Infrared and Laser Engineering, Volume. 49, Issue 4, 0413007(2020)

Thermal design of one space gas monitoring sensor and test validation

Chunmei Shen1,2, Feng Yu1,2, and Wenkai Liu1,2
Author Affiliations
  • 1Beijing Institute of Space Mechanics and Electricity, Beijing 100094, China
  • 2Key Laboratory for Advanced Optical Remote Sensing Technology of Beijing, Beijing 100094, China
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    Figures & Tables(15)
    Structure layout of gas monitoring sensor
    Payloads' deployment on satellite
    Schematic diagram of lens 7 components and voice coil motor
    Thermal control scheme of gas monitoring sensor
    Heat dissipation schemes of electronic devices 1-2 and 7-11(E: electric device)
    Insulation installation method between electronic devices and base plate
    Heat dissipation schemes of electronic devices 3-6(E: electric device; O: optical lens)
    Heat dissipation schemes of voice coil motor
    Simulation tool of satellite platform
    Temperature curves of main components on gas monitoring sensor under hot and cold case condition
    • Table 1. Heat consumption and operating time of calorigenic equipments

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      Table 1. Heat consumption and operating time of calorigenic equipments

      Calorigenic equipments Stand by mode/W Observation mode/W Calibration mode/W Operating time on orbit/min
      Electric device 1111111102
      Electric device 203368
      Electric device 300.30.363
      Electric device 40.91.21.2102
      Electric device 50.91.21.2102
      Electric device 60.91.21.2102
      Electric device 70043
      Electric device 80202063
      Electric device 90021.13
      Electric device 10888102
      Electric device 1104452
      Voice coil motor02252
      Stepper motor01.71.752
    • Table 2. Temperature control requirements of gas monitoring sensor components

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      Table 2. Temperature control requirements of gas monitoring sensor components

      ComponentsTemperature requirement/℃
      Operating timeNon-operating time
      Optical lens 719±319±7
      Optical lens 1–6,820±2
      Voice coil motor of optical lens 70–85
      Stepper motor of optical lens 7–10–80
      Electric device 1,2,7–11–10–45
      Electric device 3–60–20
    • Table 3. Thermal boundary conditions of gas monitoring sensor on orbit and simulation methods of these conditions during ground test

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      Table 3. Thermal boundary conditions of gas monitoring sensor on orbit and simulation methods of these conditions during ground test

      Thermal boundary conditionsSimulation methods during ground test
      Vacuum and space cold black backgroundUse space environment simulator
      Thermal environment on satellite platformDesign simulation tool of satellite platform,which is shown in Fig.9, Fig.5Control the temperature of simulation tool according to the given temperature boundary of satellite; Cover simulation tool surfaces facing gas monitoring sensor with MLI and put heating circuit on surface of the MLI to obtain orbit heat flux absorbed by MLI
      Orbit heat fluxUse infrared heating cage and flux sensor to abtain heat flux incidenting to the entrance of earth baffle; Put heating circuit on MLI surfaces and radiator back surface to obtain orbit heat flux absorbed by them
      Heat consumption of calorigenic equipmentsCalorigenic equipments of gas monitoring sensor operate during test according to the normal working mode on orbit
    • Table 4. Operating conditions of test

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      Table 4. Operating conditions of test

      CaseOrbit heat fluxOne orbit working modeTemperature boundary of satellite/℃
      Cold caseMinimum heat flux throughout the life cycleStandby mode−5
      Hot caseMaximum heat flux throughout the life cycleStandby mode→calibration mode→ observation mode→standby mode 45
    • Table 5. Summary of test results(Unit: ℃)

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      Table 5. Summary of test results(Unit: ℃)

      ComponentsCold case Hot case Temperature requirement
      Optical lens 118.8−1920.4−20.920±2
      Optical lens 220.8−21.020.8−21.020±2
      Optical lens 319.6−19.819.8−20.020±2
      Optical lens 421.3−21.521.0−21.320±2
      Optical lens 519.9−20.019.9−20.120±2
      Optical lens 620.2−20.520.5−21.120±2
      Optical lens 819.1−20.020.4−21.220±2
      Optical lens 716−16.619.1−20.3Operating time19±3 Non-operating time19±7
      Electric device 19.2−1214.2−19.1−10−45
      Electric device 219.8−20.426.7−27.3−10−45
      Electric device 38.4−9.79.5−12.40−20
      Electric device 48.8−10.09.9−12.80−20
      Electric device 58.7−9.99.9−12.70−20
      Electric device 68.4−10.09.5−12.80−20
      Electric device 72.6−4.517.1−21.7−10−45
      Electric device 84.8−6.520.1−24.2−10−45
      Electric device 94.5−6.620.0−24.1−10−45
      Electric device 1011.1−12.522.3−26.0−10−45
      Electric device 119.1−10.819.0−24.8−10−45
      Voice coil motor14.4−16.317.9−35.60−85
      Stepper motor18.5−18.628.7−35.9−10−80
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    Chunmei Shen, Feng Yu, Wenkai Liu. Thermal design of one space gas monitoring sensor and test validation[J]. Infrared and Laser Engineering, 2020, 49(4): 0413007

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    Paper Information

    Received: Jan. 5, 2020

    Accepted: --

    Published Online: May. 27, 2020

    The Author Email:

    DOI:10.3788/IRLA202049.0413007

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