CN114770975A - Bionic composite material airfoil and manufacturing method thereof - Google Patents
Bionic composite material airfoil and manufacturing method thereof Download PDFInfo
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- CN114770975A CN114770975A CN202210417597.4A CN202210417597A CN114770975A CN 114770975 A CN114770975 A CN 114770975A CN 202210417597 A CN202210417597 A CN 202210417597A CN 114770975 A CN114770975 A CN 114770975A
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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
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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
Abstract
The invention discloses a bionic composite material wing surface and a manufacturing method thereof, belonging to the technical field of composite material design and forming, wherein the structure and the layering design of the wing surface use the growth characteristics of bamboo in nature for reference, and the overall rigidity and the structural stability of the composite material wing surface are improved by utilizing the layering designability of the composite material and designing a ring-shaped carbon fiber material on a foam core material of the wing surface structure, so that the bending resistance and the torsion resistance of the wing surface are improved.
Description
Technical Field
The invention relates to a bionic composite material airfoil and a manufacturing method thereof, belonging to the technical field of composite material design and forming.
Background
The weight of the aircraft is closely related to the performance and the economy, and the reduction of the structural weight of the aircraft is one of the main targets in the development work of the aircraft. The composite material airfoil has excellent mechanical properties such as high specific rigidity and specific strength, good fatigue resistance and corrosion resistance and the like, and is widely applied to aviation and aerospace structures. The composite material airfoil is mainly used for ensuring the flight performance and the maneuvering performance of an aircraft under the flight state specified by technical requirements, and therefore, certain rigidity strength must be met during structural design.
In the existing carbon fiber reinforced composite material airfoil, foams such as XPS, EPP, PMI and the like can be selected as core materials, and light foamed plastics with certain hardness and pressure resistance are formed, so that a carbon fiber-core material-carbon fiber composite sandwich structure is formed. The sandwich structure can remarkably reduce the weight while maintaining the mechanical property, more importantly, the sandwich structure can reduce the cost to a certain degree, and has very wide application prospect on the composite material airfoil. However, the sandwich structure has insufficient overall matching between the carbon fibers and the core materials, and is not beneficial to force transmission and bending resistance, so that the rigidity of the composite material airfoil cannot be well matched with the bending load borne by the composite material airfoil in the flying process, the stability is poor, the bending resistance and the torsion resistance of the airfoil are low, the weight reduction effect is general, and the characteristic that the rigidity of a composite material airfoil product can be designed is not exerted.
Disclosure of Invention
The invention aims to provide a bionic composite material wing surface and a manufacturing method thereof, wherein the structure and the layer laying design of the wing surface are based on the growth characteristics of bamboo in nature, the layer laying designability of the composite material is utilized, and the annular carbon fiber material is designed on a foam core material of the wing surface structure to improve the overall rigidity and the structural stability of the composite material wing surface, so that the bending resistance and the torsion resistance of the wing surface are improved.
The technical scheme adopted by the invention is as follows:
a bionic composite material airfoil comprises a carbon fiber beam, front and rear edge foams and a skin, wherein the carbon fiber beam is used as a bearing structure, the front and rear edge foams are bonded on the front edge and the rear edge of the carbon fiber beam, and the skin covers the carbon fiber beam and the front and rear edge foams; the carbon fiber beam comprises sandwich foam and carbon fibers, wherein the sandwich foam is formed by bonding a plurality of strip-shaped foams in a chord direction, the sandwich foam is alternately provided with a first annular groove and a second annular groove at intervals in the spanwise direction of the airfoil surface, the first annular groove is an annular groove formed by surrounding a single strip-shaped foam in the chord direction, a carbon fiber strip is wound in the first annular groove, and the first annular groove is paved by the carbon fiber strip; the second annular groove is an annular groove formed by surrounding the whole sandwich foam along the chord direction, a carbon fiber strip is wound in the second annular groove, and the second annular groove is paved by the carbon fiber strip; the sandwich foam of the carbon fiber beam is polymethacrylimide foam or polyurethane foam, the front and rear edge foams are polymethacrylimide foam or polyurethane foam, and the skin is made of carbon fiber or glass fiber reinforced plastic materials.
Further, the first and second annular grooves on the sandwich foam on the carbon fiber beam are spaced closer to the root of the airfoil at a smaller distance (i.e., the annular grooves are more densely spaced).
