Inspection interval optimization of aircraft landing gear component based on risk assessment using equivalent initial flaw size distribution method

Lee, Young-Jun; Park, Jongwoon; Lee, Dooyoul

doi:10.1177/14759217211033625

Cited by 11 publications

(15 citation statements)

References 12 publications

(18 reference statements)

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“…It was reported that performing NDT resulted in a highly conservative design 4 . The reason for this is discussed herein based on discretized crack length distributions for simplicity 11 . The crack length distribution after an inspection at cycle N can be expressed as

\begin{matrix} true \\ p ({\overset{truê}{x}}^{(k)}) = p_{N} ({\overset{truê}{x}}^{(k)}) (1 - L ({\overset{truê}{x}}^{(k)})) + p_{0} ({\overset{truê}{x}}^{(k)}) L ({\overset{truê}{x}}^{(k)}), \end{matrix}

where p N is the probability mass function (PMF) for the crack length distribution at cycle N , p 0 the PMF for the initial crack length, and L the POD.…”

Section: Resultsmentioning

confidence: 99%

“…This method is known as the equivalent initial flaw size (EIFS) method. Information regarding the crack shape, loading history, and crack growth law is required when using the EIFS method 11 …”

Section: Introductionmentioning

confidence: 99%

“…Work 11 by one of the authors showed that the EIFS method is beneficial for model calibration; however, its application is limited by its requirement for a significant amount of test data and its dependency on the applied stress level. Makeev et al 16 raised the necessity of the capability to isolate the variability of the initial flaw size from the known variability of the crack growth model parameters with unknown accurate values for each crack to predict a dataset‐independent EIFS distribution.…”

Section: Introductionmentioning

confidence: 99%

“…Information regarding the crack shape, loading history, and crack growth law is required when using the EIFS method. 11 Small-crack growth depends significantly on the material microstructure. McEvily 12 said that considerable uncertainties are present owing to the randomness of the grain size, grain orientation, and initial flaw shape.…”

Section: Introductionmentioning

confidence: 99%

“…15 For probabilistic risk analyses (PRAs) that consider uncertainties in the size of initial cracks, nonnegative distributions, such as the log-normal and Weibull distributions, are used to model the distribution of initial crack lengths. 2,11,16,17 In many cases, the condition of the structure after a repair action can be considered statistically independent of the condition prior to the repair. 18 Thus, the same distribution as the initial crack size distribution is commonly used in practicing PRA.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Bayesian method for estimating initial crack size distribution for probabilistic risk analysis of repairable structural details

Lee

Lim²,

Kim³

et al. 2022

Fatigue Fract Eng Mat Struct

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A Bayesian method for estimating the initial crack length distribution is proposed for probabilistic risk analysis (PRA) of repaired structural details. Noninformative prior is updated using a likelihood function, which is constructed using inspection capability, structural geometry, and material properties. The likelihood function based on the equivalent initial flaw size method was used for the left tail to avoid calculating the small-crack growth. The right tail was estimated based on the inspection capability and the maximum possible crack length. The proposed method alleviates the difficulties in selecting the initial crack-length distribution parameters. As an application, the KT-1 aircraft risk after the repair was analyzed. The PRA was conducted using the initial crack length distribution estimated via the proposed method. The result was compared with the conventional lognormal initial crack-length distribution.

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\begin{matrix} true \\ p ({\overset{truê}{x}}^{(k)}) = p_{N} ({\overset{truê}{x}}^{(k)}) (1 - L ({\overset{truê}{x}}^{(k)})) + p_{0} ({\overset{truê}{x}}^{(k)}) L ({\overset{truê}{x}}^{(k)}), \end{matrix}

where p N is the probability mass function (PMF) for the crack length distribution at cycle N , p 0 the PMF for the initial crack length, and L the POD.…”

Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Bayesian method for estimating initial crack size distribution for probabilistic risk analysis of repairable structural details

Lee

Lim²,

Kim³

et al. 2022

Fatigue Fract Eng Mat Struct

Self Cite

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show abstract

Repair tolerance assessment for aircraft composite structures using Bayesian updating

LI,

ZUO,

YANG

2024

Chinese Journal of Aeronautics

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A sparse, triangle-shaped sensor array for damage orientation and characterization of composite structures

Qiu

Liao

et al. 2023

Smart Mater. Struct.

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Since numerous sensors are needed to create a sensor array for the structural health monitoring of large-scale structures, the equipment quantity and cost considerably increase. This study proposes a sparse, triangle-shaped sensor array to identify, orient, and assess the degree of structural damage in composite constructions in order to overcome this shortcoming. The damage-scattered Lamb waves are recorded by the sparse sensor array with a variety of features that are then extracted and fed into the Support Vector Machine (SVM) classification method. The location and severity of the damage in composite constructions can be determined by training the SVM model. The principle component analysis (PCA) technique is used to compress the wave feature vectors while maintaining the majority of the damage information because the high dimension of the wave feature vectors required a significant amount of calculation during the training phase. Proof-of-concept tests show that the trained model, by utilizing the many properties of Lamb wave signals, can orient and define the degree of damage with excellent accuracy. Multiple lamb wave properties can be used to make up for the triangle sensor array's loss of damage information. In conjunction with the SVM, the triangle-shaped sensor array that was proposed in this study can efficiently make it easier to identify and characterize damage to large-scale structures while using fewer sensors.

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Inspection interval optimization of aircraft landing gear component based on risk assessment using equivalent initial flaw size distribution method

Cited by 11 publications

References 12 publications

Bayesian method for estimating initial crack size distribution for probabilistic risk analysis of repairable structural details

Bayesian method for estimating initial crack size distribution for probabilistic risk analysis of repairable structural details

Repair tolerance assessment for aircraft composite structures using Bayesian updating

A sparse, triangle-shaped sensor array for damage orientation and characterization of composite structures

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