• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.3
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• pp.71-77
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• 2016

Characteristic of thermal reaction of Kevlar/EPDM internal insulator used in a solid rocket motor chamber was investigated at 1,030 psi, 35.86 s and 1,406 psi, 36.63 s. Surface status after test was similar each other and thermal destruction depth was 4.10 mm and 4.18 mm, respectively. Kinetic constant ${\xi}$, ${\zeta}$ and thermal destruction velocity $V_{TD}$ were also similar. It was concluded that characteristics of thermal reaction of Kevlar/EPDM internal insulator were not affected by change of chamber pressure.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.85-91
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• 2011

We developed carbon fabric/EPDM chamber insulation in order to protect motor case with high intensity gas flow. Six-inch simulation motor connected with extension tube was designed to test ablation characteristic of insulation. High intensity gas flow was induced by FRP disc with hole between motor and extension tube. After ground test, ablation depth of carbon fabric/EPDM insulation was decreased compared to another insulations after ground static test.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.6
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• pp.59-71
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• 2019

The numerical analysis of ablative thermal protection systems (TPS) for solid rockets has been carried out with various in-house codes since the 1960s. However, the application scope of commercial codes has been expanded by adding subroutines and user-defined functions (UDF) to codes such as Fluent, Marc, and ABAQUS. In the past, the flow, thermal response and structural analysis of TPS have been performed using separate approaches. Recently, research has been conducted to interrelate them. In this paper, the thermal response characteristics of thermal protection materials, the in-house codes for thermal response analysis, and the research trends of flow-thermal-structure analysis of TPS using commercial codes were reviewed.

• Proceedings of the KIEE Conference
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• 2015.07a
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• pp.1184-1184
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• 2015

현재 XLPE 절연 케이블의 상시 운전 온도는 $90^{\circ}C$나 개발된 고내열성 절연재료의 상시운전온도는 $110^{\circ}C$로 향상되었다. 개발된 고내열성 절연재료는 XLPE 절연 케이블의 상시 운전온도($90^{\circ}C$)와 비상시운전온도($110^{\circ}C$), 고내열성 절연재료의 상시운전온도($110{\circ}C$), 비상시 운전온도($130{\circ}C$)을 바탕으로 하여 열 열화 온도와 기간이 설정되었다. 열 열화는 자연순환 건조기에서 설정된 온도와 기간 동안 수행되었고, 열 열화된 고내열성 절연재료는 Mckewon전극을 이용하여 AC파괴 시험이 진행 되었다. 파괴시험데이터는 와이블 분포함수를 이용하여 통계적으로 분석되었다.

• 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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• 2008.11a
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• pp.67-71
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• 2008

Rocket nozzle components and thrusters for next-generation solid rocket with variable thrust, and small uncooled liquid rocket thrusters are required to withstand ultra-high temperature upto $2500^{\circ}C$. In this survey, the operationg environments are investigated with the suggeations of proper materials and their fabrication methods. Especially, It is suggested that Rhenium and other competative matrials are exploited to $2500^{\circ}C$ hot components, and thus needed to be developed.

• 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.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.1
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• pp.108-115
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• 2019

The thermal response of elastomeric insulators used as protection against high-temperature and high-pressure combustion gases varies depending on their composition and thermal environment conditions. In this paper, the thermal response characteristics of elastomeric insulators in different mixing environments were compared. Tests to determine thermal protection performance were carried out using a thermal protection rubber evaluation motor(TPREM), combustion gas velocities of 20 m/s and 100 m/s were tested at a chamber pressure of 1,000 psig. The pressure time curve of the chamber, the temperature time curve of the internal materials, the residual thickness and the thermal destruction depth of the test specimens were obtained. The results showed that the thermal protection performance of elastomeric insulators in different mixing environments was similar.

• 전기의세계
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• v.35 no.4
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• pp.254-258
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• 1986

최근 고분자재료의 눈부신 발전은 전기기기의 절연에도 많은 향상을 가져왔다. 전기기기의 절연재료로는 기계적, 전기적, 화학적 성능이 우수한 합성수지재료가 많이 쓰이고 있다. 전기절연재료를 대별하여 보면 박막재료와 함침재료로 나눌 수 있으며, 박막재료에는 운모, 실리콘고무, 폴리아미드필름, 폴리아미드클로즈 등이 있으며, 바니쉬류에는 내열성이 우수한 실리콘계바니쉬와 무용제함침재료가 많이 사용된다. 전기기기의 기본 구성재료이며 기기의 성능 향상과 소형화, 경량화에 중요한 인자로 작용하는 전기절연재료인 박막재료와 함침재료의 조화로 구성되는 절연시스템의 열열화와 내열수명에 영향을 미치는 절연의 신뢰성에 대하여 알아본다.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2010.06a
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• pp.275-275
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• 2010

나노하이브리드 방법으로 제조된 변성 폴리이드계 나노하이브리드 절연코팅의 표면 내열특성을 비교 분석하였다. 최근 절연코팅의 사용환경이 열적내구성을 높게 요구하는 경향이 크다. 따라서 이러한 환경에 맞는 절연성과 열적내구성을 구현하기 위해서는 열적내구성이 우수한 세라믹 일자를 수지에 분산시켜 그 성능을 개선할 필요가 있다. 본 논문에서는 나노 하이브리드 방법으로 제조된 변성 폴리이드계 나노하이브리드 절연코팅의 표면 내열특성을 비교 분석하였다.