yuan

Liang

2021

Entropy

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“…Fatigue cracks are a very common problem in aerospace operation and maintenance, as fatigue causes 60% of the total service failures in aircraft components [1]. Fatigue, the weakening of the material, occurs under external cyclic loading [2] and fatigue cracks initiate at a microscopic level [3]. Non-destructive evaluation (NDE) identifies and characterizes the damage without harming the specimen [4].…”

Section: Introductionmentioning

confidence: 99%

Mode-converted Lamb wave sensitivity prediction for part-thickness crack-like defects

Fromme

2023

Health Monitoring of Structural and Biological Systems XVII

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Fatigue crack growth is one of the most common damage types in aluminum components, widely used in aircraft structures. Detection of fatigue cracks at an early stage is important to guarantee aircraft safety. Efficient non-destructive evaluation (NDE) and structural health monitoring (SHM) can be achieved by employing low frequency guided ultrasonic waves, as they can propagate long distances along plate structures. SHM systems using distributed guided waves sensors have been proposed for efficient monitoring, but have limitations due to environmental influences such as the temperature stability of the conventional baseline subtraction method. The scattering and mode conversion of guided waves at part-thickness defects was investigated to quantify the sensitivity for defect detection and the potential for the development of a baseline-free SHM methodology employing mode converted guided waves. Baseline-free SHM methodology employing mode conversion is expected to overcome some of the limitations caused by environmental factors and to improve sensitivity and stability by employing new or modified signal processing algorithms. A three dimensional (3D) Finite Element (FE) model was developed to predict the mode conversion of the fundamental guided wave modes. The influence of defect length and depth on detection results were investigated numerically. The detection sensitivity for part-thickness defects in a plate is quantified.

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“…The fatigue failure of a material is dependent on the interaction of a large stress with critical flaws or discontinuities. Since fatigue cracks almost always nucleate at a free surface, any surface condition and treatment can have significant effect on fatigue life [115]. At low applied stresses or high cycle fatigue, the crack nucleation and early (short) crack growth period dominates the fatigue life and, therefore, factors such as surface finish and treatment become even more influential [116] [117] [118].…”

Section: Fatigue Testing and Fatigue Life Evaluationmentioning

confidence: 99%

“…Finally, in the failure stage, the remaining undamaged cross-sectional area of the material cannot bear the acted loads and the material ruptures. Failure surface shows either ductile or brittle fracture characteristics depending on the material from this stage [115].…”

Section: Fatigue Life S-n Curvesmentioning

confidence: 99%

Laser Ablation of Paint from 2024-T3 Alclad Aluminum - Numerical Simulation and Experimental Characterization

Shah¹

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Removal of paint from substrate material through laser ablation is a very promising and environmentally safe process as compared to chemical stripping and other processes.Potential thermomechanical damage of substrate material subjected to laser paint removal process plays a vital role in deciding the efficacy and the accuracy of a particular laser beam profile to be used. In the present research work, numerical simulation of thermomechanical behavior of substrate material (2024-T3 Alclad aluminum) with paint layer is developed subjected to laser heating with Gaussian (TEM00) and Super-Gaussian (Top-Hat) beam profiles. It was observed that the Gaussian beam profile had the fastest stabilization time but produced higher thermal stresses on the surface of substrate material as compared to the Top-Hat beam profile. Moreover, the effects of various paint stripping processes (laser and chemical stripping) on the fatigue life and failure pattern of the substrate material (2024-T3 Alclad aluminum) were investigated through detailed statistical analysis and scanning electron microscope (SEM) analysis. It was observed that the differences in the mean fatigue life between laser and chemical stripped specimens were statistically insignificant. However, there was a distinct difference between the laser stripped and chemically stripped specimens with regard to final fracture zone. For the laser stripped specimen failure was brittle whereas for the chemically stripped specimens' failure was ductile. In addition, surface roughness and surface microhardness measurement on the stripped surfaces were performed.

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Fatigue failure in aircraft structural components

Cited by 9 publications

References 5 publications

Relative Entropy Method Applied for the Fatigue Life Distribution of Carbon Fiber/Epoxy Composites

Relative Entropy Method Applied for the Fatigue Life Distribution of Carbon Fiber/Epoxy Composites

Mode-converted Lamb wave sensitivity prediction for part-thickness crack-like defects

Laser Ablation of Paint from 2024-T3 Alclad Aluminum - Numerical Simulation and Experimental Characterization

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