• Advanced Composite Materials
• /
• v.16 no.4
• /
• pp.349-360
• /
• 2007

Recently, natural fiber reinforced composite is attracting attention and considered as an environmentally friendly material. Usually cellulosic fibers are used to reinforce the composites, but some protein fibers such as silk and wool serve the same purpose. In this paper, we proposed a method of producing artistic composite from artistic fabric by using silk fiber reinforced biodegradable plastic, which is designated as 'silk composite', for reinforcement. In order to expand applications of the silk composite, we performed the compression molding of decorative laminates with woody material, which was selected as a core material, and examined the properties of molded decorative laminates with various content of the silk composite. Since plywood and medium-density fiberboard (MDF) are widely used for decorative laminates, we selected them as core materials. As a result, flexible decorative laminates with high flexural strength were obtained by compounding the silk composite with wood materials.

• Journal of the Society of Naval Architects of Korea
• /
• v.57 no.2
• /
• pp.104-113
• /
• 2020

The study aims to improve the previous theory-based algorithm on the lightweight design of laminate structures of a composite ship based on the mechanical properties of fiber, resin, and laminates obtained from experiments. From a case study on using a hydrometer to measure the specific gravity of e-glass fiber woven roving fabric/polyester resin used as the raw material for the hull of a 52 ft composite ship, the equation for calculating the weight of laminate was redefined, and the relationship between decreasing mechanical properties and increasing glass content was determined from the results of material testing according to ASTM D5083 and ASTM D790. After applying these experimental data to the existing algorithm and improving it, a possible laminate design that maximizes the specific strength of the composite material was confirmed. In a case study that applied the existing algorithm based on rules, the optimal lightweight design of composite structures was achieved when the weight fraction of e-glass fiber was increased by 57.5% compared with that in the original design, but the improved algorithm allowed for an increase of only 17.5%.

• Composites Research
• /
• v.25 no.4
• /
• pp.105-109
• /
• 2012

Recently, development of a small aircraft has been carried out for the BASA(Bilateral Aviation Safety Agreement) program in Korea. This aircraft adopted all composite structures for environmental friendly by low fuel consumption due to its lightness behavior. However the composite structure has disadvantage which is very weak against impact damages. Therefore, damage allowable design of aircraft structure must be performed considering compressive fracture strength. This point is very important for certification of composite structure aircraft. In this paper, it is performed the research on damage tolerance of thick laminate adopting aircraft structure. The damage tolerance of three different types of thick laminates such as no damage, open hole and impact damage is evaluated under compression loading.

• Journal of the Korean Society of Safety
• /
• v.26 no.6
• /
• pp.54-63
• /
• 2011

Steel plate or FRP materials have been typically used for the seismic retrofit of civil infrastructures. In order to overcome the limitation of each retrofitting material, a composite material, which takes advantages from both metal and fiber polymer materials, has been developed. In the study herein, the composite retrofitting material consists of metal part(steel or aluminum) and FRP sheet part(glass or carbon fiber). The metal part can enhance the ductility and the FRP part the ultimate strength. As a preliminary study to investigate the fundamental mechanical characteristics of the metal-FRP laminated composite material this study performed the tensile test with various experimental variables including the number, the angle and the combination of FRP laminates. From the test results, both aluminum and steel-FRP laminate composite material showed increased fracture toughness. However, the angle and the kind of fibers should be carefully considered in conjunction with the expected loading conditions. In general, steel-FRP laminate composite showed better tensile performance in regards to the seismic retrofit purposes.

• Journal of the Computational Structural Engineering Institute of Korea
• /
• v.28 no.5
• /
• pp.497-502
• /
• 2015

In this paper, a stress function-based approach was proposed to analyze the reduction of free-edge peeling stress in smart composite laminates using piezoelectric actuator under bending load. Electro-mechanically coupled governing equation was obtained by complimentary virtual work principle. The stress state was solved by the generalized eigenvalue procedure. The free-edge peeling stress of smart composite laminates was reduced by the piezoelectric actuation. The reduction rate of peeling stress in cross-ply composite laminate is larger than that in angle ply composite laminate.

