CN112706427B - Lightning stroke protection, electromagnetic shielding and bearing integrated aviation material and preparation method thereof - Google Patents
Lightning stroke protection, electromagnetic shielding and bearing integrated aviation material and preparation method thereof Download PDFInfo
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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
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
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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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/545—Perforating, cutting or machining during or after moulding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2250/00—Layers arrangement
- B32B2250/20—All layers being fibrous or filamentary
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
- B32B2307/206—Insulating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
- B32B2307/212—Electromagnetic interference shielding
Abstract
The invention provides a lightning stroke protection, electromagnetic shielding and bearing integrated aviation material, which comprises the following components: the conductive layer is a nickel-plated flexible carbon fiber conductive layer, the carrier layer is a carbon fiber laminated plate, and the bonding layer is a resin insulating layer. The invention also provides a preparation method of the aviation material integrating lightning protection, electromagnetic shielding and bearing, which comprises the following steps: the nickel-plated flexible carbon fiber conducting layer is prepared by a chemical deposition method, and the carbon fiber laminated plate with the protection method is prepared by a hot-pressing process. The invention has the advantages of simple structure, low cost and the like, shows excellent protection performance in the aspects of lightning damage and electromagnetic wave interference, simultaneously shows good bearing capacity because the conductive layer substrate is made of carbon fiber material, and has wide application prospect in the aspect of aviation carbon fiber protection.
Description
Technical Field
The invention belongs to the field of material manufacturing, and particularly relates to an aviation material integrating lightning stroke protection, electromagnetic shielding and bearing and a preparation method thereof.
Background
As a representative of advanced composite materials, Fiber Reinforced resin matrix Composite (CFRP) has the advantages of low density, high mechanical strength and rigidity, excellent fatigue resistance and corrosion resistance, and the like, and is a necessary trend in large-scale application in passenger planes and military planes, for example, the usage amount of CR929CFRP which flies first in 2025 years in China is expected to reach 51%. Although the use of a large amount of CFRP can effectively improve passenger capacity and fuel efficiency of a passenger plane, when a lightning strike occurs, the CFRP serving as a semiconductor material cannot rapidly disperse and release current like a metal material, so that local temperature is instantly increased, structural part damage is caused, and flight safety is seriously threatened. In addition, the low impedance mismatch between the CFRP skin of the aircraft and the air can cause electromagnetic waves to create electromagnetic interference with electronics (e.g., radar) and harm the health of the flight crew. Therefore, in order to realize the mass use of CFRP in large airplanes, lightning protection and electromagnetic shielding are currently a key technology to be solved urgently. The existing patents of the method for lightning stroke damage and electromagnetic shielding protection of the aviation carbon fiber composite material are rare, and especially the research on the method in China just starts at present.
The invention which gives consideration to the lightning damage and the electromagnetic shielding protection method of the aviation carbon fiber composite material at present only has the following documents:
1. J.J.Producer et al, available from Seattle technologies, have invented a lightning strike and EMI shielding co-cured conductive surfacing film (CN 102317383B) for thermoset composites, in which a material having a resistivity of less than 500 milliohms/square is prepared using a thermoset resin, a toughening agent, a curing agent, and greater than 35 wt.% of silver flake, based on the total weight of the composition, and a conductive film having a film weight of 0.01 to 0.15psf (pounds per square foot) is useful for exterior aircraft component surfaces to provide lightning strike protection LSP) and EMI shielding. However, the invention uses silver flakes as conductive filler, which greatly increases the cost of the aviation component protection method.
2. Boeing a.o.schiff invented a method for manufacturing an integrated lightning strike protection material and (CN 102006995B) a.o.schiff et al devised an integrated lightning strike protection method suitable for automated laying onto a composite structure, the method comprising a surfacing layer 22 composed of an organic polymer resin, a conductive layer 24 of an expanded metal foil, a spacer/adhesion layer, a carrier paper layer 26 and a carrier layer 28. The protection method mainly highlights the advantages of integration, effectively solves the problems of time consumption, high labor intensity, unstable method and the like caused by the layered laying of a multilayer method, but the weight of the protection method is increased by extending the metal foil for the conducting layer of the integration method, so that the weight of the airplane is increased, and the weight of the airplane is contrary to the weight reduction target.
