• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.4
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• pp.61-66
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• 2014

Graphite is commonly used for rocket nozzle. The purpose of the present study is to evaluate compression fracture behavior of ATJ graphite. Uniaxial compression test is conducted in accordance with ASTM C 695 in the range of R.T to $900^{\circ}C$. The size effects of specimen on the compressive strength and fracture behavior were investigated. Two types of cylindrical specimen, i.e., where the diameter to length ratio is 1:2 (ASTM C 695 specimen) or 1:1, were tested at room temperature.

• Laser Solutions
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• v.6 no.1
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• pp.17-24
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• 2003

The purpose of this study is to evaluate thermal shock resistance and thermal shock fracture toughness for ATJ graphite. Thermal shock resistance and thermal shock fracture toughness of ATJ graphite are evaluated by using CO$_2$ laser irradiation technique. The laser heat source is irradiated at the center of specimens. Temperature distribution on the specimen surface is measured using the thermocouples of type K and C. SEM and radiographic images are used to observe the cracks which are formed at the thermal shock specimens.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.38 no.12
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• pp.1435-1440
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• 2014

The effects of the specimen size and temperature on the compressive strength of ATJ graphite were investigated. Compressive tests were conducted in accordance with ASTM C 965 at room temperature, $700^{\circ}C$ and $900^{\circ}C$. Three types of cylindrical specimen at room temperature were used in uniaxial tests, where the diameter-to - length ratios were one to two for the ASTM standard specimen, one to one for the Type I specimen, and one to 0.5 for the Type II specimen. Two kinds of cylindrical specimens, with and without antioxidant coating, were tested at elevated temperature. The Compressive strength of the expanded specimens(Type I, II) were slightly higher than that of standard specimen at room temperature. The compressive strength of a specimen with antioxidant coating increased as the temperature increased to $900^{\circ}C$. In contrast, that of the non-coated specimen decreases sharply due to the oxidation of the specimen.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.39 no.11
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• pp.1091-1097
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• 2015

Graphite material has been widely used for making the rocket nozzle throat because of its excellent thermal properties. However, when compared with typical structural materials, graphite is relatively weak with respect to both strength and toughness, owing to its quasi-brittle behavior, and gets oxidized at $450^{\circ}C$. Therefore, it is important to evaluate the thermal and mechanical properties of this material for using it in structural applications. This study presents an experimental method to investigate the fracture behavior of ATJ graphite at elevated temperatures. In particular, the effects of major parameters such as temperature, loading, and oxidation conditions on strength and fracture characteristics were investigated. Uniaxial compression and tension tests were conducted in accordance with the ASTM standard at room temperature, $500^{\circ}C$, and $1,000^{\circ}C$. Fractography analysis of the fractured specimens was carried out using an SEM.

• Proceedings of the KWS Conference
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• 1995.04a
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• pp.80-83
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• 1995

• Proceedings of the Korean Society of Laser Processing Conference
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• 2002.11a
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• pp.109-113
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• 2002

• Proceedings of the Korean Vacuum Society Conference
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• 1999.07a
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• pp.41-41
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• 1999

핵융합 장치의 플라즈마 운행동안 토카막 내벽에 도달하는 온도는 최저 $600^{\circ}C$ 이상이다. 또한 플라즈마 자체와 사용자(User)들의 시료로부터 방출되는 입자들에 의한 내벽 충격(damage)은 장기간의 안정적인 운행 및 연구에 심각한 영향을 미친다. 이러한 이유로 토카막 제작시 내벽 보호재의 선정은 매우 높은 비중을 차지한다. Graphite는 높은 융점과 가공의 용이성으로 토카막 내벽의 보호재로 선호되는 물질이다. 그러나 토카막 용기(vessel)에 사용되는 스테인레스 스틸(AISI 316LN)보다 약 50배 이상의 기체 방출율(outgassing rate)을 가진다. 그러므로 장착 이전의 초기 청정화 과정이 매우 중요하며, 특히 400m2의 약 2톤(2000kg)의 graphite가 사용되므로 대량 처리를 할 수 있는 방법의 선정도 함께 개발되어야 한다. 본 연구팀에서는 처음 10개 회사의 시제품을 검토한 후, 최종 2개 회사의 4가지 종류의 시료를 선정하였다. 선정된 시료는 Union Carbide의 ATJ와 Toyo Tanso의 IG-110, IG-43, Ig-430이다. 시료는 비절삭유(oil-free) 가공에 의해 80$\times$2$\times$3 (mm)의 크기로 제작되었고 에탄올과 메탄올 용액에서 초음파 세척되었다. 건조된 시료는 TDS(Thermal Desorption Spectroscopy) 장치에 장착되어 세 단계의 실험을 하였다. 처음은 승온(상온 ~100$0^{\circ}C$)에 의한 방출 기체의 성분 분석, 두 번째는 장기간 (2주) 대기 노출 후 주요 방출 기체의 온도에 따른 변화, 마지막으로는 특정 기체에서의 장기간 보관후, 주요 방출 기체의 온도에 따른 변화를 조사하였다. 다음 그림 1은 본 연구에서 사용된 TDS 장치의 개략도이고 그림 2는 TDS 장치에 장착 직 후와 대기 중 노출된 시료들의 온도증가에 따른 총 압력의 변화이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.417-420
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• 2009

The purpose of the present study is to evaluate high temperature fracture toughness through the experimental and analytical method. The analysis method is proposed to simulate the fracture toughness of high temperatures. Load-COD curves of compact test specimen acquired by finite element method analysis using hypo elastic model are simulated to determine the crack initiation load on high temperatures. The results of experimental work are in accord with analysis in thermal shock test.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.30 no.2
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• pp.119-125
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• 2017

Ablative material in a rocket nozzle is exposed to high temperature combustion gas, thus undergoes complicated thermal/chemical change in terms of chemical destruction of surface and thermal decomposition of inner material. Therefore, method for conjugate analysis of thermal response inside carbon/phenolic material including rocket nozzle flow, surface chemical reaction and thermal decomposition is developed in this research. CFD is used to simulate flow field inside nozzle and conduction in the ablative material. A change in material density and a heat absorption caused by the thermal decomposition is considered in solid energy equation. And algebraic equation under boundary layer assumption is used to deduce reaction rate on the surface and resulting destruction of the surface. In order to test the developed method, small rocket nozzle is solved numerically. Although the ablation of nozzle throat is deduced to be higher than the experiment, shape change and temperature distribution inside material is well predicted. Error in temperature with experimental results in rapid heating region is found to be within 100 K.