• Journal of Satellite, Information and Communications
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• v.1 no.2
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• pp.32-37
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• 2006

ETRI has been developing the Ka-band Antenna subsystem for COMS(Communications, Ocean, and Meteorological Satellite) which will be launched at the end of 2008. The antenna subsystem employs the two parts: East Panel and West panel of spacecraft. ETRI in cooperation with domestic companies are under design phase for the antenna subsystem development. This paper focuses in the Ka-band reflector pointing error analysis to verify the antenna subsystem performance specification, especially EOC gain variation etc. The analysis performed is that induced by reflector surface deformation as a result of thermo elastic distortion. Beam pattern variations are verified by the use TICRA

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.2
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• pp.195-199
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• 2010

(255,223) RS(Reed-Solomon) code which is the CCSDS(Consultative Committee for Space Data Systems) standard was used in the STSAT-3 to correct errors during the downlink of payload data. The RS encoder developed by VHDL was implemented in MMU(Mass Memory Unit). Moreover, the RS decoder developed by C-language was implemented in the DRS(Data Receiving System) of ground station. In this paper, we reported the design and analysis results of RS(255,223) for STSAT-3. The BER(Bit Error Rate) performance from MMU to DRS was confirmed through the downlink test at 16 Mbps. Also, the error correction performance and capability of RS(255,223) was tested by the manual attenuation of the RF(Radio Frequency) signal in the X-band transmitter resulting in putting some errors in the communication line.

• Journal of Satellite, Information and Communications
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• v.10 no.3
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• pp.131-136
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• 2015

In this paper, prior to the flight model X-band dual-mode circular cavity filter required for the high power transmission of the observation payload in the geostationary satellite, the development model are designed and analyzed to show the analytical multipactor requirement margin. First of all, the multipaction breakdown power sensitivities were analyzed by changing the iris width and thickness within the filter, and through that the iris width and thickness was selected and then the multipaction threshold powers over the frequencies within the bandwidth were analyzed and the required margin of 8 dB was obtained. Also for the high power transmission filter, another important phenomena known as corona breakdown are analyzed for the iris width and thickness changes. Finally the development model manufactured was tested and the results met the key requirements.

• Journal of Astronomy and Space Sciences
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• v.18 no.3
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• pp.209-218
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• 2001

Global exposure time distribution through all-sky survey, one of main science missions of KAISTSAT-1, has been simulated. Exposure time distribution has its minimum on the celestial equator and increases with moving to polar regions according to the present mission operation scenario. SAA (South Atlantic Anomaly) and the moon can make further decreases of exposure time around the celestial equator Effects of SAA on all-sky survey exposure time can be compensated with a simple observational scheduling, orbit exchange between orbits allocated to all-sky survey passing through the SAA region and ones allocated to upper atmosphere observations not affected by SAA. It, however, seems that present exposure time distribution is not adequate for the concrete study of the evolution of interstellar medium. A scheme for active time allocation is needed for redistribution of exposure times weighted around the celestial poles, and additional studies on the advanced mission operation and the observational scheduling are also needed.

• Aerospace Engineering and Technology
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• v.11 no.2
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• pp.195-207
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• 2012

This paper deals with attitude controller design and integrated performance tests on the nitrogen gas reaction control system of KSLV-I. Some major factors which are necessarily required in designing a stabilizing controller of reaction control system are investigated, and the corresponding equations are given. Experimental configurations and test conditions for system level integrated performance tests of the KSLV-I nitrogen gas reaction control system are summarized. It is shown that, based on the experimental data, operational performances of nitrogen gas reaction control system can be analyzed in terms of gas consumption, thrusting force, time delay, and specific impulse. It is also shown that a conformance of the controller to flight can be evaluated. Finally the onboard controller of KSLV-I reaction control system is shown to perform normally with enough stability margin via the first flight test result.

• The Bulletin of The Korean Astronomical Society
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• v.35 no.1
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• pp.40.2-40.2
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• 2010

MIRIS 우주관측카메라는 과학기술위성 3호의 주탑재체로서 $0.8{\sim}2.0{\mu}m$의 근적외선영역에서 우주배경복사와 우리은하 평면의 Pa-$\alpha$ survey 관측을 목적으로 한다. 이러한 임무를 수행하기 위해 MIRIS 우주관측카메라에는 MCT(HgCdTe) IR 검출기가 사용되고 6개의 필터를 장착할 수 있는 필터휠이 설계되었으며, 열잡음을 줄이고 원하는 SNR을 얻기 위해 모두 100K 이하로 냉각이 요구된다. 효과적인 냉각 및 저온유지를 위해서 외부의 열을 1차적으로 차단하는 Cryostat 외부용기와 100K 이하로 냉각되는 내부 Cold Box의 이중구조를 가지는 Dewar가 설계 되었다. 내부 Cold Box의 냉각은 소형 stirling cooler로 이루어지고 외부의 열 유입량이 Cooler의 냉각용량을 넘지 않도록 설계하였다. Cryostat 외부용기는 radiation cooling으로 냉각되어 200K 이하의 온도를 유지하며 내부 Cold Box로의 열유입을 최소화하기 위해 GFRP(Glass Fiber Reinforced Plastic) 단열 지지대와 MLI(Multi Layer Insulation)가 사용된다. 또한 100K으로 냉각시 필터고정부와 Cold Box 구조에서 일어날 수 있는 구조적인 피로도를 줄이고 열변형에 의한 문제를 방지하기 위한 고려가 설계에 포함되었다. FM(Flight Model)은 고진공 환경의 우주공간에서 문제가 발생하지 않도록 설계되었다. 또한 EQM 진동시험결과를 토대로 발사환경에서 발생하는 강한 진동을 견딜 수 있도록 FEM(Finite Elements Method) 구조해석을 통하여 필터고정부에 flexible structure 설계와 완충제를 추가하고 필터휠 구동부와 harness 고정부 및 cooler 지지부를 비롯한 전체 구조물에서 충분히 진동을 극복할 수 있도록 설계하였다.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2012.10a
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• pp.740-743
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• 2012

