• 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.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2012년도 추계학술대회 논문집
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• pp.757-758
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• 2012

• 대한기계학회논문집A
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• 제33권1호
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• pp.64-71
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• 2009

In this paper, a study on low-velocity impact response of honeycomb sandwich panels was done for the changes of impact location and core fabrication angles. The test specimens were made of glass/epoxy laminate facesheet and aluminum honeycomb core. Square samples of 100mm and 100mm sides were subjected under low-velocity impact loading using instrumented testing machine at three energy levels. Impact parameters like maximum force, time to maximum force, deflection at maximum force and absorbed energy were evaluated and compared for the changes of impact location and core fabrication angle. The impact damage size were measured at facesheet surface by 3-Dimensional scanner. Also, sandwich specimens after impact test were cut to analyse the failure mode.

• 한국철도학회논문집
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• 제3권2호
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• pp.92-99
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• 2000

Composites are very useful material for light train carbody due to its high specific strength and lightweight characteristics. The composites, called 3-D board, are developed with a special stitching method. In this process, the glass fiber fabrics of skin material and foam core material are stitched together with glass fiber thread. The glass thread in Z-axis turns into FRP form. The conventional delamination problem can be solved with 3-D sandwich structure. In addition, with the lower density of foam, the weight of the panel and the operation expenses can be highly reduced. To evaluate the usefulness of the 3-D board, the double-deck light train carbody is studied. The stress analyses are carried out under various loads and boundary conditions with FEM Code, ANSYS. On comparing with the aluminum carbody, 3-D board carbody can be reduced by about 2 ton for the total weight of carbody.

• 소음진동
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• 제9권2호
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• pp.248-257
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• 1999

This paper presents the model updating of an equipment panel by using modal test and sensitivity analysis. The equipment panel is one of the major structures of communication satelite, on which broadcasting and communication equipments are mounted. For high rigidity and light weight, the panel was designed as an aluminum honeycomb sandwich panel. In addition, heat pipes were embedded in the panel for thermal control. It is essential to improve the finite element model of a spacecraft structure by using modal test in order to verify that the satellite is designed and fabricated with adequate margin under launch environment. In this paper, Young's modulus of aluminumfacesheet was selected as a modified parameter in the sensitivity analysis. The effect of boundary conditions on model improvement was also investigated.

• 한국항공우주학회지
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• 제40권9호
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• pp.771-780
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• 2012

나로호(KSLV-1)의 3차 발사에 탑재될 나로과학위성(Naro-Science Satellite)의 개발이 성공적으로 완료되었다. 나로과학위성은 100kg급의 소형 과학위성이며 전형적인 알루미늄 골격 구조에 경량 고강도의 알루미늄 허니컴 샌드위치 패널이 부착된 구조이다. 본 연구에서는 나로과학위성의 설계 요구조건에 대한 동적거동을 시험 및 전산구조 유한요소 수치해석적 방법으로 검증하였다. 연구를 통하여 발사체로부터 인가되는 각종 진동 및 외란으로 인한 파괴와 안전율(safety factor) 확보에 대한 위성 구조체 핵심 설계 및 분석기술을 확보하였다. 이러한 시험 및 수치해석 결과를 바탕으로 위성 구조설계의 신뢰성을 확보하고, 첨단 위성설계 기술의 축적을 통하여 차후 개발될 위성의 중요한 자료로 활용한다.

• 수산해양기술연구
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• 제38권2호
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• pp.101-109
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• 2002

