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热管科学与技术

ISSN 打印: 2151-7975
ISSN 在线: 2151-7991

Archives: Volume 1, 2010 to Volume 8, 2017

热管科学与技术

DOI: 10.1615/HeatPipeScieTech.2014005521
pages 169-180

PROCEDURE AND TOOLS FOR DEVELOPING THERMAL CONTROL SYSTEM FOR SCIENTIFIC SPACECRAFT EQUIPMENT

S. A. Hryshyn
B.I. Stepanov Institute of Physics, National Academy of Sciences, Minsk, Belarus
A. G. Batischev
National Research Nuclear University MEPhI, Moscow, Russia
S. V. Koldashov
National Research Nuclear University MEPhI, Moscow, Russia
Aliaksei L. Petsiuk
B.I. Stepanov Institute of Physics, National Academy of Sciences, Minsk, Belarus
V. A. Seliantev
B.I. Stepanov Institute of Physics, National Academy of Sciences, Minsk, Belarus
S. O. Marach
Institute of Heat and Mass Transfer, National Academy of Sciences, Minsk, Belarus
Viachaslau V. Doktarau
Powder Metallurgy Institute, Platonov str., 41, 220005, Minsk, Belarus
S. S. Grishin
The B. I. Stepanov Institute of Physics, 68 Prospekt Nezavisimosti, Minsk BY-220072, Republic of Belarus

ABSTRACT

The paper describes a methodology of thermal control systems development for onboard scientific instruments for use, for example, in the electronics modules of the magnetic measurement systems and the scintillation telescope designed for installation on the open platform of spacecrafts. The main steps of thermal control system development, the results of computer simulation of temperature field distribution, and the description of the hardware−software complex for thermal testing are considered. As a result, the calculations enabled determination of the type and design parameters of the heat link system. A heat pipe with powder arterial capillary micro- and nanostructure was used as the main heat link for the considered systems.


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