• Journal of Mechanical Science and Technology
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• v.14 no.5
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• pp.477-482
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• 2000

This study discusses a non-contact optical technique (electronic speckle pattern interferometry) that is well suited for thermal deformation measurement without any surface preparation and compensating process. Fiber reinforced plastics ($[0]_{16},\;[0/90]_{8S}$) were analyzed by ESPI to determine their thermal expansion coefficients. The thermal expansion coefficient of the transverse direction of a uniaxial composite is evaluated as $48.78{\times}10^{-6}(1/^{\circ}C)$. Also, the thermal expansion coefficient of the cross-ply laminate $[0/90]_{8S}$ is numerically estimated as $3.23{\times}10^{-6}(1/^{\circ}C)$ that is compared with that measured by ESPI.

• 한국방재학회:학술대회논문집
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• 2008.02a
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• pp.529-532
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• 2008

Recently the compound material has interested in using the structural material as the bridge member assembly. It is the lighter material against existing construction material and has excellent durability and economy. The existing floor of bridge has its short period to repair and replace compared to other parts of the bridge with the pavement and the shoe. These deteriorations of usage and safety by aging and corrosion are needed frequent maintenance. The use of compound material as a structural member suggests solve these problems. So this thesis evaluates the static and the fatigue performance for whether there are fiber lamination direction and stress concentration section of FRP floor plate, the compound material.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.17 no.5
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• pp.143-148
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• 2018

3D printing has been expanding beyond the bio/nano field to the automobile and aviation industries. 3D-printing technology has to overcome real problems to have economic value compared to its unlimited usability. Typically, the difference in mechanical strength along the lamination direction requires sufficient research to ensure reliability. In this paper, we study the anisotropic properties of ABS based on the stacking method of FDM 3D printing. Specifically, the mechanical properties of ABS material are determined through a tensile test and 3-point bending test, and the in-plane orthotropic properties are ascertained.

• Journal of Ocean Engineering and Technology
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• v.33 no.5
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• pp.377-386
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• 2019

Flexible composite propellers have a relatively large deformation under heavy loading conditions. Thus, it is necessary to accurately predict the deformation of the blade through a fluid-structure interaction analysis. In this work, we present an LST-FEM method to predict the deformation of a flexible composite propeller. Here, we adopt an FEM solver called OOFEM to carry out a structural analysis with an orthotropic linear elastic composite material. In addition, we examine the influence of the lamination direction on the deformation of the flexible composite propeller.

• Journal of the Korean Ceramic Society
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• v.36 no.2
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• pp.107-115
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• 1999

Microstructural variation and strengthening effects with lamination methods of alumina fiber-reinforced ${\gamma}$-LiAlO2 matrixes for Molten Carbonate Fuel Cell(MCFC) were studied. The porosities of all matrix laminated by hot-pressing of two green sheets under 1 kg/$\textrm{cm}^2$ at 45$^{\circ}C$ for 1 min and by double-casting which the second layer cast on the first green sheet dried for 3.5h were more than 50%. The strength of the Al2O3 fiber-reinforced matrix prepared by lamination was enhanced by 70% in comparison with the non-laminated matrix (115 gf/$\textrm{mm}^2$) and the strength-directionality due to fiber-orientation also could be removed. The strength of matrixes laminated by triple-casting was higher than that of the double-cast matrix, but triple-cast matrix showed the directionality with the casting direction, and furthermore its porosity was less than 50%. Although the strength of matrixes laminated by double-casting (195 gf/$\textrm{mm}^2$) is slightly less than that of matrixes laminated by hot-pressing (212 gf/$\textrm{mm}^2$), the double-casting method was evaluated to be more efficient laminating process in MCFC matrix processing.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2001.05a
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• pp.126-129
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• 2001

LIPCA (LIghtweight Piezo-composite Curved Actuator) is an actuator device which is lighter than other conventional piezoelectric ceramic type actuator. LIPCA is composed of a piezoelectric ceramic layer and fiber reinforced light composite layers, typically a PZT ceramic layer is sandwiched by a top fiber layer with low CTE (coefficient of thermal expansion) and base layers with high CTE. LIPCA has curved shape like a typical THUNDER (thin-layer composite unimorph feroelectric driver and sensor), but it is lighter an than THUNDER. Since the curved shape of LIPCA is from the thermal deformation during the manufacturing process of unsymmetrically laminated lay-up structure, an analysis for the thermal deformation and residual stresses induced during the manufacturing process is very important for an optimal design to increase the performance of LIPCA. To investigate the thermal deformation behavior and the induced residual stresses of LIPCA at room temperature, the curvatures of LIPCA were measured and compared with those predicted from the analysis using the classical lamination theory. A methodology is being studied to find an optimal stacking sequence and geometry of LIPCA to have larger specific actuating displacement and higher force. The residual stresses induced during the cooling process of the piezo-composite actuators have been calculated. A lay-up geometry for the PZT ceramic layer to have compression stress in the geometrical principal direction has been designed.

