• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.170.2-170.2
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• 2012

위성의 열진공 환경 시험은 고진공 극저온의 우주 환경을 모사하여 열제어 기능 및 임무 수행 능력을 검증하는 시험이다. 이 시험에서는 위성 주위에 부착한 방열판으로 위성 외각 온도를 변화 시켜 위성의 태양 지향 자세 또는 심우주 지향 자세를 모사하며, 이에 따른 위성의 온도 변화에 따라 지상 시험 장비로 위성의 히터 설정, 유닛 전원 형상의 변경 등을 해야한다. 또한 극고온 또는 극저온의 환경에 장시간 연속적으로 노출된 상태에서 위성의 기본적인 기능부터 영상 미션까지 검토하는 CPT 시험을 수행하며, 이 CPT 시험은 극한의 위성 상태의 시험이기 때문에 온도를 고려한 전자 시험 설계 및 24시간 위성 모니터링 시스템, 위험상황 발생 시 대처 방안 등에 대한 준비가 필요하다. 본 논문에서는 열진공 시험 시의 전자시험의 형상과 설계에 대해서 설명하고, 시험 결과에 대해서 정리하였다.

• Journal of the Korea Institute of Building Construction
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• v.16 no.3
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• pp.211-217
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• 2016

In this research, the performance of surface covering technique using a white-colored bubble sheet on reducing the cracking due to the plastic, and drying shrinkages for high rise building construction were evaluated by comparing the exposed surface without any surface treatment. From the results of the experiment conducted during fall season, desired results of decreased numbers, length, maximum width, and area of cracking were obtained without a significant difference on heat of hydration and cumulative temperature. Therefore, it is considered that the surface covering technique using bubble sheet is an appropriate method for preventing plastic and drying shrinkage cracking at fall season concrete construction.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.73-73
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• 2003

인공위성은 발사체에 실려 임무궤도에 도달하는 동안 여러 과정을 겪고 이에 따른 우주 열환경에 노출되게 된다. 본 연구에서는 발사체의 페어링(Fairing)이 열리고 이후 인공위성이 임무궤도에 도달하는 동안까지 인공위성에 대한 열해석을 수치적인 방법을 이용하지 않고 해석해를 이용하여 수행하였다. 일반적으로 발사시 인공위성에 대한 열해석은 수치모델을 개발하여야 하는 시간과 노력이 많이 드는 작업이다. 그러나 수치 모델이 완성되기 전에 주요 부품에 대한 극한 환경에서의 온도 예측이 필요한 경우가 있다. 본 연구는 해석 기법을 이용하여 주요 부품의 온도를 비교적 간단한 방법으로 예측하는 것이다. 이를 위하여 열관련 지배방정식에 여러 가정을 적용하여 지배방정식을 최대한 단순화시켰다. 그 결과, 최종적으로 1차 미분 방정식 형태의 단순화된 지배방정식을 얻게 되었다. 또한 본 연구에서는 여러가지 조건에 대한 연구가 시도하였다. 즉 고려하는 대상의 질량이 일정하게 유지 되는 경우와 일정한 비율로 질량이 감소하는 경우, 인공위성이 최악의 고온환경과 최악의 저온환경에 처한 경우, 그리고 시간에 대한 변수항 때문에 약간의 수치작업이 필요한 경우가 연구되었다. 본 연구에서 제안된 해석해 기법은 적절한 우주 열환경 조건과 결합하게 되면 발사과정에 대한 완전한 수치모델이 완성되기전에 위성체 부품에 대한 열적 안정성을 검토하는데 유용하게 이용될 수 있을 것이다.

• Proceedings of the Korean Vacuum Society Conference
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• 2012.02a
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• pp.524-524
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• 2012

Thermal Barrier Coating (TBC)은 미사일, 로켓발사체와 같이 고온에 노출되는 장비를 열로부터 보호하기 위한 코팅이다. 일반적인 Thermal Barrier Coating (TBC)은 모재와 코팅층간의 낮은 접합력과 높은 열충격으로 인한 박리가 많이 나타난다. 그래서 접합력을 높이고, 열충격을 줄이기 위해 모재와 코팅층 사이에 본드코팅층을 만든 Duplex - Thermal Barrier Coating (Duplex-TBC)이 개발되었다. 그러나 Duplex - Thermal Barrier Coating (Duplex-TBC)은 금속재료인 본드코팅층과 세라믹재료인 탑코팅층 사이에서 박리가 많이 발생한다. 이러한 문제점을 해결하기 위해 두 가지 분말을 동시에 코팅하여 본드코팅과 탑코팅의 경계가 없는 Functional Gradient Material - Thermal Barrier Coating (FGM-TBC)의 연구가 필요하다. 본 연구에서는 Functional Gradient Material - Thermal Barrier Coating (FGM-TBC)의 열충격 특성에 미치는 진공 플라즈마 용사 조건의 영향을 조사하였다. Functional Gradient Material - Thermal Barrier Coating (FGM-TBC)는 진공 플라즈마 용사장치를 사용하여 Cu-Cr 합금위에 코팅하였다. 거리, Carrier gas flow, 그리고 챔버 내부의 압력을 달리하여 제조하였다. 사용한 분말은 본드코팅용으로 Amdry 962와 내열 세라믹코팅을 위해 204NS를 사용하였고, 각각 분말 공급조건을 조절하여 두 분말의 비율을 달리하였다. 제조한 Functional Gradient Material - Thermal Barrier Coating (FGM-TBC) 코팅은 전기로에서 50분간 가열한 후, 수조에서 10분간 냉각하는 열충격 실험을 통해 열차폐 성능을 평가 하였다. 이러한 과정에서 진공 플라즈마 용사 조건 및 FGM 조성과 비율이 내열충격 특성에 미치는 영향을 미세조직학적 관점에서 고찰하였다.