Further, the depth and width of the first and second annular grooves on the sandwich foam on the carbon fiber beam are larger the closer they are to the root of the airfoil.
Furthermore, the depth of the first annular groove and the second annular groove on the sandwich foam on the carbon fiber beam is 0.5-5 mm, and the width of the first annular groove and the second annular groove is 2-20 mm.
Furthermore, the bent parts of the first annular groove and the second annular groove on the sandwich foam on the carbon fiber beam are in a fillet structure, and the size of a fillet is 0.5-3 mm.
A manufacturing method of a bionic composite material airfoil surface comprises the following steps:
1) integrally machining the integrally formed sandwich foam, and additionally machining a plurality of second annular grooves which are spaced from each other along the airfoil surface spreading direction, wherein the second annular grooves surround along the chord direction; then the sandwich foam is divided into a plurality of strip-shaped foams on a chord direction machine, and a plurality of first annular grooves which are mutually spaced are added on each strip-shaped foam along a wing surface spreading machine, and the first annular grooves surround along the chord direction; the positions of the first annular groove and the second annular groove are alternately arranged at intervals;
2) cleaning chips on the surface of the strip-shaped foam, and drying in an oven;
3) carbon fiber prepreg is fully paved in all the first annular grooves on each strip-shaped foam;
4) splicing all the strip-shaped foams treated in the step 3) into a whole piece of sandwich foam, and then paving carbon fiber prepreg in all the second annular grooves;
5) filling the sandwich foam treated in the step 4) into a foam forming tool, then putting the tool into an oven for heating and curing, and then cooling and demoulding;
6) uniformly sticking a layer of adhesive film on the surface of the product obtained by demoulding in the step 5), and then integrally coating the carbon fiber prepreg;
7) loading the carbon fiber beam processed in the step 6) into a main beam forming die, heating the die through a press to enable the upper die and the lower die to be tightly matched, and heating, curing and forming to obtain the carbon fiber beam;
8) polishing the surface of the carbon fiber beam obtained in the step 7), removing a surface resin layer, uniformly sticking a layer of adhesive film on the front edge and the rear edge of the polished carbon fiber beam, and sticking front and rear edge foams which are mechanically added into the shapes of the front and rear edges of the airfoil;
9) uniformly sticking a layer of adhesive film on the upper surface, the lower surface, the front edge foam surface and the rear edge foam surface of the carbon fiber beam, and then integrally coating the carbon fiber prepreg;
10) and (3) loading the product obtained in the step (9) into an airfoil molding die, heating and curing the airfoil molding die by using an oven, and cooling and demolding after heating to obtain the bionic composite material airfoil.
Further, the proportion of the laying layers of the carbon fiber prepregs in the steps 3), 4), 6) and 9) along the 0-degree direction of the main bearing airfoil surface is more than 50%, and the laying direction comprises +/-45 degrees and 90 degrees.
Further, the carbon fiber prepreg is selected from T300, T700, T800 or T1000 unidirectional carbon fiber.
Further, the adhesive film is selected from J-47A adhesive film.
Drawings
FIG. 1 is a perspective view of a biomimetic composite airfoil configuration according to an embodiment of the present disclosure.
FIG. 2 is a perspective view of a structure of a free-standing composite airfoil according to an embodiment of the invention.
FIGS. 3A-3B are perspective views of the structure of a single piece of strip foam of the sandwich foam of the present invention.
Description of reference numerals:
10: a carbon fiber beam;
11: a leading edge;
12: a trailing edge;
20: sandwich foam;
21-a first annular groove;
22-second annular groove.
Detailed Description
In order to make the aforementioned and other features and advantages of the invention more comprehensible, embodiments accompanied with figures are described in detail below.
Bamboo is a typical organism with good mechanical properties existing in nature. Has the advantages of high specific rigidity, good elasticity, stable performance and the like. Although the bamboo is of a thin-wall structure and has a large length-to-fineness ratio, the phenomenon of bending instability is not easy to occur when the bamboo is stressed, the phenomenon and the structure of hoops on the bamboo are dense and inseparable, and because the transverse partition plates in bamboo joints can increase the bearing area of the bamboo, the rigidity and the stability of the whole bamboo mechanism are improved. Based on the above, the present invention provides a bionic composite material airfoil.
