• Bulletin of the Korean Space Science Society
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• 2007.10a
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• pp.126.1-126.1
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• 2007

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.12
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• pp.1028-1036
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• 2018

KARI plans to launch Korea Pathfinder Lunar Orbiter (KPLO) to the Moon by December 2020 for the first step of the Korea Lunar Exploration Project. This orbiter will be launched to obtain lunar exploration technologies and science data in advance before launching a main orbiter and a lunar probe. This paper describes the verification of thermal design for the orbiter. It is exposed to more extreme thermal environment than that of low Earth orbit satellite due to the heavy infrared emission of the Moon. Accordingly, a thermal design considering this environment is needed to maintain the temperature of payloads and components equipped in the orbiter within operating temperature range in all orbits. We performed the thermal analysis for Earth-Moon transfer orbit, lunar mission orbit and lunar eclipse required for thermal design verification of the lunar orbiter. As a result, this thermal design met the design requirements.

• Journal of Aerospace System Engineering
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• v.16 no.3
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• pp.105-114
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• 2022

The purpose of this study was to present a conceptual design of the 6U micro-satellite system for optical image of 3 m GSD. An optical camera system with a payload of 3 m GSD image was designed and optimized. The optical system has a diameter of Ø78 mm, length 250 mm, and 1400 mm focal length. The requirement and constraints were configured for the 6U micro-satellite bus system with the payload. Satisfying the requirement and constraints, the subsystems of the 6U bus were designed such as attitude and orbit control, propulsion, command and data handling, electrical power, communication, structures and mechanisms, and thermal control subsystem. The mass budget, power budget, and communication link budget were also confirmed for the 6U micro-satellite comprising the optical payload and the subsystems of bus. To take optical images, a mission operation concept is proposed for the 6U micro-satellite in a low-Earth orbit. A constellation comprising many 6U micro-satellites studied in this paper, can provide with various data for reconnaissance and disaster tracking.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.20 no.3
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• pp.9-14
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• 2020

In this paper, Qualification Model of frequency synthesizer is designed for X-band SAR system and performed electrical and environment test. Designed frequency synthesizer generate 13.65 GHz with very low phase noise performance. The integrated phase noise from 10Hz to 1MHz is -37.91 dBc. IRF performances are analyzed according to phase noise and jitter. Also, thermal and structure analysis are achieved for stable operation in space environment. Designed frequency synthesizer is consist of 2 modules of 6U size and generate L-band, C-band, Ku-band. The result of this study would enhance the design ability of RF module and help the frequency synthesizer design for SAR payload system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.1
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• pp.72-78
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• 2015

Recently, the usage of the satellite is increased more and more in the areas that are communication, weather, marine, optical, radar etc. The functions of the Satellite are evolving from passive transponder to active transponder by the developing of a technology. Advanced countries in satellites install the DCAMP for increase of bandwidth efficiency, improvement of QoS by interference rejection. DCAMP includes many digital components in order to implement functions. Thus, these kinds of active transponders consume much more power compared to passive transponder and then increase the heat. In this paper, we discuss the TVAC test result of DCAMP in EQM(Engineering Qualification Model) level. The paper shows the test results of digital gain control in order to verify DCAMP status under the TVAC test. In addition, the temperature and heat condition of main components from viewpoint of derating will be treated through the official environment test for qualification.

• 한국전산유체공학회:학술대회논문집
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• 2004.10a
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• pp.131-136
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• 2004

Thermal control of satellite propellant tank is achieved by patch heaters enabled by thermostat's behavior. It is important to attach the thermostat on the appropriate position of the propellant tank. However its position cannot be given with exact numerics because tank is spherical. Actually the position for thermostat is designated in relevant drawing approximately, therby, the engineer practices depending on his own experience and intuition. The sensitivity analysis for the position of thermostat is performed such that the influence on the thermal behavior and control of tank is examined quantatively. When assembling tank module, the reasonable performance on the thermal control is believed with possible human errors if the uncertainty in the position of thermostat is not quite large.

