• Structural Engineering and Mechanics
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• 제87권2호
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• pp.107-116
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• 2023

The three-dimensional Hashin criterion and user subroutine VUMAT were used to simulate the damage in the composite layer, and the secondary stress criterion was used to simulate the interlayer failure of the cohesive element of the bonding layer and the propagation characteristics under the layer. The results showed that when the shear stress wave (shear wave) propagates on the surface of the laminate, the stress wave attenuation along the fiber strength direction is small, and thus producing a large stress profile. When the compressive stress wave (longitudinal wave) is transmitted between the layers, it is reflected immediately instead of being transmitted immediately. This phenomenon occurs only when the energy has accumulated to a certain degree between the layers. The transmission of longitudinal waves is related to the thickness and the layer orientation. Along the symmetry across the thickness direction, the greater is the stress amplitude along the layer direction. Based on the detailed investigation on the impact on various laminated composites carried out in this paper, the propagation characteristics of stress waves, the damage and the destruction of laminates can be explained from the perspective of stress waves and a reasonable layering sequence of the composite can be designed against damage and failure from low velocity impact.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2005년도 춘계학술발표대회 논문집
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• pp.141-145
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• 2005

Since the electromagnetic properties of fiber reinforced polymeric laminate composite can be tailored effectively by adjusting its composition and regulating the stacking sequence, it is plausible material for fabricating the radar absorbing structures (RAS) of desired performance. In order to design the effective electromagnetic wave (EM) absorber with the fiber reinforced polymeric laminate composite, its electromagnetic characteristics should be available and could be regulated easily in the target frequency bands. In this study, dielectric characteristics of the E-glass/epoxy laminate composites were measured by the free space method in the X-band frequency range ($8.2\;{\sim}\;12.4\;GHz$). In order to describe the dielectric behavior of laminate composites of arbitrary stacking sequences, the equivalent circuit model and the laminating equations for estimating dielectric properties were proposed, and experimentally verified. From the comparison of the predicted and measured data, the proposed method predicted well the experimentally measured data.

• Structural Engineering and Mechanics
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• 제34권5호
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• pp.597-609
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• 2010

A problem formulation and solution methodology for design optimization of laminated thin-walled composite beams of generic section is presented. Objective functions and constraint equations are given in the form of beam stiffness. For two different problems one for open section and the other for closed section, the objective function considered is bending stiffness about x-axis. Depending upon the case, one can consider bending, torsional and axial stiffnesses. The different search and optimization algorithm, known as Evolution Strategies (ES) has been applied to find the optimal fibre orientation of composite laminates. A multi-level optimization approach is also implemented by narrowing down the size of search space for individual design variables in each successive level of optimization process. The numerical results presented demonstrate the computational advantage of the proposed method "Evolution strategies" which become pronounced to solve optimization of thin-walled composite beams of generic section.

• Composites Research
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• 제30권1호
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• pp.52-58
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• 2017

본 논문에서 제시한 복합재 날개 구조물의 최적설계 기법은 파손모드를 통합한 최적화 프레임 웍을 사용하여 복합재 날개 구조물의 안전율을 자동으로 계산한다. 개발된 최적화 프레임 웍은 복합재 구조물의 설계요소에 가장 큰 영향을 주는 파손모드 즉, 최초 파손모드, 좌굴 파손 모드 및 베어링-바이패스 파손을 확인하여 구축된 적층 데이터베이스 안에서 적층수를 찾아낸다. 이는 개발과정에서 수정 및 반복되는 설계 및 해석 시간을 단축시킬 수 있는 효과가 있다. 설계변수는 계단형태로 이루어진 적층 데이터베이스이며 응답은 변형률, 좌굴, 볼트 주변부의 응력장이며 목적함수는 날개구조의 질량이다. 그리고 최적화 프레임 윅을 구동하는 Composite Optimizer의 해석결과를 검증하기 위하여 유한요소모델의 좌굴해석 결과와 비교하여 유효성을 검증하였다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2007년도 춘계학술대회A
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• pp.28-32
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• 2007

Sufficient Conditions are proposed herein for analytically obtaining fully orthotropic (A16=A26=0, Bij=0, D16=D26=0) laminate stacking sequences together with a brief literature survey. A number of specially chosen anti-symmetric balanced stacking sequences are analytically studied, in which all coupling stiffnesses including B16 and B26 are identically zero. Those specially chosen anti-symmetric balanced stacking sequences are then arranged symmetrically with respect to the laminate mid-plane to obtain a number of symmetric stacking balanced stacking sequences of which the elastic stiffnesses are fully orthotropic.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 춘계학술대회논문집
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• pp.854-857
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• 2006

The centrifugal terce acting on a rotating disk creates the in-plane loads in radial and circumferential directions. Application of fiber reinforced composite materials to the relating disk can satisfy the demand for the increment of its rotating speed. However, the existing researches have been confined to lamina disks. This paper deals with the vibration analysis of rotating composite laminate disks. Dynamic equation is formulated in order to calculate the natural frequency and critical speed for rotating laminated disks. Galerkin's method is applied to obtain the series solution. The numerical results are given for the CFRP laminate disks with stacking sequence [0/90]s and [90/0]s.

