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Method for carbon fiber composite material and aluminum alloy interface treatment

A composite material and interface treatment technology, applied in the direction of surface pretreatment bonding method, adhesive type, adhesive additives, etc., can solve the problem of large thermal residual stress at the interface of thermal expansion coefficient, etc., and achieve the effect of reducing the difference

Inactive Publication Date: 2019-05-14
WUHAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The invention provides a method for treating the interface between a carbon fiber composite material and an aluminum alloy, which solves the problem of excessive thermal residual stress at the interface caused by a large difference in thermal expansion coefficient in the longitudinal direction of the existing carbon fiber composite material / aluminum alloy

Method used

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  • Method for carbon fiber composite material and aluminum alloy interface treatment

Examples

Experimental program
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Effect test

Embodiment 1

[0018] Prepare hydrochloric acid with a volume concentration of 11%, soak aluminum alloy 6061 in hydrochloric acid, and its thermal expansion coefficient is 2.3×10 -5 / °C, the soaking time is 30min, rinse with clean water after taking it out; add carbon nanotubes with a mass fraction of 1.0% to the epoxy resin, use mechanical stirring to make the carbon nanotubes evenly distributed, add curing agent, stir evenly, Then, the epoxy resin mixed with carbon nanotubes is coated on one surface of the aluminum alloy with a thickness of 0.1 mm, and then a magnetic field device is applied to arrange the carbon nanotubes along the 0° direction, and the carbon nanotubes mixed with carbon nanotubes after orientation are aligned. The coefficient of thermal expansion of the epoxy resin of the tube is 2.1 x 10 -5 / °C, followed by curing; after curing, apply bisphenol A epoxy acrylic resin, the glass transition temperature is 60°C, the thickness is 0.5mm, and cure; cut several sheets of T700 c...

Embodiment 2

[0020] This embodiment is roughly the same as Example 1, except that the carbon nanotubes mixed in the epoxy resin are modified by surface grafting. In the mixture of concentrated sulfuric acid and concentrated nitric acid, react at 80°C for 4 hours, then use deionized water and absolute ethanol to wash the product to neutrality, disperse it into PEO oligomer after drying, and add an appropriate amount of catalyst SnCl 2 , stirred and reacted at 80°C for 12h, the product was fully washed with acetone and suction filtered, and then fully dried at 60°C to obtain surface graft-modified carbon nanotubes, the mass fraction mixed into epoxy resin was 0.5% ,. The thermal expansion coefficient of the epoxy resin mixed with carbon nanotubes after alignment is 1.7×10 -5 / °C, between the longitudinal thermal expansion coefficient of the unidirectional carbon fiber cloth in contact with the aluminum alloy and the thermal expansion coefficient of the aluminum alloy.

Embodiment 3

[0022] Prepare hydrochloric acid with a volume concentration of 11%, soak aluminum alloy 6061 in hydrochloric acid, and its thermal expansion coefficient is 2.3×10 -5 / °C, soaking time is 30min, take it out and rinse it with clean water; add the surface graft modified carbon nanotubes with a mass fraction of 0.5% to the epoxy resin, use mechanical stirring to make the carbon nanotubes evenly distributed, add and cure agent, stir evenly, and then coat the epoxy resin mixed with carbon nanotubes on one surface of the aluminum alloy with a thickness of 0.15mm, and then use a magnetic field device to apply a magnetic field to arrange the carbon nanotubes along the 0° direction, and then solidify After curing, apply bisphenol A epoxy acrylic resin with a glass transition temperature of 60°C and a thickness of 0.5 mm, and cure; cut several sheets of T700 carbon fiber unidirectional cloth, and the longitudinal thermal expansion coefficient of the T700 carbon fiber composite unidirecti...

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Abstract

The invention relates to a method for carbon fiber composite material and aluminum alloy interface treatment. The method comprises the following steps: firstly performing surface treatment on an aluminum alloy by using hydrochloric acid, and coating on the surface of the aluminum alloy by epoxy resin mixed with carbon nano tubes, enabling the carbon nano tubes to be directionally arranged by usingan externally applied magnetic field, and curing; coating by epoxy acrylic resin and curing; laying a layer of one-way carbon fiber cloth, wherein a laying angle is the same as a directional arrangement direction of the above carbon nano tubes, then laying the carbon fiber cloth, finally curing and forming. Because a longitudinal thermal expansion coefficient of the directionally arranged epoxy resin mixed with the carbon nano tubes is between the aluminum alloy and the one-way carbon fiber cloth, and the epoxy acrylic resin is positioned in a high-elastic state in a temperature above a glass-transition temperature, and serves as a stress buffer layer for absorbing partial stress, an interface heat residual stress caused by a larger difference of the longitudinal thermal expansion coefficients of two parties can be effectively reduced in a cooling process of the carbon fiber composite material and the aluminum alloy.

Description

technical field [0001] The invention relates to a method for treating the interface between a carbon fiber composite material and an aluminum alloy. Background technique [0002] Compared with the traditional metal structure gas cylinder, the new gas cylinder made of aluminum alloy as the inner liner and wound with carbon fiber composite material can not only greatly reduce the weight of the whole gas cylinder, but also improve the carrying capacity of the gas cylinder and improve the resistance Explosive performance and production efficiency, saving manufacturing costs; In addition to being used in gas cylinders, carbon fiber composite materials are currently connected with aluminum alloys as structural parts and are widely used in aviation due to their high strength, high temperature resistance, and dimensional stability. Aerospace, military and civil fields. However, carbon fiber composite materials are anisotropic materials, and the thermal expansion coefficients in the...

Claims

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Application Information

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IPC IPC(8): C09J5/02C09J163/00C09J11/04
Inventor 蔡浩鹏王攀
Owner WUHAN UNIV OF TECH
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