• 진공이야기
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• 제2권2호
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• pp.24-28
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• 2015

The brightness of an electron source, along with the aberrations of an objective lens, determines the image resolution and beam current on samples, which are two important parameters for evaluating the performance of an electron microscope. Here we introduce thermal electron source, Schottky emitter and cold field electron emitter. Thermal electron source is the cheapest and stable electron source but it has the lowest brightness. Schottky emitter is 10000 times brighter than tungsten thermal electron source, but requires ultrahigh vacuum operating condition. Cold field electron emitter is 10 times brighter than Schottky emitters, but it is rather unstable and its operation requires most stringent vacuum condition, hindering its widespread use.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2007년도 춘계학술대회 논문집
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• pp.615-616
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• 2007

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2010년도 제35회 추계학술대회논문집
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• pp.620-621
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• 2010

우주공간에서 임무를 수행하는 인공위성이 궤도상에서 원활하게 작동할 수 있도록 열모델의 보정과정을 통하여 열해석 모델을 검증하는 과정이 이루어진다. 본 연구에서는 열해석 모델을 검증하는 과정으로 지상 열진공시험결과를 이용하여 요구조건을 충족시키기 위하여 열모델의 보정을 수행하였다.

• 한국태양에너지학회 논문집
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• 제34권2호
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• pp.44-52
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• 2014

The main purpose of this paper is to develop the new BIPV module equipped with vacuum glass. Beacuse BIPV module has a function of architectural materials, thermal and PV performance should be simultaneously evaluated. To improve the thermal performance of BIPV module, this study developed BIPV module equipped with a vacuum glass. Those BIPV module was tested with a variety of encapsulants. The results are as follows. When a vacuum glass is laminated with EVA or PVB, it was broken. The reason seems to be bending by unbalance of heat expansion with center and edge of vacuum glass. In case of lamination with resin, there is no breakage and no bending of vacuum glass. Because production was conducted in low pressure & low temperature conditions. And it was also found that vacuum glass does not interfere with the UV curing process.

• International Journal of Aeronautical and Space Sciences
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• 제11권1호
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• pp.26-30
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• 2010

The present paper studies the thermally-induced vibration phenomenon of the flexible space boom structure. In order to simulate the thermally-induced vibration phenomenon of the flexible thin boom structure of the spacecraft with the attached tip mass in space, the thermally-induced vibration including thermal flutter is experimentally investigated at various thermal environments using a heating lamp in vacuum chamber. In this experimental study, fluctuating characteristics, natural frequency and thermal strains of the thermally-induced vibration are parametrically investigated at various thermal environment conditions. Finally the thermally-induced vibration of the flexible boom structure of the orbiting earth satellite in solar radiation environment from the earth eclipse region including umbra and penumbra is simulated using the power control of the heating lamp in the vacuum chamber.

• 한국태양에너지학회 논문집
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• 제28권3호
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• pp.67-73
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• 2008

This study has been carried out to investigate the effect of vacuum on the thermal performance of a nonglass evacuated tube. A series of measurements are made indoors to monitor the temperature change of the absorber plate contained in the evacuated tube under different conditions of vacuum and heat fluxes. Those temperatures measured at the thermal equilibrium could be used to assess the heat losses to the ambient in link with the steady operation of non-glass evacuated tubes for solar exploitation.

• 항공우주기술
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• 제6권1호
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• pp.64-73
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• 2007

차세대 대형위성에 대한 우주환경모사를 위한 대형열진공챔버가 한국항공우주연구원에 의해 성공적으로 국산화 구축되었다. 유효직경 8미터, 유효깊이 10미터의 대형열진공챔버는 크게 진공계와 열제어계, 방진계로 구분되며, $3.7{\times}10^{-5}Pa$($5{\times}10^{-7}torr$) 이하의 진공 환경에서 액체질소를 이용해 위성을 감싸는 쉬라우드의 온도를 $-190^{\circ}C$ 이하로 유지할 수 있고, $10^{-5}g_{rms}$ 이하의 진동레벨을 갖는 방진시스템을 갖추어 우주환경에서의 광학시험을 가능하게 한다. 또한 챔버내에 설치된 할로겐램프를 이용하여 쉬라우드의 온도를 섭씨 123도까지 상승시켜 베이크아웃 시험을 수행할 수 있으며, PLC(Programmable Logic Controller)를 기반으로 한 제어프로그램을 이용하여 대형열진공챔버의 자동화 제어를 수행할 수 있다.

• 한국항공우주학회지
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• 제37권9호
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• pp.916-922
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• 2009

우주공간에서 임무를 수행하는 인공위성의 열설계는 열모델을 활용한 열해석 결과를 바탕으로 수행되므로, 열모델의 정확성은 매우 중요하며 이것은 보정과정을 통하여 향상된다. 열모델의 보정은 인공위성이 열진공 챔버에 장착된 형상을 모사하는 모델링에서 시작하여 실제형상과 열모델간의 일치성에 대한 검증, 거시적 변수에서부터 미시적 변수에 이르기까지 열모델 변수에 대한 조정 등을 거쳐 주어진 성공 조건을 만족할 때까지 열모델을 지속적으로 수정하는 과정으로 이루어진다. 본 연구에서는 열모델 보정의 성공 기준을 수립하고 인공위성 열-구조 모델 열진공 시험결과를 활용한 열모델 보정을 수행하여 보정 기준을 충족시켰다. 본 연구에서 보정이 완료된 열모델은 저궤도 인공위성 상세 열설계에 적용될 수 있었다.

• Journal of Astronomy and Space Sciences
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• 제30권4호
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• pp.335-344
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• 2013

TRiplet Ionospheric Observatory-CubeSat for Ion, Neutron, Electron & MAgnetic fields (TRIO-CINEMA) is a CubeSat with 3.14 kg in weight and 3-U ($10{\times}10{\times}30$ cm) in size, jointly developed by Kyung Hee University and UC Berkeley to measure magnetic fields of near Earth space and detect plasma particles. When a satellite is launched into orbit, it encounters ultra-high vacuum and extreme temperature. To verify the operation and survivability of the satellite in such an extreme space environment, experimental tests are conducted on the ground using thermal vacuum chamber. This paper describes the temperature control device and monitoring system suitable for CubeSat test environment using the thermal vacuum chamber of the School of Space Research, Kyung Hee University. To build the chamber, we use a general purpose thermal analysis program and NX 6.0 TMG program. We carry out thermal vacuum tests on the two flight models developed by Kyung Hee University based on the thermal model of the TRIO-CINEMA satellite. It is expected from this experiment that proper operation of the satellite in the space environment will be achieved.

• 대한기계학회논문집B
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• 제30권6호
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• pp.594-601
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• 2006

Optimization study has been carried out to design an energy efficient, high temperature vacuum furnace which satisfies users' design requirements. First of all, the transient temperature distribution and the uniform temperature zone results have been compared with the steady state results to validate the feasibility of using steady state solution when constructing the thermal analysis DB. In order to check the accuracy, the interpolated results using thermal analysis DB have been compared with the computational and the experimental results. In this study, total heat flux is selected as the objective function, and the geometry parameters of vacuum furnace including the thickness of insulator, the heat zone sizes and the interval between heater and insulator are the design variables. The Uniform temperature zone sizes and the wall temperature are imposed as the design constraints. With negligible computational cost a high temperature vacuum furnace which has $40\sim60%$ reduction in total heat flux is designed using thermal analysis DB.