Fatigue crack growth history in damage tolerance design of aircraft structures

Nedbal, I.; Kunz, J.

doi:10.1016/j.ijfatigue.2008.05.006

Cited by 12 publications

(6 citation statements)

References 6 publications

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“…However, it must consider the defect or damage according to the method of design of the prescribed maintenance use during the period of growth control in a certain range. In the meantime, the structure should satisfy the requirement of the provisions of residual strength (including defect or crack structure bearing capacity) to ensure the safety and reliability of aircraft structure [17].…”

Section: Damage Tolerance and Stress Intensity Factormentioning

confidence: 99%

“…On the other side the bending moment M which is around the Y-axis was loaded. The through crack is directly related to the damage tolerance of the component, so in this paper, the through crack is taken as the object to study the influence of the structural parameters of the integral panel on the stress intensity factor at the crack tip [17]. In the model, the integral panel model is a three-dimensional solid unit, and the material is 2024.…”

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confidence: 99%

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Integral Aircraft Wing Panels with Penetration Cracks: The Influence of Structural Parameters on the Stress Intensity Factor

Gong

et al. 2020

Applied Sciences

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The finite element model of integral wing panels with central penetration cracks under bending load was established, and the crack propagation process of the aircraft panel was simulated. The stress intensity factor (SIF) of the crack tip during crack propagation under varying conditions of crack length and panel structural parameters was determined. The effects of the panel structure parameters and crack size on the crack tip SIF were obtained. The regression analysis of the finite simulation element results has been performed and a regression model of SIF at the crack tip of the integral panel has been established, the determination coefficient of the regression model is 0.955.

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Section: Damage Tolerance and Stress Intensity Factormentioning

confidence: 99%

mentioning

confidence: 99%

Integral Aircraft Wing Panels with Penetration Cracks: The Influence of Structural Parameters on the Stress Intensity Factor

Gong

et al. 2020

Applied Sciences

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“…An attempt was made to correlate da/dN and striation spacing measurements. Although more detailed analyses may be carried out (de Matos et al, 2005;Siegl et al, 2009), as a first approximation striation spacing may be taken as an indication of crack growth rate. This approximation proved reasonable in the present study.…”

Section: Fractographic Analysismentioning

confidence: 99%

Fractographic analysis of fatigue crack growth in lightweight integral stiffened panels

Moreira

Castro

2010

International Journal of Structural Integrity

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PurposeThe purpose of this paper is to complement available macroscopic fatigue crack growth measurements in flat stiffened panels with scanning electron microscopy (SEM) measurements of striation spacing.Design/methodology/approachThe paper's approach is fatigue testing of two‐stiffener flat panels manufactured using three different processes, with a central initial crack perpendicular to the stiffeners and load, in order to identify striation spacing during crack growth up to final fracture, using SEM.FindingsAn increase of striation spacing as cracks grow was quantified. Although when cracks approach the stiffeners the stress intensity factor decreases, there is no clear decrease of striation spacing in that region. Striation spacing is roughly similar to macroscopic crack‐propagation rate da/dN measured in the panels testing. This observation is no longer valid once the stiffeners are reached; this stage is characterized by fast acceleration of the cracking process until final complete rupture is verified, and macroscopic crack growth measurements are made difficult because of the “T” geometry in that region.Originality/valueA complete picture of the striation spacing during the fatigue crack growth up to final fracture of a two‐stiffener flat panel is provided for three different manufacturing processes: high‐speed machining, laser beam welding and friction stir welding.

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“…There are a large number of research studies on the relationship between fatigue striations spacing and fatigue crack growth rate. It is probably the most popular fractographic parameter in failure analysis of aircraft structures (Jones et al, ; Siegl et al, ). In fact, there is a strong correlation of striations spacing and fatigue cycles under crack growth rates of medium to large intensities, where each striations spacing often corresponds to one loading cycle (Lenets and Bellows, ).…”

Section: Introductionmentioning

confidence: 99%

Correlative light‐electron fractography for fatigue striations characterization in metallic alloys

Hein

Oliveira

Campos

2013

Microscopy Res & Technique

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The correlative light-electron fractography technique combines correlative microscopy concepts to the extended depth-from-focus reconstruction method, associating the reliable topographic information of 3-D maps from light microscopy ordered Z-stacks to the finest lateral resolution and large focus depth from scanning electron microscopy. Fatigue striations spacing analysis can be precisely measured, by correcting the mean surface tilting with the knowledge of local elevation data from elevation maps. This new technique aims to improve the accuracy of quantitative fractography in fatigue fracture investigations.

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Fatigue crack growth history in damage tolerance design of aircraft structures

Cited by 12 publications

References 6 publications

Integral Aircraft Wing Panels with Penetration Cracks: The Influence of Structural Parameters on the Stress Intensity Factor

Integral Aircraft Wing Panels with Penetration Cracks: The Influence of Structural Parameters on the Stress Intensity Factor

Fractographic analysis of fatigue crack growth in lightweight integral stiffened panels

Correlative light‐electron fractography for fatigue striations characterization in metallic alloys

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