• Journal of the Korean Institute of Gas
• /
• v.16 no.3
• /
• pp.29-34
• /
• 2012

Investigating safer ways to design and use to prevent a loss of life and property by failure of the structures are necessary and assessing total fatigue life with initiation and propagation of fatigue crack accurately through fatigue analysis is very important. The object of this study is to examine the initial life and propagation life when the fatigue crack is introduced from the root which is likely to appear in LOP(Lack of Penetration) cruciform fillet welded structure including bridges, ships and gas storage facilities which are impossible to be fully penetrated and to measure the rate of fatigue life until the final cleavage failure. As the result, each rate of fatigue life for fatigue failure is somewhat different in the range of 5% according to the thickness of material, however, the overall rate of initial life is in the range of 34~39% and propagation life showed the range of 61~66%.

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

• KSCE Journal of Civil and Environmental Engineering Research
• /
• v.13 no.2
• /
• pp.135-139
• /
• 1993

It was found in a series of test sections constructed in Houston, Texas that (1) concrete placement in hot season resulted in much more early-age cracks than that in cool season, and that, (2) for the hot season placement, pavements placed in the morning showed more early-age cracks than those placed in the afternoon. Early-age cracks, in this study, are defined as cracks occurring within a few days after construction. Since the early-age cracks have a tendency to be meandering and the crack widths are relatively wide, they may give an adverse effect on the long-term performance of the pavement. The objectives of this study are to recognize the effects of placement time on the early-age crack patterns and to find the reason of the effects. The effects are explained in this study by relating hydration of cement and surrounding temperature conditions.

• Proceedings of the Korean Institute of Industrial Safety Conference
• /
• 1998.05a
• /
• pp.57-62
• /
• 1998

구조물이나 기계요소내의 결함이 성장하여 파손(Failure)에 이르는 현상은 공학분야에서 중요하게 평가되어 오고 있다. 반복적으로 변하는 응력에 의하여 결함이 초기 성장을 거쳐 재료의 파손에 이르게 되는 과정인 피로파괴는 파괴역학의 한 중요한 분야이다. 이에, 본 연구에서는 열처리의 특성상 부식환경에 매우 민감한 Al-Zn-Mg-Cu Alloy 7075에 대하여 Peak Aged T65l Tempering을 실시한 Al-Alloy 7075-T65l에 대하여 각기 환경(대기, 물, 해수)의 변화가 부식피로균열성장에 미치는 영향과 부식환경에서의 긴 균열(Long Crack)과 짧은 균열(Short Clark)의 부식피로균열 성장특성을 비교, 고찰하여 초기균열의 잠재시간과 안정성장 시간을 예측하여 구조물의 수명예측 및 안전성 평가에 기여 할 수 있는데 목적이 있다. (중략)

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.21 no.7
• /
• pp.638-644
• /
• 2020

This study examines cracks that occur under the load of an aircraft. The life of aircraft vulnerability structures was analyzed and structural fitting improvements were made. Structural integrity and safety have been achieved through preemptive life expectancy and life management of aircraft structures. The crack size inspection capability of the aircraft under analysis is 0.03inch, compared with 0.032inch, which is the lowest of the three vulnerable parts. In addition, the fatigue life analysis results in approximately 1450 operating hours, the lowest of the three vulnerable parts relative to the aircraft's required life of more than 15000 operating hours, which increased the repeat count of the aircraft's initial and re-inspection times, and hence raised the resulting costs and manpower consumption. Finally, the features were improved through structural fitting of the identified three weak parts. The lowest critical crack size was secured at 0.13 through increased structural resistance to generated cracks and increased aircraft safety. The lowest structural fatigue life for cracks occurring during aircraft operation is 25000 operating hours, which are analyzed above the required structural life, resulting in more optimized improvements than the repair costs and excessive fitting range caused by cracks and fractures.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.8 no.5
• /
• pp.1173-1178
• /
• 2007

A laboratory investigation is conducted to characterize and quantity fatigue life of continuously reinforced concrete pavement with initial cracks. Four specimens scaled were made based on results of finite-element analyses and stress-strain curve comparisons. Static tests were firstly performed to obtain magnitudes of static failure loads and to predict crack patterns before fatigue tests. The fatigue lives measured in the study were compared based on the initial crack spacing. The comparison indicates that the fatigue lives of most specimens increases with increasing the initial crack spacing. The results obtained in the study can be used for maintenance and retrofit of the continuously reinforced concrete pavements.

• Composites Research
• /
• v.17 no.4
• /
• pp.68-73
• /
• 2004

An analytical study was conducted to characterize the fatigue crack growth behavior of pre-cracked aluminum plates repaired with asymmetric bonded composite patch. For single-sided repairs, due to the asymmetry and the presence of out-of$.$plane bending, crack front shape would become skewed curvilinear started from a uniform through-crack profile, as observed from Previous studies. Therefore, for the accurate investigation of fatigue behavior, it is necessary to predict the actual crack front evolution and take it into consideration in the analysis. In this study, the fatigue analysis of single-sided repairs considering crack front shape development was conducted by implementing three-dimensional successive finite element method coupled with linear elastic fracture mechanics (LEFM) concept, which enables the growing crack front to be directly traced and modeled in a step by step way. Through conducting present analysis technique, crack path of the patched plate as well as the fatigue life was evaluated with sufficient accuracy. The analytical predictions of both the crack front shape evolution and the fatigue life were in good agreement with the experimental observations.

