• Korean Journal of Optics and Photonics
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• v.21 no.4
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• pp.133-138
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• 2010

All radiation thermometers have a size-of-source effect (SSE) and a self-radiation effect (SRE). The SSE,defined as dependence of the detector signal of a radiation thermometer on the diameter of a source, is critically dependent on the wavelength since diffraction is the main cause. In this paper, we have measured the SSE and the SRE of TRT2 (Transfer Radiation Thermometer 2, HEITRONICS) widely used as a transfer standard in low and middle temperature range. At $300^{\circ}C$, The radiation temperature difference between the 60 mm diameter blackbody and 10 mm diameter blackbody due to the SSE was estimated to be $3.5^{\circ}C$ in low temperature mode ($8-14\;{\mu}m$) and $0.5^{\circ}C$ in middle temperature mode ($3.9\;{\mu}m$). In addition, the measured radiation temperature difference of the blackbody due to the SRE was found to be 110 mK when the body temperature change of TRT2 was set at $2.6^{\circ}C$.

• Proceedings of the Optical Society of Korea Conference
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• 2003.07a
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• pp.280-281
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• 2003

광도 측정의 기본단위인 칸델라 눈금을 확립하는 방법에는 흑체에서 방출되는 분광복사휘도를 기준으로 사용하는 광원 기반 방법과 극저온 절대 복사계(absolute cryogenic radiometer； ACR)로 부터 출발하여 실현하는 검출기 기반의 두 가지 방법이 사용된다. ACR를 사용하면서 검출기 기반 칸델라 눈금의 불확도가 흑체의 온도 측정 불확도로부터 전파되는 불확도 보다 휠씬 작기 때문에 각국의 국가 측정 표준 대표기관에서 검출기 기반 칸텔라 눈금을 실현하고, 교정이나 측정 서비스를 제공하고 있다. (중략)

• Journal of Aerospace System Engineering
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• v.16 no.6
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• pp.90-98
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• 2022

The output of an infrared (IR) sensor mounted on an EO/IR payload is known to change during a mission period in an orbital environment. As it is required to calibrate the output of the IR sensor periodically to obtain high-quality images, an on-board black body system is mounted on the payload. All systems operating in the space environment require performance tests on ground to verify the target performance in the orbital environment. Therefore, it is also required to test the black body system to verify the performance of the surface temperature uniformity and the estimated representative temperature error within the target temperature range in the operating environment. In this study, calibration of the estimated representative temperature error and verification of the thermal performance of the black body system were conducted by performed a performance test in the thermal vacuum chamber applying deep space radiation cooling effect of an orbital environment.

• Korean Journal of Optics and Photonics
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• v.29 no.2
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• pp.70-76
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• 2018

Comparison calibration equipment for infrared-radiation thermometers below $0^{\circ}C$ has been established, using a TRT2 (transfer radiation thermometer 2, HEITRONICS) as a transfer standard and an ME30 (Model: ME30, HEITRONICS) as a variabletemperature blackbody. The TRT2 was calibrated using three fixed points (Ice ($0.01^{\circ}C$), In ($156.5985^{\circ}C$), and Sn ($231.928^{\circ}C$)) and the Planckian Sakuma-Hattori equation, and including the interpolation and extrapolation errors at $-50^{\circ}C$ in the uncertainty. The pneumatic lid is installed upon opening of the ME30 and is opened for only 30 seconds for measuring the radiation temperature, which prevents formation of ice in the ME30 and also reduces the calibration time to half. The farther away from the $0{\sim}232^{\circ}C$ region, the larger the uncertainty of the comparison calibration equipment becomes. The expanded uncertainty of the comparison calibration equipment was estimated as 0.26 K at $-20^{\circ}C$.

• Korean Journal of Optics and Photonics
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• v.19 no.6
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• pp.400-407
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• 2008

An Instrument to measure normal spectral emissivity is built using a Fourier Transform-Infrared (FT-IR) spectrometer. The instrument is composed of four main parts, reference blackbody, sample furnace, optics system, and FT-IR spectrometer. Measurement ranges of temperature and wavelength are $200^{\circ}C{\sim}500^{\circ}C$ and $3.5{\mu}m{\sim}20{\mu}m$, respectively. Measured emissivity of the reference blackbody is greater than 0.9993 with combined relative uncertainty less than 0.69%, which can be considered an ideal blackbody. We studied the emissivity of opaque alumina, graphite, anodized aluminum, and steel (IMS 200). It is shown that emissivity increases with the roughness of the steel (IMS 200) surface.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.77-77
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• 2004

인공위성은 정상궤도에 들어선 후부터 수명을 다하는 시기까지 각종 복사, 열(온도차), 고진공, 미세중력, 미세운석과 우주파편 등에 의해 영향을 받게 된다. 특히, 위성체에 미치는 열환경은 위성이 궤도를 그리며 운동하는 동안 태양과 지구로부터의 복사량의 크기 및 분포에 따라 결정되는데, 약 5,50$0^{\circ}C$의 흑체온도를 갖고 있는 태양과 -27$0^{\circ}C$의 심우주는 위성체에서 태양이 비추는 부분과 반대편과의 온도를 극한으로 만들게 된다. (중략)

• Journal of the Korean Society for Precision Engineering
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• v.24 no.9
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• pp.32-36
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• 2007

• Proceedings of the Optical Society of Korea Conference
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• 2006.07a
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• pp.455-456
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• 2006

• Journal of the Institute of Electronics Engineers of Korea TC
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• v.43 no.5 s.347
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• pp.176-181
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• 2006

We have built the close range Dicke type radiometer with 35GHz of frequency, which consists of two stage low noise amplifier and diode detector to calibrate temperatures of materials. We have present thermal calibration methods using millimeter-wave radiometer. Output voltages linearly increase with temperatures between 299K and 309K. We are able to measure lower temperature using the liquid nitrogen although results are somewhat unstable.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.12 no.3
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• pp.71-74
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• 2012

We have manufactured a close range Dicke type radiometer which consists of two stage low noise amplifier and diode detector. Frequency range of this system is 35 GHz. And this is used for studying temperature calibration on specific objects. We have present millimeter-wave radiometer's thermal calibration method and its characteristics. From absolute temperature 299K to 309K, in proportion to increase temperature, output voltages are linearly increased. In this case, undefined objects can be measured thermal noise temperature relatively. Overall from absolute temperature 214K to 309K, we have obtained relation of temperature and output voltage;V= 0.03601K - 10.70517.