Energy Saving Thermal Management of Space Remote Sensor and Validation
An energy-efficient thermal control management method for space remote sensors using optical, mechanical, electrical, and thermal integration is proposed. The satellite power resources are insufficient, so an energy-efficient loop heat pipe (LHP) is designed for six intermittently operating detector...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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MDPI AG
2023-01-01
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| Series: | Energies |
| Subjects: | |
| Online Access: | https://www.mdpi.com/1996-1073/16/2/864 |
| _version_ | 1827626221784006656 |
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| author | Pan Lu Teng Gao Quanwang Chen Xiaohan Ren |
| author_facet | Pan Lu Teng Gao Quanwang Chen Xiaohan Ren |
| author_sort | Pan Lu |
| collection | DOAJ |
| description | An energy-efficient thermal control management method for space remote sensors using optical, mechanical, electrical, and thermal integration is proposed. The satellite power resources are insufficient, so an energy-efficient loop heat pipe (LHP) is designed for six intermittently operating detectors. The charge-coupled device (CCD) has a total heat generation of 72 W and operates for 8 min per orbital cycle. The LHP includes a capillary pump, six cold plates, and two radiators. The working fluid of the LHP is high-purity ammonia and the material of the wick is ceramic. The drive power on the capillary pump evaporator automatically switches between 30 W and 90 W depending on the operating mode of the remote sensor, resulting in an average power saving of about 58.2% compared to a conventional LHP. For the optical structure, a three-stage insulation technology was developed to save heater power and improve temperature stability. A transient numerical simulation model of the LHP was developed to study the vapor–liquid zone of two radiators under the condition of rapid power change. Vacuum thermal tests were conducted and the test data agreed well with the numerical simulation results. The in-orbit temperature data showed that the temperature fluctuations of the optical structure and CCD were less than ±0.2 °C and ±0.8 °C, respectively. |
| first_indexed | 2024-03-09T12:51:44Z |
| format | Article |
| id | doaj.art-33d353b9341d4a84a9e51c7fac10dec5 |
| institution | Directory Open Access Journal |
| issn | 1996-1073 |
| language | English |
| last_indexed | 2024-03-09T12:51:44Z |
| publishDate | 2023-01-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Energies |
| spelling | doaj.art-33d353b9341d4a84a9e51c7fac10dec52023-11-30T22:05:11ZengMDPI AGEnergies1996-10732023-01-0116286410.3390/en16020864Energy Saving Thermal Management of Space Remote Sensor and ValidationPan Lu0Teng Gao1Quanwang Chen2Xiaohan Ren3Beijing Institute of Space Mechanics and Electricity, Beijing 100094, ChinaBeijing Institute of Space Mechanics and Electricity, Beijing 100094, ChinaShandong Institute for Product Quality Inspection, Jinan 250102, ChinaInstitute of Thermal Science and Technology, Shandong University, Jinan 250061, ChinaAn energy-efficient thermal control management method for space remote sensors using optical, mechanical, electrical, and thermal integration is proposed. The satellite power resources are insufficient, so an energy-efficient loop heat pipe (LHP) is designed for six intermittently operating detectors. The charge-coupled device (CCD) has a total heat generation of 72 W and operates for 8 min per orbital cycle. The LHP includes a capillary pump, six cold plates, and two radiators. The working fluid of the LHP is high-purity ammonia and the material of the wick is ceramic. The drive power on the capillary pump evaporator automatically switches between 30 W and 90 W depending on the operating mode of the remote sensor, resulting in an average power saving of about 58.2% compared to a conventional LHP. For the optical structure, a three-stage insulation technology was developed to save heater power and improve temperature stability. A transient numerical simulation model of the LHP was developed to study the vapor–liquid zone of two radiators under the condition of rapid power change. Vacuum thermal tests were conducted and the test data agreed well with the numerical simulation results. The in-orbit temperature data showed that the temperature fluctuations of the optical structure and CCD were less than ±0.2 °C and ±0.8 °C, respectively.https://www.mdpi.com/1996-1073/16/2/864thermal designloop heat piperemote sensor thermal control |
| spellingShingle | Pan Lu Teng Gao Quanwang Chen Xiaohan Ren Energy Saving Thermal Management of Space Remote Sensor and Validation Energies thermal design loop heat pipe remote sensor thermal control |
| title | Energy Saving Thermal Management of Space Remote Sensor and Validation |
| title_full | Energy Saving Thermal Management of Space Remote Sensor and Validation |
| title_fullStr | Energy Saving Thermal Management of Space Remote Sensor and Validation |
| title_full_unstemmed | Energy Saving Thermal Management of Space Remote Sensor and Validation |
| title_short | Energy Saving Thermal Management of Space Remote Sensor and Validation |
| title_sort | energy saving thermal management of space remote sensor and validation |
| topic | thermal design loop heat pipe remote sensor thermal control |
| url | https://www.mdpi.com/1996-1073/16/2/864 |
| work_keys_str_mv | AT panlu energysavingthermalmanagementofspaceremotesensorandvalidation AT tenggao energysavingthermalmanagementofspaceremotesensorandvalidation AT quanwangchen energysavingthermalmanagementofspaceremotesensorandvalidation AT xiaohanren energysavingthermalmanagementofspaceremotesensorandvalidation |