The invention provides a bionic composite material airfoil, which comprises a carbon fiber beam, front and rear edge foams and a covering. The carbon fiber beam is used as a bearing structure, the front edge foam and the rear edge foam are bonded on the front edge and the rear edge of the carbon fiber beam, the skin covers the carbon fiber beam and the front edge foam and the rear edge foam, the front edge foam and the rear edge foam are polymethacrylimide foam or polyurethane foam, and the skin is made of carbon fiber or glass fiber reinforced plastic materials.
The structure of the carbon fiber beam is shown in figures 1-2 and 3A-3B, and comprises sandwich foam and carbon fibers wound around the sandwich foam, wherein the sandwich foam of the carbon fiber beam is polymethacrylimide foam or polyurethane foam, and the structural design aims at keeping the rigidity and reducing the weight of the structure. The sandwich foam is formed by mutually bonding a plurality of strip-shaped foams in the chord direction, and first annular grooves and second annular grooves are alternately arranged on the sandwich foam at intervals along the span direction of the wing surface.
The first annular groove is an annular groove formed by surrounding a single strip-shaped foam along the chord direction, and a carbon fiber strip is wound in the first annular groove. This carbon fiber strip paves first annular groove, twines one section at a section distance with single bar foam, can strengthen the rigidity intensity of single bar foam. The closer the first annular groove is to the root of the airfoil, the smaller the spacing distance is, the larger the depth and width of the groove are, the depth of the groove is controlled to be 0.5-5 mm (for example, 0.5mm, 1mm, 1.5mm, 2mm, 2.5mm, 3mm, 3.5mm, 4mm, 4.5mm, 5mm), the width is controlled to be 2-20 mm (for example, 2mm, 3mm, 4mm, 5mm, 6mm, 7mm, 8mm, 9mm, 10mm, 11mm, 12mm, 13mm, 14mm, 15mm, 16mm, 17mm, 18mm, 19mm, 20mm), the closer to the root of the airfoil, the more and the more dense the carbon fibers are wound, and the design is aimed at: due to the distribution of airfoil load, the composite material airfoil product has the advantages that the bending moment borne by the root part of the airfoil to the tip part of the airfoil is different, and the bending moment and the load borne by the root part area of the airfoil are large, so that the structure needs to be further enhanced, the structural rigidity is enhanced by winding more carbon fiber strips, the composite material airfoil rigidity can be well matched with the bending load borne by the composite material airfoil in the flying process, the bending resistance and the torsion resistance of the airfoil are improved, and the structural stability is improved.
The second annular groove is an annular groove formed around the whole sandwich foam along the chord direction, namely only the outer surface of the single strip-shaped foam is a partial groove section of the annular groove, specifically, the upper surface and the lower surface of the single strip-shaped foam positioned at the front edge and the rear edge and the side surface positioned at the front edge and the rear edge are groove sections of the second annular groove (see fig. 3B), and the side surface used for bonding the strip-shaped foam does not contain the single strip-shaped foam (see fig. 3A). And a carbon fiber strip is wound in the second annular groove and paves the second annular groove. The second annular groove is paved by the carbon fiber strip, and the whole sandwich foam is wound for one section at intervals, so that the combined firm strength among the strip foams and the rigidity strength of the whole sandwich foam can be enhanced. The closer the second annular groove is to the root of the airfoil, the smaller the spacing distance is, the larger the depth and width of the groove are, the depth of the groove is controlled to be 0.5-5 mm (for example, 0.5mm, 1mm, 1.5mm, 2mm, 2.5mm, 3mm, 3.5mm, 4mm, 4.5mm, 5mm), the width is controlled to be 2-20 mm (for example, 2mm, 3mm, 4mm, 5mm, 6mm, 7mm, 8mm, 9mm, 10mm, 11mm, 12mm, 13mm, 14mm, 15mm, 16mm, 17mm, 18mm, 19mm, 20mm), the closer to the root of the airfoil, the more and the more dense the carbon fibers are wound, and the design is aimed at: due to the distribution of the airfoil load, the bending moment and the load applied to the root area of the airfoil are large, so that the structure needs to be further reinforced, and the structural rigidity is increased by winding more carbon fiber strips, so that the rigidity of the composite airfoil can be well matched with the bending load borne by the composite airfoil in the flying process, the bending resistance and the torsion resistance of the airfoil are improved, and the structural stability is improved.
