• Journal of the Korean Institute of Telematics and Electronics
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• v.13 no.2
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• pp.5-13
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• 1976

An analytical and experimental design procedure is described for the Capacitor Discharge Ignition (CDI) System with a view to fuel saving ann reduction of gas exhaustion and maintenance need. Specifically, the input and output voltage and current of a given ignition coil were calculated by using a simplified circuit model for the discharging system. The results were compared with the experimental results, from which ratings of the charging capacitor, the SCR and the diodes and the required output valtage of the DC.DC converter were determined so as to satisfy the optimum ignition conditions. Protection circuits for excessive dv/dt and di/dt for the SCR were also analyzed and the results were compared with the observed results, which facilitate selection of the SCR and design of the protection circuit and the trigger circuit. Also, design of the DC.DC converter was simplified based on the analysis and experimental results of the behavior of the converter, An experimental, yet practical CDI system was built, which showed satisfactory performance in the laboratory and field tests. The results were also reported.

• Journal of Advanced Marine Engineering and Technology
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• v.35 no.6
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• pp.779-785
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• 2011

Prediction of the transient pressure variations and performance parameters has been carried out for an SI engine using one of commercial software, GT-POWER. Various models were applied for the calculation of properties of the plenum chamber, exhaust manifold and catalytic convertor which are very important components included in the intake and exhaust systems.

• Transactions of the Korean Society of Automotive Engineers
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• v.16 no.4
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• pp.1-7
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• 2008

Recent trends of development in small size gasoline engines are both to have higher compression ratio for the purpose of improved fuel consumption and to advance spark timing up to DBL in a low to mid engine speed region for a good acceleration performance of vehicles. However, there occurs the deviation of corrected engine torque results during engine performance test on dynamometer because test conditions influence the onset of knock. Therefore, this research shows the test deviation of corrected engine torque decreases when knock correction rate is used.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.213-216
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• 2008

U. S. and NATO allies have recently increased their emphasis on reducing the hazards of tactical munitions that contain energetic materials and actively started many investigations on Insensitive munitions(IM) of missile propulsion. All subcomponents of rocket motor should be properly designed and understood to increase IM properties. Insensitive propellant, motor case, ignitor and mitigation devices are important components of IM technologies of rocket motors.

• Transactions of the Korean hydrogen and new energy society
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• v.15 no.2
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• pp.129-136
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• 2004

환경문제와 석유자원의 고갈이 많은 연구자들을 기존 탄화수소연료를 대체할수 있는 재생 가능한 연료를 구하는데 많은 노력을 기울이고 있다. 수소연료는 유해배기물질이 없는 연소와 또한 연소후에 재생 가능한 물성분만 배출하는 속성으로 미래의 청정에너지로 각광을 받고 있다. 이러한 이유로 수소연료는 수송기계의 연료로도 주목을 받고 있다. 따라서 수소연료기관 개발은 21세기에도 지속적으로 진행될 것이다. 이에대한 초기연구로 기체 LPG 연료가 아닌 액체 LPG 연료를 흡기관에 분사하여 기화된 LPG 연료를 엔진으로 흡입하는 LPi엔진에 수소연료를 과급하여 엔진에 성능을 연구하고자 하였다.

• Transactions of the Korean Society of Automotive Engineers
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• v.2 no.4
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• pp.72-79
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• 1994

In an automotive spark ignition, it is important to form the proper mixture(air/fuel) on each driving condition for developing the stabilizing combustion and exhaust characteristics. Since most of supply fuel is attached on the inside wall of the intake manifold for unadequate atomization by fuel injection system, it brings a bad effect on combustion and exhaust caused by nonuniformity of fuel distribution to each cylinder and mixture variation. Also it affects engine performance variation and causes noises and vibration. In this study, we verified the effect of the mixture variation which is caused by fuel liquid film in an intake manifold on combustion characteristics and engine performance.

• Proceedings of the KAIS Fall Conference
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• 2010.05b
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• pp.1000-1003
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• 2010

기존 Non-Road 가솔린 불꽃점화 소형엔진의 경우 대부분이 캬브레이터 연료 공급 방식으로 연비 및 배기가스 성분이 매우 열악한 실정이다. 본 연구에서는 이러한 단점을 극복하고 배기규제에 대응하기위하여 전자제어식 연료분사방식으로 엔진을 변경하고, 관련핵심 부품의 설계 및 개발을 수행하였다. 전자제어식 소형엔진에 적합한 인젝터, 연료펌프를 선정하였으며 연료레일은 새로이 설계하여 장착하였다. 최적의 인젝터, 연료펌프 및 흡기포트를 선정하기위해 각각의 핵심 부품에 대한 성능개발을 수행하였다. 제작된 소형엔진은 엔진성능 개발을 통하여 연비 및 배기가스를 개발할 예정이다.

• 한국연소학회:학술대회논문집
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• 2003.12a
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• pp.125-130
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• 2003

본 논문에서는 액체로켓엔진에서 터보펌프의 160kW급 터빈을 구동하고, 액체산소와 케로신을 추진제로 사용하는 가스발생기의 설계점 연소성능시험 결과에 대해 논의하였다. 충돌형 F-O-F 인젝터, 물냉각 채널을 가진 연소실, torch ignitor, turbulence ring 그리고 측정 링을 갖는 가스발생기에 대해 기술하였고, 점화, 연소, 종료 등의 시험 cyclogram에 대해 언급하였다. 설계점에서의 연소시험 및 turbulence ring 장착여부, 연소실 길이 변화에 따른 연소시험의 결과들에 대해 기술하였다. 연소시험 결과 가스발생기는 설계점에서 안정된 작동성을 보여주었고, 연소압력 및 온도 등의 성능이 예측치에 근접하는 결과를 보여 주었다. Turbulence ring은 출구에서의 가스온도를 균일하게 분포시켜 효과적인 혼합 장치임을 보여 주었고, 4-6msec 정도에서의 잔류시간에서는 연소효율의 차이가 크지 않음을 알 수 있었다. 가스발생기 출구에서의 온도는 공급되는 추진제의 O/F ratio에 따라 매우 민감하게 반응함을 알 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.8
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• pp.111-121
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• 2005

A 100kW class gas turbine combustor was developed and tested for PPU(Primary Power Unit) of ground vehicle. The combustor which employed annular-reverse type and pressure swirl atomizer was designed through 1-D analysis, 3-D thermal flow analysis and combustor performance was experimentally investigated on the combustor test rig. The test result was satisfactory. The developed combustor was also tested for environmental and endurance specification under engine adopted conditions and the application of a state-of-the-art gas turbine combustor to ground vehicle PPU turned out to be successful.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.3
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• pp.19-28
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• 2000

In general the data such as thrust, pressure, temperature and combustion time are measured in developing the propulsion system of solid rocket motor through static firing test. But in the case of personal surface to air missile there are required a severe safety specifications in order to eliminate gunner hazard from the exhaust plume of motors. The safety requirements lead to the design of separation device and safety igniter device. The dynamic firing test for the designed two devices should be conducted under the flight environmental conditions to verify the requirements compliance. In this study the technique for dynamic firing test of propulsion system of personal surface to air missile is proposed and the method to design the dynamic test bench is also studied.