CN116394545A - Leading edge skin forming method and leading edge skin - Google Patents
Leading edge skin forming method and leading edge skin Download PDFInfo
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- CN116394545A CN116394545A CN202310677353.4A CN202310677353A CN116394545A CN 116394545 A CN116394545 A CN 116394545A CN 202310677353 A CN202310677353 A CN 202310677353A CN 116394545 A CN116394545 A CN 116394545A
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- outer skin
- honeycomb core
- skin layer
- leading edge
- adhesive film
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- 238000000034 method Methods 0.000 title claims abstract description 42
- 239000002313 adhesive film Substances 0.000 claims abstract description 60
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 28
- 229910052802 copper Inorganic materials 0.000 claims abstract description 28
- 239000010949 copper Substances 0.000 claims abstract description 28
- 239000003292 glue Substances 0.000 claims abstract description 16
- 239000011347 resin Substances 0.000 claims abstract description 16
- 229920005989 resin Polymers 0.000 claims abstract description 16
- 238000005187 foaming Methods 0.000 claims abstract description 14
- 238000007789 sealing Methods 0.000 claims abstract description 9
- 230000003014 reinforcing effect Effects 0.000 claims description 12
- 238000000465 moulding Methods 0.000 claims description 10
- 238000005498 polishing Methods 0.000 claims description 10
- 238000007711 solidification Methods 0.000 claims description 7
- 230000008023 solidification Effects 0.000 claims description 7
- 239000006260 foam Substances 0.000 claims description 4
- 239000003365 glass fiber Substances 0.000 claims description 4
- 229920000728 polyester Polymers 0.000 claims description 4
- 230000037303 wrinkles Effects 0.000 claims description 4
- 238000005553 drilling Methods 0.000 claims description 3
- 238000003892 spreading Methods 0.000 claims description 3
- 230000007480 spreading Effects 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 238000007493 shaping process Methods 0.000 claims description 2
- 230000000717 retained effect Effects 0.000 claims 1
- 230000008569 process Effects 0.000 abstract description 11
- 239000000853 adhesive Substances 0.000 abstract description 10
- 230000001070 adhesive effect Effects 0.000 abstract description 10
- 239000002131 composite material Substances 0.000 abstract description 4
- 238000009825 accumulation Methods 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 238000003825 pressing Methods 0.000 abstract description 3
- 238000005336 cracking Methods 0.000 abstract 2
- 238000005520 cutting process Methods 0.000 abstract 1
- 239000006185 dispersion Substances 0.000 abstract 1
- 238000001723 curing Methods 0.000 description 19
- 238000010586 diagram Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 4
- 230000007797 corrosion Effects 0.000 description 4
- 238000005260 corrosion Methods 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 230000004075 alteration Effects 0.000 description 2
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- 241001391944 Commicarpus scandens Species 0.000 description 1
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Images
Classifications
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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
- B29C70/342—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 isostatic pressure
-
- 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
-
- 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/688—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks the inserts being meshes or lattices
-
- 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/82—Forcing wires, nets or the like partially or completely into the surface of an article, e.g. by cutting and pressing
-
- 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
- B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
- B29C70/882—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding
- B29C70/885—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding with incorporated metallic wires, nets, films or plates
-
- 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
-
- 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
Abstract
The invention provides a leading edge skin forming method and a leading edge skin, relates to the technical field of composite materials, and solves the technical problems of high laying difficulty, resin accumulation in an R area, cracking of a honeycomb core in the R area, honeycomb marks on the surface of the skin, dispersion and poor glue caused by great loss of inner skin resin and the like in the prior art. The method comprises the following steps: the method comprises the steps of paving prepreg on a male die and solidifying to form an outer skin layer, paving an adhesive film carrier and a lightning protection copper mesh on the outer skin layer, transferring the outer skin out of the male die, transferring the outer skin and the lightning protection copper mesh to a female die, paving a honeycomb core on the outer skin, cutting off the honeycomb core in an R area, filling the cut-off area with foaming adhesive, paving an inner skin on the honeycomb core after the foaming adhesive is fixed, and solidifying to form a front edge skin. The invention ensures the surface quality of the pneumatic surface and the cementing surface of the outer skin, solves the problems of cracking and matching of the honeycomb core in the R area, reduces the R area checking, compensating and heat sealing pressing procedures of the traditional process of the front edge skin, and improves the production efficiency.
