Preparation method of thermal-protection ablative material

A technology of ablation material and heat protection, which is applied in the field of preparation of heat protection materials, can solve the problems of high density of heat protection ablation materials, achieve the goal of improving bonding performance, high surface strength, improving ablation performance and heat insulation performance Effect

Inactive Publication Date: 2013-05-08
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The present invention aims to solve the technical problem of high density of the existing carbonized heat protecti

Method used

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  • Preparation method of thermal-protection ablative material
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  • Preparation method of thermal-protection ablative material

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specific Embodiment approach 1

[0020] Specific embodiment 1: The preparation method of a kind of thermal protection ablation material of this embodiment is carried out according to the following steps:

[0021] 1. First weigh 30% to 60% of boron phenolic resin and 40% to 70% of microsphere filler according to mass percentage, and then weigh carbon nanotubes according to 1% to 20% of the total mass of boron phenolic resin and microsphere filler , then weigh the chopped carbon fiber by 1 to 3% of the total mass of the boron phenolic resin and the microsphere filler; then weigh the coupling agent by 0.5% to 2% of the total mass of the boron phenolic resin and the microsphere filler;

[0022] 2. Submerge the chopped carbon fiber weighed in step 1 in acetone for 12-20 hours, rinse it with distilled water and dry it, then immerse the chopped carbon fiber in concentrated nitric acid with a concentration of 68% for 2-3 hours, and then Rinse with distilled water and dry, and finally immerse the chopped carbon fiber ...

specific Embodiment approach 2

[0028] Embodiment 2: This embodiment differs from Embodiment 1 in that the boron phenolic resin pyrolysis carbon residue rate in step 1 is ≥ 70%. Others are the same as the first embodiment.

specific Embodiment approach 3

[0029] Specific embodiment three: the difference between this embodiment and specific embodiment one is that the boron phenolic resin pyrolysis char residue rate in step one is 75%. Others are the same as the first embodiment.

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Abstract

The invention relates to a preparation method of a thermal-protection ablative material, and relates to a preparation method of a thermal-protection material. The invention aims at solving a technical problem of high density of a carbonized-type lightweight ablative material with phenolic resin as a substrate. According to the method, boron phenolic resin is prepared into a boron phenolic resin acetone solution; chopped carbon fiber is cleaned and oxidized, and is processed by using a coupling agent; a uniform mixture of a micro-spherical filling material, carbon nano-tubes, and the chopped carbon fiber are added into the boron phenolic resin solution, and the mixture is uniformly mixed; acetone is evaporated by standing, such that a mixed paste is obtained; a phenolic honeycomb cut into a mold inner cavity shape is placed into the mold; the mixed paste is filled into the phenolic honeycomb, such that a composite blank is obtained; and the composite blank is cured and shaped, such that the thermal-protection ablative material is obtained. The material has a low density of 0.2-0.4g/cm<3>, a linear ablation rate of 0.033-0.035mm/s, and a mass ablation rate of 0.0167-0.0187g/s. The material is suitable to be used as a space vehicle thermal-protection material.

Description

technical field [0001] The invention relates to a method for preparing a thermal protection material. Background technique [0002] When a spacecraft rushes out of the atmosphere at hypersonic speed and returns to the ground to re-enter the atmosphere, its surface temperature can reach several thousand degrees under aerodynamic heating, so it is necessary to provide thermal protection for the spacecraft to reduce its surface temperature and protect its internal structure . Thermal protection methods are mainly divided into ablation method, endothermic method and radiation method. Among them, the ablation method is widely used in spacecraft thermal protection structures due to its advantages of high heat protection efficiency, reliable operation, and strong ability to adapt to flow field changes. The ablation method is an active heat protection method that consumes heat through reactions such as sublimation, melting, and carbonization of surface ablation materials at high t...

Claims

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Application Information

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IPC IPC(8): C08L61/06C08L61/14C08K13/06C08K9/06C08K9/02C08K7/06C08K7/00C08K3/04C08K7/28B29C35/02
Inventor 吴晓宏秦伟彭得群陆小龙
Owner HARBIN INST OF TECH
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