• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.4
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• pp.75-82
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• 2001

KSR-III propulsion feeding system is designed to feed a certain amount of propellant to engine by the end of combustion. The oscillation of propellant to engine would cause combustion instability and thrust oscillation and POGO phenomenon. This article deal with analysis performed such as the effect of rocket acceleration on the propulsion system and POGO analysis to ensure the performance of KSR-III

• 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.

• 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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• 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 Propulsion Engineers Conference
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• 2010.05a
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• pp.89-94
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• 2010

Fuselage propellant feeding system should supply propellants to engine with required flow rate, temperature and pressure. Propellant vibration in engine and feeding line changes feeding characteristics, and frequently inhibits to satisfy the required feeding requirements. Sloshing and POGO vibration are known to be the major vibration phenomena. Concerning sloshing and POGO, vehicle control and structural dynamics aspects are extensively studied, whereas, its effect on propellant feeding performance is not clearly understood. This paper focuses on the deviation of required feeding performance due to propellant vibration. Overall characteristics of propellant vibration and its effect on propellant supply to engine are reviewed and control mechanism for suppressing vibration is introduced.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.33-36
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• 2009

This study suggests manufacturing and cleaning the feeding system of hydrogen peroxide to use oxidizer of liquid rocket. We established the process of cleaning and passivation in order to minimize the pollution of Hydrogen Peroxide feeding system. And, we verified stability of the manufactured feeding system by leak test & hot test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.93-97
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• 2010

The energy balance program which can balance the relations among energy, mass flow, pressure in the staged-combustion cycle of the liquid rocket engine has been developed. The modular approach has been chosen for the analysis; the engine cycle consists of the elements from the predefined component analysis program. The engine with the staged-combustion cycle has been decomposed into several principal component modules, such as a thruster chamber, turbopumps, turbines, supply system components and a pre-burner. The program has been verified with comparison of the results to the selected data of the space shuttle main engine.

• 한국신재생에너지학회:학술대회논문집
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• 2010.06a
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• pp.248.2-248.2
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• 2010

바이오매스는 에너지 위기 및 $CO_2$에 의한 지구온난화 및 화석자원의 고갈이 진행되면서, 화석연료와 달리 재생이 가능하고 지속 가능한 자원으로 각광을 받고 있다. 바이오매스를 이용하는 신재생에너지 기술로는 직접연소, 열화학적 변환, 생화학적 변환 기술 등이 있다. 열화학적 변환 기술에는 바이오매스를 열분해 가스화하여 발생된 합성가스를 이용하는 기술이 포함된다. 농업부산물은 청정에너지원으로서의 가능성이 높은 것으로 알려져 있으나, 현재는 퇴비, 가축사료 등의 단순 활용이 대부분을 차지하고 있다. 농업부산물을 이용하여 고부가가치를 창출하기 위한 하나의 방안으로 열분해 가스화를 통해 고효율 에너지원으로의 사용을 고려해 볼 수 있다. 본 연구에서는 초본계 농업부산물인 왕겨를 이용한 열분해 가스화기에서 발생한 합성가스를 정제시스템을 통하여 정제한 후, 가스엔진으로 정량적으로 공급하기위한 합성가스 공급시스템의 운전 특성을 고찰하였다. 그 결과 왕겨를 이용한 가스화기에서 합성가스는 안정적으로 발생하였으며, 정제시스템에서는 90%이상의 효율을 얻었다. 또한 20 kW급 가스엔진에서 필요로 하는 합성가스 공급유량 테스트는 약 $80Nm^3/h$, 200 mmAq 조건에서 가스 누입, 누출 없이 안정적으로 공급되었다.

• 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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• 2017.05a
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• pp.108-111
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• 2017

High performance upper stage engine is necessary for space launch vehicles of geostationary orbit, and staged combustion cycle engine is suitable due to high specific impulse. Technology demonstration model for 9 tonf class staged combustion cycle engine, which is consisted of turbopump, preburner, combustion chamber and supply system, was assembled, and hot-firing test was conducted for three seconds in Upper-stage Engine Test Facility of Naro Space Center. Ignition, combustion and shut down of engine system was performed normally, and its performance parameters were evaluated.