• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.1
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• pp.8-17
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• 2003

The butt lap joint structures which are usually designed by the concept of slow crack growth damage tolerance, show frequently the behaviors of multiple site fatigue crack growth around the fastener hole edges due to the fretting between the two jointed parts. In this paper, experimental tests of fatigue crack growth have been performed of a bolted butt lap joint structure having an initial corner crack at the fastener hole edge, with different fretting conditions under a flight load spectrum. The obtained test results were reviewed to investigate the effects of fretting fatigue cracks on the damage tolerance crack growth life. Computations of corner crack growth were also carried out using an existed model to compare with test results.

• Journal of Ocean Engineering and Technology
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• v.5 no.2
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• pp.85-93
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• 1991

피로 파괴연구의 급격한 발전에 따라 최근의 기계나 구조물들은 많은 분야에서 손상허용설계원리에 근거하여 설계되고 있다. 이러한 상황 하에서 피로파손의 정확한 특성을 밝히는 것은 신뢰성을 고려한 기계나 구조물의 설계에 있어 가장 중요한 요인이 된다. 피로파손은 많은 랜덤요소를 내포하고 있으므로 실험결과 분석 및 수명예측을 분석하기 위해서는 통계학적 해석이 요구되고 있다. 본 연구의 목적은 회전굽힘피로시험을 수행하고 피로수명을 분석하는데 정규분포, 대수분포, 지수분포 및 Weibull분포를 이용하여 실험결과와 비교하고 파손확률을 찾는데 있다.

• 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 Aviation and Aeronautics
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• v.10 no.1
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• pp.95-105
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• 2002

• Journal of Ocean Engineering and Technology
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• v.5 no.2
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• pp.225-225
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• 1991

• Proceedings of the KSR Conference
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• 2006.05b
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• pp.252-257
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• 2006

• Proceedings of the KSR Conference
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• 2006.05b
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• pp.295-299
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• 2006

• Journal of Aerospace System Engineering
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• v.1 no.2
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• pp.27-36
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• 2007

The Damage Tolerant Design is developed to help alleviate structural failure and cracking problems in aerospace structures. Recently, the Damage Tolerant Design is required and recommended for most of aircraft design. In this paper, the damage tolerant design is applied to tilt rotor UAV. First of all, the fatigue load spectrum for the tilt rotor UAV is developed and fatigue analysis is performed for the flaperon joint which has FCL (fatigue critical location). Tilt rotor UAV has two modes: helicopter mode when UAV is taking off and landing; fixed wing mode when the tilt rotor UAV is cruising. To make fatigue load spectrum, FELIX is used for helicopter mode. TWIST is used for fixed wing mode. Fatigue analysis of flaperon joint is performed using fatigue load spectrum. E-N curve approach is used for picking crack initiation point. The LEFM(Linear Elastic Fracture Method) is considered for analyzing crack growth or propagation. Finally, including the crack initiation and propagation, the fatigue life is evaluated. Therefore the Damage Tolerant Design can be done.

• Korean Journal of Organic Agriculture
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• v.4 no.2
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• pp.45-61
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• 1995

• Journal of Aerospace System Engineering
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• v.14 no.spc
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• pp.22-30
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• 2020

Composite rotor blades for rotorcraft have an intrinsic vulnerability to foreign object impact from its inherent structural characteristics of insufficient strength in the thickness direction, which may easily lead to internal structure damage. Therefore, defects and strength reducing effects caused by foreign object impact should be considered in fatigue evaluation of composite blades. For this purpose, the flaw tolerant safe-life and fail-safe concepts were adopted in fatigue evaluation since 1980s, and recently those concepts have been replaced by the damage tolerance concept. In this paper, the relevant standards for fatigue evaluation are analyzed focusing on fiber reinforced composite rotor blades used in rotorcraft. In addition, fatigue evaluation procedure of composite blades considering impact damages is proposed by reviewing the practices implemented through domestic development projects.