• 대한기계학회논문집A
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• 제34권6호
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• pp.717-723
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• 2010

많은 연구자들이 평직 탄소섬유강화플라스틱에 대해서 연구해왔지만 피로 균열 진전에 관한 연구는 아직도 미지한 상태이다. 그리고 하중과 섬유 배열 각도에 따라 균열 진전 양상이 다름을 알 수 있다. 본 연구에서는 서로 다른 두 개의 섬유 배열각도($0^{\circ}$, $45^{\circ}$)에서 평직 탄소섬유강화플라스틱의 피로 균열 진전에 대해 연구하였다. 평직 탄소섬유강화플라스틱의 피로 균열 진전 테스를 하중비 0.1에 10Hz로 수행하였다. 그 시험 결과로써, 피로 균열 진전 속도(da/dN)와 에너지해방률(${\Delta}G$)과의 그래프를 도출하였고, 섬유 배열 각도에 따른 균열 진전 양상을 $0^{\circ}$의 경우에는 Mode I를 적용하였고, $45^{\circ}$의 경우에는 Mixed Mode를 적용하였다.

• 비파괴검사학회지
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• 제21권1호
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• pp.32-38
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• 2001

재료의 손상을 평가하기 위하여 초음파법에 대한 많은 연구가 진행되었고 널리 사용되고 있으나 대부분 균열의 성장 또는 두께의 감소와 같은 문제에 집중되고 있다. 본 연구에서는 2.25Cr-1Mo 강을 이용하여 반복하중에 의해 재료내부에 발생하는 미시균열을 조기에 감지하고, 피로에 의한 파괴를 미연에 방지할 수 있도록 초음파 표면파의 감쇠와 속도변화를 이용하여 균열길이 측정의 정량적인 평가방법을 제시하였다. 중심주파수 5MHz의 탐촉자를 이용하여 파단수명비 약 60%, 균열길이 약 2mm 정도에서 표면파의 속도 및 감쇠 변화를 탐지할 수 있었다. 고주파 탐촉자를 이용함으로써 미시균열의 발생을 조기에 탐지할 수 있으며, 파단수명을 예측하는 기초자료로 활용할 수 있다.

• 대한기계학회논문집A
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• 제25권12호
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• pp.2091-2099
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• 2001

Fatigue crack growth behavior of inclined cracked Al 6061-T6 thick aluminum plate(6mm) repaired with the bonded composite patch was studied. A 0°inclined crack bonded reinforced composite patch and 15°, 30°, 45°, 60°inclined crack plates were tested. The effect of patch and inclined angle were studied and compared to each other. Also we investigated to the crack propagation direction and debonding behavior during the fatigue crack growth test. In this paper. a study was con(ducted to get an fatigue life, fatigue crack growth ratio and crack growth direction. Finally, the effectiveness of composite patch on inclined cracked plate was investigated. The results demonstrated thats there was a definite variation in fatigue life and fatigue crack growth behavior depending on the inclined crack angle.

• 한국해양공학회지
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• 제1권2호
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• pp.113-122
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• 1987

Ships and offshore strrctures are exposed to the corrosive surroundings, and the extablishment of the design criteria and the elucidation on the influence by this environment are requested to maintain the safety and to demonstrate the function of the structure. In this paper, the fatigue-crack-growth behavior on the compact tension specimens of quenched, tempered HT80 grade steels and RA36 high tensile steels having a single edge fatigue cracked notch respectively, were investigated under the repeated tensile stress with constant stroke in sea water for the welded parts by shielded metal arc welding. Main results obtained are summerized as follows; 1. The fatigue-crack-growth rates da/dN in sea water appeared to be greater behavior than those in air environment at the same stress intensisy factor range $\DeltaK$. 2. The correlation data of da/dN$\DeltaK$ of the two kinds of high tensile steels in sea water showed no great difference, however, the correlation data of da/dN$\DeltaK/\sigma_y$($\sigma_y$ stands for yield strength of the material) showed that the fatigue-crack-growth behavior of RA36 plate is affected by active path corrosion(APC) mechanism, while that of HT80 grade plate is mainly affected by hydrogen embrittlement mechanism.

• 비파괴검사학회지
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• 제16권3호
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• pp.174-183
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• 1996

본 연구에서는 인코넬600 합금을 열처리 상태 및 변형속도 등이 서로 다른 SCC 발생 조건하에서 정변형 속도 시험법으로 인장시켜 그때 발생되는 AE신호와 균열 거동을 비교하므로서 SCC 발생 및 진전을 AE로서 적절히 탐지할 수 있는가를 연구하였고, AE로 탐지 가능한 초기의 최소 균열 크기를 측정하므로서 비파괴시험법으로서의 적용성을 평가하고자 하였다 실험 결과, IGSCC에서 발생되는 AE amplitude 준위는 연성파괴 및 기계적인 변형에서 발생되는 것들보다 큰 것으로 나타났으며, 이것은 AE amplitude준위가 AE발생원을 식별할 수 있는 중요한 변수가 될 수 있음을 의미한다. IGSCC 미소균열의 성장 및 주균열의 형성으로부터 주균열의 성장으로 전환되는 시점을 AE로 적절히 감시할 수 있음을 보였으며, AE로 탐지 가능한 최소 균열 크기는 길이 $200{\sim}400{\mu}m$, 깊이 $100{\mu}m$ 이하의 균열인 것으로 나타났다. 결론적으로 AE기술은 입계 응력 부식 균열의 진전을 조기 탐지할 수 있는 유용한 방법으로 평가되며 비파괴시험법으로서의 실제 적용 가능성도 높을 것으로 판단된다.