The bending parts (namely the intersection parts of any two surfaces) of four corners of a first annular groove of sandwich foam are in a fillet structure, the corner bending parts (namely the intersection parts of the side surface of a single foam positioned at the front edge and the rear edge and the upper surface and the lower surface) of a second annular groove are in a fillet structure, and the fillet size is controlled to be 0.5-3 mm (such as 0.5mm, 1mm, 1.5mm, 2mm, 2.5mm and 3 mm).
An embodiment is given below, and specifically discloses a manufacturing method of a bionic composite material airfoil, which comprises the following steps:
firstly, preparing carbon fiber beam sandwich foam.
The density is 110kg/m3The polymethacrylimide foam machine is added into an airfoil shape with 3 second annular grooves, the distance between the 1 st groove and the root of the airfoil surface is 330mm, the width of the groove is 10mm, and the depth is 2.5 mm; the distance between the 2 nd groove and the root is 630mm, the width of the groove is 8mm, and the depth is 2 mm; the 3 rd groove is 930mm away from the root, 6mm in width and 1.5mm in depth.
Dividing the machined foam into 4 pieces of strip-shaped foam along the chord direction, and adding 4 first annular grooves into each piece of foam along the spanwise machine, wherein the distance from the 1 st groove to the root of the airfoil surface is 100mm, the width of each groove is 15mm, and the depth of each groove is 3 mm; the distance between the 2 nd groove and the root is 200mm, the width of the groove is 10mm, and the depth is 2.5 mm; the 3 rd groove is 500mm away from the root, 8mm in width and 2mm in depth; the 4 th groove is 800mm away from the root, 6mm in width and 1.5mm in depth.
And secondly, carrying out foam drying treatment.
The foam surface debris was cleaned with a blower and the foam was dried in an oven at 130 ℃. + -. 5 ℃ for 3 hours.
And thirdly, winding the carbon fiber prepreg around the blocked foam annular grooves.
Laying T700/9368 unidirectional carbon fiber prepreg with the width of 15mm in a 1 st first annular groove, close to the root, of the 4 divided foams, wherein the laying direction is [90,45,0, -45, -45,0,45,90,90, 0,90]s(the angle symbol s indicates symmetrical plies, i.e. [90,45,0, -45, -45,0,45,90,90,90,0,90,90,0,90,90, 45,0, -45, -45,0,45,90]) (ii) a The 2 nd groove is internally paved with T700/9368 carbon fiber prepreg with the width of 10mm, and the paving direction is [90,45,0, -45, -45,0,45,90,90, 45,0, -45, -45,0,45,90](ii) a T700,9368 carbon fiber prepreg with the width of 8mm is paved in the 3 rd groove, and the paving direction is [90,45,0, -45, -45,0,45,90 ]]s(ii) a T700,9368 carbon fiber prepreg with the width of 6mm is paved in the 4 th groove, and the paving direction is [90,45,0, -45 ]]s. Note that in order to ensure the strength in the main force bearing direction, the fiber lay-up of this step is usually greater than 50% in the 0 degree direction of the main force bearing airfoil, but it is also necessary to have ± 45 ° and 90 ° to avoid the problem of rapid propagation in one direction after internal defects such as cracks occur.
Fourthly, winding the carbon fiber prepreg by the annular groove after the foams are spliced.
Splicing 4 foams wound by carbon fibers in sequence in the third step, and then paving T700/9368 unidirectional carbon fiber prepreg with the width of 10mm in the 1 st second annular groove of the spliced foam close to the root part, wherein the paving direction is [90,90,0,90,90,0,90,90,90,45,0, -45,90,90,0,90,90, 90](ii) a T700,9368 carbon fiber prepreg with the width of 8mm is paved in the 2 nd groove, the paving direction is [90, 90',0,90,90,0,90,90]s(ii) a Laying T700,9368 carbon fiber prepreg with the width of 6mm in the 3 rd groove in the laying direction of [90,90,0,90,90,45,0, -45,90,0,90,90]. Note that in order to ensure the strength in the main force bearing direction, the fiber lay-up of this step is usually greater than 50% in the 0 degree direction of the main force bearing airfoil, but it is also necessary to have ± 45 ° and 90 ° to avoid the problem of rapid propagation in one direction after internal defects such as cracks occur.
And fifthly, reinforcing and curing the foam.
And (3) putting the foam coated with the annular carbon fiber prepreg into a foam molding tool, putting the tool into an oven, setting the temperature of the oven at 130 ℃, keeping the temperature for 120min after reaching the temperature, shutting down, and naturally cooling to below 50 ℃ for demolding.
