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Light ablation-resistant thermal insulation integrated structure

An ablative, lightweight technology

Inactive Publication Date: 2019-03-08
SUZHOU HONGJIU AVIATION THERMAL MATERIALS TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0009] For example, the above-mentioned patents all disclose technical products related to this field, but in the actual production and use process, there are problems such as poor surface ablation resistance, poor high-temperature heat insulation performance, low structural strength, and high density. Limit its application in certain fields

Method used

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Effect test

Embodiment

[0017] A light-weight ablation-resistant and heat-insulating integrated structure, which is composed of an ablation-resistant coating, a high-strength panel, a hollow fabric, and nano-airgel. The thermal conductivity of the integrated structure at room temperature is 0.024 W / m·K, The thermal conductivity at 2000°C is 0.09W / m·K, characterized in that the ablation-resistant coating is ZrB 2 -MoSi 2 The composite coating is prepared on the surface of the high-strength panel by atmospheric plasma spraying technology; the high-strength panel is a carbon fiber-reinforced porous phenolic composite material, which is formed by impregnating the surface layer of a hollow fabric with a porous phenolic resin and pyrolyzing at a high temperature, wherein the carbon fiber volume ratio is 40%; the hollow fabric is a carbon fiber three-dimensional hollow prefabricated body, the high-strength panel and the carbon fiber skeleton form an I-shaped structure, and the carbon fiber groups are arrang...

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PUM

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Abstract

The invention discloses a light ablation-resistant thermal insulation integrated structure. The structure consists of an ablation-resistant coating, a high-strength panel, hollow fabric and nano aerogel, wherein the ablation-resistant coating is a ZrB2-MoSi2 composite coating and prepared on the surface of the high-strength panel with an atmospheric plasma spraying technology; the high-strength panel is a carbon fiber reinforced porous phenolic composite and formed by dipping the surface layer of the hollow fabric by porous phenolic resin and high-temperature pyrolysis; the hollow fabric is acarbon fiber 3D hollow preform, carbon fiber is woven in a 3D orthographic manner, the high-strength panel and a carbon fiber framework form an I-shaped structure, and carbon fiber groups are arrangedin parallel; the nano aerogel is hollow carbon aerogel spheres and realizes region filling in pores of the hollow fabric. The thermal insulation integrated structure can realize abalation shape maintenance in a high-temperature pneumatic environment, is light and high in strength and meets the requirement of ultrahigh sound velocity aircrafts for thermal insulation protection materials.

Description

technical field [0001] The invention relates to a heat-insulating integrated structure, in particular to a light-weight, ablation-resistant, heat-insulated integrated structure applied in aerospace. Background technique [0002] Hypersonic aircraft is regarded as another milestone in the history of aviation after the invention of aircraft, breaking through the sound barrier, and entering space. Major countries in the world have always regarded it as the forefront of aviation technology and given full support. The United States, Russia, France, Germany, Japan, India and other countries have successively made technological breakthroughs since the beginning of the new century, and have successively conducted ground and flight tests, which shows that hypersonic technology has entered the basic stage of concept and principle exploration. The advanced technology development stage with certain hypersonic vehicles as the application background, such as the X-51 hypersonic cruise mi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/83C04B35/52C04B35/64C04B41/85C04B38/08
CPCC04B35/524C04B35/64C04B35/83C04B38/085C04B41/5071C04B41/85C04B2235/50C04B41/507C04B41/4545
Inventor 叶信立其他发明人请求不公开姓名
Owner SUZHOU HONGJIU AVIATION THERMAL MATERIALS TECH CO LTD
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