• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 1996.11a
• /
• pp.46-50
• /
• 1996

Die sinking Electrical Discharge Machining(EDM) of TiC/Al$_2$O$_3$Ceramic Matrix Composite(CMC) was conducted for positive and negative polarity according to the change of current and Duty Factor(DF). Also FEM analysis about temperature distribution of workpiece by one spark was executed. Maximum surface roughness( R$_{max}$ ) and SEM photographs of the EDMed surface for different conditions were evaluated. Higher Material Removal Rate(MRR) was obtained for negative polarity than positive one. Better surface morphology was found as the current is decreased, but the MRR was also decreased. From the SEM photographs, the size of melt cavity due to one spark is about 100 to 150${\mu}{\textrm}{m}$ in diameterer

• Journal of the Korean Society for Precision Engineering
• /
• v.14 no.9
• /
• pp.80-89
• /
• 1997

Die sinking electrical discharge machining(EDM) was conducted for ceramic composite of 33 weight percent TiC based on AI$_{2}$O$_{3}$ ceramic matrix according to the change of current and duty factor(DF). Material removal rate(MRR) was increased as the current and the duty factor increased, but better surface mor-pholoty was obtained in the region of lower current and duty factor. From the scanning electron microscopy(SEM) photographs and the energy dispersive X-ray spectroscopy(EDX) of the EDMed surface, EDM trace formed by one discharge spark was analyzed. Although the bending strength after EDM was highly decreased, reliability obtained by weibull analysis was increased twice. The bending strength was recovered or more by barrel polishing after EDM. From the FEM analysis of temperature for one spark, the possible melting region of AI$_{2}$O$_{3}$and TiC was obtained.

• The Korean Journal of Ceramics
• /
• v.5 no.1
• /
• pp.55-72
• /
• 1999

A cheallenge in the aerospace field is to design new composites satisfying specific and sometimes conflicting properties. The key steps are ⅰ)the understanding and the control of the reaction between the reinforcement and the embedding matrix, ⅱ) the achievement of a coherent and robust matrix. The problems encountered to prepare particulate, 1D, 2D and 3D reinforced composites using polymeric are discussed. Emphasis is given to the control of the micro/nanostructure using Raman microspectrometry and depth-sensing microindentation, in order to get information on the micromechanics and fiber structure simultaneously, within ceramic (CMC's) and metal matrix (MMC's) composites.

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 1997.04a
• /
• pp.827-831
• /
• 1997

Conductive veramic matrix composite(CMC) workpiece of TiC 33%/Al /sab 2/O /sab 3/ 66% Y /sab 2/ O /sab 3/ was machined by die sinking electrical discharge machining(EDM) according to different pulse duration and suty factor for reverse polarity of electrode. Material removal rate(MRR) was examined by process under various operating conditions. The surface morphology was evaluated by surface roughness values and scanning electron microscopy(SEM) research. The more MRR was obtained according to increase pulse duration and duty factor. Also the maximum surface roughness(Rmax) of EDMed surface was slightly changed with increased pulse duration and duty factor. The SEM photographs of EDMed surface showed wide recast wide recast distribution region of melting materials in purse duration 0.130(ms) than 0.048(ms).

• Proceedings of the KSME Conference
• /
• 2008.11a
• /
• pp.234-238
• /
• 2008

The efficiency of fiber reinforced CMC(ceramic matrix composite) on the SiC materials have been investigated, in conjunction with the fabrication process by liquid phase sintering and the characterization. LPS-$SiC_f$/SiC composites was studied with the detailed analysis such as the microstructure, sintered density, flexural strength and fracture behavior. The applicability of carbon interfacial layer has been also investigated in the LPS process. Submicron SiC powder with the constant total amount and composition ratio of $Al_2O_3,\;Y_2O_3$ as sintering additives was used in order to promote the performance of the SiC matrix material. LPS-$SiC_f$/SiC composites were fabricated with hot press under the sintering temperature and applied pressure of $1820^{\circ}C$ and 20MPa for 1hr. The typical property of monolithic LPS-SiC materials was compared with LPS-$SiC_f$/SiC composites.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.23 no.2
• /
• pp.68-77
• /
• 2019

C/SiC composites were developed by a liquid silicon infiltration(LSI) method for use as heat-resistant parts of solid and liquid rocket propulsion engines. The heat resistance characteristics according to the composition ratio (carbon / silicon / silicon carbide) were evaluated by specimen test through arc plasma, supersonic torch test. An ablation equation for oxidation reactions was presented. Through the combustion test it was verified that various parts such as nozzle insert, exit cone and combustion chamber heat resistant parts for rocket propulsion can be manufactured and proved high ablation performance and thermal structure performance.

• Steel and Composite Structures
• /
• v.35 no.5
• /
• pp.671-685
• /
• 2020

This manuscript presents impacts of gradation of material functions and axial load functions on critical buckling loads and mode shapes of functionally graded (FG) thin and thick beams by using higher order shear deformation theory, for the first time. Volume fractions of metal and ceramic materials are assumed to be distributed through a beam thickness by both sigmoid law and symmetric power functions. Ceramic-metal-ceramic (CMC) and metal-ceramic-metal (MCM) symmetric distributions are proposed relative to mid-plane of the beam structure. The axial compressive load is depicted by constant, linear, and parabolic continuous functions through the axial direction. The equilibrium governing equations are derived by using Hamilton's principles. Numerical differential quadrature method (DQM) is developed to discretize the spatial domain and covert the governing variable coefficients differential equations and boundary conditions to system of algebraic equations. Algebraic equations are formed as a generalized matrix eigenvalue problem, that will be solved to get eigenvalues (buckling loads) and eigenvectors (mode shapes). The proposed model is verified with respectable published work. Numerical results depict influences of gradation function, gradation parameter, axial load function, slenderness ratio and boundary conditions on critical buckling loads and mode-shapes of FG beam structure. It is found that gradation types have different effects on the critical buckling. The proposed model can be effective in analysis and design of structure beam element subject to distributed axial compressive load, such as, spacecraft, nuclear structure, and naval structure.

