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Preparation method of light ablative material

A kind of ablation material, light weight technology, applied in the field of preparation of heat protection materials, can solve the problem of high density, achieve the effect of high surface strength, improve bonding performance, and improve the overall mechanical properties

Active Publication Date: 2013-05-15
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention aims to solve the technical problem of high density of the existing carbonized light-weight ablation material based on phenolic resin, and proposes a light-weight ablation material and its preparation method

Method used

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  • Preparation method of light ablative material
  • Preparation method of light ablative material

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specific Embodiment approach 1

[0017] Embodiment 1: The preparation method of a kind of lightweight ablation material of this embodiment is carried out according to the following steps:

[0018] 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 , and then weigh the coupling agent according to 0.5% to 2% of the total mass of boron phenolic resin and microsphere filler;

[0019] Two, the boron phenolic resin that step 1 takes is dissolved in acetone, obtains boron phenolic resin solution;

[0020] 3. First mix the microsphere filler and carbon nanotubes weighed in step 1 evenly, add them to the boron phenolic resin solution prepared in step 2, and disperse evenly by ultrasonic, then add the coupling agent weighed in step 1, and disperse evenly by ultrasonic , to obtain a mixed solution; then leave the mixed solution to volat...

specific Embodiment approach 2

[0024] 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

[0025] 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 discloses a preparation method of a light ablative material, relates to a preparation method of a thermal protection material, and is aimed at solving the technical problem of high density of the existing carbonization type light ablative material taking phenol-formaldehyde resin as a substrate. The method comprises the following steps of: dissolving boron phenol-formaldehyde resin in acetone to prepare a boron phenol-formaldehyde resin solution; adding the uniformly mixed microsphere filler and carbon nanotube into the boron phenol-formaldehyde resin solution, and mixing uniformly; standing to volatize acetone to obtain mixed paste; putting the phenol-formaldehyde honeycomb cut into a die inner cavity shape into a die, and filling the mixed paste into the phenol-formaldehyde honeycomb to obtain a composite green body; and curing and forming the composite green body to obtain the light ablative material. Through the invention, the density of the prepared light ablative material is as low as 0.2-0.4g / cm<3>, the linear ablativity is 0.035-0.115mm / s, and the mass ablativity is 0.0177-0.0216g / s; and the light ablative material can be used as a thermal protection material of a spacecraft.

Description

technical field [0001] The invention relates to a preparation method of 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 ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C08L61/14C08K7/28C08K7/00C08K3/04
Inventor 吴晓宏秦伟彭得群陆小龙
Owner HARBIN INST OF TECH
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