• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.3
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• pp.67-72
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• 2006

Several propellants were investigated experimentally for ignition characteristics in subatmospheric pressure. The threshold ignition pressure was 4 psia for HTPB/AP composite propellant. The partial replacement of AP in HTPB/AP propellant by $5{\sim}l5%$ of HMX, HNIW showed that the improvements in ignition delay was over 50% and the threshold pressure was below 0.4 psia. This appears to be due to the characteristics of HMX and HNIW exothermic dissociated at the temperature(${\sim}220^{\circ}C$) love. than that of AP. The ignition substance $B/KNO_3$ was coated thinly on the propellant surface for better ignition performance. As a result, ignition delay time of 15% was improved. NC is applied to $B/KNO_3$ ignition substance as a secondary binder and $NC-B/KNO_3$ suspension solution is coated to the propellant surface.

• 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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• 2005.11a
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• pp.433-436
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• 2005

The combustion behavior of initiators and can-type ignitor, acting on vacuum pressure, was invested. It was found that if the ignited propellants of a can-type igniter were exposed at certain level of low pressure, it would be burnt improperly or even be extinguished. When we design the can-type igniters for some rocket motor, it is most important that the pressure built-up by the gases which were already burnt inside of the igniter case keep as high as possible. For this purpose, it is recommended that the ignitor case have some strength to produce as much gases as possible before breaking out and the free volume be kept as small as possible.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.3
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• pp.19-27
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• 2002

The sequence of the propellant supply for ignition of a liquid rocket engine combustor is very important in the reliable and safe operation of the engine. The ignition sequence of KSR-III main engine was briefly described and the measuring parameters and their reliability determining ignition sequence were examined in this paper. The filling time of the engine propellant manifolds and the valve open/close time were reviewed to obtain the exact and reliable time of the propellant supply to the combustor. The combustion characteristics of the engine at starting were discussed at different supply lead of propellant. Finally, the hot firing test results with cyclogram determined by measuring parameters were presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.125-128
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• 2010

A pyrotechnic igniter with a relatively simple configuration was developed to secure the stable and reliable ignition of the gas generator in space launch vehicles. It was designed not only to provide a sufficient heat flux for the propellant ignition but also to ensure a structural safety under the conditions of very high temperatures and pressures. The burning tests of the igniters have been performed to decide several design parameters, and consequently the performance tests have proved that the pyrotechnic igniter developed in this study meets the design requirements.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.10a
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• pp.19-19
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• 1999

KSR 3단 AKM Motor Case를 개발하기 위해 추진기관 경량화에 가장 유리하고 비강도 및 비강성이 뛰어난 복합재 연소관을 고려하여 직경 300mm급의 축소형 모델을 선행 개발하였다. Netting 이론에 의해 연소관 두께를 결정하고 체적을 최소화 하기 위해 구형으로 연소관 형상을 설계하였다. 연소관을 제작하기 위한 맨드렐은 분리, 조립식으로 설계, 적용하였고 연소관 기밀 유지 및 추진기관 연소시 연소관을 보호하기 위한 삭마성 재료로 EPDM base의 고무 내열재 조성을 개발하였다. 고무 내열재는 맨드렐 위에 적층하고 Vacuum bagging 상태로 Autoclave에서 가황하여 적용하였다. 국내 최초로 Prepreg를 사용하는 Dry process로 고무 내열재가 적층된 맨드렐 위에 Winding하고, Vacuum bagging 상태에서 경화하여 연소관을 제작하였으며, 이 때 사용한 Carbor/Epoxy Perpreg 재료의 기계적 성질 및 열특성 시험을 병행하였다. 제작된 연소관은 수압 시험을 통하여 구조적 안정성을 입증하였고, NDT 검사를 통해 재료간 계면 상태를 분석하였다. 시험이 끝난 연소관은 향후 점화기 개발을 위하여 점화제 종류 및 약량을 변경하여 점화 시험을 수행하여 점화기 개발을 위한 기초 데이터를 확보하였다.

