• 콘크리트학회논문집
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• 제14권5호
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• pp.645-652
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• 2002

본 논문은 탄소 FRP 판을 이용한 철근 콘크리트 보의 휨 보강효과와 거동에 대한 연구이다. 본 연구에서의 실험인자로는 휨보강 탄소 FRP 판의 부착길이와 탄소 FRP 쉬트의 복부정착 길이이다. 시험보는 탄소 FRP 판으로 인장면에 부착하여 휨 보강하고 FRP 판을 탄소 FRP 쉬트로 복부에 정착하였다. 일반적으로 복부정착이 없는 휨 보강된 보들의 파괴형태는 횡방향 주철 근을 따라 발생한 콘크리트 덮개 박리파괴를 나타내었다. 반면, 탄소 FRP 쉬트로 복부 정착된 휨 보강 보들은 CFRP 파단파괴 후 콘크리트 경계면 전단 박리파괴를 나타내었다. 보강된 보들의 극한하중과 극한처짐은 FRP 판의 휨 부착길이의 증가에 따라 증가하였다. 또한, 휨 보강된 보들은 FRP 쉬트의 복부정착 길이의 증가에 따라 극한하중과 극한처짐 값이 증가하였다. 특히, 복부 정착한 보들은 최대 극한하중에 도달한 후에도 상당한 극한하중 지지능력을 상당한 극한 처짐 시까지 유지하였다. 시험보의 길이에 걸친 FRP 판의 변형률 분포는 휨 모멘트도의 모양과 거의 유사하여 전단지간에서 일정한 전단응력 분포를 가정할 수 있었다. 전지간을 휨 보강한 보에 있어서는 콘크리트와 FRP 쉬트에 의한 경계면에서의 극한전단 저항강도는 복부정착 길이가 늘어남에 따라 증가하였다. 전단 저항강도 중에서 본 실험에서 사용한 복부 정착 FRP 쉬트도 일부의 전단 저항강도를 부담하였다.

• 비파괴검사학회지
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• 제27권5호
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• pp.409-416
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• 2007

최근 탄소섬유, 유리섬유 등 보강재의 사용이 증가함에 따라 내구성저하의 원인이 될 수 있는 콘크리트와 보강재 사이의 박리탐사 필요성이 대두된다. 본 연구에서는 중심주파수가 15 GHz이고, 대역폭이 10 GHz인 horn antenna 를 이용하여, 탄소섬유 및 유리섬유시트 보강 콘크리트 박리를 탐사하는 실험을 실시하였다. 실험에 사용된 시편은 길이 $600\;{\times}$ 폭 $600\;{\times}$ 두께 100 mm 의 크기를 가지며, 그 표면에 1.5 mm 두께의 탄소섬유 유리섬유를 에폭시로 부착하였다. 또한, 시편의 중앙에 길이 $50\;mm\;{\times}$ 폭 50 mm 크기의 박리를 콘크리트 표면 밑에 각각 두께 2, 4, 6 mm로 만들어 매립하였고, 콘크리트 표면 위에 2 mm 두께로 만들어, 인공박리를 제작하였다. 제작된 시편은 섬유의 종류에 따라 각각 4종류씩 총 8개의 시편이 제작되었다. 실험 결과는 그래프의 면적차이를 이용한 결과처리방법으로 처리하였고, 실험 결과 탄소섬유와 유리섬유시편에 매립된 인공 박리를 찾아내어, 향후 콘크리트/보강재 박리탐사시스템 개발에 도움이 되는 자료를 제공할 것이다.

• 대한기계학회논문집A
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• 제23권11호
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• pp.1886-1895
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• 1999

The delamination behavior of multidirectional carbon-fiber/epoxy composite laminates under 10NA intermediate and high rates of test, up to rate of about 11.4m s has been investigated using the double cantilever beam specimens. The mode I loading under rates above l.0m/s showed considerable dynamic effects on the load-time curves and thus higher values of the average crack velocity than that expected from a simple proportional relationship with the test rate. The modified beam analysis utilizing only the opening displacement and crack length exhibited an effective means for evaluating the dynamic fracture energy $G_{IC}$. Based on the assumption of constant flexural modulus, values of $G_{IC}$ at the crack initiation and arrest were decreased with an increase of the test rate up to 5.7m/s, but the maximum $G_{IC}$ was increased at 11.4m/s.

