• Transactions of the Korean Society of Mechanical Engineers A
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• v.41 no.8
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• pp.751-758
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• 2017

The behavior of fatigue crack growth of nickel-based powder metallurgy superalloy that could be used in aircraft turbine disc is investigated at room temperature, and $650^{\circ}C$ considering real operating conditions. The direct current potential drop(DCPD) method was used to measure the crack length of material in real time according to ASTM E647. Tests were performed with various stress ratios (0.1 and 0.5). Experimental results show that stress ratio, and temperature all affect the behavior of fatigue crack growth. As the stress ratio and temperature increase, the fatigue crack growth rate of nickel-based powder metallurgy superalloy also increases. Results were compared and reviewed with fatigue crack growth rates of other nickel-based superalloy materials (Inconel-100) that were studied in previous papers. Fractography analysis of the fractured specimens was performed using as SEM.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.10
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• pp.35-41
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• 2005

The problem of an orthotropic composite material with a central crack inclined with respect to the principal axes of material symmetry is studied. The material is subjected to uniform biaxial loading along its outer boundaries. The normal stress ratio theory is applied to predict initial crack extension behavior in cracked composite materials. The dependence of the crack extension angle with respect to the biaxial loading and the principal axes of material symmetry is discussed. Our analysis shows significant effects of horizontal loading, crack angle and fiber angle on the crack extension.

• Transactions of the Korean Society of Mechanical Engineers
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• v.14 no.6
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• pp.1568-1575
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• 1990

Fatigue crack growth behavior was investigated in the center cracked plate of KS SB41 steel and the relation between the crack growth rate and various mechanical parameters was studied at small scale yielding, large scale yielding and full scale yielding. The crack opening ratio U was about 0.6-0.8 and had the larger value in the case of load control than that of strain control. Effective stress intensity factor range, .DELTA.K$_{eff}$ and J integral range, .DELTA.J were obtained from the notion of crack opening, and the crack growth rate was expressed with these values. The value of J integral range increased rapidly at stress ratio, R=0 in full scale yielding of load control test. COD value also increased rapidly with the increase of ligament net stress at large scale yielding of load control test.t.

• Proceedings of the KSME Conference
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• 2000.11a
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• pp.141-146
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• 2000

Crack closure and growth behavior of physically short fatigue cracks under random loading are investigated by performing narrow- and wide-band random loading tests for various stress ratios. The importance of the crack closure phenomenon is examined by predicting the growth lives of short cracks using obtained crack opening behavior. Artificially prepared two-dimensional, short through-thickness cracks are used. The crack opening load of short cracks is much lower under random loading than under constant-amplitude loading corresponding to the largest load cycle in a random load history. This result indicates that the largest load cycle in a random load history has an effect to enhance crack opening of short cracks. Most of the life prediction ratios are within the factor of 2 scatter band except several data at very short crack sizes, indicating that crack growth predictions based on the measured crack opening data are excellent. From the results obtained in this study, it can be concluded that crack closure is the primary factor governing fatigue crack growth of short cracks under random loading as well as under constant-amplitude loading.

• 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.

• Composites Research
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• v.21 no.6
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• pp.15-22
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• 2008

Reversed plane bending fatigue tests were conducted on SiC particle aluminum composite. The initiation and growth behaviors of small surface fatigue cracks were continuously monitored by the replica technique and investigated in detail. The fatigue life of MMC is shorter than that of matrix because there exists interface debonding of SiC particles and matrix on the whole face of the notch part in the casting metal matrix composite(MMC). The coalescence of micro-cracks was observed in the tests conducted at high stress levels. Due to the coalescence, a higher crack growth rate of small cracks rather than those of long cracks was recognized in da/dn-$K_{max}$ relationship.

• Proceedings of the Korea Information Processing Society Conference
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• 2024.05a
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• pp.147-148
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• 2024

WAVE 표준의 채널 구조는 하나의 제어 채널(CCH)과 여러 개의 서비스 채널(SCH)로 나뉜다. SCH 는 비안전 데이터 전송을 위해 사용되며 CCH 는 비콘 및 제어 메시지(즉, 서비스 광고 메시지)의 브로드캐스팅을 위해 사용된다. 두 간격 모두 표준에서 고정된 값(50ms)으로 설정되어 있다. 그러나 고정 길이 간격은 동적으로 변화하는 트래픽 부하에 대해 효과적으로 대응할 수 없다. 또한, 많은 차량이 동시에 제한된 채널 자원을 사용하여 데이터를 전송할 때 수많은 패킷 충돌로 인해 통신 성능이 크게 저하된다. 본 논문에서는 네트워크 성능을 향상하기 위한 적응적 자원 할당 기법을 제안한다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.15 no.5
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• pp.1635-1639
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• 1991

본 연구에서는 제1보에서의 수법을 이용하여 초기크랙길이의 분포를 고려한 재료의 불확정성 평가수법을 제시하고자 한다.

• The Korean Journal of Zoology
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• v.34 no.1
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• pp.69-80
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• 1991

점박이송사리에 관한 해부학적 자료축적의 일환으로 부속지골격의 형댈 발생 및 골화 진전양상을 조사하였다. 각 부속지의 구성골은 전피성골이 연골성골보다 먼저 골화되었다. 부속지의 기조는 가슴지느러미, 구리지느러미, 등 및 됫지느러미, 그리고 배지느러미의 순으로 골화되었다. 골화 진전에 따라 초기 자어시 유함되어 있던 수직지느러미의 기골은 방사기골과 중담기골로, 가슴지느러미의 오초-견갑골은 오훼골과 견갑골로 분리, 분화되었다. 그러나 골화진전에 따른 구성 골간의 유합은 나타나지 않았다. 5가지 부속지의 골화 완성은 가슴지느러미, 꼬리지느러미, 등지느러미, 됫지느러미 그리고 배지느러미의 순으로 이루어졌다.

• Journal of the KSME
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• v.28 no.4
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• pp.328-336
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• 1988

파괴인성은 내적 및 외적요인 등에 의해 변할 뿐만 아니라 조직의 불균질성 때문에 소성둔화 및 파괴가 균일하게 일어나지 않으므로 이에 대응한 파괴인성을 선택하여 평가함이 가장 중요하다. 또한 기계의 고속화에 따라 충격적인 하중에 의한 동적파괴의 문제가 중요하게 되고 이에 따라 동적파괴인성 평가법의 확립에도 많은 연구가 필요하다. 한편 피로균열진전거동의 실험에는 많은 시간과 인적 노력이 필요로 하며 이러한 문제점을 해결하여 균열진전 측정의 정밀화 및 효율성을 높이기 위해서는 컴퓨터의 이점을 적극적으로 응용할 필요가 있다.