• 대한기계학회논문집A
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• 제28권3호
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• pp.281-288
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• 2004

The hybrid composite material (Al/GFRP laminates) are applied to the fuselage and wing in a aircraft. Therefore, Al/GFRP laminates suffer from the cyclic bending moments. This study was to evaluate the effect of fiber stacking angle on the fatigue crack propagation and delamination behavior using the relationship between crack growth rate (da/dN) and stress intensity factor range (ΔK) in Al/GFRP laminates under cyclic bending moment. The variable delamination growth behavior in case of three different type of fiber orientations, i.e., [Al/O$_2$/Al], [Al/+45$_2$/Al] and [Al/90$_2$/Al] at the interface of Al layer and glass fiber layer was measured by ultrasonic C-scan images. As results of this study, It represent that the delamination shape should turns out to have more effective characteristics on the fiber stacking angle. The extension of the delamination zone in case of [Al/+45$_2$/Al] and [Al/90$_2$/Al] were not formed along the fatigue crack profile. The shape of delamination zone depend on fiber stacking angle and the variable type with the delamination contour decreased non-linearly toward the crack tip at the Al layer.

• 대한기계학회논문집A
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• 제25권8호
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• pp.1277-1286
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• 2001

Aluminum 5052/Aramid Fiber Reinforced Plastic(Al5052/AFRP) laminates are applied to the fuselage-wing intersection. The Al5052/AFRP laminates suffer from the cyclic bending moment of variable amplitude during the service. Therefore, the influence of cyclic bending moment on the delamination and the fatigue crack propagation behavior in Al5052/AFRP laminate was investigated in this study. Al5052/AFRP laminate composite consists of three thin sheets of Al5052 and two layers of unidirectional aramid fibers. The cyclic bending moment fatigue tests were performed with five different levels of bending moment. The shape and size of the delamination zone formed along the fatigue crack between Al5052 sheet and aramid fiber-adhesive layer were measured by an ultrasonic C-scan. The relationships between da/dN and ΔK, between the cyclic bending moment and the delamination zone size, and between the fiber bridging mechanism and the delamination zone were studied. Fiber failures were not observed in the delamination zone in this study. It represents that the fiber bridging modification factor should turn out to increase and that the fatigue crack growth rate should decrease. The shape of delamination zone turns out to be semi-elliptic with the contour decreased non-linearly toward the crack tip.

• 대한기계학회논문집A
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• 제28권2호
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• pp.174-180
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• 2004

If Fiber Reinforced Metal Laminates(FRMLs) were delaminated, the decrease of stiffness and fiber bridging effect would result in the sudden aggravation of fatigue characteristics. It was reported that the delamination of FRMLs resulted from the crack of metal layers and that it depended on the crack growth. While cracks were made in FRMLs containing a saw-cuts under fatigue loading, cracks could be produced or not in FRMLs with circular holes under the same condition. When the FRMLs with the circular holes produce not the crack but the delamination, it is not possible to analyze it by the conventional fracture parameters expressed as the function of the crack. And so, this research suggests a new analytical model of the delamination to make the comparison of the delamination behavior possible whenever the cracks occur or not. Therefore, a new analytical model called Pseudo Crack Model(PCM) was suggested to compare the delaminations whether cracks were made or not. The relationship between the crack energy consumption rate( $E_{crack}$) and the delamination energy consumption rate( $E_{del}$) was discussed and it was also known that the effect of $E_{del}$ was larger than that of $E_{crack}$.

• 대한기계학회논문집A
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• 제31권3호
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• pp.344-354
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• 2007

The objective of this study is to investigate the effect of arbitrarily located defect around the circular hole in the aircraft structural material such as Al/GFRP laminates and monolithic Al alloy sheet under cyclic bending moment. The fatigue behavior of these materials may be different due to the defect location. Material flaws in the from of pre-existing defects can severely affect the fatigue crack initiation and propagation behavior. The aim of this study is to evaluate effects of relative location of defects around the circular hole in monolithic Al alloy and Al/GFRP laminates under cyclic bending moment. The fatigue behavior i.e., the stress concentration factor($K_t$), the crack initiation life($N_i$), the relationship between crack length(a) and cycles(N), the relationship between crack growth rate(da/dN) and stress intensity factor range(${\Dalta}K$) near a circular hole are considered. Especially, the defects location at ${\theta}_1=0^{\circ}\;and\;{\theta}_2=30^{\circ}$ was strongly effective in stress concentration factor($K_t$) and crack initiation life($N_i$). The test results indicated the features of different fatigue crack propagation behavior and the different growing delamination shape according to each location of defect around the circular hole in Al/GFRP laminates.