• Journal of Ocean Engineering and Technology
• /
• v.13 no.4 s.35
• /
• pp.37-44
• /
• 1999

Hardness characteristics and microstructures of $Nb/MoSi_2$ laminate composites were evaluated from the variation of fabricating conditions such as preparation temperature, applied pressure and pressure holding time. $Nb/MoSi_2$ laminate composites composed of $MoSi_2$ powder and Nb sheets were fabricated by the hot press. From experimental results, it was found that the lamination from Nb sheet and $MoSi_2$ powder was an excellent strategy to improve hardness characteristics of monolithic $MoSi_2$. However, interfacial reaction products like(Nb, Mo)$SiO_2\;and\;Nb2Si_3$ formed at the interface of $Nb/MoSi_2$ and increased with fabricating temperature.

• The Journal of Korean Academy of Prosthodontics
• /
• v.30 no.1
• /
• pp.85-91
• /
• 1992

The purpose of this study was to evaluate the bonding strength between porcelain laminate and Ni-Cr alloy in the various surface treatments of the bonding faces. For this study the metal surface of specimens were treated : 1) etching only, 2) sandblasting only, and 3) sandblasting and etching. The porcelain laminate were made and bonded to the metal specimens with light curing composite resin cement. Instron testing machine was used to measure their bonding strength : and the result was obtained as follows : 1. The bonding strength of the double treatment of the sandblasting and etching group was higher than that of the single treatment of sandblasting or the etching group. 2. The bonding strength of the sand blasting group was higher than that of the etching group. 3. The debonding were mainly occurred between the Ni-Cr alloy and the composite resin cement.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2007.04a
• /
• pp.212-216
• /
• 2007

Predicting microcracking properties of the composite laminates in nonuniform stress conditions was the subject in this paper. The uniform stress field meant the stresses were independent of the width direction. The material was the 954-2A/IM7 laminates containing a central hole. Microcracks initiated at the edge of the hole and propagated into the laminate. Because the tensile stress concentration decreased with distance, the microcracks were arrested before the edge of the laminate. Because carbon fiber composites were opaque, a x-ray method was used to detect the length of the propagating microcracks. The microcracking at the near edge of the hole could be reasonably predicted by considering the local laminate stresses and the microcracking toughness measured in unnotched laminates. However, the date away from the hole did not agree with the predictions. The local microcrack density was always much higher than that predicted by the local laminate stress.

• Proceedings of the Korean Society For Composite Materials Conference
• /
• 2002.05a
• /
• pp.35-38
• /
• 2002

Real defects in composite structures were detected by using laser measuring system. Four types of specimens, that is, a composite laminate, a honeycomb structure, a free-edge delamination and an adhesive joint, were used to study the applicability of ESPI and Shearography to composite structures. Thermal loading method, which can easily induce the surface deformation of specimen, was used to detect defects. Experimental results show that defects in composite structures can be easily detected by ESPI and Shearography. Moreover, it shows that ESPI and Shearography can be usefully applied to the detection of defects in various kinds of composite structures.

• Advances in aircraft and spacecraft science
• /
• v.7 no.2
• /
• pp.151-168
• /
• 2020

The present study deals with the repair of composite structures by bonding composite patches. The composite structure is a carbon/epoxy laminate with stacking sequence [45/-45/0/90]S. The damaged zone is simulated by a central crack and repaired by bonding symmetrical composite patches. The repair is carried out using composite patches laminated from the same elemental folds as those of the cracked specimen. Three-dimensional finite element method is used to determine the energy release rate along the front of repaired crack. The effects of the repair technique used single or double patch, the stacking sequence of the cracked composite patch and the adhesive properties were highlighted on the variations of the fracture energy in mode I and mixed mode I + II loading.