Modelling the extraneous heat exchange of spacecraft using solar radiation simulation facility and simulators of the planetary radiation field in a number of cases is an intractable problem not only in technical, but also in methodological terms. For a number of technical reasons, the solar radiation simulator is stationary. Consequently, in order 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 physical and mathematical foundations of the heat-shielding composite materials (CM) functioning under the conditions of aerogasdynamic heating of hypersonic aircraft, as well as under the conditions of the point effect of high-energy radiation are considered. On the basis of the new laws of CM binding substance decomposition and nonlinear filtration, a complex physical and mathematical model of heat and mass transfer in anisotropic CMs is proposed, taking into account the connections of deformation and temperature fields, suitable for studying most CMs used as heat-shielding elements for modern flying vehicles (FV). A methodology has been developed for the numerical solution of the entire complex problem on the basis of economical absolutely stable numerical methods. Multiple results of numerical simulation of the thermal state of CMs under conditions of their thermal destruction at high temperatures have been obtained.
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