Non-ablative heat protection/heat insulation/bearing integrated material and preparation method thereof

Abstract

The invention relates to the technical field of heat-proof / heat-insulation / bearing materials, and provides a non-ablative heat-proof / heat-insulation / bearing integrated material and a preparation method thereof, the non-ablative heat-proof / heat-insulation / bearing integrated material comprises a variable-density ceramic fiber reinforced skeleton and nano-porous ceramic filled in the variable-density ceramic fiber reinforced skeleton; and the variable-density ceramic fiber reinforced framework sequentially comprises an upper surface layer (1), a middle layer (2) and a lower surface layer (4), and all the layers form an integral structure through needling and sewing of ceramic fiber lines (3). The mass percent of the nano porous ceramic in the non-ablative heat protection / heat insulation / bearing integrated material is 35-65%; the volume density of the upper surface layer and the lower surface layer of the variable-density ceramic fiber reinforced framework is 0.50-1.0 g / cm < 3 >, and the thickness is 0.5-4 mm; and the volume density of the middle layer of the variable-density ceramic fiber reinforced framework is 0.10-0.30 g / cm < 3 >, and the thickness of the middle layer is 5-60 mm.

Description

technical field [0001] The present invention generally relates to the technical field of heat protection / heat insulation / carrying materials, and in particular to a preparation method of a non-ablative heat protection / heat insulation / carrying integrated material. Background technique [0002] Reusable high-speed aerospace vehicles and spacecraft, etc., need to fly at high speed in the atmosphere for many times for a long time, and the large area of ​​the body (ship) faces severe aerothermal and aerodynamic loads, and its surface temperature can reach 400~1500℃, which is Ensure that the internal equipment of the fuselage is at normal operating temperature (generally ≤80°C), precisely control its flight trajectory in the atmosphere, and if the performance of the material does not decrease after returning to the ground through the rainy environment, the large-area thermal protection system of the fuselage must adopt high A high-performance reusable heat-proof / insulation / load-bea...

AI Technical Summary

Problems solved by technology

Therefore, the preparation process of the core layer and the panel is relatively complicated and the cycle is very long, resulting in high manufacturing and use costs of the sandwich insulation structure

In addition, since the nanopore structure of the core airgel material will be destroyed by the huge surface tension of water after drying in water, the material will appear micron-scale cracks [Yang Hailong, Hu Zijun, Yang Jingxing, etc. The impact of the structure on the appearance. Journal of Composite Materials, 2019, 36(04): 964-971.], if the aircraft encounters a rainy environment when it returns, it will be difficult for the heat-resistant structure to be reusable

[0008] Therefore, the existing high-temperature-resistant and heat-insulating integrated materials have problems such as complex preparation process, long cycle, high cost, and difficulty in reusability after drying in the rain. Low thermal conductivity and high strength performance, it is difficult to meet the requirements of reusable high-speed aerospace vehicles, spacecraft, etc.

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