Fiber-reinforced polymer (FRP) exhibits superior tensile strength and corrosion resistance compared to steel but has a lower elasticity. Recently, researchers have addressed this by proposing composite sections of FRP and concrete. To ensure the intended composite behavior, these FRP–concrete sections should exhibit sufficient stress transfer between the two elements through a shear connection. Herein, various shear connection methods were proposed to improve the composite behavior of glass fiber–reinforced polymer (GFRP) plates and concrete. Through push-out tests, the behavior characteristics of the prepared specimens were analyzed. The findings confirm that an FRP shear key (FSK) with a small cross-section resists high shear stresses, making it suitable for sections vulnerable to damage from bolt drilling. Additionally, combining an FSK with bolts as shear connectors on a GFRP plate proves beneficial in preventing the fracture of the plate and improving the shear resistance.

Conductive polymer composites with high electrical and mechanical properties are in demand for bipolar plates of phosphoric acid fuel cells (PAFC). In this study, composites based on natural graphite/fluorinated ethylene propylene (FEP) and different ratios of carbon black are mixed and hot formed into bars. The overall content of natural graphite is replaced by carbon black (0.2 wt% to 3.0 wt%). It is found that the addition of carbon black reduces electrical resistivity and density. The density of composite materials added with carbon black 3.0 wt% is 2.168 g/cm3, which is 0.017 g/cm3 less than that of non-additive composites. In-plane electrical resistivity is 7.68 μΩm and through-plane electrical resistivity is 27.66 μΩm. Compared with non-additive composites, in-plane electrical resistivity decreases by 95.7 % and through-plane decreases by 95.9 %. Also, the bending strength is about 30 % improved when carbon black is added at 2.0 wt% compared to non-additive cases. The decrease of electrical resistivity of composites is estimated to stem from the carbon black, which is a conductive material located between melted FEP and acts a path for electrons; the increasing mechanical properties are estimated to result from carbon black filling up pores in the composites.

최근 국내 구조물들의 노후화가 진행됨에 따라 구조물 보강과 관련된 연구에 대한 관심이 높아지고 있다. FRP보강은 노후화가 진행되어 성능이 저하된 구조물을 보강하는데 사용되며 주로 유리섬유 및 탄소섬유를 사용한다. 그러나 이 두 가지의 섬유는 경제적으로나 환경적으로나 나쁜 점이 있다. 따라서 본 연구에서는 친환경적이고 내열성이 우수한 현무암 섬유를 구조 용 보강재로 제시하고자 하였다. 또한 본 연구에서는 현무암 섬유에 가장 적합한 수지를 찾기 위하여 에폭시, 폴리에스테르 및 비닐에스테르를 함침 하였다.그 결과, 에폭시 수지를 사용하였을 때 가장 높은 인장 강도 및 탄성계수를 보였으며 전단강도 및 전단탄성계수가 타 수지에 비하여 50%정도 높게 측정되었다. 현무암섬유와 탄소, 유리 섬유의 물성을 비교한 결과 인장강도는 CFRF의 약 60%정도이나 GFRP보다 30%정도 높게 나타내었다.

Nacre of abalone shell features a “brick-and-mortar” microstructure, in which micro-plates of calcium carbonate are bonded by nanometers-thick layers of chitin and proteins. Due to the microstructure and its unique toughening mechanisms, nacre possesses an excellent combination of specific strength, stiffness and toughness. This study deals with the possibility of using nacre fragments obtained from abalone shell for making a bulletproof armor system. A composite plate laminated with abalone shell fragments is made and compression and bend tests are carried out. In addition, a bulletproof test is performed with hybrid armor systems which are composed of an alumina plate, a composite plate, and aramid woven fabric to verify the ballistic performance of nacre. The compressive strength of the composite plate is around 258.3MPa. The bend strength and modulus of the composite plate decrease according to the plate thickness and are about 149.2MPa and 50.3 GPa, respectively, for a 4.85 mm thick plate. The hybrid armor system with a planar density of 45.2 kg/m2, which is composed of an 8 mm thick alumina plate, a 2.4 mm thick composite plate, and 18 layers of aramid woven fabric, satisfy the NIJ Standard 0101.06 : 2008 Armor Type IV. These results show that a composite plate laminated with abalone shell fragments can be used for a bulletproof armor system as an interlayer between ceramic and fabric to decrease the armor system’s weight.

In this paper, the result of application of this simple method of vibration analysis developed by the author, to the special orthotropic plates with variable cross-section, and with a pair of opposite edges simple supported and the other pair of opposite edges free is presented. This problem represents the simple-supported single span bridge system without effective longitudinal edge beams. The effect of concentrated point mass/masses is also studied.

