Resin-based composite material thermo-oxidative aging prevention structure and preparation method thereof

A composite material and resin-based technology, which is applied in the field of resin-based composite material anti-thermal and oxidative aging structure and its preparation, can solve the problems of resin-based materials such as easy oxidation, decreased mechanical properties, and low service life, so as to reduce the aging rate and porosity. The effect of low efficiency and saving manufacturing cost

Active Publication Date: 2021-09-21
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to solve the technical problems of easy oxidation, low service life, rapid decline in mechanical properties and high thermal weight loss of resin-based materials in high-temperature environments

Method used

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  • Resin-based composite material thermo-oxidative aging prevention structure and preparation method thereof
  • Resin-based composite material thermo-oxidative aging prevention structure and preparation method thereof
  • Resin-based composite material thermo-oxidative aging prevention structure and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0050] Embodiment 1 provides that the resin-based composite material provided by the present invention is a flat plate structure, including a resin-based composite material and a thermal-oxidative aging-resistant film layer; the resin-based composite material and the thermal-oxidative aging-resistant film layer both have The bonding surface, the bonding surface of the heat-oxidative aging-resistant film layer and the bonding surface of the resin-based composite material are bonded and cured as one; the heat-oxidative aging-resistant mold layer is a polyimide film layer; the heat-resistant The bonding surface of the oxygen aging film layer is roughened.

[0051] The thickness of the polyimide film layer is 50 microns.

[0052] The elongation at break of the polyimide film was 80%.

[0053] The tensile strength of the polyimide film is 240MPa.

[0054] The 5% weight loss temperature of the polyimide film in nitrogen is 590°C. The roughening treatment is supercritical CO 2 Sp...

Embodiment 2

[0082] Embodiment 2 provides that the resin-based composite material provided by the present invention is a flat plate structure, including a resin-based composite material and a thermal-oxidative aging-resistant film layer; the resin-based composite material and the thermal-oxidative aging-resistant film layer both have The joint surface, the joint surface of the heat-oxidative aging-resistant film layer and the joint surface of the resin-based composite material are bonded and cured as one; the heat-oxidative aging-resistant mold layer is a polyimide film layer; the heat-resistant The bonding surface of the oxygen aging film layer is roughened.

[0083] The thickness of the polyimide film layer is 50 microns.

[0084] The elongation at break of the polyimide film was 80%.

[0085] The tensile strength of the polyimide film is 240MPa.

[0086] The 5% weight loss temperature of the polyimide film in nitrogen is 590°C.

[0087] The roughening treatment is supercritical CO 2...

Embodiment 3

[0106] Embodiment 3, the resin-based composite material anti-thermal oxygen aging structure provided by the present invention is a ring structure, including the resin-based composite material and the thermal-oxidative aging-resistant film layer; the resin-based composite material and the thermal-oxidative aging resistant film layer both have The joint surface, the joint surface of the heat-oxidative aging-resistant film layer and the joint surface of the resin-based composite material are bonded and cured as one; the heat-oxidative aging-resistant mold layer is a polyimide film layer; the heat-resistant The bonding surface of the oxygen aging film layer is roughened.

[0107] The thickness of the polyimide film layer is 50 microns.

[0108] The elongation at break of the polyimide film was 80%.

[0109] The tensile strength of the polyimide film is 240MPa.

[0110] The 5% weight loss temperature of the polyimide film in nitrogen is 590°C.

[0111] The roughening treatment i...

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Abstract

The invention relates to a resin-based composite material thermo-oxidative aging prevention structure and a forming method thereof. The resin-based composite material thermo-oxidative aging prevention structure comprises a resin-based composite material and a thermo-oxidative aging prevention film layer; both the resin-based composite material and the thermo-oxidative aging prevention film layer are provided with bonding surfaces, and the bonding surface of the thermo-oxidative aging prevention film layer and the bonding surface of the resin-based composite material are bonded and cured into a whole; the thermo-oxidative aging prevention film layer is a polyimide film layer; and the bonding surface of the thermo-oxidative aging prevention film layer is subjected to roughening treatment. The thermo-oxidative protection polyimide film used in the Resin-based composite material thermo-oxidative aging prevention structure of the invention has certain strength and toughness and excellent thermal oxidation stability, and can effectively prevent oxygen in the air from contacting with the resin matrix, thereby reducing the aging rate of the composite material.

Description

technical field [0001] The invention relates to the field of composite materials, in particular to a thermal-oxidative aging-resistant structure of a resin-based composite material and a preparation method thereof. Background technique [0002] Resin-based composites have been widely used in the aerospace field because of their high specific strength, high specific modulus, and good fatigue resistance. At present, resin-based composite materials are mainly used in aircraft fuselage structural parts in the aviation field, and the service temperature generally does not exceed 200°C, and epoxy resin and bismaleimide resin are mostly used. Compared with aircraft structural materials, aero-engines have higher requirements on the temperature resistance of materials. At present, the temperature resistance level of resin-based composite materials used in the cold-end parts of aero-engines generally needs to reach above 200°C, and the service temperature of some parts reaches 300°C. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B27/28B32B9/00B32B9/04B29C70/34B29C70/54
CPCB32B27/281B32B27/12B32B5/02B29C70/34B29C70/54B32B2250/40B32B2262/106B32B2307/552B32B2307/558B32B2307/714
Inventor 王成博雷帅倪洪江李军张代军陈祥宝
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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