• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.1
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• pp.46-51
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• 2007

In this study, test results for fatigue crack propagation of Al-2024-T3511 are presented considering corrosion effects, and fatigue lifes are compared for the cases of corrosion and non-corrosion. Higher corrosion environments show lower fatigue life and faster crack growth. To predict the corrosion fatigue life, a corrosion factor concept is newly introduced and applied in Paris' law. The predicted results show good agreement with experimental data and this corrosion fatigue model can be successfully used for the prediction of fatigue life of aluminum structure with corrosion effects.

• Journal of the Korea institute for structural maintenance and inspection
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• v.22 no.1
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• pp.129-136
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• 2018

The estimation of the fatigue design life for large welded structures is usually performed using the liner cumulative damage method such as Palmgren-Miner rule or the equivalent damage method. When a fatigue crack is detected in a welded steel structure, the residual service life has to be estimated base on S-N curve method and liner elastic fracture mechanics. In this study, to examine the 3D fatigue crack behavior and estimate the fatigue life of out-of-plane gusset fillet welded joint, the fatigue tests were carried out on the model specimens. Investigations of three-dimensional fatigue crack propagation on gusset welded joint was used the finite element analysis of FEMAP with NX NASTRAN and FRANC3D. Fatigue crack growth analysis was carried out to demonstrate the effects of aspect ratio, initial crack length and stress ratio on out-of-plane gusset welded joints. In addition, the crack behaviors of fatigue tests were compared with those of the 3D crack propagation analysis in terms of changes in crack length and aspect ratio. From this analysis result, SIFs behaviors and crack propagation rate of gusset welded joint were shown to be similar fatigue test results and the fatigue life can also be predicted.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.34 no.5
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• pp.611-617
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• 2010

A complex system involves a large number of design variables, and its operation is non-linear. To explore the characteristics in its design space, a Kriging meta-model can be utilized; this model has replaced expensive computational analysis that was performed in traditional parametric design optimization. In this study, a Kriging meta-model with a computational orthogonal array for the design of experiments was developed to optimize the fatigue life of a turbine blade whose behavior under cyclic rotational loads is significantly non-linear. The results not only show that the maximum fatigue life is improved but also indicate that the accuracy of computational analysis is achieved. In addition, the robustness of the results obtained by six-sigma optimization can be verified by comparison with the results obtained by performing Monte Carlo simulations.

• Transactions of the Korean Society of Mechanical Engineers
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• v.15 no.3
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• pp.931-935
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• 1991

본 연구에서는 유효응력확대계수로서 피로크랙 진전수명을 평가할 수 이용되 는 크랙열림비(본 논문에서는 후술하는 최대응력에 대한 크랙 열림응력의 비를 크랙 열림비로 하다)가 진전수명에 미치는 영향을 평가하기 위한것으로서, 제1보에서는 실 험에 의하여 크랙 열림점을 실측한 결과 측정입치에 따라 다른 값을 나타내며 수명평 가법 크랙 선단으로부터 떨어진 곳(크립게이지를 이용한 크랙마우스등)에서 측정한 크 랙 열림점 값을 이용함이 보다 정확함을 밝혔다.본 제2보에서는 크랙열림비가 수명 평가에 미치는 영향을 상기의 파라미터 영향도 평가수법을 이용하여 평가하고자 한다.

• International Journal of Highway Engineering
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• v.6 no.3 s.21
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• pp.27-35
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• 2004

There are two methods in estimating the remaining life of in-service airfield concrete pavement. They are a method simply using the past accumulated traffic and a method using the theoretical mechanistic analysis. Since the former method is somewhat far from the actual condition, the latter method is widely used by most engineers and researchers. The most essential component of the latter method is the fatigue model of the concrete slab. A fatigue model for airfield concrete pavement is developed in this study by a series of fatigue tests using 30 concrete cylinder specimens obtained from a 10 year old in-service airfield concrete slab. Strengths for the stress ratio calculation were obtained from the split tensile test of the cores sliced. Fatigue test mode was repeated split tensile test. The R2 of developed fatigue model was 0.5. Specimens taken from another airport had been tested for validation of the model. The results showed a good fit to the model. It was also found that the fatigue life predicted from the model was a tittle greater when the stress ratio is greater than 80 percent than other fatigue models developed earlier in America.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.1
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• pp.339-346
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• 2019

