• Composites Research
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• v.33 no.4
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• pp.205-212
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• 2020

In this study, HfC was coated on two types of carbon/carbon composites coated with SiC by vacuum plasma spraying(VPS). The experiment was performed using a plasma wind tunnel with heat flux of 5.06 MW/㎡ for 120 s heat flux before and after the coating. The mass ablation rate was calculated through the mass change before and after the test, and the length change was measured by using calipers and high speed camera. The oxidation/ablation behavior were observed by FE-SEM with EDS analysis of the specimens cross section. The plasma wind tunnel test results showed that the coated specimens had low weight loss and length change, and high oxidation/ablation resistance. However, two types of the specimens tested under the same conditions were different in the ablation behavior and ablation rate, and it was evaluated that the cylindrical type had higher oxidation/ablation resistance.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.185-188
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• 2007

The main objective of this research effort was to develope the performance of C/SiC composites manufactured by LSI (Liquid Silicon Infiltration) method for solid and liquid rocket propulsion system and ensure the performance analysis technique. The various carbon preform were manufactured by filament winding, tape rolling, involute layup and stack molding process. For the best performance of thermal and mechanical properties, many process conditions were tested and selected by varying preform, the content of SiC, temperature, impregnation resin and chemical vapour reaction. In conclusion, the high performance and reliability of C/SiC composite were proved for solid and liquid rocket propulsion system. And the performance analysis technique related to mathematical ablation model was originated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.433-438
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• 2009

The main objective of this research effort is to develop the performance of C/SiC composites manufactured by LSI (Liquid Silicon Infiltration) method for solid and liquid rocket propulsion system and ensure the performance analysis technique. The high performance and reliability of C/SiC composite are proved for solid and liquid rocket propulsion system. And the performance analysis technique related to mathematical ablation model is originated.

• 한국신재생에너지학회:학술대회논문집
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• 2010.06a
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• pp.100.1-100.1
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• 2010

고효율 실리콘 양자점 태양전지를 제작하기 위해 Si과 C target을 co-sputtering 방식으로 제조한 SiC matrix를 열처리하여 박막 내에 Si nanocrystal들을 생성하였다. Si nanocrystal의 특성은 다양한 요인에 영향을 받는 데 barrier 물질인 SiC matrix가 가장 큰 영향을 준다. SiC는 900도 이상에서 열처리하는 동안 Si과 C과 SiC으로 재배열 혹은 재결합하는 데 이 때 가장 작은 carbon이 빠르게 diffusion하는 현상에 의해 Si nanocrystal의 성장과 특성에 영향을 주게 된다. 이 현상을 연구하기 위해 stoichiometric SiC/Si-rich SiC/stoichiometric SiC의 3층 구조로 시료를 제작하여 이를 SIMS의 depth profiling을 통하여 열처리 전보다 열처리 후에 Si-rich SiC layer내에 carbon이 약 2~3%정도 증가한 것으로 carbon이 diffusion된 것을 확인하였다. 이 시료를 UV-VIS-NIR spectroscopy, Raman, GIXRD 등의 다양한 측정을 통하여 carbon diffusion에 의한 Si nanocrystal의 특성변화를 연구하였다.

• Korean Chemical Engineering Research
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• v.61 no.1
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• pp.32-38
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• 2023

In this study, the electrochemical properties of dopamine coated silicon/silicon carbide/carbon(Si/SiC/C) composite materials were investigated to improve cycle stability and rate performance of silicon-based anode active material for lithium-ion batteries. After synthesizing CTAB/SiO₂ using the Stöber method, the Si/SiC composites were prepared through the magnesium thermal reduction method with NaCl as heat absorbent. Then, carbon coated Si/SiC anode materials were synthesized through polymerization of dopamine. The physical properties of the prepared Si/SiC/C anode materials were analyzed by SEM, TEM, XRD and BET. Also the electrochemical performance were investigated by cycle stability, rate performance, cyclic voltammetry and EIS test of lithium-ion batteries in 1 M LiPF₆ (EC: DEC = 1:1 vol%) electrolyte. The prepared 1-Si/SiC showed a discharge capacity of 633 mAh/g and 1-Si/SiC/C had a discharge capacity of 877 mAh/g at 0.1 C after 100 cycles. Therefore, it was confirmed that cycle stability was improved through dopamine coating. In addition, the anode materials were obtain a high capacity of 576 mAh/g at 5 C and a capacity recovery of 99.9% at 0.1 C/0.1 C.

