• 한국철도학회:학술대회논문집
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• 한국철도학회 2005년도 춘계학술대회 논문집
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• pp.251-256
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• 2005

This study was performed the heat transportation ratio of three types of the following sandwich panel by KS F 2278(2003) ; Type ${\sharp}1$ : Carbon/epoxy Aluminum Honeycomb and Balsa Core Sandwich Panel(Thickness : 37mm), Type ${\sharp}2$ : Carbon/epoxy Aluminum Honeycomb Core Sandwich Panel(Thickness : 57mm), and Type ${\sharp}3$ : Carbon/epoxy Aluminum Honeycomb Core Sandwich Panel(Thickness : 37mm). Also was performed the heat transportation of next three types of the following sandwich panel by KS F2277(2002) ; Type ${\sharp}4$ and ${\sharp}5$ : 27mm, and 35mm thick-Aluminum Honeycomb Sandwich Panels, and Type ${\sharp}6$ : 27mm thick-Foaming Aluminum Sandwich Panel. It is the larger area between the skin and core, the heat transportation ratio is the higher, and when it is composed of the hybrid composite structure, good insulation property was shown.

• 수산해양기술연구
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• 제40권4호
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• pp.351-359
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• 2004

본 연구에서는 실선에 적용된 알루미늄 하니콤 샌드위치 판 (AHSP)을 저자가 제안한 심재의 형상이 피라미드인 알루미늄 샌드위치 판의 구조적 특성 및 진동특성을 검토해 보았다. 알루미늄 피라미드 샌드위치 판(APSP)의 기초 자료로 쓰일 수 있게 심재의 각도변화, 높이변화 및 면재와 심재의 두께변화에 따른 구조적 특성을 검토한 결과 APSP가 강도 및 강성에서 우수함을 보였으며, 질량대비 큰 강성 때문에 고유진동수도 다소 크게 평가되었다.

• 한국정밀공학회지
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• 제30권11호
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• pp.1203-1210
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• 2013

Korea's first Naro-Science small class satellite was launched by Naro launcher in 2013. The structure of the satellite is mostly composed of aluminum honeycomb and frame. The honeycomb structure is homogenized with asymptotic homogenization method and its mechanical properties were used for the numerical analysis. There have been some difficulties to modeling the honeycomb sandwich panels for FEA. In the present study, the mechanical characteristics of the sandwich panel composite were numerically computed and used for the simulation. This methodology makes it easy to overcome the weakness of modeling of complicated sandwich panels. Both an experiment of vibration test and numerical analyses were conducted simultaneously. The analysis results from the current homogenization were compared with that of experiment. It shows a good agreement on the dynamic responses and certified the reliability of the present methodology when manipulate sandwich panel structure.

• Composites Research
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• 제19권1호
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• pp.9-14
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• 2006

본 연구는 KS F 2278 2003 (창호의 단열성 시험 방법)에 의하여 철도차량 및 버스의 내/외장재로 적용 가능한 카본/에폭시 스킨-알루미늄 하니콤 & 발사코어 샌드위치 판넬(두께 : 37mm), 카본/에폭시 스킨-알루미늄 하니콤 코어 샌드위치 판넬(두께 : 57mm, 단열재 포함) 및 카본/에폭시 스킨-알루미늄 하니콤 코어 샌드위치 판넬(두께 : 37mm)에 대한 열관류율 시험을 하였다. 또한 KS F2277 . 2002 (건축용 구성재의 단열성 측정방법-교정열상자법 및 보호열상자법)에 의하여 추가로 알루미늄 스킨-알류미늄 하니콤 샌드위치 판넬들 (두께 : 27mm, 35n1m)과 알루미늄 스킨-포밍 알루미늄 샌드위치 판넬 (두께27mm)에 대한 열관류율 시험을 수행하였다. 본 연구를 통해 면제와 심재사이에 열전달은 실제 단면적이 넓을수록 열관류율이 높았으며, 하이브리드형 복합재 일수록 단열성능이 우수함을 확인하였다.

• Advanced Composite Materials
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• 제17권1호
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• pp.41-56
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• 2008

In this research, optical fiber sensors and shape memory alloys (SMA) were incorporated into sandwich panels for development of a smart honeycomb sandwich structure with damage detection and shape recovery functions. First, small-diameter fiber Bragg grating (FBG) sensors were embedded in the adhesive layer between a CFRP face-sheet and an aluminum honeycomb core. From the change in the reflection spectrum of the FBG sensors, the debonding between the face-sheet and the core and the deformation of the face-sheet due to impact loading could be well detected. Then, the authors developed the SMA honeycomb core and bonded CFRP face-sheets to the core. When an impact load was applied to the panel, the cell walls of the core were buckled and the face-sheet was bent. However, after the panel was heated over the reverse transformation finish temperature of the SMA, the core buckling disappeared and the deflection of the face-sheet was relieved. Hence the bending stiffness of the panel could be recovered.

