• Proceedings of the KAIS Fall Conference
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• 2011.05b
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• pp.602-604
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• 2011

본 연구에서는 알루미늄 폼 샌드위치 복합재료와 알루미늄 허니컴 샌드위치 복합재료의 면내 외 방향 압축실험으로 하중-변위의 관계를 분석하고 압축 특성을 비교하였다. 만능재료시험기로 1 mm/min 의 속도로 압축을 하였으며, 카메라로 실험과정을 촬영하고 로드셀에서 나오는 데이터를 컴퓨터로 저장하였다. 압축실험의 결과로 알루미늄 폼 및 허니컴 샌드위치 복합재료에서 하중이 증가함에 따라 심재에 좌굴이 발생하였다. 면내 방향 압축실험에서 알루미늄 폼 및 허니컴 샌드위치 시험편에 작용하는 압축 최대하중은 비슷하지만 비중을 고려하면 알루미늄 허니컴 샌드위치 복합재료가 더 우수한 것으로 판단되며, 면외 방향 압축실험에서도 알루미늄 허니컴 샌드위치 복합재료의 압축 최대하중이 알루미늄 폼 샌드위치 복합재료보다 높게 나왔다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.13 no.2
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• pp.478-484
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• 2012

In this study, compression analyses of sandwich composites with porous core were carried out. Finite element models of aluminum foam and honeycomb core sandwich composite material were applied solid element. In the case of aluminum foam core, valid equivalence damage model was applied. In the in-plane compression analysis, the maximum load of aluminum foam core sandwich was similar with that of aluminum honeycomb core sandwich. But in case of aluminum honeycomb core sandwich, the load support region becomes longer in comparison with aluminum foam core sandwich. In the out-plane compression analysis, compression maximum load of aluminum honeycomb core sandwich was higher than that of aluminum foam core sandwich. Through these Simulation analysis, obtains the behavior of sandwich composites.

• Aerospace Engineering and Technology
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• v.9 no.1
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• pp.9-16
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• 2010

In this study, structural analyses were carried out on the composite sandwich panel which was tested under compression loading. In the structural analyses, three types of finite element modelling were considered and linear buckling analysis and nonlinear analysis were performed for each FE-model. Through the analyses, it was found that shell elements for face parts and solid elements for core part were appropriate for the better prediction of the buckling load of the panel. If the material failure of the face is critical than overall buckling of the sandwich panel, the use of one shell element through the thickness direction was suitable in the FE-model for the better predictions of failure location and failure load.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.12 no.9
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• pp.3802-3807
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• 2011

In this study, in-plane and out-plane compression tests of aluminum foam and honeycomb sandwich composites were carried out. Through these tests, the relationships of load-displacements were analyzed and the compression characteristics were compared with each other. The specimens were compressed with the speed of 1mm/min by using the universal testing machine. Experimental procedures were taken with photograph by the camera and load cell data were stored into computer. Test results showed that buckling was occurred at the aluminum foam core and honeycomb core according to the increase of load. In the in-plane compression test, the maximum load of aluminum foam specimen was similar with that of honeycomb sandwich. The property of honeycomb was better than that of the foam in consideration of specific gravity. In the out-plane compression test, compression maximum load of aluminum honeycomb sandwich composite was higher than that of aluminum foam sandwich composite.

• Composites Research
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• v.14 no.6
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• pp.1-8
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• 2001

In this paper, the sandwich panel composites consisting of core material and face sheet were studied to evaluate the mechanical properties, noise level and fire resistance including flammability, smoke, and toxicity. Four types of sandwich panel were prepared using various kinds of panel and honeycomb materials. It was observed that Al honeycomb/Al skin composite materials had the excellent flatwise tensile strength and edgewise compressive strength compared with other types of composites. The flatwise compressive strength and flexural strength of Nomex honeycomb/Al skin composite were higher than those of other composites. PMI form/Al skin composite showed the higher core shear strength and facing bending strength. From the experimental results of flame resistance tests, it can be said that the phenol based skin composite has the excellent flame retardation properties, which are similar to those of the commercial skin composites.

