• 한국전산유체공학회지
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• 제11권3호
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• pp.8-13
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• 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.

• 한국전산유체공학회지
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• 제10권3호
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• pp.63-69
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• 2005

The COMS, the first meteorological geostationary satellite in Korea, is under development by KARI. The radiator size and the heater power for the thermal control of COMS are calculated using an analytic method. The total radiator area of $4.85\;m^2$ and the total heater power of 794.77 W are determined at a conceptual design of COMS. The commercial software, SINDA and TRASYS, are utilized in order to compare and verify the analytic results. The results of on-orbit numerical simulation of cold and hot cases show that the radiator size and heater power obtained from the analytic method are appropriate to maintain COMS equipments within required temperature ranges.

• 전기학회논문지
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• 제63권2호
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• pp.257-260
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• 2014

In this paper, a high gain waveguide array antenna combining horn antenna on slot radiator was designed. And the fabricated antenna showed enough gain, improved efficiency and broadband characteristics for receiving satellite signals, compare to conventional microstrip antenna which has dielectric loss and radiation loss on transmission line. For easy fabrication, the waveguide structure was composed by 3-stages of radiator, signal coupler and transmission line. By experiment, the array waveguide antenna of 4 by 16 showed 28.3[dBi] gain and 2:1 of VSWR. And by combining horn antenna structure, the gain was increased 1[dB]. The received signal from Koreasat 6 by measurement showed 16[dBc] of C/N on BS(Broadcasting Satellite)-band and 14[dBc] of C/N on CS(Communication Satellite)-band.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2006년도 한국우주과학회보 제15권2호
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• pp.159-159
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• 2006

• 한국항공우주학회지
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• 제45권8호
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• pp.678-685
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• 2017

지구관측위성에 탑재되는 자료처리/저장장치 방열판은 장비의 주기적인 고발열, 배치, 장착성 등 설계 특성으로 인해 쉴드가 장착된 홈 형태를 갖는다. 홈 형태 방열판의 영향성과 쉴드 방열판의 열성능을 확인하기 위해, 평판 방열판을 기준으로 홈 형태의 방열판과 쉴드 방열판을 비교하여 열진공 시험을 실시하였다. 시험결과를 바탕으로 view factor에 의한 열교환과 방열판의 온도를 이론해석적으로 분석하여 열 설계 성능비교의 타당성을 입증하였다.

• 항공우주시스템공학회지
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• 제13권2호
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• pp.66-72
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• 2019

SAR(Synthetic Aperture Radar) 관측위성과 같이 고 발열 임무장비가 다수 적용되는 경우 전장품의 발열을 효과적으로 우주공간으로 방출하기 위한 방열판의 적용이 요구된다. 그러나 위성의 식 구간에서 임무장비의 비작동 시, 방열판을 통해 지속적인 방열이 이루어짐에 따라 장비의 최소허용 온도유지를 위한 히터 적용이 불가피하게 된다. 본 연구에서는 기존 방열판에 비해 보다 효율적인 열제어를 위하여 높은 전도율의 액체금속을 이용한 우주용 가변 전도율 방열판을 제안하였다. 제안된 방열판은 탑재장비의 온도조건에 따라 두 개의 저장소 사이에서 기계식 펌프로 액체금속을 이동함으로서 열전도 특성을 가변하는 원리이다. 따라서 저온 조건에서는 방열판으로의 열전도를 차단하여 임무장비에 대한 히터 전력소모를 최소화하고, 반대로 고온 조건에서는 기존 방열판과 같이 효과적인 방열이 가능하도록 한다. 본 연구에서는 제안한 가변 전도율 방열판의 실현 가능성 입증을 위한 열해석을 실시하여 기존의 전도율이 고정된 방열판과 열적 성능을 비교 분석하였다.

• 한국전산유체공학회지
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• 제12권3호
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• pp.62-68
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• 2007

A conceptual thermal design is performed for the optical payload system of a geostationary satellite. The optical payload considered in this paper is GOCI(Geostationary Ocean Color Imager) of COMS of Korea. The radiative thermal control system is employed in order to expect a small thermal gradient in the telescope structure of GOCl. Two design margins are applied to the dedicated radiator dimensioning, and three kinds of configuration to the heater power sizing. A Monte-Carlo ray tracing method and a network analysis method are utilized to calculate radiative couplings and thermal responses respectively. At the level of conceptual design, sizing thresholds are presented for the radiator and heater on the purpose of determining the mass and power budget of the spacecraft.

• 항공우주기술
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• 제10권2호
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• pp.114-120
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• 2011

인공위성의 효율적인 열제어를 위해 알루미늄으로 만들어진 하니콤 패널과 OSR로 구성된 방열판을 사용한다. 또한 추가적으로 발열량이 많은 부품의 경우, 알루미늄으로 만들어진 더블러와 히트파이프 등을 이용하여 열제어를 수행한다. 최근 위성 전장 부품의 발열량의 증가로 정해진 위성의 크기, 발사 중량 및 비용으로 더 많은 열을 외부로 효율적으로 방출할 수 있는 방열 능력향상에 대한 필요성으로 새로운 열제어 물질에 대한 연구가 진행 중이다. 특히, 탄소 복합재는 일반적으로 열전도가 매우 높고, 가볍고, 기계적 강성에 좋은 특성이 있어 차세대 열제어를 위한 물질로 많은 연구가 진행되고 있다. 본 논문에서는 차세대 탄소 복합재인, APG(Annealed Pyrolytic Graphite)와 탄소-탄소 복합재(carbon-carbon composites)를 이용하여 통신패널의 열제어를 수행하는 경우와 기존의 열제어 방식과의 차이를 수치적으로 비교하였다.

• 한국군사과학기술학회지
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• 제26권1호
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• pp.54-63
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• 2023

In this paper, a VHF band conformal antenna for UAV mounting was developed. The proposed antenna was designed as an shape-adaptive structure by minimizing the antenna height to be advantageous in RCS reduction performance. As for the antenna radiator, the outer radiator was arranged around the inner radiator to apply the CRLH zeroth-order resonance structure. With this structure, the height of the antenna was minimized, and it was reduced by about 70 % compared to the existing blade antenna. In addition, for impedance matching, the intermediate frequency bandwidth of the VHF band was improved through the sleeve pin of the inner radiator, and the low frequency bandwidth of the VHF band was improved by applying an EMI shielding gasket to the shorting pin of the outer radiator. The proposed antenna was manufactured and measured to verify the performance of the device and the performance after UAV mounting. As a result, the standard was satisfied for the operating frequency.

• 한국전산유체공학회지
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• 제15권3호
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• pp.66-72
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• 2010

The north and south panel of a geostationary satellite are used for radiator panels to reject internal heat and utilize several heat pipe networks to control the temperatures of units and the main structures of satellite within proper ranges. The design of these panels is very important and essential at the conceptual design and preliminary satellite design stage, so several thousands of nodes or more are utilized in order to perform detailed thermal analysis of panel. Generating a large number of panel nodes takes time and is tedious work because the nodes can be easily changed and updated by locations of units and heat pipes. Also the detailed panel model can not be integrated into spacecraft thermal model due to its node size and limitation of commercial satellite thermal analysis program. Thus development of a program was required to generate a detailed panel model, to perform thermal analysis and to make a reduced panel model for the integration to the satellite thermal model. This paper describes the development and the verification of the panel thermal analysis program with its main modules and functions.