• Journal of Aerospace System Engineering
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• v.14 no.spc
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• pp.1-6
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• 2020

The flaw tolerance evaluation requirement prescribed in Federal Aviation Regulation (FAR) §29.571 Amendment 55 was established in 2012. As a result, there are not many datas of flaw tolerance evaluation. This paper introduces the series of processes and evaluation methods carried out for certification based on the flaw tolerance evaluation. An initial flaws were artificially formed on the main rotor actuator and then the damage tolerance test was performed, which was twice life time of design requirements, to demonstrate that the main rotor actuator of the rotorcraft is sufficiently capable of flaw tolerance.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.4
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• pp.306-313
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• 2011

The damage tolerance analysis is required to guarantee the structural safety and the reliability for aircraft components. The damage tolerance method, which evaluate the life considering the initial crack, considers a fatigue design model of the aircraft main structure. The fatigue crack growth life should be calculated in damage tolerance analysis and the inspection time to define the replacement cycle. In this paper, the damage tolerance analysis is performed for a turbine wheel which has complex geometry. The equation of the stress intensity factor for complex geometry is hard to know, so that they are usually processed by finite element analysis which takes long time. To solve this problem, the stress intensity factors at specified crack are obtained by the FEA and the crack growth life is evaluated using the surrogate model which is generated by the regression analysis of the FEA data. From the results, the efficiency of the crack growth life calculation and the damage tolerance analysis could be increased by taking the surrogate model.

• 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 Reliability Society Conference
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• 2000.04a
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• pp.161-168
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• 2000

고리 3,4호기 및 영광 1,2호기의 원자로보호계통 및 공학적안전설비작동계통의 정기점검주기와 허용정지시간에 대하여 계통의 신뢰도와 노신손상빈도를 평가하여 안전성이 저해되지 않는 범위에서 합리적인 정기점검주기와 허용정지시간을 도출하였다. 이를 위하여 원자로보호계통의 17개 원자로정지신호와, ESFAS계통의 11개의 안전설비작동신호에 대해서 고장수목을 작성하였고, 정기점검주기 변화에 따른 신뢰도를 평가하였다. 또한 계통의 신뢰도가 발전소의 안전성에 어떤 영향을 미치는가를 파악하기 위하여 노심손상빈도를 분석하였다. 분석 결과 현행 1개월의 점검주기를 3개월로 연장한다 하더라도 신뢰도는 20%미만 노심손상빈도는 2%정도 저하되는 것으로 나타났다. 이런 정도의 신뢰도와 위험도가 변화는 원자력발전소의 안전성에 거의 영향을 주지 못하기 때문에 점검주기를 연장하는 안이 타당한 것으로 나타났다.

• Journal of the Korean Society for Nondestructive Testing
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• v.23 no.2
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• pp.116-124
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• 2003

• Transactions of the Korean Society of Mechanical Engineers A
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• v.41 no.2
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• pp.129-136
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• 2017

This study aims to assess the damage tolerance of the wing structure of aged aircraft with long-term service through the fatigue crack growth analysis and tests. For the fatigue-critical locations (FCL) W2 and W4 in the wing structure, the fatigue stress spectrum was derived based on a previous study. Thereafter, a crack propagation analysis for the FCLs was conducted using the commercial software $NASGRO^{TM}$. The algorithm for the fatigue stress spectrum was verified. Fatigue crack growth tests were then performed for two types of specimens: Type #1 was extracted from the wing structure of aged aircraft, and Type #2 was made of the same material as the wing structure. By comparing the experimental results of these specimens, we assessed the damage tolerance of the wing structure of aged aircraft with service time.

• Journal of the KSME
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• v.54 no.7
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• pp.28-33
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• 2014

최근 풍력에너지 발전기술이 해상 풍력 및 대형 풍력으로 천이되어 감에 따라 더 향상된 신뢰성 기술을 요구하고 있고, 풍력 블레이드는 풍력발전시스템에서 고장 빈도가 비교적 낮지 않고, 고장 발생 시 심각도가 상대적으로 높아 신뢰성을 고려해야 하는 부품이다. 블레이드 제작 생산 과정과 사용 중에 발생하는 손상 및 결함은 신뢰성의 심각성에 큰 영향을 미치고 있어 본 기술에서는 블레이드에서 발생할 수 있는 결함 유형, 결함을 탐지하는 기술 그리고 신뢰성을 평가하는 시험/평가 기술에 대하여 소개하고자 한다.

• 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.

• Proceedings of the Korean Institute of Industrial Safety Conference
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• 2003.10a
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• pp.101-106
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• 2003

항공기 외부 장착물인 POD는 전자전 방해장치(ECM, electronic counter measures)로서 전자방해 장비 및 부분 부품인 전ㆍ후방 러그(lug)와 외부 케이스로 이루어져 있다. POD는 항공기 외부 동체 하단부 및 파일런(pylon)에 장착되어 작동하므로 항공기의 운용중 이륙부터 착륙간의 기동에 의한 피로하중을 주로 받게 되므로 POD 부품들에 대한 구조 건전성 확보하기 위해서는 MIL-STD-1530의 요구에 따라 내구성(durability) 및 손상허용설계(damage tolerance design) 의 평가가 요구되고 있다.(중략)

• Journal of the Korea Academia-Industrial cooperation Society
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• v.13 no.12
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• pp.6151-6158
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• 2012

By the activation of environment-friendly river works, application of vegetation mats is increasing, however, evaluation techniques for hydraulic stability of vegetation mats are not presented. This study is conducted to develop the objective test method for vegetation mats. Two kind of vegetation mats are tested by the real scale experiments, and hydraulic quantities are measured and analyzed to evaluate acting shear stresses. Roughness and shear stress are evaluated by 1 D non-uniform model. After each tests, changes in mat surfaces and sub-soil are evaluated, and from these evaluation, 3 types of mat surface damages and 2 types of sub-soil damages are presented. In the study, the case in which some damages in mat surface don't cause loss of sub-soil, is presented to be in the stable condition. Appling this stable condition and acting shear stresses, permissible shear stresses of vegetation mats are evaluated, and the results show that the reinforced mat with wire netting has more permissible shear stress.