• 대한전기학회:학술대회논문집
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• 대한전기학회 2009년도 제40회 하계학술대회
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• pp.1013_1014
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• 2009

In this paper, the electrical interfaces used in between COMS satellite bus and Ka-band communication payload are analyzed to verify the robustness of data bus. The purpose of the serial data bus of satellite is to allow serial data transfer between one bus controller or source equipment to several user terminals or slave equipments. A serial data bus in COMS satellite is mainly used for Channel Amplifier and Digital Control Unit of Ka-band Payload.

• 항공우주시스템공학회지
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• 제3권1호
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• pp.6-11
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• 2009

It is anticipated that quality assurance for the Ka band Communication Payload System(COPS) development program of the communication, Ocean & Meteorological Satellite(COMS) may be a core technical factor to be concerned in order to avoid any failure, and to assure its final performance during the mission lifetime in space. Those can be managed and verified and assessed by performing the Quality Assurance (QA) and risk management which helps to prevent and to reduce the critical fails. This paper introduces the Product Assurance (PA) system and procedures for controlling and monitoring sub-contractors which were participated in Ka band Communication Payload System (COPS) development. Also this paper shows Quality Assurance (QA) procedures and detailed their processes for assured the product performed by local companies from site survey for selecting companies to delivery of their equipment.

• 항공우주시스템공학회지
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• 제2권1호
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• pp.22-27
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• 2008

It is anticipated that quality assurance for the Ka band Communication Payload System(COPS) development program of the Communication, Ocean & Meteorological Satellite(COMS) may be a core technical factor to be concerned in order to avoid any failure, and to assure its performance during the mission lifetime in space. Those can be managed and verified and assessed by performing the Quality Assurance (QA) and risk management which helps to prevent and reduce the critical fails. This paper introduces the Product Assurance (PA) system and procedures for Ka band Communication Payload System which was established and performed during the Qualification Model (QM) manufacturing phase. In this paper, we present detailed process for the products manufactured by local companies according to PA procedures operated through whole phases from design to test of equipment. Also this paper shows Quality Assurance (QA) procedures and detailed their processes for assured the product quality manufactured by local companies.

• 한국정보통신학회논문지
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• 제10권4호
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• pp.706-711
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• 2006

본 연구에서는 SAR영상을 통해 해상풍 산출한 다음 해양연구원의 실시간 해양 해양기상 관측 자료와 비교 분석하여 그 정확도를 한반도 주변해역을 대상으로 파악하였다. SAR를 통해 추출된 해상풍 자료와 실측값의 RMS는 풍속은 0.8m/s, 풍향은 8도로 나타났다. 전체 적으로 실측값과 많은 차이를 보이지는 않지만 FFT 방법에 의한 SAR 영상의 바람 띠를 분석하기 위해서는 최소 10km 이상의 영상을 사용하여야만 하였다. 또한 본 연구에서는 우리나라 연안의 Radarsat SAR 영상을 이용하여 바람산출모델 CMOD5를 통해 해상풍 값을 산출하였다. CMOD5는 현재까지 산란계(Scatterometer)와 ERS SAR 위성을 이용해 해상풍을 산출할 때 가장 많이 사용되어오던 CMOD4 모델을 개선한 모델로써 특히 고풍속일 때의 결과에서 많은 개선을 보였다.

• 대한원격탐사학회지
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• 제33권5_1호
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• pp.607-615
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• 2017

본 연구에서는 동북아시아($15{\sim}55^{\circ}E$, $90{\sim}150^{\circ}N$) 영역에 대하여 극궤도 위성 Terra와 Aqua에 탑재된 Moderate Resolution Imaging Spectrometer (MODIS) 센서와 우리나라 정지궤도 위성인 통신해양기상위성(Communication, Ocean and Meteorological Satellite, COMS)에 탑재된 Meteorological Imager (MI) 센서에 의한 에어로졸 광학두께(AOT) 산출 결과와 지상의 Aerosol Robotic Network (AERONET) 관측 자료를 비교 분석하였다. 그 결과 MODIS와 MI에 의한 에어로졸 광학두께는 해양에서 비교적 잘 일치하였으나 구름 가장자리와 육지에서는 두 센서의 에어로졸 광학두께 차이가 크게 나타났다. 그 이유로서 MODIS는 가시 채널과 적외 채널을 혼용하는 반면 MI는 오직 가시채널 만 사용하기 때문에 구름 가장자리의 옅은 구름을 에어로졸로 인식할 수 있고 육지에서는 지표면 특성에 따라 MODIS와 MI에 의한 에어로졸 광학두께 산출 차이가 발생된다. 따라서 MI 에어로졸 광학두께는 구름 가장자리와 지표면 특성의 영향을 주는 지표면 반사도의 정확성 개선을 통해 에어로졸 광학두께 산출 결과를 개선할 수 있다고 사료된다.

