• Composites Research
• /
• v.19 no.2
• /
• pp.20-27
• /
• 2006

The hybrid composite materials with non-woven tissue (NWT) was developed to improve the mechanical properties of conventional FRP composite materials. The hybrid prepreg with NWT consists of FRP prepreg and NWT prepreg. The NWT prepreg consists of NWT and polymer resin. The NWT has short fibers, discretely distributed with in-plane random orientation fibers. The purposes of this study of hybrid prepreg with NWT are (i) to increase the interlaminar properties(the fracture toughness and strength), (ii) to improve the mechanical properties and reliability, while maintaining a low cost, (iii) to introduce a tough and strong interlayer at critical positions to be required of strength in the laminate. To accomplish the above purposes, a production technique to decrease voids in NWT layers was proposed in this paper. The interlaminar failure characteristics of laminated composite materials was tremendously improved by hybrid concept with NWT.

• Polymer(Korea)
• /
• v.24 no.3
• /
• pp.350-357
• /
• 2000

Curing behaviors of glass/epoxy prepreg for printed circuit boards (PCB) were studied by using dielectrometer and differential scanning calorimeter. This prepreg was showed the lowest ionic viscosity at about 115$^{\circ}C$, and then the ionic viscosity was gradully increased up to 15$0^{\circ}C$. This indicated that the curing reaction of this prepreg started at 115$^{\circ}C$ and the molecular weight was increased by the accelerated thermal cross-linking reaction. The loss factor and tan $\delta$ values were also measured and discussed. The dielectric behaviors of this prepreg system were also measured according to the cure cycle for PCB. This material was found to be thermally stable up to about 30$0^{\circ}C$ and then was showed an abrupt decomposition beyond this temperature.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 1995.05a
• /
• pp.23-29
• /
• 1995

Fafbric 4종, 수지2종과 상용화된 프리프레그 2종에 대한 내열특성에 관하여 비교 연구 하였다. Fabric의 특성은 알려진 바와 같이 PAN계 카본 fabric의 경우 내삭마성은 우수하나 단열성능이 떨어지고, Rayon계의 경우는 그 반대이다. 공정성면에서는 rayon spun yarn으로 제직한 경우가 가장 우수한 것으로 나타났다. Spun PAM으로 제직한 경우는 직조후 탄화공정을 채택함으로써. 노즐재료로서 PAN계 탄소섬유의 사용을 가능하게 하였지만 즉 공정성은 좋으나 단열성 및 내삭마성 모두가 떨어졌다. F940수지의 경우는 SC1008과 페놀수지의 화학적특성은 다소 차이가 있으나 물리적특성이나 열적특성은 거의 유사한 것으로 나타났다. 프리프레그의 제조는 각수지와 Fabric의 조건에 맞게 R/C, V/C를 조정하여 코팅하였다. 토오치 테스트등 결과들을 종합해보면 전체적인 노즐재료로서의 성능은 아직은 Rayon계 카본이 우수한것으로 판단할수 있으나, 보다 정확한 평가를 위해서는 실제 노즐 테스트가 필요하다.

• Composites Research
• /
• v.24 no.6
• /
• pp.7-11
• /
• 2011

Polyurethane oligomers (PUOs) such as UA8297, UP127 and EB8200 were utilized to enhance the anti-bullet property of Dyneema$^{(R)}$/vinylester composites. First, prepregs of PUO and vinylester (XSR10) were prepared via spray coating on Dyneema$^{(R)}$ fabric at 21 % resin content (by volume). In addition, spray coating and film lamination were also carried out with a mixture of XSR10/PUO for selected PUOs. Next, the prepregs were dried at RT for 1-2 h and then at $100^{\circ}C$ for 30 min to remove the solvent and to provide partial cure when necessary. The prepregs were stacked in 24 layers and cured at $120^{\circ}C$ for 5 min under the contact pressure and for additional 25 min at 150 $kg/cm^2$. Finally, the anti-bullet properties of composite samples were evaluated by measuring $V_{50}$ with simulated fragment projectile (SFP, 17 gr). The results showed a 6.5 and 9.0 % increase of $V_{50}$ with UP127 and EB8200, respectively.

