CN110341199B - Method for enhancing bonding strength of light alloy and composite material bonding interface - Google Patents

Method for enhancing bonding strength of light alloy and composite material bonding interface Download PDF

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CN110341199B
CN110341199B CN201910492803.6A CN201910492803A CN110341199B CN 110341199 B CN110341199 B CN 110341199B CN 201910492803 A CN201910492803 A CN 201910492803A CN 110341199 B CN110341199 B CN 110341199B
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light alloy
composite material
alloy
flame
enhancing
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CN110341199A (en
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熊需海
任荣
陈平
赵普
王静
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Qingdao Xindong Aviation Technology Development Co.,Ltd.
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Shenyang Aerospace University
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/02—Preparation of the material, in the area to be joined, prior to joining or welding
    • B29C66/022—Mechanical pre-treatments, e.g. reshaping
    • B29C66/0224—Mechanical pre-treatments, e.g. reshaping with removal of material
    • B29C66/02245—Abrading, e.g. grinding, sanding, sandblasting or scraping
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/02—Preparation of the material, in the area to be joined, prior to joining or welding
    • B29C66/028—Non-mechanical surface pre-treatments, i.e. by flame treatment, electric discharge treatment, plasma treatment, wave energy or particle radiation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/742—Joining plastics material to non-plastics material to metals or their alloys

Abstract

A method for enhancing the bonding strength of a light alloy and composite material bonding interface belongs to the technical field of aviation material connection. The method adopts a flame synthesis process to grow a carbon nanotube layer (CNT layer) on the surface of a light alloy bonding area in situ, and a bonding agent is smeared between the light alloy and a composite material for bonding; the CNT layer is utilized to synchronously enhance the interface strength between the adhesive and the light alloy and the body strength of the adhesive layer, so that the mechanical property of the heterogeneous adhesive joint of the light alloy and the composite material is improved. The method is simple and quick, has extremely low cost, and has wide application prospect in the field of heterogeneous bonding of light alloy and composite materials such as aerospace, transportation and the like.

