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System temperature prediction and verification of all-sky electrostatic analyzer on the lunar surface.

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Title: System temperature prediction and verification of all-sky electrostatic analyzer on the lunar surface.
Authors: Hung, Tsung-Pin1 (AUTHOR) tphung@nkust.edu.tw, Chiang, Chih-Yu2 (AUTHOR) johnson@pssc.ncku.edu.tw, Chang, Tzu-Fang1,3 (AUTHOR) jocelyn@pssc.ncku.edu.tw, Huang, Zhao-Yu2 (AUTHOR) la6091019@gs.ncku.edu.tw, Cheng, Yu-Rong4 (AUTHOR) la6101042@gs.ncku.edu.tw, Tsai, Sheng-Cheng3 (AUTHOR) z06547812@gmail.com, Yen, Tzu-En2 (AUTHOR) la6091035@gs.ncku.edu.tw, Tsai, Jih-Run5 (AUTHOR) jrsherrytsai@gmail.com, Lin, Shin-Fa5 (AUTHOR) sflin@tasa.org.tw
Source: Advances in Space Research. Oct2025, Vol. 76 Issue 8, p4647-4662. 16p.
Subjects: Electrostatic analyzers, Lunar surface, Finite element method, Heat transfer, Electronic equipment
Abstract: The study primarily investigates the thermal transfer characteristics of an all-sky electrostatic analyzer in a vacuum environment that simulates lunar sunlit conditions. Finite element analysis (FEA) was utilized to assess the operating temperature of payloads in space conditions. The experimental setup included a vacuum chamber and an isothermal plate to simulate the extreme temperature cycling of the space environment. By comparing the temperature measurements from the experiment with the results of the FEA, the reliability of the established FEA model in this study was verified. The study explores heat transfer behavior of the payload under the extreme temperature conditions of the lunar surface to determine the suitable operating temperature range and optimal landing latitude for the payload. The results indicate that, under the current system design, when the ambient temperature is below −50 °C, the thermal energy generated by the operating mode and the heating plate is insufficient to maintain the equipment at a survivable temperature. Furthermore, under a 60 °C ambient temperature, the maximum temperature of the electronic system reaches 67.9 °C, approaching the maximum critical temperature that electronic components can withstand. Therefore, it is estimated that the payload can operate during dawn or dusk at latitudes between 0° and 60° on the lunar surface. In regions with latitudes between 60° and 75°, the payload can operate throughout the lunar day. However, at latitudes above 75°, the high daytime temperatures restrict its operation to short periods around dawn or dusk on the lunar surface. [ABSTRACT FROM AUTHOR]
Copyright of Advances in Space Research is the property of Pergamon Press - An Imprint of Elsevier Science and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
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Header DbId: egs
DbLabel: Engineering Source
An: 188057284
AccessLevel: 6
PubType: Academic Journal
PubTypeId: academicJournal
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  Data: System temperature prediction and verification of all-sky electrostatic analyzer on the lunar surface.
