• Journal of Aerospace System Engineering
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• v.17 no.2
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• pp.62-70
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• 2023

We proposed a technique for predicting Stress-Life (S-N) curve or fatigue life using geometric features of a ply-overlap joint structure in which plies of two composite materials are partially or wholly laminated and bonded. Geometric features that could affect fatigue properties of a structure were selected as variables. By analyzing relationships between geometric variables and material constants of the Epaarachchi-Clausen model, a fatigue model for composites, relational expressions of these two factors were proposed. To verify the prediction accuracy of the proposed method, fatigue life of a CFRP/GFRP ply-overlap joint was predicted. Predicted life and life obtained by test data-based model were compared to actual life. High prediction accuracy was confirmed by calculating the coefficient of determination of the predicted S-N curve.

• 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.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.12
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• pp.1048-1058
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• 2017

One of the failure mechanism of spaceborne electronics is a fatigue fracture on solder joint under launch random vibration. Thus, a necessity of early diagnosis through the fatigue life evaluation on solder joint arises to prevent such potential risk of failure. The conventional life prediction methods cannot assure the accuracy of life estimation results if the packaging type changes, and also requires much time and effort to construct the analysis model of highly integrated PCB with various packaging types. In this study, we performed life prediction of PCB based on a reliability and life prediction tool of sherlock as a new approach for evaluating the structural reliability on solder joint, and those prediction results were validated by fatigue tests. In addition, we also investigated an influence of solder height on the fatigue life of solder joint. These results indicated that the Sherlock is applicable tool for evaluating the structural reliability of spaceborne electronic.

• The Korean Journal of Applied Statistics
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• v.24 no.1
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• pp.115-125
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• 2011

By use of a mortality forecasting model and a life table, forecasting the average life expectancy is an effective way to evaluate the future mortality level. There are differences between the actual values of average life expectancy at present and the forecasted values of average life expectancy in population projection 2006 from Statistics Korea. The reason is that the average life expectancy forecasts did not reflect the increasing speed of the actual ones. The main causes of the problem may be errors from judgment for projection, from choice, or use of a mortality forecasting model. In this paper, we focus on the choice of the mortality forecasting model to inspect this problem. Statistics Korea should take a mortality forecasting model with considerable investigation to proceed population projection 2011 without the errors observed in population projection 2006. We compare the five mortality forecasting models that are the LC(Lee and Carter) model used widely and its variants, and the HP8(Heligman and Pollard 8 parameter) model for handling death probability. We make average life expectancy forecasts by sex using modeling results from 2010 to 2030 and compare with that of the population projection 2006 during the same period. The average life expectancy from all five models are forecasted higher than that of the population projection 2006. Therefore, we show that the new average life expectancy forecasts are relatively suitable to the future mortality level.

• Proceedings of the Korea Contents Association Conference
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• 2011.05a
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• pp.339-340
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• 2011

본 연구는 N말단 아미노산 종류에 따라 단백질의 수명(half-life)이 결정된다는 N-end rule을 기반으로 단백질 수명을 예측해주는 프로그램인 protparam의 결과와 bleach-chase를 이용한 실험 데이터를 비교 분석하였다. 단백질 수명을 결정하는 여러 요인들을 고려하지 않고 한 가지 요인만을 반영한 protparam의 결과는 실제 측정값과 현격한 차이를 나타낸다. 특히 실제 단백질은 NME(N-terminal Methionine Excision) 현상이 일어나는데 이를 고려하지 않고 유전체에서 번역한 그대로의 아미노산 서열을 가지고 단백질 수명을 계산하는 한계를 가지고 있다. 이에 본 연구에서 N말단 아미노산을 순차적으로 제거하여 N-end rule을 적용한 결과도 실험 데이터와 일치하지 않는 결과를 보여주고 있음을 확인하였다. 따라서 현재 사용되고 있는 단백질 수명 예측 프로그램은 이런 문제점을 가지고 있기 때문에 새로운 예측 알고리즘의 개발이 요구된다.

