• Composites Research
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• v.26 no.2
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• pp.85-90
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• 2013

This paper presents the fabrication and 3-point flexion testing of carbon fiber reinforced polymer (CFRP) composite face/aluminum honeycomb core sandwich panels. Specimen sandwich panels were fabricated with three honeycomb types (3.18 mm, 4.76 mm, and 6.35 mm cell size) and three panel radii (flat, r = 1.6 m, r = 1.3 m). The curved sandwiches were fabricated normally with the core in the W-direction. The tensile mechanical properties of the CFRP $2{\times}2$ twill fabric face laminate were evaluated (modulus, strength, Poisson's ratio). The measured values are comparable to other CFRP fabric laminates. The flat sandwich 3-point flexion test core shear strength results were 11-30% lower than the manufacturer published data; the test set-up used may be the cause. With a limited sample size, the 1.3 meter panel curvature appeared to cause a 0.8-3.8% reduction in ultimate core shear strength compared to a flat panel.

• Composites Research
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• v.27 no.3
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• pp.96-102
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• 2014

In this study, we fabricated jute fiber reinforced polylactic acid (PLA) composite in the form of sandwich panel structure which includes core foam of chopped jute fiber reinforced PLA and outer skin layer of continuous glass fiber reinforced PLA. Flexural properties of the composite were assessed for different jute fiber weight fractions. Density of the core foam ranged from 0.31 to 0.67 $g/cm^3$ and void content fraction 0.51 to 0.71. The maximum flexural strength was 92.7 MPa at 12.5 wt.% of jute fiber content, and the maximum flexural modulus was 7.58 GPa at 30.0 wt.%. Cost analysis was also conducted. The cost to enhance the flexural strength of the applied structure was estimated to be $0.010USD/m^3/MPa$ for 12.5 wt.% fiber content.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.12
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• pp.1201-1206
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• 2008

This study is focused on the investigation of the modal characteristics of the preliminary models of science technology satellite-3 (STSAT-3). Prior to the final decision of the composite structure model, several candidate structure models have been developed so as to find the most qualified structures with respect to the satellite structure systems' requirements and then utilize the information achieved to a real design. The main structure is composed of fiber reinforced composite faced honeycomb sandwich panel whose modal characteristics are found and compared to each other by means of finite element numerical analyses. Results from the current study demonstrate that a rectangular box shape having supporting inner panel shows relatively higher fundamental mode frequencies than octagonal box shape and etc., and regardless of the structure model shape tested herein, the fundamental mode turns out lateral bending mode.

• Composites Research
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• v.36 no.3
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• pp.186-192
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• 2023

Recently, in the field of railway vehicles, interest in the use of composite materials for weight reduction and transportation efficiency is increasing. Accordingly, research and commercialization development to apply composite materials to various vehicle parts are being actively conducted, and evaluation is conducted centering on post-measurement such as mechanical performance evaluation of finished products to verify quality when composite materials are applied. However, the analysis of heat and stress generated during the molding process of composite materials, which are factors that greatly affect manufacturing quality, is insufficient. Therefore, in this study, in order to verify the molding quality of composite parts for railway vehicles, the molding quality analysis was conducted for the two types of composite interior panels (laminate panel and sandwich panel) that are most actively used. To this end, temperature and strain changes were monitored during the molding process by using an FBG fiber optic sensor, which is easy to apply to the inside of the composite, and the residual strain value generated after molding was completed was measured. As a result, it was confirmed that overheating and excessive residual stress did not occur, thereby verifying the excellent molding quality of the composite interior panel for railway vehicles.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.75-78
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• 2007

In this study, low velocity impact analysis on Turbo Fan Engine composite sandwich structure was performed. Sandwich structure configuration is made of carbon/epoxy face sheets and foam cores. For validating study, the results of an experimental and of a Finite Element Method analysis were compared previously. From the Finite Element Method analysis results of sandwich panel, it was confirmed that the result of analysis was reasonable. Impactor velocity to initiate damage was estimated, and in order to investigate the damage at the predicted velocity, impact analysis using Finite Element Method was performed. According to the impact analysis results of sandwich panel, it was confirmed that the damage was generated at the estimated impact velocity.

