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In-situ formation method for interface matching of heat insulating material and metal cabin section

A technology of in-situ forming and heat insulation materials, which is applied to household components, household appliances, and other household appliances. It can solve problems such as poor bonding effect and unqualified bonding quality of product batches, and achieves simple operation and simple method. , the effect of a wide range of application prospects

Inactive Publication Date: 2019-11-29
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the forming stage, metal cabin sections and thermal insulation composite components are prone to poor bonding effects, resulting in unqualified bonding quality of product batches

Method used

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  • In-situ formation method for interface matching of heat insulating material and metal cabin section

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0054] (1) Perform sandblasting on the outer wall of the cabin section to be formed, with a sandblasting pressure of 0.4MPa and a grit number of 30. The roughness of the outer wall of the cabin section after sandblasting is improved, which can enhance the interface bonding effect in the subsequent steps.

[0055] (2) Use interface treatment materials to perform interface treatment on the exterior of the preformed cabin section after step (1). The interface treatment materials are silicone rubber KH-CL-RTV-2 + aramid felt, and the thickness of the interface material is 1.5 mm. The interface treatment is: spread the interface treatment material on the outer wall of the cabin, and the silicone rubber can function as an adhesive, and the aramid felt can be bonded to the outer wall of the cabin.

[0056] (3) Put the heat-insulating material fiber preform on the section to be formed, and locate the end surface and profile characteristics during the assembly process.

[0057] (4) Assemble...

Embodiment 2

[0059] (1) Polish the outer wall of the cabin section to be formed, and the roughness of the outer wall of the cabin section after sanding can be improved, which can enhance the interface bonding effect in the subsequent steps.

[0060] (2) Use the interface treatment material to perform interface treatment on the outside of the preformed cabin section processed in step (1). The interface treatment material is an elastic resin film J261 with a thickness of 0.3 mm. The interface treatment is: spreading an elastic resin film on the outer wall of the cabin.

[0061] (3) Put the heat-insulating material fiber preform on the section to be formed, and locate the end face and profile feature during the assembly process.

[0062] (4) Assemble the cabin body with the fiber preform and the cover plate part at one end of the forming mold in place through a stop / pin hole fitting form, and then assemble the annular female mold part of the forming mold and the cover plate part in place, and finall...

Embodiment 3

[0064] (1) Polish the outer wall of the cabin section to be formed, and the roughness of the outer wall of the cabin section after sanding is improved, which can enhance the interface bonding effect in the subsequent steps.

[0065] (2) Use the interface treatment material to perform interface treatment on the outside of the preformed cabin section processed in step (1). The interface treatment material is silicone rubber RTV-400+quartz felt, and the thickness of the interface material is 1 mm. The interface treatment is: spread the interface treatment material on the outer wall of the cabin, and the silicone rubber can function as an adhesive, and the quartz felt can be bonded to the outer wall of the cabin.

[0066] (3) Put the heat-insulating material fiber preform on the section to be formed, and locate the end surface and profile characteristics during the assembly process.

[0067] (4) Assemble the cabin body with the fiber preform and the cover plate part at one end of the for...

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Abstract

The invention relates to an in-situ formation method for interface matching of a heat insulating material and a metal cabin section. The in-situ formation method comprises the following steps of: (1)a surface roughening treatment step, namely carrying out surface roughening treatment on the outside of a to-be-formed cabin section; (2) an interface treatment step, namely carrying out interface treatment on the outside of the to-be-formed cabin section which is treated in the step (1) by using an interface treatment material, wherein the interface treatment material comprises a composite material or an elastic resin rubber film which is formed by compounding a silicon rubber adhesive and a flexible thin felt, and the thickness of the interface material is 0.1 mm to 2 mm; (3) a compounding step; and (4) a formation step. According to the in-situ formation method, the type of the interface material and the thickness of the interface material are optimized so that the heat insulating composite material can completely cover the surface of the to-be-protected cabin section, and the problems existing in interface matching of the heat insulating material and a metal cabin wall are solved.

Description

Technical field [0001] The present invention relates to the technical field of thermal insulation materials, in particular to an in-situ molding method for matching the interface between thermal insulation materials and metal cabin sections. Background technique [0002] As the cruise speed of supersonic aircraft in the atmosphere increases and the cruise time is prolonged, the aircraft has to withstand more severe air and thermal loads, and the surface temperature exceeds the bearing limit of the metal cabin. In order to ensure the integrity of the aircraft's appearance and structure and the normal operation of internal components, it is necessary to use external heat-proof and heat-insulating materials that have both temperature resistance and heat insulation and load-bearing functions. In the traditional way, the insulation material components are prepared in pieces, and then they are attached to the outside of the aircraft cabin one by one. Each component needs to be aligned ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C45/14B29L31/30
CPCB29C45/14467B29C45/14786B29C2045/14868B29L2031/3076
Inventor 宋寒郭慧孙阔刘圆圆徐春晓刘韬李文静赵英民裴雨辰
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH