• 한국항공우주학회지
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• 제39권11호
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• pp.1069-1076
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• 2011

인공위성이 궤도상에서 임무를 수행하는 동안 모든 위성 부품이 허용 온도 범위 내에서 존재하도록 하기 위하여 검증된 열모델을 개발하고, 궤도 열해석을 통하여 열적 안정성을 확보하기 위한 열설계를 수행한다. 본 연구에서는 저궤도 위성 광학탑재체의 열진공/열평형 시험 결과를 이용하여 열해석 모델을 보정하고 flight heater의 작동주기를 맞추어 줌으로써 검증된 열모델을 확보하였다. 또한 위성의 열적 안정성을 확보하기 위하여 보정이 완료된 모델을 이용하여 궤도 열해석을 수행함으로써 모든 부품이 허용온도 범위내에 존재하는 것을 확인하였다.

• 한국산학기술학회논문지
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• 제21권11호
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• pp.595-601
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• 2020

10년 이상 보관된 니트로셀룰로오스 (Nitrocellulose, 니트로셀룰로오스) 재질의 화약용기 안전 검사를 진행하는 과정 중 화약이 보관되어진 용기에 균열이 발생한 것을 확인하여 고장 원인 분석 시험을 실시하였다. 고장이 발생한 데에 영향을 준 요인을 선별하기 위해 먼저 고장수목분석(Fault Tree Analysis, FTA)을 통해 고장 요인 및 원인에 대해 탐구하였으며, 보관 시 발생할 수 있는 내·외부적인 요인 및 환경에 대한 영향성을 확인한 결과 열에 의해 화학 반응이 가속화되어 발생한 화약용기의 물성 변화가 고장의 원인인 것으로 추정하였다. 이를 확인하기 위해 자연 노화된 화약용기를 이용하여 열충격시험, 양립성 시험 등의 환경시험을 수행하여 고장의 원인 분석을 수행하였으며, 가속노화시험을 통해 고장 재현 시험을 실시하였다. 이를 통해 앞선 고장수목분석 결과와 같이 열과 화약에 의해 화학 반응이 가속화되는 것을 확인할 수 있었으며, 화약용기의 물성이 변화하는 것을 확인하였다. 또한, 열 노화에 의한 수명 추정을 위해 아레니우스 모델(Arrhenius Model)을 이용하여 화약용기의 사용 수명을 추정하였다.

• 한국세라믹학회지
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• 제34권8호
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• pp.908-913
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• 1997

Multilayer NbCxC1-x/Y2O3/Ti were sputter-coated on the alumina substrate, starting with a 0.7 ㎛ thick NbCxC1-x layer grown on substrate, followed by 0.7 ㎛ thick Y2O3 layer and 1 ㎛ thick Ti layer. To find out the optimum conditions for thickness uniformity and adhesion, sputtering works have been done with the variation of sputtering power and Ar pressure. After vacuum annealing at 950℃ and 1000℃, the thermal stability of the NbCxC1-x/Y2O3/Ti coated alumina substrates has been investigated by peel off test. The coating scheme didn't cause any debonded layer after an annealing at 950℃ for 3hrs. However, it was peeled off after annealing at 1000℃ for 3hr. It was found that the thermal stability of Al2O3/NbCxC1-x/Y2O3/Ti coating scheme changed with the NbCxC1-x composition.

• 한국항공우주학회지
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• 제44권1호
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• pp.88-97
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• 2016

폐회로 열제어 시스템은 열진공 챔버의 온도를 $-150^{\circ}C{\sim}120^{\circ}C$와 같은 온도 조건으로 모사하기 위한 시스템으로, 극저온 블로워, 슈라우드, 히터, 극저온 밸브 등으로 구성된다. 본 연구는 우주 열환경 모사를 위한 폐회로 열제어 시스템의 설계 요소 정의 및 제어 변수별 실험 결과 등을 포함하고 있다. 폐회로 열제어 시스템 설계를 위해 설계 요소인 블로워 용량, 슈라우드 재질, 형태에 따른 특성 등의 분석을 수행 하였다. 폐회로 열제어 시스템의 극저온 블로워 필요 유량은 에너지 평형 방정식에 의해 결정되며, 제어는 작동 유체의 밀도 제어를 통해 제어된다. 밀도, 회전수와 같은 제어 변수별 실험을 통해 슈라우드 온도 분포 균질도 및 균일도를 측정하여 요구된 폐회로 열제어 시스템의 성능을 확인 하였다.

