• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.230-235
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• 2005

As a precedence research for the COMS(Communication, Oceanic, and Meteorological Satellite), this paper proposes the SMTC(Soble Masked Tracking Guideline) algorighm for a fast landmark matching. The experimental results show that proposed algorithm should recude a lot of calculative time.

• Proceedings of the KSRS Conference
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• 2006.03a
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• pp.390-393
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• 2006

본 논문에서는 현재 개발 중인 통신해양기상위성(COMS : Communication, Ocean and Meteorological Satellite)의 데이터를 처리하는 영상 데이터 전처리 시스템 (IMPS, IMage Preprocessing Subsystem)의 설계 과정과 예비설계 결과를 설명한다.

• Proceedings of the KIEE Conference
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• 2008.07a
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• pp.1941-1943
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• 2008

본 논문에서는 통신해양기상위성에서 사용되어지는 탑재컴퓨터 구조를 제시하였다. 제시된 구조는 2대의 동일한 탑재컴퓨터가 외장형 형태의 잉여구조로 배치되게 하였다. 또한 2대의 컴퓨터 모두 Hot Redundancy로 동작하며 Prime 탑재컴퓨터와 동일한 작업을 Redundant 탑재컴퓨터에서도 수행토록 하였다.

• Proceedings of the KSRS Conference
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• 2009.03a
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• pp.327-330
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• 2009

해양위성센터는 2009년 발사예정인 통신해양기상위성(COMS)의 해양위성관측자료의 원활한 수신 및 분석자료의 생산, 관리, 분배를 담당하고 있다. 정지궤도해양위성 위성자료수신시스템을 비롯하여, 위성자료전처리시스템, 해양위성자료처리시스템, 자료관리시스템, 통합감시시스템등을 통해서 수신/처리하는 다양한 위성자료를 해양 연구자들이 쉽게 찾아 사용할 수 있도록 위성자료분배시스템을 구축하고 있다. 위성자료의 활용성 증대 및 확산 유도를 위한 위성자료 DB 및 온라인 배포 사이트를 구축하며, 위성자료배포현황 관리를 위한 관리자 페이지도 운영할 계획이다.

• Proceedings of the KSRS Conference
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• 2007.03a
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• pp.192-197
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• 2007

한국해양연구원에서는 2008년 으 로 예정된 통신해앙기상위성(통해기)의 발사에 맞춰 통해기에 탑재된 해색센서(GOCI)자료의 수신，처리，배포를 위한 해앙위성센터 구축을 진행하고 있다. 전파수신환경，자연환경 등을 고려하여, 해양위성센터 위치를 안산(한국해양연구원 본원)으로 정하였다. 이에 따라，지금까지 안테나를 포함한 수신시스템에 대한 상세설계，내부 구조 변경，H/W 및 N/W 설계，자료처리 시스템 일부의 도입을 실시하였다. 여기에서는，해양위성센터 구축 현황을 소개하고，해색센서(GOCI)자료의 수신，처리，배포 시스템 설계 결과를 소개하고자 한다. 가장 중요한 자료 배포 시스템은 기본적으로 온라인으로 구성되며, 수신된 데이터를 1시간 내에 제공하기 위해 웹호스팅 등 외부데이터 제공 시스템도 구축하는 것을 구상 중에 있다.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.51-56
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• 2010

There are two main software in COMS ground station at the normal mode operation - stationkeeping and wheel off-loading. In this paper, ground software validation test for wheel off-loading is summarized and described. The wheel off-loading was performed the design change from E3000 heritage and analyzed. The wheel off-loading of ground software has two part; one is wheel off-loading management for parameters change at the thruster set switching time and the other is wheel off-loading set-point being sent to satellite for the reference momentum.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.11
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• pp.54-60
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• 2006

This paper discusses wheel offloading approaches of the COMS which has a single solar array system for the accommodation of the optical payloads. First of all, in an effort to reduce fuel consumption and reflect practical implementation point of view, thruster sets for wheel offloading are proposed based on numerical analyses taking into account the COMS configuration. In this analysis, it is assumed that the wheel offloading is conducted twice a day. Secondly, in order to evaluate the effectiveness of the proposed thruster sets, orbit simulations are conducted for several wheel offloading approaches and compared.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.9
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• pp.81-88
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• 2005

This paper analyzes the fuel consumption for the momentum dumping of the COMS which has a single solar array system. First, numerical analyses are conducted to find an optimal momentum dumping time considering the COMS configuration. It is assumed that the momentum dumping is conducted once a day and at a fixed time of a day. Secondly, in an effort to reduce the momentum dumping fuel consumption, this paper proposes a new approach which combines the momentum dumping and the ordinary north/south stationkeeping. Finally, to evaluate the proposed technique, the stationkeeping simulations are conducted and analyzed.

• Journal of Satellite, Information and Communications
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• v.1 no.2
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• pp.95-100
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• 2006

The COMS(Communication, Ocean and Meteorological Satellite) EPS(Electrical Power Subsystem) is derived from an enhanced Eurostar 3000 version. Eurostar 3000 EpS is fully autonomous operation in nominal conditions or in the event of a failure and provides a high level of reconfigure capability. This paper introduces the COMS EPS preliminary design result. COMS EPS consists of a battery, a solar arrat wing, a PSR(Power Supply Regulator), a PRU(Pyrotechnic Unit), a SDAM(Solar Array Drive Mechanism) and relay and fuse brackets. COMS EPS can offer a bus power capability of 3 kW. The solar array is made of a deployable wing with two panels. One type fo solar cells is selected ad GaAs/Ge triple junction cells. Li-ion battery is base lined with ten series cell module of five cells in parallel. PSR associated to battery and solar array wing generates a power bus fully regulated at 50 V. Power bus os centralized protection and distribution by relay and fuse brackets. PRU provides power for firing actuarors devices. The solar array wing is rotated by the SADM under control of the attitude orbit control subsystem. The control and monitoring of the EPS, especially of the battery, is performed by the PSR in combination with the on-board software.

• Satellite Communications and Space Industry
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• v.15 no.1
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• pp.60-67
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• 2008