Description

Method for enhancing bonding strength of light alloy and composite material bonding interface
Technical Field
The invention relates to the technical field of aviation material connection, in particular to a method for enhancing the bonding strength of a light alloy and composite material bonding interface.
Background
Light alloy and composite materials are two most important structural materials in the field of aviation; the technology of connection between light weight alloys and composite materials is one of the key technologies affecting aircraft manufacturing assembly. The mechanical fastening connection is the most main connection mode of light alloy and composite materials at present; however, the bolting and riveting processes need to drill holes in the light alloy and the composite material, the integrity of the materials is damaged in the processes, and the mechanical strength of the connecting parent metal body is reduced; the connection area also has great stress concentration, which affects the long-term bearing stability of the connector. In addition, the use of a large number of bolts and rivets results in a significant increase in the overall weight of the structural member. The adhesive bonding technique can overcome the problems of mechanically fastened joints, however, the adhesive bonded joints have lower durability and fatigue strength than mechanically fastened joints and welding. The fracture of the glue line body and the debonding of the glue agent from the surface of the light alloy are the most common failure modes of the heterogeneous glue joint of the light alloy and the composite material.
Based on the method, the appearance and chemical characteristics of the surface of the light alloy are changed by adopting mechanical polishing methods such as abrasion, sand blasting and the like, acid/alkali/electrochemical etching methods, plasma or laser etching methods and the like, and the mechanical interlocking effect, the physical adsorption effect and the chemical bonding effect between the adhesive and the irregular pits on the surface of the light alloy are improved, so that the interface strength between the adhesive layer and the light alloy is enhanced. However, these treatments have a certain impairment of the properties of the light alloys themselves; in addition, the treatment process requires special treatment equipment or causes environmental pollution. The mechanical strength of the adhesive layer can be improved by adding nano rigid particles such as Carbon Nano Tubes (CNT), graphene and the like into the adhesive; however, due to the agglomeration benefit of the nanoparticles, the nanoparticles are difficult to be uniformly dispersed in the cement, and the construction process performance of the cement is affected.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a method for enhancing the bonding strength of a light alloy and composite material cementing interface. The main approach for solving the technical problem is to grow a carbon nanotube layer (CNT layer) on the surface of the light alloy glue joint area in situ by a flame synthesis process (the action of a catalyst and flame), and further to synchronously enhance the interface strength between the glue joint and the light alloy and the bulk strength of the glue layer by utilizing the CNT layer, thereby realizing the improvement of the mechanical properties of the light alloy and composite material heterogeneous glue joint. The method is simple and quick, has extremely low cost, and has wide application prospect in the field of heterogeneous bonding of light alloy and composite materials such as aerospace, transportation and the like.
The invention discloses a method for enhancing the bonding strength of a light alloy and composite material cementing interface, which comprises the following steps:
step 1: surface pretreatment of light alloy
Removing the oxide film on the surface of the light alloy area to be bonded to obtain the pretreated light alloy;
step 2: flame method for preparing CNT layer
Uniformly spraying a catalyst solution on the surface of a region to be bonded of the pretreated light alloy, and drying to obtain a light alloy loaded with a catalyst;
placing the light alloy loaded with the catalyst in combustion flame, keeping the temperature at 800-1100 ℃ for 3-20 min, and growing a CNT layer which is intertwined with each other in a region of the light alloy to be bonded to obtain the light alloy loaded with the CNT layer; wherein the fuel of the burnup flame is hydrocarbon of C1-C7;
and step 3: glue joint
And uniformly coating the adhesive on the surface of the area to be bonded of the light alloy loaded with the CNT layer, bonding the area to be bonded with the composite material, applying pressure, and curing by adopting a curing process of the adhesive to obtain a bonding structure of the light alloy and the composite material.
Wherein the content of the first and second substances,
the light alloy is one of aluminum alloy, titanium alloy, aluminum lithium alloy and aluminum magnesium alloy.
The composite material is prepared by compounding reinforced fibers and resin.
The reinforced fiber is one of glass fiber, carbon fiber, aramid fiber or PBO fiber; the resin is one of epoxy resin, bismaleimide resin, cyanate resin or phenolic resin.