And sixthly, laying the carbon fiber beams.
Uniformly sticking a layer of J-47A adhesive film on the foam subjected to carbon fiber winding in the fifth step, and integrally coating a T700/9368 carbon fiber prepreg with the thickness of 3mm, wherein the layering direction is [45,0,0, -45,0,0,90,0,45,0,0, -45]s. Note that in order to ensure the strength in the main force bearing direction, the fiber lay-up of this step is usually greater than 50% in the 0 degree direction of the main force bearing airfoil, but it is also necessary to have ± 45 ° and 90 ° to avoid the problem of rapid propagation in one direction after internal defects such as cracks occur.
And seventhly, solidifying and forming the carbon fiber beam.
And (3) loading the laid carbon fiber beam into a main beam forming die, and detecting that the hot press and the temperature measuring probe work normally. The mould is lifted to the table of the press by a crane, and the upper panel of the press is contacted with the upper mould. The press temperature was set at 90 ℃ and the mold was heated. And (3) pressurizing (3-20) MPa when the temperature of the die is raised to 90 ℃ so as to tightly mould the upper die and the lower die. Then the temperature of the press is set to 130 ℃, and the temperature is kept for 120min when the temperature of the die is raised to 130 ℃.
And step eight, butting the carbon fiber beams with the front edge foam and the rear edge foam.
Polishing the surface of the carbon fiber beam by using No. 60 abrasive paper, removing a surface resin layer, uniformly sticking 1 layer of J-47A adhesive film on a front edge web plate and a rear edge web plate of the polished beam, and sticking a polymethacrylimide foam block which is mechanically added with the front edge and rear edge shapes of an airfoil.
And step nine, layering airfoil surface skins.
Uniformly sticking 1 layer of J-47A adhesive film on the upper and lower surfaces and the front and rear edge foam surfaces of the carbon fiber beam, and integrally coating a T700/9368 carbon fiber prepreg (the prepreg is a skin after being cured) with the thickness of 2mm, wherein the laying direction is [45,0,0, -45,0,0,90, 0-]s. Note that in order to ensure the strength in the main force bearing direction, the fiber lay-up of this step is usually greater than 50% in the 0 degree direction of the main force bearing airfoil, but it is also necessary to have ± 45 ° and 90 ° to avoid the problem of rapid propagation in one direction after internal defects such as cracks occur.
And step ten, solidifying and molding the wing surface skin.
Loading the airfoil subjected to the layering process into an airfoil forming die, and heating and curing the airfoil forming die by using an oven; setting the temperature of the oven to 130 ℃, and preserving heat for 2 hours when the temperature of the die is raised to 130 ℃; and opening the oven door after heating, and naturally cooling the mold to below 50 ℃ for demolding.
The bionic composite material airfoil manufactured in the embodiment was subjected to mechanical property tests as follows:
rigidity tests prove that the rigidity of the airfoil manufactured by the embodiment under the loading load of 100kg is improved by more than 10 percent compared with the rigidity of the airfoil without foam annular reinforcement (namely without carbon fiber strip winding). The lifting of the stiffness of the airfoil can reduce the rolling moment of the aircraft in the flying state, and the stability and consistency of the aircraft in the flying process are ensured.
The process parameters in the above steps, such as temperature, pressure, time, and layering direction, are all specific parameters that are selected according to the specific needs of this embodiment, and the present invention is not limited thereto, and those skilled in the art can select appropriate process parameters according to the actual needs according to the spirit of this embodiment. Although the present invention has been described with reference to the above embodiments, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (9)
1. A bionic composite material airfoil is characterized by comprising a carbon fiber beam, front and rear edge foams and a skin, wherein the carbon fiber beam is used as a bearing structure, the front and rear edge foams are bonded on the front edge and the rear edge of the carbon fiber beam, and the skin covers the carbon fiber beam and the front and rear edge foams; the carbon fiber beam comprises sandwich foam and carbon fibers, wherein the sandwich foam is formed by bonding a plurality of strip-shaped foams in a chord direction, the sandwich foam is alternately provided with a first annular groove and a second annular groove at intervals in the span direction of the airfoil surface, the first annular groove is an annular groove formed by surrounding a single strip-shaped foam in the chord direction, a carbon fiber strip is wound in the first annular groove, and the first annular groove is paved by the carbon fiber strip; the second annular groove is an annular groove formed by surrounding the whole sandwich foam along the chord direction, a carbon fiber strip is wound in the second annular groove, and the second annular groove is paved by the carbon fiber strip; the sandwich foam of the carbon fiber beam is polymethacrylimide foam or polyurethane foam, the front edge foam and the rear edge foam are polymethacrylimide foam or polyurethane foam, and the skin is made of carbon fiber or glass fiber reinforced plastic materials.
