年間 18 号発行
ISSN 印刷: 1064-2285
ISSN オンライン: 2162-6561
Indexed in
Heat Transfer in Instrumentation Modules of Spacecrafts with the Systems of Heat Control on the Basis of Heat Pipes
要約
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.