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  Data: <searchLink fieldCode="AR" term="%22Hung%2C+Tsung-Pin%22">Hung, Tsung-Pin</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> tphung@nkust.edu.tw</i><br /><searchLink fieldCode="AR" term="%22Chiang%2C+Chih-Yu%22">Chiang, Chih-Yu</searchLink><relatesTo>2</relatesTo> (AUTHOR)<i> johnson@pssc.ncku.edu.tw</i><br /><searchLink fieldCode="AR" term="%22Chang%2C+Tzu-Fang%22">Chang, Tzu-Fang</searchLink><relatesTo>1,3</relatesTo> (AUTHOR)<i> jocelyn@pssc.ncku.edu.tw</i><br /><searchLink fieldCode="AR" term="%22Huang%2C+Zhao-Yu%22">Huang, Zhao-Yu</searchLink><relatesTo>2</relatesTo> (AUTHOR)<i> la6091019@gs.ncku.edu.tw</i><br /><searchLink fieldCode="AR" term="%22Cheng%2C+Yu-Rong%22">Cheng, Yu-Rong</searchLink><relatesTo>4</relatesTo> (AUTHOR)<i> la6101042@gs.ncku.edu.tw</i><br /><searchLink fieldCode="AR" term="%22Tsai%2C+Sheng-Cheng%22">Tsai, Sheng-Cheng</searchLink><relatesTo>3</relatesTo> (AUTHOR)<i> z06547812@gmail.com</i><br /><searchLink fieldCode="AR" term="%22Yen%2C+Tzu-En%22">Yen, Tzu-En</searchLink><relatesTo>2</relatesTo> (AUTHOR)<i> la6091035@gs.ncku.edu.tw</i><br /><searchLink fieldCode="AR" term="%22Tsai%2C+Jih-Run%22">Tsai, Jih-Run</searchLink><relatesTo>5</relatesTo> (AUTHOR)<i> jrsherrytsai@gmail.com</i><br /><searchLink fieldCode="AR" term="%22Lin%2C+Shin-Fa%22">Lin, Shin-Fa</searchLink><relatesTo>5</relatesTo> (AUTHOR)<i> sflin@tasa.org.tw</i>
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  Data: <searchLink fieldCode="JN" term="%22Advances+in+Space+Research%22">Advances in Space Research</searchLink>. Oct2025, Vol. 76 Issue 8, p4647-4662. 16p.
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  Data: <searchLink fieldCode="DE" term="%22Electrostatic+analyzers%22">Electrostatic analyzers</searchLink><br /><searchLink fieldCode="DE" term="%22Lunar+surface%22">Lunar surface</searchLink><br /><searchLink fieldCode="DE" term="%22Finite+element+method%22">Finite element method</searchLink><br /><searchLink fieldCode="DE" term="%22Heat+transfer%22">Heat transfer</searchLink><br /><searchLink fieldCode="DE" term="%22Electronic+equipment%22">Electronic equipment</searchLink>
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  Data: The study primarily investigates the thermal transfer characteristics of an all-sky electrostatic analyzer in a vacuum environment that simulates lunar sunlit conditions. Finite element analysis (FEA) was utilized to assess the operating temperature of payloads in space conditions. The experimental setup included a vacuum chamber and an isothermal plate to simulate the extreme temperature cycling of the space environment. By comparing the temperature measurements from the experiment with the results of the FEA, the reliability of the established FEA model in this study was verified. The study explores heat transfer behavior of the payload under the extreme temperature conditions of the lunar surface to determine the suitable operating temperature range and optimal landing latitude for the payload. The results indicate that, under the current system design, when the ambient temperature is below −50 °C, the thermal energy generated by the operating mode and the heating plate is insufficient to maintain the equipment at a survivable temperature. Furthermore, under a 60 °C ambient temperature, the maximum temperature of the electronic system reaches 67.9 °C, approaching the maximum critical temperature that electronic components can withstand. Therefore, it is estimated that the payload can operate during dawn or dusk at latitudes between 0° and 60° on the lunar surface. In regions with latitudes between 60° and 75°, the payload can operate throughout the lunar day. However, at latitudes above 75°, the high daytime temperatures restrict its operation to short periods around dawn or dusk on the lunar surface. [ABSTRACT FROM AUTHOR]
– Name: AbstractSuppliedCopyright
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  Data: <i>Copyright of Advances in Space Research is the property of Pergamon Press - An Imprint of Elsevier Science and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
PLink https://search.ebscohost.com/login.aspx?direct=true&site=eds-live&db=egs&AN=188057284
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      – Type: doi
        Value: 10.1016/j.asr.2025.07.034
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      – Code: eng
        Text: English
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      Pagination:
        PageCount: 16
        StartPage: 4647
    Subjects:
      – SubjectFull: Electrostatic analyzers
        Type: general
      – SubjectFull: Lunar surface
        Type: general
      – SubjectFull: Finite element method
        Type: general
      – SubjectFull: Heat transfer
        Type: general
      – SubjectFull: Electronic equipment
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      – TitleFull: System temperature prediction and verification of all-sky electrostatic analyzer on the lunar surface.
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              Text: Oct2025
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