2023
DOI: 10.1016/j.ijfatigue.2023.107600
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Service-life assessment of aircraft integral structures based on incremental fatigue damage modeling

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Cited by 7 publications
(2 citation statements)
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“…The described approach is linear, which means that it assumes that the accumulation of damage is linearly related to the number of observed parts relevant to load cycles. Lindström et al [25] discuss how the relationship between constant amplitude stress and fatigue life is statistically described by a lognormal distribution; it addresses the need to adjust the model to account for various sources of variability like material batch differences and surface conditions. It is important to note that the approach proposed in this paper for calculating accumulated fatigue damage is only an approximation and may not accurately predict the fatigue behavior of the observed aircraft structural part due to various operational circumstances that were not recorded, such as the impact of corrosive environments or undocumented damage due to various operational occurrences.…”
Section: The Inference Modulementioning
confidence: 99%
“…The described approach is linear, which means that it assumes that the accumulation of damage is linearly related to the number of observed parts relevant to load cycles. Lindström et al [25] discuss how the relationship between constant amplitude stress and fatigue life is statistically described by a lognormal distribution; it addresses the need to adjust the model to account for various sources of variability like material batch differences and surface conditions. It is important to note that the approach proposed in this paper for calculating accumulated fatigue damage is only an approximation and may not accurately predict the fatigue behavior of the observed aircraft structural part due to various operational circumstances that were not recorded, such as the impact of corrosive environments or undocumented damage due to various operational occurrences.…”
Section: The Inference Modulementioning
confidence: 99%
“…An important aspect is determining the operational durability of aircraft structures, where a significant part of the elements are made of aluminum alloys. In [28], the fatigue strength of the 7050-T7451 aluminum alloy was analyzed. The work positively verified the model for assessing fatigue life in the HCF range under variable amplitude loads.…”
Section: Introductionmentioning
confidence: 99%