Composite material structure electric lap joint design method based on carbon nano tube conducting film

Abstract

The invention provides a composite material structure electric lap joint design method based on a carbon nanotube conductive film, and the method comprises the steps: 1, employing a co-curing molding technology to prepare a high-conductivity carbon fiber composite material structure, the high-conductivity carbon fiber composite material structure comprises a carbon fiber composite material structure, the carbon fiber composite material structure is provided with an electric lap joint wire installation point, and the electric lap joint wire installation point is provided with a carbon nanotube conductive film; bolt holes are formed in the electric lapping wire mounting points; the carbon nanotube conductive film is laid on the surface of the carbon fiber composite material structure; the gold-plated copper sheet is adhered to the electric lapping wire mounting point, and a bolt hole is formed in the gold-plated copper sheet; and 2, airborne equipment is placed on the high-conductivity carbon fiber composite material structure, and an electric lapping wire of the airborne equipment is fixedly mounted on the electric lapping wire mounting point bonded with the gold-plated copper sheet through a bolt. According to the invention, the design requirement of electrical lap joint resistance of airborne equipment in electrical lap joint with the carbon fiber composite material structure can be met.

Description

Technical Field

[0001] The present application belongs to the field of electrical connection resistance design, and in particular relates to a method for designing electrical connection of a composite structure based on a carbon nanotube conductive film. Background Art

[0002] Modern advanced aircraft have many functions, many onboard equipment, and strict weight requirements. In order to achieve high reliability and lightweight installation of onboard equipment, the design method adopted is to design the fuselage structure as a carbon fiber composite. Due to the poor conductivity of carbon fiber composite materials, it is unable to meet the design requirements of the electrical lap resistance of the onboard equipment to the fuselage structure. Although the more mature surface metallization methods such as aluminum spraying and metal mesh laying can greatly improve the surface conductivity, they still cannot meet the design requirements of the electrical lap resistance, and bring about significant weight gain, mismatch with the thermal expansion coefficient of the composite material, and deformation of the parts.

[0003] As aircraft weight indicators become more and more stringent, designing the fuselage structure with carbon fiber composites is an effective design method. In order to solve the problem of poor conductivity of carbon fiber composite structures, it is very necessary to propose a new type of composite structure electrical lap design technology.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of this application is to provide a method for designing electrical bonding of composite structures based on carbon nanotube conductive films, so as to solve the problem in the prior art that carbon fiber composite material structures cannot meet the electrical bonding resistance design requirements for connecting airborne equipment to the fuselage structure.

[0006] The technical solution of this application is:

[0007] A method for designing electrical overlap of a composite structure based on a carbon nanotube conductive film, comprising:

[0008] Step 1: Prepare a highly conductive carbon fiber composite structure by a co-curing molding process, wherein the highly conductive carbon fiber composite structure comprises:

[0009] A carbon fiber composite structure, wherein an electrical lap wire installation point is provided on the carbon fiber composite structure, and a bolt hole is provided at the electrical lap wire installation point;

[0010] A carbon nanotube conductive film laid on the surface of the carbon fiber composite structure;

[0011] A gold-plated copper sheet bonded to the mounting point of the electrical bonding wire, wherein the gold-plated copper sheet is provided with a bolt hole;

[0012] Step 2: placing the airborne equipment on the highly conductive carbon fiber composite structure, and fixing the electrical bonding wires of the airborne equipment to the electrical bonding wire installation points bonded with the gold-plated copper sheet by means of bolts.

[0013] In at least one embodiment of the present application, the carbon fiber composite structure includes an airborne equipment support plate and an electrical bonding wire mounting plate, and the electrical bonding wire mounting plate is disposed at an end of the airborne equipment support plate.

[0014] In at least one embodiment of the present application, reinforcing ribs are provided at the bottom of the airborne equipment support plate.

[0015] In at least one embodiment of the present application, the cross-section of the electrical jumper wire mounting plate is U-shaped, and an electrical jumper wire mounting point is provided on the web of the electrical jumper wire mounting plate.

