Can pitting corrosion change the location of fatigue failures in aircraft?

Crawford, Bruce R.; Loader, Chris; Liu, Qianchu; Harrison, T. J.; Sharp, P. K.

doi:10.1016/j.ijfatigue.2013.10.017

Cited by 23 publications

(8 citation statements)

References 25 publications

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“…This indicates that corrosion plays an important role in the deterioration of mechanical properties. Pits cause stress concentration to the sample surface; when the sample was tensile tested, cracks appear easily at the corrosion pit [11,19,20]. The pit depth increases with the extension of corrosion time, so the stress concentration factor continually enlarges, and the mechanical properties degradation becomes more and more serious.…”

Section: Discussionmentioning

confidence: 99%

“…Therefore, tensile stress promotes the hydrogen embrittlement process and aggravates the elongation degradation of cathodic polarized samples. Most reports [11][12][13] about the corrosion-induced mechanical properties degradation consider producing corrosion defects as the main contribution of prior corrosion. However, by comprehensively analyzing the test results, the authors attribute the mechanical properties degradation of 7475-T761 aluminum alloy to the electrochemical corrosion and corrosioninduced hydrogen embrittlement.…”

Section: Discussionmentioning

confidence: 99%

“…Some researches have focused on the corrosion-induced mechanical properties deterioration of the high-strength aluminum alloy. Most researchers [11][12][13] believe that the main contribution of the prior corrosion to the mechanical properties degradation is producing corrosion defects. Fatigue crack can easily appear at the defects, and thus the prior corroded aluminum alloy has a lower fatigue life.…”

Section: Introductionmentioning

confidence: 99%

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Effects of Prior Corrosion with and Without Stress on the Mechanical Properties of 7475-T761 Aluminum Alloy

Liu

Yuan

et al. 2015

Acta Metall. Sin. (Engl. Lett.)

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The effect of prior corrosion on the mechanical properties of 7475-T761 aluminum alloy was investigated by immersion test, stress corrosion test, cathode charge method and electrochemical polarization test. Results show that prior corrosion in the solution with 3 wt% NaCl and 0.5 wt% H 2 O 2 leads to mechanical properties deterioration of 7475-T761 aluminum alloy. Moreover, the elongation decreases significantly. This is mainly attributed to electrochemical corrosion and hydrogen embrittlement, in which corrosion plays a major role. Tensile stress promotes the degradation of the mechanical properties by accelerating the pitting corrosion and hydrogen embrittlement.

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Section: Discussionmentioning

confidence: 99%

Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Effects of Prior Corrosion with and Without Stress on the Mechanical Properties of 7475-T761 Aluminum Alloy

Liu

Yuan

et al. 2015

Acta Metall. Sin. (Engl. Lett.)

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“…On another note, the precorrosion fatigue properties of aluminum alloys have been widely studied and established by various researchers over the past few years [ 25 , 26 , 27 , 28 , 29 , 30 ]. However, there are only a few studies, which investigated the precorrosion fatigue behavior of FSW EN AW-5754 aluminum alloy specimens.…”

Section: Introductionmentioning

confidence: 99%

Effect of Corrosion and Surface Finishing on Fatigue Behavior of Friction Stir Welded EN AW-5754 Aluminum Alloy Using Various Tool Configurations

et al. 2020

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In this study, fatigue behavior of surface finished and precorroded friction stir welded (FSW) specimens using various tool configurations were comparatively investigated by the load increase method. The FSW using conventional, stationary shoulder and dual-rotational configurations was carried out by a robotized tool setup on 2 mm EN AW-5754 aluminum sheets in butt joint formation. After extraction of the specimens, their weld seam and root surfaces were milled to two different depths of 200 µm and 400 µm to remove the surface and the FSW tool shoulder effects. This surface finishing process was performed to investigate the effect of the surface defects on the fatigue behavior of the FSW EN AW-5754 aluminum alloy sheets. It was found that material removal from the weld and root surfaces of the specimens, increased the fracture stresses of conventional and dual-rotational FSW from 204 to 229 MPa and 196 to 226 MPa, respectively. However, this increase could not be detected in stationary shoulder FSW. Specimens with finished surfaces, which showed superior properties, were used in salt spray and cyclic climate change test to investigate the effect of corrosion on the fatigue behavior of FSW specimens. It was shown that cyclic climate change test reduced the fatigue properties of the base material, conventional, stationary shoulder and dual-rotational FSW approximately 1%–7%. This decrease in the fatigue properties was greater in the case of the salt spray test, which was 7% to 21%.

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“…Therefore, some U.S. military standards and handbooks, such as the MIL-STD-1530C (2) , MIL-STD-810G (14) , AFRL-VA-WP-TR-2003-3002 (15) , etc., take the issue of corrosion into account in aircraft production and usage. Many investigators also have devoted to the research of corrosion fatigue issues of aircraft (16)(17)(18)(19)(20)(21)(22)(23) .…”

Section: Introductionmentioning

confidence: 99%

Service fatigue life and service calendar life limits of aircraft structure: aircraft structural life envelope

Zhang

et al. 2016

Aeronaut. j.

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The service life of aircraft structure includes the fatigue life and calendar life. The Aircraft Structural Life Envelop (ASLE) is a safe and reliable life scope of aircraft structures in service. The specific steps to establish the ASLE are developed, and a residual life prediction method for aircraft structure under service environments is established by combining the ASLE with the Miner theory. Furthermore, a service life extension method of aircraft structure is proposed based on a scope extension of the ASLE, including methods based on reliability analysis and structural repair. Finally, an application example of the ASLE is presented.

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Can pitting corrosion change the location of fatigue failures in aircraft?

Cited by 23 publications

References 25 publications

Effects of Prior Corrosion with and Without Stress on the Mechanical Properties of 7475-T761 Aluminum Alloy

Effects of Prior Corrosion with and Without Stress on the Mechanical Properties of 7475-T761 Aluminum Alloy

Effect of Corrosion and Surface Finishing on Fatigue Behavior of Friction Stir Welded EN AW-5754 Aluminum Alloy Using Various Tool Configurations

Service fatigue life and service calendar life limits of aircraft structure: aircraft structural life envelope

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