• Korean Journal of Remote Sensing
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• v.33 no.5_1
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• pp.521-535
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• 2017

Since satellites, including payloads, are limited in how they can respond to problems after launch, the functionality of the satellite should be verified sufficiently by EGSE (Electrical Ground Support Equipment). In addition, considering the trend that the development period of the satellite is shortening and the development of the EGSE must precede the development of the engineering model of electronic equipment, early securing of EGSE is necessary to comply with the development schedule of the entire satellite. In this paper, we propose a method for early securing highly reliable EGSE by devising a scenario based operating payload packet analyzer, which is a part of the EGSE, through functional modularization and external parameterization, and show the result of applying the implemented payload packet analyzer to real satellite program.

• Korean Journal of Remote Sensing
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• v.26 no.2
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• pp.167-173
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• 2010

This paper introduces Geostationary Ocean Color Imager, IMage Pre-processing Subsystem (GOCI IMPS) of Communication, Ocean, and Meteorological Satellite (COMS), and describes its functions, development states, and operational concepts. The primary and backup systems of GOCI IMPS have been installed in Korea Ocean Satellite Center (KOSC) and Satellite Operation Center (SOC) and the system are the prelaunch test phase after completing all required tests. It is expected that the GOCI data observed continuously over the Korea Peninsular in the geostationary orbit will be usefully utilized in marine environment research fields such as sea surface temperature changes or marine ecosystems.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.161-167
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• 2010

CEU(Camera Electronic Unit) loaded in optical satellite for a high resolution image acquisition is composited with CC(Camera Controlloer), FPA(Focal Plane Assembly) and CEUP(CEU Power supply). EMC test and analysis results are explained in this paper. CE, CS, RE and RS test is performed in the 1st EMC test, RE, RS test which is not complied and influence considerably after shielding structure is performed in the 2nd EMC test. An effect due to the noise of CEU in the GPS/S-band receiving band is analyzed based on 2nd EMC test results. Margin more than 6dB is guaranteed when CEU is shielded.

• The Bulletin of The Korean Astronomical Society
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• v.36 no.1
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• pp.64.2-64.2
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• 2011

MIRIS (Multi-purpose InfraRed Imaging System), 다목적 적외선 영상시스템은 한국천문연구원에서 개발하고 있는 과학위성 3호의 주 탑재체이다. MIRIS 우주관측카메라는 한국에서 최초로 발사되는 천문우주관측용 적외선 우주망원경이다. 그 유효 구경은 80mm 이고, 탑재되는 검출기는 Teledyne사의 PICNIC $256{\times}256$ Array 이며, 이 검출기를 적용한 관측 화각(FoV)은 $3.67 deg{\times}3.67 deg$, Pixel Scale은 51.6 arcsec/pixel 이다. MIRIS는 현재 비행모델의 납품을 앞두고 우주환경 시험을 준비 및 진행하고 있으며, 시스템의 최적화 작업을 함께 수행하고 있다. 최근에 과학기술위성 3호의 발사체가 러시아 Dnepr로 결정되면서 시험 조건이 변경된 시험 항목에 대해서 EQM의 Sine진동, 충격 시험이 Qualification level로 진행되었다. 그리고 MIRIS 비행모델의 열진공 환경 시험 및 진동시험에 대한 준비 현황을 보고한다. MIRIS 비행 모델의 환경시험은 실제 위성이 겪는 acceptance level로 진행되며, 모든 시험을 통과하면 최종 납품이 이뤄질 예정이다. 또한 시스템의 최적화를 위해 수행했던 조립의 수정 항목들도 함께 보고한다.

• Proceedings of the Optical Society of Korea Conference
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• 2003.07a
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• pp.134-135
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• 2003

Medium-sized Aperture Camera (MAC)는 근적도궤도(Near Equatorial Orbit) 지구관측위성 MACSAT의 주탑재체로, 우리나라의 (주)쎄트렉아이와 말레이시아의 ATSB社와 오는 2004년 발사를 목표로 공동 개발되고 있다. MAC은 push-broom 방식의 전자광학 탑재체로, 지상해상도 2.5 m를 가지는 PAN band 1개, 지상해상도 5 m를 가지는 Multi-Spectral band 4 개를 가지고, 지상의 swath width는 20 km를 가진다. (중략)

