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Modelling the extraneous heat exchange of spacecraft using solar radiation simulation facility and simulators of the
planetary radiation field in several cases is an intractable problem not only in technical but also in methodological
terms. For some technical reasons, solar radiation simulator is stationary. Consequently, to reproduce a possible
change in the orientation of the test object relative to the solar radiation flux, it is necessary to equip the thermal vacuum
unit with devices that allow the test object to be rotated at least about two axes. In this paper, a mathematical
model and a method for solving the problem of heat transfer in a multilayer structure of screen-vacuum thermal insulation
under the influence of solar radiation is proposed. A method is proposed for the numerical solution of a normal
system of nonlinear differential equations using the linearisation of nonlinear terms. Various results of numerical modelling
were obtained, which indicate the adequacy of the proposed mathematical model. It has been revealed that
high-inertia thermal insulation of sufficient thickness is required to stabilise the thermal state inside the spacecraft.
The work was carried out with the financial support of the
state project of the Ministry of Education and Science
project code FSFF-2020-0017.
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