• 한국자동차공학회논문집
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• 제15권6호
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• pp.50-61
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• 2007

The structural stiffness, strength and stability on the bodyshell and floor structures of the Korean Low Floor Bus composed of laminate, sandwich panels and metal reinforced frame were evaluated. The laminate composite panel and facesheet of sandwich panel were made of WR580/NF4000 glass fabric/epoxy laminate, while aluminum honeycomb or balsa was applied to the core materials of the sandwich panel. A finite element analysis was used to verify the basic design requirements of the bodyshell and the floor structure. The use of aluminum reinforced frame and honeycomb core was beneficial for weight saving and structural performance. The symmetry of the outer and inner facesheet thickness of sandwich panels did not affect the structural integrity. The structural strength of the panels was evaluated using Von-Mises criterion for metal structures and total laminate approach criterion for composite structures. All stress component of the bodyshell and floor structures were safely located below the failure stresses. The total laminate approach is recommended to predict the failure of hybrid sandwich composite structures at the stage of the basic design.

• International Journal of Aerospace System Engineering
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• 제1권1호
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• pp.16-20
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• 2014

Recently, various kinds of study on light weight structure are performing in the world. The Al honeycomb sandwich structural type adopt for improvement of lightness and structural stability to major part structure of aircraft or spacecraft. Adhesion badness properties of adhesive and adhesion properties of fillet mainly studied about al honeycomb structure. But study for adhesive properties of sandwich construction with surface treatment of Aluminum alloy barely performed. In this study, adhesive film was used between Al and honeycomb core of honeycomb panel[1]. The study for adhesive properties of sandwich construction with surface treatment of AA 5052 skin was performed.

• Composites Research
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• 제26권2호
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• pp.85-90
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• 2013

본 논문에서는 탄소섬유강화플라스틱 면재와 알루미늄 샌드위치 심재를 가지는 복합재 샌드위치의 제조와 3절점 굽힘 실험에 대해 연구하였다. 시편은 3가지 하니컴 종류(3.18 mm, 4.76 mm, 6.35 mm의 셀 크기)와 3가지 곡률 반지름(평판, r = 1.6 m, r = 1.3 m)을 가지도록 제작하였다. 샌드위치 곡률의 기준은 W-방향을 기준으로 제작 하였다. CFRP $2{\times}2$ 트윌의 인장에서 기계적 물성치(탄성계수, 강도, 푸아송 비)를 측정하여 그 값들을 다른 CFRP 섬유 적층판의 값과 비교하였다. 실험결과 평판 샌드위치 패널의 3절점 굽힘 실험에서 심재의 전단강도는 공개된 데이터에 비해 11-30% 낮게 나왔다. 제한된 시편 크기에서 1.3미터 곡률을 가지는 패널은 평판 패널에 비해 심재의 극한 전단강도가 0.8-3.8% 감소한 것으로 나타났다.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2001년도 춘계학술발표대회 논문집
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• pp.78-82
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• 2001

Impact behaviors of Aluminum Honeycombs Sandwich Panel(AHSP) by drop weight test were investigated. Two types of specimens with 1/2" and 1/4" cell size were tested by two impactors which are weight of $5.25\textrm{kg}_{\textrm{f}}$ and $11.9\textrm{kg}_{\textrm{f}}$. Parametric studies were achieved including the impactor weight and impact sites which consist face, long-edge, short-edge, and point of the specimen. Face one of impact sites was the strongest and short-edge one of impact sites was the weakest. The damaged area of AHSP was enlarged with the increase of impactor weight that is equal to impact energy. After 3 point bending test, fracture modes of AHSP were analyzed with AE counts. Lower facesheet was fractured in the long-edge direction and then separated between facesheet and core. In the short-edge direction after core wrinkled, lower facesheet tear occurred. Impact behavior by FE analysis were increased localized damage in fast velocity because the faster velocity of the impact was, the smaller the stress of core was. Consequently, impactor weight had an effect on widely damaged area, while the impact velocity was caused on the localized damaged area.aged area.

• Advances in aircraft and spacecraft science
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• 제6권2호
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• pp.169-187
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• 2019

This work presents a practical detailed finite element (FE) approach for the three-dimensional (3D) free-vibration analysis of actual aircraft and spacecraft-type lightweight and thin honeycomb sandwich panels. It consists of calling successively in $MATLAB^{(R)}$, via a developed user-friendly GUI, a detailed 3D meshing tool, a macrocommands language translator and a commercial FE solver($ABAQUS^{(R)}$ or $ANSYS^{(R)}$). In contrary to the common practice of meshing finely the faces and core cells, the proposed meshing tool represents each wall of the actual hexagonal core cells as a single two-dimensional (2D) 4 nodes quadrangularshell element or two 3 nodes triangular ones, while the faces meshes are obtained simply using the nodes at the core-faces interfaces. Moreover, as the same 2D FE interpolation type is used for meshing the core and faces, this leads to an automatic handling of their required FE compatibility relations. This proposed approach is applied to a sample made of very thin glass fiber reinforced polymer woven composite faces and a thin aluminum alloy hexagonal honeycomb core. The unknown or incomplete geometric and materials properties are first collected through direct measurements, reverse engineering techniques and experimental-FE modal analysis-based inverse identification. Then, the free-vibrations of the actual honeycomb sandwich panel are analyzed experimentally under different boundary conditions and numerically using different mesh basic cell shapes. It is found that this approach is accurate for the first few modes used for pre-design purpose.