• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.27-30
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• 2011

For the successful development of korean lunar lander, the ground test is required in order to verify performance of propulsion system, attitude control system, performance of landing device and etc. In order to develop the lunar lander ground test model, development of large size thruster and pressure regulated propulsion system is now in progress. In this paper, the results of 200N class monopropellant thruster development and propulsion system design will be presented.

• Journal of the Korean Society of Propulsion Engineers
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• v.27 no.1
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• pp.49-57
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• 2023

The autogenous pressurization has been widely adopted for propulsion systems of next-generation reusable rockets due to its low cost and high reliability. The autogenous pressurization has a simple structure, but an understanding of the heat and mass transfer occurring inside the tank is essential. For this reason, a simulation test of the autogenous pressurization was conceived. The experiment equipment was constructed based on overseas pressurization test facilities cases and expert advice. Unlike the actual autogenous pressurization system, the propellant tank was insulated to exclude external influences. The pressurized gas supply line and the propellant pipe were separated. Using the manufactured autogenous pressure experiment equipment, it is possible to evaluate the condensation phenomenon of pressurants in cryogenic propellants, comparison of the efficiency of pressurization using helium and evaporated gas and the pressurization capacity according to the temperature of pressurant.

• 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.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.4
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• pp.47-58
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• 2002

The pressure regulator has been developed as a pressure-control device of propellant tank in KSR-III. The pressurization system of KSR-III is a basic pressurization system composed of pressurant, He tank and propellant tank. The pressure-control regulator is the most important part of gas-pressurized feed system along with He tank, pyrovalve and He fill valve. The first model of the regulator is tested to satisfy in leakage, strength and basic performance. The second model is tested in the overall test of the KSR-III propulsion system using water. From the test result of the second model, we conclude that the capacity of valve(Cv) must be increased in real system. The third model is modified and tested in the overall test of KSR-III propulsion system using propellant. Finally, the pressure-control regulator is qualified from firing test.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.6
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• pp.56-63
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• 2009

In this paper, we present technical survey results on propulsion systems for Personal Air Vehicles (PAV). Reciprocating engines are suitable for current PAVs because of their superior efficiency and price advantages, except they produce noise problems. Turbo-Shaft engines are suitable for VTOL PAVs because of high specific power and wide operating range even though they are expensive. However, fuel cells and batteries may replace conventional engines in the near future.

• Review of KIISC
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• v.9 no.3
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• pp.22-22
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• 1999

정보통신 기술의 발달로 사회의 모든 분야에서 인터넷의 활용이 급속히 확산되어 전자 결제, 전자상거래, 인터넷뱅킹등의 편리한 서비스가 제공되고 있다. 그러나 인터넷을 이용한 여러 종류의 거래는 거래 당사자간 비접촉 · 비대면을 특징으로 한다. 이러한 특징이 편리함을 제공하는 반면 거래당사자간의 상호신뢰에 있어서 취약하다는 문제점을 가진다. 이 문제점을 해결하기 위해 정부는 전자거래기본법, 전자서명법 등 법적 · 제도적 장치를 마련하여 "공인인증" 제도를 도입하였으며 이에 부응하여 금융결제원은 금융분야 공인인증기관으로 인증서비스를 제공하기 위해 준비중이다. 본고에서는 금융결제원의 인증서비스의 추진원칙, 인증서비스 제공을 위한 시스템 구축, 인증서를 이용한 서비스에 대한 부분으로 나누어 서술한다. 인증서비스의 추진원칙은 1999년 내에 공인인증기관 지정획득을 하고 IETF의 PKIX 표준안 , RSA의 PDCS표준안, OpenGroup의 CDSA 표준안을 충실히 따르는 인증시스템을 일괄 개발한다. 인증서비스 제공을 위한 시스템 구축은 최상위 인증기관인 전자서명인증관리센타에서 제시한 기본원칙을 충실히 따르며 금융분야 인증서비스를 위해 알맞게 변경하여 구축한다. 금융결제원이 발행한 인증서는 인터넷 뱅킹과 전자상거래등에 이용된다.

• Review of KIISC
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• v.9 no.3
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• pp.23-30
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• 1999

정보통신 기술의 발달로 사회의 모든분야에서 인터넷의 활용이 급속히 확산되어 전 자 결제 전자상거래 인터넷뱅킹등의 편리한 서비스가 제공되고 있다. 그러나 인터넷을 이용 한 여러종류의 거래는 거래당사자간 비접촉.비대면을 특징으로 한다. 이러한 특징이 편리 함을 제공하는 반면 거래당사자간의 상호신뢰에 있어서 취약하다는 문제점을 가진다. 이문 제점을 해결하기 위해 정부는 전자거래기본법 전자서명법 등 법적.제도적 장치를 마련하여 "공인인증" 제도를 도입하였으며 이에 부응하여 금융결제원은 금융분야 공인인증기관으로 인증서비스를 제공하기 위해 준비중이다. 본고에서는 금융결제원의 인증서비스의 추진원칙 인증서비스 제공을 위한 시스템 구축 인증서를 이용한 서비스에 대한 부분으로 나누어 서술 한다. 인증서비스의 추진원칙은 1999년 내에 공인인증기관 지정획득을 하고 IETF의 PKIX 표준안 RSA의 PDCS표준안 OpenGroup의 CDSA 표준안을 충실히 따르는 인증시스템을 일 괄개발한다. 인증서비스 제공을 위한 시스템 구축은 최상위 인증기관인 전자서명인증관리센 타에서 제시한 기본원칙을 충실히 따르며 금융분야 인증서비스를 위해 알맞게 변경하여 구 축한다. 금융결제원이 발생한 인증서는 인터넷 뱅킹과 전자상거래등에 이용된다.거래등에 이용된다.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.4
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• pp.1-10
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• 2006

In this paper, a calculation method of the thermodynamic parameters of cryogenic propellant is proposed when a cryogenic propellant tank is pressurized by gaseous helium(GHe) bubbling. Temperature of cryogenic propellant and mass of dissolved GHe into propellant were analyzed at the various operation of pressurization of tile liquid oxygen(LOX) and hydrogen($LH_2$) tank using helium bubbling. It was evaluated how the GHe bubbling influences to the thermodynamic parameters of LOX and $LH_2$ with results of the analysis. With the proposed calculation method, It will be able to confirm the feasibility of GHe bubbling as a pressurization system of cryogenic propellant tank and to optimize the pressurization system using GHe bubbling.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.795-796
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• 2011

During launch process, ground support facilities perform its duty in established processes by communications with launch vehicle. All ground support systems are operated independently or organically. This paper studied algorithm of propellant filling process and method for liquid oxygen filling system in launch operation in Naro space complex.

• Spatial Information Research
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• v.1 no.1
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• pp.29-38
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• 1993

Each office developped GIS for their own purpose recantly. But many cases, establ ished in some local government off ices, were found not to perform properly. The main problem is to integrate different offices' systems. Also. accurate nation-wide digital basemap database does not exist in Korea. To solve these problems, the suggestions are following: $\circled1$ develop the nation¬wide digital basemap database to increase the effectiveness of GIS, $\circled2$ make the database with standardized format, $\circled3$ educate and train people to be spcialist, $\circled4$ make laws and regulations to share and to integrate database.