• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.468-471
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• 2012

This paper describes a construction scheme of hot backup or triple modular redundancy control system in a ground hot-firing test facility to carry out performance assessment of propulsion system used in a space launch vehicle. It was possible for a hot backup redundancy control system with manual operated console to simulate TMR control system. A console layout of control system in control center to restrict imprudent works of operators was proposed.

• 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.

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.109-112
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• 2011

The result of design review and arrangement of a combustion chamber test facility(CTF) and a turbo-pump real propellant test facility(TPTF) is briefly described. The development/qualification tests of combustion chamber and turbo-pump for 75ton-class liquid rocket engine will be performed in CTF and TPTF. The critical design of hydraulic-pneumatic system, control and data acquisition system, test stand cell, and auxiliary facilities in CTF and TPTF was performed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.219-222
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• 2007

This research on 2nd stage solid rocket motor of KSLV-I for performance change was carried out. Solid rocket motor shall ignite on altitude of 300km. Solid Rocket Motor performed Static Firing Test and High Altitude Test for motor performance. A study made an analysis of specific impulse variation for nozzle ambient pressure.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1204-1204
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• 2017

• 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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• v.y2005m4
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• pp.151-154
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• 2005

A study was conducted to investigate safe testing on propulsion system, especially concentrated on effects of contaminants accumulation and transfer in LOX system. Several methods for system operation decreasing accidents caused by oxidizer leakage and contaminants accumulation was investigated. These methods can be applied to LOX system and other propellants system in liquid propellants propulsion system.

• Korean Chemical Engineering Research
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• v.54 no.3
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• pp.360-366
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• 2016

The Propulsion Test Facilities for the development of Korea Space Launch Vehicle-II are being built, some test facilities are completed and various combustion tests are running. The Propulsion Test Facilities consists test-stand, which carries out tests for engine development model, and various sub-systems and vessels containing LOX and Jet A-1 as propellant. There are always risks of fire and explosion at the test-stand since engine development model is conducted at test-stand with real combustion test with very high pressure, mixed propellant and high energy. In this paper, in order to establish the consequence analysis and risk reduction measures in the Propulsion Test Facilities, followings are considered. 1) a propellant leak accident scenario is assumed in test-stand. 2) TNT equivalent model equation based on blast wave of the explosion was used to analyze blast overpressure and impacts. Also, technical, systematic and managemental measure is described to ensure risk reduction for propulsion test facility.

• Proceedings of the Korea Institute of Fire Science and Engineering Conference
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• 2011.11a
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• pp.405-408
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• 2011

본 논문은 발사체 추진기관의 지상 시험을 수행 하면서 쌓은 경험을 바탕으로 한 운용방법에 대해서 서술하고 있다. 운용방법은 발생 할 수 있는 사고를 줄이기 위한 특별한 방법 및 정책, 그리고 사고를 줄이기 위한 기술적 해결책을 포함 하고 있다. 이러한 운용방법은 추진기관 시험 시에 발생 할 수 있는 비정상적 상황에 관한 연구를 통하여 정립되었다. 서술한 운용방법을 통해서 발사체 추진기관의 시험운용을 개선 할 수 있으며, 안전하게 수행할 수 있다.