CN115742343A - Tenon-and-mortise connected composite material airfoil and forming method thereof - Google Patents
Tenon-and-mortise connected composite material airfoil and forming method thereof Download PDFInfo
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- CN115742343A CN115742343A CN202211413672.6A CN202211413672A CN115742343A CN 115742343 A CN115742343 A CN 115742343A CN 202211413672 A CN202211413672 A CN 202211413672A CN 115742343 A CN115742343 A CN 115742343A
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- 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 relates to a mortise and tenon joint composite material airfoil and a forming method thereof. The composite material airfoil comprises an airfoil framework and an outer skin; the airfoil framework comprises a metal joint, a composite material solid area and foam which are sequentially connected; and the composite solid area and the foam are positioned and connected through a mortise and tenon structure. One end of the composite material solid area is connected with the slot on the metal joint through a plug; and the other end of the composite material solid area is connected with the tenon structure of the foam through a mortise structure. The composite material solid area comprises an upper cover with a tenon structure and a lower cover with a mortise structure, and the upper cover and the lower cover are connected in a positioning mode through the mortise structure. Compared with the traditional wing surface, the composite wing surface has the advantages of more reasonable rigidity distribution, stronger elastic deformation capability and better internal quality, is more firmly connected when bearing the action of bending moment and torque, can obviously improve the bearing capacity of the wing surface, and has lighter weight on the basis of meeting the dynamic requirements of an aircraft.
Description
Technical Field
The invention relates to a composite material mortise-tenon joint spar structure, which can be applied to a main bearing wing surface of an aircraft and belongs to the technical field of resin-based composite materials.
Background
The high aspect ratio wing surface bears large bending moment and torque under the action of aerodynamic force and the like during flying, the upper wing surface is easy to buckle, and the front edge of the wing surface is easy to generate torsional deformation. Because the composite material has the characteristics of light weight, high strength and high designability, the wing surface with the large aspect ratio is usually designed and manufactured by the composite material at present, and the weight reduction of the aircraft can be realized while the main bearing capacity requirement of the aircraft is ensured.
The foam sandwich type composite material airfoil structure adopts a forming method of winding prepreg after butt joint of a foam core material and a metal joint and then curing, has the advantages of light weight, simple process, strong designability and the like, and is widely applied. However, the rigidity difference between the foam core material and the metal is large, reasonable distribution of the structural rigidity of the airfoil is difficult to realize through a simple connection mode, so that instability damage is easy to occur at the metal-foam connection position, and the bearing capacity of the airfoil is limited to be improved. In addition, the foam core material is easy to deform in the forming process, the quality of the skin is affected, and the bearing capacity of the airfoil surface has fluctuation.
Disclosure of Invention
The invention aims to provide a composite material airfoil adopting tenon-and-mortise structure connection and a forming method thereof, so that the reasonable distribution of the structural rigidity of the airfoil is realized, and the bearing capacity of the airfoil is improved.
The technical scheme of the invention is as follows:
a tenon-and-mortise connected composite material airfoil comprises an airfoil framework and an outer skin; the airfoil framework comprises a metal joint, a composite material solid area and foam which are sequentially connected; and the composite solid area and the foam are positioned and connected through a mortise and tenon structure.
Furthermore, one end of the composite material solid area is connected with a slot on the metal joint through a plug; the other end is connected with the tenon structure of the foam through a mortise structure.
Furthermore, the number of the plugs at one end of the composite material solid area is 3-10, and the length of the plug area is 50-150 mm; the number of the inserting holes of the mortise structure at the other end is 3-10, and the length of the mortise structure between the composite material solid area and the foam is 50-200 mm. Where length refers to the length along the length of the airfoil.
Furthermore, the composite solid area is composed of an upper cover with a tenon structure and a lower cover with a mortise structure, the upper cover and the lower cover are connected in a locating mode through the mortise and tenon structure, the airfoil framework effect of the solid area is guaranteed, and the deformation coordination capacity of the solid area under the bending load effect is improved.
Furthermore, the plug at one end of the composite material solid area alternately extends out from the root parts of the upper cover and the lower shell, and is limited by inserting the metal joint, so that the coordinated deformation of the upper cover and the lower shell in the bearing process is ensured, the rigidity change of the solid area and the metal joint is weakened, and the high-efficiency transmission of the solid area to load is realized.
Furthermore, the outer skin is made of fiber reinforced resin matrix composite materials, and the wing surface framework and the outer skin cooperatively deform to jointly realize bearing.
