• 한국항공우주학회지
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• 제42권9호
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• pp.789-794
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• 2014

정지궤도급 차세대 통신위성에 탑재될 디지털신호처리기에는 디지털 고속통신을 위한 FPGA가 사용된다. 적용된 FPGA는 높은 열소산량을 가지고 있으며, 이로 인한 접합온도의 상승은 부하경감 요구조건을 만족하기 어렵고 장비의 수명과 신뢰도 저하의 주요 원인이다. 지상과는 달리 우주환경에서의 전장품의 열제어는 대부분 열전도를 통하여 이루어지고 있다. CCGA 또는 BGA 형태의 FPGA는 인쇄회로기판에 장착되지만, 인쇄회로기판의 열전도율은 FPGA의 열제어에 효율적이지 못하다. FPGA의 열제어를 위하여 부품 리드와 하우징을 직접 연결하는 히트싱크를 제작하였으며, 우주인증레벨의 열진공시험을 통하여 그 성능을 확인하였다. 높은 전력소모량을 가진 FPGA는 우주환경에 적용하기 어려웠으나, 히트싱크를 적용함으로써 부하경감 온도 마진을 확보하였다.

• 한국진공학회:학술대회논문집
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• 한국진공학회 2016년도 제50회 동계 정기학술대회 초록집
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• pp.200.2-200.2
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• 2016

Carbon-based materials have been known as ablative material and have been used for thermal protection systems. Ablation is an erosive phenomenon that results in thermochemical and thermomechanical changes on materials. Ablation resistance is one of the key properties that determines performance and life-time of the thermal protection material under ablative conditions. In this study, ablation properties of graphite, 3-dimensional (C/C) composites (needle-punched type and rod type) were investigated byusing a plasma wind tunnel which produce a supersonic plasma flow from a segmented arc heater with the power level of 0.4 MW. The mass losses and surface roughness changes which contain main result of the ablation are measured. A morphological analysis ofthe carbon-based materials, before and after the ablation test, are performed through field emission scanning electron microscopy (FE-SEM) and non-contact 3D surface measuring system. Electronic balance and a portable surface roughness tester were used for evaluation of the recession and mass loss of the test samples.

• 한국전산유체공학회지
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• 제15권2호
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• pp.28-34
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• 2010

Conductive and radiative thermal model configurations of an imager of a geostationary satellite are presented. A two-plane method is introduced for three dimensional conductive coupling which is not able to be treated by thin shell plate thermal modeling technique. Especially the two-plane method is applied to massive matters and PIP(Payload Interface Plate) in the imager model. Some massive matters in the thermal model are modified by adequate correction factors or equivalent thickness in order to obtain the numerical results of thermal modeling to be consistent with the analytic model. More detailed nodal breakdown is specially employed to the object which has the rapid temperature gradient expected by a rule of thumb. This detailed thermal model of the imager is supposed to be used for analyses and test predictions, and be correlated with the thermal vacuum test results before final in-flight predictions.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.107-107
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• 2004

• Journal of Astronomy and Space Sciences
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• 제16권2호
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• pp.177-190
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• 1999

An absorbed heat-flux method for ground simulation of on-orbit thermal environment of satellite is addressed in this paper. For satellite ground test, high vacuum and extremely low temperature of deep space are achieved by space simulation chamber, while spatial environmental heating is simulated by employing the absorbed heat-flux method. The methodology is explained in detail with test requirement and setup implemented on a satellite. Developed heat-load control system is presented with an adjusted PID-control logic and the system schematic realized is shown. A practical and successful application of the heat simulation method to KOMPSAT(Korea Multi-purpose Satellite)thermal environmental test is demonstrated, finally.

