• 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.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.147-154
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• 2002

This paper describes the devlopment and implementation for the KOMPSAT-1 scheduling & automatic command plan generator(KSCG). Some problems in mission planning and command planning had occurred using the mission & command planning s/w in MAPS(Missin Analysis and Planning Subsystem) during the LEOP(Launch & Early Orbit Phase) & early normal mission phase due to lots of manual input process and non-automatic process. Therefore, the more mission operations for KOMPSAT-1. In order to prevent the development of new one(KSCG) which should reduce the manual process and generate automatically the command plan has been needed. As a result, the mission operations of KOMPSAT-1 has greatly became stable and more effient.

• Defense and Technology
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• no.5 s.291
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• pp.54-65
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• 2003

실전에 배치될 미국의 차세대 지상발사 탄도미사일 방어시스템은 Lockheed Martin사가 주계약 업체로 개발 중인 미 육군의 THAAD(Theater High Altitude Area Defense) 시스템이 될 것으로 예상된다. 프로젝트 정의 및 위험감소 단계는 1995년에 시작되었으며, 체계개발 단계는 2003년 시작되고 이어서 2004년에는 발사시험이 실시될 예정이다. 그리고 연간 40기의 미사일을 생산하는 초도생산단계는 2006년경에, 최종적인 양산은 2008년부터 시작되어 연간 320기의 미사일을 생산할 계획이다. 1999년 8월에 실시된 발사시험에서 고도 100km 이상의 표적을 대기권 밖에서 요격하는 데 성공한 바있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.11-15
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• 2005

Compared with the conventional ground rocket launching, air-launching has many advantages. However, comprehensive and integrated system design approach is required because the physical geometry of air launch vehicle is quite dependent on the installation limitation of the mother plane. The system design has been performed using two different approaches: the sequential optimization and the multidisciplinary feasible(MDF) optimization method. Analysis modules include mission analysis, staging, propulsion analysis, configuration, weight analysis, aerodynamics analysis and trajectory analysis. MDF optimization shows better result than sequential optimization. As a result of system optimization, a supersonic air launching rocket with total mass of 1244.91 kg, total length of 6.18 m, outer diameter of 0.60 m and the payload mass of 7.5 kg has been successfully designed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.12
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• pp.26-32
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• 2005

Compared with the conventional ground rocket launching, air-launching has many advantages. However, a comprehensive and integrated system design approach is required because the physical geometry of air launch vehicle is quite dependent on the installation limitation of the mother plane. The system design has been performed using two different approaches: the sequential optimization and the multidisciplinary feasible(MDF) optimization method. Analysis modules include mission analysis, staging, propulsion analysis, configuration, weight analysis, aerodynamics analysis and trajectory analysis. MDF optimization shows better results than the sequential optimization. As a result of system optimization, a supersonic air launching rocket with total mass of 1244.91kg, total length of 6.36m, outer diameter of 0.60m and the payload mass of 7.5kg has been successfully designed.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.90-90
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• 2003

한국항공우주연구원은 액체추진기관 시스템을 이용한 3단형과학로켓(이하 KSR-III)을 국내 최초로 개발하여 비행시험을 수행하였다. 액체추진기관 로켓의 비행시험을 위해서는 이전의 고체 추진기관을 이용한 과학로켓 1, 2와는 달리 비행시험 조건에 부합하게 액체추진제 및 가압제 등을 공급하는 지상설비가 필요하다. 이에 한국항공우주연구원은 독자적으로 비행시험에 필요한 제반 설비를 갖춘 발사장을 구축하였다. KSR-III는 압축 헬륨가스(GHe)를 이용하여 연료(Jet A-1)와 산화제(LOx)를 가압하여 추력을 얻는 액체추진기관 시스템이다. 따라서 발사장에서의 지상공급설비는 유공압 설비와 발사시나리오에 따라 해당 부품을 제어하고 자료를 저장하는 제어/계측 설비 및 기타설비들로 구성되어 있다. 지상공급설비 중 유공압 설비는 LOx의 저장 및 기체 내 산화제 탱크의 충전을 위한 산화제 공급설비, Jet A-1의 저장 및 기체 내 연료 탱크의 충전을 위한 연료 공급 설비, 지상설비용 밸브구동 및 기체 내부 퍼지 등에 필요한 질소($N_2$)를 저장/공급하는 설비, 기체내부 밸브 구동 및 가압제로 사용되는 기체헬륨(He)을 저장/공급하는 설비들로 구성되어 있다. 이러한 구축된 공급설비는 기능시험, 연계시험 등의 각종 입증시험을 통해 그 성능을 검증한 후 단인증모델(SQTM)을 이용하여 발사 시나리오에 따른 추진제 공급능력을 입증한 후 KSR-III의 비행시험을 성공적으로 수행하였다. 수행된 연구결과는 향후 건설되어질 우주센터내의 발사장 기반설비 설계의 기초 자료로 활용할 수 있을 것이다.

