• 대한기계학회논문집A
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• 제34권2호
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• pp.203-209
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• 2010

본 연구는 철도차량에 적용되는 직물 유리섬유/에폭시 적층 복합재의 피로특성 및 피로수명에 대해 평가하였다. 이때, 피로시험은 0.1의 응력비(R)와 5Hz의 주파수에서 인장-인장 하중 조건이 고려되었으며, 시험편은 카본/에폭시 플라이가 보강된 시험편과 보강되지 않은 시험편 두 가지 타입을 고려하였다. 또한, 직물 유리섬유/에폭시 적층 복합재의 피로수명을 평가하기 위해 철도차량 차체와 언더프레임에 주로 사용되는 알루미늄 6005와 비교하였다. 본 연구를 통하여 3장의 카본/에폭시 플라이가 보강된 직물 유리섬유/에폭시 적층 복합재 시험편이 보강되지 않은 기본 시험편보다 피로강도 및 피로수명이 크게 향상됨을 확인하였다.

• 한국항공우주학회지
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• 제30권1호
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• pp.49-55
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• 2002

광섬유 브래그 격자/외부 패브리-페로 간섭 (FBG/EFPI) 센서를 이용하여 비대칭 적층판의 성형시 및 성형후 변형률과 온도를 동시에 모니터링 하였따. 본 논문에서는 광섬유 센서의 출력에 대한 변형률 및 온도의 관계를 수치적으로 유도하였으며 이를 통해 센서의 특성 행렬을 구하였다. 따라서 각각의 센서에 대해 특성 행렬을 구하기 위해 센서의 보정실험을 수행할 필요가 없다. 광원으로는 파장 이동 광섬유 레이저를 사용하였다. 두 개의 FBG/EFPI 센서를 Gr/Ep 비대칭 직교적층 복합적층판에 방향과 위치를 달리하여 삽입하고 오토클레이브 내에서 성형하는 동안 두 지점에서의 성형변형률과 온도를 실시간으로 모니터링 하였다. 또한 열챔버 내에서 제작된 적층판의 열변형률과 온도를 측정하였다. 이러한 실험들을 통해 복합재료의 효울적인 스마트 프로세싱에 대한 기초를 마련할 수 있으며 비대칭 직교적층 복합적층판의 열적 거동에 대해 알 수 있을 것이다.

• 한국항공우주학회지
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• 제30권2호
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• pp.59-66
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• 2002

광섬유 브래그 격자/외부 패브리-페로 간섭 (FBG/EFPI) 복합 센서를 이용하여 여러 가지 복합재료 적층판의 성형과정 동안 발생하는 변형률과 온도를 동시에 모니터링하였다. 일방향 적층판, 대칭 직교 적층판, 그리고 평직 적층판에 대하여 각각 두개씩의 FBG/EFPI 센서를 방향과 위치를 달리하여 삽입하고 오토클레이브 내에서의 성형 동안 복합재료 적층판 내부의 두 지점에서의 성형변형률과 온도를 실시간으로 측정하였다. 이러한 실험들을 통해 FBG/EFPI 센서는 보합재료 구조물 성형시의 스마트 모니터링에 효율적임을 알 수 있었다.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2001년도 춘계학술발표대회 논문집
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• pp.69-73
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• 2001

Damage induced by low-velocity impact on the curved composite laminates was experimentally evaluated for CFRP cylindrical shells with the radius of curvatures of 50, 150, 300, and 500 mm. The result was then compared with that of flat laminates. The radius of curvatures and the effective shell stiffness appeared to considerably affect the dynamic impact response of curved shells. Under the same impact energy level, the maximum contact force increased with the decreasing radius of curvatures, with reaching 1.5 times that for plates at the radius of curvature of 50 mm. Since the maximum contact force is directly related to the impact damage, curved laminates can be more susceptible to delamination and less resistant to the low-velocity impact damage. The distribution of delamination along the thickness direction of curved laminates are also different from that of flat plates. Delamination was distributed rather even]y at each interface along the thickness direction of curved laminates. This implies that the effect of curvatures has to be considered for the design of a curved composite laminate.

• Steel and Composite Structures
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• 제3권3호
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• pp.213-229
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• 2003

A high precision shear deformable triangular element has been proposed for free vibration analysis of composite trapezoidal plates. The element has twelve nodes at the three sides and four nodes inside the element. Initially the element has fifty-five degrees of freedom, which has been reduced to forty-eight by eliminating the degrees of freedom of the internal nodes through static condensation. Plates having different side ratios (b/a), boundary conditions, thickness ratios (h/a=0.01, 0.1 and 0.2), number of layers and fibre angle orientations have been analyzed by the proposed shear locking free element. Trapezoidal laminate with concentrated mass at the centre has also been analyzed. An efficient mass lumping scheme has been recommended, where the effect of rotary inertia has been included. For validation of the present element and formulation few results of isotropic trapezoidal plate and square composite laminate have been compared with those obtained from open literatures. The numerical results for composite trapezoidal laminate have been given as new results.