• Fire Science and Engineering
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• v.29 no.6
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• pp.84-90
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• 2015

Multi-layered material (sandwich panel) consists of double-sided steel plate which is incombustible material or similar material and core material which is not incombustible material. In case of sandwich panel which uses combustible material as insulation, flames spread inside the steel plate at the time of fire so that it is difficult to extinguish fire from the outside and flames spread rapidly and may cause the building to collapse. The current Building Act requires the sandwich panel to secure fire-retardant performance according to the purpose and size of building. In this study, the fire spreading prevention structure applied to partial exterior walls was applied to multi-layered material and its effect was measured through full scale fire test and the possibility to secure fire safety of buildings by applying the fire spreading prevention structure to multi-layered material in future was presented.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.6
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• pp.586-594
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• 2009

This paper is the study on random, sinusoidal and shock vibration responses for the STSAT-3(science and technology satellite-3) proto-model which is the first small size all-composite satellite in Korea. The structure system of the STSAT-3 forms box type structure by joining several hybrid sandwich panels comprised of honeycomb core and carbon fiber reinforced laminated composite skins on both side. Mode shape, stress, displacement and acceleration responses are obtained on both the frequency domain and time domain by means of a commercial FEA software MSC/NASTRAN. From these analysis results, failure, safety factor and design validity are assessed. These results can be successfully applicable as reference data when a new satellite is developed as well as giving out an excellent criteria in satellite vibration treatment design.

• Proceedings of the Korea Institute of Fire Science and Engineering Conference
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• 2011.11a
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• pp.486-489
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• 2011

건축물 내 외벽에 주로 사용되는 건축용 자재 중 샌드위치 패널은 양면으로 도장한 철판 사이에 심재로 단열재를 넣어 구성된 합성복합자재이다. 샌드위치 패널의 사용범위는 창고시설 및 공업용 건축 등의 용도로 많이 사용되고 있으며, 최근에는 시공에 따른 이점으로 주택 및 상업용등으로 널리 확대되어 사용되고 있다. 본 연구에서는 화재초기의 연기밀도는 인명 대피 시 시야확보에 있어 중요한 역할을 하기에 현재 국내에서 사용되는 건축용 외장재를 용도별로 선정하여 시간에 따른 연기밀도의 값을 구하고 용도에 따른 화재 연기의 확산 정도를 예측하는데 목적을 두었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.7
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• pp.727-736
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• 2010

A satellite that has an all-composite structure, STSAT-3(science and technology satellite), was initially developed in Korea. Partially use of advanced composites in space applications such as solar panel is well developed, however the application of an all-composite satellite bus has never been achieved in Korea. This study emphasizes the application of composite technology to the design and fabrication of an all-composite spacecraft bus for small-class satellite STSAT-3. Moreover its structure design concept is totally different from the one that was used in the previous satellites developed in Korea.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.31 no.4
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• pp.506-516
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• 2007

In this paper, a study on low-velocity impact response of four different sandwich panels for the hybrid bodyshell and floor structure application of the Korean low floor bus vehicle was done. Square samples of 100mm sides were subjected low-velocity impact loading using an instrumented testing machine at six energy levels. Impact parameters like maximum force, time to maximum force, deflection at maximum force and absorbed energy were evaluated and compared for four different types of sandwich panels. The impact damage size and depth of the permanent indentation were measured by 3-Dimensional Scanner. Failure modes were studied by sectioning the specimens and observed under optical microscope. The impact test results show that sandwich panel with composite laminate facesheet could not observe damage mode of a permanent visible indentation after impact and has a good impact damage resistance in comparison with sandwich panel with metal aluminum facesheet.