Infrared and Laser Engineering, Volume. 49, Issue 4, 0413007(2020)
Thermal design of one space gas monitoring sensor and test validation
Figures & Tables(15)
Fig. 3. Schematic diagram of lens 7 components and voice coil motor
Fig. 5. Heat dissipation schemes of electronic devices 1-2 and 7-11(E: electric device)
Fig. 6. Insulation installation method between electronic devices and base plate
Fig. 7. Heat dissipation schemes of electronic devices 3-6(E: electric device; O: optical lens)
Fig. 10. 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
View tableView in ArticleTable 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 1 11 11 11 102 Electric device 2 0 3 3 68 Electric device 3 0 0.3 0.3 63 Electric device 4 0.9 1.2 1.2 102 Electric device 5 0.9 1.2 1.2 102 Electric device 6 0.9 1.2 1.2 102 Electric device 7 0 0 4 3 Electric device 8 0 20 20 63 Electric device 9 0 0 21.1 3 Electric device 10 8 8 8 102 Electric device 11 0 4 4 52 Voice coil motor 0 2 2 52 Stepper motor 0 1.7 1.7 52
Table 2. Temperature control requirements of gas monitoring sensor components
View tableView in ArticleTable 2. Temperature control requirements of gas monitoring sensor components
Components Temperature requirement/℃ Operating time Non-operating time Optical lens 7 19±3 19±7 Optical lens 1–6,8 20±2 Voice coil motor of optical lens 7 0–85 Stepper motor of optical lens 7 –10–80 Electric device 1,2,7–11 –10–45 Electric device 3–6 0–20
Table 3. Thermal boundary conditions of gas monitoring sensor on orbit and simulation methods of these conditions during ground test
View tableView in ArticleTable 3. Thermal boundary conditions of gas monitoring sensor on orbit and simulation methods of these conditions during ground test
Thermal boundary conditions Simulation methods during ground test Vacuum and space cold black background Use space environment simulator Thermal environment on satellite platform Design simulation tool of satellite platform，which is shown in Fig.9 ,Fig.5 Control 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 flux Use 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 equipments Calorigenic equipments of gas monitoring sensor operate during test according to the normal working mode on orbit
Table 4. Operating conditions of test
View tableView in ArticleTable 4. Operating conditions of test
Case Orbit heat flux One orbit working mode Temperature boundary of satellite/℃ Cold case Minimum heat flux throughout the life cycle Standby mode −5 Hot case Maximum heat flux throughout the life cycle Standby mode→calibration mode→ observation mode→standby mode 45
Table 5. Summary of test results（Unit: ℃）
View tableView in ArticleTable 5. Summary of test results（Unit: ℃）
Components Cold case Hot case Temperature requirement Optical lens 1 18.8−19 20.4−20.9 20±2 Optical lens 2 20.8−21.0 20.8−21.0 20±2 Optical lens 3 19.6−19.8 19.8−20.0 20±2 Optical lens 4 21.3−21.5 21.0−21.3 20±2 Optical lens 5 19.9−20.0 19.9−20.1 20±2 Optical lens 6 20.2−20.5 20.5−21.1 20±2 Optical lens 8 19.1−20.0 20.4−21.2 20±2 Optical lens 7 16−16.6 19.1−20.3 Operating time19±3 Non-operating time19±7 Electric device 1 9.2−12 14.2−19.1 −10−45 Electric device 2 19.8−20.4 26.7−27.3 −10−45 Electric device 3 8.4−9.7 9.5−12.4 0−20 Electric device 4 8.8−10.0 9.9−12.8 0−20 Electric device 5 8.7−9.9 9.9−12.7 0−20 Electric device 6 8.4−10.0 9.5−12.8 0−20 Electric device 7 2.6−4.5 17.1−21.7 −10−45 Electric device 8 4.8−6.5 20.1−24.2 −10−45 Electric device 9 4.5−6.6 20.0−24.1 −10−45 Electric device 10 11.1−12.5 22.3−26.0 −10−45 Electric device 11 9.1−10.8 19.0−24.8 −10−45 Voice coil motor 14.4−16.3 17.9−35.6 0−85 Stepper motor 18.5−18.6 28.7−35.9 −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
Paper Information
Received: Jan. 5, 2020
Accepted: --
Published Online: May. 27, 2020
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