• Proceedings of the KSME Conference
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• 2005.11a
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• pp.22.1-22.1
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• 2005

• Proceedings of the Korean Vacuum Society Conference
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• 2004.08a
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• pp.102-102
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• 2004

• Bulletin of the Korean Space Science Society
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• 2007.10a
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• pp.124.2-124.2
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• 2007

• Current Industrial and Technological Trends in Aerospace
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• v.8 no.2
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• pp.65-75
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• 2010

In 2014, Japan is scheduled to launch GCOM(Global Change Observation Mission)-C for the global change observation mission, where SGLI(Second-generation Global Imager) is planned for optical multi-channel observation ofa radiation budget and a carbon cycle. Depending on the spectral channels, SGLI consists ofS GLI-VNR(Visible Near IR) and SGLI-IRS(IR Scanning). Their main design schemes are mostly based upon those ofthe previous instruments ever developed in Japan, which is intended to reduce the development risk for the advanced performance. Accordingly, for the better understanding ofSG LI, the paper reviews the history oft he Japanese optical payloads from two different views: VNR and IR. Through the review, a comparison among the Japanese optical instruments is made to distinguish the development trend toward SGLI ofGC OM-C.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.8
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• pp.710-717
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• 2016

Satellite payload can be classified as electro-optical payload, SAR, microwave radiometer, communication payload, navigation payload and so on in accordance with the mission objective. The technology of satellite payload was tried to be obtained through development of KOMPSAT series, COMS and STSAT in Korea. In this paper, the required technology for the development and world market trend of satellite payload were studied and described. Since KOMPSAT program has been started in 1994, technology status and future prospects of satellite payload in Korea are studied and analyzed.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.68-68
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• 2004

국가 우주개발 중장기 계획에 따르면 2003년부터 2015년 까지 다목적실용위성 7기, 과학위성 4기, 통신해양기상위성을 포함한 정지궤도 위성 4기 등 총 15기의 위성 개발 계획을 갖고 있다. 이러한 위성들은 지구의 대기, 해양, 기상 등을 관측하고, 우주환경의 측정 및 각종 실험 등을 수행하며, 안정적인 통신 방송 서비스를 제공하는 역할을 하게 될 것이다. 특히 다목적실용위성의 경우, 위성체의 눈 역할을 하는 위성탑재체인 고해상도 과학관측카메라를 탑재하고 있는데, 현재까지는 외국과의 기술협력을 통해 자립개발을 꾀하고 있다. (중략)

• Proceedings of the Optical Society of Korea Conference
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• 2008.07a
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• pp.127-128
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• 2008

• Proceedings of the Optical Society of Korea Conference
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• 2008.07a
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• pp.399-400
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• 2008

본 논문은 광학 탑재체에서 성능예측에 있어 주요 MTF인자를 MATLAB으로 계산하여 기본 광학계 성능 해석 모델을 통합적인 툴로 구현하였다. 그 결과 광학 탑재체 성능 해석에 있어 광학 탑재체의 초기 설계 단계에서 주요 설계인자를 도출하여, 인공위성 광학 탑재체에 있어 지배적인 영향을 미치는 Jitter, Smear, Detector sampling, Detector diffusion등의 MTF인자 및 PSF인자들을 활용하여 광학 탑재체의 성능 예측을 수행함에 있어 간단하고 효율적인 툴을 개발하였다.

• Korean Journal of Remote Sensing
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• v.33 no.2
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• pp.159-169
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• 2017

The Satellite Electro-Optic Payload System needsspecial requirements with the conditions of limited power consumption and the space environment of solar radiation. The acquired image quality should be mainly depend on the GSD (Ground Sampled Distance), SNR (Signal to Noise Ratio), and MTF (Modulation Transfer Function). On the well-manufactured sensor level, the thermal noise is removed on ASP (Analog Signal Processing) using the CDS (Corrective Double Sampling); the noise signal from the image sensor can be reduced from the offset signals based on the pre-pixels and the dark-pixels. The non-uniformity shall be corrected with gain, offset, and correction parameter of the image sensor pixel characteristic on the sensor control system. This paper describes the SNR enhancement method of the satellite EOS payload using the mentioned noise remove processes on the system design and operation, which is verified by tests and simulations.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.11
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• pp.1069-1076
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• 2011

All of the satellite components must be operated within the permissible temperature range during the mission in orbit. Therefore, thermal design is performed to develop verified thermal model and to secure thermal stability on the ground. In this study, thermal model correlation was performed to satisfy the criteria of correlation using ground thermal vacuum/thermal balance test results of LEO satellite optical payload. We also secured verified thermal model by controlling operating cycle of flight heaters. In addition, it was confirmed that all components are within the permissible temperature range through conducting orbit environment thermal analysis. We also secured thermal stability of the satellite.