• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.1
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• pp.56-64
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• 2010

A system design has been conducted of the liquid rocket engine for Korean launch vehicle (KSLV-II, Korea Space Launch Vehicle II). The present turbopump-fed liquid rocket engine of vacuum thrust 76 ton and vacuum specific impulse 297 sec adopts gas generator cycle. The combustion pressure of the regeneratively cooled combustor is 60 bar. The propellant is LOx/kerosene. The engine is started by pyrostarter and the combustor is ignited by TEA (TriEthylAluminium). The engine system performance and the subsystems performance requirements are given through energy balance analysis. The combustion pressure, specific impulse and the engine mass are analyzed to be reasonable comparing with the published data. The startup analysis method which will be used in the future has been validated against the turbopump-gas generator coupled test. The tuning method for performance variation of the engine which is not actively controled has been prepared by mode analysis and performance deviation analysis.

• Journal of Korea Technology Innovation Society
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• v.15 no.1
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• pp.163-184
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• 2012

Although there are some technical reports on the example of Korea's first rocket, the Naro, there has been no studies on why there were two technical incidences in the space development programs which massive amount of physical and human resources were invested. For this, the objective of this study is to investigate the example of the Naro from the aspect of management and institutions as well as technical in terms of the responsibility of the R&D organization. Most important part in the responsibility of the R&D organization is the professional responsibility and it is difficult to attain the goals when they are diluted by political situations. Furthermore, this study also looked at the cause of the failure to exert righteous sovereign authority in the conflict with Russia from the discrepancy of goals between the authority and the agent, and studied efforts to prevent the recurrence of discrepancy.

• Journal of Aerospace System Engineering
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• v.4 no.1
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• pp.1-9
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• 2010

As the rocket KSLV-1 called NARO was launched lately, development of domestic rocket technology has been accelerated elastically. Since the rocket technology needs a lot of empirical data, a variety of experiments should be done and lots of time have to be spent for accumulating the foundation of technology. However using a computer can be the solution to close a gap of technique because the simulation can be executed in short time against real experiments and calculate a multiplicity of cases easily. In this research, the transient analysis of turbopump-fed liquid rocket system was worked by the one dimensional modeling. The rocket system consists of the modulized components that are engine, turbopump and so on. For 70 ton class system, the rocket transient process of starting was studied and the performance analysis in steady condition was achieved. In addition, the estimation of nozzle internal flow was investigated by using a nozzle coefficient.

• Current Industrial and Technological Trends in Aerospace
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• v.4 no.1
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• pp.25-33
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• 2006

대한민국의 다목적 실용위성(아리랑 2호, KOMPSAT 2)가 2006년 7월 28일 금요일 러시아 플레체스크 우주발사장에서 발사되었다. 대한민국에서는 그동안 우리별 위성 시리즈, 과학위성 시리즈, 무궁화 위성 시리즈, 다목적 위성 시리즈, 과학 로켓 시리즈 및 우주발사체(KSLV-1)를 개발했거나 개발 중이다. 이러한 과정은 국가우주개발중장기 기본계획에 의하여 진행되고 있는데, 원하는 기간 내에 합리적 비용으로 목표를 이루고자하는 상황에서 우리가 본 받을만한 국가를 선정하여 모델로 삼는 것이 타당할 것이다. 이러한 필요 가운데 비교적 벤치마킹 대상으로 삼을만한 국가로 이스라엘이 부상하고 있다. 따라서 본 논문에서는 비교적 잘 알려지지 않았지만 우리가 벤치마킹의 대상으로 고려하는 이스라엘의 우주개발 역사를 살펴봄으로써, 우리나라의 우주개발 분야에 참고가 되고자 한다.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.162.1-162.1
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• 2012

한국형 달 착륙선의 안전하고 효율적인 달 착륙을 위해 임무 시나리오 시뮬레이션을 수행하였다. 달 착륙은 보통 두 가지 방법이 사용되는데, 지구에서 출발하여 달에 도착한 후 달착륙지에 직접 착륙하는 방법과 달의 주차궤도를 돌다가 달 착륙지에 착륙하는 방법이 있다. 미국의 Surveyor호는 직접 착륙 방법을 사용하였고 아폴로 시리즈는 달 궤도를 공전하다가 착륙하는 방법을 사용하였다. 본 연구에서는 두 가지 방법을 모두 사용하여 착륙 임무 시나리오를 시뮬레이션을 수행한 후 장단점을 비교분석하였다. 달 주차궤도를 이용한 착륙은 달고도 100km에서 공전을 하다가 고도 15km까지 하강한 후 Powered descent 단계를 통해 착륙지에 착륙하는데 Powered descent 단계는 다시 감속단계, 접근 단계, 최종 하강 단계로 나뉘어진다. 달 착륙선은 나로우주센터에서 KSLV-2에 실려 2025년에 발사되며, 달 착륙지는 달의 과학적 임무를 고려하여 달 남극 근처로 가정하였다. 달 착륙 시뮬레이션을 통해 달 착륙선의 비행 궤적과 필요한 연료량 계산 등의 정보를 통해 직접 착륙 방법과 달 주차궤도를 이용하는 방법의 장단점을 확인할 수 있었다.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.4
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• pp.104-111
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• 2019

