Design and verification of focal plane assembly thermal control system of one space-based astronomy telescope

Wen-gang Yang; Xue-wu Fan; Chen-jie Wang; Ying-hao Wang; Liang-jie Feng; Yun-fei Du; Guo-rui Ren; Wei Wang; Chuang Li; Wei Gao

doi:10.1117/12.2199517

8 October 2015 Design and verification of focal plane assembly thermal control system of one space-based astronomy telescope

Wen-gang Yang, Xue-wu Fan, Chen-jie Wang, Ying-hao Wang, Liang-jie Feng, Yun-fei Du, Guo-rui Ren, Wei Wang, Chuang Li, Wei Gao

Author Affiliations +

Proceedings Volume 9678, AOPC 2015: Telescope and Space Optical Instrumentation; 96780Q (2015) https://doi.org/10.1117/12.2199517
Event: Applied Optics and Photonics China (AOPC2015), 2015, Beijing, China

Abstract

One space-based astronomy telescope will observe astronomy objects whose brightness should be lower than 23th magnitude. To ensure the telescope performance, very low system noise requirements need extreme low CCD operating temperature (lower than -65°C). Because the satellite will be launched in a low earth orbit, inevitable space external heat fluxes will result in a high radiator sink temperature (higher than -65°C). Only passive measures can’t meet the focal plane cooling specification and active cooling technologies must be utilized. Based on detailed analysis on thermal environment of the telescope and thermal characteristics of focal plane assembly (FPA), active cooling system which is based on thermo-electric cooler (TEC) and heat rejection system (HRS) which is based on flexible heat pipe and radiator have been designed. Power consumption of TECs is dependent on the heat pumped requirements and its hot side temperature. Heat rejection capability of HRS is mainly dependent on the radiator size and temperature. To compromise TEC power consumption and the radiator size requirement, thermal design of FPA must be optimized. Parasitic heat loads on the detector is minimized to reduce the heat pumped demands of TECs and its power consumption. Thermal resistance of heat rejection system is minimized to reject the heat dissipation of TECs from the hot side to the radiator efficiently. The size and surface coating of radiator are optimized to compromise heat reject ion requirements and system constraints. Based on above work, transient thermal analysis of FPA is performed. FPA prototype model has been developed and thermal vacuum/balance test has been accomplished. From the test, temperature of key parts and working parameters of TECs in extreme cases have been acquired. Test results show that CCD can be controlled below -65°C and all parts worked well during the test. All of these verified the thermal design of FPA and some lessons will be presented in this paper.

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Wen-gang Yang, Xue-wu Fan, Chen-jie Wang, Ying-hao Wang, Liang-jie Feng, Yun-fei Du, Guo-rui Ren, Wei Wang, Chuang Li, and Wei Gao "Design and verification of focal plane assembly thermal control system of one space-based astronomy telescope", Proc. SPIE 9678, AOPC 2015: Telescope and Space Optical Instrumentation, 96780Q (8 October 2015); https://doi.org/10.1117/12.2199517

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KEYWORDS

Charge-coupled devices

Space telescopes

Telescopes

Staring arrays

Astronomy

Control systems design

Astronomical telescopes

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