3. Yixiaosu et al invented a lightweight lightning strike protection surface layer and a preparation and use method (CN 107825810B) thereof, the lightning strike protection surface layer comprises a continuous conductive network, a matrix, an energy-absorbing component and a conductive filler, the thickness of the lightning strike protection surface layer is 10-500 μm, the mass per unit area is 20-500 g/m2, and the diameter of the fiber forming the conductive network is 1-20 μm; the particle size of the energy-absorbing component is 0.1-300 mu m, and the mass ratio of the energy-absorbing component in the resin matrix is 5-50%; the particle size of the conductive filler is 10 nm-100 mu m, the content of the conductive filler is 0-40% of the mass content of the matrix, the material has good flexibility and material and process compatibility, can realize co-curing in different composite material curing processes, and is suitable for surface protection treatment of complex workpieces, but the protection method does not mention electromagnetic wave protection and bearing.
In conclusion, the existing aviation carbon fiber structural part lightning stroke protection method has the problems of heavy weight, complex structure, single function, insufficient mechanical property and the like. Therefore, it is necessary to design a material capable of solving the above problems.
Disclosure of Invention
The invention is carried out to solve the problems and aims to provide an aviation material integrating lightning stroke protection, electromagnetic shielding and bearing and a preparation method thereof.
The invention provides a lightning stroke protection, electromagnetic shielding and bearing integrated aviation material, which is characterized by comprising the following components in percentage by weight: the conductive layer is a nickel-plated flexible carbon fiber conductive layer, the carrier layer is a carbon fiber laminated plate, and the bonding layer is a resin insulating layer.
The invention also provides a preparation method of the integrated aviation material for lightning stroke protection, electromagnetic shielding and bearing, which is characterized by comprising the following steps of: step 1, adding 4-10 g of stannous chloride and 2-5 mL of hydrochloric acid into 400mL of deionized water to prepare sensitizing solution, immersing a prepared flexible carbon fiber cloth into the sensitizing solution, magnetically stirring for 15min at 20-40 ℃, washing with deionized water for multiple times to obtain sensitized flexible carbon fiber cloth, and drying for later use; step 2, adding 0.01-0.05 g of palladium chloride and 0.1-0.5 mL of hydrochloric acid into 400mL of deionized water to prepare an activation solution, immersing the sensitized flexible carbon fiber cloth into the activation solution, magnetically stirring for 20-40 min at 30 ℃, washing with deionized water for multiple times to obtain the activated flexible carbon fiber cloth, and drying for later use; step 3, adding 4-10 g of nickel chloride hexahydrate and 6-15 g of sodium citrate into 400mL of deionized water, then adding ammonia water at 24-50 ℃ to prepare a plating solution, immersing the activated flexible carbon fiber cloth into the plating solution, raising the temperature of the plating solution to 70-90 ℃ under magnetic stirring for later use, then dissolving 6-15 g of sodium hypophosphite into 40mL of deionized water to prepare a reducing solution, dropwise adding the reducing solution into the plating solution, reacting for 30min, washing the flexible carbon fiber plated with metallic nickel with deionized water for multiple times, and drying to obtain the nickel-plated flexible carbon fiber conducting layer; step 4, laying the carbon fiber prepreg into a mold, then placing the mold and the carbon fiber prepreg on a hot press together for heating treatment, then naturally cooling to room temperature, and cutting the cured carbon fiber laminated plate into a specified size for later use; and 5, adhering the nickel-plated flexible carbon fiber conducting layer to the surface of the carbon fiber laminated plate by adopting an epoxy adhesive film through a hot pressing process, and curing to obtain the carbon fiber laminated plate with a protective effect, namely the carbon fiber protective material.
In the method for preparing the integrated aviation material with lightning stroke protection, electromagnetic shielding and bearing, the method can also have the following characteristics: in the steps 1 to 3, the deionized water is washed for 3 to 4 times.
The lightning stroke protection, electromagnetic shielding and bearing provided by the inventionThe preparation method of the integrated aviation material can also have the following characteristics: wherein in the step 4, [45/0/-45/90 is adopted]2SAnd laying the carbon fiber prepreg into the mold in a laying mode.
In the method for preparing the integrated aviation material with lightning stroke protection, electromagnetic shielding and bearing, the method can also have the following characteristics: wherein, in the step 4, the cutting size is 150mm multiplied by 100mm multiplied by 3 mm.
