CN112124556A - Multifunctional skin structure and preparation method thereof - Google Patents
Multifunctional skin structure and preparation method thereof Download PDFInfo
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- CN112124556A CN112124556A CN202011049441.2A CN202011049441A CN112124556A CN 112124556 A CN112124556 A CN 112124556A CN 202011049441 A CN202011049441 A CN 202011049441A CN 112124556 A CN112124556 A CN 112124556A
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- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical group [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
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- 239000003822 epoxy resin Substances 0.000 claims description 3
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- 229910052759 nickel Inorganic materials 0.000 claims description 3
- 229920003192 poly(bis maleimide) Polymers 0.000 claims description 3
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Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
-
- 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
- B29L2031/3085—Wings
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention provides a multifunctional skin structure and a preparation method thereof, relates to the technical field of aviation manufacturing, can have lightning protection and electric heating anti-icing and deicing functions, is simple in preparation method, does not need to enter an autoclave for many times, and is low in cost; the structure is a layered structure which sequentially comprises a conducting layer, a first insulating layer, a heating layer, a second insulating layer and a bearing layer; the conductive layer is used for providing a lightning path; the first insulating layer and the second insulating layer are used for positioning the heating layer and protecting the bearing layer from being subjected to different potential corrosion; the heating layer is used for electrically heating to prevent and remove ice; the bearing layer is used for providing bearing functions for other layers. The technical scheme provided by the invention is suitable for the aviation manufacturing process.
Description
[ technical field ] A method for producing a semiconductor device
The invention relates to the technical field of aviation manufacturing, in particular to a multifunctional skin structure and a preparation method thereof.
[ background of the invention ]
When the airplane flies under the icing meteorological condition at the subsonic speed less than a certain critical Mach number, the windward surfaces of some parts, such as wing slats, can be iced due to the impact and accumulation of supercooled water drops in the atmosphere, the aerodynamic appearance of the airplane can be obviously affected, and the aerodynamic performance is deteriorated, and the control performance and the stability are reduced. The radial section of the front edge of the nacelle of the engine and wing slats have similar aerodynamic shapes, the thrust of the engine can be reduced due to icing of the air inlet channel, and when an ice layer in the air inlet channel falls off and enters the inside of the engine along with airflow, blades rotating at high speed can be injured, even the engine is damaged, and therefore icing protection is needed.
Ice protection is provided by a number of methods, such as: super-hydrophobic materials (CN206636710U), carbon nano-tubes (CN110744833A) or micro-fiber structures (CN206602672U) and the like are added, wherein the electric heating deicing control heating efficiency is high and the coverage range is wide when the electric heating layer is embedded into the surface of the protection area; compared with a metal structure, the fuel consumption can be greatly reduced by using a large amount of composite materials on the airplane structure, but wing slats and the front edge of a nacelle belong to high-probability surfaces subjected to initial lightning adhesion, the composite materials are high-impedance materials, high voltage drop can be caused when lightning current flows through the composite material structure, the composite material structure is broken down, the flight safety is seriously threatened, and therefore the lightning protection function is required.
The manufacturing difficulty of the multifunctional skin structure lies in the integration and integrated manufacturing of the electric heating layer, the lightning protection layer and the composite material layer. The electric heating layer is generally manufactured by adopting a metal thermal spraying process in the manufacturing process, molten metal is sprayed on the surface of a base material in a high-speed particle flow mode to generate a coating, the outlet temperature (about 3000 ℃) and the particle speed (500m/s-2100m/s) of a thermal spraying nozzle are very high, the visual distances and parameters of the coating sprayed on the surface of the base material are different, the resin softening temperature of the thermosetting composite material is about 180 ℃, the use temperature of the thermosetting prepreg is about 80 ℃, the resin in the composite material prepreg is easy to cure and deform in advance due to high temperature and high impact during spraying, and the prior solution methods are of two types.