• Proceedings of the KIEE Conference
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• 2006.07d
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• pp.1797-1798
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• 2006

함상에서 발사되는 유도탄 등의 무기체제는 함정의 운동에 따라 초기 발사 자세 및 그 변화율이 변화하므로 함정의 운동을 고려하여 발사시점을 결정하여야 한다. 함상 발사대에 장착된 유도탄은 자체 센서에 의하여 함정의 자세 및 자세변화율을 측정하며 이렇게 측정된 함정 운동정보를 적절히 필터링하고 유도탄 발사 시퀀스 지연시간만큼 예측하여 발사시점을 결정한다. 본 논문에서는 함정운동을 모델링하고 이 모델에 근거하여 함상발사 유도탄의 초기 발사 시점 결정에 필요한 함운동을 추정 및 예측하는 필터를 제안하고 그 성능을 검토하였다. 시험결과 제안된 방법을 이용하여 우수한 성능으로 함운동을 예측할 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.12
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• pp.1087-1094
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• 2016

The responsibility of the vehicle holding device (VHD) is to hold the launch vehicle while it is stayed on launch pad and release the holding mechanism to allow a lift-off of launch vehicle at a moment of lift-off. During a release of the holding mechanism, in order to prevent the Ka doing a doing a doing mode which is vertical oscillation of entire liquid propellant and very severe for vehicle structure, gradual release of holding force is required. Also, a release operation of all 4 VHD should be synchronized very precisely. In this study, to comply the "gradual release and synchronized operation requirement", concept of VHD hydraulic system using an accumulator, pyro valve and orifice to control speed of hydraulic cylinder is proposed instead of using complicated hydraulic components. Then through multi-body dynamic analysis and computational hydraulic analysis, a size of orifice to meet a target speed of hydraulic cylinder is calculated. Through this study, simple and reliable VHD hydraulic system complying requirements is designed.

• Journal of Aerospace System Engineering
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• v.18 no.3
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• pp.27-33
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• 2024

According to the success of the Nuri Space Launch Vehicle (KSLV-II) and the development goal of the next generation space launch vehicle (KSLV-III), it is expected that the domestic geostationary satellite capability will be increased from (1 to 3.7) ton. Also, it is predicted that substantial ability of about 1 ton can be provided for the space exploration of the Moon, Mars, asteroids, etc. The Goheung space launch site is optimized for sun-synchronous small satellites, and due to the essential precondition that the launch trajectory does not impinge another country's sovereign airspace, it is not satisfactory as a geostationary satellite launching site. Its latitude also requires more energy to shape the rotating orbital plane from the initial injection status. This results in a decreasing factor of economic feasibility, including the operating complexity. Therefore, in parallel with the development of a next generation space launch vehicle, the practical process for acquisition of oversea land or sea space launch site near the Earth's equator and research for the optimization of orbiting methods of geostationary satellite injection must be continued.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.147-150
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• 2005

Space launch vehicles mainly use the liquid-propellant propulsion system which has easy thrust control ability and high specific impulse for that the payload like satellite and spacecraft should be entered into exact orbit. However, the liquid-propellant propulsion system is very difficult to develop because it is more complicate than the solid rocket propulsion system and demands very high technology. In space launch vehicle developing procedure the system design level is very important thing to reduce cost, shorten schedule, and improve the performance. The system design process was introduced for selecting the best liquid-propellant propulsion system on this paper.