• Proceedings of the KSME Conference
• /
• 2001.06a
• /
• pp.26-36
• /
• 2001

Smart sensors and actuators have recently been developed. In this study, first, small-diameter fiber Bragg grating (FBG) sensors developed by the author, whose cladding and polyimide coating diameters were 40 and $52{\mu}m$, respectively, were embedded inside a laminate without resin-rich regions around sensors and the deterioration of mechanical properties of the composite laminate. The small-diameter FBG sensor was embedded in $0^{\circ}$ ply of a CFRP laminate for the detection of transverse cracks in $90^{\circ}$ ply of the laminate. The reflection spectra from the FBG sensor were measured at various tensile stresses. The spectrum became broad and had some peaks with an increase of the transverse crack density. Furthermore, the theoretical calculation reproduced the change in the spectrum very well. These results show that the small-diameter FBG sensors have a potential to detect the occurrence of transverse cracks through the change in the form of the spectrum, and to evaluate the transverse crack density quantitatively by the spectrum width. On the other hand, shape memory alloy (SMA) films were used to suppress the initiation and growth of transverse cracks in CFRP laminates. Pre-strained SMA films were embedded between laminas in CFRP laminates and then heated to introduce the recovery stress in SMA films and compressive stresses in the weakest plies ($90^{\circ}$ ply). The effects of recovery stresses are demonstrated in the experiments and well predicted using the shear-lag analysis and the nonlinear constitutive equation of SMA films.

• Proceedings of the Korean Ceranic Society Conference
• /
• 2002.10a
• /
• pp.101.1-101
• /
• 2002

• Proceedings of the Korean Ceranic Society Conference
• /
• 2003.10a
• /
• pp.225.1-225
• /
• 2003

• Structural Engineering and Mechanics
• /
• v.16 no.5
• /
• pp.557-580
• /
• 2003

Laminated composite structures find wide range of applications in many branches of technology. They are much suited for weight sensitive structures (like aircraft) where thinner and lighter members made of advanced fiber reinforced composite materials are used. The orientations of fiber direction in layers and number of layers and the thickness of the layers as well as material of composites play a major role in determining the strength and stiffness. Thus the basic design problem is to determine the optimum stacking sequence in terms of laminate thickness, material and fiber orientation. In this paper, a new optimization technique called Cellular Automata (CA) has been combined with Genetic Algorithm (GA) to develop a different search and optimization algorithm, known as Cellular Genetic Algorithm (CGA), which considers the laminate thickness, angle of fiber orientation and the fiber material as discrete variables. This CGA has been successfully applied to obtain the optimal fiber orientation, thickness and material lay-up for multi-layered composite hybrid beams plates and shells subjected to static buckling and dynamic constraints.

• Journal of Ocean Engineering and Technology
• /
• v.9 no.2
• /
• pp.89-97
• /
• 1995

The investigate the effect of fiber orientation on the interlaminar fracture toughness of carbon fiber reinforced plastics three prepregs which are domestic products are used in this paper. Those are used for the unidirectional composites, but only one is used for the cross-ply laminate composites which is molded $[0/90]_{6s},\;[0/45]_{6s},\;and\;[0/45/90]_{4s}$. The specimens used for the mode I and mode II Tests are DCB and ENF samples are examined by scanning electron microscope(SEM). The value of $G_{IC}$ is almost same when modified three calculating methods are applied. The highest value of $G_{IC}$at crack initiation is obtained at the $[0/90]_{6s}$ interlaminar and the lowest one is at the $[0/45/90]_{4s}$ interlaminar. The highest value of $G_{IIC}$ at crack initiation, however, is obtained at the $[0/90]_{6s}$ interlaminar and the lowest one is at the $[0/45]_{6s}$. The photographs of SEM show a difference behaviour between mode I and mode II fracture surface.

• Composites Research
• /
• v.29 no.5
• /
• pp.231-235
• /
• 2016

In this study, integrated co-bonded panels with the same configuration of hat stiffeners were fabricated and measured for ply waviness phenomenon. Total specimens consisted of 2 types; 1) the general co-bonded panel and 2) the co-bonded panel with caul plate made of carbon epoxy composite materials. The first general co-bonded panel specimen exhibited that laminate thickness on the stiffener location area was much thicker than the non-stiffener area and, there was ply waviness with 0.61 mm height and 3.29 mm length. In the second co-bonded panel specimen, the reduced waviness with 0.22 mm height and 1.37 length resulted in more than 50% improvements, which is due to the uniform pressure distribution of co-bonded interface by caul plate.

