• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2003년도 추계학술발표대회 논문집
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• pp.234-237
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• 2003

The absorption and the interference shielding of the electromagnetic wave problem have been a very important issue for commercial and military purposes. This study dealt with the simulation reflection loss for electromagnetic absorbing sandwich type structures in X-band(8.2Ghz~12.4GHz). Glass/epoxy composites containing conductive carbon blacks were used for the face sheets and styrofoams were used for the core. Their permittivities in X-band were measured using the transmission line technique. Simulation results of 3-1ayered sandwich type structures showed the reflection loss using the theory about transmission and reflection in a multi-layered medium.

• 항공우주시스템공학회지
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• 제4권1호
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• pp.23-26
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• 2010

In this study, it was performed damage assesment of small scale composite aircraft developing. This aircraft adopted the sandwich structure to skin of wing. This study aims to investigate the residual strength of sandwich composites with Nomex honeycomb core and carbon fiber face sheets after the open hole damage by the experimental investigation. The 4-point bending tests were used to find the bending strength, and the open hole was applied to introduce the simulated damage on the specimen. The bending strength test results after open hole was compared with the results of no damaged specimen test. The FEM analysis is assessed via an experimental 4-point bending test.

• Steel and Composite Structures
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• 제46권5호
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• pp.659-667
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• 2023

Nonlinear forced vibration behaviors of sandwich plates having graphene platelets (GPL) based face sheets have been researched in this article. Possessing low weight together with low stiffness, square honeycomb cores are mostly constructed by aluminum. Herein, the square shaped core has been fortified by two skins of GPL-based type in such a way that the skins have uniform and linearly graded GPL dispersions. The square shaped core has the effective material specification according to the relative density concept. The whole formulation has been represented based upon classical plate theory (CPT) while harmonic balance approach is applied for solving the problem and plotting the amplitude-frequency curves. The forced vibration behaviors of such plates are influenced by square-shaped core and the relative density, skin's height and GPL fortification.

• Composites Research
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• 제24권4호
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• pp.17-22
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• 2011

본 연구에서는, 복합재 샌드위치를 수중운동체용 구조물에 적용하기 위한 기초연구로서, 샌드위치 복합재 원통의 제작, 좌굴 해석 및 시험 방법, 중량저감 효과를 분석하였다. 우선 변재에 주름이 생기지 않도록 하는 2단계 샌드위치 제작 방법을 소개하고, 이를 사용하여 원통을 제작하여 수압시험을 수행하였다. 동시에 MSC Nastran의 셀요소와 고체요소를 사용한 유한 요소해석을 수행하여 시험결과와 비교하였다. 시험과 해석의 결과 비교로부터 선형 유한요소해석으로도 샌드위치 원통의 좌굴압력을 3% 내외의 오차로 정확히 예측할 수 있음을 확인하였다. 또한 필라멘트 와인딩 원통에 대한 인자연구를 통해 샌드위치를 사용할 경우 동일한 지지압력에서 필라멘트 와인딩 원통보다 최소 30% 이상 무게가 줄어드는 것을 확인하였다.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2005년도 춘계학술발표대회 논문집
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• pp.207-211
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• 2005

The Korean Tilting Train eXpress (TTX) with service speed of 180km/h have been developing using hybrid design concept combined with a sandwich composite structure for the carbody and stainless steel structure for the underframe to match the challenging demands with respect to cost efficient lightweight design for railway carriage structures. The sandwich composite structure was used to minimize the weight of the carbody, while the metal underframe was used to modify the design easily and to keep the strength of underframe for the installation of the electrical equipments. The sandwich composite structure was 23 meters long, 3 meters wide and 2.7 meters high, and cured as one body in a large autoclave equipment with the length of 30 meters and the diameter of 5 meters. The joint part between the carbody structure made of sandwich composites and the metal underframe was joined by the proposed design.

• Composites Research
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• 제13권2호
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• pp.81-90
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• 2000

자동차의 경량화를 위해서 AA5182/Polypropylene/AA5182 형태의 알루미늄 합금과 폴리프로필렌으로 구성된 샌드위치 판재가 개발되었다. 샌드위치 판재의 성형성을 평가하기 위해서 0.2mm 두께의 AA5182 판재와 1.2mm 두께의 샌드위치 판재의 성형한계도를 수정된 Marciniak-Kuczynski(M-K) 이론에 의해서 구하였다. 판재의 이방성을 표현하기 위해서 Hill의 1948년 항복곡선 표현 식을 사용하였다. 그 결과 샌드위치 판재의 성형한계도가 AA5182판재보다 더 우수하게 평가되었으며 이것은 실험값과 잘 일치하였다.