Further, the composite solid area connects the metal joint and the foam, and the composite solid area and the foam should be in a cured structure when assembled.
Furthermore, the composite material (referring to the composite material of the whole airfoil surface, including the composite material of the outer skin and the composite material of the solid area of the composite material) is a continuous fiber reinforced epoxy resin composite material, wherein the fiber is one of carbon fiber, glass fiber and aramid fiber, and is formed by adopting a mould pressing curing or resin transfer molding method.
Further, the metal joint and the composite solid area are connected together through a plug-slot structure and an adhesive, wherein the adhesive is preferably an epoxy adhesive.
Furthermore, the root of the metal joint is connected with the airfoil connecting mechanism, and the other end of the metal joint is provided with a plurality of grooves which can be positioned and connected with the composite material solid area through a plug-slot structure.
Furthermore, the tenon-and-mortise structures are all isosceles trapezoid structures, and the vertex angle of the isosceles trapezoid is 50-130 degrees, so that the positioning and connecting effects are provided.
Furthermore, the foam root part of the foam is provided with a plurality of tenon structure plugs (tenons) which are connected with mortise structures (mortises) at one end of the solid area of the composite material in a positioning manner.
Furthermore, the foam is polymethacrylimide foam or polyurethane foam, and the appearance requirement is realized by machining.
Further, the foam is preferably reinforced foam, i.e., the compression resistance and load-bearing capacity of the foam can be improved by using reinforcement treatment, including but not limited to using segmented foam, wrapping composite skin outside the foam, adding longitudinal/transverse composite reinforcement ribs inside the foam, etc.
Furthermore, the connecting end of the composite material solid area and the foam is covered with the foam root part by 0-500 mm, so that the foam in the thick skin area is enhanced, the collapse of the foam at the root part is prevented, and the quality of the wing surface skin is improved.
Furthermore, in the solid area of the composite material, the composite material layering is alternately and symmetrically designed at 0 degrees, +45 degrees and-45 degrees, wherein the proportion of 0 degree is not less than 50 percent.
Furthermore, the appearance characteristics of the upper cover and the lower cover of the composite material solid area can be obtained by machining after molding, and can also be obtained by directly molding through controlling a mold.
A method for forming a mortise-tenon joint composite material airfoil comprises the following steps:
(1) Molding an upper cover and a lower shell of the composite material solid area: respectively performing layer laying and post-curing molding in molding tools of an upper cover and a lower shell of the composite material solid area to obtain the upper cover and the lower shell of the composite material solid area;
(2) Preparation of the reinforcing foam: adding the foam core material into a required shape, integrally wrapping the prepreg, and placing the prepreg in a foam reinforced forming mold for mold pressing and curing forming;
(3) Assembly of solid areas and reinforcing foam: polishing the surfaces of the composite solid area and the reinforced foam, coating an adhesive on a contact area, assembling the reinforced foam and the lower shell of the composite solid area through a mortise and tenon structure, and assembling the upper cover of the composite solid area through the root of the reinforced foam and the mortise and tenon structure of the lower shell of the composite solid area to obtain a composite solid area-reinforced foam assembly;
(4) Assembling an airfoil framework (metal joint-solid area-reinforced foam): coating an adhesive on the surface of the metal joint, and inserting a plug of the composite material solid area into a groove of the metal joint to obtain an airfoil framework;
(5) Forming outer skin of the wing surface: and (3) paving an outer skin outside the airfoil skeleton, and curing and forming by adopting a mould pressing method or a resin transfer molding method to obtain an airfoil product.
Further, the assembly sequence of the airfoil skeleton is as follows: and (3) installing the plug with the tenon structure at the foam root part into the mortise structure of the lower shell of the composite material solid area, positioning and connecting the upper cover of the composite material solid area through the tenon structure of the upper cover of the solid area, the mortise structure of the lower shell and the mortise structure connected with the foam, and inserting the assembled composite material solid area-foam assembly into the groove of the metal joint through the plug of the composite material solid area to obtain the complete airfoil framework.