In the method for preparing the integrated aviation material with lightning stroke protection, electromagnetic shielding and bearing, the method can also have the following characteristics: in step 4, the temperature raising process includes the following substeps: firstly, heating the mould and the carbon fiber prepreg to 90 ℃ together, keeping the temperature for 1.5h, then heating to 120 ℃, and finally keeping the temperature for 1.5h under 5 Mpa.
In the method for preparing the integrated aviation material with lightning stroke protection, electromagnetic shielding and bearing, the method can also have the following characteristics: in step 5, the curing process includes the following substeps: firstly heating to 70-90 ℃ and keeping for 10-30 min under 1-4 MPa, then heating to 100-120 ℃ and keeping for 40-70 min under 1-4 MPa.
Action and Effect of the invention
According to the integrated aviation material for lightning protection, electromagnetic shielding and bearing and the preparation method thereof, flexible carbon fiber cloth is selected as the base material of the conducting layer, after the metal nickel is successfully plated by using the chemical deposition method, the conducting layer forms a double-conducting network respectively taking the carbon fiber and the metal nickel as the channels, and the high conducting performance is realized under the condition of low metal content.
In addition, the conductive layer substrate and the laminated plate are both made of carbon fibers, so that compared with other lightning protection methods, the mechanical property of the composite material structural member is greatly enhanced, the considerable bearing performance is shown, and the conductive layer substrate and the laminated plate have wide application prospects in the aspect of aviation carbon fiber protection.
In conclusion, the lightning protection device is simple in structure, economical and practical, lightning damage protection and electromagnetic interference shielding are simultaneously considered through the design of the double-conducting network, so that the lightning protection device has excellent protection effects on both lightning damage and electromagnetic interference, lightning current is effectively prevented from being conducted to the carbon fiber laminated plate through the design of the insulating layer, the damage of the lightning current to the carbon fiber laminated plate is greatly weakened, and a good lightning damage protection effect is achieved.
Drawings
FIG. 1 is a view of a carbon fiber laminate with a protective effect according to the present invention;
FIG. 2 is a lightning strike damage diagram of the carbon fiber laminate with protection effect in the invention;
FIG. 3 is a graph of the electromagnetic shielding performance of the carbon fiber laminate with protection of the present invention;
FIG. 4 is a graph of the compressive performance of the carbon fiber laminate with protective effect after lightning strike in the invention.
Detailed Description
In order to make the technical means and functions of the present invention easy to understand, the present invention is specifically described below with reference to the embodiments and the accompanying drawings.
As shown in FIG. 1, the integrated aviation material for lightning protection, electromagnetic shielding and bearing of the invention comprises: the conductive layer is a nickel-plated flexible carbon fiber conductive layer, the insulating layer is a resin insulating layer, and the resin insulating layer is a carbon fiber laminated plate.
The invention also provides a preparation method of the aviation material integrating lightning protection, electromagnetic shielding and bearing, which comprises the following steps:
1. preparation of nickel-plated flexible carbon fiber conducting layer by chemical deposition method
Step 1, adding 4-10 g of stannous chloride and 2-5 mL of hydrochloric acid into 400mL of deionized water to prepare a sensitizing solution, immersing the prepared flexible carbon fiber cloth into the sensitizing solution, magnetically stirring for 15min at 20-40 ℃, washing for 3-4 times with deionized water to obtain the sensitized flexible carbon fiber cloth, and drying for later use.
And 2, adding 0.01-0.05 g of palladium chloride and 0.1-0.5 mL of hydrochloric acid into 400mL of deionized water to prepare an activation solution, immersing the sensitized flexible carbon fiber cloth into the activation solution, magnetically stirring for 20-40 min at 30 ℃, washing for 3-4 times by using the deionized water to obtain the activated flexible carbon fiber cloth, and drying for later use.
And 3, adding 4-10 g of nickel chloride hexahydrate and 6-15 g of sodium citrate into 400mL of deionized water, then adding ammonia water at 24-50 ℃ to prepare a plating solution, immersing the activated flexible carbon fiber cloth into the plating solution, raising the temperature of the plating solution to 70-90 ℃ under magnetic stirring for later use, then dissolving 6-15 g of sodium hypophosphite into 40mL of deionized water to prepare a reducing solution, dropwise adding the reducing solution into the plating solution, reacting for 30min, washing the flexible carbon fiber plated with metallic nickel with deionized water for 3-4 times, and drying to obtain the nickel-plated flexible carbon fiber conducting layer.