본 논문에서 알루미늄 하니콤 샌드위치판 구조(AHSP)의 특성에 대해 해석한 결과는 다음과 같다. 1) AHSP의 H/T비가 낮아질수록 응력이 감소하며, 셀 크기(H)보다는 코어의 두께(T)가 두꺼워질수록 강도와 강성이 증가함을 알 수 있다. 2) AHSP 구조가 동일한 질량에서부터 증가하면서 EASP 구조에 비해 2.5～6.0배 정도의 높은 강도를 보이는 것을 알 수 있다. 3) AHSP의 면재의 두께변화는 AHSP 전체의 강성에 별로 영향을 미치지 못했으나, 심재의 두께가 증가할수록 단면 2차 모멘트의 값이 커지기 때문에 AHSP의 강성이 매우 커짐을 알 수 있다. 4) EASP보다 강성이 큰 AHSP의 고유진동수가 크며, 진동 모드 사이의 차도 커짐을 알 수 있다. 5) 비교연구 결과 AHSP 구조가 EASP 구조보다 적은 질량으로 훨씬 더 높은 강성을 갖는, AHSP 구조의 우수성이 입증된다. 따라서 중량경감이 가장 중요한 문제 중의 하나인 초고속선 및 대형선의 경우 AHSP 구조가 높은 굽힘강성을 갖고 다른 재료에 비해 상대적으로 적은 중량이 필요하므로 구조 재료로서의 적합성을 알 수 있다.

• 대한기계학회논문집A
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• 제26권2호
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• pp.387-398
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• 2002

The impact response and damage of CLAS panel was investigated experimentally. The facesheet material used was RO4003 woven-glass hydrocarbon/ceramic and the core material was Nomex honeycomb with a cell size of 3.2mm and a density of 96 kg/㎥. The shield plane used was RO4003 and 2024-T3 aluminum. Static indentation and impact test was conducted to characterize the type and extent of the damage observed in two CLAS panels, and the performance of antenna used in a wireless LAN system. Correlation of peak contact force, residual indentation and the delamination area shows impact damage of the panel with an aluminum shield plane is larger than that of the panel with RO4003 shield plane, although the former is more penetration resistant. The damage was observed by naked eye, ultrasonic inspection and cross sectioning. The shape and size of delamination was estimated by ultrasonic inspection, and the area of delamination linearly increases as impact energy increases. The performance of impact damaged antenna was estimated by measuring return loss and radiation pattern. It was revealed that the performance of antenna was related to the impact damage and there was a threshold that the performance of antenna fell as impact energy level changed. The threshold was between the impact energies of 1.5J and 1.75J.

• Composites Research
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• 제29권4호
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• pp.209-215
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• 2016

본 논문에서는 두께와 재료의 구성이 변하는 복잡한 형상의 복합재 샌드위치 구조의 파손 거동을 연구하였다. 구조물은 두께가 일정한 알루미늄 하니콤 코어 샌드위치 판넬이, 두께가 줄어드는 폼코어 샌드위치 천이부를 거쳐, 최종적으로는 면재와 면재가 만나 단순 적층판을 이루면서 다른 구조물에 체결되는 형상을 갖는다. 하중은 인장 및 압축하중의 형태로 가해지며 각 3개씩 총 6개 시편에 대한 시험을 수행하였다. 시험 결과 압축시험의 경우 재료불연속선을 따른 면재의 파손에 취약하며, 재료불연속선을 따른 파손을 피할 수 있는 경우 알루미늄 코어와 카본 면재의 디본딩에 의한 파손이 나타남을 알 수 있었다. 파손하중은 디본딩에 의한 파손까지 견디는 경우가 약 16% 높게 나타났다. 인장시험의 경우 파손모드는, 곡률부를 갖는 복합재 구조물에서 가장 취약한 부분인, 플랜지와 웹이 만나는 곡률부의 층간분리 파손이 주를 이루었다. 파손하중은 압축하중이 인장하중에 비하여 약7배 가량 높은 것으로 나타났다. 따라서 본 구조물은 주로 압축하중을 견디기 위한 목적의 구조물에 적용하여야 할 것으로 보인다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2008년도 추계학술대회A
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• pp.548-553
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• 2008

Low Floor buses have no steps to get on or get off the main cabin to provide the old and the handicapped with easy access. The car body for the low floor bus was designed to consider Korean physical standard, passenger capacity (standee, seated, handicapped), arrangement of vehicle components, and bus law or regulations. It was designed as an one body, without any reinforcement armature, which has light-weight sandwich constructions with glass epoxy skins, aluminum honeycomb cores and inner-frames. In this paper, torsion rigidity of the designed car body was evaluated and compared with that of a car body with reinforcement armatures in the cabin. Finite element method verified that the designed car body without reinforcement armatures could satisfy requirements of torsion rigidity.