• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.4
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• pp.47-58
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• 2002

The pressure regulator has been developed as a pressure-control device of propellant tank in KSR-III. The pressurization system of KSR-III is a basic pressurization system composed of pressurant, He tank and propellant tank. The pressure-control regulator is the most important part of gas-pressurized feed system along with He tank, pyrovalve and He fill valve. The first model of the regulator is tested to satisfy in leakage, strength and basic performance. The second model is tested in the overall test of the KSR-III propulsion system using water. From the test result of the second model, we conclude that the capacity of valve(Cv) must be increased in real system. The third model is modified and tested in the overall test of KSR-III propulsion system using propellant. Finally, the pressure-control regulator is qualified from firing test.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.157-166
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• 2003

IPPT(Integrated Propulsion Performance Test)s were carried out as a final stage of KSR-III(Korea Sounding Rocket-III) propulsion system development three kinds of engine with different injector faceplate were tested, therefore a engine with composite baffle was certified for a KSR-III launcher. Though a engine with STS baffle which was designed for verification of combustion instability suppression ability was not final design, due to the combustion tests with this engine, it can be described that baffle has capability to suppress combustion instability at ignition and at mainstage in the case of KSR-III combustor.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.3
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• pp.75-86
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• 2004

KSR-III is the first Korean sounding rocket propelled by a liquid propellant propulsion system and it has been developed over 5 years using purely domestic technologies. The propulsion system of KSR-III is a 13-ton class see-level thrust liquid rocket engine(LRE) which utilizes liquid oxygen and kerosene for its propellants and employed pressurized propellant feeding and ablative cooling system. The problem of combustion instabilities which has brought the most difficulty in the development was resolved by implementation of a baffle. Through the development of KSR-III LRE, meaningful achievements have been made in the core technologies of LRE such as design of injectors and combustion chambers and test, evaluation, and control of combustion instabilities. The acquired technologies will be applied to the development of higher performance LREs necessary for future space development programs such as Korean Small Launch Vehicles(KSLV) In this paper, the development of KRE-III LRE system is described including its design, analyses. performance tests and evaluation.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2002.11b
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• pp.250-254
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• 2002

It is conducted to analyze vibration loads on KSR-III(KSR: Korea Sounding Rocket) and its major segments during their ground transportation and various handling process. These loads may be different from the real flight environment. Inadequate assessment of these loads can cause not only local damages on the rocket system but also the critical problem like flight mission failure. Therefore, transportation and handling loads must be considered during design and attenuated to ensure that the rocket structural damage does not occur. This work is concerned with the generation of criteria and prediction of transportation and handling loads for KSR-III. The results show that the shipping container is well designed to satisfy the design requirements. The maximum vibration level recorded during whole transportation and handling for KSR-III is less than 2g, the criteria of KSR-III movement condition.

• Aerospace Engineering and Technology
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• v.1 no.1
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• pp.128-134
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• 2002

Outer surfaces of KSR-III are insulated to protect outer structure and inner payloads from the aerodynamic heating. The characteristics of insulation material (BMS 10-102), selected through careful tests and thermal analyses, are low heat transfer rate and low density. It is applied in a wet and continuous spray pattern for outer surfaces of KSR-III. In the present study, the honeycomb sandwich structure of nose fairing, which is one of the typical multi-layer structures of KSR-III, is thermally analyzed with insulation.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.105-114
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• 2003

It is conducted to analyze vibration loads on the 1st stage of KSR-III(KSR : Korea Sounding Rocket) during their ground transportation and various handling process. These loads may be different from the real flight environment. Inadequate assessment of these loads can cause not only local damages on the rocket system but also the critical problem like flight mission failure. Therefore, transportation and handling loads must be considered during design and attenuated to ensure that the rocket structural damage does not occur. This work is concerned with the generation of criteria and prediction of transportation and handling loads for KSR-III. The results show that the shipping container is well designed to satisfy the design requirements. The maximum vibration level recorded during whole transportation and handling for KSR-III is less than 2g, the criteria of KSR-III movement condition.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.1
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• pp.81-84
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• 2004

A water-cooled calorimeter chamber with 8 cooling channels based on KSR-III sub-scale chamber has been designed and manufactured. One dimensional empirical correlation has been used at the design stage and full three-dimensional CFD analysis has been conducted to confirm the cooling condition for hot fire test is safe. Predicted heat flux is accurate around the nozzle throat when the thermal resistance of carbon deposit is considered. However relatively large difference is observed in chamber part.

• 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 KIEE Conference
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• 2000.11d
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• pp.721-723
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• 2000

국내 과학관측 로켓(Korea Sounding Rocket-III; 이하 KSR-III) 발사통제 시스템 개발 중 로켓 임무 달성에 필요한 시스템 구성과 제작에 대한 전반적인 설계내용을 기술하였다. 로켓 임무와 설계 요구 조건에 의해 각 통제 콘솔과 발사 상황판은 설계되었고 현재 제작 중에 있으며. 향후 KSR-III 발사시험 시 활용 할 계획이다.

• Proceedings of the KIEE Conference
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• 2002.07d
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• pp.2662-2664
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• 2002

액체추진 과학로켓으로 개발되고 있는 KSR-III(Korea Sounding Rocket-III)의 발사통제시스템의 개발에 관하여 기술하였다. 발사통제시스템은 장기간에 걸쳐 개발된 로켓을 발사시키는데 필수적인 시스템으로서 신뢰성과 강인성이 최대한 요구된다. KSR-III 발사통제시스템의 하드웨어는 콘솔, PLC, 신호분배기, DAS로 구성되어 있으며 소프트웨어로서 HMI 및 DAS 제어프로그램이 있다.