• Advances in materials Research
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• 제5권1호
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• pp.11-20
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• 2016

In bonded composite repair of aircraft structures, the damage of the adhesive can thus reduce significantly the efficiency and the durability of the bonded composite repair. The adhesive damage models using critical zone have proven their effectiveness due to simplicity and ap-plicability of the damage criteria in these models. The scope of this study is to analyze the effects of the patch thickness and the adhesive thickness on the damage damage in bonded composite repair of aircraft structures by using modified damage zone theory. The obtained results show that, when the thickness of adhesive increases the damage zone increases and the adhesive loses its rigidity, inversely when the patch is reduced the adhesive damage be-comes more significant.

• 대한기계학회논문집A
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• 제33권5호
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• pp.474-481
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• 2009

Fracture models and criteria of adhesive with two parameters, namely $G_C$ and ${\sigma}_{max}$, have been developed to describe the fracture process of adhesive joints. Cohesive zone model(CZM) is a representative two parameter failure criteria approach. In CZM, ${\sigma}_{max}$ is a critical, limiting maximum value of the stress in the damage zone ahead of the crack and is assumed to have some physical significance in adhesive failure. Based on CZM and finite element analysis method, the relationship between fracture load and adhesive properties, as $G_{IC)$ and $({\sigma}_{max})_I$, was investigated in adhesively bonded joint tensile test and T-peel test. The two parameters in tensile mode loading were evaluated by using the relationship. The value of $G_{\IC}$ evaluated by proposed method showed close agreement with analytical solution for tapered double cantilever beam(TDCB) test which proposed in an ASTM standard.

• Advances in aircraft and spacecraft science
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• 제5권3호
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• pp.385-400
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• 2018

In this paper dynamic behavior (modal analysis and dynamic transient response) of a novel sandwich T-joint is numerically and experimentally investigated. An epoxy adhesive is selected for bonding purpose and making the step wise graded behavior of adhesive region. The effect of the step graded behavior of the adhesive zone on dynamic behavior of a sandwich T-joint is numerically studied. Finite element analysis (FEA) of the T-joints with carbon fiber reinforced polymer (CFRP) face-sheets is performed by ABAQUS 6.12-1 FEM code software. Modal analysis and dynamic half-sine transient response of the sandwich T-joint are presented in this paper. Two verification processes employed to verify the dynamic modeling of the manufactured sandwich panels and T-joint modeling. It has been shown that the step wise graded adhesive zone cases have changed the second natural frequency by about 5%. Also, it has been shown that the different arranges in the step wise graded adhesive zone significantly affect the maximum stresses due to transient dynamic loading by 1112% decrease in maximum peel stress and 691.9% decrease in maximum shear stress on the adhesive region.

• Composites Research
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• 제21권4호
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• pp.22-28
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• 2008

복합재료 체결부는 전체 복합재 구조물의 성능을 결정하는 중요한 부분이므로, 체결부에 대한 해석과 강도평가는 매우 중요하다. 본 논문에서는 복합재 접착 체결부의 강도를 실험적으로 평가하고 분석하였으며, 구조해석으로 평가한 체결부의 강도와 상호 비교하였다. 접착 체결부의 강도예측을 위하여 최대 변형률 이론과 파손영역 이론을 사용하였으며, 비선형 유한요소 해석을 통해 제안된 파손영역비를 기준으로 접착 체결부의 파손강도를 예측할 결과, 최대 22.2% 범위 내에서 파손강도를 예측할 수 있었다.

• 비파괴검사학회지
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• 제21권4호
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• pp.391-397
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• 2001

비균질 적층 구조물에서의 유도초음파 전파는 이론적 분산성에 기초하여 실험적으로 규명된다. 이는 입사각도와 주파수의 적절한 선택은 적층 구조물에서의 유도초음파 발생에 중요하나는 깃을 드러낸다. 이론적 분산성은 접착층 두께와 층 두께, 물성치에 크게 의존한다. 실험적으로 분산성의 변화를 관찰하므로 비균질 적층 구조물의 접착층 두께를 측정하는 것이 가능하였다.