• 한국태양에너지학회 논문집
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• 제32권4호
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• pp.43-50
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• 2012

Metal-metal oxide (M-M oxide) cermet solar selective coatings with a double cermet layer film structure were deposited on the Al-deposited glass substrate by using a directed current (DC) magnetron sputtering technology. M oxide (CrO and ZrO) was used as the ceramic component in the cermets, and Cr and Zr used as the metallic components. In addition, black Cr (Cr-$Cr_2O_3$ cermet) solar selective coatings were deposited on the Ni-plated Cu substrate by using a electroplating method for comparison. The thermal stability tests were carried out for performance evaluation of solar coatings. Reflectance measurements were used to evaluate both solar absorptance(${\alpha}$) and thermal emittance (${\epsilon}$) of the solar coatings before and after thermal testing by using a spectrometer. Optical properties of optimized cermet solar coatings were ${\alpha}{\simeq}0.94-0.96$ and ${\epsilon}{\simeq}0.1$ ($100^{\circ}C$). The results of thermal stability test of M-M oxide solar coatings showed that the Cr-CrO cermet solar selective coatings were more stable than the Zr-ZrO cermet selective coatings at temperature of both $400^{\circ}C$ in air and $450^{\circ}C$ in vacuum. The black Cr solar selective coatings were degraded in air at temperature of $400^{\circ}C$. The main optical degradation modes of these coatings were diffusion of metal atoms, and oxidation.

• Corrosion Science and Technology
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• 제18권5호
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• pp.182-189
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• 2019

A thin spray coating of inorganic black lithium polysilicate (IBLP) on black anodized AZ31B magnesium alloy was fabricated for better corrosion resistance and thermo-optical properties for thermal control of spacecraft components. The morphology of the specimens with and without IBLP-based spray coating was characterized by SEM-EDS techniques. Impedance and potentiodynamic measurements on the specimens revealed better corrosion resistance for the specimen with a thin coating of lithium polysilicate. This was primarily due to the presence of lithium polysilicate inside the micro-cracks of the black anodized specimen, restricting the diffusion paths for corrosive media. Environmental tests, namely, humidity, thermal cycling, thermo vacuum performance, were used to evaluate the space-worthiness of the coating. The thermo-optical properties of the coating were measured before and after each environmental test to ascertain its stability. The specimen with an IBLP-based spray coating showed enhanced thermo-optical properties, greater than ~0.90. Hence, the proposed coating demonstrated better handling, better corrosion resistance, and space-worthiness during the pre-launch phase owing to its improved thermo-optical properties.

• Journal of Astronomy and Space Sciences
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• 제31권2호
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• pp.177-186
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• 2014

The Immersion Grating Infrared Spectrometer (IGRINS) is a near-infrared wide-band high-resolution spectrograph jointly developed by the Korea Astronomy and Space Science Institute and the University of Texas at Austin. IGRINS employs three HAWAII-2RG Focal Plane Array (H2RG FPA) detectors. We present the design and fabrication of the detector mount for the H2RG detector. The detector mount consists of a detector housing, an ASIC housing, a Field Flattener Lens (FFL) mount, and a support base frame. The detector and the ASIC housing should be kept at 65 K and the support base frame at 130 K. Therefore they are thermally isolated by the support made of GFRP material. The detector mount is designed so that it has features of fine adjusting the position of the detector surface in the optical axis and of fine adjusting yaw and pitch angles in order to utilize as an optical system alignment compensator. We optimized the structural stability and thermal characteristics of the mount design using computer-aided 3D modeling and finite element analysis. Based on the structural and thermal analysis, the designed detector mount meets an optical stability tolerance and system thermal requirements. Actual detector mount fabricated based on the design has been installed into the IGRINS cryostat and successfully passed a vacuum test and a cold test.

