12 July 2018 Thermal design utilizing radiative cooling for the payload module of LiteBIRD
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Abstract
The conceptual thermal design of the payload module (PLM) of LiteBIRD utilizing radiative cooling is studied. The thermal environment and structure design of the PLM strongly depend on the precession angle α of the spacecraft. In this study, the geometrical models of the PLM that consist of the sunshield, three layers of Vgrooves, and 5 K shield were designed in the cases of α = 45° , 30° , and 5° . The mission instruments of LiteBIRD are cooled down below 5 K. Therefore, heat transfers down to the 5 K cryogenic part were estimated in each case of α. The radiative heat transfers were calculated by using geometrical models of the PLM. The conductive heat transfers and the active cooling with cryocoolers were considered. We also studied the case that the inner surface of the V-groove is coated by a high-emissivity material.
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Takashi Hasebe, Takashi Hasebe, Shingo Kashima, Shingo Kashima, Satoru Uozumi, Satoru Uozumi, Hirokazu Ishino, Hirokazu Ishino, Shin Utsunomiya, Shin Utsunomiya, Hirofumi Noda, Hirofumi Noda, Kazuhisa Mitsuda, Kazuhisa Mitsuda, Yutaro Sekimoto, Yutaro Sekimoto, Tadayasu Dotani, Tadayasu Dotani, Tomotake Matsumura, Tomotake Matsumura, Hajime Sugai, Hajime Sugai, Masahiro Tsujimoto, Masahiro Tsujimoto, Hiroaki Imada, Hiroaki Imada, Masashi Hazumi, Masashi Hazumi, "Thermal design utilizing radiative cooling for the payload module of LiteBIRD", Proc. SPIE 10698, Space Telescopes and Instrumentation 2018: Optical, Infrared, and Millimeter Wave, 1069864 (12 July 2018); doi: 10.1117/12.2313034; https://doi.org/10.1117/12.2313034
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