2. The biomimetic composite airfoil of claim 1, wherein the first annular groove and the second annular groove in the sandwich foam on the carbon fiber beam are spaced closer together than the root of the airfoil.
3. The biomimetic composite airfoil of claim 1, wherein the depth and width of the groove increases the closer the first and second annular grooves on the sandwich foam on the carbon fiber beam are to the root of the airfoil.
4. The biomimetic composite airfoil of claim 1, wherein the first and second annular grooves in the sandwich foam on the carbon fiber beam have a groove depth of 0.5 to 5mm and a width of 2 to 20 mm.
5. The biomimetic composite airfoil as recited in claim 1, wherein the bends of the first and second annular grooves on the sandwich foam on the carbon fiber beam have a rounded corner configuration, and the rounded corner is 0.5-3 mm.
6. A method of manufacturing a biomimetic composite airfoil for use in manufacturing a biomimetic composite airfoil as claimed in any of claims 1 to 5, comprising the steps of:
1) integrally machining the integrally formed sandwich foam, and additionally machining a plurality of second annular grooves which are spaced from each other along the airfoil surface spreading direction, wherein the second annular grooves surround along the chord direction; then the sandwich foam is divided into a plurality of strip-shaped foams on a chord direction machine, and a plurality of first annular grooves which are mutually spaced are added on each strip-shaped foam along the airfoil surface spreading machine, and the first annular grooves surround along the chord direction; the positions of the first annular groove and the second annular groove are alternately arranged at intervals;
2) cleaning chips on the surface of the strip-shaped foam, and drying in an oven;
3) carbon fiber prepreg is fully paved in all the first annular grooves on each strip-shaped foam;
4) splicing all the strip-shaped foams treated in the step 3) into a whole piece of sandwich foam, and then paving carbon fiber prepreg in all the second annular grooves;
5) filling the sandwich foam treated in the step 4) into a foam forming tool, then putting the tool into an oven for heating and curing, and then cooling and demoulding;
6) uniformly sticking a layer of adhesive film on the surface of the product obtained by demoulding in the step 5), and then integrally coating the carbon fiber prepreg;
7) putting the carbon fiber beam treated in the step 6) into a main beam forming die, heating the die by a press to enable the upper die and the lower die to be tightly matched, and heating, curing and forming to obtain the carbon fiber beam;
8) polishing the surface of the carbon fiber beam obtained in the step 7), removing a surface resin layer, uniformly sticking a layer of adhesive film on the front edge and the rear edge of the polished carbon fiber beam, and sticking front and rear edge foams which are mechanically added into the shapes of the front and rear edges of the airfoil;
9) uniformly sticking a layer of adhesive film on the upper surface, the lower surface, the front edge foam surface and the rear edge foam surface of the carbon fiber beam, and then integrally coating the carbon fiber prepreg;
10) and (3) loading the product obtained in the step (9) into an airfoil molding die, heating and curing the airfoil molding die by using an oven, and cooling and demolding after heating to obtain the bionic composite material airfoil.
7. The method of claim 6, wherein the lay-up of carbon fibre prepregs in steps 3), 4), 6) and 9) has a proportion of more than 50% in the 0 degree direction of the main messenger plane, the lay-up directions encompassing ± 45 ° and 90 °.
8. The method of claim 6, wherein said carbon fiber prepreg is selected from T300, T700, T800 or T1000 unidirectional carbon fiber.
9. The method of claim 6, wherein the adhesive film is selected from a J-47A adhesive film.
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| CN116494435A (en) * | 2023-05-19 | 2023-07-28 | 北京科技大学 | Preparation method of butterfly-like cambered surface flexible wing pulse wing and wing pulse wing |
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| CN116494435B (en) * | 2023-05-19 | 2024-03-15 | 北京科技大学 | Preparation method of butterfly-like cambered surface flexible wing pulse wing and wing pulse wing |
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