Volume 6 Issue 2
Apr.  2013
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JIANG Fan, WU Qing-wen, LIU Ju, LI Zhi-lai, YANG Xian-wei, YU Shan-meng. Thermal design of lightweight space remote sensor integrated with satellite in low earth orbit[J]. Chinese Optics, 2013, 6(2): 237-243. doi: 10.3788/CO.20130602.0237
Citation: JIANG Fan, WU Qing-wen, LIU Ju, LI Zhi-lai, YANG Xian-wei, YU Shan-meng. Thermal design of lightweight space remote sensor integrated with satellite in low earth orbit[J]. Chinese Optics, 2013, 6(2): 237-243. doi: 10.3788/CO.20130602.0237

Thermal design of lightweight space remote sensor integrated with satellite in low earth orbit

  • Received Date: 13 Nov 2012
  • Rev Recd Date: 17 Jan 2013
  • Publish Date: 10 Apr 2013
  • A thermal simulation was established according to sensor parameters and the mission requirements to accomplish the thermal design of a lightweight space remote sensor. Atomic oxygen resistant cloth was chosen as the outmost material to reduce the damage by the space environment approximating to the earth. For some satellite devices installed on the back frame of the remote sensor, the connections with high heat resistance were designed and heat insulators were used to eliminate the heat influence on the devices. The positions and powers of the heaters were distributed according to the remote sensor's structure characters. However, none radiator was set because of such small power and duty factor of the CCD components. Finally, the thermal design was certified by a thermal balance test. Three cases designed according to the orbit parameters and attitudes of the remote sensor were simulated and tested. The experiments show that the temperatures of frames and mirrors are (184) ℃ and (182) ℃, respectively, and the temperatures of the CCD components are lower than 30 ℃. The simulation analysis and the thermal balance test results both indicate that the thermal design is valid and content to the mission requirements.

     

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