Spaceflight thermal protection material

Abstract

The invention belongs to the technical field of spaceflight, relates to a thermal protection material for an outer layer of a space orbit spacecraft, and aims to improve thermal protective performance of the material and reduce the material density. The fundamental principle of the material is as follows: in a space microgravity environment, gas is very weak in natural convection and heat conduction and has good heat insulation performance. The thermal protection material is formed by a metal coating film with a bubble structure, the fundamental structure is that a certain bubble structure is distributed on the surface of the metal coating film, and a certain type of gas with certain pressure is sealed in bubbles, which are shown in attached pictures. The spaceflight thermal protection material has the advantages of low density, high specific heat and good thermal protective performance.

Description

technical field [0001] The invention belongs to the field of spaceflight technology, and relates to a heat protection material used for orbital spacecraft such as satellites, spaceships and extravehicular spacesuits operating in space, in particular to a heat protection material for the outer surface of the spacecraft. Background technique [0002] At present, the thermal protection structure used on the outer surface of the spacecraft mostly adopts a laminated structure of plastic films with metal coatings (hereinafter referred to as metal coating films). , and vent holes are distributed on the film. The basic idea of ​​this structural design is to reduce radiation heat transfer by the metal coating of the film, reduce conduction heat transfer by the heat insulation mesh pad between the films, and the vent hole on the film is to accelerate the degassing between the multi-layer materials. The amount of interlayer gas is released to reduce convective heat transfer. However,...

AI Technical Summary

Problems solved by technology

However, in practical applications, due to the wrinkle of the metal coating film, and the influence of process factors such as perforation and heat insulation mesh pad, the surface radiation characteristics of the metal coating film change, and the barrier performance to heat radiation is reduced.

For the heat insulation mesh pad between multi-layer films, if the mesh is too loose, the direct contact between the films cannot be effectively cut off, so that the barrier effect on heat conduction will be deteriorated and the number of layers needs to be increased; and if the mesh is too dense It will reduce the insulation effect of the heat insulation mesh pad itself on heat conduction, and also directly lead to an increase in the overall mass of the laminated structure

In addition, in the orbital microgravity environment, the natural convective heat transfer of the gas is very weak, so the significance of reducing the convective heat transfer by drilling holes in the film to reduce the amount of interlayer gas is limited

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