The initial role of the operating system acts as an intermediary between the computer and the user, and, hardware and process management, and the convenience of your computer system is to use. Of these operating systems as well as servers and personal computers, smartphones and tablet mounted on mobile devices such as mobile operating system was born. Mobile Operating System has been expanded a TV or Car Area that built into a simple embedded operating system, is emergence of a variety of devices, cloud services, combined with the desire of users due to the high built-in simple embedded operating system that was working on a TV or a car is expanding to the area. The reason for the emergence of a variety of devices, cloud services, combined with the desire of users is high. In this paper, the mobile operating system, N-Screen, Smart TV to find out about and through the analysis of the major smart TV, the future Find out about trends in the mobile operating system.

• Proceedings of the KSRS Conference
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• 2009.03a
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• pp.167-171
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• 2009

정지궤도에서는 세계 최초의 해양관측위성으로 개발된 정지궤도 해양위성(GOCI, Geostationary Ocean Color Imager)은 통신해양기상위성(COMS, Communication, Ocean and Meterological Satellite)의 탑재체로서 2009년말 발사 예정이다. 정지궤도 해양위성의 복사보정은 센서의 전기적 특성에 의한 잡음을 제거하기 위한 암흑전류 교정(Dark Current Correction)을 먼저 수행한 다음, 주운영지상국인 해양위성센터(KOSC, Korea Ocean Satellite Center)에서 수신된 위성의 원시자료의 Digital Number(DN)를 실제 해양원격탐사에서 이용하는 물리량인 복사휘도(Radiance, $W/m^2/{\mu}m/sr$)로 변환하는 복사보정을 수행한다. 정확도 높은 복사보정을 수행하기 위해서는 기준광원의 복사휘도와 센서의 물리적 특성을 정확하게 알아야 한다. 정지궤도 해양위성 궤도상 복사보정(on-orbit radiometric calibration)에서는 태양이 기준광원이기 때문에, 기준 태양복사모델(Thuillier 2004 Solar Irradiance Model)에서 지구-태양간 거리 변화(1년 주기)를 보정한 태양의 방사도 (Irradiance)를 이용하고, 태양입사각에 대한 태양광 확산기의 감쇄 특성 변화를 고려하여 센서에 입력되는 복사휘도를 계산한다. 센서의 물리적 특성으로 인한 복사보정의 오차를 줄이기 위해 우주방사선 및 우주먼지(space debris)로 인해 위성 운용기간 중 그 특성이 저하되는 태양광 확산기(solar Diffuser)의 특성변화를 모니터링하기 위한 DAMD(Diffuser Aging Monitoring Device)를 이용한다. 정지궤도 해양위성 주관운영기관인 한국해양연구원의 해양위성센터에서는 정지궤도 해양위성 복사보정을 수행하기 위한 S/W를 통신해양기상위성 자료처리시스템 개발사업의 일환으로 개발하였으며, 관련 성능 시험을 수행하고 있다.

• Journal of Navigation and Port Research
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• v.34 no.5
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• pp.311-317
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• 2010

Mobile Harbor(MH) is a new paradigm for maritime transport system introduced in Korea, the target of which is to carry out ship-to-ship cargo operation rapidly and effectively even under a condition of sea state 3. A MH ship is moored alongside a large container vessel anchored at the defined anchorage and also equipped with gantry cranes for handling containers. The MH study concerned includes rapid container handling system, optimum design for floating structure, hybrid berthing & cargo operation system, design for cargo handling crane, etc. This paper is to deal with a conceptual design of a stabilized mooring system and mooring equipment under a condition of ship-to-ship mooring. In this connection, we suggest a positioning control winch system in order to control heave motions of the MH ship which is to add constant brakepower and stabilized function to an auto-tension winch and mooring equipment used currently in large container ships.

• Journal of Satellite, Information and Communications
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• v.7 no.2
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• pp.67-71
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• 2012

This paper represents the impact analysis results of antenna reflector for the UHF-band antenna of Space Launch Vehicle. Three types of UHF-band antenna reflector model have been proposed and simulated to compare their characteristics such as resonance frequency, reflection loss and radiation pattern etc. Simulation results showed that resonance frequency and return loss of each reflector models were rarely affected even if reflector sizes are changed. The antenna gain and 3dB bandwidth were slightly changed to the worse directions as the reflector sizes are smaller.