Various studies have been conducted to evaluate the probabilistic fatigue life of steel railway bridges, but many of them are based on a relatively simple model of crack propagation. The model assumes zero minimum stress and constant loading amplitude, which is not appropriate for the fatigue life evaluation of railway bridges. Thus, this study proposes a new probabilistic method employing an advanced crack propagation model that considers the live-dead load ratio for the fatigue life evaluation of steel railway bridges. In addition, by using the rainflow cycle counting algorithm, it can handle variable-amplitude loading, which is the most common loading pattern for railway bridges. To demonstrate the proposed method, it was applied to a numerical example of a steel railway bridge, and the fatigue lives of the major components and structural system were estimated. Furthermore, the effects of various ratios of live-dead loads on bridge fatigue life were examined through a parametric study. As a result, with the increasing live-dead stress ratio from 0 to 5/6, the fatigue lives can be reduced by approximately 30 years at both the component and system levels.

• The Journal of the Acoustical Society of Korea
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• v.28 no.7
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• pp.646-652
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• 2009

In this paper, welding pitch optimization technique of vehicle subframe is presented considering the fatigue life of spot welding nuggets. Fatigue life of spot welding nuggets is estimated by using the frequency-domain fatigue analysis technique. The input data, which are used in the fatigue analysis, are obtained by performing the dynamic analysis of vehicle model passing through the Belgian road profile and also the modal frequency response analysis of finite element model of vehicle subframe. According to the fatigue life result obtained from the frequency-domain fatigue analysis, the design points to optimize the weld pitch distance are determined. For obtaining the welding pitch combination to maximize the fatigue life of the spot welding nuggets, 4-factor, 3-level orthogonal array experimental design is used. This study shows that the optimized subframe improves the fatigue life of welding nugget with minimum fatigue life about 65.8 % as compared with the baseline design.

• Journal of the Korean Society of Fisheries and Ocean Technology
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• v.36 no.2
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• pp.147-154
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• 2000

실온 대기 중에서 탄소강배관(STS370)의 피로시험을 행하였다. 배관에는 외부결함을 인공적으로 상정하여, 피로균열진전 및 관통의 거동, 균열형상, 누설 및 파단수명, 균열개구변위를 실험과 이론의 양면으로부터 비교·검토하였다. 특히, 배관의 벽두께 관통후에 있어서의 응력확대계수를 평가하기 위하여 새로운 식을 제안하였다. 피로균열이 관벽을 관통하기 전에 있어서는 판모델에 의한 Newman-Raju의 응력확대계수 평가식을 이용하므로서 aspect비와 누설수명 등 관통전의 피로균열성장거동을 평가할 수 있음을 나타내었다. 또한, 피로균열이 관벽을 관통한 후에 있어서는 본 논문에서 제안한 배관모델에 의한 응력확대계수의 평가식을 이용하여 관통후의 균열형상, 파단수명 및 균열개구변위 등 관통후의 피로균열성장거동을 평가하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.1
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• pp.35-40
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• 2019

The objective of this paper is to identify the fatigue properties of carbon-fiber composite which is widely applied for the development of aircraft structures and obtain data for full-scale fatigue test. The durability and damage tolerance evaluation of composite structures is achieved by fatigue tests and parameters such as fatigue life factor and load enhancement factor. The specimens are made with carbon-fiber/epoxy UD tape and fabric prepreg. Fatigue tests are performed with several stress ratios and lay-up patterns. The Weibull shape parameters are analyzed by Sendeckyj model and individual fatigue lives with Weibull distribution. And the fatigue life factor and load enhancement factor considering reliability are evaluated.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.7
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• pp.642-652
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• 2009

Most of lap jointed aircraft structures encounter the fretting damages, which provoke fretting cracks prematurely and lead to significant reduction of fatigue life. In the case of ageing aircrafts especially, this fretting fatigue problem is a fatal threat for the safety and airworthiness. Recently, as the service life extension program(SLEP) of ageing aircrafts has become a hot issue, the prediction of fretting fatigue life is also indispensable. On these backgrounds, a series of experimental tests of fretting fatigue on bolted lap joint specimens, were performed. And the fretting crack initiation and propagation life of each specimen were evaluated using existing and newly proposed prediction models with the fretting parameters obtained from the FEA results for elasto-plastic contact stress analyses. The validations of prediction models were also discussed, comparing the prediction results with experimental test ones.