Development of Boiling and Two-Phase Flow Experiments on Board ISS (Condensation Section)

DOI:10.15011/ijmsa.33.330103
Int. J. Microgravity Sci. Appl. 2016p330103
Author
R. IMAI, K. SUZUKI, H. KAWASAKI, H. OHTA, Y. SHINMOTO, H. ASANO, O. KAWANAMI, K. FUJII, S. MATSUMOTO, T. KURIMOTO, H. TAKAOKA, M. SAKAMOTO, K. USUKU and K. SAWADA
Organization
Course of Aerospace Engineering, Muroran Institute of Technology, Dept. Mechanical Engineering, Tokyo University Science-Yamaguchi, Japan Aerospace Exploration Agency, Dept. Aeronautics and Astronautics, Kyushu University, Dept. Mechanical Engineering, Kobe University, Dept. Mechanical Engineering, University of Hyogo, Nara Institute of Science and Technology
Abstract
Thermal design and evaluation test for condenser system was conducted for the planned ISS experiments on two-phase boiling flow promoted by JAXA. Here perfluorohexane is planned to be used as a working fluid. In this condenser, eight rectangular copper tubes where circular channel of 6mm in diameter was installed on a flat type cold plate; same one which had be operated as thermal control system of on-orbit experimental modules. Arithmetic thermal model of condenser was established considering tube wall conductivity, heat transfer coefficient on condensation and cooling water flow. Specification of the condenser was determined for 400 W of the maximum heat transport requirements through the analysis by this arithmetic model. Evaluation tests using BBM and EM were conducted to verify thermal performance of condenser. In the BBM test FC72 was used as a working fluid. System requirement for condenser; that is, liquid subcooling at outlet is 10 K and more in consideration of suction performance of circular pump was proved to be satisfied.
Keyword(s)
Condenser, Condensation, Boiling flow, Heat transfer coefficient, Arithmetic thermal model, Evaluation test
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Received 30 October 2015, Accepted 13 January 2016, Published 31 January 2016

© The Japan Society of Microgravity Applicaiton

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