Screen-Vacuum Thermal Insulation of Orbital Spacecraft

Screen-vacuum thermal insulation (SVTI) is one of the most common and reliable means of passive thermal control in the system for ensuring the thermal regime of a spacecraft. The use of SVTI provides the opportunity to significantly reduce the heat transfer rate of the structural elements and equipment of the spacecraft with the environment, that is, to reduce the heat flux arriving to the structural elements and equipment of the spacecraft from the sun. Known screen-vacuum thermal insulation of the spacecraft thermal control system, containing the outer and inner facing layers and screens located between them with a single-sided metallized surface, separated from each other by separators of low-heat-conducting material, in which the screens are oriented with a metallized surface to the inner facing layer, and their non-metallic surface made with a ratio of the absorption coefficient of solar radiation to the degree of blackness of not more than 0.55.