The beneficial effects of the invention are:
according to the composite material airfoil, the metal joint and the foam are positioned and connected by adopting the composite material solid area through the mortise and tenon structure, and by adding the composite material solid area, the rigidity gradual transition from the metal joint to the composite material solid area and then to the foam is realized, and a high-efficiency load transfer path from the foam to the solid area to the metal joint is provided; meanwhile, the composite material solid area components connected through the tenon-and-mortise structures can realize coordinated deformation, so that the elastic deformation capacity of the airfoil structure is improved, and the elastic deformation capacity of the airfoil structure is improved while the strength of the airfoil structure is ensured; in addition, the composite material solid area connected with the foam root part supports the root part area which is most prone to collapse, the problems that the outer skin forming quality is poor and the volatility is high due to collapse of the foam root part of a traditional airfoil structure are solved, and the internal quality and the process stability of the airfoil structure are further improved. Compared with the traditional structure airfoil structure, the airfoil adopting the structure has the advantages of more reasonable rigidity distribution, stronger elastic deformation capability and better internal quality, is more firmly connected when bearing the action of bending moment and torque, has higher deformation coordination capability, can obviously improve the bearing capacity of the airfoil, and has lighter weight on the basis of meeting the dynamic requirements of an aircraft.
Drawings
FIG. 1 is a schematic illustration of a composite airfoil skeleton construction.
FIG. 2 is an exploded view of a composite airfoil skeleton.
Fig. 3 is a schematic view of a composite solid area upper cover.
FIG. 4 is a schematic view of a composite solid section lower shell.
FIG. 5 is an assembled view of solid areas of composite material.
FIG. 6 is a schematic representation of a composite airfoil reinforcing foam structure.
FIG. 7 is a flow chart of the composite airfoil skeleton assembly.
FIG. 8 is a structural view of a composite material airfoil connected in a mortise and tenon manner.
Detailed Description
The invention is further described below with reference to the figures and specific examples, without limiting the scope of the invention.
The invention provides a mortise-tenon joint composite material airfoil which comprises an airfoil framework and an outer skin. The airfoil framework is shown in figure 1 and comprises a metal joint, a composite material solid area and foam which are sequentially connected, and the composite material solid area and the foam are positioned and connected through a mortise and tenon joint structure. In this example, a reinforcing foam was used as the foam. In the embodiment, one end of the composite solid area is provided with a plug, is connected with the slot on the metal joint through the plug and is fixed by adopting an adhesive; the other end of the composite material solid area is connected with the tenon structure of the foam through a mortise structure.
In one embodiment of the invention, the composite solid area comprises an upper cover and a lower cover, and the upper cover and the lower cover are connected in a locating manner through a mortise and tenon joint structure as shown in fig. 2. Fig. 3 and 4 further illustrate the mortise and tenon joint structure of the upper cover and the lower cover of the composite material solid area. Fig. 5 is a schematic view of the assembled upper and lower shells of the composite solid section. The plug at one end of the composite material solid area alternately extends out from the roots of the upper cover and the lower shell and is inserted into the metal joint for limiting, so that the upper cover and the lower shell are ensured to be coordinately deformed in the bearing process. The number of the plugs at one end of the composite material solid area is 3-10, and the length of the plug area is 50-150 mm; the number of the jacks of the mortise structure at the other end is 3-10, and the length of the mortise structure between the composite material solid area and the foam is 50-200 mm.
In one embodiment of the present invention, the foam is a reinforced foam, i.e., the compression and load bearing capacity of the foam can be enhanced by using reinforcement treatments including, but not limited to, using segmented foam, wrapping a composite skin over the foam, adding longitudinal/transverse composite stiffeners within the foam, etc. The reinforcing foam has the appearance shown in fig. 6 and the structure shown in fig. 8.
In one embodiment of the invention, the outer skin is a fiber reinforced resin-based composite material.
In one embodiment of the invention, the mortise and tenon joint structure is an isosceles trapezoid structure, and the vertex angle of the isosceles trapezoid is 50-130 degrees.
In one embodiment of the invention, the connecting end of the composite solid area and the foam covers the root of the foam by 0-500 mm, so that the foam in the thick skin area is reinforced.
In one embodiment of the invention, the composite material layering of the composite material solid area is in an alternating symmetrical design of 0 degrees, +45 degrees and 45 degrees, wherein the 0 degree is not less than 50 percent.
