CN106079481B - Forming method of composite material with lightning protection effect - Google Patents

Forming method of composite material with lightning protection effect Download PDF

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Publication number
CN106079481B
CN106079481B CN201610517789.7A CN201610517789A CN106079481B CN 106079481 B CN106079481 B CN 106079481B CN 201610517789 A CN201610517789 A CN 201610517789A CN 106079481 B CN106079481 B CN 106079481B
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composite material
resin
conductive particles
resin film
fiber
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CN106079481A (en
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段玉岗
王奔
辛志博
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Xian Jiaotong University
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Xian Jiaotong 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B7/00—Mixing; Kneading
    • B29B7/002—Methods
    • 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
    • B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
    • B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
    • 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
    • B29C41/00—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor
    • B29C41/02—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor for making articles of definite length, i.e. discrete articles
    • B29C41/12—Spreading-out the material on a substrate, e.g. on the surface of a liquid

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Oral & Maxillofacial Surgery (AREA)
  • Thermal Sciences (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Reinforced Plastic Materials (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

The invention discloses a method for forming a composite material with a lightning protection effect. The method comprises the steps of firstly, paving and pasting a resin film dispersed with nano conductive particles on a fiber woven fabric preformed body, and then forming gradient distribution of the nano conductive particles along the thickness direction of the composite material through an improved resin film infiltration process, so that the conductive characteristic of the composite material is improved, and the lightning damage of the composite material is reduced. Compared with the traditional lightning protection mode of using the composite material with the modified metal surface, the forming method is simple and easy to implement, greatly saves the energy consumption, saves the manufacturing cost, effectively reduces the weight of the composite material member, and avoids the problems of corrosion of the metal protection material, low adhesion with the composite material and the like.