• International Journal of Aeronautical and Space Sciences
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• 제16권3호
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• pp.360-369
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• 2015

A methodology for determining the design allowables of composite laminates by using lamina level test data and finite element analysis (FEA) is proposed and verified in this paper. An existing method that yields the laminate design allowables by using the complete test results for laminates was improved to reduce the expensive and time-consuming tests. Input property samples for FEA were generated after considering the statistical distribution characteristics of lamina level test data., and design allowables were derived from several FEA analyses of laminates. To apply and verify the proposed method, Hexcel 8552 IM7 test data were used. For both un-notched and open-hole laminate configurations, it was found that the design allowables obtained from the analysis correctly predicted the laminate test data within the confidence interval. The potential of the present simulation to substitute the laminate tests was demonstrated well.

• 한국안전학회지
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• 제17권1호
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• pp.25-32
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• 2002

The tensile tests for [0/90]s, [90/0]s, and $[0/{\pm}45/90]s$ laminate composite were accomplished with acoustic sensor and failure processes were recorded by a video camera in real time. Also SEM examinations for fracture and side surface were carried out. The purpose of study is estimation of the failure mechanism and the mechanical properties effected by lay-up orientation for CFRP laminate composite with the hole notch. From the results, mechanical properties were obtained and they are similar between two kinds of cross-ply orientation in CFRP laminate composites, but not on $[0/{\pm}45/90]s$. And accordings to increasing the load, accumulate AE count was increased, regardless of lay-up orientation. Futhermore, failure mechanism was described by a video monitoring and SEM.

• 대한기계학회논문집A
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• 제22권3호
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• pp.579-587
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• 1998

In this study, fatigue behavior of the optical fiber sensor embedded in composite laminate was investigated. Static tensile and fatigue tests were performed for three types of laminated composite specimens with embedded optical fiber sensor in the neutral plane ; [0/sub 6//OF/0/sub 6/]/sub T/, [0/sub 2//90/sub 4//OF/90/sub 4//0/sub 2/]/sub T/ and [0/sub 3//90/sub 3//OF/90/sub 3//0/sub 3/]/sub T/. The fracture of the embedded optical fiber sensor was detected by the intensity drop off of laser signal transmitted through the optical fiber sensors embedded within laminated composite specimen. The maximum fatigue stress applied to laminated specimen was compared with the average tensile stress at which the fracture of the embedded optical fiber within the laminate occurred under static tensile loading. From the experiments, firstly it is observed that the decrease in the life of optical fiber sensors embedded within unidirectional-ply laminate by the fatigue loading is relatively small compared to that of cross-ply laminate. Secondly, the optical fiber embedded in unidirectional-ply laminate is fractured by the fatigue damage due to the growth of internal defects of optical fiber, however the optical fiber embedded in cross-ply laminate is fractured by the growth of transverse matrix crack.

• The Journal of Advanced Prosthodontics
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• 제6권4호
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• pp.278-284
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• 2014

PURPOSE. There is insufficient data regarding the durability of porcelain laminate veneers bonded to existing composite fillings. The aim of the present study was to evaluate the fracture resistance and microleakage of porcelain laminate veneers bonded to teeth with existing composite fillings. MATERIALS AND METHODS. Thirty maxillary central incisors were divided into three groups (for each group, n=10): intact teeth (NP), teeth with class III composite fillings (C3) and teeth with class IV cavities (C4). Porcelain laminate veneers were made using IPS-Empress ceramic and bonded with Panavia F2 resin cement. The microleakage of all of the specimens was tested before and after cyclic loading ($1{\times}10^6$ cycles, 1.2 Hz). The fracture resistance values (N) were measured using a universal testing machine, and the mode of failure was also examined. The statistical analyses were performed using one-way ANOVA and Tukey post hoc tests (${\alpha}=.05$). RESULTS. There was a significant difference in the mean microleakage of group C4 compared with group NT (P=.013). There was no significant difference in the fracture loads among the groups. CONCLUSION. The microleakage and failure loads of porcelain laminate veneers bonded to intact teeth and teeth with standard class III composite fillings were not significantly different.

• 복합신소재구조학회 논문집
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• 제3권2호
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• pp.47-54
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• 2012

In this study, composite laminate cantilever type cylindrical shells with edge-stiffeners are analyzed. A versatile 4-node flat shell element which is useful for the analysis of shell structures is used. An improved flat shell element is established by the combined use of the addition of non-conforming displacement modes and the substitute shear strain fields. Two models by load conditions are considered. Load type A and B are loaded by point load at the free edge and line load respectively. A various parameter examples are presented to obtain proper stiffened length and stiffened thickness of edge-stiffeners. It is shown that the thickness of shell can be reduced minimum 30% by appropriate edge-stiffeners.