• Composites Research
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• 제16권3호
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• pp.9-17
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• 2003

타이어 벨트층내의 코드간 균열연결 및 층간균열진전을 모사하기 위해 자유단을 갖는 2층 고무/코드 적층시험편에 대한 4~11mm 변위제어 실험을 수행하였다. 자유단의 코드간 균열연결시의 폭방향 균열진전량은 45$^{\circ}$ 경사진 코드들간 길이의 절반에 도달할 때의 측정값으로 하였으며, 이는 탐침법에 의해 측정되었다 또한, 자유단에서 코드들간 균열연결을 모사하기위해 2차원의 이상화된 모델링 기법을 고안하였다. 이론수명은 테어링에너지(균열파단면의 단위면적당 방출에너지)를 이용하여 코드간 균열연결수명(임계값)과 이후 최종파손까지의 수명으로 구분하였으며, 이들을 각기 실험값과 비교하였다. 임계값까지의 수명예측은 실험과 비교하여 약 20%, 최종파손까지 약 65%의 오차가 발생하였다. 따라서, 전체 이론수명은 실험과 비교하여 약 45%의 오차를 발생하였다.

• 한국재료학회지
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• 제11권7호
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• pp.556-561
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• 2001

실리사이드반웅을 이용하여 니켈모노실리사이드의 양측계면에 단결정실리콘을 적층시켜 전도성이 우수하며 식각특성이 달라 MEMS용 기판으로 채용이 가능한 SOS (Silicon-on-Silicide) 기판을 제작하였다. 실리콘 기판 전면에 Ni를 열증착법으로$ 1000\AA$두께로 성막하고, 실리콘 기판 경면과 맞블여 후 $300~900^{\circ}C$온도범위에서 15시간동안 실리사이드 처리하여 니켈모노실리사이드가 접합매체로 되는 기판쌍들을 완성하였다. 완성된 기판쌍들은 IR (infrared) 카메라를 이용하여 비파괴적으로 접합상태를 확인하고. 주사전자현미경 (scaning electron microscope)과 투과전자현미경 (tranmission electron microscope)을 이용하여 수직단면 미세구조를 확인하였다. Ni 실리사이드의 상변화가 일어나는 온도를 제외하고는 Si NiSi ∥Si 기판쌍은 기판전면에 52%이상 완전접합이 진행되었음을 확인하였고 생성 실리사이드의 두께에 따라 나타나는 명암부에 비추어 기판쌍 중앙부에 두꺼운 니켈노실리아드가 형성되었다고 판단되었다. 완성된 Si NiSi ∥ Si 기판쌍을 SBM 수직단면에 의괘 확인한 결과 접합이 완성된 기판중심부의 접합계면은 $1000\AA$ 두께의 NiSi가 균일하게 형성되었으며 배율 30,000배의 해상도에서 계면간 분리부분없이 완전한 접합이 진행되었음을 확인하였다. 반면 기판쌍 에지 (edge)부분에는 실리사이드가 헝성되지 않은 비접합상태가 발견되었다. 수직단면루과전자현미경 결과물에 근거하여 접합된 중심부에서는 피접합되는 실리콘의 경면과 니켈이 성막된 실리콘 경면 상부계면에 10-20$\AA$의 비정질막이 발견되었으며, 산화막으로 추정되는 이 막이 접합률을 현저히 저하시키는 것을 확인하였다. 접합이 진행되지 않은 에지부는 이러한 산화막이 열처리 진행중 급격히 성장하여 피접합 실리콘층의 분리가 발생하였다. 따라서 Si NiSi ∥Si 기판쌍의 접합률을 향상시키기 위해서는 피접합 실리콘 계면과 Ni 상부층간의 비정질부를 적극적으로 제거하여야 함을 알 수 있었다.