• Structural Engineering and Mechanics
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• 제43권6호
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• pp.739-759
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• 2012

The tailoring optimization technique recently developed by the author for improving structural response and energy absorption of composites is extended to sandwich shells using a previously developed zig-zag shell model with hierarchic representation of displacements. The in-plane variation of the stiffness properties of plies and the through-the thickness variation of the core properties are determined solving the Euler-Lagrange equations of an extremal problem in which the strain energy due to out-of-plane strains and stresses is minimised, while that due to their in-plane counterparts is maximised. In this way, the energy stored by unwanted out-of-plane modes involving weak properties is transferred to acceptable in-plane modes. As shown by the numerical applications, the critical interlaminar stress concentrations at the interfaces with the core are consistently reduced without any bending stiffness loss and the strength to debonding of faces from the core is improved. The structural model was recently developed by the author to accurately describe strain energy and interlaminar stresses from the constitutive equations. It a priori fulfills the displacement and stress contact conditions at the interfaces, considers a second order expansion of Lame's coefficients and a hierarchic representation that adapts to the variation of solutions. Its functional d.o.f. are the traditional mid-plane displacements and the shear rotations, so refinement implies no increase of the number of functional d.o.f. Sandwich shells are represented as multilayered shells made of layers with different thickness and material properties, the core being treated as a thick intermediate layer.

• 한국정밀공학회지
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• 제17권9호
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• pp.81-86
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• 2000

This paper was carried out to investigate the characteristics of interlaminar fracture toughness of foam core sandwich structures under opening loading mode by using the double cantilever beam (DCB) specimens in Carbon/Epoxy and foam core composites. instead of using symmetric geometry of DCB specimen non-symmetric DCB specimen was used to calculate the interlaminar fracture toughness. Three approaches for calculating the energy release rate({{{{ {G }_{IC } }}}}) were compared. Fracture toughness of foam core sandwich structures by autoclave vacuum bagging and hotpress were compared and analyzed. Experiment nonlinear beam bending FEM method were performed. Suggested bonding surface compensation and equivalent area inertia moment was used to calculate the energy release rate in nonlinear analytical results. The conclusions among experimental nonlinear analytical and FEM results was observed. The vacuum bagging method was shown to be able to substitute method in stead of autoclave without serious loss of Mode I energy release rate({{{{ {G }_{IC }}}}}) to be able to substitute method in stead of autoclave without serious loss of Mode I energy release rate({{{{ {G }_{IC }}}}}).

• 한국공작기계학회논문집
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• 제16권6호
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• pp.205-211
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• 2007

In this paper, foam-composite sandwich structures for EDM machine tool components such as column and column block designed by controlling stacking sequences and cross-sectional dimensions of the composite structures. The original column block is a box-shaped structure made of aluminum connecting a column and a Z-stage of the system. This research was focused on the design of efficient column block structure using a foam-composite sandwich structure which have good bending stiffness and damping characteristics to reduce the mass and increase damping ratio of the system. Vibration tests for getting damping ratio with respect to the stacking angle and thickness of the composites were carried out. Finite element analyses for static defection and vibration behaviour were also carried out to find out the appropriate stacking conditions; that is, stacking sequence and rib configuration. From the test and analysis results it was found that composite-foam sandwich structures for the microfactory system can be successful alternatives for high precision machining.

• 한국항공우주학회지
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• 제47권7호
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• pp.535-540
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• 2019

MDO(Multi-disciplinary Optimization)를 위한 서로 다른 모델 간의 결합은 계산 프레임 워크의 복잡성을 크게 증가시키는 동시에 CPU 시간과 메모리 사용을 증가시킨다. 이러한 어려움을 극복하기 위해 POD(Proper Orthogonal Decomposition)와 RBF(Radial Basis Function)를 사용하여 복합 샌드위치 구조가 항공기 날개 스킨 재료로 사용될 때 복합재와 샌드위치 코어의 두께를 결정하는 최적화 문제의 해를 구했다. POD와 RBF를 사용하여 날개 형상과 하중 데이터에 대한 대리 모델을 만들었으며 대리 모델에 의해 얻어진 목적 함수 및 제약 함수 값을 사용하여 최적해를 구하였다.