10 W/90 K single-stage pulse tube cryocoolers |
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| Authors: | Haizheng Dang Libao Wang Kaixiang Yang |
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| Affiliation: | 1. NASA Kennedy Space Center, M/S: NE-F6 Kennedy Space Center, FL, USA, 32899;2. NASA Marshall Space Flight Center, M/S:ER-24 Huntsville, AL, USA, 35812;1. Univ. Grenoble Alpes, CEA, INAC, SBT, F-38000 Grenoble, France;2. ISAS-JAXA, 3-1-1Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan;3. R&D-JAXA, 2-1-1 Sengen, Tsukuba, Ibaraki 305-8505, Japan;4. High Energy Accelerator Research Organization (KEK), 1-1 Oho, Tsukuba, Ibaraki 305-0801, Japan;5. CNES Toulouse, F-31055 Cedex 4, France;6. ESA-ESTEC, Noordwijk, The Netherlands;1. Key Laboratory of Cryogenics, Technical Institute of Physics and Chemistry, Chinese Academy of Sciences, Beijing 100190, China;2. Lihan Cryogenics Co., Ltd, Shenzhen 518055, China;3. Graduate University of Chinese Academy of Sciences, Beijing 100190, China;2. Department of Orthopaedic Surgery, Yong Loo Lin School of Medicine, National University Health System, National University of Singapore, 1E Kent Ridge Road, Singapore 119074/119288, Singapore;3. Department of Orthopaedic Surgery & Biochemistry and Molecular Biology, Mayo Clinic, Rochester, MN 55905, USA;4. Department of Biochemistry, Yong Loo Lin School of Medicine, National University of Singapore, Singapore 117596, Singapore |
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| Abstract: | A single-stage 10 W/90 K coaxial pulse tube cryocooler has been developed for space-borne optics cooling. The design considerations are described, and the optimizations on the double-segmented inertance tubes are presented. The preliminary engineering model (EM) of the cooler has been worked out, which typically provides the cooling of 10 W at 90 K with the input power of 175.6 W at 310 K reject temperature, and achieves around 14% of Carnot efficiency at 90 K. The reject temperature dependence experiments on the EM show a smaller slope of 10.2 W/10 K and indicate a good adaptability to the reject temperature range from 290 K to 333 K. |
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