• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.51-51
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• 2003

인공위성의 개발 단계는 Prototype Model(PM), Engineering Model(EM), Qualification Model(QM) 그리고 Flight Model(FM)로 구분된다. 이때, Prototype 개발을 제외한 EM, QM, FM 개발단계는 반드시 종합조립시험(AIT)을 통하여 System Integration Test를 수행한다. 이 중에서 위성발사 전 최종 종합조립시험단계인 FM AIT는 위성의 최종시험단계이므로 Scenario Test를 포함한 지상에서 수행하여야 할 모든 시험을 수행한다. 이때, EM, QM 단계와는 다르게 FM AIT는 전기적 및 기계적 시험을 수행하나, 본 논문에서는 전기적 시험 과정과, Control Center 구성도 등을 포함하고 있는 Hardware 부분과, 관련 시험을 수행하게 될 Simulator를 포함한 Software 부분으로 나누어 소개하며, 기타 FM AIT 수행에 필요한 Electrical Ground Support System (EGSE) 전체 구성을 소개한다.

• Journal of Advanced Navigation Technology
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• v.27 no.5
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• pp.534-539
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• 2023

Currently, in Korea, to obtain a jet type rating, you must receive training on a small business jet model. The reason is because of the law in the Aviation Safety Act Enforcement Rules 『Appendix 4』 that states, "You must receive at least 2 hours of flight training." In the end, it is acquiring type rating as a small business jet aircraft with relatively low operating costs. The qualifications acquired in this way are different from those for aircraft operated by airlines. However, if you have an initial jet type rating, you can acquire an airline aircraft qualification just by training on a simulator, so airlines want you to have at least a small-jet type rating. However, in the United States and Australia, there is a system in place to acquire initial jet type rating through simulator training without actual flight training.

• Journal of Aerospace System Engineering
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• v.2 no.3
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• pp.29-32
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• 2008

The overview of KUH design and development process is presented according to Buede's systems and development "vee" model. The system decomposition and integration activities exemplify KUH specification tree, design maturity and analysis according to design stage(conceptual, preliminary, and detail design), scheduled work breakdown structure, qualification test, ground test, and flight test. This process can be applied to the development of a new aircraft.

• 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.

• The Bulletin of The Korean Astronomical Society
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• v.41 no.2
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• pp.64.3-65
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• 2016

The NISS (Near-infrared Imaging Spectrometer for Star formation history) is the near-infrared instrument optimized to the Next Generation of small satellite series (NEXTSat). The capability of both imaging and low spectral resolution spectroscopy in the near-infrared range is a unique function of the NISS. The major scientific mission is to study the cosmic star formation history in local and distant universe. For those purposes, the main observational targets are nearby galaxies, galaxy clusters, star-forming regions and low background regions. The off-axis optical design is optimized to have a wide field of view ($2deg.{\times}2deg.$) as well as the wide wavelength range from 0.95 to $3.8{\mu}m$. Two linear variable filters are used to realize the imaging spectroscopy with the spectral resolution of ~20. The mechanical structure is considered to endure the launching condition as well as the space environment. The compact dewar is confirmed to operate the infrared detector as well as filters at 80K stage. The electronics is tested to obtain and process the signal from infrared sensor and to communicate with the satellite. After the test and calibration of the engineering qualification model (EQM), the flight model of the NSS is assembled and integrated into the satellite. To verify operations of the satellite in space, the space environment tests such as the vibration, shock and thermal-vacuum test were performed. Here, we report the test results of the flight model of the NISS.

• 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.

• The Bulletin of The Korean Astronomical Society
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• v.35 no.1
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• pp.40.1-40.1
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• 2010

The Main payload of the STSAT-3 (Korea Science & Technology Satellite-3), MIRIS (Multipurpose Infra-Red Imaging System) has been developed for last 3 years by KASI, and its Flight Model (FM) is now being developed as the final stage. All optical lenses and the opto-mechanical components of the FM have been completely fabricated with slight modifications that have been made to some components based on the Engineering Qualification Model (EQM) performances. The components of the telescope have been assembled and the test results show its optical performances are acceptable for required specifications in visual wavelength (@633 nm) at room temperature. The ensuing focal plane integration and focus test will be made soon using the vacuum chamber. The MIRIS mechanical structure of the EQM has been modified to develop FM according to the performance and environment test results. The filter-wheel module in the cryostat was newly designed with Finite Element Analysis (FEM) in order to compensate for the vibration stress in the launching conditions. Surface finishing of all components were also modified to implement the thermal model for the passive cooling technique. The FM electronics design has been completed for final fabrication process. Some minor modifications of the electronics boards were made based on EQM test performances. The ground calibration tests of MIRIS FM will be made with the science grade Teledyne PICNIC IR-array.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.52-52
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• 2003

