• Transactions of the Korean Society of Mechanical Engineers
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• v.15 no.1
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• pp.49-60
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• 1991

Fatigue behavior of carbon fiber reinforced polyimide composite materials was studied experimentally and analytically. The physical variables, such as cyclic displacements and hysteresis loop energy were observed during fatigue tests. Fatigue life of the investigated [0/90]$_{2S}$ laminates was predicted by H'||'&'||'H models which was proposed based on the fatigue modulus and resultant strain. The predicted fatigue life by H'||'&'||'H curves was reasonably close to the experimental data. Fractography study shows that fatigue failure mechanism of [0/90]$_{2S}$ laminated composite materials involves failure break, matrix tearing and fiber-matrix debonding as well as delamination of layers.

• Journal of Chest Surgery
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• v.42 no.2
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• pp.148-156
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• 2009

Background: As cardiovascular operations become more complex and sophisticated, there is an increasing need for various bioprostheses for use as components of blood vessels and heart valves. We developed a fatigue stimuli test instrument to objectively evaluate the mechanical durability of a bioprosthesis, and we tested several currently known processing methods for bovine pericardium and we then compared the results. Material and Method: Fresh bovine pericardium was collected at the butcher shop with using aseptic technique, and each piece of pericardium was fixated and/or decellularized by 16 representative methods. We measured the permeability and compliance of the processed bovine pericardium samples, and measured them again after exposure to the fatigue stimuli. All the pieces of pericardium underwent microscopic examinations before and after the fatigue stimuli. Result: A mixture of glutaraldehyde and solvent treatment showed better mechanical durability than did the single glutaraldehyde treatment. High concentration glutaraldehyde treatment showed equal or no worse results than did low concentration glutaraldehyde treatment. After SDS (sodium dodecylsulfate) decellularization, the mechanical property of the bioprosthesis became much worse ($20{\sim}190$ times) and the mechanical durability to the fatigue stimuli was also very poor. Conclusion: We obtained the basic durability data after various fixation methods with using a home-made fatigue test instrument.

• 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 of Propulsion Engineers
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• v.23 no.2
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• pp.111-117
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• 2019

An experimental study on the welding part of a heat transfer plate that constitutes the lightweight and high efficiency recuperator is presented in this paper. In particular, to find out the service life of the welded part, fatigue characteristics were determined through experiments. Experiments were carried out on two materials (STS347, AL20-25 + nb), which are selected as the material of the recuperator; further, the specimens were manufactured through the methods used for actual fabrication and the standards recommended by ASTM. To evaluate the mechanical properties of the specimens at room and high temperature, MTS-810 was used in a high-temperature furnace. The tensile test was carried out at room and high temperatures for each specimen. The fatigue test was carried out by setting the load ratio corresponding to 50%, 40%, 30%, 20%, and 10% of the tensile strength at the stress ratio of 0.1. Finally, the fatigue life characteristics obtained by the experiment were compared with the stresses owing to the load generated in the operating conditions of the recuperator, and the lifetime of the welds was evaluated to prepare for the operation time required by the UAV.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.40 no.8
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• pp.721-724
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• 2016

Because of the inherent uncertainties caused by the manufacturing process variations, future loading conditions, and incomplete damage models, the lifetimes of mechanical structures under field conditions are significantly different from the results obtained in the laboratories. In this study, a dual sensor was developed to prognosticate the fatigue failure of structures under these uncertain conditions, and its effectiveness was demonstrated on a rectangular columnar structure under repeated uni-axial loading. The dual sensor is a slightly weaker structure embedded in the target structure, so that failure occurs in the sensor earlier than in the target structure. From the signal differences in the strain gauges in the embedded dual sensor, it is possible to differentiate between the normal status and warning status, even under variable loads.

• The korean journal of orthodontics
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• v.30 no.5 s.82
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• pp.625-642
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• 2000

The purpose of this study is to evaluate the effects of mechanical and thermal fatigue stress on the shear, tensile and shear-tensile combined bond strengths(SBS, TBS, CBS) in various orthodontic brackets bonded to human premolars with chemically cured adhesive(Ortho-one, Bisco, USA). Five types of commercially available metal brackets with various bracket base configurations of Photoetched base(Tomy, Japan), Non-Etched Foil Mesh base(Dentaurum, Germany), Micro-Etched Foil Mesh base(Ortho Organizers, USA), Chessboard base(Daesung, Korea), and Integral base(3M Unitek, USA) were used. Samples were divided into 3 groups, the first group was acted with shear-tensile combined loads($45^{\circ}$) of 200g for 4 weeks(mechanical fatigue stress), the second group was subjected to the 5,000 thermocycles of 15 second dwell time each in $5^{\circ}C\;and\;55^{\circ}C$ baths(thermal fatigue stress), and the third group was the control. Bond strengths were measured at the crosshead speed of 0.5mm/min. The cross-section of bracket base/adhesive interface and the fracture surface were examined with the stereoscope and the scanning electron microscope. The resin remnant on bracket base surface was assessed by ART(Adhesive Remnant Index). The obtained results were summarized as follows, 1. In static bond strength, Photoetched base bracket showed the maximum bond strength and Integral base bracket showed the minimum bond strength(p<0.05). In all brackets, shear bond strength(SBS) was in the greatest value and shear-tensile combined strength(CBS) was in the least value(p<0.05). 2. After mechanical fatigue test, Photoetched base bracket showed the maximum bond strength and Integral base bracket showed the minimum bond strength(p<0.05). In Photoetched base bracket and Micro-Etched Foil Mesh base bracket, shear bond strength(SBS), tensile bond strength(TBS) and shear-tensile combined strength(CBS) were decreased after mechanical fatigue test(p