• Structural Engineering and Mechanics
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• 제59권1호
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• pp.123-132
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• 2016

Many military and commercial aging aircrafts flying beyond their design life may experience severe crack and corrosion damage, and thus lead to catastrophic failures. In this paper, were used in a finite element model to evaluate the effect of corrosion on the adhesive damage in bonded composite repair of aircraft structures. The damage zone theory was implemented in the finite element code in order to achieve this objective. In addition, the effect of the corrosion, on the repair efficiency. Four different patch shapes were chosen to analyze the adhesive damage: rectangular, trapezoidal, circular and elliptical. The modified damage zone theory was implemented in the FE code to evaluate the adhesive damage. The obtained results show that the adhesive damage localized on the level of corrosion and in the sides of patch, and the rectangular patch offers high safety it reduces considerably the risk of the adhesive failure.

• Journal of Welding and Joining
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• 제33권5호
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• pp.14-19
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• 2015

This study has been performed to investigate the adhesive slag at GTAW weld zone after FCAW multi-pass welding. The cause of adhesive slag formation was examined using optical microscope, field emission scanning electron microscope(FE-SEM) and XRD analysis. The results obtained in this experiment are summarized as follows. Slag of GTAW weld zone surface during welding were formed by mixing the presence of slag in FCAW weld zone. While the slag cools, Cr-spinel phase were formed due to reactions in slag/metal interface. Also, a Cr moves form the weld metal to the slag to strong affinity between oxide atoms and Cr atoms. Hence, detachability of slag was exacerbated by decreasing the interfacial tensions between slag and weld metal.

• International Journal of Aeronautical and Space Sciences
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• 제18권1호
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• pp.56-62
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• 2017

Because adhesively bonded joints are used in many structural systems, it is important to predict accurate adhesive strengths. Composite aircraft with many joints are easily exposed to low temperatures and high relative humidity. This paper presents a humidity aging effect on the adhesive strength of a composite single-lap joint (SLJ). The adhesive strength of the SLJ is predicted using a finite element analysis with a cohesive zone model (CZM) technique. The humidity aging effect is evaluated based on the adhesive strength and CZM parameters. A lap joint test is carried out on the composite SLJ specimens, which are exposed for four months of 100% R.H. at $25^{\circ}C$. The predicted strengths are in good agreement with experimental data, and the actual crack propagation is satisfactorily simulated using the local CZM technique.

• 소성∙가공
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• 제18권5호
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• pp.385-391
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• 2009

An adhesively bonded power steering cylinder with a steel tube and an aluminum bracket was developed to reduce the weight of steering systems. To achieve the joint strength between the steel tube and of the aluminum bracket, the shape aluminum bracket re-designed by using the FE-analysis. Fracture behavior of the adhesive layer was considered by a cohesive zone model(CZM), which is based on the two-parameter fracture phenomenon with critical stress and fracture toughness. From the result of FE-analysis with CZM, re-designed power steering cylinder satisfied the desired joint strength for axial and torsion modes. And its joint strength was verified by the fracture test in each mode.

• 대한기계학회논문집A
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• 제38권11호
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• pp.1265-1272
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• 2014

본 논문에서는 CZM(Cohesive Zone Model)을 이용하여 돔 분리형 복합재 압력용기 접착 체결부의 점진적 파손 해석에 대한 연구를 수행하였다. 접착 요소(cohesive element)의 물성을 도출하기 위해 모드I, II 그리고 혼합모드에 대한 층간파괴인성들을 시험을 통해 도출하였다. 이때, 모든 시험편은 복합재 압력용기와 동일한 필라멘트 와인딩 제작공정을 통해 제작되었다. 이중 겹치기 이음(double-lap joint) 시험은 접착제의 전단강도와 CZM을 이용한 점진적 파손해석의 신뢰도 검증을 위해 수행하였다. 그 결과, 접착제의 전단강도는 시험으로부터 32MPa을 얻었고, 시험과 해석의 오차는 약 4.4%의 오차가 발생하여 CZM이 접착 체결부의 점진적 파손 거동을 비교적 잘 모사함을 확인하였다. 최종적으로 신뢰성이 검증된 CZM을 복합재 압력용기 접착 체결부에 적용하여 운용하중조건에서의 점진적 파손해석을 수행한 결과, 전체 200mm를 갖는 접착 체결부 길이의 약 5.8%만이 점진적 파손이 발생하는 것으로 나타나 복합재 압력용기의 구조 안전성에는 영향을 주지 않음을 확인하였다.