• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.89-89
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• 2003

로켓엔진의 연소에 필요한 추진제를 안정적으로 공급하기 위한 추진제 공급시스템의 주요 구성과 설계 주요 인자를 정리하였다 공급시스템은 추진제 주입/배출 장치, 추진제탱크 가압 및 배기 장치, 추진제 공급 주/분기 배관, 극저온 산화제 온도 유지 장치 등으로 구성되어 있다. 주요 설계 제한 조건으로는 터보 펌프 입구에서의 추진제 압력 및 온도, 필요 추진제 공급 유량 및 온도 그리고 추진제 충진 및 비상 배출 허용 시간 등이며 이는 각 로켓의 해당 임무에 따라 적절히 결정된다. 발사체로부터 할당된 중량값 이내에서 고신뢰도의 작동성, 안정성이 보장되는 시스템을 설계하여야 하며 초기 설계 단계에서 개발 및 수급 가능성을 동시에 고려하여야 할 것이다. 또한 고추력 생성을 위해 엔진 클러스터링이 수행되어야 할 경우 각 엔진으로의 균등한 추진제 배분 공급이 설계의 중요한 요구 조건이 된다. 이러한 공급시스템의 개념은 액체산소와 케로신 조합의 액체 로켓인 100kg급 소형 위성 발사체(KSLV-Ⅰ)에 적용될 예정이다.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.154.2-154.2
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• 2012

액체로켓엔진 조립을 위한 엔진 조립장이 국내에 구축되어야 하며 이에 대하여 국내의 사례가 없으므로 해외 엔진 조립장의 사례를 조사하였다. SNECMA, EADS, Rocketdyne 등의 조립장의 구조, 레이아웃, 청정설비, 크레인 등을 조사하였다. SNECMA 엔진조립장은 Vulcain 엔진의 대형엔진 조립라인 및 HM7, Vinci 엔진 등의 소형엔진 조립라인으로 구성되어 있다. 청정도는 코어 및 Subassembly 조립실은 100 K class 이며, 기타 나머지 조립공간은 300K class로 구축되어 있다. EADS의 엔진 조립장은 중앙에 연소기 부품을 가공하는 가공장비들이 배치된 하이베이 구역이 있으며, 이 하이베이 구역의 측면에 사무실, 측정실, 회의실 등의 로우베이 기능실들이 배치되어 있다. Rocketdyne 엔진 조립시설은 청정도 300K class이하의 엄격한 청정도 관리가 없는 것으로 보이며 치구형태의 개별 플랫폼을 사용하여 공간 활용을 효율적으로 할 수 있도록 하고 있다.

• 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 of Propulsion Engineers Conference
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• 2008.05a
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• pp.125-128
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• 2008

Atomization characteristics of small LRE-injector spray are investigated by using dual-mode phase Doppler anemometry (DPDA). Velocity, size, number density, and volume flux were measured at various injection pressures along the radial distance to make a close inquiry into spatial distribution characteristic of spray droplets. As the injection pressure increases, the velocity, turbulence intensity, number density, and volume flux of spray droplets become higher, whereas the droplet size ($D_{10}$ or $D_{32}$) gets smaller. Also, velocity and volume flux are proportional to Sauter mean diameter (SMD, $D_{32}$).

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.5
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• pp.1-8
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• 2008

Dual-mode Phase Doppler Anemometry (DPDA) was used to scrutinize the spatial distribution characteristics of spray emanating from a small Liquid-Rocket Engine (LRE) injector. Droplet size and velocity were measured according to the variation of injection pressure along the plane normal to the spray stream and then the spray characteristic parameters such as Arithmetic Mean Diameter (AMD), Sauter Mean Diameter (SMD), number density, span of drop size distribution, and volume flux were deduced for an investigation of spray breakup characteristics. As the injection pressure increases, the number density, span, and volume flux of spray droplets become higher, whereas the AMD gets smaller.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.498-501
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• 2012

The Model Rocket Engine Test Facility has been improved to develop the Korea Space Launch Vehicle II(KSLV-II). The modified Model Rocket Engine Test Facility will be used to develop 7-tonf class liquid rocket engine combustor. The test result and test technique acquired from this facility will be used to develop the high performance liquid rocket engine combustor. This paper describes the modified Model Rocket Engine Test Facility for a Sub-scale model test of the 7-tonf class combustor.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.4
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• pp.277-285
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• 2022

There has been significant increase in demand of launch opportunities from the small satellite sector that represents the new space era. Providing smallsat-dedicated launch service at an affordable price is a new business model many startup companies have pursued, which requires innovative solutions for cost reduction in combination of low cost components, volume production and optimized manufacturing. We set out a preceding study at KARI to develop a suite of critical and cost-cutting technologies in preparation for a two-staged small launch vehicle development, based on the liquid rocket engine technologies developed from the Nuri program in accordance with the 3^rd master plan for national space development. In this work, we introduce the concept of a two-staged small launch vehicle that aims to be innovative and cost competitive for small satellites, and describe mission design results including staging as well as overall vehicle configuration of the launch vehicle.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.11a
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• pp.209-212
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• 1996

접촉발화성 액체추진제를 사용하는 소형 추진기관의 성능을 확인하기 위해 핵심 부품의 상온 성능 시험 및 추진기관 조립품의 연소성능시험을 실시하여 추력 400 파운드급의 로켓엔진의 설계성능을 확인하였다. 로켓엔진의 성능측정은 요소분사기의 미립화, 혼합성능의 측정을 위한 상온수류시험과 추진기관 조립체의 지상연소시험으로 실시하였으며, 연소성능은 산화제로 질산을 연료로는 아민계 혼합물로 구성된 접촉발화형 이원 액체추진제를 사용하여 가압방식에 의해 연소실에 분사하는 방법으로 수행하였다. 성능시험결과는 설계성능 및 이상성능과 비교함으로서 이들의 상관관계를 파악하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.6
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• pp.71-75
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• 2005

An experimental study was carried out to investigate the effect of film cooling in the lab-scale dump-cooled liquid rocket engine using LOX and kerosene as propellants. The nozzle of the rocket engine was film cooled with water as coolant. A special film cooling adapter was fabricated to introduce the film-coolant into the thrust chamber. The flow rates of film coolant was approximately 15~19 percent of the total propellant. The nozzle heat flux was determined from the measured temperature rise and flow rate of the coolant(water). Large reductions in the nozzle heat flux was resulted when film cooling adapter located directly upstream of the nozzle.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.507-510
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• 2009

The small size of hybrid rocket using PE-$LN_2O$ was designed, constructed and launched for a development basic technology of Hybrid rocket vehicle. The hybrid engine ignition system was designed with valve system using external actuator and confirmed working without any fault. To design fuel grain an internal ballistics design was carried out, and to estimate rockets flight path an external ballistics analysis was carried out. So the rocket was designed and constructed, and the launch test proves that hybrid rocket's design was suitable. The hybrid rocket(weight : 9kg, diameter : 110 mm, height : 1.7 m) was launched successfully. But parachute was deployed on mid-flight and the mission could not finish its purposed flight. Some of problems were found in this activity but next launch vehicle will be improved.