• 한국태양에너지학회 논문집
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• 제37권4호
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• pp.35-47
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• 2017

Energy efficiency solutions are being pursued as a sustainable approach to reducing energy consumption and related gas emissions across various sectors of the economy. Vacuum Insulation Panel (VIP) is an energy efficient advanced insulation system that facilitates slim but high-performance insulation, based on a porous core material evacuated and encapsulated in a barrier envelope. Although VIP has been applied in buildings for over a decade, it wasn't until recently that efforts have been initiated to propose and adopt a global standard on characterization and testing of VIP. One of the issues regarding VIP is its durability and aging due to pressure and moisture dependent increase of the initial low thermal conductivity with time; more so in building applications. In this paper, the aging of commercially available VIP was investigated experimentally; thermal conductivity was tested in accordance with ISO 8302 standard (guarded hot box method) and long-term durability was estimated based on a non-linear pressure-humidity dependent equation based on study of IEA/ECBCS Annex 39, with the aim of assessing durability of VIP for use in buildings. The center-of-panel thermal conductivity after 25 years based on initial 90% fractile with a confidence level of 90 % for the thermal conductivity (${\lambda}90/90$) ranged from 0.00726-0.00814 (W/m K) for silica core VIP. Significant differences between manufacturer-provided data and measurements of thermal conductivity and internal pressure were observed.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.281-284
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• 2004

According to the National Space Program of Korea, KARI (Korea Aerospace Research Institute) has been developing a large space simulator (working dimension; $\Phi8m\;\times\;L10m$) to verify the performance of future large satellites under the space environment conditions. Especially, a very low temperature condition of space will be simulated by shrouds covering the inside surface of the vessel. The surface of shrouds will be cooled down to 17K by liquid nitrogen (LN2) from ambient temperature and hence, an optimal LN2 circulation system design is necessary to remove gaseous nitrogen (GN2) sufficiently and maintain the shrouds at the LN2 temperature.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2006년도 제32회 KOSCO SYMPOSIUM 논문집
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• pp.121-127
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• 2006

It has become inevitable to search for alternative fuels due to severe energy crisis these days. Use of alternative fuels, which are typically of lower quality, tends to increase environmental pollution, including formation of nitrogen oxides (NOx). In this paper performance of vacuum residue has been investigated experimentally as well as numerically in typical operating conditions of a furnace. Heat release reaction is modeled as sequential steps of devolatilization, simplified gas phase reaction and char oxidation as that for pulverized coal. Thermal and fuel NOx are predicted by conditional estimation of elementary reaction rates and are compared against measured experimental data. On the overall reasonable agreement is achieved for spatial distributions of major species, temperature and NOx for all test cases.

• 한국진공학회지
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• 제22권2호
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• pp.45-54
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• 2013

맥동관형 크라이오펌프 개발 사업 2단계를 맞아 우성진공(유)을 중심으로 상용화 시제품 개발이 성공적으로 끝나가고 있다. 최종 크라이오펌프 개발품은 흡기구 직경(내경) 16.5 (14) 인치에 질소 배기속도 3,600 L/s 이상을 목표로 하고 있다. 개발품의 성능확인을 위해 우선 몬테카를로 계산을 통해 배기속도를 예측하고 구조설계를 최적화했으며 이를 바탕으로 가공 조립된 크라이오펌프 시제품의 성능을 표준화된 장치에서 표준화된 절차를 통해 평가하여 설계 목표값과 비교했다. 시제품의 질소 배기속도는 4,600 L/s로 측정되어 설계값과 잘 일치하였으며 개발목표를 훨씬 상회하였다.

• Journal of Astronomy and Space Sciences
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• 제23권1호
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• pp.39-54
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• 2006

HAUSAT-2는 한국항공대학교 우주시스템 연구실에서 개발하고 있는 25kg급의 소형위성 이다. 위성의 시스템과 부품의 안정적인 작동을 확인하기 위하여 위성의 시스템과 박스모듈 그리고 전장보드 수준에서 열해석을 수행하였다. 시스템과 박스-레벨 열해석에 적용한 열 모델링은 HAUSAT-2 구조-열 모델의 열진공/균형 시험을 통하여 검증 및 보정되었다. 본 연구에서는 주요 소자를 직접 모델링하는 방법의 보드-레벨 열해석 방법론을 제안하고, 그에 따른 결과 분석 및 타당성을 제시하였다.