In the step 1, the surface of the light alloy can be treated and modified; the surface treatment modification method comprises one or more of abrasion, sand blasting, mechanical polishing, acid/alkali etching, electrochemical etching, plasma etching and laser etching.
In the step 2, in the catalyst solution, the catalyst is one or more of ferric chloride, nickel chloride, cobalt chloride, ferric nitrate, nickel nitrate and cobalt nitrate, preferably nickel nitrate.
In the step 2, the concentration of the catalyst solution is 0.5-2 mol/L, preferably 1 mol/L.
In the step 2, the combustion flame is one or more of an ethanol flame, a methanol flame, a methane flame, a butane flame, a heptane flame, an acetone flame, an acetylene flame or an ethylene flame, and is preferably an ethanol flame;
in the step 2, the growth temperature is preferably 1000 ℃, and the holding time is preferably 10 min.
In the step 3, preferably, the adhesive is one of epoxy resin, bismaleimide resin, cyanate resin and phenolic resin.
The method for enhancing the bonding strength of the light alloy and composite material cementing interface has the beneficial effects that:
1) the CNT layer grows on the surface of the light alloy bonding area in situ by adopting a flame method, and the interface strength of the surface of the light alloy and the adhesive and the body strength of the adhesive layer of the adhesive joint are enhanced by utilizing the CNT layer, so that the mechanical strength of the heterogeneous bonding structure of the light alloy and the composite material is improved. Since the burning flame provides both a carbon-rich environment suitable for CNT production and the required heat, and expensive equipment is not required; therefore, the method can be applied to strengthening the mechanical properties of heterogeneous adhesive joint structures of various light alloys and composite materials in aerospace on a large scale.
2) The method disclosed by the invention does not damage the performance of the light alloy body, is simple in implementation process, extremely low in cost, low in consumption, green and environment-friendly, high in flexibility, strong in adaptability and easy for industrial popularization.
3) The method of the invention can be used independently, and can also be used together with the traditional light alloy surface treatment modification processes such as abrasion, sand blasting, mechanical polishing, acid/alkali etching, electrochemical etching, plasma etching, laser etching and the like, and more excellent modification effect can be obtained due to the coupling of multiple functions.
Drawings
FIG. 1 is an SEM image of an in-situ grown CNT layer on the surface of an aluminum alloy in example 1;
fig. 2 is a schematic structural diagram of a single lap joint of an aluminum alloy and glass fiber/epoxy (GF/EP) composite material in embodiment example 1: 1-GF/EP composites; 2-aluminum alloy; 3-a CNT-rich reinforced epoxy glue layer; 4-Small CNT-reinforced epoxy resin adhesive layer
Detailed Description
In order to make the technical means, innovative features and attainment effects of the present invention easier to understand, the present invention will be further described with reference to the following detailed description.
In the following examples, all epoxy resin cements refer to adhesives that already contain curing agents.
Comparative example
A method for cementing light alloy and composite materials comprises the following steps:
step I: surface pretreatment of light alloy
Polishing the light alloy sample piece by using 400-mesh sand paper, and removing an oxide film on the surface to obtain a pretreated light alloy;
step II: glue joint
And uniformly coating the cementing agent on the surface of the pretreated light alloy to be cemented, then lapping the surface with the composite material, applying pressure, solidifying and cooling to obtain the light alloy and composite material single-lap joint cementing head sample piece.
Example 1
A method for enhancing the bonding strength of a light alloy and composite material cementing interface comprises the following steps:
step 1: surface pretreatment of light alloy
Polishing the aluminum alloy sample piece by using 400-mesh abrasive paper, and removing an oxide film on the surface to obtain a pretreated aluminum alloy;
step 2: flame method for preparing CNT layer
Uniformly spraying a nickel nitrate solution with the mass concentration of 1mol/L on the surface of a polished and pretreated aluminum alloy area to be bonded through a spray gun, and drying to obtain a catalyst-loaded aluminum alloy;
placing the surface of the aluminum alloy loaded with the catalyst at the position of 800 ℃ of alcohol flame temperature, staying for 10 minutes, and growing a CNT layer which is intertwined with each other in the area of the aluminum alloy to be bonded to prepare the aluminum alloy loaded with the CNT layer; SEM scanning is carried out on the surface of the prepared CNT layer loaded aluminum alloy, and an SEM image of the in-situ grown CNT layer on the surface of the prepared aluminum alloy is shown in figure 1.
And step 3: glue joint