• Journal of the Korean Society of Safety
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• v.30 no.3
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• pp.7-12
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• 2015

CFRP composites are used as primary structural members in various industrial fields because their specific strength and specific stiffness are excellent in comparison to conventional metals. Their usage is expanding to high added-value industrial fields because they are more than 50% lighter than metals, and have excellent heat resistance and wear resistance. However, when CFRP composites suffer impact damage, destruction of fiber and interface delamination occur. This causes an unexpected deterioration of strength, and for this reason it is very difficult to ensure the reliability of the excellent mechanical properties. Therefore, for the destruction mechanism in bending with impact damage, this study investigated the reinforcement data regarding various external loads by identifying the consequential strength deterioration. Specimens were damaged by impact with a steel ball propelled by air pressure. Decrease in bending strength caused by the tension and compression of the impact side, and depending on the lamination direction of fiber and interface inside the specimen. From the bending test it was found that the bending strength reduced when the impact energy increased. Especially in the case of compression on the impact side, as tensile stress occurred at the damage starting point, causing rapid failure and a substantially reduced failure strength.

• Carbon letters
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• v.16 no.4
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• pp.241-246
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• 2015

Rapid industrial development in recent times has increased the demand for light-weight materials with high strength and structural integrity. In this context, carbon fiber-reinforced plastic (CFRP) composite materials are being extensively used. However, laminated CFRPs develop faults during impact because CFRPs are composed of mixed carbon fiber and epoxy. Moreover, their fracturing behavior is very complicated and difficult to interpret. In this paper, the effect of the direction of lamination in CFRP on the absorbed impact energy and impact strength were evaluated, including symmetric ply (0°/0°, −15°/+15°, −30°/+30°, −45°/+45°, and −90°/+90°) and asymmetric ply (0°/15°, 0°/30°, 0°/45°, and 0°/90°), through drop-weight impact tests. Further, the thermal properties of the specimens were measured using an infrared camera. Correlations between the absorbed impact energy, impact strength, and thermal properties as determined by the drop-weight impact tests were analyzed. These analyses revealed that the absorbed impact energy of the specimens with asymmetric laminated angles was greater than that of the specimens with symmetric laminated angles. In addition, the asymmetry ply absorbed more impact energy than the symmetric ply. Finally, the absorbed impact energy was inversely proportional to the thermal characteristics of the specimens.

• Smart Structures and Systems
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• v.13 no.4
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• pp.659-683
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• 2014

The static analysis of structures with arbitrary cross-section geometry and material lamination via a refined one-dimensional (1D) approach is presented in this paper. Higher-order 1D models with a variable order of expansion for the displacement field are developed on the basis of Carrera Unified Formulation (CUF). Classical Euler-Bernoulli and Timoshenko beam theories are obtained as particular cases of the first-order model. Numerical results of displacement, strain and stress are provided by using the finite element method (FEM) along the longitudinal direction for different configurations in excellent agreement with three-dimensional (3D) finite element solutions. In particular, a layered thin-walled cylinder is considered as first assessment with a laminated conventional cross-section. An atherosclerotic plaque is introduced as a typical structure with arbitrary cross-section geometry and studied for both the homogeneous and nonhomogeneous material cases through the 1D variable kinematic models. The analyses highlight limitations of classical beam theories and the importance of higher-order terms in accurately detecting in-plane cross-section deformation without introducing additional numerical problems. Comparisons with 3D finite element solutions prove that 1D CUF provides remarkable three-dimensional accuracy in the analysis of even short and nonhomogeneous structures with arbitrary geometry through a significant reduction in computational cost.

• Proceedings of the KSME Conference
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• 2001.06a
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• pp.363-369
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• 2001

By alternating $Al_{18}B_4O_{33}$/AC4CH composites with Al1050 sheets and then hot pressing, MMC/Al laminate composites have been successfully fabricated as parameters of the laminate structure and the number of Al sheet. Impact properties for laminate composites have been evaluated both in the laminate structure and in the impact load direction. Lamination of Al sheet and MMC layer showed a remarkable improvement in the absorbed impact energy compared to that of monolithic MMC. Laminate composites mounted with Al sheet at the outside of the configuration had a higher impact energy in the edge wise compared to that with Al sheet at the inside. Furthermore, there was an anisotrpy in the impact value of laminate composites, that is, impact values for the flat wise in a constant volume fraction of Al sheet dramatically increased along with Al sheet number, even if impact values fur the edge wise were nearly constant.