• Proceedings of the Korean Institute of Surface Engineering Conference
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• 2018.06a
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• pp.113-113
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• 2018

환경 친화형 전기자동차, 하이브리드 자동차, 전철 등에서는 고내압 및 소형으로 전력손실을 감소시킬 수 있는 파워 디바이스가 필수이다. 최근, 실리콘 카바이드(SiC, silcon carbide)는 기존 실리콘(Si)보다 스위칭 손실의 저감 및 고온환경에서의 동작 특성이 우수하여, 차세대 저 손실 전력반도체 재료로서 기대를 받고 있다. 용액 성장 법에서 고품질 SiC 결정을 만들 수 있다. 그러나 늦은 성장 속도 때문에 SiC의 양산을 어렵게 하고 있다. 현재까지 성장 속도 향상을 위한 Si용매에 Cr을 첨가하여 탄소 용해도를 높이는 방법이 사용되고 안정된 성장을 위한 Si-Cr용매에 Al를 첨가하는 등 다양한 금속을 첨가하는 방법이 이용되고 있다. 선행 연구에서는 다양한 용매인 탄소 용해도를 실측하고 특히 큰 탄소 용해도를 보인 것은 Co이었다. 본 연구에서는 $Si_{0.6}Cr_{0.4}$원료와 Co를 첨가한 $Si_{0.56}Cr_{0.4}Co_{0.04}$의 용매에 의한 SiC용액 성장을 실시하고 결정 성장 속도 및 표면 상태의 변화를 검토했다. on-axis 4H-SiC(000-1)을 사용한 Top-seeded solution growth(TSSG)법과 원자 비율로 $Si_{0.6}Cr_{0.4}$와 $Si_{0.56}Cr_{0.4}Co_{0.04}$의 용매를 이용하여 SiC 용액 성장을 실시했다. Ar가스에서 저항 가열로 내를 치환 후에 $1800^{\circ}C$까지 가열하고 종자화 후에 120분간 유지하고 결정 성장을 실시했다. 냉각 후에 성장의 표면에 남은 용매를 $HF+HNO_3$에서 제거했다. 광학 현미경을 이용하여 결정면과 두께를 관찰 측정했다. Co를 첨가한 $Si_{0.56}Cr_{0.4}Co_{0.04}$의 경우는 $Si_{0.6}Cr_{0.4}$의 경우보다 결정 성장 속도가 향상됐다. 또한 $Si_{0.6}Cr_{0.4}$보다 step-flow의 성장을 나타낸 결정의 표면이 전반적으로 관찰됐으며 안정된 결정성장을 나타냈다. 본 연구에서 실시한 연구 방법과 결과는 고품질 및 고속의 SiC 용액성장을 위한 매우 유용한 자료로 활용 될 수 있을 것으로 판단한다.

• Korean Journal of Materials Research
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• v.27 no.9
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• pp.471-476
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• 2017

In order to improve the high temperature oxidation resistance and lifespan of mat type porous carbon insulation, SiC was coated on carbon insulation by solution coating using polycarbosilane solution, curing in an oxidizing atmosphere at $200^{\circ}C$, and pyrolysis at temperatures up to $1200^{\circ}C$. The SiOC phase formed during the pyrolysis process was converted into SiC crystals as the heat treatment temperature increased, and a SiC coating with a thickness of 10-15 nm was formed at $1600^{\circ}C$. The SiC coated specimen showed a weight reduction of 8.6 % when it was kept in an atmospheric environment of $700^{\circ}C$ for 1 hour. On the other hand, the thermal conductivity was 0.17 W/mK, and no difference between states before and after coating was observed at all.

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

• Korean Journal of Optics and Photonics
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• v.33 no.5
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• pp.218-229
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• 2022

We have investigated reliable inspection methods for finding the defects generated during the manufacturing process of lightweight, large-aperture satellite telescope mirrors using silicon carbide, and we have measured the basic physical properties of the mirrors. We applied the advanced ceramic material (ACM) method, a combined method using liquid-silicon penetration sintering and chemical vapor deposition for the carbon molded body, to manufacture four SiC mirrors of different sizes and shapes. We have provided the defect standards for the reflectors systematically by classifying the defects according to the size and shape of the mirrors, and have suggested effective nondestructive methods for mirror surface inspection and internal defect detection. In addition, we have analyzed the measurements of 14 physical parameters (including density, modulus of elasticity, specific heat, and heat-transfer coefficient) that are required to design the mirrors and to predict the mechanical and thermal stability of the final products. In particular, we have studied the detailed measurement methods and results for the elastic modulus, thermal expansion coefficient, and flexural strength to improve the reliability of mechanical property tests.

• Resources Recycling
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• v.2 no.4
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• pp.17-22
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• 1993

SiC whiskers were synthesized from rice hulls and activated carbon by carbothermal reduction method. The effects of gases and various additives were studied. Carbothermal reduction to produce SiC whiskers was conducted at $1450^{\circ}C$ and the synthesized SiC whiskers were examined using SEM and XRD. The length of whiskers is increased with the increases of $H_2$concentration and total gas flows. The most favorable form of SiC whiskers couble be obtained in the following experimental conditins : Ar : $H_2$=300:45(ml/min), $SiO_2$(inrice hulls): $CaF_2$=1:0.5:0.5(mole ratio) and the addition of Ni flakes ($1{\times}1$mm).