Ablation-resistant lightweight heatproof integrated composite material with thermal insulation function and preparation method thereof

A composite material and ablation-resistant technology, which is applied in chemical instruments and methods, aerospace vehicle heat protection devices, synthetic resin layered products, etc., can solve the problems of short service life, heat insulation and heat-resistant materials that are not resistant to ablation, etc. , to achieve the effect of avoiding the bonding process, excellent ablation resistance, and short preparation cycle

Active Publication Date: 2019-07-05
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The technical problem to be solved by the present invention is to provide an ablation-resistant lightweight heat-proof and heat-insulating integrated composite mater

Method used

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  • Ablation-resistant lightweight heatproof integrated composite material with thermal insulation function and preparation method thereof
  • Ablation-resistant lightweight heatproof integrated composite material with thermal insulation function and preparation method thereof
  • Ablation-resistant lightweight heatproof integrated composite material with thermal insulation function and preparation method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0040] An ablation-resistant, lightweight, heat-proof and heat-insulating integrated composite material, the middle layer of the composite material is formed by using chopped high-silica fibers as reinforcement, phenolic resin as resin, and glass microbeads as low-density filler, and a surface layer is formed. With high silica fiber cloth as reinforcement, with B 4 C powder, montmorillonite powder and silicon carbide powder are the surface layer ceramic fillers.

[0041] The preparation of the ablation-resistant lightweight heat-proof and heat-insulation integrated composite material includes the following steps:

[0042] (1) Put B 4 C powder and SiC powder were dispersed in a NaOH aqueous solution with a NaOH content of 10wt.% for 1 h, then filtered and washed with distilled water or deionized water until the filtrate was neutral, and dried at 150°C for later use; the montmorillonite powder was dispersed in anhydrous ethanol 2% by mass of powder was added as a surface modif...

Embodiment 2

[0054] An ablation-resistant, lightweight, heat-proof and heat-insulating integrated composite material, the middle layer of the composite material is reinforced with chopped quartz fiber, phenolic cyanate is used as resin, glass microbeads are used as low-density filler, and the surface The layer is reinforced with quartz fiber cloth, with B 4 C powder, glass powder, kaolin and silicon carbide powder are ceramic fillers.

[0055] The preparation method of the above-mentioned ablation-resistant lightweight heat-proof and heat-insulation integrated composite material comprises the following steps:

[0056] (1) Put B 4 C powder and SiC powder were dispersed in NaOH aqueous solution with NaOH content of 10wt.% and treated for 1h, then filtered with distilled water or deionized water until the filtrate was neutral, and dried at 150℃ for later use; the glass powder and kaolin were dispersed in absolute ethanol 2% by mass of powder was added as a surface modifier, suction filtrati...

Embodiment 3

[0068] An ablation-resistant, lightweight, heat-proof and heat-insulating integrated composite material, the middle layer of the composite material is reinforced with chopped mullite fiber, phenolic resin is used as resin, and ceramic microbeads are used as low-density filler; Alumina fiber cloth as reinforcement, MoSi 2 Powder, mica, feldspar and silicon carbide powder are ceramic fillers for the surface layer.

[0069] The preparation method of the above-mentioned ablation-resistant lightweight heat-proof and heat-insulation integrated composite material comprises the following steps:

[0070] (1) MoSi 2 The powder and SiC powder were dispersed in NaOH Hanling 10wt.% NaOH aqueous solution for 1 h, washed with distilled water or deionized water by suction filtration until the filtrate was neutral, and dried at 150°C for use; mica and feldspar powder were dispersed in anhydrous ethanol 2% by mass of powder was added as a surface modifier, suction filtration after 1 h, and dr...

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Abstract

Provided is an ablation-resistant lightweight integrated composite material with a thermal insulation function. The composite material is of a sandwich structure, the middle layer adopts a chopped fiber as a reinforcing body, phenolic resin as a substrate and hollow microbeads as thermal insulation fillers, upper and lower surface layers are bonded to each other by a fiber cloth pre-impregnation material, and the three layers are cured to improve the bearing capacity and the anti-scouring capacity. The preparation method of the composite material comprises eight steps including ceramic powdertreatment, pretreatment of the chopped fiber and a fiber cloth, mixing, drying, slurry preparation, brushing or impregnation, mold filling, curing formation and demolding. The composite material can be applied to the ablation working condition of medium and low heat flux density; the composite material is formed at one time, so that the preparation cycle is short, and the cost is low; a stable ablation-resistant ceramic layer can be formed on the surface in a temperature range from 800 DEG C to 1,300 DEG C, and meanwhile, low-density fillers such as the hollow microspheres achieve a thermal insulation function. In this way, the integrated thermal insulation function under the conditions of medium and low heat flux density and oxidation is achieved.

Description

technical field [0001] The invention generally belongs to the technical field of aircraft thermal protection, and in particular relates to an ablation-resistant lightweight heat-proof and heat-insulation integrated composite material and a preparation method thereof. Background technique [0002] The integrated lightweight thermal protection material is a key technology for spacecraft represented by space maneuvering vehicles to achieve miniaturization, high payload ratio, and rapid entry and exit into space, which determines the advancement, reliability and economy of spacecraft. sex. With the development of new spacecraft in my country, there is an urgent need for lightweight thermal protection materials with integrated functions of heat and heat insulation. [0003] In 1976, 1996 and 2004, NASA's Mars "Viking", "Pioneer" and "Exploration Rover" successfully landed on Mars respectively. The windward side of the detectors above are all made of SLA-561V honeycomb reinforce...

Claims

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Application Information

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IPC IPC(8): B32B9/00B32B9/04B32B27/42B32B27/20B32B27/04B32B37/06B32B37/10B32B38/08B32B38/00B64G1/58
CPCB32B5/02B32B27/12B32B27/20B32B27/42B32B37/06B32B37/10B32B38/00B32B38/08B32B2038/0076B32B2255/02B32B2255/26B32B2260/023B32B2260/046B32B2307/304B32B2307/3065B32B2307/718B64G1/58
Inventor 陈思安胡海峰陈志华
Owner NAT UNIV OF DEFENSE TECH
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