The first method is to spray the cured composite pre-impregnated fiber surface and mechanically join it to the loaded composite structure. Such solutions greatly increase the assembly effort and weight, require multiple curing, are costly, and reduce the continuity of the surface heating zone. The second method is to select high temperature resistant thermoplastic composite materials such as polyetheretherketone PEEK, polyimide PI and polyetherimide PEI (patent FR 293967). Because the PEEK resin melting temperature is 340 ℃, the PEI melting temperature is 220 ℃, the PI melting point is 334 ℃, and the use temperature of the thermoplastic prepreg is about 120 ℃, the method has high requirements on the parameter interval of thermal spraying and has low heating layer bonding strength.
Accordingly, there is a need to develop a multifunctional skin structure and a method for manufacturing the same that address the deficiencies of the prior art to address or mitigate one or more of the problems set forth above.
[ summary of the invention ]
In view of the above, the invention provides a multifunctional skin structure and a preparation method thereof, which have lightning protection and electric heating deicing prevention functions, are simple in preparation method, do not need to enter an autoclave for many times, and are low in cost.
On one hand, the invention provides a multifunctional skin structure which is characterized in that the skin structure is a layered structure, and the layered structure sequentially comprises a conducting layer, a first insulating layer, a heating layer, a second insulating layer and a bearing layer;
the conductive layer is used for providing a lightning path;
the first insulating layer and the second insulating layer are used for positioning the heating layer and protecting the bearing layer from being subjected to different potential corrosion;
the heating layer is used for electrically heating to prevent and remove ice;
the bearing layer is used for providing bearing functions for other layers.
The above aspect and any possible implementation further provide an implementation, wherein the conductive layer is a mesh structure or a loop structure.
The above aspect and any possible implementation manner further provide an implementation manner, wherein the thickness of the conductive layer is 0.1-0.2mm, and the area density is 107g/m2～190g/m2。
The above aspects and any possible implementation manners further provide an implementation manner, and the material of the first insulating layer and/or the second insulating layer is a glass fiber fabric, a dry fiber or other insulating materials with a softening temperature of not lower than 1600 ℃.
The above aspect and any possible implementation further provide an implementation in which the first insulating layer has a thickness within 0.5mm, and the second insulating layer has a thickness greater than the thickness of the first insulating layer.
The above-described aspects and any possible implementations further provide an implementation in which the heating layer is a copper-based or nickel-based material.
The above aspect and any possible implementation further provides an implementation in which the material of the carrier layer is a fiber fabric or dry fiber, and the thickness is greater than 1.5 mm.
The above aspect and any possible implementation further provide an implementation in which a thickness of the heating layer is less than 0.1 mm.
The above aspect and any possible implementation manner further provide an implementation manner that the skin structure is a combined structure of any one or two or more of a planar structure, a bent structure and an arc structure.
In another aspect, the invention provides a method for manufacturing a multifunctional skin structure, wherein the method is used for manufacturing the skin structure as described in any one of the above;
the preparation method comprises the following steps:
s1, preparing a second insulating layer in a paving mode;
s2, preparing a heating layer on the surface of the second insulating layer in a thermal spraying mode to obtain a first intermediate;
s3, preparing a bearing layer in a paving mode in a mould;
s4, transferring the first intermediate onto the bearing layer;
s5, preparing a first insulating layer on the surface of the heating layer in a paving mode;
s6, paving a conducting layer on the surface of the first insulating layer to obtain a preformed body;
and S7, injecting resin into the pre-formed body in a vacuum environment, cooling and shaping, and then demoulding to obtain the skin structure with the required shape.
The above-mentioned aspect and any possible implementation manner further provide an implementation manner, and the content of step S7 includes: the preform is bagged and evacuated and resin is injected from the top of the bag.
The above aspects and any possible implementations further provide an implementation where the resin is any one of an epoxy resin, an unsaturated polyester resin, a vinyl resin, and a bismaleimide resin.
