A carbon-based lightweight thermal protection material and its preparation method and application

Abstract

The invention relates to a carbon-based lightweight thermal protection material as well as a preparation method and an application thereof. Carbon fiber rigid thermal insulation tiles are taken as a matrix of the thermal protection material, phenolic aerogel and boron-containing phenolic resin dense layer composition are subjected to gradient compositing in pores of the matrix, and a boron-containing phenolic resin dense layer is formed by the boron-containing phenolic resin dense layer composition on the high temperature surface of the rigid thermal insulation tile matrix. The invention provides the preparation method of the thermal protection material. The preparation method mainly comprises the following steps: preparing the carbon fiber rigid thermal insulation tile matrix, coating the carbon fiber rigid thermal insulation tile matrix with a precursor of the boron-containing phenolic resin dense layer composition, performing impregnation with a phenolic aerogel precursor, and then performing ageing, solvent replacement and supercritical drying to obtain the carbon-based lightweight thermal protection material. The prepared material has the characteristics of low density, low ablation rate, low thermal conductivity, high emissivity, good thermal insulation effect, excellent anti-airflow scouring performance and the like, and has important application value in thermal protection materials on outer surfaces of an aircraft.

Description

technical field [0001] The invention relates to the technical field of functional composite materials, in particular to a carbon-based lightweight thermal protection material and its preparation method and application. Background technique [0002] When an interplanetary vehicle such as a Mars probe enters the atmosphere of an extraterrestrial planet at high speed and re-enters the Earth's atmosphere from outer space, it will generate severe aerodynamic heating due to its extremely fast speed. Therefore, thermal protection measures must be implemented on the outer surface of the vehicle. The weight of the aircraft determines the thrust requirements of the required launch vehicle, which in turn determines the feasibility of the project. Therefore, reducing the weight of the thermal protection system on the outer surface of the interplanetary exploration vehicle is very critical to the realization of the project. [0003] Early high-density ablative thermal protection materia...

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Problems solved by technology

However, these materials only use ordinary phenolic resin as the filling phase, which has high thermal conductivity, and ordinary phenolic resin will burn in a high-temperature air atmosphere at 1200°C, resulting in low oxidation resistance, insufficient temperature resistance, and fast ablation rate. In addition, the anti-airflow erosion performance of these materials is not excellent enough, and the surface emissivity is low, which cannot effectively suppress the temperature rise of the aircraft surface due to radiation (see Chinese patent CN201611100591)

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