Description

Forming method of composite material with lightning protection effect
Technical Field
The invention relates to the field of lightning protection of composite materials, in particular to a method for forming a composite material with a lightning protection function.
Background
The fiber reinforced resin matrix composite material has the advantages of high specific strength, high corrosion resistance and designable strength, is widely applied to aircraft structural materials to improve the weight, maneuverability and reliability of an aircraft and also can greatly improve the flight time of the aircraft, and the using amount and the application level of the fiber reinforced resin matrix composite material become important marks for measuring the structural advancement of the aircraft. However, compared with the traditional metal material, although the carbon fiber in the composite material has better conductivity, the insulating resin matrix obstructs a conductive path, so that the lightning current is difficult to be led out on the surface of the material to generate a large amount of joule heat, the composite material is ablated, the strength and the rigidity of the composite material are greatly reduced, and great challenges are brought to the safety and the economy of the airplane structure.
At present, for the lightning stroke protection method of the composite material, a high-conductivity metal material is attached to the surface of the composite material structure mainly by methods of net foil coating, surface spraying and the like. For example, the lightning protection measure of the composite fuselage structure of the boeing 787 aircraft is to add a metal net in the manufacturing process of the composite fuselage to lead away lightning current. However, the high density of the metal material not only increases the weight of the composite structure, but also increases the manufacturing cost of the composite structure; moreover, metal materials are prone to corrosion and have low bonding strength with resin, so that gaps are prone to appear on the surface between the metal materials and the composite material, electric arcs and sparks are generated when lightning current can pass through, and even fuel tanks in the structure can be ignited seriously to cause aircraft explosion. The invention aims to provide a new solution to the problems of the existing lightning protection measures.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provide a method for forming a composite material with a lightning protection function.
The technical solution of the invention is as follows:
a method for forming a composite material with a lightning protection effect comprises the following steps:
1) preparing a resin film dispersed with nano conductive particles; mixing and dispersing the nano conductive particles and resin containing a solvent for 2-3 hours in a high-speed stirrer, dissolving a film-forming agent into the mixture of the dispersed nano conductive particles and the resin, and adding a high-temperature curing agent for mixing; pouring the obtained resin system on an iron plate at the temperature of 90-120 ℃ to form a resin film containing dispersed nano conductive particles by tape casting; the nano conductive particles are one or more of carbon nano tubes, graphene, nano silver and nano nickel; the resin containing the solvent is unsaturated polyester, epoxy resin, bismaleimide resin, cyanate resin and a corresponding solvent system thereof, or a mixture of a plurality of resins and a solvent system thereof; the high-temperature curing agent is one or more of aromatic polyamine, acid anhydride, methyl phenolic resin and dicyandiamide;
2) shaping the fiber preformed body; firstly cutting a resin film and fiber cloth according to the size of a mold, then paving and sticking the cut fiber cloth along the surface of the mold, covering the resin film on the fiber cloth, and sealing the periphery of the preformed body by using a sealant; the fiber cloth is woven by one or more fibers of glass fiber, carbon fiber and aramid fiber, and the sealant is a rubber and polytetrafluoroethylene high-temperature-resistant sealant;
3) molding a fiber preformed body; according to the resin film infiltration process, a microporous filter membrane is laid on the preformed body, a vacuum diversion system is constructed on the microporous filter membrane, a mold is sealed by a vacuum bag membrane to form a mold cavity, the sealed mold cavity is vacuumized, and the mold is heated at the same time, so that the temperature of the mold reaches between 100 ℃ and 140 ℃;
4) curing the composite material; and (3) putting the fiber preformed body into a vacuum oven, and heating and curing according to the curing process conditions of the resin types to prepare a composite material part with the surface containing the nano conductive particles.
The microporous filter membrane is made of nylon, polypropylene or polyether sulfone.
The method has the advantages that through the improved resin film infiltration process, the nano conductive particles form gradient distribution along the thickness direction of the composite material, so that the conductive characteristic of the composite material is improved, and the lightning damage of the composite material is reduced. Compared with the traditional lightning protection mode of using the composite material with the modified metal surface, the invention adopts an integrated forming mode, is simple and easy to implement, greatly saves the energy consumption, saves the manufacturing cost, effectively reduces the weight of the composite material member, and avoids the problems of corrosion, weak caking property and the like of metal. Moreover, the distribution of the nano conductive particles in the composite material can be controlled by the content of the resin film nano conductive particles and the infiltration process parameters, so that the conductive characteristic of the composite material is designed, and the lightning protection requirements of different parts of an aircraft are met.
Drawings
FIG. 1 is a schematic view of a composite material with lightning protection and a molding method thereof
Detailed Description
The invention is further described below with reference to the accompanying drawings.
1) And (3) preparing a resin film dispersed with the nano conductive particles. Mixing and dispersing the nano conductive particles and the resin containing the solvent for 2-3 hours in a high-speed stirrer, then dissolving the film forming agent into the mixture of the nano conductive particles and the resin which are dispersed in the previous step, and adding the high-temperature curing agent for mixing. Finally, the obtained resin system is poured on an iron plate at the temperature of 90-120 ℃ and is subjected to tape casting to form a resin film containing the dispersed nano conductive particles.
2) And (5) shaping the fiber preformed body. Firstly cutting a resin film and fiber cloth according to the size of a mold, then paving and pasting the cut fiber cloth along the surface of the mold, then covering the resin film on the fiber cloth, and finally sealing the periphery of the preformed body by using a sealant.
3) And (4) forming a fiber preform. According to the resin film infiltration process, a microporous filter membrane is laid on the preformed body, a vacuum diversion system is constructed on the microporous filter membrane, a mold is sealed by a vacuum bag membrane to form a mold cavity, the sealed mold cavity is vacuumized, and the mold is heated at the same time, so that the temperature of the mold reaches 100-140 ℃. During resin infiltration, the resin film on which the nano conductive particles are laid on the surface of the fiber cloth can only be infiltrated in the thickness direction due to the action of the sealant, and the conductive particles form a concentration gradient in the thickness direction of the composite material due to the fact that the fiber cloth can obstruct the flow of the conductive nano particles.
4) And (5) curing the composite material. And (3) putting the fiber preformed body into a vacuum oven, and heating and curing according to the curing process conditions of the resin types to prepare a composite material part with the surface containing the nano conductive particles.