A composite material was prepared for the bipolar plates of phosphoric acid fuel cells(PAFC) by hot pressing a flake type natural graphite powder as a filler material and a fluorine resin as a binder. Average particle sizes of the powders were 610.3, 401.6, 99.5, and 37.7 μm. The density of the composite increased from 2.25 to 2.72 g/cm3 as the graphite size increased from 37.7 to 610.3 μm. The anisotropy ratio of the composite increased from 1.8 to 490.9 as the graphite size increased. The flexural strength of the composite decreased from 15.60 to 8.94MPa as the graphite size increased. The porosity and the resistivity of the composite showed the same tendencies, and decreased as the graphite size increased. The lowest resistivity and porosity of the composite were 1.99 × 10−3 Ωcm and 2.02 %, respectively, when the graphite size was 401.6 μm. The flexural strength of the composite was 10.3MPa when the graphite size was 401.6 μm. The lowest resistance to electron mobility was well correlated with the composite with lowest porosity. It was possible the flaky large graphite particles survive after the hot pressing process.

Compared with conventional construction materials such as steel and concrete, the advanced composite materials are corrosion-free, light-weight, and when used as construction materials, the construction period can be made less than one-tenth needed for conventional materials. However, because of the difficult theories and formulas, the ordinary construction engineers have difficulties in understanding and calculating formulas needed in construction. In this paper, calculation of the stiffnesses of the advanced composite laminated plates and compared with the result of stiffnesses.

Impact damages induced by a low-velocity impact load on carbon fiber reinforced polymer (CFRP) composite plates fabricated with various stacking sequences were studied experimentally. The impact responses of the CFRP composite plates were significantly affected by the laminate stacking sequences. Three types of specimens, specifically quasi-isotropic, unidirectional, and cross-ply, were tested by a constant impact carrying the same impact energy level. An impact load of 3.44 kg, corresponding to 23.62 J, was applied to the center of each plate supported at the boundaries. The unidirectional composite plate showed the worst impact resistance and broke completely into two parts; this was followed by the quasi-isotropic lay-up plate that was perforated by the impact. The cross-ply composite plate exhibited the best resistance to the low-velocity impact load; in this case, the impactor bounced back. Impact parameters such as the peak impact force and absorbed energy were evaluated and compared for the impact resistant characterization of the composites made by different stacking sequences.

In this study, we performed non-elastic dynamic analyses using LS-DYNA for plate structures made of laminated composite materials. It was used mat_59_composite_failure_shell_model providing from LS-DYNA as material model of composite material The material which is applied in the analysis as CFRP and GFRP, were compared by performing the dynamic analysis in accordance with various layup sequences. Numerical results show structural resistance against impact loading for different materials. In addition, The significance of the layup sequence in analyzing composite structures under impact loading is enunciated in this paper

A study on the vibration and buckling analyses of laminated composite plates is described in this paper. In order to carry out the analyses of laminated composite plates, a NURBS-based isogeometric general plate element based on Reissner-Mindlin (RM) theory is developed. The non-uniform rational B-spline (NURBS) is used to represent the geometry of plate and the unknown displacement field and therefore, all terms required in this element formulation are consistently derived by using NURBS basis function. Numerical examples are conducted to investigate the accuracy and reliability of the present plate element. From numerical results, the present plate element can produce the isogeometric solutions with sufficient accuracy. Finally, the present isogeometric solutions are provided as future reference solutions.

This study is aimed to examine the influence of the rotational stiffness of U-shaped ribs on the local buckling behaviors of laminated composite plates. Applying the orthotropic plates with eight layers of the layup [(0°)4]s and [(0°/90°)2]s, 3-dimensional finite element models for the U-rib stiffened plates were setup by using ABAQUS and then a series of eigenvalue analyses were conducted. There is a need to develope a simple design equation to establish the rotational stiffness effect, which could be easily quantified by comparing the theoretical critical stress equation for laminated composite plates with elastic restraints based on the Classical laminated plate theory. Through the parametric numerical studies, it is confirmed that there should clearly exist an increasing effect of local plate buckling strength due to the rotational stiffness by closed-section ribs. An applicable coefficient for practical design should be verified and proposed for future study. This study will contribute to the future study for establishing an increasing coefficient for the design strength and optimum design of U-rib stiffened plates.

This study is aimed to examine the influence of the rotational stiffness of U-shaped ribs on the local buckling behaviors of laminated composite plates. Applying the orthotropic plates with eight layers of the layup [(0°)4]s and [(0°/90°)2]s, 3-dimensional finite element models for the U-rib stiffened plates were setup by using ABAQUS and then a series of eigenvalue analyses were conducted. There is a need to develope a simple design equation to establish the rotational stiffness effect, which could be easily quantified by comparing the theoretical critical stress equation for laminated composite plates with elastic restraints based on the Classical laminated plate theory. This study will contribute to the future study for evaluating the design strength and optimum design of U-rib stiffened plates.

