• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.45-45
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• 2003

경희대학교 우주탑재체 연구센터에서 개발중인 과학기술위성 2호(STSAT-2) 주탑재체인 Lyman-alpha Imaging Solar Telescope(LIST)의 개발 현황에 대해 논의한다. LIST는 2002년 10월에 개발에 착수한 후 상위수준의 시스템 디자인을 확정하는 System Design Review(SDR)에 이어, 현재 기초 기기 디자인을 수행하는 Preliminary Design Review(PDR) 단계에 와 있다. 본 연구에서는 LIST의 각 부분별 상세 디자인과 시스템 엔지니어링에 대해 논의한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.10
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• pp.992-997
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• 2010

The Propulsion Control Module(PCM) of Hall-thruster Propulsion System(HPS) for Science and Technology Satellite-3 (STSAT-3) has the flow control accuracy of less than ${\pm}$3% and the pressure control accuracy of less than ${\pm}$5%. The pressure controller adjusts pressure around the set point by using a Proportional Flow Control Valve (PFCV) and a high pressure transducer, while the flow controller regulates the flow rate using PFCV and the anode current telemetry of the Hall Thruster. The controllers are chosen as the Proportional and Integral(PI) type, and the PI gains are tuned based on the Matlab simulations. The result of the PCM test had the flow control accuracy of less than ${\pm}$1.87% and the pressure control accuracy of less than ${\pm}$5%. This paper describes the design, realization, and performance test results of the PCM.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.2
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• pp.96-100
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• 2006

We develop the Dual Head Star Tracker (DHST) to obtain the attitude information of science and Technology Satellite2 (STSAT-2). Because most of star sensor has only one head camera, star recognition is impossible when camera point to sun or earth. We therefore considered the DHST which can obtain star images from two spots simultaneously. That is, even though we fail a star recognition from an image obtained by one camera, it is possible to recognize stars from an image obtained by the other camera. In this paper, we introduce engineer model (EM) of the DHST and propose a star recognition and a star track algorithm.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.11
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• pp.115-120
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• 2005

This paper describes the design and implementation of engineering model(EM) of Mass Memory Unit(MMU) for Science and Technology Satellite 2(STSAT-2) and the results of integration test. The use of Field-Programmable Gate Array(FPGA) instead of using private electric parts makes a miniaturization and lightweight of MMU possible. 2Gbits Synchronous Dynamic Random Access Memory(SDRAM) module for mass memory is used to store payload and satellite status data. Moreover, file system is applied to manage them easily in the ground station. RS(207,187) code improves the tolerance with respect to Single Event Upset(SEU) induced in SDRAM. The simulator is manufactured to verify receiving performance of payload data.

• The Transactions of The Korean Institute of Electrical Engineers
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• v.59 no.2
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• pp.417-422
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• 2010

When memory devices are exposed to space environments, they suffer various effects such as SEU(Single Event Upset). Memory systems for space applications are generally equipped with error detection and correction(EDAC) logics against SEUs. In this paper, several error detection and correction codes - RS(10,8) code, (7,4) Hamming code and (16,8) code - are analyzed and compared with each other. Each code is implemented using VHDL and its performances(encoding/decoding speed, required memory size) are compared. Also the failure probability equation of each EDAC code is derived, and the probability value is analyzed for various occurrence rates of SEUs which the STSAT-3 possibly suffers. Finally, the EDAC algorithm for STSAT-3 is determined based on the comparison results.

• Proceedings of the KIPE Conference
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• 2007.07a
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• pp.46-48
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• 2007

위성체의 전력계 서브시스템은 임무기간 중 탑재체 및 위성체 버스의 각 서브시스템으로 전력을 제어하고 분배한다. 과학기술위성 2호의 전력계 서브시스템은 태양에너지를 전기에너지로 변환하는 태양전지판, 에너지 저장을 위하여 재충전이 가능한 배터리, 그리고 태양전지판으로부터 배터리를 통해 다른 장치에 전력을 전달하는 전력조절 및 제어시스템으로 구성된다. 본 논문은 과학기술위성 2호의 전력계 서브시스템의 구성과 상세설계사양에 관하여 설명한다.

• The Transactions of the Korean Institute of Electrical Engineers D
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• v.54 no.8
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• pp.482-485
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• 2005

STSAT-2 is first satellite which is scheduled to launch by first Korea launcher. Ground station Baseband Controller(GBC) for operating STSAT-2 is now developing. GBC control data flow path between satellite operation computers and ground station antennas and count number of received data packets among demodulated audio signals from three antennas and also set data flow path to good-receiving antenna automatically In GBC two uplink FSK modulators(1.2kbps, 9.6kbps) and six downlink FSK demodulators(9.6kbps, 38.4kbps) are embedded. STSAT-2 GBC hardware is more simpler than STSAT-1 GBC by using FPGA in which all digital logic implemented. Now test and debugging of GBC hardware and Software(FPGA Code and CBC Manager Program) is well progressing in SaTReC, KAIST. This paper introduce GBC structure, functions and test results.

• Proceedings of the KIEE Conference
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• 2005.05a
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• pp.116-118
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• 2005

STSAT-2 is first satellite which is scheduled to launch by first Korea launcher. After launch Ground station Baseband Controller(GBC) for operating STSAT-2 is now developing. GBC control data flow path between satellite operation computers and ground station antennas. and GBC count number of received data packets among demodulated audio signals from three antennas and set data flow path to good-receiving antenna automatically. In GBC two uplink FSK modulators(1.2kbps, 9.6kbps) and six downlink FSK demodulators(9.6kbps, 38.4kbps) are embedded. STSAT-2 GBC hardware is more simpler than STSAT-1 GBC by using FPGA in which all digital logic implemented. Now test and debugging of GBC hardware and Software(FPGA Code and GBC Manager Program) is well progressing in SaTReC, KAIST. This paper introduce GBC structure, functions and test results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.1
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• pp.98-105
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• 2004

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.5
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• pp.460-465
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• 2007

This paper deals with the Fine Digital Sun Sensor (FDSS) for Science & Technology Satellite 2(STSAT-2). The FDSS was firstly developed by using CMOS-Image sensor(CIS) in South Korea. This paper will describe the configuration of the FDSS, the design of the optical part, the analysis result of the optical characteristics of the sunlight, and the calibration result measured by solar simulator.