• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.56-61
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• 2011

The deign and lay-out of a combustion chamber test facility(CTF), a turbopump real propellant test facility(TPTF), a rocket engine test facility for 3rd stage engine(SReTF), 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 engine component, 3rd stage engine system and 75ton-class liquid rocket engine system will be performed in CTF, TPTF, SReTF, ReTF and HAReTF and the development test of 1st/2nd/3rd 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.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.1
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• pp.85-90
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• 2014

To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The CCTF is the test facility to develop the combustor of rocket engine, which uses liquid oxygen as a oxidizer and kerosene as a fuel. Present paper introduces the detailed design results of compressed gas supply system of CCTF, which is planned to be installed at Naro Space Center.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.632-636
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• 2017

In this study, we design an altitude test facility for hypersonic propulsion engine by constructing a test facility and cold flow test. Cold flow test is performed both with and without test models. The results show that the facility can simulate almost similar altitude condition without any significant change in pressure regardless of test models. We also constructed a database that might be useful for a variable test in the future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.41-44
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• 2007

Ground test facility for the hypersonic propulsion system was designed, constructed and performance test was conducted. The design point was selected using quasi，1-Dimensional CFD analysis before the conceptual design for construction of hypersonic facility After that, specific designs for performance and components were completed using unit analysis CFD code and performance tests were conducted for the various operation conditions.

• 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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• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.139-142
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• 2012

The deign and development status of a combustion chamber test facility(CTF), a turbopump real propellant test facility(TPTF), a rocket engine test facility for 3rd stage engine(SReTF), 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 engine component, 3rd stage engine system and 75ton-class liquid rocket engine system will be performed in CTF, TPTF, SReTF, ReTF and HAReTF and the development test of $1^{st}/2^{nd}/3^{rd}$ propulsion systems for KSLV-II will be performed in PSTC. The CTF/TPTF are under construction such as ordering the long delivery items and the detailed design of ReTF/PSTC is being prepared.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.2
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• pp.87-94
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• 2019

Liquid rocket propulsion test facility should provide for the interface condition installed on the upper level system for the test article. In addition, safety provision should be provided to be ready for accident such as explosion which can be occurred during development stage. For this purpose infra-structures of test facilities must be constructed so that stable combustion test can be performed and be guard against accidents. In this article, various aspects for infrastructures of propulsion test facilities are investigated including architecture and civil engineering aspects, test stand, room arrangements, interfaces among facilities, fire-fighting facilities, electrical power facilities.

• 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.885-891
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• 2011

This paper describes the results of preliminary design of rocket engine test facility for the performance evaluation of liquid rocket engine. Design specification and composition of rocket engine test facility are suggested based on the design requirements. The results of the preliminary design of rocket engine test facility will be used as base data for the detail design and construction of rocket engine ground test facility of KSLV-II 75tonf liquid rocket engine.