• Proceedings of the Korea Information Processing Society Conference
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• 2016.04a
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• pp.76-79
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• 2016

자동차 산업의 발달과 전세계적으로 차량의 증가로 인해 보행자의 사고 발생율이 증가하고 있고 보행자의 안전에 대해 연구와 안전장비들이 계속적으로 개발되고 있다. 보행자와 차량의 충돌시 보행자의 상해를 감소시키는 시스템 중 화약식 액티브 후드 시스템(active hood system, AHS)은 부하가 화약성분이므로 부하의 성분을 검출하는데 한계가 있고, 위험성이 높으므로 정밀한 고장진단이 필요하다. 이러한 문제점을 해결하기 위해 화약의 부하저항을 측정하는 방법과 저항성 누설전류를 측정하는 방법을 제시하고, 이 방법을 점화회로의 이상 유무를 확인하는 고장진단 기법으로 제안한다. 그리고 고장진단시 squib가 점화되는 오동작을 방지하고저 고장진단 모드와 점화모드를 구별하여 진단전류와 점화전류를 구분하는 기법을 제안한다.

• Transactions of the Korean Society of Automotive Engineers
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• v.3 no.1
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• pp.45-53
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• 1995

스파크 점화기관에서 화염전파과정에 관한 연구를 수행하기 위하여는, 초기화염핵 구간에서의 화염의 형성과 발달의 거동을 정확히 파악하여야 한다. 그러므로 화염핵의 형성과 발달에 영향을 미치는 최소 화염핵 크기의 이론적인 계산을 수행하였다. 이론식을 정립하기 위하여 열점화 이론을 이용하였다. 최소 화염핵 크기를 계산하기 위해 열전도 계수, 화염온도, 층류연소속도, 기타 열역학적 상태량 등을 계산하였다. 계산에 의존한 화염핵 크기의 신뢰성을 확인하기 위하여, 점화에너지를 변화시킬 수 있는 점화장치를 사용하여 실기 운전을 통하여 희박연소 한계가 그 때의 화염핵이 성정할 수 있는 영역이라고 가정하여 그 정확도를 확인 하였다.

• Journal of ILASS-Korea
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• v.21 no.1
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• pp.37-46
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• 2016

For the SI engines, at only full load, the pumping loss has a negligible effect, while at part load conditions, the pumping loss increases. To avoid the pumping loss, the spark-ignited engines are designed to inject gasoline directly into the combustion chamber. In the spark-ignited direct-injection engines, ignition probability is important for successful combustion and the flame propagation characteristics are also different from that of pre-mixed combustion. In this paper, a visualization experiment system is designed to study the ignition probability and combustion flame characteristics of spark-ignited direct-injection CNG fuel. The visualization system is composed of a combustion chamber, fuel supply system, air supply system, electronic control system and data acquisition system. It is found that ambient pressure, ambient temperature and ambient air flow velocity are important parameters which affect the ignition probability of CNG-air mixture and flame propagation characteristics and the injected CNG fuel can be ignited directly by a spark-plug under proper ambient conditions. For all cases of successful ignition, the flame propagation images were digitally recorded with an intensified CCD camera and the flame propagation characteristics were analyzed.

• Fire Science and Engineering
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• v.18 no.1
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• pp.18-23
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• 2004

This paper describes the minimum ignition limits for propane-air 5.25 Vol.% mixture gases in low voltage inductive circiuts. The improved effects on the ignition limit are studied by parallel safety components(resistors) for propane-air 5.25 Vol.% mixture gas in low voltage inductive circuits. The experimental devices used in this test are the IEC type spark ignition test apparatus. The minimum ignition limits are controlled by the values of current in inductive circuit. Energy supplied from electric source is first accumulated at the inductance, it's extra energy is working as ignition source of the explosive gas. The improved effects on the ignition limit are respectively obtained as the maximum rising rate of 330% by composing parallel circuits between inductance and resistor as compared with disconnecting inductance with the safety components. The more values of inductance increase the higher improved effects of ignition limit rise. The less values of resistor the higher improved effects of ignition limit rise. It is considered that the result can be used for not only data for researches and development of intrinsically safe explosion-proof machines which are applied equipment and detectors used in dangerous areas but also for datum for its equipment tests.