• 한국항공우주학회지
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• 제38권8호
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• pp.842-847
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• 2010

본 연구는 인공위성 탑재품 열진공 시험시 적용된 열환경 조건, 탑재품 시험용 열진공 챔버의 형상, 위성체 내부의 열환경들을 고려하여 열진공 시험 과정을 모사하는 수치해석모델을 설계하여 열해석을 수행하였다. 피시험체인 탑재품과 열진공 챔버 구성요소의 시간에 따른 온도 변화를 보여주는 과도적(Transient) 해석 결과를 구할 수 있다. 열해석에 의한 성능향상 설계를 반영하여 업그레이드한 열진공 챔버를 이용한 탑재품 환경시험을 수행하였으며, 시험 결과와 열해석 결과에 대한 비교/검증을 수행하였다.

• KIEAE Journal
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• 제16권3호
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• pp.121-128
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• 2016

Purpose: The vacuum glazing should constantly retain the gap in vacuum state to maintain high thermal performance. To do so, pillars are used to prevent the glazing from clinging to each other by the atmospheric pressure and therefore surface of the vacuum glazing is consistently affected by residual stress. The vacuum glazing could be applied to curtain wall systems at spandrel area to fulfill a rigorous domestic standard on U-value of the external wall. However, this can lead to high glazing temperature increase by heat concentration at a back panel and finally thermal stress breakage. This study experimentally determined weakness of the vacuum glazing systems on the thermal stress breakage and investigated effect of the residual stress. Method: The experiment first built two scale-down mock-up facilities that replicate the spandrel area in curtain wall, and then installed single low-e glass and vacuum glazing respectively. The two mock-up facilities were exposed to outside to induce the thermal stress breakage. Result: The experiment showed that the temperature occurred the thermal stress breakage was $114.4^{\circ}C$ for the single low-e glass and $118.9^{\circ}C$ for the vacuum glazing respectively. The result also showed the vacuum glazing reached the critical point earlier than the single low-e glass, which means that the vacuum glazing has high potential to occur the thermal shock breakage. In addition, the small temperature difference between two glazing indicates that the residual stress scarcely affects breakage of the vacuum glazing.

• 설비공학논문집
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• 제9권3호
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• pp.300-311
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• 1997

A theoretical method was developed to analyze the effect of low-$\varepsilon$ coatings which have influence on thermal performance of vacuum windwo glazing and double pane glazing. The overall heat transfer coefficient(U) value and thermal performance were analyzed by theroretical method on various kins of windows. TRNSYS program was used to analyze total heating and cooling energy consumption on the model building which has various windows. As the result, better thermal insulation can be achieved on the vacuum window glazing than double pane glazing when low-$\varepsilon$ coating was done on the surface of glass. Total heating and cooling energy consumption was almost same on the double pane window glazing but was lessened on the vacuum window glazing when the window size of south direction increased. Therefore, low-$\varepsilon$ coating was very necessary for vacuum window glazing in order to improve thermal insulation performance and efficient energy conservation can be achieved by vacuum window glazing at the real building which has large window.

• 한국항공우주학회지
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• 제43권11호
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• pp.1008-1015
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• 2015

위성체의 지상 검증 시험에는 열진공 챔버가 사용되며, 열제어 시스템은 열진공 챔버의 핵심이라고 할 수 있다. 특히, 기체 질소를 이용한 폐회로 열제어 시스템의 성능은 극저온 블로워의 성능에 의해 결정된다. 본 연구의 최종 목표는 설계 요구조건 $-150^{\circ}C{\sim}150^{\circ}C$의 온도 조건, 유량 150 CFM, 0.5 bara 이상의 차압을 갖는 극저온 블로워를 개발하는 것으로, 1차원 해석툴 및 CFD를 이용한 성능해석을 통해 임펠러를 설계 하였으며, 구동부와 유체부의 열전달 방지를 위한 열장벽, 모터의 과열 방지를 위한 냉각 시스템 등이 설계되었다. 표준대기상태에서 실험을 통해 성능을 검증하였으며, 최종적으로 열진공 챔버내에 설치하여 운영 조건에서 극저온 블로워의 성능을 확인하였다.

