• Composites Research
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• 제29권6호
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• pp.379-387
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• 2016

본 논문에서 전자기장과 열 하중을 받는 복합재료 평판에 대하여 압전재료를 이용한 압전제어를 수행하였다. 구조물에 가해지는 전자기장과 열 하중, 그리고 구성방정식에서 고려되는 압전효과가 모두 포함된 지배방정식을 FSDT 판 이론에 기초하여 Hamilton 원리에 의하여 유도하였다. 평판의 경계면에서 발생하는 제어력과 제어 모멘트는 비례제어 및 속도제어 로직에 의하여 적용되었다. 전자기장과 열 하중, 그리고 압전효과가 복합재료 평판의 동특성에 미치는 영향에 대하여 고찰하고, 압전효과 및 복합재료의 섬유각 변화를 통하여 복합재 구조물의 동특성을 효과적으로 제어 가능함을 확인하였다.

• Steel and Composite Structures
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• 제48권3호
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• pp.275-291
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• 2023

This paper has focused on presenting vibration analysis of trapezoidal sandwich plates with 3D-graphene foam reinforced polymer matrix composites (GrF-PMC) core and FG wavy CNT-reinforced face sheets. The porous graphene foam possessing 3D scaffold structures has been introduced into polymers for enhancing the overall stiffness of the composite structure. Also, 3D graphene foams can distribute uniformly or non-uniformly in the plate thickness direction. The effective Young's modulus, mass density and Poisson's ratio are predicted by the rule of mixture. In this study, the classical theory concerning the mechanical efficiency of a matrix embedding finite length fibers has been modified by introducing the tube-to-tube random contact, which explicitly accounts for the progressive reduction of the tubes' effective aspect ratio as the filler content increases. The First-order shear deformation theory of plate is utilized to establish governing partial differential equations and boundary conditions for trapezoidal plate. The governing equations together with related boundary conditions are discretized using a mapping-generalized differential quadrature (GDQ) method in spatial domain. Then natural frequencies of the trapezoidal sandwich plates are obtained using GDQ method. Validity of the current study is evaluated by comparing its numerical results with those available in the literature. It is explicated that 3D-GrF skeleton type and weight fraction, carbon nanotubes (CNTs) waviness and CNT aspect ratio can significantly affect the vibrational behavior of the sandwich structure. The plate's normalized natural frequency decreased and the straight carbon nanotube (w=0) reached the highest frequency by increasing the values of the waviness index (w).

• Smart Structures and Systems
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• 제20권5호
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• pp.595-605
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• 2017

The present article reported the thermal buckling strength of the sandwich shell panel structure and subsequent improvement of the same by embedding shape memory alloy (SMA) fibre via a general higher-order mathematical model in conjunction with finite element method. The geometrical distortion of the panel structure due to the temperature is included using Green-Lagrange strain-displacement relations. In addition, the material nonlinearity of SMA fibre due to the elevated thermal environment also incorporated in the current analysis through the marching technique. The final form of the equilibrium equation is obtained by minimising the total potential energy functional and solved computationally with the help of an original MATLAB code. The convergence and the accuracy of the developed model are demonstrated by solving similar kind of published numerical examples including the necessary input parameter. After the necessary establishment of the newly developed numerical solution, the model is extended further to examine the effect of the different structural parameters (side-to-thickness ratios, curvature ratios, core-to-face thickness ratios, volume fractions of SMA fibre and end conditions) on the buckling strength of the SMA embedded sandwich composite shell panel including the different geometrical configurations.

• 대한기계학회논문집A
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• 제31권1호
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• pp.121-128
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• 2007

Enhanced lower order shear deformation theory is developed in this study. Generally, lower order theories are not adequate to predict accurate deformation and stress distribution through the thickness of laminated plate. For the accurate prediction of detailed stress and deformation distributions through the thickness, higher order zigzag theories have been proposed. However, in most cases, simplified zigzag higher order theory requires $C_1$, shape functions in finite element implementation. In commercial FE softwares, $C_1$, shape functions are not so common in plate and shell analysis. Thus zigzag theories are useful for the highly accurate prediction of thick composite behaviors but they are not practical in the sense that they cannot be used conveniently in the commercial package. In practice, iso-parametric $C_0$ plate model is the standard model for the analysis and design of composite laminated plates and shells. Thus in the present study, an enhanced lower order shear deformation theory is developed. The proposed theory requires only $C_0$ shape function in FE implementation. The least-squared energy error between the lower order theory and higher order theory is minimized. An enhanced lower order shear deformation theory(ELSDT) in this paper is proposed for smart structure under complex loadings. The ELSDT is constructed by the strain energy transformation and fully coupled mechanical, electric loading cases are studied. In order to obtain accurate prediction, zigzag in-plane displacement and transverse normal deformation are considered in the deformation Held. In the electric behavior, open-circuit condition as well as closed-circuit condition is considered. Through the numerous examples, the accuracy and robustness of present theory are demonstrated.

• 마이크로전자및패키징학회지
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• 제13권2호
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• pp.1-7
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• 2006

본 논문에서는 솔더 레지스트(solder resist)의 두께와 코어의 물성에 따른 인쇄회로기판의 철의 크기와 형상에 대하여 연구하였다. 인쇄회로기판의 굽힘 변형은 적층되는 재료의 열팽창계수의 차이에 의해 발생한다. 따라서 굽힘 변형의 감소를 위해서는 열팽창계수의 차이가 작은 적층 재료를 사용하는 것이 필요하며, 구조 형상에서도 상면과 하면의 불균일성을 완화시킬 필요가 있다. 또한, 적층 재료에서 코어의 강성을 높여 점의 발생을 억제할 수 있다. 코어를 이루는 복합재료는 적층 순서와 섬유 각에 따른 물성 특성의 방향성에 따라 굽힘과 비틀림이 연성되는 현상을 보이며, 이와 같은 성질을 이용하면 휨을 제어할 수 있다. 본 연구에서는 2층으로 구성된 chip scale package (CSP) 기판의 휨에 대한 연구로, 실험 및 유한 요소해석 툴을 이용하여 개선 결과를 도출하였다.