2. Carbon fiber laminated plate with protection effect prepared by hot pressing process
Step 4, adopting [45/0/-45/90 for carbon fiber prepreg]2SLaying the carbon fiber laminated board in a laying mode into a mould, then placing the mould and the carbon fiber prepreg on a hot press together for heating treatment, then naturally cooling to room temperature, and cutting the cured carbon fiber laminated board into the size of 150mm multiplied by 100mm multiplied by 3mm for later use.
In the present invention, the temperature raising process includes the following substeps: firstly, heating the mould and the carbon fiber prepreg to 90 ℃ together, keeping the temperature for 1.5h, then heating to 120 ℃, and finally keeping the temperature for 1.5h under 5 Mpa.
And 5, adhering the nickel-plated flexible carbon fiber conducting layer to the surface of the carbon fiber laminated plate by adopting an epoxy adhesive film through a hot pressing process, and curing to obtain the carbon fiber laminated plate with a protective effect, namely the carbon fiber protective material.
In the present invention, the curing process comprises the following substeps: firstly heating to 70-90 ℃ and keeping for 10-30 min under 1-4 MPa, then heating to 100-120 ℃ and keeping for 40-70 min under 1-4 MPa.
< example 1>
Step 1, adding 4g of stannous chloride and 2mL of hydrochloric acid into 400mL of deionized water to prepare sensitizing solution, immersing a prepared flexible carbon fiber cloth into the sensitizing solution, magnetically stirring for 15min at 30 ℃, washing for 3-4 times by using the deionized water to obtain the sensitized flexible carbon fiber cloth, and drying for later use.
And 2, adding 0.02g of palladium chloride and 0.2mL of hydrochloric acid into 400mL of deionized water to prepare an activation solution, immersing the sensitized flexible carbon fiber cloth into the activation solution, magnetically stirring for 15min at 30 ℃, washing for 3-4 times by using the deionized water to obtain the activated flexible carbon fiber cloth, and drying for later use.
And 3, adding 4g of nickel chloride hexahydrate and 6g of sodium citrate into 400mL of deionized water, then adding 24mL of ammonia water to prepare a plating solution, immersing the activated flexible carbon fiber cloth into the plating solution, raising the temperature of the mixed solution to 85 ℃ under magnetic stirring, dissolving 6g of sodium hypophosphite into 20mL of deionized water to prepare a reducing solution, dropwise adding the reducing solution into the plating solution, reacting for 30min, washing the flexible carbon fiber plated with metallic nickel with the deionized water for 3-4 times, and drying to obtain the nickel-plated flexible carbon fiber conducting layer.
Step 4, the carbon fiber prepreg is processed according to the specification of [45/0/-45/90 ]]2SLaying the carbon fiber laminated board in a laying mode into a mould, then placing the mould and the prepreg on a hot press together, heating to 90 ℃ together, keeping the temperature for 1.5h, then heating to 120 ℃, keeping the temperature for 1.5h under 5Mpa, naturally cooling to room temperature, and cutting the cured carbon fiber laminated board into the carbon fiber laminated board with the thickness of 150mm multiplied by 100mm multiplied by 3mm for later use.
And 5, adhering the nickel-plated flexible carbon fibers to the surface of the carbon fiber laminated plate by using an epoxy adhesive film through a hot pressing process to obtain the carbon fiber laminated plate with the protection effect. The curing process comprises the following steps: first heated to 80 ℃ and kept at 1MPa for 10min, then heated to 100 ℃ and kept at 1MPa for 30 min.
As shown in fig. 2-4, after the carbon fiber laminate is subjected to the waveform D lightning current discharge test, the conductive layer on the surface of the carbon fiber laminate has a significant damage, but the damage of the carbon fiber composite material serving as the carrier layer is extremely small, which fully highlights the effectiveness of the embodiment in lightning strike damage. Meanwhile, due to the increase of the flexible carbon fiber protective material, the average electromagnetic shielding effectiveness of the carbon fiber laminated plate is increased from 39.77dB to 58.11dB, the electromagnetic shielding effectiveness of the carbon fiber laminated plate is effectively improved, when the nickel-plated flexible carbon fiber protective material is added, the average electromagnetic shielding performance of the composite material reaches 92.87dB, and the effectiveness of the protective material in the aspect of electromagnetic shielding is proved. In addition, the residual mechanical property after lightning strike damage before and after nickel plating is tested, and the addition of the metallic nickel can greatly improve the compression strength of the composite material and effectively improve the bearing capacity of the composite material.
