• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.3
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• pp.22-29
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• 2003

The propulsion feeding system of KSR-III is composed of tubes, valves and PSC, and controls the flow of propellant entering to engine. The test of PTA-I is carried out to verify the characteristic of propulsion feeding system and component. The tests of operation characteristic of component, hydraulic characteristic of tubes, flow control using venturi, oscillation of dynamic pressure, characteristic of regulator are carried out. Troubles of component are found out, and renewed, and the performance of the propulsion feeding system is verified through PTA-I. The results of PTA-I are used to the configuration of propulsion feeding system and test of PTA-II.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.36-40
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• 2017

The launch operation for a space launch vehicle(SLV) is to be conducted by the systematic operation between SLV and the Technological Equipment(TE) such as the mechanical, fuel, and electrical ground support equipment at launch complex(LC). The basic source for the operation of the instruments in LC is the electrical power supply system, Technological Equipment Power Supply System(TEPSS), which is one of the Launch Control System. Thus TEPSS should supply the required electrical power to TE with reliability. In this paper, TEPSS which supplies operational electrical power to TE is introduced.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.322-325
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• 2007

This paper shows the development procedure of the low pressure LOX feed system which is used in the liquid rocket with a turbopump. Korean Air has cooperated with KARI in developing the LOX feed system to turbopump. The LOX feed system is characterized with cryogenic temperature and the thin-thickness tube for weight saving. The system in this project is composed with a main feed line and a recirculation line for the LOX temperature conditioning. Each piping system has many components, namely, bellows, filter, orifice, valves, flange and support. In this paper, system design & manufacturing, structural & thermal analyses, and component tests are explained. Finally, the system was assembled to the KARI's PTF test facility and functioned well to meet its required performance.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.79-82
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• 2004

Propellant feeding system is the system to satisfy propellant feeding requirements(mass flow rate, pressure, temperature) at engine inlet of launch vehicle. Propellant feeding test facility is being constructed for the development scheme of pressurization system, processing in tank, propellant piping system, and flow control system that are main technologies in order to develope propellant feeding system. This paper introduces the propellant feeding test facility being constructed in KARI.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.79-84
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• 2010

The supply system module of the liquid rocket engine has been developed, which consists of the various supply system components such as pipes, orifices, elbows, bellows, valves and flanges. This module can size the components and calculate pressure drops between them. For the assembly of the supply system components, the supply system module can evaluate the number of the components, total pressure drop, outlet pressure and total system weight.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.122-126
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• 2006

Two types of pressurization system and low weight feeding piping system are developed. With sub-system tests, ullage pressure control performance was verified for 1 step and 2 step pressurization system and the feeding performance of feeding piping system was also verified. The weight of the feeding piping system is low enough for the application of launch vehicle. In addition, LOX conditioning system is developed for avoiding geysering and LOX temperature rise. Integrated performance was verified through integrated on-board feeding system performance tests.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.3
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• pp.45-52
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• 2002

This article deals with the introduction of longitudinal instability of liquid rocket (pogo) and the analytical results on the frequency responses of Korean Sounding Rocket (KSR-III) propulsion feeding system. Both the stiffness of bellows and the cavitation volume of venturi affect the frequency response of the feeding system. Especially, bellows has a great roll to reduce the natural frequency of the feeding system. Also, oxidizer and fuel feeding systems of the KSR-III have natural frequencies of about 280Hz and 90Hz, respectively.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.52-57
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• 2012

A liquid rocket system consists of a combustion chamber, a gas generator, a turbo pump, and a turbine, etc. Each component is connected by supply components such as valves, pipes, and orifices. Since each component has a combined effect on engine performance, preliminary analysis for overall system must be required before the conceptual design stage. Comprehensive analysis program considered the supply system has not been developed yet. In this paper, a supply component model of the liquid rocket engine has been designed after verification of each component. The gas generator cycle with supply components has been composed. The results of the cycle has been compared to those of the F-1 engine with the representative gas generator cycle.

• Proceedings of the Korean Society of Postharvest Science and Technology of Agricultural Products Conference
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• 2003.04a
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• pp.141-141
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• 2003

신선농산물의 호홉속도를 측정하는 방법 중 하나인 개방계(open system) 호흡속도 측정시스템은 소정의 농도로 조정된 혼합기체를 측정대상시료에 흘려 보내며 측정하는 방법이다. 개방계 측정법의 장점은 혼합 기체조성 영역에서 정확한 호흡속도를 얻을 수 있으며 방치시간이 필요 없으므로 반복 측정이 용이한 것 등이다. 그러나 개방계 측정법은 공급되는 혼합기체의 농도와 유속이 일정하여야 하며 연속으로 호흡속도 측정용 챔버의 혼합기체 공급측과 배기측에서 기체시료를 수집하여 매우 미세한 기체농도의 차이를 측정할 수 있어야 하고 기체 시료 수집에 상당한 주의가 요구된다. 이러한 문제를 개선하기 위하여 개방계 호흡속도 측정 시스템을 자동화하였다. 자동화된 호흡속도 측정 시스템은 혼합기체 발생장치, 온도조절이 가능한 기체기밀용 챔버와 G.C로 구성되어 있다. 환경기체조성을 위한 혼합기체발생장치는 $N_2$, $O_2$, $CO_2$ 압축 실린더에서 공급되는 기체를 압력 조절기를 통해서 일차압력을 조정하고 정밀 압력 조절기를 이용하여 0.1~0.2 kg/$\textrm{cm}^2$의 정압을 유지시켰다. 압력이 일정해진 기체는 metering valve를 이용하여 각 기체의 유량을 소정의 비율로 제어할 수 있도록 하였으며 각각의 기체는 gas mixed cell에서 실험 농도의 환경기체조성으로 혼합되어 항온기내의 호흡속도 측정 챔버($25^{\circ}C$)로 공급될 수 있도록 하였다. 호흡속도 측정용 챔버는 개스킷이 장착된 아크릴 재질이며 온도 조절이 가능한 항온기로 구성되어 있다. 호흡속도 측정용 챔버와 G.C간의 기체흐름은 three way solenoid valve에 의하여 제어되며 전원의 on/off에 따라 공급측의 가스와 배기측의 가스가 선택적으로 G.C에 공급될 수 있도록 구성하였다. 측정 대상 챔버의 기체는 제어된 유로를 따라 multi-position valve를 통과하여 G.C에서 분석되도록 하였다. 본 연구에서 개발된 개방계 호흡속도 자동 측정 시스템의 성능 실험에서 혼합기체발생장치에서 조제된 혼합 기체의 농도를 설정치와 비교한 결과 $O_2$와 $CO_2$의 농도에서 평균오차 0.2%로 정밀한 것으로 나타났으며 호흡속도 측정용 챔버의 혼합기체 공급측과 배기측의 가스 농도를 3회 반복 측정한 결과 재현성에서는 0.1%이하의 편차로 나타났다. 개방계 호흡속도 자동 측정 시스템을 이용하여 환경기체조성하에서 토마토의 호흡속도를 측정하는 실측 실험을 수행한 결과 2$0^{\circ}C$에서 12.7~42.1mg$CO_2$/kg.hr였으며 12$^{\circ}C$에서 2.5~8.2mg$CO_2$/kg.hr로 일반적으로 보고되고 있는 토마토 호흡속도와 일치하는 결과를 나타내었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2001.04a
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• pp.108-108
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• 2001