Dynamic heating of thermal control coatings under the influence of a temperature field

Аuthors

Viatlev A. P.

LLC «Center of optical glass», Khimki, Moscow region, Russia

e-mail: antonvyatlev@gmail.com

Abstract

The work is devoted to the study of dynamic heating of elements of thermal control coatings (TCC) under the influence of a temperature field. Solar reflector class TCC elements are mounted on the honeycomb panels of spacecraft heat exchangers and are integral parts of the passive thermal management system. The TCC elements have a multilayer structure and are plates with a substrate of transparent optical radiation-resistant glass with reflective, protective, and in some cases if necessary to protect the surface of the spacecraft and its devices from static electricity, electrically conductive coatings. The main task of the TCC elements is to protect the spacecraft from the excessive influence of electromagnetic solar radiation, simultaneously dissipate excess heat into the surrounding space, maintain the necessary thermal regime in a certain temperature range and, in the presence of an electrically conductive layer and an equipotential surface of the TCC element, discharge static energy. The TCC mainly operates in an airless environment free of matter – a vacuum, as a result of which, it can be concluded that there is no convective method of heat energy transfer. Based on this, the main methods of thermoregulation are achieved through the use of TCC with the necessary characteristics of solar radiation absorption As and the radiation coefficient (blackness) of the outer surfaces of the spacecraft and its components. In this paper, a thermal calculation of a sample of a TCC element is carried out, the temperature behavior of which is modeled by a thermally conductive three-layer element. The solution is based on the integral Laplace transform in time with subsequent reference using tables and properties of the Laplace transform and the convolution integral. As a result of the work done, the dependence of the temperature fields of the sample under study on time in various coordinates is presented, the temperature fields along the thickness of the package at various points in time are shown, the distribution of heat fluxes in time and coordinate is shown, and a comparative analysis with experimental data is performed.

Keywords:

thermal control coating, TCC, thermal management system, spacecraft, solar reflector, Laplace transform, dynamic heating

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