• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.752-757
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• 2010

For the launch preparation of KSLV-I, gaseous nitrogen with various level of pressure and cryogenic liquid nitrogen are required. Nitrogen Supply System on launch complex has been developed to perform the production of high pressure gaseous nitrogen, the production of gaseous nitrogen with temperature of $273{\pm}2K$ for protection purge of launch vehicle after loading of propellant and the supply of cryogenic liquid nitrogen for cooling of fuel (kerosene) and oxidizer (liquid oxygen). The operational instability of vaporizer mainly caused by its heat transfer characteristics which sensitively depends on the atmospheric conditions was removed by introducing parallel installation of two vaporizer and their switching operation. The developed Nitrogen Supply System carried out its function successfully in preparation of KSLV-I flight tests.

• 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.

• Current Industrial and Technological Trends in Aerospace
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• v.7 no.2
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• pp.3-11
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• 2009

On August 25th, Korea launched KSLV-1(Naro), the first Korean launch vehicle with the payload of a small satellite. The launch itself was successful in that the first and second stage of the launch vehicle functioned properly but unfortunately the satellite was unable to be put into earth orbit due to the failure of a nose faring detachment. As the history of human space activities shows, it is recognized as a difficult task to be a launching state requiring efforts to obtain enough technical ability. But along with the technical ability, there has to be an understanding on international legal systems on space launch vehicle. It is because the launch may cause cross-border losses and because the launcher is regarded as a strategic technology resulting in international control. This paper aims to study the international status of launching state and to consider legal regimes necessary for launcher development.

• Journal of Aerospace System Engineering
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• v.16 no.4
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• pp.28-34
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• 2022

In 2021, Virgin Orbit converted a 747-400 aircraft into an air launch platform, and successfully launched it twice in February and July. Compared to the existing ground launch, interest in the air launch is increasing due to its great utility, such as its independence from the launch location or weather, cost reducing factor, shorter launch preparation time, and its benefit pursuant to altitude and speed. Additionally, as small satellites have similar performance to mid/large satellites in the past due to the miniaturization and precision of electronic equipment, small satellite launches are expected to dominate in the future. In this paper, institutional certification methods such as domestic, overseas, civilian and military airworthiness certification regulations/procedures are reviewed to ensure flight safety of aerial projectiles using large domestic civil aircraft, and applicable civil and military airworthiness certification technology standards are reviewed and analyzed. Additionally, we will review and suggest effective airworthiness certification application plans that reflect the reality, and present airworthiness certification standards (draft) for aerial launch vehicles, by analyzing applicable airworthiness certification technical standards when remodeling aerial launch vehicles.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.207-210
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• 2011

Chollian bipropellant propulsion system is composed of one main engine for orbit transfer and fourteen thrusters for on-station operations. The design and analyses of the propulsion system were carried out in the framework of international collaboration. Following the system integration and testings required, the Chollian was transported to Kourou Space Center in French Guiana and launched successfully. 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.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.9
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• pp.103-113
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• 2004

The satellite is exposed to the severe vibration environments such as random vibration environments such as random vibration, acceleration, shock, and acoustics during launch ascent and transportation. It is also faced with various space environments such as thermal vacuum, radiation and microgravity during the mission life. The satellite should be designed, manufactured, assembled and tested to be able to endure in these harsh environments. This paper addresses the results of the structural and thermal design and analyses for the HAUSAT-1 picosatellite which is scheduled to launch in the first quarter of 2005 by Russian launch vehicle "Dnepr". The qualification vibration and thermal vacuum tests have been conducted and passed at the satellite level to ensure that the HAUSAT-1 mechanical system was designed to be stable with enough margin.

• Journal of Space Technology and Applications
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• v.1 no.3
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• pp.319-336
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• 2021

This paper discusses the results of launch environment tests for the engineering qualification model (EQM) of nanosatellite Scale magNetospheric and Ionospheric Plasma Experiment (SNIPE) for scientific missions and lessons learned for the design of nanosatellites. SNIPE is a group of four formation-flying 6U nanosatellites with a range of payloads for missions including space weather measurement. We developed the EQM to verify the preliminary design prior to fabricating the flight model. Launch environment test of EQM was conducted for the first time in 2019, and all failures were corrected and verified at the second test conducted in 2021. A notable point of the two tests is that the nanosatellite deployer used in the first test is different from that of the second test. The second deployer has the capability to fix the internal satellite whereas the first deployer just contains and deploys the satellite. Thus actual mechanical loads the satellite receives is reduced for the second test compared to the first test. This work compares the mechanical responses of two tests and proposes general guidelines for structural design of nanosatellites.

• Journal of Astronomy and Space Sciences
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• v.16 no.1
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• pp.79-88
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• 1999

The satellite experiences the severe launch environment such as vibration, acceleration, shock, and acoustics induced by rocket. Therefore, the satellite should be designed and manufactured to endure such severe launch environments. In this paper, we describe the structure of the KITSAT-3 FM(Flight Model) and the processes and results of the launch environmental test to ensure the reliability during launch period.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1997.04a
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• pp.75-80
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• 1997

1999년 한반도 상공에 발사되어 21세기 한국의 우주 시대를 열어나갈 국내 최초의 다목적 실용위성인 KOMPSAT의 개발이 한국 항공 우주 연구소를 주관 기관으로 국내외의 여러 기업 및 연구기관들이 참여한 가운데 현재 진행 중이다. 본 논문에서는 위성체의 설계, 제작 및 시험의 국산화 일환으로 국내에서 제작된 이중 추진 장치(Dual Thrust Module)의 발사 환경 시험에 대한 과정 및 결과에 대하여 언급코자 한다. 일반적으로 목표 궤도에서 발사체로부터 분리된 위성체는 자세 제어를 수행하며, 또한 저궤도 위성의 경우 궤도상에 존재하는 공기등의 저항으로 인하여 빈번한 궤도수정이 필요하다. DTM은 이러한 궤도수정 업무를 담당하는 중요한 위성체의 부품이다. 그러나, 지상에서 발사시 발사체로부터 전달되는 진동 및 소음의 영향으로 인하여 기능 장애를 일으킬 우려가 있음에 따라, 제작된 DTM은 위성 본체에 장착되기 전 반드시 발사 시와 동일한 환경하에서 고유의 기능을 성공적으로 수행할 수 있는지에 대한 검증 절차가 필요하다. 본 연구에서는 DTM의 발사 환경 시험을 성공적으로 수행함으로써 위성체 및 부품의 시험기술을 축적하여 국내 위성 개발 분야에 기여코자 한다.

• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.122-128
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• 2005

A work breakdown structure of 3-staged launch vehicle has been developed during the preliminary design step of KSLV-I program. In the present paper, the background, the detailed contents, and the total structures of WBS have been studied. The management plan for WBS has been also provided.