• Journal of the Korean Society for Railway
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• v.12 no.1
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• pp.110-114
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• 2009

This study is for the evaluation of compressive strength restoration of sandwich composite laminates with adhesively bonded scarf patches. It was used in this study that the sandwich composite laminate with an aluminum honeycomb core and CF1263 woven fabric carbon/epoxy faces was applied to the car body structure for Korean tiling train. In this study, it was damaged by low velocity impact and repaired using scarf repair method. Then, the compressive strength restoration of assessed by compressive after impact (CAI) test. From the test, it could be known that the compressive strength was restored up to 72% by only scarf repair method and 91% applied by an extra ply over the undamaged one.

• Journal of the Korean Society for Railway
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• v.13 no.1
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• pp.31-36
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• 2010

The objective of this study is to evaluate effects of honeycomb cell size for compressive behaviors of square sandwich composite tubes with woven fabric carbon/epoxy skin and Al honeycomb core. In order to achieve these goals, four different kinds of tubes were fabricated and compressed to 200mm~250mm under quasi-static load of 10mm/min. The Al honeycombs with cell size of 6.35mm and 9.53mm were used. The relationship of mean compressive load and cell size was evaluated. In addition, the effect of peel strength and equivalent elastic modulus in ribbon direction for the mean compressive load was investigated.

• Composites Research
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• v.26 no.2
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• pp.116-122
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• 2013

In this study, impact behavior of aluminium and glass-fiber structure is studied under low impact velocity. Compression test is carried out to investigate the compressive strength of the specimens. The degree of damage is observed using microscopy and compared with the experimental analysis data. The maximum load capacity, impact strength and elastic energy of glass-fiber honeycomb sandwich panel are more than the aluminium honeycomb sandwich panel.

• Composites Research
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• v.30 no.6
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• pp.384-392
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• 2017

Sandwich panels with three different joint configurations were tested to design a novel sandwich joint structure that can effectively support both the tensile and compressive loads. The sandwich core was mainly aluminum flex honeycomb but the PMI foam core was limitedly applied to the ramp area which is transition part from sandwich to solid laminate. The face of sandwich panel was made of carbon fiber composite. For configuration 1, the composite flange and the sandwich panel were cocured. For configurations 2 and 3, an aluminum flange was fastened to the solid laminate by HI-LOK pins and adhesive. The average compressive failure loads of configurations 1, 2, and 3 were 295, 226, and 291 kN, respectively, and the average tensile failure loads were 47.3 (delamination), 83.7 (bolt failure), and 291 (fixture damage) kN, respectively. Considering the compressive failure loads only, both the configurations 1 and 3 showed good performance. However, the configuration 1 showed delamination in the corner of the composite flange under tension at early stage of loading. Therefore, it was confirmed that the structure that can effectively support tension and compressive loads at the same time is the configuration 3 which used a mechanically fastened aluminum flange so that there is no risk of delamination at the corner.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.30-30
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• 1999

샌드위치 복합재는 단일 부재의 금속재나 복합재에 비해 높은 비강성과 비강도를 얻을 수 있을 뿐 아니라 면재와 코아를 적절하게 조합하면 우수한 피로특성, 단열성, 흡음성 등을 얻을 수 있기 때문에 항공기, 철도차량, 선박, 냉동컨테이너, 건축재 등에 널리 활용되고 있다. 대부분의 샌드위치 복합재는 면재와 코아를 일차 또는 이차 선착을 통해 제작하기 때문에 운용 중 샌드위치 복합재에 가해질 수 있는 충격하중 등으로 인해 면재와 코아 사이의 층간분리, 면재의 인장파괴, 코아의 압축파괴, 코아의 진단파괴 등과 같은 손상이 생길 우려가 있다. 최근에는 샌드위치 복합재가 갖는 이러한 문제점들을 해결하기 위한 방편으로 코아의 양면에 부착된 면재들을 코아의 두께방향으로 스티칭함으로써 서로 일체형으로 결합시킨 형태인 스티칭된 샌드위치 복합재의 개발이 시도되고 있다.