The nano conductive particles are one or more of carbon nano tubes, graphene, nano silver, nano nickel and the like, and the surfaces of the nano conductive particles can meet the actual dispersion requirements through different modification modes.
The resin containing the solvent is unsaturated polyester, epoxy resin, bismaleimide resin, cyanate resin and a corresponding solvent system thereof, or a mixture of a plurality of resins and a solvent system thereof.
The fiber cloth is woven by one or more fibers such as glass fiber, carbon fiber, aramid fiber and the like.
The sealant functions to restrict the resin flow direction and to allow the resin to infiltrate in the thickness direction. The sealant is high temperature resistant sealant such as rubber, polytetrafluoroethylene and the like.
The microporous filter membrane has the function of preventing the nanometer conductive particles from being discharged out of a curing system along with resin, and is made of nylon, polypropylene, polyether sulfone and other microporous filter membranes.
In the preparation method, the resin film infiltration auxiliary material mainly comprises a flow guide cloth, a rubber guide pipe and a vacuum bag which form the resin film infiltration system.
During the vacuum pumping treatment, the vacuum degree of the die cavity is preferably more than 0.09MPa, the heating temperature of the die is required to be between 110 and 140 ℃, the whole resin film infiltration time is preferably between 3 and 5 hours, and then the temperature is kept for 7 to 12 hours to be used as the precure of the resin.
In the above preform molding process, the pre-curing time and temperature are determined according to the curing characteristics of the resin system, and the preferred pre-curing system allows the first resin system to be properly cured while preventing the resin system from being completely cured.
The principle of the invention is shown in figure 1, a resin film 1 containing nano conductive particles is paved on a fiber cloth 2 through a resin film infiltration process, and the resin film infiltration process is completed through a heating die 3, so that the nano conductive particles are deposited on the surface of the composite material, the surface conductivity of the composite material is improved, and the lightning damage of the composite material is reduced.
Example 1
In this embodiment, for example, the cabin door of the airplane cabin is prepared, and the multi-walled carbon nanotubes are used to improve the surface conductivity of the carbon fiber reinforced cyanate ester composite material, so as to reduce the damage of lightning to the cabin door of the airplane cabin.
The specific method is that,
1) and (3) preparing a multi-wall carbon nanotube dispersed resin film. 0.5 part of hexadecylamine modified multi-walled carbon nanotube is added into 300 parts of dimethyl phthalate, mixed and dispersed for 3 hours under a high-speed stirrer, then 100 parts of N, N '- (4,4' -methylene diphenyl) is added, and the mixture is ultrasonically dispersed for 30 minutes at normal temperature and then stirred for 2 hours at high speed.
The dispersed mixture of multi-walled carbon nanotubes and resin was stirred at 180 ℃ for 12 hours and the solvent was removed by evaporation. Then, the temperature of the mixture was raised to 135 ℃, 86 parts of 2, 2' -diallylbisphenol A was added thereto, and the mixture was stirred for 40 minutes, and 186 parts of bisphenol A type cyanate ester was added thereto at 100 ℃ and stirred until it was clear. Heating the material to 190 ℃, adding 5 parts of film-forming agent polyether sulfone, stirring to dissolve the film-forming agent polyether sulfone in the resin, and stirring until the mixture is clear. And pouring the mixed mixture of the reinforcement and the resin system into an upper iron plate at 120 ℃, and cooling to room temperature to perform tape casting on the resin film.
2) And (5) shaping the carbon fiber preform. 300g/m selected for carbon fiber cloth2T300 unidirectional carbon fiber woven cloth. Firstly cutting a resin film and carbon fiber cloth according to the size of an airplane cabin door, then paving the cut carbon fiber cloth along the surface of a mold, then covering the resin film on the carbon fiber cloth, and finally sealing the periphery of the preformed body by using sealant 4 rubber.
3) And (4) forming the carbon fiber preform. According to the resin film infiltration process, a microporous filter membrane is laid on the preformed body, a vacuum diversion system is constructed on the microporous filter membrane, a mold is sealed by a vacuum bag membrane to form a closed mold cavity, the sealed mold cavity is vacuumized, the vacuum degree reaches 0.09MPa, the mold is heated to 120 ℃, the whole resin film infiltration time is 3 hours, and then the temperature is kept for 8 hours to perform pre-curing of the resin.
4) And (5) curing the composite material. Putting the carbon fiber preform into a vacuum oven, carrying out curing treatment at 200 ℃/5h +230 ℃/3h, cooling to room temperature along with the oven, obtaining the aircraft cabin door made of the carbon fiber composite material with the multi-wall carbon nanotube in gradient distribution along the thickness direction, wherein the surface resistance of the aircraft cabin door can reach 4 x 102square-1。
Example 2
In the embodiment, the preparation of the wings of the unmanned aerial vehicle is taken as an example, and the nano silver is adopted to improve the surface conductivity of the glass fiber reinforced epoxy resin composite material and reduce the damage of lightning to the wings of the unmanned aerial vehicle.
The specific method is that,
1) and preparing a nano silver dispersed resin film. Adding 1 part of nano silver into 300 parts of acetone, stirring at a high speed, adding 100 parts of novolac epoxy resin F-51, ultrasonically dispersing for 30 minutes at normal temperature, and then mixing and dispersing for 2 hours and 1 hour under a high-speed stirrer. The dispersed mixture of multi-walled carbon nanotubes and epoxy resin was stirred at 90 ℃ for 12 hours and the solvent was removed by evaporation. And then, raising the temperature of the material to 190 ℃, adding 5 parts of film-forming agent polyether sulfone, stirring to dissolve the film-forming agent polyether sulfone in the resin, then cooling to 120 ℃, adding 30 parts of high-temperature curing agent diaminodiphenyl sulfone, and stirring until the mixture is clear. And pouring the mixed mixture of the reinforcement and the resin system into an upper iron plate at the temperature of 130 ℃, and cooling to room temperature to perform tape casting on the resin film.
2) And (5) shaping the glass fiber preformed body. 480g/m selected from glass fiber cloth2The glass fiber woven cloth without twist. Firstly cutting a resin film and glass fiber cloth according to the size of an unmanned aerial vehicle wing, then paving and pasting the cut glass fiber cloth along the surface of a mould, then covering the resin film on the glass fiber cloth, and finally sealing the periphery of a preformed body by using a sealant 4 polytetrafluoroethylene.
3) And (4) forming a glass fiber pre-forming body. According to a resin film infiltration process, a microporous filter membrane is laid on the preformed body, a vacuum diversion system is constructed on the microporous filter membrane, a mold is sealed by a vacuum bag membrane to form a closed mold cavity, the sealed mold cavity is vacuumized, the vacuum degree reaches 0.095MPa, the mold is heated to 130 ℃, the whole resin film infiltration time is 4 hours, and then the temperature is kept for 9 hours to perform pre-curing of the resin.
4) And (5) curing the composite material. Putting the carbon fiber preformed body into a vacuum oven, carrying out curing treatment at 180 ℃/5h +200 ℃/3h, cooling to room temperature along with the oven, and obtaining the glass fiber composite material unmanned aerial vehicle wing with nano-silver distributed in a gradient manner along the thickness direction, wherein the surface resistance of the wing can reach 104square-1。