Description
Technical Field
The invention relates to the technical field of composite materials, in particular to a leading edge skin forming method and a leading edge skin.
Background
The honeycomb sandwich panel is a special type of composite material, has the advantages of high specific strength, high specific rigidity, good fatigue resistance and the like, can obviously improve the rigidity of parts on the premise of realizing light weight, and is widely applied to the fields of aerospace, military and the like. The honeycomb sandwich panel comprises an upper panel and a lower panel, and honeycomb sandwich materials arranged between the panels, wherein the panels are mainly made of fiber reinforced resin matrix composite materials.
The front edge skin of the aircraft is a honeycomb sandwich plate, the curvature of the front edge skin is large, the outer surface is a pneumatic surface, the pneumatic surface quality of the outer skin needs to be ensured, the requirement on the quality of parts is high, and the forming difficulty is large. One of the usual shaping methods for the leading edge skin is to lay an outer skin (containing lightning protection copper mesh) on the female mould, after curing the outer skin (containing lightning protection copper mesh) to place a honeycomb core on the outer skin and to complete the subsequent laying and curing of the inner skin. The other molding mode is to finish the one-step laying and stacking of the outer skin, the honeycomb core and the inner skin and co-curing molding. The honeycomb used in the prior art is typically a monolithic honeycomb.
When the outer skin, the honeycomb core and the inner skin are co-cured and formed, more honeycomb marks exist on the skin of the board core area, resin in the skin easily flows into the honeycomb, and serious glue-lack and nondestructive faults can occur on the surfaces of parts. Meanwhile, the honeycomb core is not fully fixed in the forming process and is positioned on the inclined plane, so that the defects of collapse, displacement and the like of the honeycomb core are easy to occur. The outer molded surface of the front edge skin is a pneumatic surface, and the smooth smoothness of the outer surface of the molded part is required to meet the pneumatic requirement of an airplane, so that the outer skin is molded in a female molding mode.
The applicant found that the prior art has at least the following technical problems:
the honeycomb used in the prior art is usually an integral honeycomb, the curvature change of the front edge skin is large, and the curvature at the R area is maximum, so that on one hand, the honeycomb core is easy to break when being placed, held and pressurized, and on the other hand, the honeycomb core and the outer skin are not easy to be stuck, so that the matching of parts and the honeycomb core is poor, and even no damage fault occurs.
The outer skin is molded in a female molding mode, so that the paving difficulty is high, the operation difficulty is high, and bridge (gaps exist between prepregs and between the prepregs and a tool) is easily caused in the paving process to cause nondestructive faults; the region of the outer skin R is affected by auxiliary materials (vacuum bags, etc. involved in the manufacturing process) during the in-can press curing process, and this region is not sufficiently pressed, which tends to cause resin build-up in the region of the molding face R (opposite side of the pneumatic face).
Disclosure of Invention
The invention aims to provide a leading edge skin forming method and a leading edge skin, which are used for solving the technical problems that the paving difficulty is high, the female mold R area is difficult to pave and the resin in the cured outer skin R area is accumulated when the outer skin is formed by adopting the female mold in the prior art. The preferred technical solutions of the technical solutions provided by the present invention can produce a plurality of technical effects described below.
In order to achieve the above purpose, the present invention provides the following technical solutions:
the invention provides a front edge skin forming method, which comprises the following steps: laying prepreg on the male die, and forming an outer skin layer after curing; spreading a glue film carrier and a lightning protection copper mesh on the outer skin layer formed after solidification, and transferring the outer skin layer and the copper mesh to a female die; paving an adhesive film on one side of the honeycomb core of the outer skin, paving the honeycomb core, sealing a vacuum bag, vacuumizing and fixing in an autoclave; and curing the honeycomb core to prepare an inner skin layer.
