• Composites Research
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• v.17 no.6
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• pp.14-21
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• 2004

Failure process, mode and strength of unidirectional composite single lap bonded joints were investigated experimentally with respect to bonding methods, those are, co-curing with and without adhesive and secondary bonding. The co-cured joint specimens without adhesive had the largest failure strength. Progressive failures along the adhesive layer occurred in the secondary bonded specimens. In the co-cured specimens with adhesive film which had better material strength and adhesion performance, delamination failure occurred and the joint strengths were less than those of secondary bonded specimens. Delamination failure did not occur in the secondary bonded specimens because of earlier crack growth and progressive failure in the adhesive layer. Therefore, failure strength of composite bonded Joints were not always proportionate to material strength and adhesion performance of the adhesive due to the weakness of delamination in composite materials. The effects of surface roughness, bondline thickness and fillets were also studied on secondary bonded specimens.

• Journal of Korean Society of Steel Construction
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• v.13 no.3
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• pp.233-244
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• 2001

In this study, flexural rigidity reduction of multi-delaminated composite beams are investigated. In order to evaluate the flexural rigidity reduction. Performed theoretical analysis. In order to investigate flexural rigidity reduction about effects of delamination on composite beams, the general kinematic governing equations are derived and solved by dividing the delaminated beam and imposing the continuity conditions into each sub-beam. For condition to appear multiple delamination through the laminated composite beams, the flexural rigidity reduction are compared according to many stacking sequences and several forms for delaminations. The present study could be used to evaluate the flexural rigidity reduction of composite laminated beams on multi-delaminations.

• Composites Research
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• v.18 no.1
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• pp.1-9
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• 2005

A methodology is presented for the failure prediction of composite single-lap bonded joints considering both of composite adherend failure and bondline failure. An elastic-perfectly plastic model of adhesive and a delamination failure criterion are used in the methodology. The failure predictions have been performed using finite element method and the proposed methodology. The failure prediction results such as failure mode and strength have very good agreements with the test results of joint specimens with various bonding methods and parameters. The influence of variations in the effective strength (that is, adhesion performance) and plastic behavior of adhesive on the failure characteristics of composite bonded Joints are investigated numerically. The numerical results show that optimal joint strength is archived when adhesive and delamination failure occur in the same time.

• Journal of the KSME
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• v.32 no.1
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• pp.4-17
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• 1992

이 글에서는 복합적층판의 역학적 특성인 층간분리, 모재균열, 초기파손 후의 거동에 대한 문헌을 간단히 서술하고 그 특성을 살펴 보았다. 이상에서 살펴본 바와 같이 이방성인 층으로 구성된 복합적층 구조의 역학적 특성은 균질인 단일구조와 달리 각층의 재료상수가 달라층과 층 사이의 층간응력이 존재하여 층간분리현상이 발생하지 않도록 섬유방향뿐만 아니라 적층순서를 중요한 설계변수로 고려하여야 한다. 또한 모재균열로 인한 기계적 거동의 변화를 이해하고 초기파손 후의 손상을 고려한 해석을 수행하여 복합적층 구조의 응력해석 및 파손, 강도예측을 한다.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.32 no.4
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• pp.233-240
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• 2019

Open-hole tensile tests are usually performed to measure the tensile strengths of composites as they are an essential parameter for designing composite structures. However, correctly modeling the tensile test is extremely challenging as it involves various damages such as fiber and matrix damage, delamination, and debonding damage between the fiber and matrix. Therefore, a progressive damage model was developed in this study to estimate the in-plane failure and delamination between the fiber and matrix. The Hashin damage model and cohesive zone approach were used to model ply and delamination failures. The results of the present model were compared with previously published experimental and numerical findings. It was observed that neglecting delamination during finite element analysis led to overestimation of tensile strength.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2004.05a
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• pp.75-75
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• 2004

