• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.1
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• pp.98-110
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• 2015

Recently, a validation research of maneuvering and attitude control logics of a spacecraft under a ground condition is getting increase by using operating simulators with compact and precise components. For that, a cold gas propulsion system is generally used for maneuvering and attitude control of spacecraft ground simulators for its simplicity and a high reliability. In the present study, major design parameters of a cold gas propulsion system are derived to meet mission requirements based on conceptual design results of a simulator. And additionally, commercial components with proper specifications are selected for system assembly.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.4
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• pp.80-89
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• 2003

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.676-677
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• 2010

In Naro Space Center, Naro launch vehicle launched 2 times. Launch pad for Naro launch vehicle in Naro space center equipped propellant feeding facility for operating launch process. This paper studied development process and operating method for liquid oxygen filling system of cryogenic propellant systems in launch pad propellant feeding facility.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.10
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• pp.1048-1053
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• 2009

It proposes an simple and intuitive method that calculates the equilibrium pressures of a propellant tank by appling the mass conservation principle on the helium in the liquid propellant and in an ullage volume of the propellant tank. A propellant loading analysis program is developed and validated against the existing reference data. And it has applied to the present developing program, COMS Chemical Propulsion Subsystem and the results are compared, it may use to develop a technology of the next geostationary complex satellite's propulsion system.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.65-70
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• 2005

The KOMPSAT program is carrying out successfully in spite of the short domestic space development history, but there are still many difficulties in Koreanization of most core parts. Because the development of core parts is essential to participate in the advanced nations in space based on the mid-long term national space program, KARI has carried out development of Fill/Drain valve for propellant/pressurant supply of satellite, which has high possibilities to be koreanized, with Hanwha Corp.. This paper summarizes overall processes of development including design, manufacturing and test, and finally 4 sets of modules were successfully made. Also the satisfaction of performance requirements are verified through acceptance tests.

• Aerospace Industry
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• v.48
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• pp.34-38
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• 1997

중국측과의 협상시 상대적인 우위확보와 협상이 결렬되었을 경우를 대비할 목적으로 검토되었던 중형항공기 대안사업은 ''''96년 6월 중국과의 협상이 최종결렬되자 해외업체와의 협력을 본격적으로 추진하게 되었다. 현재 급격히 변화하는 국제환경과 제한적인 국내여건을 극복학 위한 여러 가지 시도가 검토, 수행되고 있는 바, 본고에서는 현재 검토되고 있는 중형항공기사업의 기본 추진방향 및 해외협력대상업체에 대하여 간략히 소개해 보고자 한다.

• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.179-185
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• 2005

It is an essential subject to decrease the mass of a launch vehicle for improving performance and efficiency of space launch system. Particularly, reducing the engine supporting area is necessary for high efficiency of propulsion system with clustered engine systems. The engine supporting area is related to the branch location of the oxidizer feeding line. This article deals the performance variation of the propulsion system such as the mass of the oxidizer feeding line, pressurization pressure of the oxidizer tank, and the onset of nucleation boiling in the oxidizer pipe with the branch location of the main feeding line.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.92-98
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• 2006

An 1 lbf of NASA standard monopropellant thruster, MRE-1, is used for KOMPSAT (Korea Multi-Purpose Satellite) which is launched in 2006 and provides reliable and cost-effective means for attitude and maneuvering control system. The monopropellant thruster obtains required thrust by thermal decomposition process of propellant through catalyst bed. During firing, the decomposition plays a role of a heat source that may occur an excessive radiation heat transfer to peripheral structures and electronics in relatively low temperature condition.Therefore, the radiation heat shield is needed to prevent the critical radiative heat exchange between thruster and satellite during firing. This paper summarizes an overall development process of radiation heat shield from the design engineering up to the manufacturing.

• Current Industrial and Technological Trends in Aerospace
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• v.9 no.1
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• pp.130-138
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• 2011

A vent relief valve performs as a safety valve, which ensures ventilation of propellant tank during filling and protection from tank overpressure after filling. Because of the reliability and cost saving, the virtually same vent relief valve has been used on all US cryogenic liquid fueled launch vehicles. Some modification to the valve has been applied to satisfy the various mission requirements of launch vehicles. This paper reviews the main technology trends of the vent relief valve applied to the propellant feed system for launch vehicle with respect to design and manufacture. This paper also introduces the operating technology of vent relief valve applied for launch vehicles of advanced countries in space development.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.797-800
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• 2011

For the space launch vehicle, propulsion system is the most important subsystem among others. For the evaluation of development level for rocket engine, integrated system test performed in appropriate facility is needed. In this study, test article and major parameters for certifying the propulsion system of launch vehicle were reviewed.