Further, the prepreg is paved on the male die, and an outer skin layer is formed after curing, and the method specifically comprises the following steps: and (3) laying prepreg on the male die, forming an outer skin layer after solidification, drilling positioning holes in the outer skin layer, checking the surface quality of the outer skin layer after demolding, polishing and flattening the positions where wrinkles, uneven surfaces and resin piles exist on one side of the pneumatic surface of the outer skin layer, and cleaning by using acetone. The surface quality of the outer skin close to one side of the honeycomb core is guaranteed through the male die paving and curing of the outer skin layer, and matching of the honeycomb core and the skin in the subsequent process is facilitated.
Further, the adhesive film carrier is a polyester felt or glass fiber felt adhesive film carrier for preventing electric corrosion caused by potential difference; and (3) laying the adhesive film carrier and the copper mesh on the outer skin layer, transferring the outer skin layer and the copper mesh to the female die, and sealing the vacuum bag and vacuumizing to be in close fit with the female die tool.
Further, the honeycomb cores are disconnected in the R area, and foaming glue is filled between the honeycomb cores at two sides of the deep groove of the outer skin layer.
Further, the curing and manufacturing the inner skin layer on the honeycomb core comprises the following operations: placing a first layer of adhesive film on the honeycomb core; placing a layer of nonporous isolating film and a layer of conformal soft mold on the adhesive film of the honeycomb core; after assembly, the soft mold and the isolating film are removed after the tank is put into the tank for fixing.
Further, the soft mold has the following structure: the soft mold is internally provided with reinforcing layers, and the number of the reinforcing layers of the R area in the soft mold is more than that of the reinforcing layers of other areas except the R area of the soft mold.
Further, the method further comprises the following steps: and trimming, polishing and curing the foaming adhesive and the adhesive film area to make the surface smoothly transition.
Further, a second adhesive film is laid after holding, then a prepreg is laid, and the laid prepreg is cured to form an inner skin layer.
Further, the thickness of the first adhesive film layer is consistent with the thickness of the second adhesive film layer, and the thickness of the adhesive film laid between the honeycomb core and the outer skin layer is twice that of the first adhesive film layer.
The invention provides a front edge skin, which is prepared by adopting the front edge skin molding method.
One of the above technical solutions has at least one of the following advantages or beneficial effects:
according to the invention, the outer skin layer is subjected to male die paving and solidification, so that the problems of high paving difficulty, R-region resin accumulation, R-region paving bridging and the like in outer skin female die paving can be effectively solved, and meanwhile, the surface quality of one side of the outer skin honeycomb core and the matching degree with the honeycomb core are effectively ensured;
the outer skin is solidified firstly, then an adhesive film carrier and a lightning protection copper mesh are paved, so that the problems that when the existing outer skin and copper mesh are solidified and formed together, the fluidity of the resin on the die surface is insufficient, bubbles between prepregs cannot be completely discharged, and then the bubbles are attached to the copper mesh surface, and needle holes exist are effectively solved;
the electric corrosion problem between metal and carbon fiber can be effectively solved by arranging the adhesive film between the copper net and the outer skin layer;
the split honeycomb cores are adopted, foam rubber is filled in the deep grooves of the outer skin layers to splice and solidify the honeycomb cores at two sides, so that the problem of matching of the honeycomb cores and an R region of the outer skin can be effectively solved, the situation that the honeycomb cells crack after the R region is bent in an integral honeycomb core forming mode is reduced, and one or more R region verification and compensation procedures are reduced;
a layer of flexible mold with shape is placed in the honeycomb core and the foaming glue filling area, so that the problems of adhesive film sinking and adhesive film loss caused by direct pressurization of a vacuum bag on an adhesive film when the surface of the honeycomb core is fixed can be effectively solved, and the surface leveling state of the foaming glue filling position is ensured;
the top surface adhesive film of the honeycomb core area of the inner skin is placed twice, and the adhesive film solidified on the honeycomb core in the fixing stage can prevent the resin of the inner skin from filling the honeycomb cells when the inner skin is solidified in the inner skin solidification process, avoid the problems of poor adhesive, chromatic aberration and no damage of the surface of the honeycomb core area, and reduce one adhesive film heat sealing and pressing procedure.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a leading edge skin shown according to an exemplary embodiment;
FIG. 2 is an enlarged view of a portion of FIG. 1 according to A;
FIG. 3 is a schematic diagram of a leading edge skin forming process (making an outer skin layer on a male mold) shown according to an example embodiment;
FIG. 4 is a schematic diagram of a leading edge skin forming process (laying a copper mesh in the outer skin layer) shown according to an example embodiment;
FIG. 5 is a schematic diagram of a leading edge skin forming process (transferring the outer skin layer and copper mesh to a female mold and laying down a honeycomb core) shown according to an example embodiment;
FIG. 6 is a schematic diagram of a leading edge skin molding process (filling foam between honeycomb cores) shown according to an example embodiment;
FIG. 7 is a schematic diagram of a leading edge skin forming process (making an inner skin layer) shown according to an example embodiment;
FIG. 8 is a schematic cross-sectional view of a leading edge skin shown according to an example embodiment;
FIG. 9 is a schematic diagram of a front view of a soft mold shown according to an exemplary embodiment;
fig. 10 is a partial enlarged view at B in fig. 9.