• 항공우주시스템공학회지
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• 제1권1호
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• pp.25-35
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• 2007

In this paper, the interlaminar crack problems of a fiber metal laminate (FML) under generalized plane deformation are studied using the theory of anisotropic elasticity. The crack is considered to be embedded in the matrix interlaminar region (including adhesive zone and resin rich zone) of the FML. Based on Fourier integral transformation and the stress matrix formulation, the current mixed boundary value problem is reduced to solving a system of Cauchy-type singular integral equations of the 1st kind. Within the theory of linear fracture mechanics, the stress intensity factors are defined on terms of the solutions of integral equations and numerical results are obtained for in-plane normal (mode I) crack surface loading. The effects of location and length of crack in the 3/2 and 2/1 ARALL, GLARE or CARE type FML's on the stress intensity factors are illustrated.

• 한국자동차공학회논문집
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• 제4권4호
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• pp.171-178
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• 1996

DCB(pure mode I) and CLS(mixed mode) tests were performed to investigate the effect of fracture mode on the interlaminar fracture of composite laminate. Mode I critical strain energy release rate was found to be $133J/m^2$ from the DCB test and total strain energy release rate decreased from $1, 270J/m^2$ as thickness ratio(tl/t) varied from 0.333 to 0.667 from the crease from the CLS test. Crack length had no effect on the total strain energy release rate and load was almost constant during the crack growth of the specimen which had the specific thickness ratio. Crack initiated when the stress of the strap ply reached constant stress $42kgf/mm^2$ which was found to be independent of the thickness ratio.

• Steel and Composite Structures
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• 제28권1호
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• pp.25-37
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• 2018

For the first time, the parametric instability characteristics of tow-steered variable stiffness composite laminated (VSCL) cylindrical panels is investigated using B-spline finite strip method (FSM). The panel is considered containing geometrical defects including cutout and delamination. The material properties are assumed to vary along the panel axial length of any lamina according to a linear fiber-orientation variation. A uniformly distributed inplane longitudinal loading varies harmoni-cally with time is considered. The instability load frequency regions corresponding to the assumed in-plane parametric load-ing is derived using the Bolotin's first order approximation through an energy approach. In order to demonstrate the capabili-ties of the developed formulation in predicting stability behavior of the thin-walled VSCL structures, some representative results are obtained and compared with those in the literature wherever available. It is shown that the B-spline FSM is a proper tool for extracting the stability boundaries of perforated delaminated VSCL panels.

• Steel and Composite Structures
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• 제33권5호
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• pp.653-661
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• 2019

In this paper aeroelastic behavior of 3-phase nano-composite beam-plate with double delaminations is investigated. It is tried to study the effect of carbon nano-tubes (CNTs) on critical flutter pressure of reinforced damaged nano-composite structures. In this case, the CNTs are appending to the polymer matrix uniformly. The Eshelby-Mori-Tanaka model is used to obtain the effective material properties of 3-phase nano-composite beam-plate. To investigate the aeroelastic behavior of delaminated beam-plate subjected to supersonic flow, it is assumed that the damaged segments are forced to vibrate together. The boundary conditions and auxiliary conditions at edges of delaminated segments are used to predict critical flutter pressure. The influence of CNTs and different delamination parameters such as delamination length, axial position and its position through thickness are investigated on critical flutter pressure.

• Composites Research
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• 제20권5호
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• pp.34-42
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• 2007

본 논문에서는 탄소 복합재와 알루미늄으로 구성된 이종재료 단일겹침 접착 체결부에서, 파손하중에 영향을 미치는 주요인자들의 효과를 실험적으로 연구하였다. 실험을 위해 접착압력 4가지(2, 3, 4, 6기압), 겹침길이 6가지(15, 20, 25, 30, 35, 40 mm), 모재 두께 2가지(1.58, 3.01 mm)에 대한 시편 총 66개를 제작하였다. 실험 결과 접착제 FM73에 대해 제작사에서 제시한 접착압력은 약 3기압이었지만 본 연구에서 사용한 이종재료 접착의 경우, 최소 4기압 이상의 접착압력이 필요함을 확인하였다. 겹침길이를 증가시킬 경우 파손하중이 증가하지만 접착부의 폭과 길이의 비가 1을 넘어갈 경우 접착강도 즉 단위 접착면적당의 파손하중의 증가는 크지 않았다. 모재의 두께도 접착부 파손하중 및 강도에 큰 영향을 미쳤으며 모재의 두께가 약 2배로 증가할 때 접착강도는 $12{\sim}32%$까지 증가하였다. 접착부의 파손은 대부분 복합재 모재의 층간분리 형태로 발생하였으며, 접착압력이 높아질수록, 접착길이가 길어질수록 층간분리가 발생하는 위치가 적층판 내부로 깊게 확대되는 경향이 있다.

