• Composites Research
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• v.33 no.3
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• pp.101-107
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• 2020

This study investigates the characterization on the thermal insulation properties of silicon carbide coating on the C_f-C composites. The silicon carbide coatings by chemical vapor deposition on the C/C composites are prepared to evaluate thermal resistance. Firstly, we perform the basic insulation test by thermal shock at 1350℃ in air on the C/C composite and SiC-coated C/C composite. We also performed the burner tests on the surface of the composites at high temperatures such as 1700 and 2000℃, and the weight change after burner tests are measured. The damages on the surface of C/C composite and SiC-coated composite are observed. As a result, the SiC coating is beneficial to protect the C/C composite from high temperature even though damages such as defoliation, crack and voids are observed during burner test at 2000℃.

• Composites Research
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• v.13 no.2
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• pp.22-29
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• 2000

Although C/C composites have excellent mechanical properties at high temperature, the disadvantage of oxidation in air restricts their applications. Thus a lot of investments have been studied to improve this drawback. In this study, SiC used as a thermal protective coating material possesses almost the same expansion coefficient compared to that of carbon, so SiC was coated on 4D C/C composites by Pack-Cementation process. For SiC-coated C/C composites, optical microscopy observations were performed to estimate the conversion mechanism involved and air oxidation tests were also performed to evaluate the improvement of oxidation resistance. Afterwards the optimum conditions of coating process were estimated from the results of several analysis and tests.

• Composites Research
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• v.12 no.5
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• pp.12-22
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• 1999

Aluminum based metal matrix composites(MMCs) are well known for their high specific strength, stiffness and hardness. They are gaining further importance because of their high wear resistance. In this study wear behavior of $Al/Al_2O_3/C$ hybrid MMCs fabricated by squeeze infiltration method was characterized by the abrasive wear test under various sliding speeds at room and high temperature. Wear resistance of MMCs was improved due to the presence of reinforcements at high sliding speed. Especially wear resistance of carbon hybrid MMCs was superior to other materials because of its solid lubrication of carbon. The friction coefficient of MMCs was not affected by the sliding speed.

• Composites Research
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• v.33 no.6
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• pp.415-420
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• 2020

The interfacial properties in carbon fiber composites, which control the overall mechanical properties of the composites, are very important. Effective interface enhancement work is conducted on the modification of the carbon fiber surface with carbon nanotubes (CNTs). Nonetheless, most surface modifications methods do have their own drawbacks such as high temperatures with a range of 600~1000℃, which should be implemented for CNT growth on carbon fibers that can cause carbon fiber damages affecting deterioration of composites properties. This study includes the use of in-situ interfacial polymerization of polyamide 610/CNT to fabricate the carbon fiber composites. The process is very fast and continuous and can disperse CNTs with random orientation in the interface resulting in enhanced interfacial properties. Scanning electron microscopy was conducted to investigate the CNT dispersion and composites morphology, and the thermal stability of the composites was analyzed via thermogravimetric analysis. In addition, fiber pull-out tests were used to assess interfacial strength between fiber and matrix.

• Journal of the Korean Society of Hazard Mitigation
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• v.1 no.1 s.1
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• pp.127-138
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• 2001

Although Carbon/Carbon Composites(CFRCs) have excellent mechanical properties at high temperature, the disadvantage of combustion in air restricts their applications. Thus a lot of investments have been studied to improve the drawback of CFRCs. In this study, SiC used as a thermal protective coating material possesses almost the same expansion coefficient compared to that of carbon, so SiC was coated on 4D (directional) CFRCs by Pack-Cementation process. For the 4D CFRCs coated with SiC, optical microscopy observations were performed to estimate the coating mechanism involved and TGA tests were also performed to evaluate the improvement of combustion resistance. And their high temperature combustion properties were investigated by the arc torch plasma test. From the results, it is found that the mechanical properties and high temperature combustion properties of the 4D(directional) CFRCs coated with SiC were much better than bare 4D CFRCs.

• Polymer(Korea)
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• v.33 no.6
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• pp.575-580
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• 2009

Carbon fabric-reinforced silicon carbide composites (C/SiC) have attracted a considerable attention for high temperature structural application because of their outstanding oxidation resistance property and thermal shock resistance. In this study, we reported on the preparation of C/SiC composites by the polymer impregnation and pyrolysis (PIP) method. For this, polycarbosilane solution was impregnated into the carbon fabric and then cured by electron beam irradiation under argon atmosphere. Afterwards, the cured composite was pyrolyzed at $1300^{\circ}C$ for 1 h under argon atmosphere to produce the C/SiC composite. The porosity and density of the C/SiC composite were 13.5% and $2.44\;g/cm^3$, respectively, when the impregnation of the carbon fabric with the 30 wt% polycarbosilane solution conducted four times. In addition, in the isothermal experiment at $1500\;^{\circ}C$ in air for 5 h, the 95.9 wt% of the C/SiC composite was remained, indicating that the prepared C/SiC composite has a outstanding oxidation resistance.