In a further aspect, the invention provides an aircraft slat characterised in that it is manufactured using a skin structure as described in any preceding claim.
In a further aspect, the present invention provides an aircraft nacelle leading edge structure, wherein the aircraft nacelle leading edge structure is partially or wholly made using a skin structure as defined in any one of the above.
Compared with the prior art, the invention can obtain the following technical effects: the thermal influence of the metal layer prepared by thermal spraying on the resin in the composite material is greatly reduced, and the use variety and the spraying parameter interval of the composite material are expanded; the lightning protection and electric heating functions are achieved; the integration level is high, and the overall weight is reduced; the preparation method is simple, does not need to enter an autoclave for many times, and has low cost.
Of course, it is not necessary for any one product in which the invention is practiced to achieve all of the above-described technical effects simultaneously.
[ description of the drawings ]
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic view of a multi-functional skin structure provided by one embodiment of the present invention;
FIG. 2 is an illustration of an aircraft slat of a skin structure provided by an embodiment of the present invention;
FIG. 3 is a view of the configuration of the leading edge of an aircraft nacelle provided in accordance with one embodiment of the invention;
FIG. 4 is a schematic view of a spray heater layer provided by one embodiment of the present invention;
FIG. 5 is a schematic illustration of a finished lay-up skin structure provided by one embodiment of the present invention;
FIG. 6 is a schematic view of a liquid molding process provided by one embodiment of the present invention.
[ detailed description ] embodiments
For better understanding of the technical solutions of the present invention, the following detailed descriptions of the embodiments of the present invention are provided with reference to the accompanying drawings.
It should be understood that the described embodiments are only some embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the examples of the present invention and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
Aiming at the defects of the prior art, the invention provides a multifunctional skin structure and a preparation method thereof, wherein the structure integrates the functions of electric heating ice prevention, lightning protection and bearing; the preparation method is simple, the influence of the spraying process of the electric anti-icing and deicing heating layer on the temperature resistance of the composite material structure is eliminated, and the autoclave is not required to be fed for curing for many times.
Firstly, structure introduction:
the structure is a skin structure and is a five-layer composite structure. As shown in fig. 1, the skin structure includes a conductive layer 1, a first insulating layer 2, a heating layer 3, a second insulating layer 4, and a bearing layer 5 in this order. The conductive layer is generally 0.1-0.2mm and has an areal density in the range of 107g/m2-190g/m2(ii) a The thickness of the heating layer can be changed according to the power requirement and the metal type, the smaller the thickness is, the larger the resistance is, and the larger the thickness is, the smaller the resistance of the metal layer is, generally less than 0.1 mm; the thickness of the bearing layer can be generally larger than 1.5mm according to the stress condition of the part and the used material; to ensure that heat is conducted away to the outer surface to be heated, while protecting the carrier layer 5, the thickness of the insulating layer 4 should at least ensure adequate thermal insulation, and is generally greater than the insulating layer 2, the insulating layer 2 generally being within 0.5 mm.
The conducting layer 1 is made of a metal wire mesh or a conducting polymer mesh material, can provide a lightning path, avoids lightning from puncturing a composite material structure, and greatly improves the permeation efficiency of injection resin in the preparation process. The conductive layer 1 may also be loop-shaped.
The first insulating layer 2 and the second insulating layer 4 are made of insulating materials, such as glass fiber fabrics or dry fibers (the softening temperature is about 1600 ℃), and resin in the prepreg is not cured in advance due to the fact that the insulating layers do not contain resin and high temperature and high impact force in the spraying process, so that high-temperature damage to the composite material structure in the direct spraying process is avoided in the manufacturing process, and the adaptability to the curved surface structure is good when the mold transfer is carried out; because the insulating layer can resist high temperature and high impact in the heat spraying process, the carbon fiber laminated structure of the inner layer can be prevented from forming different potential corrosion, and the upper and lower insulating layers can also provide a positioning function for the heating layer 3 in the liquid forming process.
