• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.166.2-166.2
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• 2012

국내에서 개발한 고기동 저궤도 위성이 일본 다네가시마 우주센터에서 2012년 5월 18일 발사되었다. 자세제어계는 위성의 임무수행을 완수할 수 있도록 발사 후부터 위성 수명 기간 동안 자세명령을 생성하고 제어 및 결정을 하며, 궤도 조정과 모멘텀 덤핑등의 임무를 수행한다. 이러한 임무 수행을 가능하게 하기 위해 자세제어계는 적절한 센서와 구동기 조합을 사용하여 추력기 기반 안전모드, 궤도 조정을 위한 Del-V Burn 기동 모드, 태양지향 서브모드 및 목표지향 서브모드 등을 설계했다. 고기동 위성의 초기 운용 중 자세제어계는 자세제어계 하드웨어의 초기 구동 및 점검을 수행하고 설계한 각 모드의 기능과 성능 확인을 수행하게 된다. 본 연구는 성공적으로 완료한 자세제어계 하드웨어의 초기 점검 결과를 소개하는 것이 목적이다. 초기 운용은 위성이 발사된 직후 탑재컴퓨터가 깨어나면서부터 시작되는데, 발사 후 최초 접속시 추력기 기반 안전모드에서 태양 획득 성능 및 제어 성능을 확인한 후 정상 상태 모드인 태양지향 자세로 전환하기 위해 자세제어계 하드웨어인 별 추적기, 자기토커, 반작용휠의 초기 구동 및 점검을 수행하였다. 본 연구에서는 각 하드웨어의 초기 구동 점검과 성능 및 기능 요구조건 만족에 대한 성능 분석 결과를 정리하였다.

• The Journal of the Convergence on Culture Technology
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• v.9 no.6
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• pp.1057-1063
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• 2023

The urban railway sleeper floating track, the subject of this study, is an anti-vibration track to reduce vibration transmitted to the structure. currently, the replacement cycle of resilience pad for sleeper floating tracks is set and operated based on load. however, most previous studies were conducted on load-based structural safety aspects, such as fatigue life evaluation of sleeper anti-vibration pads and increase in track impact coefficient and track support stiffness due to increase in spring stiffness. therefore, in this study, we measure the vibration acceleration of the ballast for each analysis section and use the results of 7 million fatigue tests to calculate the spring stiffness of the resilience pad for each section. the spring stiffness of the resilience pad calculated for each section was set as the analysis data and the concrete vibration acceleration was derived analytically. the adequacy of analysis modeling was verified as the analyzed concrete bed vibration acceleration for each section was within the field-measured concrete bed vibration acceleration range. using the vibration acceleration curve according to the derived spring stiffness change, the spring stiffness of the resilience pad is estimated from the measured vibration acceleration. therefore, we would like to present a technique that can estimate the spring stiffness of resilience pad of a running track using the vibration acceleration of the measured concrete bed.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.16 no.2
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• pp.141-151
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• 2003

Railway bridges are subject to dynamic loads generated by the interaction between moving vehicles and the bridge structures. These dynamic loads result in response fluctuations in bridge members. To investigate the real dynamic behavior of the bridge, therefore, a number of analytical and experimental Investigations should be carried out. In this paper, a train/track/bridge interaction analysis program for evaluating the dynamic characteristics of bridges due to KTX operation in terms of structural safety, operational safety and passenger comfort is developed. To build a practical model of train/track/bridge, Hertzian spring for wheel/rail contact modeling and Winkler element for ballast are applied. This program also used torsional degree of freedom and constraint equation based on geometrical relationship in order to take into consideration three-dimensional eccentricity effect due to the operation on double track through quasi-three dimensional analysis. To verify the developed Program, comparison has been made between the measured results and those of simulation of the typical PSC box bridge(2@40m=80m) of the KHSR bridges.

• Satellite Communications and Space Industry
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• v.7 no.2 s.16
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• pp.34-46
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• 1999

한국통신은 현재 동경 116도 궤도에 무궁화1호 및 2호를 운영하며 통신 및 방송 서비스를 제공하고 있다. 무궁화 3호 위성은 대용량 위성으로 1/2호 위성의 중계기 용량을 모두 수용하며 동남아 지역을 대상으로 하는 가변빔 및 Ka-band 중계기를 탑재하고 있다. 3호 위성은 발사 후 동경 116도에 위치하여 올해로 수명이 다하는 1호 위성이 제공하는 서비스 및 2호 위성 서비스를 수용할 예정이며, 2호 위성은 113도로 이동하여 신규 서비스를 수용할 예정이다. 본 고에서는 무궁화3호 위성 탑재체의 설계사양 및 설계단계 성능분석에 대해 간략하게 소개하며, 분석결과와 실제 측정 데이터를 비교하였다. 또한 Ka-band 중계기의 주요 성능 파라미터들의 변화에 따라 디지털 통신캐리어를 가정하여 무궁화3호 위성 통신시스템의 비트오율 성능분석을 실시하였다. 시뮬레이션을 실시한 이유는 탑재체에 실제 서비스 캐리어가 실린 경우 탑재체의 통신품질을 예측하기 위함이다. 무궁화3호 위성의 공정현황 및 제공서비스에 대해서도 간략하게 소개하였다.

