• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.1
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• pp.76-86
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• 2015

KSLV-II, a new launch vehicle of Korea, requires a new launch complex(LC) for its own and proper launch operations. The new launch complex will be constructed in NARO Space Center neighboring KSLV-I launch complex for maximizing operation efficiency and economic matters. The launch complex consists of three ground support equipments, i.e., mechanical, electrical, and fuel in general. The fuel ground support equipment could be defined as a combination of systems for storage and supply of propellants and gases which are required by a launch vehicle. The compositions, functions and capabilities of fuel ground support equipment are introduced in this paper. In addition, basic design results of flame deflector configurations are included.

• Bulletin of the Korean Space Science Society
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• 2006.04a
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• pp.110-110
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• 2006

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.1
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• pp.91-97
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• 2017

The KSLV-II launch complex system consists of mechanical ground support equipment(MGSE), fuel ground support equipment(FGSE), electrical ground support equipment(EGSE) and infrastructures. Compressed gas supply system, as a part of FGSE, is responsible for launch operations such as gas intake, storage, supply to launch vehicle and ground support equipments. This system consists of three primary elements such as gas storage part, control panel and controller. Automatic panels, as a part of control panel, are manufactured to operate remotely by controller. This study presents compressed gas supply system which is designed for KSLV-II and ground support equipment characteristics.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.152.2-152.2
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• 2012

우주발사체 발사를 위해서는 발사대시스템 개발이 필수적이다. 발사대시스템은 기계설비와 추진제공급설비, 관제설비로 구성되며, 그 중 기계설비는 발사지지대(Launch Pad), 이렉터(Erector), 트랜스포터이렉터(Transport-Erector), 케이블마스트(Cable-mast), 자동체결장치(Auto-coupling Device) 총 다섯 부분으로 나눌 수 있다. 발사지지대는 발사 전까지 발사체를 지지하는 구조물로 발사체의 안전을 보장하고 공급배관 및 통신라인의 경로를 제공한다. 이렉터는 발사준비과정에서 수평으로 이송된 발사체를 2개의 대형 유압실린더를 사용하여 기립시키는 장비로 발사 취소 시 발사체를 수평으로 전환한다. 트랜스포터이렉터는 조립공간에서 조립을 마치고 최종점검이 완료된 발사체를 전용차량을 이용하여 발사대로 이동하고 발사체를 안전하게 잡아준다. 자동체결장치는 지상으로부터 발사체로 연결되는 추진제, 압축가스 등의 연결배관을 자동으로 연결/분리하는 장치이다. 케이블마스트는 우주발사체 상단부의 UCU-E(Umbilical Connectors Unit-Electrical)를 통해서 전기, 고압가스, 고온공기 등을 공급하기 위한 통로로 발사 전까지 발사체시스템과 지상장비와의 통신수단이다. 또한 발사체로 연결되는 라인들을 발사 시에 나오는 후류에 의한 충격으로부터 보호하고, UCU-E가 기계적으로 분리되도록 구성되어 있다. 본 논문은 기존에 적용된 케이블마스트에 대한 구성, 기능 및 운용절차에 관한 것으로, 현재 진행 중인 한국형발사체 개발을 위한 기초 자료조사로 활용하고자 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.36-40
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• 2017

The launch operation for a space launch vehicle(SLV) is to be conducted by the systematic operation between SLV and the Technological Equipment(TE) such as the mechanical, fuel, and electrical ground support equipment at launch complex(LC). The basic source for the operation of the instruments in LC is the electrical power supply system, Technological Equipment Power Supply System(TEPSS), which is one of the Launch Control System. Thus TEPSS should supply the required electrical power to TE with reliability. In this paper, TEPSS which supplies operational electrical power to TE is introduced.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.2
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• pp.102-110
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• 2017

In this paper, the liquid oxygen filling system (LOXFS) of the launch complex system of Korea Space Launch Vehicle-II (KSLV-II) is introduced based on critical design result by KARI in 2015 to 2016. The function and specification of the main systems of the liquid oxygen filling system, such as the storage tank, the drainage tank, the supply pumping system, the curved heat exchanger with liquid nitrogen, end valve block system, and umbilical connection, are presented.

• 한국정보통신설비학회:학술대회논문집
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• 2004.08a
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• pp.362-365
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• 2004

국간망과 가입자망의 초고속화가 이루어지더라도 구내망이 이를 뒷받침하지 않으면 초고속망 서비스의 제공은 이루어질 수 없다. 따라서 구내망의 구내통신선로설비는 구내의 인프라 구축에 매우 중요한 시설물이다. 이를 위해 국내에서는 초고속정보통신의 활성화를 위하여 1999년부터 초고속정보통신건물인증제도를 시행하고 있으며, 2004년1월1일부터는 공동주택의 특등급을 신설하여 세대내 광케이블이 시설되도록 요구하고 있다. 또한 국내의 구내통신선로설비에 대한 표준화는 한국통신기술협회에서 추진하고 있으며 현재까지 25개의 표준이 개발되었다. 주거용 건축물에 대한 표준을 2003년 12월에 개정하였으며 현재는 업무용 건축물에 대한 표준화 개정 연구를 진행하고 있다. 미국의 경우는 TIA를 통하여 자국내의 표준화 연구를 활발히 하고 있으며 이에 대한 내용을 근거로 국제표준화 연구를 진행하는 ISO에 제안하고 있다. 본 논문에서는 구내통신에 대하여 국제표준화와 미국을 중심으로 최근 표준화 동향에 대하여 조사 분석하고 이를 바탕으로 국내에서 제정하려고 하는 기술표준에 기여하고, 초고속정보통신건물인증제도와 국내 기술기준을 비교 분석을 통한 기술기준 개정방향을 기술하고자 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.6
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• pp.92-97
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• 2012

The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The oxidizer supply system modeling using AMESim was performed based on the results of the detailed design, and the oxidizer supply characteristics was analyzed in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.502-506
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• 2012

The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The oxidizer supply system modeling using AMESim was performed based on the results of the detailed design, and the oxidizer supply characteristics was analyzed in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.322-325
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• 2007

This paper shows the development procedure of the low pressure LOX feed system which is used in the liquid rocket with a turbopump. Korean Air has cooperated with KARI in developing the LOX feed system to turbopump. The LOX feed system is characterized with cryogenic temperature and the thin-thickness tube for weight saving. The system in this project is composed with a main feed line and a recirculation line for the LOX temperature conditioning. Each piping system has many components, namely, bellows, filter, orifice, valves, flange and support. In this paper, system design & manufacturing, structural & thermal analyses, and component tests are explained. Finally, the system was assembled to the KARI's PTF test facility and functioned well to meet its required performance.