Uniformly coating epoxy resin on the surface to be bonded of the aluminum alloy loaded with the CNT layer, overlapping the surface to be bonded with a glass fiber reinforced epoxy resin (GF/EP) composite material, applying pressure, curing and cooling to obtain an aluminum alloy-GF/EP composite material single-lap joint adhesive joint sample, wherein the structural schematic diagram is shown in figure 2. Compared with the aluminum alloy single lap heterogeneous adhesive joint which is only polished by sand paper and prepared by adopting the method of the comparative example, the tensile shear strength (LSS) of the in-situ CNT layer reinforced aluminum alloy-GF/EP composite material single lap joint is improved by 32 percent.
Example 2
A method for enhancing the bonding strength of a light alloy and composite material cementing interface comprises the following steps:
step 1: surface pretreatment of light alloy
Polishing the titanium alloy sample piece by using 400-mesh sand paper, and removing an oxide film on the surface to obtain a pretreated titanium alloy;
step 2: flame method for preparing CNT layer
Uniformly spraying a nickel nitrate solution with the mass concentration of 1mol/L on the surface of a titanium alloy to-be-bonded area subjected to polishing pretreatment through a spray gun, and drying to obtain a catalyst-loaded titanium alloy;
and (3) placing the surface of the titanium alloy loaded with the catalyst at the position of 1000 ℃ of alcohol flame temperature, staying for 20 minutes, and growing a CNT layer which is intertwined with each other in the area of the titanium alloy to be bonded to prepare the titanium alloy loaded with the CNT layer.
And step 3: glue joint
Uniformly coating bismaleimide resin on the surface of the CNT layer-loaded titanium alloy to be bonded, overlapping the surface with a carbon fiber reinforced bismaleimide resin (CF/BMI) composite material, applying pressure, curing and cooling to obtain a single-overlapping bonded sample piece of the titanium alloy-CF/BMI composite material. Compared with the titanium alloy single lap heterogeneous glue joint which is only sanded and prepared by adopting the method of the comparative example, the tensile shear strength (LSS) of the in-situ CNT layer reinforced titanium alloy-CF/BMI composite material single lap joint is improved by 46 percent.
Example 3
A method for enhancing the bonding strength of a light alloy and composite material cementing interface comprises the following steps:
step 1: surface pretreatment of light alloy
The method comprises the following steps of (1) carrying out sand blasting on an aluminum-magnesium alloy sample piece, removing an oxide film on the surface, and increasing the roughness of the surface to obtain a pretreated aluminum-magnesium alloy;
step 2: flame method for preparing CNT layer
Uniformly spraying ferric chloride solution with the mass concentration of 0.5mol/L on the surface of an aluminum-magnesium alloy area to be bonded, which is subjected to sand blasting pretreatment, through a spray gun, and drying to obtain the catalyst-loaded aluminum-magnesium alloy;
and (3) placing the surface of the catalyst-loaded aluminum-magnesium alloy at a position with the flame temperature of methanol and ethanol of 900 ℃, staying for 15 minutes, and growing a CNT layer which is intertwined with each other in a region to be bonded of the aluminum-magnesium alloy to prepare the CNT layer-loaded aluminum-magnesium alloy.
And step 3: glue joint
Uniformly coating phenolic resin on the surface of the aluminum-magnesium alloy loaded with the CNT layer to be bonded, overlapping the surface with the aramid fiber reinforced phenolic resin composite material, applying pressure of 1MPa, and curing and cooling to obtain the aluminum-magnesium alloy-aramid fiber reinforced phenolic resin composite material single-lap-joint bonding sample piece.
Example 4
A method for enhancing the bonding strength of a light alloy and composite material cementing interface comprises the following steps:
step 1: surface pretreatment of light alloy
Etching the aluminum lithium alloy sample piece by using laser, removing an oxide film on the surface and simultaneously increasing the surface roughness of the aluminum lithium alloy sample piece to obtain a pretreated aluminum lithium alloy;
step 2: flame method for preparing CNT layer
Uniformly spraying a mixed solution (the molar ratio is 1:1) of cobalt nitrate and cobalt chloride with the mass concentration of 2mol/L on the surface of a region to be bonded of the polished and pretreated aluminum-lithium alloy through a spray gun, and drying to obtain the catalyst-loaded aluminum-lithium alloy;
and (3) placing the surface of the catalyst-loaded aluminum lithium alloy at the position of the ethylene flame temperature of 1100 ℃, staying for 5 minutes, and growing a CNT layer which is intertwined with each other in the area to be bonded of the aluminum lithium alloy to prepare the aluminum lithium alloy loaded with the CNT layer.
And step 3: glue joint
And uniformly coating bismaleimide resin on the surface of the aluminum lithium alloy loaded with the CNT layer to be bonded, overlapping the bismaleimide resin with the PBO fiber reinforced bismaleimide resin composite material, applying pressure, curing and cooling to obtain the aluminum lithium alloy-PBO fiber reinforced bismaleimide resin composite material single-lap-joint bonding sample piece.