< example 2>
Step 1, adding 8g of stannous chloride and 4mL of hydrochloric acid into 400mL of deionized water to prepare sensitizing solution, immersing flexible carbon fiber cloth prepared in advance into the sensitizing solution, magnetically stirring for 15min at 30 ℃, washing with deionized water for 3-4 times to obtain sensitized flexible carbon fiber cloth, and drying for later use.
And 2, adding 0.04g of palladium chloride and 0.4mL of hydrochloric acid into 400mL of deionized water to prepare an activation solution, immersing the sensitized flexible carbon fiber cloth into the activation solution, magnetically stirring for 15min at 30 ℃, washing for 3-4 times by using the deionized water to obtain the activated flexible carbon fiber cloth, and drying for later use.
And 3, adding 8g of nickel chloride hexahydrate and 12g of sodium citrate into 400mL of deionized water, then adding 48mL of ammonia water to prepare a plating solution, immersing the activated flexible carbon fiber cloth into the plating solution, raising the temperature of the mixed solution to 85 ℃ under magnetic stirring, dissolving 12g of sodium hypophosphite into 40mL of deionized water to prepare a reducing solution, dropwise adding the reducing solution into the plating solution, reacting for 30min, washing the flexible carbon fiber plated with metallic nickel with the deionized water for 3-4 times, and drying to obtain the nickel-plated flexible carbon fiber conducting layer.
Step 4, the carbon fiber prepreg is processed according to the specification of [45/0/-45/90 ]]2SLaying the carbon fiber laminated board in a laying mode into a mould, then placing the mould and the prepreg on a hot press together, heating to 90 ℃ together, keeping the temperature for 1.5h, then heating to 120 ℃, keeping the temperature for 1.5h under 5Mpa, naturally cooling to room temperature, and cutting the cured carbon fiber laminated board into the carbon fiber laminated board with the thickness of 150mm multiplied by 100mm multiplied by 3mm for later use.
And 5, adhering the nickel-plated flexible carbon fibers to the surface of the carbon fiber laminated plate by using an epoxy adhesive film through a hot pressing process to obtain the carbon fiber laminated plate with the protection effect. The curing process comprises the following steps: first to 90 ℃ and held at 2MPa for 20min, then to 115 ℃ and held at 2MPa for 60 min.
Effects and effects of the embodiments
According to the embodiment, when the carbon fiber laminated plate is subjected to a discharge test by adopting the waveform D lightning current, the damage of the carbon fiber composite material serving as the carrier layer is extremely small; when the carbon fiber laminated plate is subjected to an electromagnetic shielding test, the average electromagnetic shielding effectiveness is improved; when the carbon fiber laminated plate is subjected to a residual mechanical property test after lightning damage before and after nickel plating, the compressive strength of the composite material is improved by adding the metallic nickel.
According to the integrated aviation material for lightning protection, electromagnetic shielding and bearing and the preparation method thereof, flexible carbon fiber cloth is selected as the base material of the conducting layer, after the metal nickel is successfully plated by using the chemical deposition method, the conducting layer forms a double-conducting network respectively taking the carbon fiber and the metal nickel as the channels, and the high conducting performance is realized under the condition of low metal content.
In addition, the conductive layer substrate and the laminated plate are both made of carbon fibers, so that compared with other lightning protection methods, the mechanical property of the composite material structural member is greatly enhanced, the considerable bearing performance is shown, and the conductive layer substrate and the laminated plate have wide application prospects in the aspect of aviation carbon fiber protection.
In conclusion, the lightning protection device is simple in structure, economical and practical, lightning damage protection and electromagnetic interference shielding are simultaneously considered through the design of the double-conducting network, so that the lightning protection device has excellent protection effects on both lightning damage and electromagnetic interference, lightning current is effectively prevented from being conducted to the carbon fiber laminated plate through the design of the insulating layer, the damage of the lightning current to the carbon fiber laminated plate is greatly weakened, and a good lightning damage protection effect is achieved.
