• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.7-7
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• 2000

과거 로켓엔진의 개발은 군사적, 혹은 국가 간 기술 선점을 목적으로 그 개발이 이루어져 왔으나, 최근에는 인공위성 발사, 대기관측 등 상업적 목적에 의한 개발이 두드러지고 있다. 이와 같은 상업적 로켓 개발에 있어서는 신뢰도와 경제성이 가장 중요한 요소이다. 한국항공우주연구소에서 개발중인 3단형 과학로켓(KSR-III)의 엔진은 상업적 목적의 인공위성 발사를 목표로 하여, 엔진 시스템의 단순화를 통한 신뢰도 향상과 엔진 제작비용 절감을 통한 경제성을 고려하여 개발되고 있다.(중략)

• Proceedings of the KAIS Fall Conference
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• 2009.05a
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• pp.539-542
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• 2009

본 연구은 자동차용 가솔린엔진에 장착되는 인젝터의 연료공급 특성에 대한 것으로, 4홀과 12홀 인젝터의 분무질량분포, 벽류 및 가시화 실험을 수행하였다. 분무질량분포 실험을 통하여 인젝터 별 분무특성을 파악하고, 벽류측정실험을 통하여 흡기포트내의 연료 Wetting 특성을 확인하였다. 가시화실험을 통하여 분사각과 분무특성을 비교 분석하였다. 4홀과 12홀 인젝터의 분무특성비교를 통한 각 인젝터의 연료공급 특성분석은 가솔린엔진 설계시 기초자료로 활용될 수 있을 것이다.

• Clean Technology
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• v.12 no.2
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• pp.78-86
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• 2006

Computational analyses are conducted on the combustion characteristics of the coal- and the biomass-derived synthetic gases with low-Btu heating value in gas engine. Using thermochemical analyses on the synthetic gases, combustion pressure, temperature, exhaust gas composition, NO emission and engine power are predicted and the predicted results are compared with small-scale pilot engine test results. In order to investigate the unsteady combustion phenomena in gas engine combustion chamber, CFD analyses are carried out on the coal and the biomass synthetic gases and their computed results are compared to provide the guidelines for the design modification and the tuning of the gas engine burning the synthetic gases as alternative fuels.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.35-38
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• 2007

Aiming at time-dependent performance prediction of Liquid Rocket Engine(LRE) system, Modular Program for Conceptual Design of LRE is reviewed, and a modeling and dynamic analysis of rocket engine system with reference to Rocket Engine Dynamic Simulator(REDS) is outlined. Component modeling is based on classical thermodynamic and inviscid theories, and were formulated mathematically in terms of essential parameters. Essential design parameters are addressed. The rocket engine is modeled as a system of pipes with various hydraulic elements, and then the operate characteristic of that elements are simulated by solving conservation equation sequentially.

• Journal of Aerospace System Engineering
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• v.18 no.1
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• pp.46-52
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• 2024

Engine test cell should provide controlled test environment to properly verify requirements of engine performance and operational characteristics. However, since test cells cannot be perfectly identical to each other, new test cell requires processes to verify reliability of test results and correct differences through correlation testing using a baseline test cell. This paper studies about what should be considered when correlation testing is performed based on commonalities and differences between turbofan and turboshaft engine. It provides examples of correlation test procedure. In the future, it is expected that this study will help set up a standard that can certify test facility according to engine type.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.239-242
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• 2004

In this paper, the general mathematical model of LRE(Liquid Rocket Engine) is presented. For the analysis about the trend of dynamics and the stability of open type LRE, it is transformed to linear model by Laplace transform and synthesized to the linear complex model of LRE with Matlab/Simulink.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.750-755
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• 2011

The ignition characteristics of liquid rocket engine thrust chambers which have been developed by domestic technology were analyzed. Analysis results showed that low frequency fluctuation appeared in a partial ignition range according to different temperature profiles and vaporous state in the oxidizer manifold with startup sequences. This low frequency fluctuation wasn't developed as a malfunction factor, but this fluctuation is thought to be taken a continuous concern considering interfaces with engine system and launch vehicle.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.34-37
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• 2010

One dimensional transient analysis was studied for turbopump-fed liquid propellant rocket engine(LRE) system in starting using AMESim. The effects of timing of gas generator fuel valve opening and gas generator ignition to start-up stability were researched for open cycle type system using LOX/RP-1 to propellants. Result show that the parameters and sequence on start-up should be considered to design optimized turbopump-fed LRE system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.189-192
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• 2004

Test Facility for hot firing test of small size liquid rocket engine has been developed to research the cooing characteristics of kerosene for cylinder part especially. Propellants for the tests are kerosene and liquid oxygen as fuel and oxidizer respectively and they are fed by gaseous nitrogen. The engine components used hot firing test except for cylinder are cooled by tap-water. Valves for supply of propellants and coolants are controlled by pneumatically. System control and data recording are conducted automatically.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.235-238
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• 2004

In the present study, the stability of turbopump through the rotor dynamics was analyzed with the location analysis method of the pole of characteristic equation for stability analysis of LRE and the design guideline for turbopump was presented according to design requirements of the LRE.