• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.190-200
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• 2007

A pyrogen type igniter was designed to satisfy the requirements of KSLV-I Kick Motor system. To insure the reliability of the igniter before the production of the flight model, we have been performed the structure, environmental, combustion tests. The hydraulic test was carried out to confirm the strength of the components of the igniter. The shock and vibration tests were considered to check whether the igniter operates normally under the severe environmental condition. The combustion tests were also performed to understand the ignition characteristics with the variation of initial condition. Finally, we confirmed that the igniter could provide the acceptable energy to ignite the propellant of kick motor at the ground test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.130-133
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• 2009

The sequence of the propellant supply is very important for the reliable and safe operation of a LRE combustion test. So combustion performance tests were performed to find an optimum test sequence by changing supply time of propellants and purge gas in the moment of ignition and extinction. The liquid rocket engine consisted of a catalytic ignitor and six swirl-coaxial injectors which used hydrogen peroxide and kerosene. Conclusively, an optimum sequence was found for stable combustion in the moment of ignition and extinction.

• Fire Science and Engineering
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• v.24 no.1
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• pp.116-121
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• 2010

The present study has been performed to investigate the ignition characteristics of a n-dodecane fuel droplet on the hot surface. Simplified bench scale test setup was built to examine the effect of air flow on the ignition temperature of fuel droplet. IR pyrometric sensor was used to measure the surface temperature, the measured temperature using IR pyrometer was directly compared with k-type thermocouple. The ignition of n-dodecane fuel droplet was divided into two stage - cool flame and hot flame - with the air flow rate except the case of air flow rate 3.0 lpm. The ignition temperature and probability was greatly affected by the air flow rate and the MHSIT of the present study was about $300^{\circ}C$ for air flow rate of 0.5 lpm.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.5
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• pp.393-401
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• 2018

Reliability prediction of an electronic arm fire device(EAFD) was studied which is applied to prevent accidental ignition in a solid rocket motor. For predicting the reliability, the main components of the EAFD were first defined(Control unit, LEEFI, TBI) and the operating principle of each component was analyzed. Performance modeling of each part is established using selected input variables through system analysis. When complex analysis is required, we approximated it with polynomial equation using response surface method. Monte-Carlo simulation is applied to performance modeling to estimate the design reliability.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.62-63
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• 2002

램젯 엔진을 장착한 미사일은 기존의 터보젯 이나 터보팬 엔진에 비해 압축기와 터빈과 같은 엔진 구성품이 없어 무게가 가볍고 초음속에서 저항도 적으며 고속의 비행영역에서 연료효율과 생존성능이 뛰어나기 때문에 차세대 미사일 추진 시스템으로서 세계 여러 국가에서 개발 및 운용이 이루어지고 있다. 하지만 램젯 엔진은 충분한 램 효과를 얻어야 초기 점화가 가능하기 때문에 현재 개발되고 있는 대부분의 시스템은 최초 발사시 로켓 부스터에 의해 가속하고 로켓연료를 모두 소모하고난 후에 흡입구가 개방되어 램젯 엔진이 점화하는 방식을 취하고 있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.750-755
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• 2011

The ignition characteristics of liquid rocket engine thrust chambers which have been developed by domestic technology were analyzed. Analysis results showed that low frequency fluctuation appeared in a partial ignition range according to different temperature profiles and vaporous state in the oxidizer manifold with startup sequences. This low frequency fluctuation wasn't developed as a malfunction factor, but this fluctuation is thought to be taken a continuous concern considering interfaces with engine system and launch vehicle.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.6
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• pp.73-78
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• 2012

The ignition characteristics of liquid rocket engine thrust chambers which have been developed by domestic technology were analyzed through hot-firing tests. Thrust chambers used in hot-firing tests have different characteristics in terms of the injector for ignition, film cooling method and the position of the oxidizer inlet. Also, these thrust chambers used their respective startup sequences. Analysis results showed that according to temperature profiles of the oxidizer manifold, low frequency fluctuation was appeared in ignition area. This low frequency fluctuation didn't give rise to violent malfunction of the thrust chamber, but the continuous observation as a concern parameter in the side of interfaces with engine system and launch vehicle should be demanded.

• Korean Chemical Engineering Research
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• v.57 no.5
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• pp.620-627
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• 2019

In this study, ignition delay characteristics of various bio aviation fuels (Bio-ADD, Bio-6308, Bio-7720) produced by HEFA process using different raw materials were compared and analyzed. In order to confirm the feasibility of applying bio aviation fuel to actual system, ignition delay characteristics of petroleum-based aviation fuel (Jet A-1) and blended aviation fuel (50:50, v:v) also analyzed. Ignition delay time of each aviation fuel was measured by using CRU, surface tension measurement and GC/MS and GC/FID analysis were performed to interpret the results. As a result, ignition delay time of Jet A-1 was the longest at all temperature because it contains aromatic compounds about 22.8%. The aromatic compounds can produce benzyl radical which is thermally stable and has low reactivity with oxygen during decomposition process. In the case of bio aviation fuels, ignition delay times were measured similarly because the ratio of n-paraffin/iso-paraffin constituting each aviation fuel is similar (about 0.12) and the composition ratio of cycloparaffin also has no difference. In addition, ignition delay times of blended aviation fuels (50:50, v:v) were measured close to the mean value those of each fuel so it was confirmed that it can be applied without any changing or improving of existing system.

• The Transactions of the Korea Information Processing Society
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• v.5 no.7
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• pp.1896-1907
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• 1998

확장된 마크흐름선도(EMFG: Extednded Mark Flow Graph)는 기존의 MFG를 개선한 그래프로서, 회로변수식에 의해 실제회로로 쉽게 구현가능하므로 이산제어시스템의 모델링과 설계 및 구현의 강력한 도구로 사용될 수 있다. 본 논문은 EMFG의 트랜지션들이 점화하는 과정 및 트랜지션들이 점화완료하였을 때 각 박스들의 마크수 변화를 부울함수식과 벡터를 사용하여 표현하였다. 또한 시스템의 상태변화를 쉽게 판단할 수 있게 하는 EMFG의 동작알고리듬을 제안하였으며, 제안된 알고리듬은 3-비트 증가계수기를 설계한 EMFG와 시간트랜지션이 포함된 가상의 EMFG에서 잘 수행되었다. EMFG의 동작이 부울함수로 해석가능해짐으로 인해 시스템의 분석 및 설계가 용이하며 컴퓨터를 이용한 자동화된 시스템의 분석과 설계가 가능하다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.51-54
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• 2010

Physical characteristics of liquid and gaseous oxygen and the detailed ignition characteristics of oxygen system were introduced. Compatible and non-compatible materials for oxygen were discussed. To ensure the safety operation of the oxygen system, one of the most important point, cleaning, was reviewed. To design the gaseous and liquid oxygen system, key points were introduced. To safe operation, the operating procedure and considerations were introduced.