• Composites Research
• /
• v.28 no.5
• /
• pp.249-253
• /
• 2015

This paper reports a study on a method for achieving lightweight thermoplastic laminate composites referred to as tow spreading technology. Thickness of an unspread 12 K carbon fiber tow is reduced by increasing the tow width from 7 mm to 20 mm. The polypropylene (PP) film was used to stabilize and impregnate the spread tow, covering it into a partially consolidated prepreg: 12 K carbon fiber spread tow/PP. Laminates were fabricated from the spread tow prepreg and control laminate composites were produced from unspread tow prepreg consisting of 12 K carbon fiber and PP. The void content, tensile and flexural properties of the composite laminates were investigated. Consequently, the spread tow laminate composite exhibited lower void content and improved mechanical properties.

• Journal of the Microelectronics and Packaging Society
• /
• v.20 no.1
• /
• pp.21-26
• /
• 2013

This study presents new analysis method to predict bending behavior of packaging substrate structure by comparing finite element method simulation and measured curvature using 3D scanner. Packaging substrate is easily bent and deflected while undergoing various processes such as curing of prepreg and copper pattern plating. We prepare specimens with various conditions and measure contours of each specimen and compute the residual stresses on deposited films using analytical solution to find the principle of bending. Core and prepreg in packaging substrate are made up of resin and bundles of fiber which exist orthogonally each other. Anisotropic material properties cause peculiar bending behavior of packaging substrate. We simulate the bending deflection with finite element method and verify the simulated deflection with measured data. The plating stress of electrodeposited copper is about 58 MPa. The curing stresses of solder resist and prepreg are about 13 MPa and 6.4 MPa respectively in room temperature.

• Composites Research
• /
• v.35 no.4
• /
• pp.288-297
• /
• 2022

This study investigated the effect of addition of zirconia(zirconium oxide) powder on the curing behavior of phenolic resins. The heating rate controlled curing and isothermal curing behaviors of the phenol resin according to the content of the zirconia powder were analyzed. The viscosity and thermal decomposition characteristics of the phenolic resin with the zirconia content were also examind. From the DSC analysis, the degree of cure and the rate of cure were obtained. Finally, the activation energy for the cure reaction were calculated from the DSC data of the zirconia added phenolic resin. As a found, the higher the zirconia content, the longer the curing was delayed and the greater the activation energy required for curing. Additionally, the TGA result that as the content of zirconia increased, less weight loss was observed. The surface tackiness of the Carbon/Phenol prepreg was partially changed according to the zirconia content, but had no significant effect.

• Journal of Ocean Engineering and Technology
• /
• v.11 no.2
• /
• pp.48-56
• /
• 1997

This work has been investigated in order to study the influence of the moisture absorption on the mechanical pf the glass fiber/epoxy resein composites and the carbon fiber/epoxy resein composites. The types of glass fiber used in the glass fiber/epoxy resein composites were randomly oriented fiber and plain fabric fiber. And carbon fiber.epoxy resein composites was laminated with fabric prepreg which was formed with carbon fiber and epoxy resein. Both composites were immersed up to 100 days in distilled water at $80^{\circ}C$, and then dried up to 3 days in an oven at 80$80^{\circ}C$. Both composites were measured for the weight gain of water(wt.%) and tensile strength through immersion and dry time. Consequently, it was found that the tensile strength of thw glass fiber/epoxy resein composites and the carbon fiber/epoxy resein composites were reduced proportionally to the moisture absortion rate. Also, the tensile strength of glass fiber composites was decreased more than that of the carbon fiber composites. Additionally, it was found that the tensile strength of all composites which decreased by moisture absorption were partly recovered by drying in an oven at 80$80^{\circ}C$.

• Composites Research
• /
• v.14 no.1
• /
• pp.22-29
• /
• 2001

The purpose of this paper is to determine the effect of the autoclave inner pressure rate, heat-up rate, tool round angle, Thickness of core, height of joggle on defects, and to minimize the defects of aircraft sandwich structure reinforced with honeycomb core occurred in autoclave processing. The results showed that the geometry of aircraft sandwich structure and tool such as tool round angle, thickness of core, height of joggle, and the autoclave cure conditions such as inner pressure rate, heat up rate strongly affected the core movement, core wrinkle, bridge phenomenon of prepreg and depression of core that occurred in autoclave processing.

• Proceedings of the Korean Society For Composite Materials Conference
• /
• 1999.04a
• /
• pp.189.1-192
• /
• 1999

Mechanical characteristics of composite laminates with carbon tissue and glass scrim are evaluated in this paper. Composite laminates in USN125 group are made by inserting carbon tissue and glass scrim between layers. Consequently it was shown that mechanical characteristics of carbon fiber reinforced composite materials were improved by inserting carbon tissue.