• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.71-71
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• 2004

KSLV-I 추진기관 기체공급계는 상부의 산화제 탱크로부터 나온 산화제 주배관이 하부의 연료탱크를 관통하여 엔진공급계로 이어지도록 구성되어 있다. 연료탱크에는 산화제 배관의 관통을 위한 tunnel이 구성되어 있으며 배관과 tunnel은 일정한 간격을 유지하게 된다. 배관과 연료탱크 사이의 열전달을 줄이기 위하여 산화제 배관에 단열재를 적용할 수 있으나, 이 경우 배관의 운송, 조립시에 handling이 힘들게 되고, 특히 발사체에 조립된 후에 발생하는 단열재의 파손 및 성능감소에 대한 유지보수가 불가능하다. (중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.33-36
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• 2009

This study suggests manufacturing and cleaning the feeding system of hydrogen peroxide to use oxidizer of liquid rocket. We established the process of cleaning and passivation in order to minimize the pollution of Hydrogen Peroxide feeding system. And, we verified stability of the manufactured feeding system by leak test & hot test.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.2
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• pp.63-70
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• 2010

A construction process of hydrogen peroxide supply system was investigated to use hydrogen peroxide as an oxidizer of bi-propellant liquid rocket engine. To use hydrogen peroxide as a rocket propellant, it has to be in high concentration over 90%. It is very important to make the supply system free of pollutants, because highly concentrated hydrogen peroxide has a characteristic of hypersensitive reaction to pollutants such as dust and oil sludge. We suggested the cleaning and passivation process of main components to minimize pollutants of the supply system. In conclusion, we verified stability of the constructed supply system by leak test and hot test.

• Aerospace Engineering and Technology
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• v.10 no.1
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• pp.79-88
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• 2011

A fill-drain valve is operated by provided control gas at the ground for liquid propellant feeding system of space launch vehicle, which fills or drains on-board propellant tanks with a cryogenic oxidizer. We have analyzed and modified the data of fill-drain valve designed by Yuzhnoye. The simulation model of fill-drain valve is designed by using the AMESim code to predict and evaluate the dynamic characteristics and pneumatic behavior of valve. In this study, we performed a dynamic characteristic simulation on design parameter. And we could predict opening/closing time and pressures, operating performances on design parameters. This study will serve as one of reference guides to enhance the developmental efficiency of fill-drain valves with the various operating requirements, which shall be used in the Koreanized Space Launch Vehicle.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.3
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• pp.45-52
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• 2002

This article deals with the introduction of longitudinal instability of liquid rocket (pogo) and the analytical results on the frequency responses of Korean Sounding Rocket (KSR-III) propulsion feeding system. Both the stiffness of bellows and the cavitation volume of venturi affect the frequency response of the feeding system. Especially, bellows has a great roll to reduce the natural frequency of the feeding system. Also, oxidizer and fuel feeding systems of the KSR-III have natural frequencies of about 280Hz and 90Hz, respectively.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.14-20
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• 2017

In this paper, KSLV-I flight test data and critical design results of filling operation for liquid oxygen filling system are compared to validate the reliability of the critical design modeling. Applying the filling and operation conditions on the critical design modeling, comparison of major flow rates and pressure values between test data and calculation results are conducted.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.122-126
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• 2006

Two types of pressurization system and low weight feeding piping system are developed. With sub-system tests, ullage pressure control performance was verified for 1 step and 2 step pressurization system and the feeding performance of feeding piping system was also verified. The weight of the feeding piping system is low enough for the application of launch vehicle. In addition, LOX conditioning system is developed for avoiding geysering and LOX temperature rise. Integrated performance was verified through integrated on-board feeding system performance tests.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.5
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• pp.107-114
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• 2018

Korea Space Launch Vehicle (KSLV)-I flight test data and the modified 1-dimensional steady state modeling data from the critical design results of the KSLV-II liquid oxygen filling system operation are compared to validate the reliability of critical design modeling. A comparison of major flow rates and pressure values between test data and calculation results are conducted. The relative errors relative to maximum total flow rate for each cooling, filling, and replenishment mode are determined within 6.7%. Calculated pressure values at the outlet of the pump and the inlet of flow control valves are within 5.1%. The pressure at the inlet of the launch vehicle for each operation mode are within the measured pressure range.

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.81-86
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• 2013

This article deals with the manufacturing and performance evaluation on the specimen pipes which have large size diameter and thin thickness. This specimen is for LOX main pipe of KSLV-II propulsion feeding system. The material of specimen is alloy 21-6-9. Alloy 21-6-9 has higher strength and better weldability rather than STS-300 class pipes. We found that the specimen using alloy 21-6-9 satisfied the requirement by pressurization tests.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.6
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• pp.48-55
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• 2009

The purpose of using Gas Generator Oxidizer On/Off Valve(GOV) is to control opening and closing of oxidizer mass flow. This paper describes analytical results of flow and structural properties for four different GOV models, using commercial software such as Fluent(Ver. 6.3.26) and NASTRAN(2005 r.2), PATRAN(2005 r.2). Analytical results show that GOVs could generate 2.3~3.8 kg/s of oxidizer mass flow rate and come up with 1.09~1.42 of safety factor.