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Thermal Design Analysis of a Space Solar Power System Module

[+] Author Affiliations
Masao Furukawa

Japan Aerospace Exploration Agency, Tsukuba, Ibaraki, Japan

Paper No. ESDA2004-58026, pp. 27-39; 13 pages
doi:10.1115/ESDA2004-58026
From:
  • ASME 7th Biennial Conference on Engineering Systems Design and Analysis
  • Volume 1
  • Manchester, England, July 19–22, 2004
  • ISBN: 0-7918-4173-1 | eISBN: 0-7918-3741-6
  • Copyright © 2004 by ASME

abstract

A theoretical analysis has been made to examine feasibilities of a proposed Space Solar Power System module in thermal aspects. Analyzed first is the system thermal balance. Obtained analysis results are normalized by the electromagnetic transmitting power to express the specific cold plate area, the specific radiator area, and the specific heat rejection. Equations for the cold plate design are derived from relations describing the boiling heat transfer and the two-phase heat transport in a modeled evaporator. Solutions are arranged to determine the equivalent hydraulic diameter and the heat transfer surface are density. Equations governing the radial heat transfer, the axial heat transport, and the heat rejection are solved to give the total condenser length and the dimensionless active surface area of a condensing radiator. A fluid loop pressure loss model and a system mass breakdown model are also presented. All the expressions and models are coded to form a computer program available to parametric design studies. Computations have been done with the solar concentration ratio and the cell base plate temperature as main parameters of interest. Numerical results are graphically shown in the figures to contribute to design practices of a 100 kW power module composed of equally sized seven submodules.

Copyright © 2004 by ASME

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