Carbon-based lightweight thermal protection material as well as preparation method and application thereof

A thermal protection material and a lightweight technology, applied in the field of carbon-based lightweight thermal protection materials and their preparation, can solve the problems that the temperature rise of the aircraft cannot be effectively suppressed, the anti-airflow erosion performance is not excellent enough, the surface emissivity is low, etc. Excellent anti-airflow erosion performance, good thermal insulation effect and low thermal conductivity

Active Publication Date: 2017-11-10
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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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

Method used

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  • Carbon-based lightweight thermal protection material as well as preparation method and application thereof
  • Carbon-based lightweight thermal protection material as well as preparation method and application thereof
  • Carbon-based lightweight thermal protection material as well as preparation method and application thereof

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preparation example Construction

[0033] The process flow chart of the preparation method of the carbon-based lightweight thermal protection material provided by the present invention in the second aspect is as follows figure 1 Shown, specifically, described method comprises the following steps:

[0034] (1) Preparation of carbon fiber rigid insulation tile matrix:

[0035] Mix chopped carbon fiber, phenolic resin prepolymer and acetone and stir evenly, filter, put the filter cake in a mold to form a green body, and the green body is sequentially subjected to gradient temperature rise, drying and curing, high temperature cracking and heat treatment to produce Obtain carbon fiber rigid insulation tile matrix. Specifically, chopped carbon fibers with a diameter of 14 to 16 microns (such as 14, 15 or 16 microns) and a length of 1 to 2 millimeters (such as 1, 1.5 or 2 millimeters), phenolic resin prepolymer and acetone according to (100 ~120): (10~15): (20000~25000) (for example, 100:10:20000, 100:10:22000, 100:...

Embodiment 1

[0042] First, add 100g of chopped carbon fiber with a diameter of 15 microns and a length of 1.5mm, 10g of phenolic resin prepolymer and 20kg of acetone into the mixing tank, stir for 1-2 hours to disperse evenly, filter, and place the filter cake in a mold for molding To obtain the green body, place the green body in a drying and curing machine, heat it at 120°C for 2 hours, at 140°C for 2 hours, at 160°C for 2 hours, and at 180°C for 2 hours to complete the gradient temperature rise drying and curing. Then heat up to 900°C in an argon-protected atmosphere furnace for cracking for 2 hours, heat up to 1800°C in an argon-protected atmosphere furnace and then heat-treat for 30 minutes to obtain a carbon fiber rigid heat-insulating tile. Then, get boron phenolic resin prepolymer 100g, borosilicate glass powder 5g, boron carbide 1g, silicon tetraboride 1g, molybdenum disilicide 2g and ethanol 200g mix uniformly, obtain boron phenolic resin compact layer composition precursor, boron...

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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...

Claims

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Application Information

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IPC IPC(8): C04B41/89C04B35/83C04B35/622C08G8/08
Inventor 鲁胜刘圆圆李文静刘斌赵英民
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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