일반적으로 피로수명은 예측모델과 외부하중 및 기타 환경조건에서의 불확실성으로 인해 정확한 예측이 어렵다. 정확하고 신뢰성 있는 피로균열 예측을 바탕으로 강구조물의 수명관리가 효율적으로 수행될 수 있는데, 이를 위해서는 피로균열 성장 예측과 관련된 정보의 효과적이고 지속적인 업데이트가 필수적이다. 피로균열 예측 업데이트는 기존 예측모델의 변수들을 가용한 현재의 정보와 통합하는 과정을 의미하는데, 업데이트되는 변수들에 따라 예측모델의 결과가 달라진다. 본 연구에서는 피로균열 예측 업데이트에 필요한 가장 적절한 변수들을 결정하는 기법을 제시한다. 이를 위해 피로균열 예측 모델의 모든 변수들의 조합을 고려하여, 발견된 균열의 크기와 업데이트된 변수들의 차이를 평가한다. 피로균열 예측모델의 변수 업데이트를 위해 Markov chain Monte Carlo 시뮬레이션 기반 Bayesian 업데이트 기법을 적용하며, 발견된 균열의 크기와 업데이트된 예측균열의 크기 비교를 위해 평균절대오차(Mean absolute error) 기법과 Kullback-Leibler(KL) divergency 기법을 적용한다.

Aging aircraft structures are inevitably exposed to environment for a long time facing many potential problems, including corrosion and wide spread fatigue damage, which in turn cause the degradation of flight safety. In this study, the environmental surface damages on aging aircraft structures induced during service were quantitatively analyzed. Additionally, S-N fatigue tests were performed with center hole specimens extracted from aging aircraft structures. From the results of quantitative analyses of the surface damages and fatigue tests, it is concluded that corrosion pits initiated during service reduce the fatigue life significantly. Finally, using the fracture mechanics and the EIFS (equivalent initial flaw size) concepts, the remaining fatigue life was predicted based on actual fatigue test results.

PURPOSES: The objective of this paper is to select the confidential intervals by utilizing the second moment reliability index(Hasofer and Lind; 1974) related to the number of load applications to failure which explains the fatigue failure and rut depth that it indicates the permanent deformation. By using Finite Element Method (FEM) Program, we can easily confirm the rut depth and number of load repetitions without Pavement Design Procedures for generally designing pavement depths. METHODS : In this study, the predictive models for the rut depth and the number of load repetitions to fatigue failure were used for determining the second moment reliability index ( ). From the case study results using KICTPAVE, the results of the rut depth and the number of load repetitions to fatigue failure were deducted by calculating the empirical predictive equations. Also, the confidential intervals for rut depth and number of load repetitions were selected from the results of the predictive models. To determine the second moment reliability index, the spreadsheet method using Excel’s Solver was used. RESULTS : From the case studies about pavement conditions, the results of stress, displacement and strain were different with depth conditions of layers and layer properties. In the clay soil conditions, the values of strain and stresses in the directly loaded sections are relatively greater than other conditions. It indicates that the second moment reliability index is small and confidential intervals for rut depth and the number of load applications are narrow when we apply the clay soil conditions comparing to the applications of other soil conditions. CONCLUSIONS : According to the results of the second moment reliability index and the confidential intervals, the minimum and maximum values of reliability index indicate approximately 1.79 at Case 9 and 2.19 at Case 22. The broadest widths of confidential intervals for rut depth and the number of load repetitions are respectively occurred in Case 9 and Case 7.

Sheet aluminum alloys have been used in manufacturing of machine structures. In fatigue crack propagation behavior of thin sheet aluminum alloys, it is important that fatigue crack growth rate is affected by crack closure phenomenon. In this work, we analyzed the characteristics of fatigue crack propagation behavior in experiment of constant stress condition for thin sheet Al 2024-T3 alloys, and identified the retardation behavior of crack growth by comparing experimental results of thin and thick plate specimen. We attempt to operate the fatigue life estimating process using the fatigue related material constants from referred fatigue crack propagation analysis. And we analyzed the experimental and prediction results of fatigue life of thin sheet aluminum alloy in order to identify the relation between retardation behavior of fatigue crack growth and crack closure phenomenon.

본 논문은 선박용 엔진인 S60MC-C의 프레임 박스 용접부에 대한 피로수명 예측을 위한 수치적 기법을 제시한다. 피로 수명 평가를 위해 싸이클 동안의 동적인 응력변화를 계산해내야 하며, 이에 따라 선행된 연구에서 얻은 엔진의 한 싸이클 동안의 하중 조건으로 상용 유한요소해석 프로그램을 이용한 구조해석을 실시하였다. 구조해석은 8단계에 대해 이루어 졌으며, 그 결과를 바탕으로 프레임 박스 용접부의 피로수명 평가를 위해서 HSS(Hot spot stress), Reservoir counting method, Palmgren-miner's rule을 적용하였다. 결과적으로 구조해석을 통한 대상 엔진의 취약부와 과잉 설계부를 확인하였고, 피로수명의 평가를 통해 설계의 적절성 여부를 평가하였다.