Screen-Vacuum Thermal Insulation of Orbital Spacecraft

Screen-Vacuum Thermal Insulation (SVTI) is a widely used and reliable passive thermal control method for spacecraft. Its primary purpose is to design, manufacture, and test screen-vacuum thermal insulation for orbital spacecraft, provide thermal protection for landing descent capsules and devices, and offer protection against micrometeorites and space debris. The use of SVTI significantly reduces the heat transfer rate between the structural elements and equipment of a spacecraft and its environment, thereby minimizing the heat flux from the sun. The SVTI system typically consists of outer and inner facing layers, with screens positioned between them. These screens have a single-sided metallized surface and are separated by low-heat-conducting material separators. The metallized surface of the screens is oriented towards the inner facing layer, while their non-metallic surface is designed with a ratio of solar radiation absorption coefficient to blackness degree not exceeding 0.55. The product has flight qualification and can be adapted to customer requirements.