• Journal of Advanced Marine Engineering and Technology
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• v.38 no.1
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• pp.99-104
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• 2014

In this paper, Fire resistance test was carried out in accordance with the change of the insulation conditions on the exposed side and unexposed side of the coaming to obtain optimal insulation conditions for class H-120 insulation in connection with specimen-1 of the preceding paper for the evaluation of fireproof performance for fire dampers according to hydrocarbon fire conditions. As a test result, specimen-2(88 mm, $171^{\circ}C$) was satisfied class H-120 insulation, but specimen-3(76 mm, $181^{\circ}C$) was exceeded thermal insulation acceptance criteria at 110 minutes, therefor, specimen-2(88 mm) is optimal insulation conditions as possible lightweight than specimen-1. Test result comparison, we concluded that temperature rising of the coaming insulation surface was influenced by conductive heat from the bulkhead, and coaming surface was influenced by radiant heat from blade & coaming.

• The Journal of the Korea Contents Association
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• v.16 no.8
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• pp.419-426
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• 2016

The research is done to analyze the change of personal dosimeter according to the elapsed times(24 hours, 1 week, 2 weeks, 3 weeks, 4 weeks) and magnetic field and find out the effective exposure treatment for radiation workers. At first, research the heat treatment and radiation of grouped TLD and keep them in different environments-exposed separately to observe the consequences of glow curve and the level of radiation exposure. As a result, we could find that 24 hours passing TLD group showed the difference in glow curve and the level of radiation. This can be considered as the change caused by magnetic exposure. Also the average radiation exposure level of TLD group, unexposed to the magnetic field, was 15.41 mSv. And the average radiation exposure level of TLD group, exposed to the magnetic field, was 14.83 mSv which decreased the biggest amount(3.80%) among the other groups. If a radiation worker, who works in PET-MRI room, uses TLD as a personal dosimeter, the level of real radiation exposure caused by exposure to the magnetic field won't change significantly as recorded at a regular record cycle but with not regular record but interim record, the lower exposure dose will be appeared than the real level of radiation.

• Proceedings of the Korean Aquaculture Society Conference
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• 2005.05a
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• pp.87-87
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• 2005

• Journal of the Korean Society of Radiology
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• v.6 no.6
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• pp.499-505
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• 2012

The purpose of this study was to find out the difference of radiation dose value through energy, exposure number, fluoroscopy time, the number of days of exposed scatter X-ray when TLD and OSLD is used in diagnostic radiology. The difference of value were measured by relative ratio and interval. Energy makes high relative ratio of TLD($1.81{\pm}0.41$) than OSLD($1.40{\pm}0.26$), exposure number makes high of OSLD($1.40{\pm}0.26$) than TLD($2.10{\pm}0.10$). There are no significant differences between relative ratio of TLD and OSLD in fluoroscopy time and the number of days of exposed scatter X-ray. But interval of relative ratio in the number of days of exposed scatter X-ray was narrowed in less 0.2. That means, the measurement of scatter X-ray could more confident in TLD and OSLD than the measurement of direct ray. In conclusion, we have to recognize the relative ratio of TLD and OSLD could be vary depending on exposed condition of radiation. And in some cases, double test of TLD and OSLD get more creditable results of dose value.

• Journal of the Korea institute for structural maintenance and inspection
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• v.17 no.2
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• pp.94-100
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• 2013

In this paper, Machinery analysis was conducted, in order to predict highest exposure temperatures and the analyze fire damage in the case of fire on reinforced concrete structure. After analyzing differential thermal of reference materials in accordance with temperature of concrete reference core specimen, it turned out that powerful endothermic peak came resulting from evaporation of capillary water and get water untill $200^{\circ}C$, another endothermic peak came resulting from decomposition of calcium hydroxide at $520^{\circ}C$, and then mass of reference materials remarkably decreased due to endothermic reaction. Another powerful endothermic reaction came after decomposition of calcite at $720^{\circ}C$. After analyzing X-ray diffraction of reference materials in accordance with temperature of concrete reference core specimen, it turned out that calcium hydroxide existed until the temperature of $400^{\circ}C$, but CH almost disappeared and CaO appeared from $600^{\circ}C$. The production increased in proportion to the temperature. This is because that calcium hydroxide and calcite are decomposed and CaO is produced when the temperature of concrete increases with fire. It is estimated that calcium hydroxide and calcite are utterly decomposed and peak disappears, and peak of CaO is remarkably formed instead, at the temperature of $700-800^{\circ}C$.

• Journal of Aerospace System Engineering
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• v.14 no.1
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• pp.36-43
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• 2020

The start of satellite thermal design was to predict the worst operating environment through analysis of the thermal environment of the operation orbit. Because the satellites have different types of operating trajectories for their mission, the exposed thermal environment also varies. Thus, it is necessary to analyze in consideration of the orbital conditions, and a design was performed to guarantee thermal stability for the worst case defined through the analysis. The orbital thermal environmental analysis required an understanding of the basic orbit mechanics and the heat exchange relationship between the space environment and satellite. The purpose of this paper was to provide an understanding of the orbital thermal environment analysis by providing basic data on the space thermal environment in the earth-orbit and describing thermal relations that calculate the amount of space heat inflow into satellites. Additionally, an example of a virtual satellite shows the overall process of analyzing the orbital thermal environment during a mission lifetime.