[0016] In at least one embodiment of the present application, the process of preparing a highly conductive carbon fiber composite structure by a co-curing molding process includes:

[0017] Conduct thermal distribution analysis on molding tooling to determine the location of thermocouples for temperature monitoring;

[0018] Prepare carbon fiber composite structure samples;

[0019] According to the carbon fiber composite structure sample, the airborne equipment support plate with carbon nanotube conductive film and the electrical bonding wire installation plate are prepared by using a molding tool, and the airborne equipment support plate and the electrical bonding wire installation plate are demoulded with a release agent;

[0020] Determine the electrical bonding wire installation point on the electrical bonding wire installation board, open a bolt hole at the electrical bonding wire installation point, and then bond the gold-plated copper sheet to the electrical bonding wire installation point;

[0021] The airborne equipment support plate and the electrical wiring installation plate of the carbon fiber composite structure are placed in an autoclave for mold assembly, and a highly conductive carbon fiber composite structure is obtained after curing;

[0022] Inspect the assembly quality of highly conductive carbon fiber composite structures.

[0023] In at least one embodiment of the present application, a gold-plated copper sheet is prepared by a gold wire rolling plating process.

[0024] In at least one embodiment of the present application, the process of preparing a gold-plated copper sheet using a rolling gold wire plating process includes:

[0025] The copper sheet is subjected to the first ultrasonic chemical degreasing;

[0026] The copper sheet is subjected to a second ultrasonic chemical degreasing process;

[0027] The copper sheet is subjected to secondary water washing;

[0028] Electrolytic degreasing of copper sheets;

[0029] The copper sheet is washed in three stages;

[0030] Activate the copper sheet;

[0031] The copper sheet is washed in three stages;

[0032] Nickel catalysis of copper sheets;

[0033] The copper sheets are then washed after recovery;

[0034] The copper sheet is subjected to secondary water washing;

[0035] A certain proportion of gold salt and water are mixed to prepare a gold aqueous solution, and a copper sheet is placed in the gold aqueous solution to form a gold-plated copper sheet through the principle of electroplating;

[0036] The gold-plated copper sheet is washed in three stages;

[0037] Drying the gold-plated copper sheet;

[0038] Inspection of gold-plated copper sheets.

[0039] The invention has at least the following beneficial technical effects:

[0040] The electrical bonding design method for composite structures based on carbon nanotube conductive films disclosed in the present application can comprehensively improve the electrical conductivity of the surface of the carbon fiber composite structure, can meet the electrical bonding resistance design requirements for electrical bonding of airborne equipment to the carbon fiber composite structure, has high reliability, and lays a technical foundation for the development of lightweight, highly conductive carbon fiber composite structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 This is a schematic diagram of the electrical connection structure between an airborne device and a highly conductive carbon fiber composite structure according to one embodiment of the present application;

[0042] Figure 2 yes Figure 1 A partial schematic diagram of the CEC joint location.

[0043] in:

[0044] 1-airborne equipment; 2-electric bonding wire; 3-electric bonding wire installation point; 4-carbon fiber composite structure; 5-gold-plated copper sheet; 6-bolt. DETAILED DESCRIPTION

[0045] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0046] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0047] The following is combined with Figure 1 to Figure 2 This application is described in further detail.

[0048] This application starts from the design requirements of the electrical bonding resistance of the bonding structure of airborne equipment, conducts a comprehensive study on improving the conductive performance of the surface of the carbon fiber composite structure, and proposes a composite structure electrical bonding design method based on carbon nanotube conductive film, including the following steps:

[0049] Step 1: Prepare a highly conductive carbon fiber composite structure by a co-curing molding process. The highly conductive carbon fiber composite structure includes:

[0050] A carbon fiber composite structure 4, on which an electrical bonding wire installation point 3 is provided, and the electrical bonding wire installation point 3 is provided with a bolt hole;

[0051] A carbon nanotube conductive film laid on the surface of the carbon fiber composite structure 4;

[0052] A gold-plated copper sheet 5 bonded to the electrical bonding wire installation point 3, wherein a bolt hole is provided on the gold-plated copper sheet 5;

[0053] Step 2: Place the airborne device 1 on the highly conductive carbon fiber composite structure, and fix the electrical bonding wire 2 of the airborne device 1 to the electrical bonding wire installation point 3 bonded with the gold-plated copper sheet 5 by means of bolts 6.

