• 한국전산유체공학회지
• /
• 제13권2호
• /
• pp.48-54
• /
• 2008

COMS (Communication, Ocean and Meteorological Satellite) is a geostationary satellite and has been developing by KARI for communication, ocean and meteorological observations. It will be launched by ARIANE 5. Ka-band components are installed on South panel, where single solar array wing is mounted. Radiators, embedded heat pipes, external heat pipe, insulation blankets and heaters are utilized for the thermal control of the satellite. The Ka-band payload section is divided several areas based on unit operating temperature in order to optimize radiator area and maximize heat rejection capability. Other equipment for sensors and bus are installed on North panel. The ocean and meteorological sensors are installed on optical benches on the top floor to decouple thermally from the satellite. During the transfer orbit operation, satellite will be under severe thermal environments due to low dissipation of components, satellite attitudes and LAE(Liquid Apogee Engine) firing. This paper presents temperature and heater power prediction and validation of thermal control design during transfer orbit operation.

• 한국위성정보통신학회논문지
• /
• 제1권1호
• /
• pp.48-53
• /
• 2006

지상의 인프라 못지않게 중요시 되고 있는 GNSS (global navigation satellite system) 를 위한 한국형 위성기반 보강시스템을 제안하였다. 제안된 시스템은 가장 경제적인 위성기반 보강시스템 구축을 위하여 시스템 요소로서 현재 존재하는 시스템의 사용을 적극 고려하였다. 기준시스템은 현재 운용되고 있는 DGPS (differential global positioning system) 네트워크를 최대한 활용하는 것으로 하였고, 위성은 통신해양기상위성 1호(COMS-1)을 근간으로 조사하였다. 버스 시스템은 최소한의 변경이 예상되는 반면 통신탑재체는 주요한 변화를 겪게 될 것으로 분석되었다. 지상의 주제어 센터는 새롭게 건설되어야 하지만 소프트웨어, 인력 등 센터의 필수적인 요소는 DGPS네트워크의 운용 경험을 통하여 쉽게 확보될 수 있으리라 판단된다 .

• 한국지능시스템학회논문지
• /
• 제11권8호
• /
• pp.764-770
• /
• 2001

본 논문에서는 대용량의 퍼지 데이터를 고속으로 전송 및 추론하기 위해 새로운 PCI 버스 기반 병렬 퍼지 시스템을 제안한다. 많은 퍼지 데이터의 고속전송을 위해 PCI 9050 인터페이스를 사용하고, 병렬 퍼지 추론 시스템을 위한 병렬 퍼지 모듈들을 FPGA로 설계하여 PCI 타겟 코어로서 병렬로 동작하게 한다. 여기서 소속함수들의 각 요소와 전건부 또는 후건부부분의 병렬화을 고려하여 제안된 시스템을 VHDL을 사용하여 설계 및 구현하였다. 제안된 시스템은 실시간에 고속의 퍼지추론을 요하는 시스템 또는 대용량 인공위성 영상 데이터의 패턴 인식 등과 같이 다수의 전건부, 후건부의 변수를 갖는 시스템에 활용될 수 있다.

• 전력전자학회:학술대회논문집
• /
• 전력전자학회 2007년도 하계학술대회 논문집
• /
• pp.55-57
• /
• 2007

A Power control and Distribution Unit (PCDU) plays roles of protection of battery against overcharge by active control of solar array generated power, distribution of unregulated electrical power via controlled outlets to bus and instrument units, distribution of regulated electrical power to selected bus and instrument units, and provision of status monitoring and telecommand interface allowing the system and ground operate the power system, evaluate its performance and initiate appropriate countermeasures in case of abnormal conditions. In this work, we perform the preliminary design of a PCDU for the small Low Earth Orbit (LEO) Satellite applications. The main constitutes of the PCDU are the battery interface module, solar array regulators with maximum power point tracking (MPPT) technology, heater power distribution modules, internal converter modules for regulated bus voltage generation, power distribution modules of unregulated and regulated primary bus, and instrument power distribution modules.

• 한국조명전기설비학회:학술대회논문집
• /
• 한국조명전기설비학회 2005년도 춘계학술대회논문집
• /
• pp.283-287
• /
• 2005

In this paper, one general approach is proposed for the design of power system that can be applicable for next generation LEO satellite application. The power system consists of solar panels, battery, and power control and distribution unit(PCDU). The PCDU contains solar array modules, battery interface modules, low-voltage power distribution modules, high-voltage distribution modules, heater power distribution modules, on-board computer interface modules, and internal DC/DC converter modules. The PCDU plays roles of protection of battery against overcharge by active control of solar array generated power, distribution of unregulated electrical power via controlled outlets to bus and instrument units, distribution of regulated electrical power to selected bus and instrument units, and provision of status monitoring and telecommand interface allowing the system and ground operate the power system, evaluate its performance and initiate appropriate countermeasures in case of abnormal conditions. We review the functional schemes of the main constitutes of the PCDU such as the battery interface module, the auxiliary supply module, solar array regulators with maximum power point tracking(MPPT) technology, heater power distribution modules, spacecraft unit power distribution modules, and instrument power distribution module.