• Journal of Aerospace System Engineering
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• v.14 no.3
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• pp.51-59
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• 2020

In the case of cubesat, a PCB-based deployable solar panel advantageous in terms of weight reduction and electrical circuit design is widely used considering the limited weight and volume of satellites. However, because of the low thermal conductivity of PCB, there is a limit relative to heat dissipation. In this paper, the thermal gap pad is applied to the contact between the PCB-based solar panel and the aluminum stiffener mounted on the outside of the panel. Thus, the heat transfer from the solar cell to the rear side of the panel is facilitated. It maximizes the heat dissipation performance while maintaining the merits of PCB panel, and thus, it is possible to improve the power generation efficiency from reducing the temperature of the solar cell. The effectiveness of the thermal design of the 6U cubesat's deployable solar panel using the thermal gap pad has been verified through on-orbit thermal analysis based on the results, compared with the conventional PCB-based solar panel.

• Aerospace Engineering and Technology
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• v.8 no.2
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• pp.113-121
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• 2009

Shaker system is used to simulate the vibration from the launch environment. The vibration tests are performed in the vertical and lateral direction. For the lateral vibration test, the slip table system is used with shaker system. For the latest large satellite, vibration test adaptor is made of the steel. But slip table of lateral vibration is made of magnesium, so there is big difference of thermal expansion ratio between slip table and vibration test adaptor. This paper encompasses the following items; verification process of thermal characteristics and overturning moment and a solution for lateral vibration test with steel vibration test adaptor.

• Bulletin of the Korean Space Science Society
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• 2009.10a
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• pp.45.2-45.2
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• 2009

과학기술위성 3호의 주탑재체인 MIRIS (Multi-purpose InfraRed Imaging System)는 우주관측카메라, 지구관측카메라로 구성되어 있으며, 우주관측카메라는 구경 80mm(f/2)의 광시야 굴절식 광학계로 구성되어 있다. 지상과 우주에서 사용하는 적외선 망원경의 경우 열잡음을 줄이기 위해 광학계과 검출기를 냉각하게 되는데, MIRIS의 경우 공간과 무게를 줄이기 위해 복사 냉각을 위한 passive cooling 방법으로 설계를 하였다. 우주관측 카메라의 광학계를 200K 이하로 냉각하기 위하여, 관측시야 밖에서 입사하는 불필요한 photon 들을 반사시키기 위한 winston cone baffle, 위성체로부터 유입되는 열을 차단하기 위한 30층의 MLI(Multi Layer Insulation), 광학계와 구조물의 지지를 열전달율이 낮은 GFRP(Glass Fiber Reinforced Polymer)로 설계하여 제작하였다. 우주관측 카메라를 열진공 챔버 내부에 설치하고 우주공간과 비슷한 환경을 조성하여 광학계가 200K 이하로 냉각되는 것을 확인 하였으며 그 실험 결과에 대해 논의 하고자 한다.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2014.06a
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• pp.105-106
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• 2014

대한민국은 2022년부터 위성을 통한 GPS 측위 보강시스템인 SBAS의 본격 서비스를 목표로 연구개발을 진행 중에 있으며, 기존에 운용되고 있는 전국망 해양 DGPS국을 SBAS 기준국으로 활용하기 위한 방안을 모색하고 있다. 이런 이유에서 본 논문은 해양 DGPS국의 효과적인 공동 활용방안 제안을 위하여 SBAS 기준국의 요구기능과 성능을 분석하고, 해양 DGPS국과 비교하였다. SBAS는 관련 장비와 시설에 대한 검증이 엄격하고, 인증이 필수적이다. 따라서 본 논문에서는 해양 DGPS국이 SBAS 기준국으로써 SBAS 운영에 필요한 성능을 만족시키면서 해양 DGPS의 본래 기능과 성능, 표준 준수는 물론이고, 위성항법 시스템의 다원화에 유연하게 대응할 수 있도록 DGPS국의 구조를 설계하였다.