• 한국통신학회논문지
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• 제24권8A호
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• pp.1149-1155
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• 1999

저궤도위성 시스템은 지구 및 과학 관측분야(지도제작, 해양생태감시, 우주환경 관측, 기상관측, 대기관측 등)와 군사분야(군사통신, 첩보, 적군정찰 등)에서 사용되었으며, 최근에는 상업적 이용을 위해 GMPCS를 위한 이동위성통신 분야에서 개발이 진행되고 있다. 우리나라에서는 1999년 10월 발사를 목표로 다목적 실용위성 1호가 개발되고 있다. 본 논문에서는 저궤도위성 관제시스템을 위한 위성링크를 설계하고 위성의 움직임에 따른 위성의 통과시간과 지구국의 양각 관계를 계산한다. 그리고 수신데이터의 패킷오율을 확률이론에 의해 유도하고, RT모드와 PB모드 그리고 RT+RNG모드에 대한 패킷오율을 위성과 통과시간에 따라 예측한다. 패킷오율 계산결과는 RT모드, PB모드, RT+RNG모드의 순으로 좋으며 EFP의 평균도 각각 99.999999%, 99.995945%로 계산되었다. 따라서 원격측정 데이터의 전송순서는 위성의 통과시간에 따른 PER 순서로 즉, RT, PB, RT+RNG순으로 결정한다.

• 항공우주시스템공학회지
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• 제1권3호
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• pp.1-6
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• 2007

The COMS(Communication, Ocean & Meteorological Satellite)is the geostationary satellite which will be performing three main objectives such as meteorological service, ocean monitoring and Ka-band satellite communications. This paper presents the analysis of the electromagnetic radiated compatibility between COMS satellite and the ARIANE 5 launch vehicle. As a conclusion, a good level of confidence can be given at present time to demonstrate the compatibility between the spacecraft and the launcher, and vice versa. No threat has been identified regarding the other units powered during launch mode.

• 전기학회논문지
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• 제57권3호
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• pp.439-445
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• 2008

In this paper, the preliminary EMC analysis process between the Communication, Ocean and Meteorological Satellite (COMS) and Geostationary Earth Orbit (GEO) launch vehicles in the frequency range [1MHz-47MHz] is described. The considered launch vehicles are arian V, sea Launch, land Launch, atlas III&V, delta IV, proton M/breeze M, soyuz, HII-A and Angara. The launch vehicle Radiated Emission (RE) specifications have been compared to COMS satellite Radiated Susceptibility (RS) limits. The COMS RS limits are the RS qualification levels of COMS units during launch. As a result, The radiated emission levels of arian V, sea launch, atlas III&V, delta IV, proton M/breeze M, HII-A and angara are compliant with COMS RS limits. The negative margins appear between land launch or soyuz launch vehicle RE and COMS RS. Then, if the land launch or soyuz is chosen by the customer, The tests should be performed at satellite level in order to demonstrate the compatibility with respect to launch vehicles specifications.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2008년도 학술대회 논문집 정보 및 제어부문
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• pp.369-370
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• 2008

The Payload Interface Unit (PIU) provides the interface between payload equipment (GOCI, MODCS and Ka Band P/L) and the SCU. The PIU is a MIL-STD-1553-Bus Remote Terminal (RT). The MPIU distributes commands to, acquires telemetry from and takes part in the thermal control of the payload equipment. When in ON mode, the PIU is completely observable and can be used for payload control. When in OFF mode, the PIU is non active except the thermal control electronics.

• 항공우주시스템공학회지
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• 제3권2호
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• pp.31-38
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• 2009

COMS On-board FDIR(Failure Detection, Isolation and Recovery) functions are implemented on the on-board software to satisfy the autonomy and failure tolerance requirements. This paper presents concepts of COMS Failure Management with hierarchical layers and addresses the characteristics of the FDIR layer from low level to high level. It is aimed at giving the reader the understanding how the COMS FDIR was designed and how works. It first recalls what are the system level applicable requirements, which are based on the COMS mission requirements. Then it describes the philosophy and structure of the FDIR and subsequently breaks it down into the several FDIR layers. It could be used as an important and useful reference of the information to design and develop an automatic FDIR mechanism in the future.