• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2005년도 한국우주과학회보 제14권1호
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• pp.56-56
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• 2005

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1994년도 Proceedings of the Korea Automatic Control Conference, 9th (KACC) ; Taejeon, Korea; 17-20 Oct. 1994
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• pp.34-37
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• 1994

A satellite communications monitoring and control system(SCMCS) has been developed at ETRI to provide the capabilities of in-orbit test (IOT) for communications payload and communications system monitoring(CSM) for the satellite communications services. The paper discusses the system level design of SCMCS and its tasks.

• 한국항공우주학회지
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• 제39권5호
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• pp.474-480
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• 2011

지구의 저궤도에서 운용되는 영상센서는 극저온 환경에서 태양 복사 뿐 아니라 지구의 적외선 및 알베도(Albedo)의 영향을 받는다. 극한 환경에 노출되는 영상센서는 작동/비작 동시 허용 온도를 벗어나지 않도록 열설계가 필요하며, 정상상태 에너지 평형식을 통해 필요한 방열판 면적 및 히터 예비 설계 값을 설정한다. 일반적으로 위성체 패널에 주기를 갖는 발열장비가 장착되어, 패널의 일부를 방열판 면적으로 설계한다. 본 논문에서는 위성체와 분리하여 설계하는 영상센서의 열제어를 위하여, 내부에서 항상 발열하는 장비의 열을 히트파이프를 이용하여 패널에 장착된 방열판으로 효과적으로 전달하도록 설계하였다. 예비 설계값을 기준으로 수치해석에 기반을 두는 SINDA를 이용하여 궤도 열해석을 실시하여, 방열 면적 및 히터 설계는 쉽고 빠르게 계산되어졌다. 또한, 방열 성능을 유지하면서 질량을 줄이도록 방열판을 립형상(Rib-type)으로 설계하였으며, 궤도 열해석 결과, 영상센서의 열적 요구사항을 만족함을 검증하였다.

• International Journal of Aeronautical and Space Sciences
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• 제17권1호
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• pp.73-79
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• 2016

The characteristics of the SBAS satellite orbit and clock corrections are highly affected by the narrow network size in the Korean peninsula, which is expected to have an important role in the future dual frequency SBAS. The correlation between satellite corrections can be analyzed in terms of the spatial decorrelation effect which should be analyzed to keep the service area as wide as possible. In this paper, the characteristics of satellite error corrections for the potential Korean dual frequency SBAS were analyzed, and an optimal filter design approach is proposed to maximize the service area.

• Journal of Astronomy and Space Sciences
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• 제16권2호
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• pp.199-208
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• 1999

In this paper, KOMPSAT satellite launch and deployment operations are discussed. The U.S. Taurus launch vehicle delivers KOMPSAT satellite into the mission orbit directly. Launch and deployment operations is monitored and controlled by several international ground stations including Korean Ground Station (KGS). After separation from launch vehicle, KOMPSAT spacecraft deploys solar array by on-board autonomous stored commands without ground inter-vention and stabilizes the satellite such that solar arrays point to the sun. Autonomous ground communication is designed for KOMPSAT for the early orbit ground contact. KOMPSAT space-craft has capability of handing contingency situation by on-board fault management design to retry deployment sequence.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
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• pp.101-101
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• 2000

MSC(Multispectral Camera), which will be a unique payload on KOMPSAT-II, is designed to collect panchromatic and multi-spectral imagery with a ground sample distance of 1m and a swath width of 15km at 685km altitude in sun-synchronous orbit. The instrument is designed to have an orbit operation duty cycle of 20% over the mission life time of 3 years. MSC electronics consists of three main subsystems; PMU(Payload Management Unit), CEU(Camera Electronics Unit) and PDTS(Payload Data Transmission Subsystem). PMU performs all the interface between spacecraft and MSC, and manages all the other subsystems by sending commands to them and receiving telemetry from them with software protocol through RS-422 interface. CEU controls FPA(Focal Plane Assembly) which contains TDI(Timc Delay Integration) CCD(Charge Coupled Device) and its clock drivers. PMU provides a Master Clock to synchronize panchromatic and multispectral camera. PDTS performs compression, storage and encryption of image data and transmits them to the ground station through x-band.

• Journal of Astronomy and Space Sciences
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• 제17권2호
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• pp.309-316
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• 2000

KOMPSAT-2 will carry MSC(Multi-Spectral Camera) which provides 1m resolution panchromatic and 4m resolution multi-spectral images at the altitude of 685km sun-synchronous mission orbit. The mission operation of KOMSPAT-2 is to provide the earth observation using MSC with nadir pointing. KOMPSAT-2 will also have the capability of roll/pitch tilt maneuver using reaction wheel of satellite as required. In order to protect MSC from thermal distortion as well as direct sunlight, MSC shall be operated within the constraint of sun incidence angle. It is expected that the sunlight will not violate the constraint of sun incidence angle for normal mission operations without roll/pitch maneuver. However, during roll/pitch tilt operations, optical module of MSC may be damaged by the sunlight. This study analyzed sun incidence angle of payload using KOMPSAT-2 AOCS (Attitude and Orbit Control Subsystem) Design and Performance Analysis Soft ware for KOMPSAT-2 normal mission operations.

• 한국항공운항학회지
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• 제23권4호
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• pp.140-145
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• 2015

An on-board reaction wheel is payload of small satellite for space environment test. The reaction wheel is designed for considering physical, electrical, and environmental requirements. In this paper, we report design, manufacturing process and operation performance verification. Furthermore, the specifications of environmental test are performed under environmental conditions for guarantee of stability and reliability. The operation and environment test results are presented to meet the requirements at the reaction wheel flight model.

• 한국항공우주학회지
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• 제39권2호
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• pp.178-182
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• 2011

Dubaisat-1 저궤도 위성을 위한 FSK 수신기 RF 블록이 개발되었다. 수신기는 위성 명령을 위한 상향링크 채널에 주파수 편이 보상을 위한 도플러 추적 기능을 가지고 있다. 수신기는 LNA, 주파수 하향기 그리고 중간주파수 모듈로 구성되어 있다. 중간주파수 모듈은 입력신호에 대한 추종 및 고정을 위한 도플러 추적회로를 가지고 있다. 수신기는 무게, 전력소모, 추적속도 및 BER 등의 Dubaisat-1 요구사항을 만족한다.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2005년도 Proceedings of ISRS 2005
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• pp.586-588
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• 2005

The MSC (Multi Spectral Camera) system is a remote sensing payload to obtain high resolution ground image. This system uses lossy image compression method for &Direct mission& that transmit whole image during one contact. But some image degradation occurred especially at high compression ratio. To reduce this degradation, the MSC uses NUC (Non-uniformity Correction) Unit. This unit correct CCD (Charge Coupled Device)'s high-frequency non-uniformity. So high frequency contents of image can be minimized and whole system SNR can be maximized. But NUC has some disadvantage either. It decreases entire system reliability by adding one electronic system. Adding NUC also led to difficulty of electronic design, assembly and testability. In this paper, the comparison is performed between on-orbit non-uniform correction and on ground correction. by evaluating NUC advantage for the point of view of image quality. Using real MSC parameter and proper model, considerable reference point for the system design came to possible.