• 한국재료학회지
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• 제17권10호
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• pp.509-515
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• 2007

In order to fabricate adhesiveless 2-layer flexible copper clad laminate (FCCL) used for COF (chip on film) with high peel strength, polyimide (PI; Kapton-EN, $38\;{\mu}m$) surface was modified by reactive $O_2^+$ and $N_2O^+$ ion beam irradiation. 300 mm-long linear electron-Hall drift ion source was used for ion irradiation with ion current density (J) higher than $0.5\;mA/cm^2$ and energy lower than 200 eV. By vacuum web coating process, PI surface was modified by linear ion source and then 10-20 nm thick Ni-Cr and 200 nm thick Cu film were in-situ sputtered as a tie layer and seed layer, respectively. Above this sputtered layer, another $8-9{\mu}m$ thick Cu layer was grown by electroplating and subsequently acid and base resistance and thermal stability were tested for examining the change of peel strength. Peel strength for the FCCLs treated by both $O_2^+$ and $N_2O^+$ ion irradiation showed similar magnitudes and increased as the thickness of tie layer increased. FCCL with Cu (200 nm)/Ni-Cr (20 nm)/PI structure irradiated with $N_2O^+$ at $1{\times}10^{16}/cm^2$ ion fluence was proved to have a strong peel strength of 0.73 kgf/cm for as-received and 0.34 kgf/cm after thermal test.

• 항공우주시스템공학회지
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• 제17권2호
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• pp.94-102
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• 2023

큐브위성용 태양전지판 분리장치는 열선 또는 저항소자의 발열로 나일론선을 절단하여 구조물의 구속을 해제하는 나일론선 절단방식 구속분리장치가 주로 적용되고 있다. 일반적으로 태양전지판 조립체의 발사하중을 고려한 구조해석을 수행하여 구속분리장치의 설계가 이루어지고 있으나, 발사 이후 궤도 열환경에 대한 구속분리장치의 열적 검토 및 분석사례는 전무한 실정이다. 따라서, 본 논문에서는 현재 개발중인 큐브위성 STEP Cube Lab-II에 적용되는 나일론선 절단 기반 구속분리장치의 열적 안정성 평가를 수행하고자 한다. 위성이 POD (Picosatellite Orbital Deployer)에서 사출되고 태양전지판이 전개되기까지의 분리장치 온도 분포를 검토하여 분리장치의 허용온도 범위 내에서 안정적인 구속 분리가 될 수 있도록 분리장치에 대한 궤도 열해석을 수행하였다. 또한, 열해석 결과를 기반으로 열진공시험을 수행하여 분리장치의 설계를 검증하였다.

• 한국진공학회:학술대회논문집
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• 한국진공학회 2009년도 제38회 동계학술대회 초록집
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• pp.319-319
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• 2010

Dye-sensitized solar cells (DSSCs) based on plastic substrates have attracted much attention mainly due to extensive applications such as ubiquitous powers, as well as the practical reasons such as light weight, flexibility and roll-to-roll process. However, conventional high temperature fabrication technology for glass based DSSCs, cannot be applied to flexible devices because polymer substrates cannot withstand the heat more than $150^{\circ}C$. Therefore, low temperature fabrication process, without using a polymer binder or thermal sintering, was required to fabricate necked $TiO_2$. In this presentation, we proposed polymer-inorganic composite photoelectrode, which can be fabricated at low temperature. The concept of composite electrode takes an advantage of utilizing elastic properties of polymers, such as good impact strength. As an elastic material, poly(methyl methacrylate) (PMMA) is selected because of its optical transparency and good adhesive properties. In this work, a polymer-inorganic composite electrode was constructed on FTO/glass substrate under low temperature sintering condition, from the mixture of PMMA and $TiO_2$ colloidal solution. The effect of PMMA composition on the photovoltaic property was investigated. Then, the enhanced mechanical stability of this composite electrode on ITO/PEN substrate was also demonstrated from bending test.