• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 춘계학술대회논문집A
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• pp.109-114
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• 2000

A research fur development of composite body panel is in progress for lightening tare. In this study, experiments on estimation of mechanical properties of LPMC (Low pressure molding compound) including fatigue and impact characteristics were carried out. The experiments show that LPMC satisfied basic requirements of car body panel. The fatigue life of LPMC was predicted and the material degradation due to fatigue and impact were fined out.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2002년도 춘계학술발표대회 논문집
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• pp.131-134
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• 2002

Supersonic flutter analysis of cylindrical composite panels with structural damping treatments has been performed using the finite element method based on the layerwise shell theory. The natural frequencies and loss factors of cylindrical viscoelastic composites are computed considering the effects of transversely shear deformation. The panel flutter of cylindrical composite panels is analyzed considering structural damping effect. Various damping characteristics for unconstrained layer damping, constrained layer damping, and symmetrically co-cured sandwich laminates are compared with those of an original base panel in view of aeroelastic stabilities.

• Composites Research
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• 제33권3호
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• pp.140-146
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• 2020

본 논문은 차량에 사용되는 파티션 패널을 기존의 알루미늄 소재에서 Carbon Fiber Reinforced Plastics(CFRP)로 소재를 변경하여 경량화 가능성을 확인하는 것을 목적으로 한다. 복합재 제작에는 3가지 방법의 직조 방법(평직, 능직, 주자직)이 사용되었고, 복합재 시편을 제작하고 시험을 수행하여 물성을 도출하였다. 이를 통해 비틀림 조건에 대한 복합재 파티션 패널 해석 모델을 구성하고, Tsai-Hill 파손 기준에 따라 구조적 안정성과 시스템 강성을 평가하였다. 섬유 배향 각도와 적층 순서에 대한 설계변수를 통해, 진화론적 알고리즘을 수행하였고, 그 결과로 최적의 복합재 파티션 패널을 설계하였다. 또한, 강도 및 비강성에 대한 구조해석 결과를 기존의 알루미늄 파티션 패널과 복합재 파티션 패널를 비교하여, 경량화 가능성을 검증하였다.

• 해양환경안전학회지
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• 제20권2호
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• pp.234-240
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• 2014

본 연구에서는 허니컴 패널의 지배방정식을 이용하여 경계행렬식을 유도하였고, 이를 전달행렬법에 적용하여 허니컴 패널을 적용한 차음패널에 대한 해석 이론을 정립하였다. 또한, 허니컴 패널을 선박용 차음패널의 표면재로 적용하여 차음성능을 분석하였고, 철판을 표면재로 적용한 기존의 선박용 차음패널과 차음성능을 무게 당 감음량 기준으로 비교 분석하였다. 그 결과, 허니컴 패널의 차음성능이 0.35 mm 철판에 비해 STC 기준으로 2dB 높게 나와 허니컴 패널을 적용한 차음패널의 차음성능이 철판을 사용한 차음패널에 비해 무게 당 감음량을 고려할 시 우수하다는 것을 확인하였다. 또한, 허니컴 패널을 표면재로 사용한 차음패널의 면밀도가 철판을 사용한 차음패널에 비해 약 $5.2kg/m^2$ 가볍게 나타났고, 이는 약 31.7 % 무게 감소를 의미한다.

• Journal of the Korean Wood Science and Technology
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• 제19권3호
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• pp.53-61
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• 1991

Mechanical properties of composite panel made with 3mm thick Apitong(Dipterocarpus grandiflorus) veneer on each face of particleboard core of 4 different specific gravity were determined. The results obtained were as follows: 1. Measured MOR and MOE increased with an increased in specific gravity of particleboard core. 2. Test results showed that the difference in bending properties between flatwise bending and edgewise bending was present. The average MOE value of flatwise loading was higer than that of epdgewise loading. But it was shown reverse tendency in MoR and MOE. 3. The delamination between face veneer and core particle was found in flatwise bending but nell in edgewise. 4. These composite panel could be substituted for plywood and other panel materials in furniture making as considered suitable allowable stress and bending strength.

