Multilayer structure composite high-temperature-resistant thermal protection material and preparation method thereof

A protective material and multi-layer structure technology, which is applied in the field of multi-layer structure composite high temperature resistant thermal protective material and its preparation, can solve the problem that the thermal protective material is difficult to meet the tight combination of multi-layer materials at the same time

Active Publication Date: 2020-08-28
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The invention provides a multi-layer structure composite high temperature resistant heat protection material and its preparation method to solve the problem that the existing...

Method used

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  • Multilayer structure composite high-temperature-resistant thermal protection material and preparation method thereof
  • Multilayer structure composite high-temperature-resistant thermal protection material and preparation method thereof
  • Multilayer structure composite high-temperature-resistant thermal protection material and preparation method thereof

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preparation example Construction

[0029] The preparation method of the high temperature resistant thermal protection material at least includes the following steps S110 to S140:

[0030] Step S110, using a high temperature resistant fiber preform as a core fiber preform, and needle-punching or puncturing a single-layer fiber cloth on one side of the core layer fiber preform.

[0031] In this step, the high temperature resistant fiber preform used is one or more of quartz fibers, basalt fibers, mullite fibers, aluminum silicate fibers, zirconia fibers, alumina fibers, carbon fibers, and silicon carbide fibers Composite fiber mat, board or woven prefabricated body.

[0032] Step S120, coating the ceramic precursor sol on the single-layer fiber cloth on the side of the sample in step S110, and pre-curing it, the pre-curing temperature is 20-300°C, and the time is 0.5-12h; The surface of the single-layer fiber cloth on the side where the ceramic precursor sol is coated is needle-punched or punctured to sew the mu...

Embodiment 1

[0040] The high-temperature-resistant fiber prefabricated body selected in this embodiment is alumina fiber, the puncture and acupuncture suture line is high-temperature quartz fiber thread, the fiber cloth is alumina fiber cloth, the ceramic precursor of the upper panel is alumina sol, and the core layer is injected The aerogel is made of silica aerogel, the supercritical medium is ethanol, and the resin injected into the lower panel is made of epoxy resin. The thickness of the ceramic matrix composite material layer of the upper panel is 2mm, the thickness of the heat insulation core layer of the airgel composite material layer is 20mm, and the thickness of the resin matrix composite material layer of the lower panel is 0.5mm. The specific operation steps are as follows:

[0041] (1) Puncture and sew a single layer of alumina fiber cloth on the upper surface of the alumina fiber preform, coat one side with alumina sol, and cure at 80° C. for 6 hours.

[0042] (2) After curi...

Embodiment 2

[0049] The high-temperature-resistant fiber prefabricated body selected in this embodiment is mullite fiber, the puncture and acupuncture suture line is carbon fiber thread, the fiber cloth is carbon fiber cloth, the ceramic precursor of the upper panel is silicon carbide precursor sol, and the core layer is injected The airgel is made of silica and alumina binary airgel, the supercritical medium is carbon dioxide, and the resin injected into the lower panel is Shuangma resin. The thickness of the ceramic matrix composite material layer of the upper panel is 5mm, the thickness of the heat insulation core layer of the airgel composite material layer is 28mm, and the thickness of the resin matrix composite material layer of the lower panel is 2mm.

[0050] (1) Needle punch the upper surface of the mullite fiber prefabricated body with a single-layer carbon fiber cloth, coat the silicon carbide precursor sol on one side, and cure at 150°C for 8 hours;

[0051] (2) After curing, t...

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Abstract

The invention relates to a multilayer structure composite high-temperature-resistant thermal protection material and a preparation method thereof. The preparation method comprises the following steps:adopting a high-temperature-resistant fiber prefabricated body as a core layer fiber prefabricated body, and sewing single-layer fiber cloth on the surface of one side of the core layer fiber prefabricated body in a needling or puncturing mode; coating the single-layer fiber cloth with ceramic precursor sol, and carrying out pre-curing; needling or puncturing the surface of the single-layer fibercloth coated with the ceramic precursor sol to sew multilayer fiber cloth, vacuumizing, and injecting a ceramic precursor on the multilayer fiber cloth; performing overall heat treatment on the obtained sample to obtain an upper panel of the ceramic-based composite material layer; performing vacuum assisted injection of aerogel precursor sol on the finished sample, and performing supercritical drying treatment to obtain a core layer of a heat-insulating aerogel composite material layer; and laying, needling or puncturing the lower surface of the aerogel composite material layer to sew a fiberreinforcement, injecting resin in a vacuum-assisted manner, then curing, and naturally cooling to obtain a lower panel of the resin-based composite material layer.

Description

technical field [0001] The invention relates to the technical field of protective materials, in particular to a high-temperature-resistant thermal protective material with a multilayer structure and a preparation method thereof. Background technique [0002] In the past 20 years, the world's aerospace powers have carried out a series of research work on the background of hypersonic space-to-ground shuttle systems, hypersonic missiles and hypersonic aircraft. Hypersonic technology will play an important strategic role in the future military, politics and economy, and has become a sharp weapon for countries to seize air and space superiority. As one of the key subsystems of hypersonic vehicles, the thermal protection system has become the focus of research in the field of hypersonic vehicles. The high-speed air flow around the aircraft will produce "aerodynamic heating" on the surface of the aircraft. The surface temperature of the aircraft will increase proportionally to the...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/58C04B35/565C04B35/10C04B41/89
CPCC04B35/10C04B35/565C04B35/58078C04B41/52C04B41/89C04B41/009C04B2235/5224C04B2235/5228C04B2235/656C04B2235/6567C04B2235/5248C04B2235/5244C04B2235/3826C04B2235/3813C04B35/803C04B35/806C04B41/5035C04B41/4535C04B41/5031C04B41/522C04B41/5059C04B41/488C04B41/4892
Inventor 田响宇韩银龙周粮邱海鹏陈明伟梁艳媛
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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