• Journal of Korean Society of Steel Construction
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• v.14 no.2
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• pp.365-373
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• 2002

In this paper, the system reliability concept was presented to predict the lifespan of bridges. Lifetime distribution functions (survivor functions) were used to model real bridges to predict their remaining life. Using the system reliability concept and lifetime distribution functions (survivor functions), a program called LIFETIME was developed. The survivor functions give the reliability of component at time t. The program was applied to an existing Colorado state highway bridge to predict the failure probability of the time-dependent system. The bridge was modeled as a system, with failure probability computed using time-dependent deteriorating models.

• Journal of the KSME
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• v.36 no.9
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• pp.855-866
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• 1996

승요차 앞자축에 장착되어 회전하면서 동력을 전달하는 드라이브축은 운행중에 주로 비틀림하중을 받는다. 따라서 동 부품의 피로해석 및 설계를 위해서는 실제 운행중에 받는 서비스토크의 크기, 주파수 등에 관한 데이터가 필요하다. 차량에 탑재된 엔진의 토크와 회전수 등의 규격으로부터 드라이브축에 부가되는 최대 토크 값을 예측할 수 있으나, 자동차 운행주에는 승차인원, 도로조건, 운전자의 운전습관 등 여러가지 외적인 영향으로 인하여 서비스토크가 불규칙하게 변할 것으로 예상되므로 서비스토크를 정확히 예측하기는 어려운 실정이다. 또한, 최근의 자동차 구조부품에 대한 설계개념이 무한수명 설계에서 경량화 설계로 변화되고 있으며, 따라서 자동차 드라이브축도 실제 운용하중을 바탕으로 한 정확한 수명예측 및 강도설계가 요구되고 있다. 본 연구에서는 4륜구동형 승용차용 드라이브축에 대해 실제 운용하중에서의 피로수명을 예측하기 위해 1)텔리메트리를 이용하여 토크를 측정하고, 2) 일정진촉하중하에서의 드라이브축의 비틀림 피로시험을 수행하고, 3) 일정진폭하중하에서의 드라이브축의 비틀림 피로시험을 수행하고, 4) 축류 소재의 피로특성 데이터를 구성하여 5) 자체 개발한 프로그램으로 피로수명을 예측하고자 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.2
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• pp.44-49
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• 2011

A study of the fatigue life of copper alloy which was used in inner jacket of regenerative cooling chamber of liquid rocket engine has been performed. Generally used life prediction methods -original universal slopes method, modified universal slopes method, Mitchell's method, B$\"{a}$umel and Seeger's method, and Ong's method- have been used for predicting the fatigue data. It was found that the novel life prediction method which was modified from Ong's method was suggested since almost all data have not been predicted well with the widely used methods. The suggested modified Ong's method predicted well within 3X scatterbands.

• Composites Research
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• v.26 no.2
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• pp.79-84
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• 2013

The prediction and analysis procedure of fatigue damage crack growth life for a stiffener bonded composite laminate panel including center hole and edge notch damage, was studied. It was performed on the basis of fatigue damage growth test results on a laminated skin panel specimens and the analysis results of stress intensity factor for the stiffener bonded composite panel. According to the comparison between experimental test and prediction results of fatigue damage growth life, it was concluded that the residual strength and damage tolerance assessment can be carried out along to the edge notch crack growth.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.89-92
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• 2010

A study about the fatigue life of copper alloy which is used in inner jacket of regenerative cooling chamber of liquid rocket engine has been performed. Generally used life prediction methods-original universal slopes method, modified universal slopes method, Mitchell's method, Baumel and Seeger's method, and Ong's method-have been used for predicting the fatigue data. It was found that the novel life prediction method which is modified from Ong's method was suggested since almost all data have not been predicted well with the widely used methods. The suggested modified Ong's method predicted well within 3X scatterbands.