• Transactions of the Korean Society of Mechanical Engineers
• /
• v.16 no.8
• /
• pp.1536-1544
• /
• 1992

A relatively simple prediction method is proposed for initially semicircular surface crack growth under axial loading. The method takes into account the difference in surface crack closure behavior at the depth point and at the surface intersection point, and also the relationship of crack closure for surface crack and through-thickness crack. The prediction method provides conservative estimation for fatigue life within factor of two, and the predicted crack geometry variations agree well with the observed results. As a result, the prediction method proposed here is considered to be useful for engineering application.

• Proceedings of the KWS Conference
• /
• 2010.05a
• /
• pp.56-56
• /
• 2010

최근 강구조물의 건설이 지속적으로 증가되어 왔다. 또한 강구조물의 유지관리 및 안전성에 대한 관심이 급증하고 있다. 시설물의 안전성 확보는 대형사고의 사전 예방, 공용 중 갑작스런 가동 중지에 의하여 발생되는 비용증가를 사전에 차단 할 수 있다는 점에서 그 중요성은 매우 크다고 할 수 있다. 또한 각종 구조물은 열악한 사용조건, 고온, 고압, 고속, 대형화됨에 따라 일단 사고가 발생 했을 경우 대형사고의 위험이 예상되므로, 제작시 검사의 강화뿐만이 아니라 공용 중 구조물의 안전성을 진단 할 수 있는 모니터링 체계의 확립이 필요한 시점이다. 현재 국내에서 강구조물들의 균열 모니터링 시스템에 관한 연구는 매우 미흡한 실정이며, 현재 사용되고 있는 비파괴검사 방법은 UT와 RT등이다. 이러한 방법들은 많은 시간과 경비가 소요되며 또한 거대구조물 혹은 사람의 접근이 어려운 곳에는 적용하기가 힘들다. 또한 주기적인 검사 작업으로 인한 막대한 시간과 비용의 손실이 발생되고 있으며 초기 결함을 조기에 인지하지 못함으로써 적절한 보수 보강 대책이 이루어지지 않아 보수 보강 비용의 증대를 초래한다. 더욱이, 결함이 진전된 이후에도 이것을 인지하지 못하여 적절한 대응을 하지 않는다면 대형사고로 이어질 수도 있다. 따라서 강구조물에 대한 효율적인 유지관리가 가능하고, 초기결함으로부터 균열이 진전하여 붕괴되는 사고를 미연에 방지하며 초기에 보수보강 작업을 수행함으로써 보수보강 비용도 절감 할 수 있는 모니터링 시스템의 개발이 요구되고 있다. 이러한 모니터링 시스템의 개발은 기술적 측면에서 강구조물의 효율적인 유지 관리 노하우를 얻을 수 있으며 경제 산업적 측면에서는 보수 보강 비용 및 불필요한 주기적 점검 비용을 절감 할 수 있다. 이 연구에서는 전위차법을 이용하여 강구조물의 필렛 용접부에서의 균열진전양상을 파악하고 정량화를 통해 필렛용접부의 잔여수명을 예측하였다.

• Journal of Advanced Marine Engineering and Technology
• /
• v.18 no.3
• /
• pp.52-62
• /
• 1994

기계나 구조물 파괴의 대부분은 노치부를 기점으로 하여 발생하기 때문에 첨단복합재료를 노지부 재로서 안전하면서도 경제적으로 사용하기 위해서는 각종 조건하에 있어서 강도특성을 명확히 하는 것은 대단히 중요하다. 본 연구에서는 노치를 갖는 복합재료를 이용하여 각종조건하에서 강도특성평가실험을 행하였으 며, 얻어진 결과를 종합하면 다음과 같다. (1) 첨단복합재료 노치재는 試驗片의 幾可學的 形狀과는 관계없이 노치반경 p만에 의해 결정되는 최대탄성응력 $\sigma_{max}$일정의 條件下에서 破t짧된다. (2) 破斷時 최소단면에서의 공칭응력 $\sigma_{c}$와 응력집중계수 $K_{t}$와의 관계에 있어서,$\sigma_{c}$의 값이 $K_{t}$의 증대와 더불어 떨어지고 있는 부분과, $K_{t}$와 관계없이 거의 일정하게 되고 있는 부분으로 나누어지는 現象은 노치재의 回轉굽힘 또는 인장압축파열에서 보여지는 현상과 外觀上 對應하고 있다. 즉, 정적파괴와 피로파괴는 파괴의 양상이 비슷하다 (3) PEN수지단체의 경우, 피로균열발생은 점발생적 피로균열이 최대탄성응력에 의해 지배되며, 노치에 만감하며,균열전파수명은전수명에 비해 상당히 짧다. (4) 단탄소섬유강화복합재료의 경우, 피로균열은 섬유端에 응력이 집중하기 때문에 일반적으로 섬유端에서 아주 빠른 시기에 발생하지만, 섬유가 피로균열진전에 대해 방해물로 작용하기때문에 아주 천천히 전파한다. (5) 短탄소鐵維는 피로균열발생에 대해서는 負의 강화작용 전수명의 극히 초기단계에 피로균열 발생을, 피로균열전파에 대해서는 正의 강화작용을 한다. (6) 단탄소섬유를 PEN에 강화함으로 인해 정적강도 보다 피로강도에 더 큰 강화효과를 초래했으며, 선형노치역학의 개녀은 첨단 복합재료의 강도평가에 대단히 유효했다.