• Journal of Space Technology and Applications
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• v.3 no.2
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• pp.101-117
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• 2023

Active debris removal, a technology that approaches and removes space debris in orbit, and the on-orbit service, a technology for extending the mission life of satellites by fuel charging or by exchanging the battery, are gaining interest with the growth of the space community. SaTReC plans to develop a satellite capable of capturing and removing Korean satellites orbiting in space after the end of their missions. In contrast to the previously launched satellites by Korea, which were mainly intended to observe Earth and the space environment, rendezvous/docking technologies, as required in the future during, for instance, space exploration missions, will be implemented and demonstrated. In this paper, an orbital transition method for next-generation small satellites that will capture and remove space debris will be introduced. It is assumed that a small satellite with a mass of approximately 200 kg will be injected into the mission orbit through Korea Space Launch Vehicle-II in 2027. Because the satellite must access the target using a minimum amount of fuel, an approaching technology using Earth's J2 perturbation force has been developed. This method is expected to enable space debris removal missions for relatively lightweight satellites and to serve as the basis for carrying out a new type of space exploration in what is termed the 'Newspace' era.

• Journal of Satellite, Information and Communications
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• v.5 no.2
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• pp.29-33
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• 2010

Satellites industry has been developing with the commercial and military needs. Because power system of satellite is very important to survival operation and hard to test, increasing reliability is very critical. Due to LEO small satellites are very sensitive to power system, effective stabilization control is important. Therefore, this paper introduce methods for general modeling of power converting system which it can be used design of controller and analysis of external disturbance influences. In conclusion, a modeling of LEO small satellites power converting system and a possible guide line to design reliable controller which optimizing power converters of LEO small satellite are generated.

• Journal of Satellite, Information and Communications
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• v.6 no.2
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• pp.102-106
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• 2011

Space Environment including Solar activities such as Solar explosion, Corona Mass Ejection(CMS) is always not friendly for human. Especially it may be fatal to artificial satellites. The lifetime of geostationary communication satellites are reducing due to plasma such as electrons, protons etc. emitting from Sun. This is because the active components constituting communication satellite are easily affected by plasma. Even though the radiation shielding on the components can be a way to prevent, the cost will be high. So the appropriate shielding is necessary and the study on space environment is also. In this study spacecraft anomalies will be investigated from low earth orbit to deep space spacecraft and the correlation between spacecraft anomalies and space environment events including space explosion, geomagnetic storms etc is analyzed.

• Journal of the Korean Society for Railway
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• v.11 no.3
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• pp.326-333
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• 2008

This study is objected by presenting preliminary data to revise the periodic replacement criteria of continuous welded rail (CWR) in using. In this study, it is investigated information resources for foreign standards, the cause and types of damage in welded rails and the track maintenance history of Seoul metro to analysis the correlation between rail failure and accumulated passing tonnage. Also, it is performed bending test for the laid welded rail reaching the periodic replacement criteria. In result, the correlation between rail failure and accumulated passing tonnage is not obvious and it is a lot of cases for the construction error of welded rail. Also, as a result of bending test of laid welded rail, according to reducing about $17{\sim}18%$ the bending fracture strength of rail, the laid welded rail reaching the periodic replacement criteria is well enough ensured for the load carrying capacity of rail.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.12
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• pp.1037-1048
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• 2018

In this paper, we investigated the international guidelines and actual disposal maneuver cases to prepare KOMPSAT-2 post mission disposal. And then, disposal maneuver plan was established using current propellant of KOMPSAT-2 and verification was also performed to find out whether the international guidelines are satisfied. As a result, the lifetime of KOMPSAT-2 was 3.6 years when 45kg propellant was used to decrease perigee altitude to 300km. And if more than 14.5kg propellant consumed for same strategy, KOMPSAT-2 can satisfy the international guidelines. Finally, re-entry survivability analysis was performed and it represented that heat resistant objects, such as propellant tank and reaction wheel, could be survived but total ground casualty probability was less than international guidelines.

• Journal of Astronomy and Space Sciences
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• v.18 no.2
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• pp.153-162
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• 2001

In this paper, space radiation environment and total ionizing dose(TID) effect have been analyzed for the KOMPSAT-2 operational orbit. It has been revealed that the trapped protons are concentrated in the SAA(South Atlantic Anomaly) area and that the trapped protons and electrons, and solar protons are main factors affecting TID. It turned out that low energy Particles can be effectively blocked by aluminum shielding thickness, but high energy Particles can not be effectively blocked by increasing aluminum shielding thickness. KOMPSAT-2 total radiation dose which is accumulated continuously to spacecraft electronics has been expressed as the function of aluminum thickness. These values ran be used as the criteria for the selection of electronic parts and shielding thinkness of the KOMPSAT-2 structure or electronic box.