The above embodiments are preferred examples of the present invention, and are not intended to limit the scope of the present invention.
Claims (6)
1. The utility model provides a thunderbolt protection, electromagnetic shield and bear integration aviation carbon fiber protective material which characterized in that includes: a conductive layer and a carrier layer,
wherein the carrier layer is bonded to the surface of the conductive layer by an adhesive layer, and the adhesive layer serves as an insulating layer for isolating current,
the conducting layer is a nickel-plated flexible carbon fiber conducting layer, the carrier layer is a carbon fiber laminated plate, the bonding layer is a resin insulating layer,
the preparation method of the aviation carbon fiber protective material integrating lightning protection, electromagnetic shielding and bearing comprises the following steps:
step 1, adding 4-10 g of stannous chloride and 2-5 mL of hydrochloric acid into 400mL of deionized water to prepare sensitizing solution, immersing a prepared flexible carbon fiber cloth into the sensitizing solution, magnetically stirring for 15min at 20-40 ℃, washing with deionized water for multiple times to obtain sensitized flexible carbon fiber cloth, and drying for later use;
step 2, adding 0.01-0.05 g of palladium chloride and 0.1-0.5 mL of hydrochloric acid into 400mL of deionized water to prepare an activation solution, immersing the sensitized flexible carbon fiber cloth into the activation solution, magnetically stirring for 20-40 min at 30 ℃, washing with deionized water for multiple times to obtain the activated flexible carbon fiber cloth, and drying for later use;
step 3, adding 4-10 g of nickel chloride hexahydrate and 6-15 g of sodium citrate into 400mL of deionized water, then adding ammonia water at 24-50 ℃ to prepare a plating solution, immersing the activated flexible carbon fiber cloth into the plating solution, raising the temperature of the plating solution to 70-90 ℃ under magnetic stirring for later use, then dissolving 6-15 g of sodium hypophosphite into 40mL of deionized water to prepare a reducing solution, dropwise adding the reducing solution into the plating solution, reacting for 30min, washing the flexible carbon fiber plated with metallic nickel with deionized water for multiple times, and drying to obtain the nickel-plated flexible carbon fiber conducting layer;
step 4, paving carbon fiber prepreg into a mold, then placing the mold and the carbon fiber prepreg on a hot press together for heating treatment, then naturally cooling to room temperature, and cutting the cured carbon fiber laminated plate into a specified size for later use;
and 5, adhering the nickel-plated flexible carbon fiber conducting layer to the surface of a carbon fiber laminated plate by adopting an epoxy adhesive film through a hot pressing process, and curing to obtain the carbon fiber laminated plate with a protective effect, namely the carbon fiber protective material.
2. The integrated aviation carbon fiber protective material for lightning stroke protection, electromagnetic shielding and bearing according to claim 1, characterized in that:
in the steps 1 to 3, the deionized water is washed for 3 to 4 times.
3. The integrated lightning protection, electromagnetic shielding and load bearing aviation carbon fiber protective material as claimed in claim 1, wherein:
wherein in the step 4, [45/0/-45/90 is adopted]2SAnd laying the carbon fiber prepreg into the mold in a laying mode.
4. The integrated aviation carbon fiber protective material for lightning stroke protection, electromagnetic shielding and bearing according to claim 1, characterized in that:
wherein, in the step 4, the cutting size is 150mm multiplied by 100mm multiplied by 3 mm.
5. The integrated lightning protection, electromagnetic shielding and load bearing aviation carbon fiber protective material as claimed in claim 1, wherein:
in the step 4, the temperature raising process includes the following substeps: firstly, heating the mould and the carbon fiber prepreg to 90 ℃ together, keeping the temperature for 1.5h, then heating to 120 ℃, and finally keeping the temperature for 1.5h under 5 Mpa.
6. The integrated aviation carbon fiber protective material for lightning stroke protection, electromagnetic shielding and bearing according to claim 1, characterized in that:
wherein, in the step 5, the curing process comprises the following substeps: firstly heating to 70-90 ℃ and keeping for 10-30 min under 1-4 MPa, then heating to 100-120 ℃ and keeping for 40-70 min under 1-4 MPa.
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