• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.3
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• pp.52-59
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• 2001

In this study, a technique has been developed to analyze the performance of the launching system using a gas generator of solid propellant. The physical model which described the thermodynamic behaviors of all launching devices from gas generator to canister and the dynamic behavior of missile was established, applying the empirical coefficients in the heat loss model. The processes of combustion, flow, and heat transfer inside the chamber of gas generator and the launching system were simulated by numerical method. The theoretical analysis guided the optimal design of gas generator and system, which made the launching system satisfy the requirements of good performance and high reliability.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.676-677
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• 2010

In Naro Space Center, Naro launch vehicle launched 2 times. Launch pad for Naro launch vehicle in Naro space center equipped propellant feeding facility for operating launch process. This paper studied development process and operating method for liquid oxygen filling system of cryogenic propellant systems in launch pad propellant feeding facility.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.187.1-187.1
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• 2012

본 논문은 저궤도 위성의 각 유닛의 온도 정보를 획득하기 위해 사용되는 온도 센서인 써미스터의 data 처리를 위한 calibration 방법을 정리한 것이다. 써미스터는 온도에 따라 저항 값이 바뀌는 소자이며, 위성 프로세서는 정전류 소스를 공급하고 여기에 걸리는 전압을 AD converter를 이용해 데이터로 전송한다. 지상에서는 전송된 데이터를 calibration 공식에 대입하여 온도 정보를 얻어낸다. 특히 발사 준비 및 발사 후 발사체와 분리되기 전까지 계속 모니터링이 필요한 배터리 온도 정보의 경우 배터리 내부의 한 개 써미스터에 대해 발사장전기시험장비와 발사체의 MUX 시스템 그리고 위성 내부 프로세서에서 프로세싱이 동시에 이루어지기 때문에 각 시스템의 영향성까지 고려해야 한다. 본 논문에서는 저궤도 위성의 열진공 시험 및 발사 동안의 실제 데이터 처리 결과를 통해 정밀한 써미스터 데이터 처리 및 그 시스템 설계에서 고려해야 할 점들을 정리한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.12
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• pp.83-91
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• 2005

Air-Launching is an effective method that can launch the 'Nanosat' with low launching cost. In this study, system and subsystem design of the air launching rocket for nanosats which perform a simple mission, have been performed. For this purpose, the WBS of the MIRINAEⅡ, and the subsystem schematics have been defined first. Based on these results, detailed configuration and DMU have been developed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.66-68
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• 2011

Chollian is a geostationary satellite, and its bipropellant propulsion system is mainly composed of one main engine for orbit transfer and fourteen thrusters for on-station operations. The Chollian was launched successfully at Kourou Space Center in French Guiana. After it separated from the launcher, the propulsion system was initialised automatically. Then three times of main engine firing were successfully performed, and the target obit insertion was accomplished. This paper details the major CPS events during LEOP phase for the Chollian satellite.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.99-105
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• 2006

A Launch vehicle which consists of many sub-systems is one sophisticated huge system. A lot of experience and system integration technique are needed for the launch vehicle to accomplish a mission successfully. The characteristics and complexity in the development of the launch vehicle depend on the size of that. However the systematic work flow is similar to each other. This paper introduces a standardized development process which is based on the whole program life cycles and experiences of NASA on the development of the launch vehicle. The development process can be categorized into 10 phases through the life cycle of the launch vehicle.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.2
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• pp.73-80
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• 2015

It had been almost a half century since Apollo Mission was ended. However, in these days, a lot of researches are being conducted for restoration and making improvements in technologies used in Saturn V rocket's development. This study reviews the first stage of Saturn V rocket(S-IC), from development history to technologies in various subsystems such as engine purge system, POGO suppression system, hydraulic and pneumatic control system, propellant dispersion system, telemetry system and retrorocket system. Understandings of S-IC stage's operation systems would be helpful in understanding of launch vehicle system and reduction of time and cost in future development process.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.9
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• pp.41-47
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• 2005

Conceptual design process is defined for the air-launching rocket by including analysis modules like mission analysis, staging, propulsion analysis, configuration, weight analysis, aerodynamics analysis and trajectory analysis. As a result of the conceptual design, the supersonic(M=1.5) air-launching rocket with hybrid engine for first stage propulsion system is designed. For the best system alternative selection, trade study for the 1st stage engine type and launching speeds using sequential optimization and confirming feasibility of baseline air-launching rocket has been performed. As a result of trade study, all alternatives are competitive in total weight and show only small difference in total weight per unit payload weight. Therefore, it is confirmed that the baseline air-launching rocket which has advantage in system safety especially in supersonic launching is feasible.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.656-657
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• 2010

The ground oxidizer supply system in the launch site of NARO space center had operated 9 times from the start of tests with ILV on May, 2009 to the 2nd flight test of the NARO vehicle. This system operated successfully for twice launches of the NARO vehicle. To judge the successful operation of the ground facility, it should have reproducibility and reliability. In this report, we have analyzed the liquid oxygen consumption of the system to judge of its reproducibility and it can be a reference for using this system for the next generation of KSLV system.

• Proceedings of the KIEE Conference
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• 2002.07d
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• pp.2656-2658
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• 2002

로켓과 지상장비의 각 모듈 사이에서 교환되는 데이터와 제어 정보, 상호작용 등을 정확하게 기술하기 위해 UML 객체 지향 방법을 이용해서 로켓 발사시스템을 모델링한다. 이렇게 만들어진 상위레벨 객체 모델을 기반으로 해서 발사통제 시스템에서 지시하는 명령들의 시퀀스로서 발사 시나리오를 구성한다. 본 논문의 UML 객체 다이어그램과 발사 시퀀스 다이어그램은 로켓과 지상장비를 운영하고 통제하는 다양한 작업에 유용하게 사용될 수 있다.