• 항공우주시스템공학회지
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• 제14권3호
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• pp.69-77
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• 2020

본 논문에서는 35 kg급 재난치안용 멀티콥터 무인기의 기체구조 개발에 대해 기술한다. 경량화를 위해 구조재료는 T-700급 탄소 복합재료를 사용하였으며, 동체는 세미 모노코크 구조로, 제어 및 통신장비가 장착되는 판재는 샌드위치 구조로 설계하였다. 설계된 부품과 동일한 적층판과 파이프를 제작하고 시편시험을 수행하여 강도와 강성을 확인하였다. 정적강도 및 진동 해석을 수행하여 복합재료 적층순서를 결정하였고, 착륙속도 및 지상이격 요구조건과 비선형 해석을 통해 착륙장치 스트러트의 적층순서를 결정하였다. 정적강도시험을 통해 구조 건전성을 평가하고 착륙장치의 거동을 확인하였다.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 1999년도 추계학술발표대회 논문집
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• pp.57-62
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• 1999

In order to fabricate a involute construction structure, the pattern design for prepreg stacking was developed. For obtaining the demanded strength in the circumferencial and axial direction of the involute construction and tile proper processablity of prepreg stacking, the shaped pattern method was established which has a calculated length suitable for stacking. We can obtain the involute construction with clean interface between laminated plies and suitable dimension by using pattern design method developed in this study. Test specimens with varied arc angle were designed to test the structural properties of involute construction. Tensile and compressive strength decreased with the increase of arc angle. Tensile modulus and compressive failure strain were calculated under the conditon of transformation of material properties successfully.

• 항공우주시스템공학회지
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• 제3권1호
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• pp.12-16
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• 2009

The laminated sequence and thickness of a composite structure is an important design parameter which affect the strength and impact damage. In this study, it was investigated the residual strength of carbon fiber laminate after impact damage by the experimental investigation. The tensile strength test and compressive strength test were used to find the mechanical properties, previously. Impact test was performed using low-velocity drop-weight test equipment. The impact damages were finally assessed by the compressive strength test. The investigation results revealed the residual strength of the damaged specimens due to the impact damage.

• Composites Research
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• 제13권2호
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• pp.30-39
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• 2000

고급복합재료(advanced composite material)는 여러 가지 훌륭한 장점에도 불구하고 건설기술자에게는 그 이론이 너무 복잡하여 건설구조에 대한 응용이 지연되고 있다. [$\alpha$/$\beta$/$\beta$/$\gamma$/$\alpha$/$\alpha$/$\beta$]r, $\alpha$=-$\beta$, $\gamma$=$0^{\circ}$또는 $90^{\circ}$와 같은 몇 가지 배향각을 갖은 적층판은, r이 증가함에 따라, $B_{i,j}$ 강성이 0으로 접근한다(1995). 또한 건설구조물은 그 치수가 크고 r이 증가해도 지간 대 두께비가 충분히 커서, 횡방향 변형율($varepsilon_{xz}$, $varepsilon_{yz}$)의 영향이 무시될 수 있다. 이 경우 판의 지배방정식은 간단한 특별직교 이방성 판의 지배방정식으로 변화된다. 김덕현은 토목구조물에 흔히 적용될 수 있는 이러한 배향각을 가진 적층판의 지배방정식을 취급이 간단한 특별직교 이방성 판의 경우로 변경시킨 다음 해석을 더 간단히 진행할 수 있도록 기술자들이 유사 등방성 상수(quasi-isotropic constant)를 사용하여 낯익은 등방성판의 방정식으로 답을 구하고 그가 개발한 "수정계수(correction factor)"를 사용하여 "정확한"해를 구하는 방법을 발표한 바 있다(1991).이 논문에는 [$\alpha$/$\beta$/$\beta$/$\gamma$/$\alpha$/$\alpha$/$\beta$]r 배향각을 갖는 적층판을, 일반기술자들이 이해하기 쉬운 본 논문의 방법으로 해석하는 방법을 제시하고 기술자들의 참고자료로 사용될 수 있는 여러 가지 경우에 대한 고유진동수의 계산결과가 제공되고 있다. 고유진동수의 계산결과가 제공되고 있다.

• 한국안전학회지
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• 제29권6호
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• pp.9-14
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• 2014

Recently many efforts and researches have been done to cope with industrial facilities that require a low energy machines due to the gradual depletion of the natural resources. The fiber-reinforced composite materials in general have good properties and have the proper mechanical properties according to the change of the ply sequences and fiber distribution types. However, in the fiber-reinforced composite material, there are several problems, including fiber breaking, peeling, layer lamination, fiber cracking that can not be seen from the metallic material. Particularly, the fracture and delamination are likely to be affected by the thickness of the stacking laminates when the bi-material laminated structure is subjected to a load of the mixed mode. In this study, we investigated the effect of the thickness ratio of the difference in the CFRP/GFRP bi-material laminate composites by measuring the cracking behavior and the AE characteristics in a mixed mode loading, which may be generated in the actual structure. The results show that the thickness of the CFRP becomes more thick, the mode I energy release rate becomes a larger, and also the influence of mode I is greater than that of mode II. In addition, AE amplitude which shows the level of the damage in the structure was obtained the more damage in the CFRP with the thin thickness.