• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.4
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• pp.12-20
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• 2017

The ablation characteristics of graphite nozzle throat insert was analyzed for the use in solid rocket propulsion system. The propulsion system was composed of three types of conventional nozzles, such as De-Laval type, blast tube type, and submerged type. Various kinds of propellants were used in ten kinds of propulsion system that had different shapes with each other. Total forty eight tests were performed. From the results of the analysis, it was found that the ablation rate was increased for the higher average chamber pressure and the higher oxidizer mole fraction. A useful correlation for nozzle throat ablation rate was developed in terms of the chamber pressure, oxidizer mole fraction, and throat size. The calculated ablation rates from the correlation showed agreement within ${\pm}0.10mm/s$ with the experimentally determined values.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.203-207
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• 2005

An experimental study was carried out to investigate the effect of film cooling in the thrust chamber of liquid rocket using LOx and Kerosene as propellant. The heat fluxes were obtained from the measured wall temperature to the axial direction of thrust chamber for different type of coolant, the various O/F ratio, mass flow rate and the location of the film cooling injector. A thin wall combustion chamber and nozzle were used to obtain the heat flux.

• Journal of the KSME
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• v.28 no.2
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• pp.99-105
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• 1988

우리나라의 과학기술발전을 선도하는 중추적, 핵심적인 국책연구개발사업(national R '||'&'||' D project)d이라 할 수 있는 특정연구개발사업은 지난 82년에 시작된 이후 금년 들어 시행 7년째를 맞아 본격적인 성숙기에 접어들고 있다. 그 동안 본 사업은 과학기술처를 중심으로 관련부처의 적극적인 협조와 산. 학. 연의 긴밀한 협동연구체제아래 국가장기발전계획의 목표구현에 부응하 고 당면한 경제. 사회적 요구에 대응하기 위한 기술개발을 추진해옴으로서 기술개발을 통한 제품의 경쟁력 제고, 생산성 향상 및 국제수지개선효과 등 경제적 기여는 물론 산업계의 연구분 위기를 활성화하고 기술개발에 대한 자신감을 고취하는 등 기술개발의 기반을 조성하는 데도 크게 기여하여 왔다. 아울러 앞으로도 국가연구개발사업의 선도적 위치에서 우리의 과학기술 장기발전 목표인 "세계 10위권 기술선진국 구현"을 실질적으로 뒷받침하는 핵심 역할을 담 당해 나갈 것이다. 여기서는 그 동안 과학기술처가 중심이 되어 추진해오고 있는 특정연구개발 사업에 대한 추진실적을 간단히 살펴본 다음 88년도 추진방향을 중점적으로 기술함으로써 기 계학회 여러 회원들의 이해를 도모하는 한편 향후 동 사업에 적극적인 협조와 조언을 모색해 나가고자 한다.다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.489-492
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• 2012

Basic design result for propulsion system test complex(PSTC) of KSLV-II is briefly described. KSLV-II is a three stage launch vehicle will be used liquid rocket engine for each. PSTC is will be used for development and performances qualification tests of $1^{st}/2^{nd}/3^{rd}$ propulsion systems for KSLV-II. In the future, this result will be applied to critical design and manufacturing of PSTC after deciding lay-out and operating program.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.1
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• pp.33-45
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• 2019

In this study, numerical simulations were performed to investigate the steady-state characteristics of a symmetric pintle nozzle by varying the position of the pintle and the altitude. The pintle nozzle shape was used in a linear pintle nozzle that had been analyzed prior to the study, and the boundary conditions of the chamber were considered to be according to the propellant burn-back characteristics. A software was used to perform a verification analysis of the square nozzle, pintle nozzle, and high-altitude conditions with an appropriate analytical technique. The pintle position had three different nozzle throat area conditions-: fully closed, half open, and fully open, and the altitude was set at 0, 5, and 20 km. The study compared the thrust, pintle drive load, and static stability at each condition.

• Korea Petroleum Association Journal
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• no.1 s.11
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• pp.43-45
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• 1982

석유위기가 또다시 올 것에 대비할 필요성은 상존하고 있다. 이러한 인식과 준비없이는 제2의 경제도약은 생각할 수 없다. 따라서 석유기업들은 우선 중화학공업 육성이라는 국가적 차원에서의 지원체계에 포함되어 주요산업으로서의 위치와 책임을 공유할 수 있어야 할 것이다. 또한 전략적과제를 추진할 수 있는 재투자재원의 확보, 경쟁력을 구축할 수 있는 수익성의 실현, 가격정책 및 주요경영정책상의 자율성확대가 불가피하게 요청된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.147-150
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• 2006

The influences of injection conditions and recess configuration of liquid-liquid swirl coaxial injector on spray characteristics were investigated. The characteristics of the coaxial spray in internal mixing injection region were mai y controlled by the merging phenomenon and momentum balance between two liquid sheets, but those in internal mixing injection region were influenced by the impingement phenomenon as well as momentum balance between two liquid sheets.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.107-110
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• 2009

A basic design for a Technical Development Model (TDM) of liquid oxygen lines from the turbopump exit to the oxidizer valves of the combustion chamber and the gas generator was conducted to develop a turbopump-fed liquid rocket engine. The TDM is composed of straight lines, elbows, bellows, a branch, an orifice, flanges and a heat insulator. Materials were determined by consideration of operation conditions, weight constraint and manufacturing procedures. The size and the location of each component were determined by flow analysis of the required flowrate and the pressure loss. Basic designs of the components were conducted by consideration of the operating temperature and the maximum expectation operating pressure. The safety factors were evaluated by structural analysis of design of each component.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.3
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• pp.1-8
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• 2006

The influences of injection conditions and recess configuration of liquid-liquid swirl coaxial injectors on spray characteristics were investigated. The characteristics of the coaxial spray in internal mixing injection region were mainly controlled by the merging phenomenon and momentum balance between two liquid sheets, but those in internal mixing injection region were influenced by the impingement phenomenon as well as momentum balance between two liquid sheets.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.814-819
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• 2017

The objective of this paper is to observe effects of an ignition position and time on the ignition transition. A gaseous oxygen and liquid kerosene are used for propellants with the shear-coaxial injector. In order to study the ignition delay time and combustion instability intensity, the pressure transducer was used. The ignition position was changed with the injector spacer. Sequences except the igniter operation time were fixed to compare the ignition time only. Initial pressure peak and ignition delay time increased as the ignition time was delayed. Also, the unstable flame development zone was detected as the igniter was away from the injector.