Multilayer insulation (MLI) is widely used in a thermal control systems of a spacecraft because of its low thermal conductivity and mass. However a MLI blanket is not a rigid structure and its characteristic properties make thermal performance prediction difficult. Therefore an extensive thermal testing of the spacecraft is required to confirm the system efficiency, what causes increasing of a cost and a production time. One of these characteristic properties is a layer density variation in MLI blankets. This variation is a result of geometry of structure and imperfection processing. In this article a formulation of an improved MLI mathematical model is considered. This model is supposed to describe not theoretic but real multilayer insulation and take into account the influence of near-field radiative heat transfer on a heat flux between insulation layers. This type of heat transfer takes place in distances between bodies less than a characteristic wavelength of radiation and is a result of non-propagating electromagnetic waves interaction. It can be a cause of heat flux magnitude enhancement when a vacuum gap between layers decreases but current models do not take into account this changing of the radiative heat transfer nature. The new model consists of near-field radiative component dependent on vacuum gap width. The application of the presented model will allow analysing the heat flux between layers depending on a compressed multilayer insulation area size with better accuracy before thermal testing.
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