• 한국항공우주학회지
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• 제41권10호
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• pp.833-839
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• 2013

위성체는 지상에서 우주환경시험을 거쳐 기능 및 작동상태를 점검해야 하며, 이를 위해서는 우주환경을 모사 할 수 있는 우주환경 모사장비가 필요하다. 위성체 및 위성체의 부품 성능을 검증하기 위해 사용되는 열진공 챔버는 진공용기, 진공시스템, 열제어 시스템 등으로 구성이 된다. 특히, 고온 및 극저온의 열환경을 모사하는 열제어 시스템이 열진공 챔버의 핵심이라고 할 수 있으며, 열제어 시스템의 성능은 극저온 블로워의 성능에 의해 결정된다. 본 논문에서는 극저온 블로워의 유동 해석과 블레이드의 구조해석을 통해 원심팬을 설계 하였으며, 구동부와 유체부의 열전달 방지를 위한 열장벽, 모터의 과열 방지를 위한 냉각 시스템 등이 설계되었으며, 이는 열해석을 통해 검증 되었다. 최종적으로 성능실험을 수행하여 극저온 블로워의 성능을 확인하였다.

• 한국항공우주학회지
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• 제39권5호
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• pp.466-473
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• 2011

인공위성의 열제어는 인공위성이 운용궤도상에서 겪는 고진공, 극한의 온도변화 환경에서 위성 구성품의 온도변화를 허용한계 온도 범위 내에서 유지하는데 목적이 있다. 본 연구에서는 저궤도 관측위성(LEO)의 광학탑재체에 대한 열해석 과정으로 열진공 시험 조건, 열진공 챔버의 형상, 위성 탑재체 내부의 열적 환경을 고려하여 열해석 모델을 구성하고 궤도 조건에 따른 열해석을 수행하였다. 또한 광학탑재체의 지상 열진공 시험 조건에 따른 열해석 수행하여 열진공 시험을 위한 시험조건을 정립하였다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.216-221
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• 2003

A thermal vacuum chamber is mainly used to simulate thermal environments of a test satellite in satellite orbits in which daily temperature variations range from 80K to above 400K depending on solar radiation under the vacuum below $10^{-4}$ torr. The test facility is quite complex and consists of expensive parts. So any modification of control software is discouraged in fear of unexpected system failure. The purpose of this study is to develop a realtime dynamics model of the thermal vacuum chamber in view of controller design and simulate its electrical inputs and outputs for interface with a PLC (programmable logic controller). A PLC program that was used in the thermal vacuum chamber is applied to the realtime simulator. The realized simulator dynamics is found to be quite similar to that of the thermal vacuum chamber and serve to an appropriate plant to verify the control performance of a programmed PLC.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집D
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• pp.325-330
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• 2001

One of the principal components of the KSTAR (Korea Superconducting Tokamak Advanced Research) tokamak structure is the vacuum vessel, which acts as the high vacuum boundary for the plasma and also provides the structural support for internal components. Hyundai Heavy Industries Inc. has performed the engineering design of the vacuum vessel. Here the overall configuration of the KSTAR vacuum vessel was briefly described and then the design methodology and the analysis results were presented. The vacuum vessel consists of double walls, several ports, leaf spring style supports. Double walls are separated by reinforcing ribs and filled with baking/shielding water. The overall external dimensions of the main body are 3.39 m high, 1.11 m inner radius, 2.99 m outer radius, and made of SA240-316LN. The vacuum vessel was designed to be capable of achieving the base pressure of $1\times10^{-8}$ Torr, and also to be structurally capable of sustaining the vacuum pressure, the electromagnetic and thermal loads during plasma disruption and bakeout, respectively. The vacuum vessel will be baked out maximum $150^{\circ}C$ by hot pressurized water through the channels formed between double walls and the reinforcing ribs. A 3-D temperature distribution and the resulting thermal loads in the vessel were calculated during bakeout. It was found that the vacuum vessel and its supports were structurally rigid based on the thermal stress analysis. The maximum electromagnetic loads on the vacuum vessel induced by eddy and halo currents resulting from the engineering plasma radial and vertical disruption scenarios have been estimated. The stress analyses have been performed based on these electromagnetic loads and the resulting stresses at he critical locations of the vacuum vessel were within the allowable stresses.

• 한국진공학회:학술대회논문집
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• 한국진공학회 2003년도 제24회 학술발표회 초록집
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• pp.157-157
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• 2003

• 한국초전도저온공학회:학술대회논문집
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• 한국초전도저온공학회 2000년도 KIASC Conference 2000 / 2000년도 학술대회 논문집
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• pp.119-120
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• 2000

The thermal shield for the TF coils and PF coils has been located between the coils and vacuum vessel. The thermal shielding cryopanel is cooled under 80K by a fored flow of helium gas using cooing pipes on the cryopanel. Design of the KSTAR thermal shield of vacuum vessel is described.