The heating layer 3 is distributed between the upper and lower insulating layers, and can select metal materials with high bonding strength of the insulating layers, such as copper-based materials and nickel-based materials.
The bottom layer is a bearing layer 5 which mainly provides a bearing function and is made of fiber fabrics, dry fibers and the like.
The skin structure of the present invention may be applied to aircraft slat or nacelle leading edge structures. The skin structure described above is shown in fig. 2 when applied to an aircraft slat and in fig. 3 when applied to a nacelle leading edge structure. The structure is required to be used in the anti-icing area and the lip of the nacelle in the front edge structure of the nacelle for one circle.
Secondly, the overall forming method comprises the following steps:
the skin structure is manufactured using a VARI liquid forming process. The main forming process comprises the following steps: laying a second insulating layer 4 → spraying a preparation heating layer 3 on the surface of the second insulating layer 4 → laying a bearing layer 5 on a mold → transferring the heating layer 3 and the second insulating layer 4 onto the bearing layer 5 → laying a first insulating layer 2 on the surface of the heating layer 3 → laying a conductive layer 1 on the surface of the first insulating layer 2 → preheating the mold → bagging the preform, preparing for injection resin → evacuation → pressure maintaining → injection resin → cooling and shaping → demoulding.
Resin is injected from the top end, the conducting layer 1 on the outermost layer is in a net material or loop shape, the resin flow can be promoted, the permeability of the injected resin is improved, and the resin can permeate the heating layer to permeate into the bearing layer on the bottom layer after the resin is injected; after solidification, the layer has the function of lightning protection. The resin selected for injection may be any one of epoxy resin, unsaturated polyester resin, vinyl resin, and bismaleimide resin.
The skin structure can integrate three functions of lightning protection, electric heating ice prevention and removal and bearing; the thermal influence of the metal layer prepared by thermal spraying on the resin in the composite material is greatly reduced, and the use variety and the spraying parameter interval of the composite material are expanded; the integration level is high, and the overall weight is reduced; the preparation method is simple, does not need to enter an autoclave for many times, and has low cost. The structure is not limited to a planar structure.
When the heating layer 3 is prepared, the second insulating layer 4 is firstly paved, then the electric heating film is processed by adopting a metal thermal spraying technology, and different shapes such as a square-shaped shape, a grid shape, a fold line shape and the like are sprayed on the surface of the second insulating layer according to the design requirement of heating power, as shown in fig. 4. Because the insulating layer does not have resin, the high temperature and the high impact force in the spraying process can not generate the advanced curing of the resin in the prepreg, and the resin can permeate into the bearing layer of the bottom layer through the heating layer after being injected. And metal interfaces are reserved at two ends to be connected with power supply cables.
After the heating layer 3 is prepared, a mold is prepared, a bearing layer is laid, the heating layer and the second insulating layer are transferred to the upper side of the bearing layer, the first insulating layer 2 and the conducting layer 1 are sequentially laid, and the upper insulating layer and the lower insulating layer play roles in positioning and protecting the heating layer. The finished skin structure is shown in figure 5.
And after paving, injecting resin into the top end of the mold, and curing according to the curing process curve of the resin. And demolding to obtain the integrated electric anti-icing composite material structure. The system structure of the resin injection is shown in fig. 6. The preformed body is placed in a vacuum bag, and the vacuum bag is formed by vacuumizing through vacuum pumps on two sides of the bag body. And injecting resin from the top end of the preformed body through a resin tank and a pipeline, cooling and shaping, and then demolding to obtain the integrated electric anti-icing composite material structure.
The multifunctional integrated structure with the functions of electric heating ice prevention and lightning protection and the preparation method thereof provided by the invention can have the functions of electric heating ice prevention and lightning protection, are highly integrated with a composite material, do not need mechanical connection, enable a heating area to be more uniform, have simple preparation method and lower cost, realize structural function integration, and are applied to the front edge of an engine nacelle and wing slats.