1, a copper net; 2. an outer skin layer; 3. foaming glue; 4. a honeycomb core; 5. an inner skin layer; 6. a male mold; 7. a female die; 8. an adhesive film; 9. soft mold; 901. a reinforcing layer.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, based on the examples herein, which are within the scope of the invention as defined by the claims, will be within the scope of the invention as defined by the claims.
The invention provides a leading edge skin forming method, which comprises the following steps:
laying prepreg on the male die 6, and forming an outer skin layer 2 after curing;
spreading a glue film carrier and a lightning protection copper mesh 1 on the outer skin layer 2 formed after solidification, transferring the outer skin layer 2 and the copper mesh 1 to a female die 7, sealing a vacuum bag, vacuumizing and compacting with a female die 7 tool;
paving an adhesive film on one side of a honeycomb core of the outer skin layer 2, paving a honeycomb core 4, sealing a vacuum bag, vacuumizing and fixing in an autoclave;
an inner skin layer 5 is cured on the honeycomb core 4.
According to the invention, the outer skin female die is transferred to the male die for laying, so that the problems of high resin accumulation and high laying difficulty in the R region of the outer skin female die and difficult laying in the R region of the female die can be effectively solved.
The outer skin is solidified, a layer of adhesive film carrier is paved on the outer skin layer 2, the lightning protection copper net 1 is paved on the adhesive film carrier 1, and then the outer skin layer 2 and the copper net 1 are transferred to the female die 7, so that the problem that the fluidity of the resin of the die bonding surface is insufficient, and bubbles between prepregs cannot be completely discharged so as to be attached to the surface of the copper net, and needle holes exist when the existing outer skin and the copper net are solidified and formed together is effectively solved.
And a layer of adhesive film carrier is added between the copper net 1 and the outer skin layer 2, the adhesive film carrier is preferably polyester felt or glass fiber felt, and the copper net 1 and the outer skin layer 2 are separated by the polyester felt or the glass fiber felt, so that the electric corrosion carrier between metal and carbon fiber is effectively solved. The carbon fiber and the metal material have larger potential difference, if in direct contact, the galvanic corrosion of the metal material can be caused, and effective damage can be caused in a shorter time.
And (3) carrying out can feeding curing operation on the prepreg laid on the male die to form the outer skin layer 2. And (3) in-can curing, namely, after the parts and the tooling envelope are assembled, placing the parts and the tooling envelope into a pressure container, pressurizing the container (the pressure is several times of atmospheric pressure) and heating and curing.
Regarding vacuum pumping of the sealed vacuum bag, the method specifically comprises the following steps: and (3) placing a vacuum bag around the edge of the tool to seal the part, and then exhausting the gas through a vacuum device to keep the vacuum state in the vacuum bag.
In one example, the prepreg is laid up on the male mold 6, and after curing, the outer skin layer 2 is formed, specifically including the following: 5-10 layers of prepreg are paved on the male die 6, for example, 8 layers of prepreg are paved on the male die 6, an outer skin layer 2 is formed after solidification, positioning holes are drilled in the outer skin layer 2, the surface quality of the outer skin is checked, and polishing treatment is carried out on the positions, where wrinkles exist on the pneumatic surface of the outer skin layer 2 and resin is piled up.