• Proceedings of the Korean Vacuum Society Conference
• /
• 2016.02a
• /
• pp.135-135
• /
• 2016

차세대 가스터빈 엔진 및 초음속 항공기 내 고온부의 온도가 증가함에 따라, 기존의 초내열합금 기반 소재를 사용하기 어려워지고 있다. 초고온 세라믹스는 높은 기계적 물성, 화학적 안정성 등 우수한 고온 특성을 가지고 있어 기존의 초고온 소재를 대체 할 수 있는 물질로 부상되고 있다. 하지만 기존의 금속 기반 소재 대비 높은 밀도로 인하여 초고온 세라믹 단일체를 비행체 부품에 적용하기에는 어려움이 있다. 이에 초고온 세라믹스와 탄소섬유를 포함하는 세라믹 복합체(Ceramic Matrix Composite, CMC)를 제작하여 동등한 기계적 물성을 보이면서 무게를 감소시키는 연구들이 진행 중에 있다. 초고온 세라믹스가 함침 된 세라믹 복합체의 경우 우수한 내삭마, 내산화 특성을 보이지만, 장시간 고온에 노출되어 탄소 섬유가 드러나게 되면 급격한 산화로 인해 소재 특성의 열화가 진행되는 단점을 가지고 있다. 따라서, 탄소 섬유가 드러나지 않도록 복합체 표면에 코팅층을 형성하여 세라믹 복합체 모재를 보호하는 방법이 활발히 연구되고 있다. 본 연구에서는 진공 플라즈마 용사 공정을 이용하여 다양한 공정조건 하에서 초고온 세라믹 코팅층을 형성하였다. 수십 마이크론 크기 분포를 갖는 HfC 분말을 Ar 유송 가스를 이용하여 플라즈마 화염 내부로 투입하였다. 플라즈마 화염 가스는 Ar 과 H2를 혼합하여 구성되었으며, 분위기 가스로는 N2를 사용하였다. 코팅에 사용된 모재로는 ZrB2 단일체와 SiC가 미량 포함된 HfC 단일체를 사용하였다. 다양한 공정 조건하에서 형성된 HfC 코팅층의 두께, 미세 조직구조를 SEM을 이용하여 관찰하였으며, XRD를 이용하여 형성된 HfC 코팅층의 결정구조를 분석하였다.

• Nuclear Engineering and Technology
• /
• v.45 no.6
• /
• pp.811-820
• /
• 2013

SiC has been under investigation as a potential cladding for LWR fuel, due to its high melting point and drastically reduced chemical reactivity with liquid water, and steam at high temperatures. As SiC is a brittle material its behavior during the reflood phase of a Loss of Coolant Accident (LOCA) is another important aspect of SiC that must be examined as part of the feasibility assessment for its application to LWR fuel rods. In this study, an experimental assessment of thermal shock performance of a monolithic alpha phase SiC tube was conducted by quenching the material from high temperature (up to $1200^{\circ}C$) into room temperature water. Post-quenching assessment was carried out by a Scanning Electron Microscopy (SEM) image analysis to characterize fractures in the material. This paper assesses the effects of pre-existing pores on SiC cladding brittle fracture and crack development/propagation during the reflood phase. Proper extension of these guidelines to an SiC/SiC ceramic matrix composite (CMC) cladding design is discussed.

• Composites Research
• /
• v.32 no.3
• /
• pp.148-157
• /
• 2019

In this study, $C_f/SiC$, $SiC_f/SiC$ and $C_f-SiC_f/SiC$ ceramic composites reinforcing carbon fiber, SiC fiber and hybrid fiber were fabricated by hybrid TGCVI and PIP process. After the thermal shock cycle, 3-point bending and Oxy-Acetylene torch test, their mechanical behavior, oxidation and erosion resistance were evaluated. The $C_f/SiC$ composite showed a decrease in mechanical property along with increasing temperature, a pseudo-ductile fracture mode and a large quantity of erosion. The $SiC_f/SiC$ composite exhibited stronger mechanical property and lower erosion rate compared to the $C_f/SiC$, but brittle fracture mode. On the other hand, hybrid type of $C_f-SiC_f/SiC$ composite gave the best mechanical property, more ductile failure mode than the $SiC_f/SiC$, and lower erosion rate than the $C_f/SiC$. During the Oxy-Acetylene torch test, the $SiO_2$ formed by reaction of the SiC matrix with oxygen prevented further oxidation or erosion of the fibers for $C_f-SiC_f/SiC$ and $SiC_f/SiC$ composites particularly. In conclusion, if a hybrid composite with low porosity is prepared, this material is expected to have high applicability as a high temperature thermo-structural composite under high temperature oxidation atmosphere by improving low mechanical property due to the oxidation of $C_f/SiC$ and brittle fracture mode of $SiC_f/SiC$ composite.