In this paper, an efficient yet accurate method for the thermal stress analysis using a first order shear deformation theory(FSDT) is presented. The main objective herein is to systematically modify transverse shear strain energy through the mixed variational theorem(MVT). In the mixed formulation, independent transverse shear stresses are taken from the efficient higher-order zigzag plate theory, and the in-plane displacements are assumed to be those of the FSDT. Moreover, a smooth parabolic distribution through the thickness is assumed in the transverse normal displacement field in order to consider a transverse normal deformation. The resulting strain energy expression is referred to as an enhanced first order shear deformation theory, which is obtained via the mixed variational theorem with transverse normal deformation effect(EFSDTM_TN). The EFSDTM_TN has the same computational advantage as the FSDT_TN(FSDT with transverse normal deformation effect) does, which allows us to improve the through-the-thickness distributions of displacements and stresses via the recovery procedure. The thermal stresses obtained by the present theory are compared with those of the FSDT_TN and three-dimensional elasticity.

This study presents a governing equations of bending behavior of anisotropic sandwich plates with multi-layered laminated composite faces. Based on zig-zag models for through thickness deformations, the shear deformation of composite faces is included. All edges of plate are assumed to be simply supported. Results of the bending analysis under lateral loads are presented for the influence of various lay up sequences of antisymmetric angle-ply laminated faces. The accuracy of the approach is ascertained by comparing solutions from the sandwich plates theory with composite faces to the laminated plates theory. Since the present analysis considers the bending stiffness of the core and also the transverse shear deformations of the laminated faces, the proposed method showed higher than that calculated according to the general laminated plates theory. The information presented might be useful to design sandwich plates structure with polymer matrix composite faces.

This paper presents free vibration characteristics of laminated composite plates with different embedded delamination sizes and locations using three-dimensional finite elements. The free vibration analysis using the 3D finite element (FE) delamination model has merits in that it shows better accuracy but also shows the entire mode shape compared to the conventional approaches. This study investigates free vibration characteristics of laminated composite plates containing an various embedded delamination. The numerical results obtained are in good agreement with those reported by other investigators. Specifically, in this paper, attention is paid to the effects of the local vibration mode for various parameters, such as size of delamination, aspect ratio, and location of delamination.

Even though the longitudinally stiffened laminated composite plates with closed section ribs should be an effective system for axially compressed members, the existing researches on the applications of closed-section ribs, especially for the laminated composite plates, are not sufficient. This study is aimed to examine the influence of the sectional stiffness of U-shaped ribs on the buckling modes and strengths of laminated composite plates. Applying the orthotropic plates with eight layers of the layup [(0°)4]s and [(0°/90°)2]s, 3-dimensional finite element models for the U-rib stiffened plates were setup by using ABAQUS and then a series of eigenvalue analyses were conducted. From the parametric studies, the minimum required ply thicknesses as well as the buckling strengths were presented for the analysis models. The buckling strengths were compared with the theoretical critical stress equation for simply supported plates based on the Classical laminated plate theory. This study will contribute to the future study for evaluating the minimum required stiffness and optimum design of U-rib stiffened plates

압축을 받는 복합적층판의 보강을 위해 폐단면리브를 적용하는 것이 효과적이나, 적정 크기나 최적 두께에 대한 충분한 연구자료가 제시되지 못하고 있다. 이에 따라 폐단면리브 단면 제원에 따른 복합적층판의 압축좌굴 거동에 대한 영향이 우선 검토되어야 할 필요성이 있다. 본 논문에서는 직교이방성 [(0°)4]s와 Cross-ply [(0°/90°)2]s 적 층단면을 각각 고려하여 U리브 단면강성에 따른 복합적층 보강판의 탄성좌굴강도 및 좌굴모드의 변화를 수치해석 적으로 검토하였다. 구조부재로써 적용성을 고려하여 U리브 단면 모델을 선정하였고 유한요소해석 프로그램인 ABAQUS를 이용하여 U리브 적층두께에 따른 고유치 해석을 실시하였다. U리브와 같은 폐단면 보강재를 적용한 복 합적층판에서는 단순지지 조건의 판좌굴 강도에 비해 상승효과가 있음이 본 연구의 수치해석 결과로부터 입증되었 으며 본 해석연구 대상 모델에 대해 U리브 최적 적층두께를 분석하였다. 본 논문의 연구 결과는 향후 U리브의 최 적 단면 선정방안을 제시하는데 기여할 수 있을 것으로 기대된다.

복합적층판은 다른 금속재료에 비해 높은 비강도, 비강성 등의 우수한 역학적 특성을 지니므로 최근 다양한 분야에서 사용하고 있다. 그러나 이러한 복합적층판은 일반 금속재료에 비해 충격에 약하다는 단점이 있다. 이 점을 해결하기 위한 연구는 많은 연구자들에 의해 다양하게 시도되고 있다. 본 연구는 복합적층판에 초기응력을 도입하여 충격거동 특성을 파악한다. 고전적인 이론식인 Hertz의 접촉법칙과 실험식인 Sun과 Tan의 압입법칙을 포함한 유한요소프로그램을 이용하여 복합적층판의 초기응력에 의한 충격거동 특성을 조사한다.