1996년 미국 버클리 대학의 Space Science Laboratory와 공동으로 고온 성간 물질의 관측에 대한 Conceptual Study로부터 시작되어 1998년 과학위성 1호의 주 탑재체로 선정되면서 본격적인 개발에 들어간 원자외선 분광기(FIMS: Far-ultraviolet IMaging Spectrograph)는 Engineering Model 개발, Qualification Model 개발, Flight Model의 개발 및 보정, 그리고 최종적으로 과학기술위성 1호 본체와의 조립 시험 및 환경시험을 거쳐 2003년 9월 26일 러시아의 플레세츠크에서 COSMOS-3M 발사체에 의해 발사된다. FIMS를 포함한 과학위성 1호는 현재 발사를 위해 러시아 현지에 이송되어 최종 시험을 진행 중이며, 발사 후 약 20일 가량은 위성의 운용 시험을 하게 되며, 이후 FIMS의 운용에 영향을 줄 수 있는 Out-gassing이 충분히 이루어진 후 FIMS의 Test 및 초기 운용이 이루어 진다. FIMS의 Detector로 사용되는 MCP(Micro Channel Plate)의 정상적 동작이 확인되면, 1년여에 걸쳐 FIMS의 주 임무인 원자외선 영역(900∼1750')의 은하계 전천 탐사를 수행하게 된다. 전천 탐사가 마무리 되면, 전천탐사의 결과를 바탕으로 개별 천체의 영상 및 분광 자료를 획득하게 되며, 동시에 원자외선 영역의 오로라 및 지구 대기광 측정을 수행한다.

• Bulletin of the Korean Space Science Society
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• 2009.10a
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• pp.45.1-45.1
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• 2009

과학기술위성 3호의 주탑재체인 MIRIS (Multi-purpose InfraRed Imaging System)는 우주관측카메라 (Space Observation Camera, SOC)와 지구관측카메라 (Earth Observation Camera, EOC)가 독립적인 시스템으로 구성되어 있다. 지구관측카메라는 유효 구경 100 mm, F/5의 광학계로 3-5 마이크론 파장영역을 관측하며, 국내에서 개발된 적외선 검출기의 우주 인증 시험과 유사시 한반도 적외선 감시를 주요 목적으로 하고 있다. 고도 700km에서 지상을 볼 때 약 42m/pixel의 공간분해능을 나타낼 것으로 기대하고 있다. 지구관측카메라의 인증 모델(Qualification Model)은 냉동기를 제외한 모든 부품이 국내기술로 제작되었으며, 미러 본딩 및 릴레이 렌즈 조립 기술, 적외선 영상 검교정 기술 등 다양한 경험과 도전을 제공했다. 이 발표에서는 지구관측카메라 인증모델을 이용하여 수행한 주요 시험 과정을 소개한다. 국내 회사 (주)i3 system에서 제작된 적외선 검출기는 $320\times256$ HgCdTe array (평균 양자효율 80% 이상) 이며 77K에서 정상적으로 운영된다. Micro Stirling Cooler에 의해 듀어는 전원을 켠 후 5분 이내에 검출기 운영온도인 77K까지 내려간다. 적외선 광학계의 정렬, 시스템 MTF 측정, 흑체 측정 및 검교정 작업을 수행한 후 야외에서 다양한 경우에 대해 Field Test를 진행했다. 이 발표에서는 Field Test 과정과 이를 통해 얻은 결과를 발표하고, FM (Flight Model) 제작에 있어 수정해야 할 사항들을 제안해 본다.

• Bulletin of the Korean Space Science Society
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• 2009.10a
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• pp.44.3-44.3
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• 2009

The MIRIS (Multi-purpose IR Imaging System), as the main payload of Science and Technology Satellite-3 (STSAT-3), is being developed by KASI in collaboration with several institutes for wide-field space observation in near IR wavelength. The Engineering Qualification Model (EQM) of MIRIS has been designed and fabricated in the laboratory. The system performance tests have been made including opto-mechanics, vibration test, thermal-vacuum environmental test and passive cooling test down to 200K. Most of the performance test results were satisfied with system requirements. The results of MIRIS performance tests have been presented at Critical Design Review (CDR) on September 2009. Several revisions were also recommended for Flight Model (FM) design, and detailed plan to develop FM of MIRIS is discussed in this paper.