Calculation of complex heat transfer in the liquid circuit of the spacecraft thermal control system based on real topology and thermophysical properties

Автор: Shevchenko Yu. N., Kishkin A.A., Tanasiyenko F.V., Shilkin O.V., Sokolov S.N.

Журнал: Сибирский аэрокосмический журнал @vestnik-sibsau

Рубрика: Авиационная и ракетно-космическая техника

Статья в выпуске: 3 т.20, 2019 года.

Бесплатный доступ

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.

Еще

Thermal control system, liquid circuit, thermal resistance, complex heat transfer

Короткий адрес: https://sciup.org/148321930

IDR: 148321930   |   DOI: 10.31772/2587-6066-2019-20-3-375-382

Список литературы Calculation of complex heat transfer in the liquid circuit of the spacecraft thermal control system based on real topology and thermophysical properties

  • Meseguer J., Perez-Grande I., Sanz-Andres A. Spacecraft thermal control. Cambridge, UK: Woodhead Publishing Limited, 2012. 413 p.
  • Gilmore D. G. Spacecraft thermal control handbook. The Aerospace Corporation Press, 2002. 413 p.
  • Алексеев В. А., Малоземов В. В. Обеспечение теплового режима радиоэлектронного оборудования космических аппаратов. М.: МАИ, 2001. 52 с.
  • Крушенко Г. Г., Голованова В. В. Совершенствование системы терморегулирования космических аппаратов // Вестник СибГАУ. 2014. № 3 (55). С. 185-189.
  • Чеботарев В. Е., Зимин И. И. Procedure for evaluating the effective use range of the unified space platforms // Сибирский журнал науки и технологий. 2018, Т. 19, №. 3, С. 532-537. 10.31772/2587- 6066-2018-19-3-532-537. DOI: 10.31772/2587-6066-2018-19-3-532-537
Статья научная