• 항공우주기술
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• 제9권2호
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• pp.161-167
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• 2010

지구관측을 위한 광학위성에 탑재되는 고해상도 영상 획득을 목적으로 하는 위성카메라의 카메라전자부(CEU : Camera Electronic Unit)는 CC(Camera Controller)와 FPA(Focal Plane Assembly), CEUP(CEU Power supply)로 구성된다. 본 논문은 광학위성 탑재체(CEU)의 전자파시험결과와 이를 토대로 한 시스템 양립성 검토결과를 설명하였다. CEU의 1차 전자파시험은 전도성 방출시험, 전도성 감응시험, 복사성 방출시험 및 복사성 감응시험을 수행하였고 2차 시험에서는 1차 시험에서 규격을 만족하지 못함으로서 시스템 성능에 중요한 영향을 미칠 수 있는 복사성 방출시험과 복사성 감응시험을 차폐제를 이용하여 기구적인 차폐를 보강 후 수행하였다. 2차 시험결과에 대한 시스템 양립성은 탑재체(CEU)에서 방출하는 노이즈의 주파수성분이 위성의 GPS/S-Band 수신 성능에 미치는 영향성을 분석하였다. 기구적인 차폐보강이 전제되었을 때, 두 수신대역 내에서 발생하고 있는 노이즈 주파수성분에 대하여 6dB 이상의 마진을 갖는 것으로 나타났다.

• 항공우주기술
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• 제6권2호
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• pp.73-78
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• 2007

현재 개발되고 있는 위성용 전자광학시스템의 설계 파라미터를 적용하여 알려진 식에 의해 위성의 운용고도와 자세변화에 따른 전자광학시스템의 GSD 및 라인레이트 변화관계를 살펴보았다. 그리고 고도변화에 따른 적용 가능한 라인레이트와 위성의 지상 스캔율의 차이에 의해 발생할 수 있는 성능변화 요소로서의 MTF에 대한 영향을 검토하였다. 즉 현재 개발이 진행되고 있는 카메라 전자부의 설계 파라미터를 적용하여 조정 가능한 라인레이트의 한계를 알아보고 이에 의한 성능감소 변화를 검토함으로써 현재 개발 진행되는 전자광학시스템의 카메라전자부의 설계요소에 대한 분석을 수행하였다.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2005년도 Proceedings of ISRS 2005
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• pp.637-640
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• 2005

In the development of a electronic system for a optical payload comprising mainly EOS(Electro-Optical Sub-system) and PDTS(Payload Data Transmission Sub-system), many aspects should be investigated and discussed for the easy implementation, for th e higher reliability of operation and for the effective ness in cost, size and weight as well as for the secure interface with components of a satellite bus, etc. As important aspects the interfaces between a satellite bus and a payload, and some design features of the CEU(Camera Electronics Unit) inside the payload are described in this paper. Interfaces between a satellite bus and a payload depend considerably on whether t he payload carries the PMU(Payload Management Un it), which functions as main controller of the Payload, or not. With the PMU inside the payload, EOS and PDTS control is performed through the PMU keep ing the least interfaces of control signals and primary power lines, while the EOS and PDTS control is performed directly by the satellite bus components using relatively many control signals when no PMU exists inside the payload. For the CEU design the output channel configurations of panchromatic and multi-spectral bands including the video image data inter face between EOS and PDTS are described conceptually. The timing information control which is also important and necessary to interpret the received image data is described.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2003년도 Proceedings of ACRS 2003 ISRS
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• pp.1121-1123
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• 2003

The CCD (Charge coupled device) detector that is used to convert the light into electronic data is very important component in satellite camera. A Linear CCD Spectral detector shall be used in the MSC (Multi-Spectral Camera, to obtain data for high-resolution images) Payload. In this paper, the design concept of the CCD detector control module in the MSC CEU (Camera electronic unit) system which will be a payload on KOMPSAT is described in terms of H/W (clock speed and accuracy).

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2003년도 Proceedings of ACRS 2003 ISRS
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• pp.1118-1120
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• 2003

In MSC(Multi-spectral camera ), the incoming light is converted to electronic analog signals by the CCD(charge coupled device) detectors. The analog signals are amplified, biased and converted into digital signals (pixel data stream) in the FPE(Focal plane electronics ). The digital data is transmitted to the PMU for pre-processing to correct for nonuniformity, to partially reorder the pixel stream and to add header data for identification and synchronization In this paper, the video data streams is described in terms of hardware.

• 대한원격탐사학회지
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• 제18권1호
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• pp.53-59
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• 2002

The MSC is a payload on the KOMPSAT-2 satellite to perform the earth remote sensing. The instrument images the earth using a push-broom motion with a swath width of 15 km and a GSD(Ground Sample Distance) of 1 m over the entire FOV(Field Of View) at altitude 685 km. The instrument is designed to haute an on-orbit operation duty cycle of 20% over the mission lifetime of 3 years with the functions of programmable gain/offset and on-board image data compression/storage. The MSC instrument has one channel for panchromatic imaging and four channel for multi-spectral imaging covering the spectral range from 450nm to 900nm using TDI(Time Belayed Integration) CCD(Charge Coupled Device) FPA(Focal Plane Assembly). The MSC hardware consists of three subsystem, EOS(Electro Optic camera Subsystem), PMU(Payload Management Unit) and PDTS(Payload Data Transmission Subsystem) and each subsystems are currently under development and will be integrated and verified through functional and space environment tests. Final verified MSC will be delivered to spacecraft bus for AIT(Assembly, Integration and Test) and then COMSAT-2 satellite will be launched after verification process through IST(Integrated Satellite Test). In this paper, the introduction of MSC, the configuration of MSC electronics including electrical interlace and design of CEU(Camera Electronic Unit) in EOS are described. MSC Operation parameters induced from the operation concept are discussed and analyzed to find the influence of system for on-orbit operation in future.