• 한국재난정보학회 논문집
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• 제11권2호
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• pp.235-243
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• 2015

콘크리트 구조물의 방호 방폭성능을 향상시키기 위한 보강방법으로 배면보강이나 콘크리트 재료의 물성보강에 따른 방법과, 구조 부재나 지지물 등을 추가로 설치하여 저항성능을 향상시키는 방법 등을 고려하였을 때 경제적인 측면과 구조적인 측면에서 효율성이 떨어진다. 본 논문에서는 패널의 각 단층 구성 재료에 고인장, 경량화, 부착성능, 내화성능 등을 향상시켜 단층 각각의 개별적인 특수 성능과 복합패널 구성물로서의 방호방폭 성능을 극대화 할 수 있는 섬유복합패널 외피와 충전제로서 나노복합소재 및 접착제에 대한 기초 연구를 수행하였다. 그 결과 섬유복합패널 외피(아라미드-폴리에스터 비 6:4, 6.5:3.5)의 최대 인장강도 2,348MPa, 최대 신율 1.8%의 값을 얻었고, 나노복합소재와 접착제를 혼합한 충전제의 최대 인장전단접착강도 4MPa을 얻었다. 또한 나노복합소재로 제작한 충전제는 보통포틀랜드시멘트의 30%의 경량화의 결과를 얻었다.

• 한국공작기계학회논문집
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• 제15권1호
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• pp.95-101
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• 2006

Minimum weight design of laminated composite panel under combined loading was studied using linear and nonlinear deformation theories and by closed-form analysis and finite difference energy methods. Various buckling load factors are obatined for laminated composite panels with rectangular type longitudinal stiffeners and various longitudinal length to radius ratios, which are made from Carbon/Epoxy USNl25 prepreg and are simply-supported on four edges under combined loading, and then for them, minimum weight design analyses are carried out by the nonlinear search optimizer, ADS. This minimum weight design analyses are constructed with various process such as the simple design process, test simulation process and sensitivity analysis. Subseguently, the buckling mode shapes are obtained by buckling and minimum weight analyses.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2004년도 추계학술발표대회 논문집
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• pp.51-55
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• 2004

A composite Iso-grid panel is manufactured and tested by compressive load. Vertical stringers and side stringers are joined with skin by secondary bonding using a liquid type adhesive. Bonding fixtures were developed to attach the stringers to skin. A-scan was done for inspection of secondary bonding region. The out of displacement field is visualized by shadow moire system. The strain and vertical displacement are measured by strain gages and L VDT (Linear Variable Differential Transformer). A local buckling is occurred at all grid sections. After that, the final failure is occurred. The strain of side stringer is much less than that of vertical stringer and skin. Due to the side stringer, the local buckling is delayed. Therefore the ratio of the first buckling to failure load is greater than that of vertical stringer stiffened panel.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2000년도 추계학술발표대회 논문집
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• pp.75-78
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• 2000

This study investigates the effect of surface treatment on the shear strength between aluminum panel and composite plate. The aluminum panel was surface-treated by DC Plasma and the composite Plate was surface-treated by ion beam. Lap shear test and T-peel test were performed to determine the shear strength and T-peel strength. Results showed that the shear strength of surface-treated case was 2.5 times higher than that of untreated case. The T-peel strength of treated case was more than 5 times higher than that of untreated case. SEM examination showed that the strength increase of surface-treated case was due to the more spread of epoxy to the panel.

• Steel and Composite Structures
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• 제17권2호
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• pp.159-172
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• 2014

A finite element model with the consideration of damage initiation and evolution has been developed for the analysis of the dynamic response of a composite sandwich panel subject to low velocity impact. Typical damage modes including fiber breakage, matrix crushing and cracking, delamination and core crushing are considered in this model. Strain-based Hashin failure criteria with stiffness degradation mechanism are used in predicting the initiation and evolution of intra-laminar damage modes by self-developed VUMAT subroutine. Zero-thickness cohesive elements are adopted along the interface regions between the facesheets and the foam core to simulate the initiation and propagation of delamination. A crushable foam core model with volumetric hardening rule is used to simulate the mechanical behavior of foam core material at the plastic state. The time history curves of contact force and the core collapse area are obtained. They all show a good correlation with the experimental data.