• 한국추진공학회지
• /
• 제23권3호
• /
• pp.96-103
• /
• 2019

본 연구에서는 지상 시험과 수치해석을 비교하여 시험용 달 궤도선의 추진제 공급부 설계 검증을 하고자 한다. 비행 모델의 유동 흐름을 모사할 수 있는 지상 시험용 검증 모델을 제작하고 있으며, 지상 시험용 검증 모델과 비교하기 위한 항목을 배관 내 전체 압력 강하량, 추력기 밸브 구동에 의한 수격현상 그리고 유량 제어 및 수격현상 완화를 위한 오리피스 장착의 세 가지로 선정하였다. 해석 결과를 향후 지상 시험 결과와 비교하여 최종적으로 설계 확정을 위한 근거 자료를 확보하고자 한다.

• 항공우주기술
• /
• 제4권2호
• /
• pp.60-64
• /
• 2005

과학기술위성 2호의 주요 임무는 주 탑재체인 마이크로웨이브파 라디오미터(DREAM: Dual-channel Radiometers for Earth and Atmosphere Monitoring)개발, 부 탑재체인 레이저 반사경(SLR: Satellite Laser Ranging) 개발, 그리고 위성체 핵심기술 선행연구를 위한 Frame-Type 위성구조체, 복합소재 태양전지판, Dual-Head 별추적기, CCD 태양센서, 펄스형 플라즈마 추력기, 소형 탑재 컴퓨터 및 고속 X-band 송신기 개발 등을 포함한 100kg급 저궤도 소형위성 개발이다. 본 논문에서는 과학기술위성 2호 시스템에 대하여 설명을 한다. 과학기술위성 2호의 시스템 정의 및 기본적인 운영개념, 과학기술위성 2호의 주 탑재체인 마이크로웨이브파 라디오미터, 부 탑재체인 레이저 반사경, 그리고 이들을 지원하기 위한 위성본체 등을 포함한다.

• 한국전산유체공학회지
• /
• 제11권3호
• /
• pp.8-13
• /
• 2006

The north panel of a geostationary satellite is used as one of the main radiators, on which communication equipment or bus equipment are installed. The thermal control of panel is designed by using embedded heat pipes and surface heat pipes (or external heat pipes) to spread out heat dissipated from equipment all over the radiator evenly and finally to reject the heat to the space through the radiator efficiently. This panel is also divided by several areas based on the operating temperature and dissipation of equipment in order to increase heat rejection capability of radiator. The thermal analysis is carried out for the hot case, Winter Solsitce EOL (End Of Life), in order to validate thermal design of the panel utilized 6 surface heat pipes and 8 embedded heat pipes. The sensitivity studies for the heat pipe failure case and no heat pipe case are performed and compared to its normal state. The heat transport capability of heat pipe is also obtained from these calculations.

• International Journal of Aeronautical and Space Sciences
• /
• 제1권1호
• /
• pp.70-80
• /
• 2000

The attitude knowledge error model is formulated for specifically KOMPSAT attitude determination system using the Lefferts/Markley/Shuster method, and the attitude determination(AD) error analysis is performed so as to investgate the on-board attitude determination capability of KOrea Multi-Purpose SATellite(KOMPSAT) using the covariance analysis method. Analysis results show there is almost no initial value effect on Attitude Determination (AD) error and the sensor noise effects on AD error are drastically decreased as is predicted because of the inherent characteristic of Kalman filter structure. However, it shows that the earth radiance effect of IR-sensor(earth sensor) and the bias effects of both IR-sensor and fine sun sensor are the dominant factors degrading AD error and gyro rate bias estimate error in AD system. Analysis results show that the attitude determination errors of roll, pitch and yaw axes are 0.056, 0.092 and 0.093 degrees, respectively. These numbers are smaller than the required values for the normal mission of KOMPSAT. Also, the selected on-orbit data of KOMPSAT is presented to demonstrate the designed AD system.

• Journal of Astronomy and Space Sciences
• /
• 제17권1호
• /
• pp.117-122
• /
• 2000

The KOMPSAT(Korea Multi-Purpose SATellite) has two optical imaging instruments called EOC(Electro-Optical Camera) and OSMI (Ocean Scanning Multispectral Imager). The image data of these instruments are transmitted to ground station and restored correctly after post-processing with the telemetry data transfeered from KOMPSAT spacecraft. The major timing information of the KOMPSAT is OBT (On-Board Time) which is formatted by the on-board computer of the spacecraft, based on 1Hz sync. pulse coming from the GPS receiver involved. The OBT is transmitted to ground station with the house-keeping telemetry data of the spacecraft while it is distributed to the instruments via 1553B data bus for synchronization during imaging and formatting. The timing information contained in the spacecraft telemetry data would have direct relation to the image data of the instruments, which should be well explained to get a more accurate image. This paper addresses the timing analysis of the KOMPSAT spacecraft and instruments, including the gyro data timing analysis for the correct restoration of the EOC and OSMI image data at ground station.