Claims (2)

1. A method for forming a composite material with a lightning protection effect is characterized by comprising the following steps:
1) preparing a resin film dispersed with nano conductive particles; mixing and dispersing the nano conductive particles and resin containing a solvent for 2-3 hours in a high-speed stirrer, dissolving a film-forming agent into the mixture of the dispersed nano conductive particles and the resin, and adding a high-temperature curing agent for mixing; pouring the obtained resin system on an iron plate at the temperature of 90-120 ℃ to form a resin film containing dispersed nano conductive particles by tape casting; the nano conductive particles are one or more of carbon nano tubes, graphene, nano silver and nano nickel; the resin containing the solvent is unsaturated polyester, epoxy resin, bismaleimide resin, cyanate resin and a corresponding solvent system thereof, or a mixture of a plurality of resins and a solvent system thereof; the high-temperature curing agent is one or more of aromatic polyamine, acid anhydride, resol and dicyandiamide;
2) shaping the fiber preformed body; firstly cutting a resin film and fiber cloth according to the size of a mold, then paving and sticking the cut fiber cloth along the surface of the mold, covering the resin film on the fiber cloth, and sealing the periphery of the preformed body by using a sealant; the fiber cloth is woven by one or more fibers of glass fiber, carbon fiber and aramid fiber, and the sealant is a rubber and polytetrafluoroethylene high-temperature-resistant sealant;
3) molding a fiber preformed body; according to the resin film infiltration process, a microporous filter membrane is laid on the preformed body, a vacuum diversion system is constructed on the microporous filter membrane, a mold is sealed by a vacuum bag membrane to form a mold cavity, the sealed mold cavity is vacuumized, and the mold is heated at the same time, so that the temperature of the mold reaches between 100 ℃ and 140 ℃;
4) curing the composite material; and (3) putting the fiber preformed body into a vacuum oven, and heating and curing according to the curing process conditions of the resin types to prepare a composite material part with the surface containing the nano conductive particles.
2. The method for forming a composite material with lightning protection function as claimed in claim 1, wherein the microporous membrane is a nylon, polypropylene or polyethersulfone microporous membrane.
CN201610517789.7A 2016-07-04 2016-07-04 Forming method of composite material with lightning protection effect Active CN106079481B (en)

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CN109808201B (en) * 2019-01-22 2020-08-18 西安交通大学 Preparation and forming method of nano gradient fiber reinforced wear-resistant composite material
CN111716835A (en) * 2020-06-19 2020-09-29 哈尔滨工业大学 Lightning protection composite material and preparation method thereof
CN115431605A (en) * 2022-07-25 2022-12-06 成都飞机工业（集团）有限责任公司 X-band stealth/lightning protection skin and preparation method thereof

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CN101891942A (en) * 2010-07-27 2010-11-24 沈阳航空航天大学 Method for preparing nanocomposite hybrid multi-dimension material

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CN101830095B (en) * 2010-03-10 2011-12-07 中国人民解放军国防科学技术大学 Composite material member with surface function layer and VIMP preparation method thereof
WO2014050896A1 (en) * 2012-09-26 2014-04-03 東邦テナックス株式会社 Prepreg and method for producing same
US9434139B2 (en) * 2014-05-01 2016-09-06 The Boeing Company Structural integrated repair method and system tool device for repairing delaminated composite structures

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CN101891942A (en) * 2010-07-27 2010-11-24 沈阳航空航天大学 Method for preparing nanocomposite hybrid multi-dimension material

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