• Journal of the KSME
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• v.19 no.2
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• pp.119-123
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• 1979

높은 탄성계수와 인장응력, 우수한 피로 및 충격저항력, 그리고 높은 진동 흡수력을 가지면서도 가벼운 보강된 복합재료는 로켓트나 미사일 부분에서 뿐만 아니라 다방면의 산업분야에 응용될 수 있다. (다음, 호에 타 응용분야를 소개할 예정임), 경량의 고강도 복합재료야인 High-Performance을 만들기 위해서는 첫째 우수한 성능을 발견할 수 있는 기계의 제조, 둘째 기계 상호간을 강력하게 결합시킬 수 있는 매트릭스 재료(Matrix Material)의 선정, 셋째, 기계와 매트릭스 재료의 결합을 강화시키기 위한 기계의 표면처리, 넷째 원하는 모양으로 만드는 성 형(Forming and Shaping) 기술의 개발이 필수적이다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.8
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• pp.789-798
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• 2013

The procedures and relevant programs developed for analyzing mechanical load data of wind turbine generator systems, which are obtained through type certification tests, are verified. The following issues according to IEC 61400-13 are covered in the developed programs: data validation, time series analysis, summary load statistics, generation of fatigue load spectra, and estimation of equivalent loads. A capture matrix for normal power production is generated to determine whether the collected data sets are sufficient to carry out fatigue analysis. Fatigue load spectra are obtained through the rainflow counting method using 50 load ranges; finally, equivalent loads are calculated using different S-N curve slopes, m, according to the relevant materials. Case studies are performed using aero-elastic simulation data of the NREL 5 MW baseline wind turbine with a monopile foundation.

• Journal of Welding and Joining
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• v.13 no.4
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• pp.7-13
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• 1995

마이크로솔더링에 의한 전자기기는, 사회기능의 중추가 되는 컴퓨터, 통신 기기, 항공기 인공위성 등의 제어계를 구성하므로, 그 접속부에 대한 높은 신뢰성의 요구는 그 무엇보다 중요하다. 전자기기에 있어서의 솔더 접속부는 집과 기판의 전기 적.기계적 접속의 역할을 하고 있으며, 따라서 개개의 접속부의 파단은 전체의 불량 으로 연결된다. 실제 전자콤포넌트와 그 시스템의 단선 등의 사고에 있어서 자주 발생 하는 사고중의 하나가 솔더접속부의 단선에 의한 것이며, 그 단선중에서도 가장 보편 적이며 또한 대단히 심각한 문제로서 주목을 받고 있는 것이 솔더접속부의 열피로파단 이다. 전자기기를 사용할 때, 스위치의 on-off에 의한 power cycle과 환경의 온도변화 에 기인하는 반복열 사이클은 솔더접속부의 피로를 일으키게 되고, 결국에는 사용중에 파단을 초래하게 된다. 이러한 온도변화의 범위는 약 -55.deg. - 150.deg.C로 예상할 수 있으며, 여기서 최고온도인 150.deg.C는 Pb-Sn 공정합금의 경우 0.9Tm.p.이상의 고온에 해당한다. 이 피로는 등온적으로 또는 열사이클중에 발생하기도 한다. 솔더접 속부의 열피로수명은 대부분의 공업재료에서 나타나는 저사이클피로거동과 유사하게 발생하며, 솔더 접속부에 인가되는 열변형/응력(thermal strain/stress)의 크기에 크게 의존하는 것으로 알려져 있다. 솔더는 서로 다른 열팽창계수를 갖는 칩과 회로 기관의 두종류의 재료를 접속하기 때문에, 상기한 바와 같은 반복열사이클에 의하여 발생하는 열변형/응력이 접속부의 피로.파단을 야기시킨다. 이러한 솔더접속부에 대한 주기적인 응력/변형의 인가는 접속부에 내.외적으로 현저한 변화를 야기시키게 되고, 열피로로 연결되며 결국에는 시스템의 전기적 단선을 초래하게 된다. 또한 열피로파단 현상는 변형/응력의 크기 뿐 만아니라 솔더합금자체의 야금학적인 물성에도 크게 의존 하며, 내적.외적인 열변화에 의한 야금학적인 특성변화도 크게 영향을 미친다. 솔더 접속부의 신뢰성에 대한 연구는, 그 중요성에 비추어 볼 때, 지금까지 수많은 연구가 행하여져 왔다. 그러나 신뢰성과 관련된 열피로파단현상에 대한 야금학적인 면에서의 연구는 비교적 적은 편이다. 따라서 본 해설에서는 전자기기의 마이크로 솔더접속부 에서 발생하는 열피로파단현상에 대한 야금학적인 면에 중점을 두어 서술하고자 한다.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.40 no.12
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• pp.1027-1035
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• 2016

In this study, a strain-controlled fatigue test of widely-used 316L stainless steel with excellent corrosion resistance and mechanical properties was conducted, in order to assess its fatigue life. Low cycle fatigue behaviors were analyzed at room temperature, as a function of the strain amplitude and strain ratio. The material was hardened during the initial few cycles, and then was softened during the long post period, until failure occurred. The fatigue life decreased with increasing strain amplitude. Masing behavior in the hysteresis loop was shown under the low strain amplitude, whereas the high strain amplitude caused non-Masing behavior and reduced the mean stress. Low cycle fatigue life prediction based on the cyclic plastic energy dissipation theory, considering Masing and non-Masing effects, showed a good correlation with the experimental results.