• 대한치과보철학회지
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• 제44권6호
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• pp.683-689
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• 2006

Statement of problem. Interfacial toughness is important in the mechanical property of layered dental ceramics such as core-veneered all-ceramic dental materials. The interfaces between adjacent layers must be strongly bonded to prevent delamination, however the weak interface makes delamination by the growth of lateral cracks along the interface. Purpose. The purpose of this study was to determine the effect of the reaction layer on the interfacial fracture toughness of the core/veneer structure according to the five different divesting. Materials and methods. Thirty five heat-pressed Lithia-based ceramic core bars (IPS Empress 2), $20mm{\times}3mm{\times}2mm$ were made following the five different surface divesting conditions. G1 was no dissolution or sandblasting of the interaction layer. G2 and G3 were dissolved layer with 0.2% HF in an ultrasonic unit for 15min and 30 min. G4 and G5 were dissolved layer for 15min and 30min and then same sandblasting for 60s each. We veneered bilayered ceramic bars, $20mm{\times}2.8mm{\times}3.8mm$(2mm core and 1.8mm veneer), according to the manufacturer's instruction. After polishing the specimens through $1{\mu}m$ alumina, we induced five cracks for each of five groups within the veneer close to interface under an applied indenter load of 19.6N with a Vickers microhardness indenter. Results. The results from Vickers hardness were the percentage of delamination G1:55%, G2:50%, G3:35%, G4:0% and G5:0%. SEM examination showed that the mean thickness of the reaction layer were G1 $93.5{\pm}20.6{\mu}m$, G2 $69.9{\pm}14.3{\mu}m$, G3 $59.2{\pm}20.2{\mu}m$, G4 $0.61{\pm}1.44{\mu}m$ G5 $0{\pm}0{\mu}m$. The mean interfacial delamination crack lengths were G1 $131{\pm}54.5{\mu}m$, G2 $85.2{\pm}51.3{\mu}m$, and G3 $94.9{\pm}81.8{\mu}m$. One-way ANOVA showed that there was no statistically significant difference in interfacial crack length among G1, G2 and G3(p> 0.05). Conclusion. The investment reaction layer played important role at the interfacial toughness of body ceramic bonded to Lithia-based ceramic.

• Structural Engineering and Mechanics
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• 제37권2호
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• pp.149-162
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• 2011

The aim of this research is a comprehensive review and evaluation of beam theories resting on elastic foundations that used to model mode-I delamination in multidirectional laminated composite by DCB specimen. A compliance based approach is used to calculate critical strain energy release rate (SERR). Two well-known beam theories, i.e. Euler-Bernoulli (EB) and Timoshenko beams (TB), on Winkler and Pasternak elastic foundations (WEF and PEF) are considered. In each case, a closed-form solution is presented for compliance versus crack length, effective material properties and geometrical dimensions. Effective flexural modulus ($E_{fx}$) and out-of-plane extensional stiffness ($E_z$) are used in all models instead of transversely isotropic assumption in composite laminates. Eventually, the analytical solutions are compared with experimental results available in the literature for unidirectional ($[0^{\circ}]_6$) and antisymmetric angle-ply ($[{\pm}30^{\circ}]_5$, and $[{\pm}45^{\circ}]_5$) lay-ups. TB on WEF is a simple model that predicts more accurate results for compliance and SERR in unidirectional laminates in comparison to other models. TB on PEF, in accordance with Williams (1989) assumptions, is too stiff for unidirectional DCB specimens, whereas in angle-ply DCB specimens it gives more reliable results. That it shows the effects of transverse shear deformation and root rotation on SERR value in composite DCB specimens.