Staged combustion cycle engines exhibit higher combustion performance compared with open cycle engines with a gas generator. An advanced research of the staged combustion cycle engine is going on for the next program following the KSLV-II program. Various experiments have been carried out for the technology demonstration model, TDM0A and TDM0B. The experiments on the combustion performance are aimed to understand the engine start condition and combustion characteristics. They also aim to develop the oxidizer-rich pre-burner and the combustor of the staged combustion cycle engine. The engine-shaped model, TDM1A is fabricated based on the experimental data. The combustion experiment of the TDM1A shows that the combustion pressure of the combustor is approximately 91 bar and the turbine rotation is approximately 28,00 rpm. The result is stable and satisfies the development requirements. The present paper reports on the development process and characteristics of engine models from TDM0A to TDM1A.

• The Optical Journal
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• s.121
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• pp.23-27
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• 2009

1980년 말에 시작한 우주개발에 참여한 우리나라는 약 20년이라는 짧은 시간 동안 급속하게 기술축적을 하여 위성체 개발 기술을 상당부분 보유하게 되었고, 오는 7월이면 KSLV-1의 발사를 통하여 우주진입 기술 확보도 시작하게 될 것으로 기대되고 있다. 과학기술위성 3호 영상분광기 코미스(COMIS)는 개발 과정도 하나의 목표로 취급되고 있어, 모든 개발 과정이 100% 국내에서 이뤄지고 있다. 특히, 광학 소자의 가공 및 평가에 국내 민수 광학 업체들이 참여하고 있다. 광학 업체의 위성탑재체 개발 참여를 통한 매출 증가는 아직 미비하지만 이를 통하여 초정밀 초청밀 가공 및 평가 기술, 초경량화 및 신소재, 환경평가 기술들을 확보하는 계기로 판단하여 적극적인 참여의지 표시가 필요할 것으로 보인다.

• Journal of the Korean Society of Systems Engineering
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• v.2 no.1
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• pp.54-60
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• 2006

LCC(Launch Control Center) in NARO space center performs a data monitoring and control through the interface to the external system of launch vehicle. Launch control function needs high reliability and processing speed. Hence, LCS(Launch Control System) is made up a real time system. An important role of the LCS Prototype is discovering a risk element and minimizing it through developing a launch control system. This paper deals with a real time data processing among the simulator, gateway, data distribution server, command and control server which is involving LCS Prototype.

• Journal of Aerospace System Engineering
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• v.9 no.4
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• pp.67-72
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• 2015

The analysis has been performed on the blockage effect at the propellant flow passage in a liquid rocket engine. This simulates an example of emergency situation where flow passage is partially blocked. The analysis method has been validated by predicting the pump head and flow rate within 1% precision against the measured data of turbopump-gas generator coupled test. When the oxidizer passage is reduced it is predicted that the mixture ratio decreases, the oxidizer pump head increases and the gas generator pressure increases. When the fuel passage is reduced it is predicted that the mixture ratio increases, fuel flow rate decreases and the fuel pump head increases.

• Proceedings of the Korea Society for Simulation Conference
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• 2005.05a
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• pp.106-111
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• 2005

LCC(Launch Control Center) in NARO Space Center perform a data monitoring and control through the interface to the external system of launch vehicle. Launch Control function needs a high reliability and processing speed. Hence, LCC's remote control system configure a real time system. An important role of the Simulation system is discovering a risk element and minimize it When developing a launch control system. Also, secure a development technique to solve the risks. Launch Vehicle simulator is composed of various component at characteristic of the Launch Vehicle. To be like this each function component the developer will be able to develop easily in order, it using the LabVIEW which is a Graphical Program and it programs, The LabVIEW GOOP(Graphical Object-orinted Programming) which supports an Object-orinted programming it uses with the Component it develops will have a strong point which reusability and a unit test, maintenance, size of program and individual developments.