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Nanopore heat-proof composite material and bearing structure co-curing method

A composite material and curing molding technology, applied in the field of heat-resistant materials, can solve the problems of destroying the structural integrity of the heat-resistant structure and load-bearing structure, affecting the manufacturing accuracy of the heat-resistant structure, and reducing the load-bearing efficiency of the structure, so as to improve the interface load Efficiency, avoidance of stress accumulation and interface failure, synergistic improvement of thermal insulation performance and structural load-bearing performance

Active Publication Date: 2018-12-14
EAST CHINA UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, these molding processes may affect the manufacturing accuracy of the heat-resistant structure, as well as the stress accumulation between the heat-resistant layer and the bearing layer, which will lead to the problem of overall structural deformation control
The way of mechanical connection will destroy the structural integrity of the heat-proof structure and the load-bearing structure, causing local stress concentration problems and reducing the load-bearing efficiency of the structure

Method used

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  • Nanopore heat-proof composite material and bearing structure co-curing method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0038] The laying density in the inner mold is 0.5g / cm 3 The carbon fiber prefabricated body is closed, and the mold is vacuumed with a vacuum pump, and the vacuum degree in the mold is controlled to -0.05MPa. The epoxy resin is slowly injected into the mold with an injection pressure of 0.08MPa. The mold was cured in a blast oven at 120°C for 10 hours. Take out the mold and cool down to room temperature, open the outer mold, and use silicone rubber to make the density 0.15g / cm 3The quartz fiber mesh tire is bonded to the surface of the cured carbon fiber bearing structure, the mold is closed, the vacuum degree in the mold is controlled to reach -0.05MPa~-0.1MPa, and the mass fraction of 30% boron phenolic resin / isopropyl The alcohol solution is injected into the mould, and the injection pressure is 0.01MPa. After the air bubbles are exhausted, the mold is sealed and placed in a 120°C normal pressure blast oven. After aging for 10 hours, the sample is taken out of the mold a...

Embodiment 2

[0040] The laying density in the inner mold is 0.5g / cm 3 The carbon fiber prefabricated body is closed, and the mold is vacuumed with a vacuum pump, and the vacuum degree in the mold is controlled to -0.05MPa. The epoxy resin is slowly injected into the mold with an injection pressure of 0.08MPa. The mold was cured in a blast oven at 120°C for 10 hours. Take out the mold and cool down to room temperature, open the outer mold, and use silicone rubber to make the density 0.30g / cm 3 The glass fiber mesh tire is bonded on the surface of the cured carbon fiber bearing structure, the mold is closed, the vacuum degree in the mold is controlled to reach -0.05MPa~-0.1MPa, and the mass fraction of 25% of the organic silicon modified phenolic resin is used by the low pressure RTM process. / Isopropanol solution is injected into the mold with an injection pressure of 0.01MPa. After the air bubbles are exhausted, the mold is sealed and placed in a 120°C normal pressure blast oven. After ...

Embodiment 3

[0042] The laying density in the inner mold is 0.5g / cm 3 The carbon fiber prefabricated body is closed, and the mold is vacuumed with a vacuum pump, and the vacuum degree in the mold is controlled to -0.05MPa. The epoxy resin is slowly injected into the mold with an injection pressure of 0.08MPa. The mold was cured in a blast oven at 120°C for 10 hours. Take out the mold and cool down to room temperature, open the outer mold, and use silicone rubber to make the density 0.30g / cm 3 The high-silica fiber is bonded to the surface of the cured carbon fiber bearing structure, the mold is closed, the vacuum degree in the mold is controlled to reach -0.05MPa~-0.1MPa, and the mass fraction of 35% silicone modified phenolic resin is / Isopropanol solution is injected into the mold with an injection pressure of 0.01MPa. After the air bubbles are exhausted, the mold is sealed and placed in a 120°C normal pressure blast oven. After aging for 10 hours, the sample is taken out of the mold ...

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Abstract

The invention relates to a nanopore heat-proof composite material and bearing structure co-curing method. The method comprises the following steps: taking a bearing layer and a heat-proof layer of a nanopore structure as raw materials, performing low-pressure RTM impregnation, medium / low-temperature curing and normal pressure drying, thereby obtaining the fiber-reinforced heat-insulating materialof the nano-porous structure. The bearing / heat-insulating / heat-proof integrated structure prepared by the method has the advantages of being short in preparation cycle, simple in preparation process,high in designability and machinability and the like, and can be widely applied to external thermal insulation layers of various tactical and strategic weapons in short-term operations, internal ablation insulation and heat prevention layers of engines, large area heat protection of disposable hypersonic flight vehicles, and the like.

Description

technical field [0001] The invention relates to the field of heat-resistant materials, in particular to a method for co-curing a nanoporous heat-resistant composite material and a load-bearing structure. Background technique [0002] At present, large-area low-density heat-resistant material systems at home and abroad mainly use honeycomb-reinforced low-density ablation materials, C / SiC cover plates, winding-formed ceramizable phenolic cover plates, SPQ ablation materials and other material systems. The bonding and hot-pressing forming process realizes the secondary bonding molding of the large-area heat-proof layer and the structural bearing. [0003] The preparation process of the large-area windward surface heat-resistant material of the American Apollo spacecraft is as follows: firstly, the honeycomb is bonded to the surface of the load-bearing structure, and then the ablation-resistant material is filled in the honeycomb cell structure, and after curing, the heat-resist...

Claims

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Application Information

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IPC IPC(8): B29C70/78B29C70/36
CPCB29C70/36B29C70/683B29C70/78
Inventor 龙东辉董金鑫姚鸿俊朱召贤罗艺
Owner EAST CHINA UNIV OF SCI & TECH