The multifunctional skin structure and the preparation method thereof provided by the embodiment of the application are described in detail above. The above description of the embodiments is only for the purpose of helping to understand the method of the present application and its core ideas; meanwhile, for a person skilled in the art, according to the idea of the present application, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present application.
As used in the specification and claims, certain terms are used to refer to particular components. As one skilled in the art will appreciate, manufacturers may refer to a component by different names. This specification and claims do not intend to distinguish between components that differ in name but not function. In the following description and in the claims, the terms "include" and "comprise" are used in an open-ended fashion, and thus should be interpreted to mean "include, but not limited to. "substantially" means within an acceptable error range, and a person skilled in the art can solve the technical problem within a certain error range to substantially achieve the technical effect. The description which follows is a preferred embodiment of the present application, but is made for the purpose of illustrating the general principles of the application and not for the purpose of limiting the scope of the application. The protection scope of the present application shall be subject to the definitions of the appended claims.
It is also noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a good or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such good or system. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a commodity or system that includes the element.
It should be understood that the term "and/or" as used herein is merely one type of association that describes an associated object, meaning that three relationships may exist, e.g., a and/or B may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.
The foregoing description shows and describes several preferred embodiments of the present application, but as aforementioned, it is to be understood that the application is not limited to the forms disclosed herein, but is not to be construed as excluding other embodiments and is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the application as described herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the application, which is to be protected by the claims appended hereto.
Claims (10)
1. The multifunctional skin structure is characterized in that the skin structure is a layered structure, and the layered structure sequentially comprises a conducting layer, a first insulating layer, a heating layer, a second insulating layer and a bearing layer;
the conductive layer is used for providing a lightning path;
the first insulating layer and the second insulating layer are used for positioning the heating layer and protecting the bearing layer from being subjected to different potential corrosion;
the heating layer is used for electrically heating to prevent and remove ice;
the bearing layer is used for providing bearing functions for other layers.
2. The multi-functional skin structure of claim 1, wherein the conductive layer is a mesh structure or a loop structure.
3. The multifunctional skin structure of claim 1, wherein the first insulating layer and/or the second insulating layer are made of fiberglass fabric, dry fiber or other insulating materials with a softening temperature of not less than 1600 ℃.
4. The multi-functional skin structure of claim 1, wherein the heating layer is a copper-based or nickel-based material.
5. The multifunctional skin structure of claim 1, wherein the material of the carrier layer is a fabric or dry fiber.
6. A method for producing a multifunctional skin structure, characterized in that the method is used for producing a skin structure according to any one of claims 1 to 5;
the preparation method comprises the following steps:
s1, preparing a second insulating layer in a paving mode;
s2, preparing a heating layer on the surface of the second insulating layer in a thermal spraying mode to obtain a first intermediate;
s3, preparing a bearing layer in a paving mode in a mould;
s4, transferring the first intermediate onto the bearing layer;
s5, preparing a first insulating layer on the surface of the heating layer in a paving mode;
s6, paving a conducting layer on the surface of the first insulating layer to obtain a preformed body;
and S7, injecting resin into the pre-formed body in a vacuum environment, cooling and shaping, and then demoulding to obtain the skin structure with the required shape.
7. The method for preparing the multifunctional skin structure according to claim 6, wherein the step S7 comprises the steps of: the preform is bagged and evacuated and resin is injected from the top of the bag.
8. The method for manufacturing the multifunctional skin structure according to claim 6, wherein the resin is any one of epoxy resin, unsaturated polyester resin, vinyl resin and bismaleimide resin.
9. An aircraft slat, wherein the aircraft slat is made using a skin structure according to any of claims 1 to 5.
10. An aircraft nacelle leading edge structure, wherein the aircraft nacelle leading edge structure is partially or wholly made using a skin structure according to any one of claims 1 to 5.
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