[0054] The electrical bonding design method of the composite structure based on the carbon nanotube conductive film of the present application is as follows: Figure 1 , 2 As shown, a layer of carbon nanotube conductive film is laid on the surface of the carbon fiber composite structure 4 to improve the conductive performance of the surface of the carbon fiber composite structure 4. At the same time, a copper sheet is bonded to the electrical bonding wire installation point 3 of the carbon fiber composite structure 4 to further reduce the electrical bonding resistance. In order to improve the conductivity and corrosion resistance of the copper sheet, a layer of gold film is plated on the surface of the copper sheet using a rolling gold wire plating process to form a gold-plated copper sheet 5. The above components: carbon fiber composite structure 4, carbon nanotube conductive film, and gold-plated copper sheet 5 can be formed into a highly conductive carbon fiber composite structure through co-curing molding technology. The electrical bonding wire 2 extending outward from the airborne equipment 1 is fixed to this highly conductive carbon fiber composite structure by bolts 6, so that the electrical bonding resistance design requirements of the airborne equipment 1 can be achieved.

[0055] In a preferred embodiment of the present application, the structural shape of the carbon fiber composite structure 4 can be designed according to the actual installation requirements of the airborne equipment 1. In this embodiment, the carbon fiber composite structure 4 includes an airborne equipment support plate and an electrical lap wire mounting plate, and the electrical lap wire mounting plate is arranged at the end of the airborne equipment support plate. The top of the airborne equipment support plate serves as a supporting plane for supporting the airborne equipment 1, and the bottom of the airborne equipment support plate is preferably provided with reinforcing ribs. The electrical lap wire mounting plate is used for assembling the electrical lap wire 2 of the airborne equipment 1. The cross-section of the electrical lap wire mounting plate is U-shaped, and an electrical lap wire mounting point is arranged on the web of the electrical lap wire mounting plate.

[0056] In a preferred embodiment of the present application, the process of preparing a highly conductive carbon fiber composite structure by a co-curing molding process includes:

[0057] Conduct thermal distribution analysis on molding tooling to determine the location of thermocouples for temperature monitoring;

[0058] Prepare 4 carbon fiber composite structure samples;

[0059] According to the carbon fiber composite structure 4 samples, the airborne equipment support plate with carbon nanotube conductive film and the electrical bonding wire installation plate are prepared by using a molding tool, and the airborne equipment support plate and the electrical bonding wire installation plate are demoulded with a release agent;

[0060] Determine the electrical bonding wire installation point 3 on the electrical bonding wire installation board, open a bolt hole at the electrical bonding wire installation point 3, and then bond the gold-plated copper sheet 5 to the electrical bonding wire installation point 3;

[0061] The airborne equipment support plate and the electrical connection wire installation plate of the carbon fiber composite structure 4 are placed in an autoclave for mold assembly, and a highly conductive carbon fiber composite structure is obtained after curing;

[0062] Inspect the assembly quality of highly conductive carbon fiber composite structures.

[0063] In this embodiment, the thermal distribution analysis of the molding tooling of the highly conductive carbon fiber composite structure is performed to determine the position of the thermocouple used for temperature monitoring to ensure that the product temperature meets the requirements of the curing system. The accuracy of the assembly position is ensured by making a sample.

[0064] In a preferred embodiment of the present application, the gold-plated copper sheet 5 is prepared by a rolling gold wire plating process, and the preparation process of the gold-plated copper sheet 5 includes:

[0065] The copper sheet is subjected to the first ultrasonic chemical degreasing;

[0066] The copper sheet is subjected to a second ultrasonic chemical degreasing process;

[0067] The copper sheet is subjected to secondary water washing;

[0068] Electrolytic degreasing of copper sheets;

[0069] The copper sheet is washed in three stages;

[0070] Activate the copper sheet;

[0071] The copper sheet is washed in three stages;

[0072] Nickel catalysis of copper sheets;

[0073] The copper sheets are then washed after recovery;

[0074] The copper sheet is subjected to secondary water washing;

[0075] A certain proportion of gold salt and water are mixed to prepare a gold aqueous solution, and a copper sheet is placed in the gold aqueous solution to form a gold-plated copper sheet 5 through the principle of electroplating;

[0076] The gold-plated copper sheet 5 is subjected to three-stage water washing;

[0077] Drying the gold-plated copper sheet 5;

[0078] The gold-plated copper sheet 5 was inspected.

