• Proceedings of the Optical Society of Korea Conference
• /
• 2003.02a
• /
• pp.98-99
• /
• 2003

2005년 국산 소형위성 발사체에 탑재되어 발사 될 예정으로, 과학기술위성2호의 개발이 2002년 10월부터 시작되었다. 과학기술위성2호는 약 100kg의 소형위성으로, 경사각 60～80$^{\circ}$의 300km x 1500km 타원궤도에 발사될 것으로 예상되고 있으며, 라만-a태양촬영망원경(LIST, Larman-a Imaging Solar Telescope)과 레이저정밀거리측정용 반사경이 각각 주 및 부 탑재체로 탑재될 예정이다. 위성레이저정밀거리측정(SLR, Satellite Laser Ranging)이란 위성간의 거리를 가장 정확하게 측정할수 있는 축지학적 기술이다. (중략)

• Aerospace Engineering and Technology
• /
• v.2 no.2
• /
• pp.45-49
• /
• 2003

A Bake-Out test for STSAT-1 FM(Flight Model) was performed in a Bake-Out Chamber at SITC(Satellite Integration & Test Center) in KARI(Korea Aerospace Research Institute). The purpose of this test is to measure and analyze the outgassing rate to affect the optical equipment(FIMS) and to eliminate contaminants through the high temperature bake-out. This Bake-Out test is composed of three parts which are honeycomb panels & harnesses(Batch 1), an assembled satellite(Batch 2), and a disassembled satellite(Batch 3). For each test, quantitative and qualitative measurements and analysis were performed using TQCM(Thermoelectric Quartz Crystal Microbalance) and RGA(Residual Gas Analyzer.)

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.34 no.2
• /
• pp.96-100
• /
• 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
• /
• v.33 no.11
• /
• pp.115-120
• /
• 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.

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

• Bulletin of the Korean Space Science Society
• /
• 2003.10a
• /
• pp.45-45
• /
• 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
• /
• v.35 no.5
• /
• pp.460-465
• /
• 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.

• The Transactions of the Korean Institute of Electrical Engineers D
• /
• v.54 no.8
• /
• pp.482-485
• /
• 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
• /
• 2005.05a
• /
• pp.116-118
• /
• 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.

• Aerospace Engineering and Technology
• /
• v.9 no.2
• /
• pp.123-128
• /
• 2010

Science and Technology SATellite-3 (STSAT-3) is science purpose satellite which weighs below 170kg. This is classified as small satellite or micro satellite more specifically. The launch vehicles (launchers) for small satellite has their own requirements for environmental interface. Since the small satellites are usually launched with cluster or multiple payloads, the selection option for appropriate launcher is limited. Therefore, the satellite should be designed with the consideration of environmental requirements of these launchers. In this paper, the environmental requirement of most candidated launchers for small satellite is summarized and give satellite environmental requirement to accommodate all launchers requirements.