• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.68-76
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• 2004

It is essential to develop a transient engine system analysis model for turbopump fed type liquid rocket engine development, especially for deriving engine system test number and conditions. In this study, we proposed a mathematical model of turbopump fed type liquid rocket engine, and inspected transient mode changes around the nominal thrust level of a rocket engine according to variations of trust control valve's opening ratio. To verify the results, we solved the same problem with AnaSyn software from Russia, and concluded that the transient code showed the similar results within $2\%$ with AnaSyn.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.151-156
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• 2003

Liquid rocket engine system is classified into an engine of pressurization and turbo pump type by the way of fuel fed-supporting system. In the KSR-III sounding rocket, an engine of pressurization type was used, but there was lots of technical problems to be solved for a use as the first stage engine of space launch vehicle. So, an engine of turbo pump type was required to be developed to overcome the technical limitation of liquid rocket engine. In this research, the analysis of propellant of Kerosine-LOX and methane-LOX which are noticed as a future propellant was carried out for the purpose of studying the basic characteristics. And to review the basic characteristics of an engine of turbo pump type, among the sizing variant of the space launch vehicle, the ways of injecting a satellite to a direct orbit and transient orbit were discussed in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.147-150
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• 2007

In this study, cooling characteristics of combustion gas were investigated by injecting liquid nitrogen into liquid rocket combustion chamber. A injection ring of liquid nitrogen was installed between a combustion chamber and a mixing chamber which was designed for mixing of combustion gas and nitrogen. At first, a ignition test of liquid rocket engine was conducted to verify a stable combustion process and 10 second combustion tests were successfully conducted. The results showed that combustion gas of LRE could be cooled by using liquid nitrogen.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.6
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• pp.91-97
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• 2011

A test range for a 75tf class gas generator cycle liquid propellant rocket engine is defined. The engine system test range is defined by the performance variation during flight, the dispersion after engine calibration, and additional margin. The component development test range includes the operation range corresponding to the engine system test range and the component performance margin.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.51-56
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• 2011

A test range for a 75tf class gas generator cycle liquid propellant rocket engine is defined. The engine system test range is defined by the performance variation during flight, the dispersion after engine calibration, and additional margin. The component development test range includes the operation range corresponding to the engine system test range and the component performance margin.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.177-180
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• 2006

It is essential for engine design and establishment of test program to assign an appropriate performance range of liquid propellant rocket engine(LRE). The present study surveys the operation and qualification test range of LRE developed in Japan, United States, Europe and Russia.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.157-162
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• 2006

A Liquid Rocket Engine(LRE) ground firing test facility was built in Korea Aerospace Research Institute(KARI) in 2001 to develop the LRE for the first Korean liquid rocket, KSR-III. Around 170 tests were conducted since its establishment until recently by September 2006, and in the meantime, a considerable improvements were made in the capability. This paper describes the outline, conducted tests and operation techniques which have been accumulated through the operation of KARI LRE ground firing test facility.

• Current Industrial and Technological Trends in Aerospace
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• v.8 no.2
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• pp.86-97
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• 2010

This paper treats with the history and current trends in the developments of liquid-propellant rocket engine in Russia and Ukraine which are among world leaders in the technology of liquid rocket engine(LRE). In 1960s formerly the Soviet Union accepted the closed cycle engine for increasing the pressure in the combustion chamber and specific impulse to the maximum. However, since financially difficult times after 1990, they have decreased the cost for the development of new rocket engines. It was achieved by using existing units for new developed engines and minimizing the total number of engines and tests through the reasonable planning in the process for the experimental improvement of LRE. In addition, nowadays international cooperation in supplying LRE for commercial rocket and development of next generation LRE, such as 3 components engines and mathane engines, are proceeding.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.383-387
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• 2008

To design a high altitude test facility for testing liquid rocket engine optimal technical solutions with general understanding about characteristics of engines and test stands, mission of a rocket and the financial aspects of tests are required. In this paper conditions and requirements needed at the stage of conceptual design of high altitude engine test facility were suggested, and preliminary calculations of the sizes of a supersonic diffuser and volume of cooling water were carried out.

• 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.