Claims (8)

1. A method for enhancing the bonding strength of a light alloy and composite material cementing interface is characterized by comprising the following steps:
step 1: surface pretreatment of light alloy
Removing the oxide film on the surface of the light alloy area to be bonded to obtain the pretreated light alloy;
step 2: flame method for preparing CNT layer
Uniformly spraying a catalyst solution on the surface of a region to be bonded of the pretreated light alloy, and drying to obtain a light alloy loaded with a catalyst; in the catalyst solution, the catalyst is one or more of ferric chloride, nickel chloride, cobalt chloride, ferric nitrate, nickel nitrate and cobalt nitrate; a catalyst solution, the concentration of the substance amount of which is 0.5-2 mol/L;
placing the light alloy loaded with the catalyst in combustion flame, keeping the temperature at 800-1100 ℃ for 3-20 min, and growing a CNT layer which is intertwined with each other in a region of the light alloy to be bonded to obtain the light alloy loaded with the CNT layer; wherein the fuel of the burnup flame is hydrocarbon of C1-C7;
and step 3: glue joint
And uniformly coating the adhesive on the surface of the area to be bonded of the light alloy loaded with the CNT layer, bonding the area to be bonded with the composite material, applying pressure, and curing by adopting a curing process of the adhesive to obtain a bonding structure of the light alloy and the composite material.
2. The method for enhancing the bonding strength of the cementing interface of the light alloy and the composite material as claimed in claim 1, wherein the light alloy is one of aluminum alloy, titanium alloy, aluminum lithium alloy and aluminum magnesium alloy.
3. The method for enhancing the bonding strength of the light alloy and composite material cementing interface of claim 1, wherein the composite material is a composite material prepared by compounding reinforcing fibers and resin.
4. The method for enhancing the bonding strength of the light alloy and composite material cementing interface of claim 3, wherein the reinforcing fiber is one of glass fiber, carbon fiber, aramid fiber or PBO fiber; the resin is one of epoxy resin, bismaleimide resin, cyanate resin or phenolic resin.
5. The method for enhancing the bonding strength of the light alloy and composite material cementing interface of claim 1, wherein in the step 1, the light alloy is subjected to surface treatment modification; the surface treatment modification method comprises one or more of abrasion, sand blasting, mechanical polishing, acid/alkali etching, electrochemical etching, plasma etching and laser etching.
6. The method for enhancing the bonding strength of the light alloy and composite material cementing interface of claim 1, wherein in the step 2, the combustion flame is one or more of an ethanol flame, a methanol flame, a methane flame, a butane flame, a heptane flame, an acetone flame, an acetylene flame or an ethylene flame.
7. The method for enhancing the bonding strength of the light alloy and composite material cementing interface of claim 1, wherein in the step 2, the growth temperature is 1000 ℃ and the holding time is 10 min.
8. The method for enhancing the bonding strength of the light alloy and composite material bonding interface of claim 1, wherein in the step 3, the adhesive is one of epoxy resin, bismaleimide resin, cyanate resin and phenolic resin.
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CN110842365A (en) * 2019-11-26 2020-02-28 佳普电子新材料(连云港)有限公司 Laser surface treatment process for metal base material of shielding material
CN112196123A (en) * 2020-09-27 2021-01-08 南京工程学院 FRP (fiber reinforced plastic) section-steel section groove tooth cementing connection node and construction method
CN112296505B (en) * 2020-10-19 2022-05-10 沈阳航空航天大学 Alloy-composite material friction stir welding joint and preparation method thereof
CN112937062A (en) * 2021-02-03 2021-06-11 沈阳中钛装备制造有限公司 Preparation method of adhesive type titanium alloy composite protection plate

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07172807A (en) * 1993-12-21 1995-07-11 Nec Corp Working method of carbon nanotube
CN103895287A (en) * 2012-12-26 2014-07-02 北京有色金属研究总院 Method for improving bonding of interfaces between shape memory alloy and polymer material

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07172807A (en) * 1993-12-21 1995-07-11 Nec Corp Working method of carbon nanotube
CN103895287A (en) * 2012-12-26 2014-07-02 北京有色金属研究总院 Method for improving bonding of interfaces between shape memory alloy and polymer material

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