In one example, the honeycomb cores 4 are broken in the R region, and the foam 3 is filled between the honeycomb cores 4 on both sides of the deep groove of the outer skin layer 2. The split honeycomb core 4 is adopted, the foam adhesive 3 is filled in the deep groove of the outer skin layer 2 to splice and solidify the honeycomb cores 4 at two sides, so that the problem of matching between the honeycomb cores 4 and an R region of the outer skin can be effectively solved, the situation that the honeycomb cells crack after the R region is bent in the integral honeycomb core 4 forming mode is reduced, and one or more R region verification and compensation procedures are reduced.
Paving honeycomb cores 4 on the outer skin layers 2, breaking the honeycomb cores 4 in an R area, filling foaming glue 3 between the honeycomb cores 4 on two sides of the deep groove of the outer skin layers 2, and sealing a vacuum bag for vacuumizing and fixing. The vacuum bag applies pressure to the honeycomb core 4 through atmospheric pressure difference, and the honeycomb core 4 and the outer skin layer 2 are primarily bonded through the adhesive film, so that the honeycomb is not shifted.
In one example, with respect to the curing of the inner skin layer 5 on the honeycomb core 4, the following operations are included:
placing a first layer of adhesive film on the honeycomb core 4;
placing a layer of nonporous isolating film and a layer of conformal soft mold 9 on the adhesive film of the honeycomb core 4;
after assembly, the material is put into a tank for fixing, and after fixing, the soft mold 9 and the isolating film are removed;
polishing the solidified foaming adhesive 3 and the adhesive film to make the surface smoothly transition;
a second adhesive film is laid up, then the prepreg is laid up, and the laid up prepreg is cured to form the inner skin layer 5.
And polishing the adhesive film after the curing of the inner skin area, placing one layer of adhesive film (second layer of adhesive film) on the outer skin area and the honeycomb core area after polishing, then laying up the prepreg, and curing the second layer of adhesive film and the prepreg to form the inner skin layer 5.
A layer of flexible mold 9 is arranged in the filling area of the honeycomb core 4 and the foaming adhesive 3, so that the problems of sinking of the adhesive film (first adhesive film) and loss of the adhesive film caused by directly pressing the vacuum bag on the adhesive film when the surface of the honeycomb core is fixed can be effectively solved, and the surface leveling state of the filling position of the foaming adhesive 3 is ensured.
The top surface adhesive film of the honeycomb core 4 area is placed twice, namely a first adhesive film and a second adhesive film, and the adhesive film (the first adhesive film) cured on the honeycomb core 4 can prevent the resin of the inner skin from filling the honeycomb lattice when the inner skin is cured, so that the problems of poor adhesive, chromatic aberration and no damage on the surface of the honeycomb core 4 area are avoided.
The top surface adhesive film in the area of the honeycomb core 4 is placed twice, the thickness of the two adhesive films is consistent, and the thickness of the adhesive film laid between the honeycomb core 4 and the outer skin layer 2 is twice that of the first adhesive film.
In one example, the structure of the soft mold 9 is as follows: the reinforcing layer 901 is provided in the soft mold 9, and the number of R region reinforcing layers 901 in the soft mold 9 is greater than the number of reinforcing layers 901 in the other region of the soft mold 9 than the R region. Referring to fig. 9-10, one embodiment of a soft mold 9 is shown. The number of the R-region reinforcing layers 901 in the soft film 9 is three, and the lengths of the reinforcing layers 901 on the two sides in the radian direction are different.
Specific embodiments of the leading edge skin forming method can be seen as follows:
laying 8 layers of prepreg on a male die 6, assembling into a tank, curing to form an outer skin layer 2, drilling positioning holes on the outer skin layer 2, polishing the positions where wrinkles exist on the pneumatic surface of the outer skin layer and resin is piled up, cleaning by using acetone, and then laying a glue film carrier and a lightning protection copper mesh 1;
placing the outer skin layer 2 and the copper net 1 on the female die 7 through the tooling positioning holes, fixing, bagging, vacuumizing and compacting with the tooling of the female die 7;
placing a glue film with the thickness of 0.4mm according to the glue joint area of the outer skin layer 2, placing a honeycomb core 4 on the glue joint, placing a foaming glue 3 at the deep groove position of the outer skin layer 2, bagging, pre-vacuumizing, and fixing the honeycomb core 4;
placing a layer of adhesive film with the thickness of 0.2mm on the top surface of the honeycomb core 4, then placing a layer of non-porous isolating film and a layer of flexible die 9 with the shape, and after assembling, placing into a tank for holding;
removing the isolating film and the soft mold 9 after the fixing, polishing the cured foaming adhesive 3 and the adhesive film, and smoothly transiting the surface;
a layer of 0.2mm adhesive film is integrally laid on the held honeycomb core 4 and the outer skin, then a prepreg is laid, and the prepreg laid on the honeycomb core 4 is cured to form an inner skin layer 5.