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.213-220
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• 2013

Korean Lunar Explorer is planned to be launched in the 2020s according to national space development strategy. The Lunar Explorer will be developed as two unmanned light weight models: a lunar orbiter and a lunar lander. The Lunar Explorer's structure should be designed to have light weight due to constraints from launcher as well as to provide structural safety against launch load, in-orbit condition and landing condition and to serve accommodation space for mission equipment. Core technology related to structural development of lunar explorer should be developed in advance. Especially, for lunar lander, technology for developing landing gear which enables lander to land safely on lunar surface is required essentially. This paper deals with structural development of lunar lander ground test model including design, manufacturing and test.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.155-169
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• 2004

Space launch vehicles and reentry vehicles are exposed to extreme heating conditions due to high aerodynamic heating while flying at high Mach numbers in the atmosphere. To protect the vehicle itself or the payload from the aerodynamic heating, the thermal load imposed on the surface should be exactly predicted and proper thermal protection should be applied based on the prediction results. But this requires rigorous thermal analysis and testing to prevent loss of payload capacity caused by excessive heat shielding, and the amount of thermal protection material to be applied is determined through aerodynamic heating tests. Various design points to be considered to upgrade the prototype aerodynamic thermal simulation facility(ATSF) used for the KSR-series sounding rocket development to the one suitable for the KSLV(Korean Space Launch Vehicle)-series launch vehicle are considered in this research. The need and limitation for the facility are first considered, and the functions required for KSLV testing are determined. The specifications of the upgraded facility are briefly suggested and these results will be used for the future fabrication and installation of the facility.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.53-53
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• 2004

과학기술위성 1호는 2003년 9월 27일 러시아의 플레세츠크에서 성공적으로 발사된 후 6개월 여간의 운용을 통하여 초기 위성 안정화 과정과, 임무 수행기간인 2년 동안 정상적으로 위성이 운용될 수 있도록 위성의 운용모드에 따른 파라미터를 궤도상에서 보정하는 과정을 거쳐 전력 시스템이 최상의 조건을 가질 수 있도록 하였다. 초기 위성의 상태 점검과정과 탑재체의 관측을 위한 운용모드 시험과정을 거쳐 현재 위성은 각 궤도별로 “정밀 자세 제어 모드”, “최대 태양 전력 입력 지향 모드”, “자동 지상국 교신모드”, “탑재체 운용 모드”, “S/W 전력 제어”, “자동 파일 다운로드” 등으로 분류되어 운용되고 있으며, 위성의 주컴퓨터에 시나리오 명령구조를 사용하여 탑재체를 운용하고 있다. (중략)

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.4
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• pp.101-110
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• 2004

Flight and Qualification Models of Single Board Computer (SBC), called On-Board Computer (OBC), for HAUSAT-l picosatellite, which is scheduled to launch on September, 2004 by Russian "Dnepr" launch vehicle, have been developed. The OBC of HAUSAT-1 has been designed with some improved features compared to other picosatellites. A multifunctional controller and up-to-date SPI (Serial Peripheral Interface) and 1-Wire interface are implemented to simplify the harness routing and to minimize the mass and size of OBC. The improved fault-tolerant architecture design methodology is incorporated in the HAUSAT-1 OBC to protect against space radiation environment. The functions of the OBC were fully tested and verified by the Electrical Test Bed (ETB) model. This paper is also addressing the environmental test results, such as random vibration and thermal vacuum tests.

• Journal of Satellite, Information and Communications
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• v.3 no.2
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• pp.43-47
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• 2008

COMS is the one of Korean hybrid geostationary satellite and is scheduled to be launched in 2009 by Arian V into $128^{\circ}$ E longitude. COMS is designed and manufactured for three main objectives which are Communications, Oceanographic, and Meteorological missions. It provides the weather monitoring, ocean monitoring, and Ka band satellite communication services by means of three different payloads. The Ka band communications payload was developed by Electronics and Telecommunications Research Institute (ETRI), and provides not only the digital transmission for the communication services against natural disaster but also digital transmission for the high speed multimedia services. This paper describes the overview of the electrical and mechanical design and measured performances of the Ka band communications transponder flight model (FM) for COMS.