• Proceedings of the Materials Research Society of Korea Conference
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• 2003.03a
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• pp.228-228
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• 2003

고강성 탄소섬유는 높은 비강도 및 고 강성 특성 때문에 탄소-탄소 복합재료의 가장 우수한 강화재로 각광을 받고 있다. 이 섬유는 미세 결정립의 높은 이방성을 나타내며, 이러한 높은 흑연화 특성은 기계적, 전기적, 전기적 그리고 화학적 특성 등을 좋게한다. 이러한 모든 방면에서의 우수한 특성 때문에 항공우주 재료분야에 의심 없이 가장 우수한 재료로 고려되고 있다. 이렇게 가벼우면서 고온강도가 요구되는 재료로써 탄소재료가 이용되면서 rocket의 nozzle이나 nosecone으로의 응용에는 고온 산화가 중요한 연구주제로 대두되어 왔다. 탄소재료의 산화반응은 결정구조 인자 및 그 배열에 가장 큰 영향을 받는다고 알려져 있는데, 출발원료 및 제조 조건에 따라 그 구조 및 배열이 현격하게 달라진다. 탄소재료의 구조 해석은 주로 TEM과 XRD를 이용해 왔다. 많은 연구자들은 오래 전부터 탄소재료 연구에 TEM에서 얻은 상이 불확실하고 문제가 있다고 보고하였고, 최근 TEM 장치의 발달과 더불어 실제 구조를 얻기가 가능함을 보여주고 있다 그러나 TEM 시편은 여전히 작고 시편으로부터 얻는 정보는 불과 nm 수준이다. 따라서 일반적으로 TEM으로 얻은 정량적인 정보는 불과 특정한 점에서의 정보이기 때문에 여전히 논란의 소지가 많다. XRD는 탄소재료의 미세구조 해석을 위하여 가장 널리 이용되는 분석기기이다.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.4
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• pp.47-53
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• 2006

In this paper, the thermal insulator structure of a real rocket which is fabricated in a way that laminated composite rings are connected in series is analyzed using 3-dimensional axisymmetric finite element models. Simulation of cowl zone using a real operating conditions provides that the stress distribution in the laminated composite ring is largely influenced by ply-angles, axial dimensions, and boundary conditions. Notably the plylift that is the precursor to the wedge-out occurs in the ring-to-ring bonding region. It is hypothesized that after the plylift the wedge is dropped out due to the shear stresses in the ply-angle direction and axial compressive stresses.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.40 no.11
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• pp.927-933
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• 2016

In a solid propulsion system, the rocket nozzle is exposed to high temperature combustion gas. Hence, choosing an appropriate material that could demonstrate adequate performance at high temperature is important. As advanced materials, carbon/silicon carbide composites (C/SiC) have been studied with the aim of using them for the rocket nozzle throat. However, when compared with typical structural materials, C/SiC composites are relatively weak in terms of both strength and toughness, owing to their quasi-brittle behavior and oxidation at high temperatures. Therefore, it is important to evaluate the thermal and mechanical properties of this material before using it in this application. This study presents an experimental method to investigate the fracture behavior of C/SiC composite material manufactured using liquid silicon infiltration (LSI) method at elevated temperatures. In particular, the effects of major parameters, such as temperature, loading, oxidation conditions, and fiber direction on strength and fracture characteristics were investigated. Fractography analysis of the fractured specimens was performed using an SEM.

• Korean Journal of Materials Research
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• v.3 no.3
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• pp.292-299
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• 1993

In this paper the effects of the length of carbon fiber on the wear properties of carboni carbon composites were investigated. Carbon/carbon composites were fabricated by the liquid impregnation method using the resol-type phenolic resin as a matrix precursor and PAN-based, non-surface treated carbon fiber as a reinforcement. The measured values of the friction coefficient of carbon/carbon composites against AlSl 304 stainless steel ranged from 0.2 to 0.3 under the operating condition used in this study. The effect of the length of carbon fiber on the friction coefficient of carbon/carbon composites were not found. But, it was realized that the wear rate of carbon/carbon composites tends to increase, as the length of carbon fiber increases.