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External thermal insulation composite material and preparation method thereof

The technology of composite material and prefabricated body is applied in the field of preparation of external thermal insulation composite material, which can solve the problems of increasing the complexity of the process, difficulty in controlling the profile precision, and increasing the cost, so as to reduce the punching and stitching process, shorten the preparation cycle, low cost effect

Inactive Publication Date: 2018-12-07
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the sandwich structure material involves three-layer lamination, sewing and other processes, which not only increases the complexity of the process, but also increases the cost, and there is a risk of easy delamination. In addition, because the surface cannot be machined, it is difficult to control the surface accuracy

Method used

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  • External thermal insulation composite material and preparation method thereof
  • External thermal insulation composite material and preparation method thereof
  • External thermal insulation composite material and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] Preparation of Example 1 External Thermal Insulation Composite Material

[0042] 1) The selected density is 0.70g / cm 3 , the mullite fiber felt with a thickness of 1mm is a high-density fiber felt, and the selected density is 0.10g / cm 3 , The quartz fiber felt with a thickness of 24mm is a low-density fiber felt.

[0043] 2) Firstly, methyltrimethoxysilane is used to hydrophobically treat the quartz fiber mat, and then the quartz fiber mat and mullite fiber mat are prepared into a high-temperature-resistant fiber preform with an integral density gradient by needle punching. The needle punching density is 15 stitches / cm 2 .

[0044] 3) Place the prefabricated body in a closed container, impregnate the composite mullite fiber mat with the silica sol by vacuum impregnation, repeat the impregnation 9 times, and then perform high temperature treatment to remove organic matter.

Embodiment 2

[0045] Embodiment 2 Preparation of external thermal insulation composite material

[0046] 1) The selected density is 0.70g / cm 3 , the mullite fiber felt with a thickness of 1mm is a high-density fiber felt, and the selected density is 0.10g / cm 3 , The quartz fiber felt with a thickness of 24mm is a low-density fiber felt.

[0047] 2) First, use methylphenyl silicone resin solution to hydrophobically treat the quartz fiber mat, and then prepare the quartz fiber mat and mullite fiber mat by needling to form an integral high-temperature-resistant fiber preform with a density gradient. 15 stitches / cm 2 .

[0048] 3) Place the prefabricated body in a closed container, impregnate the composite mullite fiber mat with the silica sol by vacuum impregnation, repeat the impregnation 9 times, and then perform high temperature treatment to remove organic matter.

Embodiment 3

[0049] Embodiment 3 Preparation of external thermal insulation composite material

[0050] 1) The selected density is 0.70g / cm 3 , the silicon carbide fiber felt with a thickness of 1mm is a high-density fiber felt, and the selected density is 0.10g / cm 3 , The mullite fiber felt with a thickness of 24mm is a low-density fiber felt.

[0051] 2) First, use methyltrimethoxysilane to hydrophobically treat the mullite fiber mat, and then prepare the mullite fiber mat and the silicon carbide fiber mat by needling to form an integral high-temperature-resistant fiber preform with a density gradient. Puncture density is 15 needles / cm 2 .

[0052] 3) Place the prefabricated body in a closed container, impregnate the composite mullite fiber mat with the mullite sol by vacuum impregnation, repeat the impregnation 9 times, and then perform high temperature treatment to remove organic matter.

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Abstract

The invention relates to a preparation method of an external thermal insulation composite material, comprising the following steps: (1) performing a hydrophobic treatment on a hydrophilic first reinforcement to obtain a hydrophobic first reinforcement; (2) connecting the hydrophobic first reinforcement and a hydrophilic second reinforcement to obtain a preform; and (3) impregnating the part of thepreform including at least the second reinforcement with a hydrophilic impregnant used for impregnation, and then drying to obtain the external thermal insulation composite material. The invention also relates to an external thermal insulation composite material prepared by the above preparation method. The an anti-scouring aerogel composite material prepared from the external thermal insulationcomposite material can be used for profile machining to obtain a component of a desired profile, or the overall external profile machining is carried out after assembling of an aircraft, so as to accurately ensure aerodynamic shape of the aircraft.

Description

technical field [0001] The invention relates to a preparation method of an external thermal insulation composite material, and also relates to an external thermal insulation composite material prepared by the preparation method. Background technique [0002] The aerodynamic friction between the surface of the thermal protection system of the hypersonic aircraft and the air on the way to and from the atmosphere or the sky produces high temperature and aerodynamic pressure. Currently, the thermal protection materials that can withstand are rigid heat insulation tiles and ablation materials. [0003] Ablation material is a heat protection method widely used in re-entry vehicles at present. It mainly uses the heat absorption of ablation material cracking and gas diffusion to take away heat to achieve the purpose of heat protection, but it has high density, poor heat insulation performance and linear ablation. Very obvious shortcomings. [0004] Rigid ceramic tiles are the main ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/14C04B35/185C04B35/622
CPCC04B35/14C04B35/185C04B35/622C04B2235/5228C04B2235/5232C04B2235/6567C04B2235/656C04B2235/77C04B2235/9607C04B2235/96
Inventor 苏力军裴雨辰李文静张丽鹃宋寒杨洁颖
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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