• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.479-483
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• 2012

This paper describes the development status of rocket engine test facility for the performance evaluation of liquid rocket engine of KSLV-II 1st stage. Design specification and composition of rocket engine test facility are suggested based on the design requirements. The results of the basic 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.155-158
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• 2007

As a secondary stage of the liquid rocket engine development test, turbopump-gas generator powerpack tests are being performed. The schematics of the test hardware and the test facility for the TP+GG coupled test are presented. The results of a preliminary test results for the verification of the propellant supply system of the test facility are also presented. Based on the preliminary tests results, the verification of the propellants supply systems of the facility system was performed.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.5
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• pp.84-91
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• 2010

For the successful development of 75-tonf-class liquid rocket engine, a plenty of tests on each engine component have to be performed and this is equally true for a combustor. However the test facility which is in operation at Korea Aerospace Research Institute lacks its capacity to perform fire tests of a 75 tonf class combustor at its nominal thrust. Since the test facility has to be ready prior to the start of development tests, it is very urgent to establish the test facility. The preliminary design of a test facility for a 75 tonf class combustor which was performed according to such a necessity is described in the paper.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.3
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• pp.69-78
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• 2010

Korea Aerospace Research Institute started on design and development of a hypersonic air-breathing engine test facility from 2000 and completed the test facility installation in July 2009. This facility, designated as Scramjet engine test facility(SeTF), is a blow-down type high enthalpy wind tunnel which has a pressurized air supply system, air heater system, free-jet test chamber, fuel supply system, facility control/measurement system and exhaust system. In this paper, details of the specifications, and configuration of the SeTF are described. For verifying characteristics of the SeTF, wind tunnel tests are now on progress and some of the data are also described.

• 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.

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.835-840
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• 2011

The development of a turbopump is fundamental to have an independent LRE(liquid rocket engine) for KSLV-II. Recently, the detail design of a turbopump real-propellant test facility based on liquid oxygen and kerosene has been performed to structure the test facility for the experimental validation of the turbopump. In this paper, the design requirements of the turbopump and the specifications of the test facility was presented and the representative sub-facilities were explained on the basis of the design results. Also, the uncertainty of the sub-facilities which could be appeared during the operation was removed in advance through the simulation method and the experimental verification.

• 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.