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DOI: 10.1615/HeatTransRes.v32.i7-8.80
7 pages

Heat Transfer in Instrumentation Modules of Spacecrafts with the Systems of Heat Control on the Basis of Heat Pipes

A. N. Kozlobrodov
Scientific-Research Institute of Applied Mathematics and Mechanics at the Tomsk State University, Tomsk, Russia
G. V. Kuntsevich
Scientific-Research Institute of Applied Mathematics and Mechanics at Tomsk State University, Tomsk, Russia
S. F. Sandu
Scientific-Research Institute of Applied Mathematics and Mechanics at the Tomsk State University, Tomsk, Russia

ABSTRACT

The process of heat transfer in an instrumentation module of a spacecraft with the systems of heat control on the basis of low-temperature heat pipes is studied numerically. Special attention is paid to an analysis of heat transfer due to internal reirradiation and operation of heat pipes. A multi-dimensional character of heat propagation in the structure of the instrumentation module and the possibility of construction of these design-arrangement schemes which could provide stable operation of instrument panels under extremum conditions of heat transfer are shown. It is found that a number of heat pipes and their arrangement exert a substantial effect on the distribution of temperature fields of all the panels of the module and an account for internal re-emission leads to leveling of them.


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