• Composites Research
• /
• v.16 no.5
• /
• pp.39-44
• /
• 2003

Embedding viscoelastic-damping materials into composites can greatly increase the damping properties of composite structures. Usually viscoelastic-damping materials behave isotropically so that their damping properties are the same in all directions. In these days, there is a desire to develop viscoelastic-damping materials that behave orthotropically so that damping properties vary with material orientation. These orthotropic damping materials can be made by embedding rows of thin wires within the viscoelastic materials. These wires add significant directional stiffness to the damping materials. where the stiffness variation with wire orientation follows classical lamination theory. In this paper, the loss factor of composite laminate was evaluated based on Ni and Adams' theory. To investigate the effect of directional damping material, the low-velociy impact response analysis was also performed. The present analysis results show that directional damping material has a great influence on vibration and damping characteristic of composite laminate.

• Journal of Magnetics
• /
• v.16 no.4
• /
• pp.398-402
• /
• 2011

A novel laminate composite of FeCuNbSiB/FeNi /PZT is proposed, where FeCuNbSiB has a permeability of around 100000, which is much larger than that of FeNi. The high-permeability FeCuNbSiB was laminated with piezomagnetic FeNi rather than attached to its ends. It is expected that the effect produced by the high permeability will act on the whole of the piezomagnetic layer. While a FeNi layer was laminated with a FeCuNbSiB layer, the strong demagnetization produced by the latter was expected to be imposed on the FeNi layer as well as the applied fields. The distribution of applied fields was altered by the high-permeability material (both bias and ac field) and the field variation positively contributed to the ME effect in piezomagnetic/piezoelectric composites. Thus the ME voltage coefficient along with the field sensitivity were improved.

• Journal of the Korean Ceramic Society
• /
• v.37 no.11
• /
• pp.1058-1064
• /
• 2000

연속슬립캐스팅 및 상압소결법으로 $Al_2$O$_3$/ZrO$_2$적층복합체를 제조하였으며, 적층복합체에서 ZrO$_2$층을 단사정, 정방정 및 입방정으로 각각 달리 적층하여 균열생성 및 전파 거동에 미치는 ZrO$_2$상의 영향을 고찰하였다. 균열 생성은 냉각시 $Al_2$O$_3$층과 ZrO$_2$층 간의 열팽창 계수의 차이에 의한 열적불일치응력이 가장 큰 요인으로 작용하였다. 적층체 내에 존재하는 균열은 tetra-ZrO$_2$의 경우 적층두께 조절로 가능하였으며, cubic-ZrO$_2$의 경우는 냉각속도 조절로 균열밀도로 크게 낮출 수 있었다. $Al_2$O$_3$/ZrO$_2$적층체를 구성하는 세가지 ZrO$_2$상(mono, tetra, cubic)들 중에서 cubic-ZrO$_2$가 포함된 적층체의 경우 $Al_2$O$_3$와 ZrO$_2$계면에 형성된 잔류압축응력으로 인한 균열굴절 효과를 얻을 수 있었다.

• Journal of the Korea Convergence Society
• /
• v.10 no.5
• /
• pp.165-171
• /
• 2019

Engineering and Technology have been influencing a lot in the field of sports. Competitiveness, attributes of sports, have forced not only sports players but sports goods to enhance those performance. Particularly in the field of motorsports, the convergence of sports and technology has long been done to satisfy between performance and safety. In this study, strength analysis was carried with FEM to develop CFRP Laminate(Carbon Fiber Reinforced Plastic Laminate) bucket seat targeted to motorsports and car tuning industries and FIA($F\acute{e}d\acute{e}ration$ Internationale de l'Automobile) regulation was applied to design the racing seat and evaluate its strength. FEM modeling considered the attributes of composites was followed by strength evaluation based on Tsai-Wu failure index were done according to Lay-up sequence and layer numbers. The result showed that the lay-up sequence with stacking angle such as $[0^{\circ}/30^{\circ}/60^{\circ}/90^{\circ}/-30^{\circ}/-60^{\circ}]_4$ with 3mm form core was optimal selection in the field of weight and strength evaluation.