Научная электронная библиотека ULRICH'S Periodicals Directory

Сибирский государственный университет
науки и технологий имени академика М.Ф. Решетнева

Сибирский аэрокосмический журнал
ISSN 2712-8970 (Print) ISSN 2782-5760 (on-line)

Сведения об образовательной организации

UDK 629.78 Doi: 10.31772/2587-6066-2019-20-3-375-382
CALCULATION OF COMPLEX HEAT TRANSFER IN THE LIQUID CIRCUIT OF THE SPACECRAFT THERMAL CONTROL SYSTEM BASED ON REAL TOPOLOGY AND THERMOPHYSICAL PROPERTIES
Yu. N. Shevchenko, A. A. Kishkin, F. V. Tanasiyenko, O. V. Shilkin, S. N. Sokolov
Reshetnev Siberian State University of Science and Technology, 31, Krasnoyarsky Rabochy Av., Krasnoyarsk, 660037, Russian Federation; JSC “Academician M. F. Reshetnev “Information Satellite Systems”, 52, Lenin St., Zheleznogorsk, Krasnoyarsk region, 662972, Russian Federation. E-mail: spsp99@mail.ru.
The thermal control system (TCS) is one of the most important systems, which largely determines the design of the spacecraft. At the present stage of development of methods and tools for spacecraft design, a promising direction is the creation of thermal mathematical models of the TCS, calculation algorithms, which allow to create effective design solutions at various design stages. The purpose of this work is to bring the system of equations of heat balances of the liquid circuit (LC) of TCS to a form that allows programmatic numerical integration in the solution search algorithm along the length of the middle line of the heat and mass exchange fluid circuit taking into account certain complex thermal resistances. In fact, this means that the terms of the temperature of the contour and the linear coordinate, the integration variable, should remain as variables in the equation record, everything else should be numerically determined from the properties of the real object. For the boundary conditions of the LC TCS of the spacecraft, the coefficients of complex heat transfer were calculated taking into account the actual topology of the circuit and the thermal properties of the coolant. Using these values, the system of thermal balances of the spacecraft of the spacecraft on the characteristic surfaces of constant temperatures was reduced to a form that allows a numerical solution: the number of equations corresponds to the number of detected temperatures along the north and south panels and is closed through the temperature of the liquid circuit refrigerant. The resulting system of equations allows us to investigate the thermal state of nonhermetic formation spacecraft at the stage of preliminary design with varying operational and design parameters in order to determine the area of efficiency and the area of optimal operation under certain performance criteria.
Key words: thermal control system, liquid circuit, thermal resistance, complex heat transfer.
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Shevchenko Yulia Nikolaevna – head of the laboratory of the Department of Refrigeration, Cryogenic Engineering
and Conditioning; Reshetnev Siberian State University of Science and Technology. E-mail: delkov-mx01@mail.ru

Kishkin Alexander Anatolievich – Dr. Sc., professor, head of the Department of Refrigeration, Cryogenic
Engineering and Conditioning; Reshetnev Siberian State University of Science and Technology. E-mail:
spsp99@mail.ru.

Tanasienko Fedor Vladimirovich – post-graduate student of the Department of Refrigeration, Cryogenic
Engineering and Conditioning; Reshetnev Siberian State University of Science and Technology. E-mail:
prometey_86@mail.ru.

Shilkin Oleg Valentinovich – head of sector; JSC “Academician M. F. Reshenev “Information Satellite Systems”.
E-mail: o.shilkin61@mail.ru.

Sokolov Sergey Nikolayevich – engineer; JSC “Academician M. F. Reshenev “Information Satellite Systems”.
E-mail: sokolovsergey92@mail.ru.


  CALCULATION OF COMPLEX HEAT TRANSFER IN THE LIQUID CIRCUIT OF THE SPACECRAFT THERMAL CONTROL SYSTEM BASED ON REAL TOPOLOGY AND THERMOPHYSICAL PROPERTIES