The invention provides a front edge skin, which is prepared by adopting the front edge skin molding method. The method for forming the front edge skin is specifically described above, and will not be described in detail herein.
In the description of the present invention, it is to be noted that, unless otherwise indicated, the meaning of "plurality" means two or more; the terms "upper", "lower", "left", "right", "inner", "outer", "front", "rear", "head", "tail", etc., refer to an orientation or positional relationship based on that shown in the drawings, and are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "mounted", "connected" and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present invention can be understood as appropriate by those of ordinary skill in the art.
In the description of the present specification, a description referring to the terms "one embodiment," "some embodiments," "examples," "specific examples," or "one example" etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present application. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing is merely illustrative of the present invention, and the present invention is not limited thereto, and any person skilled in the art will readily recognize that variations or substitutions are within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. A method of shaping a leading edge skin comprising:
laying prepreg on the male die, and forming an outer skin layer after curing;
spreading a glue film carrier and a lightning protection copper mesh on the outer skin layer formed after solidification, and transferring the outer skin layer and the copper mesh to a female die;
paving an adhesive film on one side of the honeycomb core of the outer skin, paving the honeycomb core, sealing a vacuum bag, vacuumizing and fixing in an autoclave;
and curing the honeycomb core to prepare an inner skin layer.
2. The method of claim 1, wherein the step of laying up the prepreg on the male mold and curing the prepreg to form the outer skin layer comprises the steps of:
and (3) laying prepreg on the male die, forming an outer skin layer after curing, drilling positioning holes in the outer skin layer, checking the surface quality of the outer skin layer after demolding, and polishing the positions where wrinkles exist on the pneumatic surface of the outer skin layer and resin is piled.
3. The leading edge skin forming method according to claim 1, wherein the film carrier is a film carrier of polyester felt or glass fiber felt;
and transferring the outer skin layer and the copper net onto the female die, and sealing a vacuum bag and vacuumizing to be adhered to the female die tool.
4. The leading edge skin molding method according to claim 1, wherein the honeycomb core is broken in the R region, and the foam is filled between the honeycomb cores on both sides of the outer skin layer deep groove.
5. The method of any one of claims 1-4, wherein curing the inner skin layer on the honeycomb core comprises:
placing a first layer of adhesive film on the honeycomb core;
placing a layer of nonporous isolating film and a layer of conformal soft mold on the adhesive film of the honeycomb core;
after assembly, the soft mold and the isolating film are removed after the tank is put into the tank for fixing.
6. The leading edge skin forming method of claim 5, wherein the soft mold has the following structure:
the soft mold is internally provided with reinforcing layers, and the number of the reinforcing layers of the R area in the soft mold is more than that of the reinforcing layers of other areas except the R area of the soft mold.
7. The leading edge skin forming method of claim 5, wherein the in-can retained further comprises:
polishing the solidified foaming glue area and the surface glue film on the honeycomb core to make the surface smoothly transition.
8. The leading edge skin forming method of claim 5, wherein the second adhesive film is laid after holding, then the prepreg is laid, and the laid prepreg is cured to form the inner skin layer.
9. The method of claim 8, wherein the thickness of the first adhesive film is equal to the thickness of the second adhesive film, and the thickness of the adhesive film laid between the honeycomb core and the outer skin layer is twice the thickness of the first adhesive film.
10. A leading edge skin prepared by the leading edge skin molding method of any one of claims 1-9.
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| CN202310677353.4A CN116394545B (en) | 2023-06-09 | 2023-06-09 | Leading edge skin forming method and leading edge skin |
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| CN116394545B (en) | 2023-08-04 |
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