Carbon/epoxy는 기존의 금속재료에 비해 피로강도 및 기계적 특성이 매우 우수하다. 따라서 최근 튜브형태의 Carbon/epoxy 활용방안이 부각되고 있다. 그러나 Carbon/epoxy는 탄소재료의 특성상 고압, 충격 및 부식에 매우 취약하다. 또한, 장기간 고압피로 및 크리프에 노출될 경우, 금속재료에서는 관찰할 수 없는 층간분리(delamination)가 발생된다. 이러한 층간분리는 섬유방향과 평행하게 진전될 때 급격한 파손을 야기하므로 층간분리에 대한 메커니즘을 이해하고 그 방지책을 강구하는 것은 매우 중요하다.(중략)

• Journal of the Society of Naval Architects of Korea
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• v.40 no.6
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• pp.49-57
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• 2003

This method surely needs a hole that causes local strength and stiffness deterioration of the structure because of stress intensity. In this work, three dimensional stress analysis of pin-loaded joint for quasi-isotropic composite laminates was performed using commercial finite element software. Stress distribution was calculated near the edge of the pin-leaded hole and effects of the stacking sequence on the delamination were investigated. Also, the delamination strength of the composite laminates was predicted using the Ye-delamination failure criterion and compared with the experimental results. finally, newly modified failure criterion has been suggested owing to the consideration of effects of interlaminar normal stress on the delamination strength.

• Composites Research
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• v.18 no.1
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• pp.30-37
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• 2005

The bending strength characteristics and local deformation behaviors of honeycomb sandwich composites were investigated using three-point bending experiment and finite element simulation with a real model of honeycomb core. Two kinds of cell sizes of honeycomb core, two kinds of skin layer thicknesses, perfect bonding specimen as well as initial delamination specimen were used for analysis of stress and deformation behaviors of honeycomb sandwich beams. Various failure modes such as skin layer yielding, interfacial delamination, core shear deformation and local buckling were considered. Its simulation results were very comparable to the experimental ones. Consequently, cell size of honeycomb core and skin layer thickness had dominant effects on the bending strength and deformation behaviors of honeycomb sandwich composites. Specimens of large core cell size and thin skin layer showed that bending strength decreased by $30\~68\%$.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2000.11a
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• pp.88-91
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• 2000

흑연분말, 카본블랙, 탄소섬유분말을 첨가제로 한 저밀도 2-D 탄소/탄소 복합재의 밀도 및 기 기공도에 피치는 영향과 ILSS, 굽힘강도 및 충격에너지와 같은 기계적 물성과의 상관관계에 대하여 연구하였다. 흑연분말을 약 9 vol.% 첨가한 경우 가장 큰 ILSS값과 굽힘강도 및 충격에너지 흡수 거동을 나타내었는데, 특히 흑연의 함량이 증가함에 따라 puncture mode로의 충격 거동을 나타내 띠 많은 충격에너지를 흡수하였고, 인성이 상당히 증가하였다 카본블랙이 첨가된 경우에는, 약 3 vol.%에서 ILSS 값이 증가하였으나 큰 개선을 보이지 못하였으며, 굽힘강도는 감소하였다. 탄소섬유분말의 첨가량이 증가함에 따라 층간분리에 의해 밀도가 현저히 감소하여 ILSS 및 굽힘강도의 감소를 보였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.3
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• pp.204-211
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• 2007

Experiments were conducted to investigate the failure and strengths of carbon composite-to-aluminum single-lap bonded joints with 5 different bonding lengths. Joint specimens were fabricated to have secondary bonding of laminate and aluminum with a film type adhesive, FM73m. Tested joints have the bonding strengths between the values of aluminum-to-aluminum joints and composite-to-composite joints. In the joints with bonding length-to-width ratio smaller than 1, the strength decreases as the bonding length increases. In the joints with the ratio larger than 1, however, the strength converges to a constant value. Final failure mode of all the specimens was delamination. To use the maximum strength of the adhesive, it is important to design the joint to have strong resistance to delamination.