[0079] In this embodiment, before the gold-plated copper sheet 5 is electroplated, the copper sheet is subjected to multiple degreasing and water washing treatments, so that the oil stains and other impurities on the surface of the copper sheet can be cleaned to ensure the quality of the gold-plated copper sheet 5 during the manufacturing process.

[0080] The electrical bonding design method of the composite structure based on carbon nanotube conductive film of the present application can meet the electrical bonding resistance design requirements of the airborne equipment 1 electrically bonded to the carbon fiber composite structure 4, has high reliability, and lays a technical foundation for the development of lightweight, highly conductive carbon fiber composite structures.

[0081] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for designing electrical overlap of a composite structure based on a carbon nanotube conductive film, characterized in that: include: Step 1: Prepare a highly conductive carbon fiber composite structure by a co-curing molding process, wherein the highly conductive carbon fiber composite structure comprises: A carbon fiber composite structure, wherein an electrical lap wire installation point is provided on the carbon fiber composite structure, and a bolt hole is provided at the electrical lap wire installation point; A carbon nanotube conductive film laid on the surface of the carbon fiber composite structure; A gold-plated copper sheet bonded to the mounting point of the electrical bonding wire, wherein the gold-plated copper sheet is provided with a bolt hole; Step 2: placing the airborne equipment on the highly conductive carbon fiber composite structure, and fixing the electrical bonding wires of the airborne equipment to the electrical bonding wire installation points bonded with the gold-plated copper sheet by means of bolts.

2. The method for designing electrical overlap of a composite structure based on a carbon nanotube conductive film according to claim 1, characterized in that: The carbon fiber composite structure comprises an airborne equipment support plate and an electrical bonding wire installation plate, wherein the electrical bonding wire installation plate is arranged at the end of the airborne equipment support plate.

3. The method for designing electrical overlap of a composite structure based on a carbon nanotube conductive film according to claim 2, characterized in that: The bottom of the airborne equipment support plate is provided with reinforcing ribs.

4. The method for designing electrical overlap of a composite structure based on a carbon nanotube conductive film according to claim 3, characterized in that: The cross section of the electrical jumper wire installation plate is U-shaped, and an electrical jumper wire installation point is arranged on the web of the electrical jumper wire installation plate.

5. The method for designing electrical overlap of a composite structure based on a carbon nanotube conductive film according to claim 4, characterized in that: The process of preparing a highly conductive carbon fiber composite structure using a co-curing molding process includes: Conduct thermal distribution analysis on molding tooling to determine the location of thermocouples for temperature monitoring; Prepare carbon fiber composite structure samples; According to the carbon fiber composite structure sample, the airborne equipment support plate with carbon nanotube conductive film and the electrical bonding wire installation plate are prepared by using a molding tool, and the airborne equipment support plate and the electrical bonding wire installation plate are demoulded with a release agent; Determine the electrical bonding wire installation point on the electrical bonding wire installation board, open a bolt hole at the electrical bonding wire installation point, and then bond the gold-plated copper sheet to the electrical bonding wire installation point; The airborne equipment support plate and the electrical wiring installation plate of the carbon fiber composite structure are placed in an autoclave for mold assembly, and a highly conductive carbon fiber composite structure is obtained after curing; Inspect the assembly quality of highly conductive carbon fiber composite structures.

6. The method for designing electrical overlap of a composite structure based on a carbon nanotube conductive film according to claim 5, characterized in that: The gold-plated copper sheet was prepared by the gold-rolling wire plating process.

7. The method for designing electrical overlap of a composite structure based on a carbon nanotube conductive film according to claim 6, characterized in that: The process of preparing gold-plated copper sheets using the gold-plating wire rolling process includes: The copper sheet is subjected to the first ultrasonic chemical degreasing; The copper sheet is subjected to a second ultrasonic chemical degreasing process; The copper sheet is subjected to secondary water washing; Electrolytic degreasing of copper sheets; The copper sheet is washed in three stages; Activate the copper sheet; The copper sheet is subjected to three-stage water washing; Nickel catalysis of copper sheets; The copper sheets are then washed after recovery; The copper sheet is subjected to secondary water washing; A certain proportion of gold salt and water are mixed to prepare a gold aqueous solution, and a copper sheet is placed in the gold aqueous solution to form a gold-plated copper sheet through the principle of electroplating; The gold-plated copper sheet is washed in three stages; Drying the gold-plated copper sheet; Inspection of gold-plated copper sheets.

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