• 한국전산구조공학회논문집
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• 제36권5호
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• pp.331-338
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• 2023

현대의 방탄 장갑은 우수한 관통 저항성을 갖추어야할 뿐만 아니라 군인과 군용차량의 기동성이 확보되어야 하기 때문에 경량화가 중요한 개발 요소가 되었다. 이종 적층 평판 구조의 방탄 장갑의 방탄 성능은 동일 중량 대비 구성 재료의 배열에 따라 달라진다. 본 논문에서는 케블라, 초고분자량 폴리에틸렌 그리고 에바 폼으로 구성된 방탄 장갑의 적층 배열에 따른 방탄 성능을 분석한다. 구성 재료의 두께가 5mm와 6.5mm인 두 가지 경우에서 6가지 적층 배열에 대하여 7.62 × 51mm NATO 탄환의 M80 탄을 856m/s의 속도로 충돌시키는 피탄 해석을 수행하였다. 방탄 성능을 평가하기 위해 이종 적층 평판을 관통한 발사체의 잔류 속도와 잔류 에너지를 측정하였다. 시뮬레이션 결과를 통해 케블라, 초고분자량 폴리에틸렌, 에바 폼의 배열 순서를 갖는 적층 구조가 동일 중량에 대해 가장 우수한 방탄 성능을 가짐을 확인하였다.

• Steel and Composite Structures
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• 제19권5호
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• pp.1221-1236
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• 2015

Since the coefficients of thermal expansion (CTE) between concrete and GFRP, steel and GFRP are quite different, GFRP laminates with different laminas stacking-sequence present different thermal behavior and currently there is no specification on mechanical properties of GFRP laminates, it is necessary to investigate the thermal influence on composite girder with stay-in-place (SIP) bridge deck at different levels and on different scales. This paper experimentally and theoretically investigated the CTE of GFRP at lamina's and laminate's level on micro-mechanics scales. The theoretical CTE values of laminas and laminates agreed well with test results, indicating that designers could obtain thermal properties of GFRP laminates with different lamina stacking-sequence through micro-mechanics methods. On the basis of the CTE tests and theoretical analysis, the thermal behaviors of composite girder with hybrid GFRP-concrete deck were studied numerically and theoretically on macro-mechanics scales. The theoretical results of concrete and steel components of composite girder agreed well with FE results, but the theoretical results of GFRP profiles were slightly larger than FE and tended to be conservative at a safety level.

• 한국융합학회논문지
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• 제10권5호
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• pp.165-171
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• 2019

오늘날 공학과 기술은 스포츠 분야에 많은 영향을 미치고 있다. 스포츠의 속성인 경쟁은 스포츠선수 뿐만이 아니라 스포츠용품에 있어서도 보다 높은 성능을 요구하게 된다. 특히 모터스포츠분야는 성능과 안전이라는 측면에서 오래전부터 스포츠와 기술의 융합이 자연스럽게 이루어지고 있다. 본 연구에서는 모터스포츠와 일반 자동차튜닝 시장을 겨냥한 카본 버킷 시트(Bucket seat)의 개발을 위하여 유한요소해석을 통해 구조강도 평가를 시행하였다. FIA($F\acute{e}d\acute{e}ration$ Internationale de l'Automobile)의 규정을 기본 설계와 강도평가에 적용하였으며, 복합소재의 특성을 고려한 유한요소 모델링과 CFRP 라미네이트(Carbon Fiber Reinforced Plastic Laminate)의 적층각도와 적층수에 따른 시트의 강도를 Tsai-Wu Failure index를 구하여 평가하였다. 해석 결과 3mm의 폼코어를 적용한 $[0^{\circ}/30^{\circ}/60^{\circ}/90^{\circ}/-30^{\circ}/-60^{\circ}]_4$인 적층이 다른 실험조합에 비하여 무게와 강도 면에서 만족할 만한 성능을 나타내고 있어 최적 적층으로 선정하였다.

• Structural Engineering and Mechanics
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• 제77권2호
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• pp.245-259
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• 2021

In this research, the influence of the laminate stacking sequence on thermal stress distribution in symmetric composite plates with a quasi-square cutout subjected to uniform heat flux is examined analytically using the complex variable technique. The analytical solution is obtained based on the thermo-elastic theory and the Lekhnitskii's method. Furthermore, by employing a suitable mapping function, the solution of symmetric laminates containing a circular cutout is extended to the quasi-square cutout. The effect of important parameters including the stacking sequence of laminates, the angular position, the bluntness, the aspect ratio of cutout, the flux angle and the composite material are examined on the thermal stress distribution. It is found out that the circular shape for cutout may not necessarily be the optimum geometry for all stacking sequences. The finite element analysis results are used to validate the analytical solution.