• 한국생산제조학회지
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• 제8권1호
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• pp.119-125
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• 1999

The distribution of fatigue crack growth rate is subjected to the measuring interval and calculated method of growth rate. In this paper, in order to establish the method of determining the distribution of fatigue crack growth rate, which ignores those influences, a series of fatigue crack growth experiments and measuring intervals of crack length calculated reasonable are presented. The main conclusions obtained are summarized as follows: 1) As a result of the ΔP constant test and ΔK constant test, it is thought that an approximate measuring interval of 0.3~0.7mm is reasonable, which allows for few errors and is little subjected to the calculated method of crack growth rate. 2) After generally comparing the error estimation by using the experimental data of CCT specimen with the error rating of the CT specimens, it is possible that the fatigue test has few errors within the measuring interval, ξ(Δa/W)=0.0067~0.017, regardless of the dimension of specimen geometry.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 1996년도 추계학술대회 논문집
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• pp.928-932
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• 1996

Single overload fatigue tests with overload sizes ranging from 50% and 100% have been performed to investing ate the fatigue crack growth retardation behavior. A modified and experimental method of Willenborg's model for prediction of crack growth retardation behavior has been developed, based on evaluations of equivalent plastic zone size (EPZS) changing its size along the overload plastic zone boundary. The minimum crack growth rates of each overload size are linearly decreased with overload size increasing, but fatigue lives extended by single overload are increasing much more unlike the crack growth rates. Comparisons of crack growth behavior predicted by EPZS model and Willenborg model have shown that the EPZS model accounts for overload effects better than Willenborg model. These effects include delayed retardation, large retardation region, minimum crack growth rate, and the increase rate of crack growth rate in the region crack growth rate recovered.

• 한국해양공학회지
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• 제4권2호
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• pp.250-250
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• 1990

In this paper, fatigue tests were carried out at stress test levels of 461 MPa, 441 MPa, and 431 MPa by using smooth specimen of$2_{1/4}$ Cr-1 Mo steel with the stress ratio(R) of 0.05. The initiation, growth and coalescense process of the major cracks and sub-cracks among the fatigue cracks on the smooth specimen are investigated and measured under each stress level at a constant cycle ratio by the replica technique with optical microscope. Some of the important results are as follows: In spite of the difference of stress levels, the major crack data gather into a small band in the curve of surface crack length and crack depth against cycle ratio N/Nf. The sub-crack data, however, deviate from the band of the major crack. The growth rates, da/dN, of major and sub-crack plotted against the stress intensity factor range, ${\Delta}K$, have the tendency to be compressed on a relatively small band. But it is more effective to predict fatigue life through major cracks. The propagation behavior of surface microcracks on the smooth specimens coincides with that of the specimen having an artificial small surface defect or through crack.

• 대한기계학회논문집A
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• 제25권12호
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• pp.2070-2077
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• 2001

An experimental investigation of the effect of composite patching repair was conducted to characterize the fatigue crack growth behavior in thick A16061-T6 (6mm) panels with single bonded patch by fiber reinforced composite patch. Four patch lengths and no patch plate were examined. An analytical procedure, involving three-dimensional finite element method having three layers to model cracked aluminum plate, epoxy by adhesive and composite Patch, is calculated the stress intensity factors. From the calculated stress intensity factors, the fatigue crack growth rates are obtained. At the single patching type, different fatigue crack growth ratios through the palate thickness were investigated by using the experimental and analytical results. The results demonstrated that there was a definite variation in fatigue life depending on the size of composite patch. While crack reached the patch end, retardation of crack growth was also revealed in the bonded repair.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집A
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• pp.292-298
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• 2001

An experimental investigation of the effect of composite patching repair was conducted to characterize the fatigue crack growth behavior in thick A16061-T6 (6mm) panels with single bonded patch by fiber reinforced composite patch. Four patch lengths and no patch plate were examined. An analytical procedure, involving three-dimensional finite element method having three layers to model cracked aluminum plate, epoxy by adhesive and composite patch, is calculated the stress intensity factors. From the calculated stress intensity factors, the fatigue crack growth rates are obtained. At the single patching type, different fatigue crack growth ratios through the plate thickness were investigated by using the experimental and analytical results. The results demonstrated that there was a definite variation in fatigue life depending on the size of composite patch. While crack reached the patch end, retardation of crack growth was also revealed in the bonded repair.