• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.2
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• pp.47-59
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• 2022

Liquid hydrogen/liquid oxygen rocket engines with highest specific impulse have been developed since the 1950s and used until now to maximize the capability of space launch vehicles. Domestic liquid hydrogen infrastructures for the production, transportation and distribution are being expanded at world-class level with the rise of hydrogen economy, which is a great opportunity for the performance enhancement for indigenous space launch vehicles. In this paper, feasibility of applying liquid hydrogen as a propellant is investigated in various aspects. The status of domestic liquid hydrogen infrastructure, the technologies required for liquid hydrogen engines, and operational aspects for safe handling of hydrogen are reviewed. In addition, test facilities for developing hydrogen engines are introduced briefly.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.5
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• pp.91-97
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• 2015

After-burner test facility for gas generators of 75 tonf class liquid rocket engines was designed, which was verified by the facility certification test of the Combustion Chamber Test Facility(CCTF). The purpose of the certification test of the after-burner test facility is to verify the combustion stability of gas torches equipped in the gas generator and the after-burner test facility by using methane and oxygen gases. In the case of the autonomous test, the supply system provided steadily methane and oxygen gases to the after-burner system without pressure drop. The combustion pressure of the gas torch approached the design requirement. In the case of the coupled test, the gas generator ignition and the fuel-rich exhaust gas combustion were successfully carried out, leading to the verification of the test facility.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.97-103
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• 2011

This paper describes the main considerations for the development of engine emergency protection system and applications to preliminary engine development tests. Emergency protection system performed its role without failure to shutdown test very quickly for the prevention of development of malfunctioning of test articles, which protected test articles and test facility in all abnormal situation occurred during preliminary engine development test program. This results will be used for the development of engine emergency protection system.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.3
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• pp.43-49
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• 2007

A ground firing test facility for Liquid Rocket Engine(LRE) combustor was built in Korea Aerospace Research Institute(KARI) in 2001 to support the development of the first Korean LRE for the KSR-III. About 170 tests were conducted up to date since its establishment and in the meantime a considerable improvements were made in the facility capability. This paper describes the outline, conducted tests and operation techniques which have been acquired through the operation of the test facility.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.814-815
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• 2010

Korea Aerospace Research Institute plan to develop propulsion system test facilities for combustor, engine system, propulsion systems of KSLV-II propulsion system in process of Korea Space Launch Vehicle project. By review for heavy test facilities specifications of foreign technically developed nations of the world, it will be referenced for test facility development plan of Korea Space Launch Vehicle project in the future.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.3
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• pp.84-91
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• 2014

The flow rate control of a cavitating venturi has been investigated with downstream pressure variation. A set of cavitating venturies for a liquid rocket engine thrust chamber firing test facility have been designed and manufactured. The flow characteristics of the cavitating venturies have been analyzed by experimental and computational methods. Results showed that constant mass flow rate condition was established by the cavitation inside the venturi. However, upstream pressure less than the actual design pressure of the cavitating venturi could not supply a constant flow rate.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.343-346
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• 2010

The construction plan of a combustion chamber test facility(CTF), a turbopump real propellant test facility(TPTF), a rocket engine ground/high altitude test facility(ReTF, HAReTF) and a propulsion system test complex(PSTC) for KSLV-II is briefly described. The development/qualification tests of 75ton-class liquid rocket engine system and engine component will be performed in CTF, TPTF, ReTF and HAReTF and the development test of $1^{st}/2^{nd}/3^{rd}$ propulsion systems for KSLV-II will be performed in PSTC. These propulsion test facilities will be built in NARO space center considering construction schedule, cost, safety distance and utility factor of propulsion test facilities.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.23-26
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• 2005

The method of decreasing the ecological risk for the LRE(Liquid Rocket Engine) test is developed, working on the cryogenic oxidizer and the high-boiling fuel(Kerosene). This Method is based on the study that contains a technical solution method and an accident occurrence range for decreasing of accident probability and damage. This paper contains schematic on the all risk circumstance bring to accident, block-diagram for an accident growth process in case of the propellant leakage, evaluation method of safety distance from test stand to residential area. It will be used to alternative method for the risk reduction of complex technical systems.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.193-196
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• 2003

The KSR-III developed by KARI is the first rocket vehicle which is adopting the liquid propellant rocket engine system in Korea and its flight test was successfully done last year. KSR-III is a sounding rocket class launch vehicle, but there is a sense to accomplish design, manufacture, performance test and finally its flight test by domestic technology. In this paper, the authors are intended to introduce the multi-purpose test facility(PTA-II Test Facility) which is constructed for the variety of tests on KSR-III feeding system(single component tests, verification tests, cold flow tests and combustion tests) and its test results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.601-602
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• 2009

대한항공은 2003년 소형위성발사체(KSLV-I) 사업 참여와 함께 2005년부터는 국내 액체로켓엔진 개발관련 한국항공우주연구원 주관의 각종 개발에 참여하고 있다. 본 논문에서는 현재 국내에서 진행중인 75톤급 액체로켓엔진 시스템 선행개발관련 대한항공이 수행하고 있는 분야별 업무의 소개와 함께 대한 항공의 향후 추진 계획을 다루고자 한다.