In an embodiment of the present invention, a method for forming a mortise-tenon joint composite material airfoil is provided, a main flow is shown in fig. 7, and the method specifically includes the following steps:
respectively layering in forming tools of an upper cover and a lower shell of a composite material solid area, closing the dies and carrying out die pressing and curing to obtain the upper cover and the lower shell of the composite material solid area;
machining a foam core material into a theoretical shape, integrally wrapping the prepreg, and placing the prepreg in a foam reinforced forming die for die pressing and curing;
polishing the surfaces of the composite material solid area and the reinforced foam, coating an adhesive on a contact area, assembling the reinforced foam and the lower shell of the composite material solid area through a mortise and tenon structure, and assembling the upper cover of the composite material solid area through the root of the reinforced foam and the mortise and tenon structure of the lower shell of the composite material solid area to obtain a composite material solid area-reinforced foam component;
coating an adhesive on the surface of the metal joint, and inserting a plug of the solid area of the composite material into the metal joint to obtain an airfoil framework;
and (4) laying an outer skin outside the airfoil skeleton, and molding by adopting a mold pressing curing process to obtain an airfoil product.
FIG. 8 is a view of a mortise and tenon joint for a composite airfoil wherein the root of the metal joint is attached to the airfoil attachment mechanism.
In one embodiment of the present invention, the assembling sequence of the airfoil framework is as follows: the tenon structure at the root of the foam is arranged on the mortise structure of the lower shell of the composite solid area, the tenon structure of the upper cover of the composite solid area, the mortise structure of the lower shell and the mortise structure connected with the foam are positioned and connected, the assembled composite solid area-foam assembly is inserted into the groove of the metal joint through the plug of the composite solid area, a complete airfoil framework is obtained, and the rigidity transition from the foam to the composite solid area to the metal joint is realized.
In one embodiment of the invention, the method for forming the mortise-tenon joint composite material airfoil comprises the following specific steps:
1. preparation of Sandwich foam
The density is 110kg/m 3 The PMI foam machine of (1) adds the appearance that requires, the foam divides into four along the chord direction, divides into 3 areas from root to wing tip in total along the wing span direction: plug area with tenon structure, 3mm skin district, 2mm skin district.
2. Foam-reinforced lay-up, curing
And each foam is externally wrapped with a unidirectional carbon fiber prepreg paving layer group with the paving direction of [90/-45/0/+45 ]. Splicing the four foams together, putting the four foams into a foam reinforcing tool, placing a die on a press panel, setting the temperature at 100 ℃, pressurizing at 3MPa when the temperature of the die reaches 80 ℃, and checking that the die closing gap is not more than 0.1mm. The temperature of the press is set to be 150 ℃, the temperature of the press is adjusted to be 120 ℃ when the temperature of the die reaches 120 ℃, and the temperature is kept for 2h. And closing the press, and demolding to obtain the reinforced foam after the mold is naturally cooled to below 50 ℃.
3. Layering solid areas of the composite material and curing
Unidirectional carbon fiber prepreg according to [ +45/0/0/-45]、[-45/0/0/+45]And [0] 4 The cloth is folded in the laying direction, and the cloth is cut by a cloth cutting machine according to a specified blanking sample plate. Respectively laying layers in the upper cover forming die and the bottom shell forming die of the solid area, wherein the laying direction is [ +45/0/0/-45 [)]，[0] 4 ，[-45/0/0/+45]. And after the paving is finished, closing the upper die.
And (3) hoisting the die to a press, setting the temperature of the press to be 100 ℃, pressurizing to 3MPa when the temperature of the die reaches 80 ℃, and checking that the die closing gap is not more than 0.1mm. The temperature of the press is set to be 150 ℃, when the temperature of the die reaches 120 ℃, the temperature of the press is adjusted to be 120 ℃, and the temperature is kept for 2 hours. And closing the press, and demolding after the mold is naturally cooled to below 50 ℃ to obtain the upper cover and the lower shell of the solid area.
4. Reinforced foam, solid area and metal joint assembly
Polishing the surfaces of the upper cover and the lower shell of the reinforced foam and the composite solid area, pasting epoxy adhesive on the surfaces of the upper cover and the lower shell, installing a plug with a tenon structure at the foam root into the mortise structure of the lower shell of the composite solid area, and positioning and connecting the upper cover of the composite solid area through the tenon structure of the upper cover of the solid area, the mortise structure of the lower shell and the mortise structure connected with the foam. And filling an epoxy adhesive in the groove of the metal joint, inserting the assembled solid area-foam assembly into the groove of the metal joint through the solid area plug, and curing the adhesive to obtain the complete airfoil framework.
5. Airfoil skin ply
The span direction of the airfoil skeleton is divided into 3 areas from the root to the wingtip: 5mm skin area (metal joint area + solid area), 3mm skin area, 2mm skin area.
Covering 16 layers of unidirectional carbon fiber prepreg in a skin area of 5mm of an airfoil framework, wherein the layering direction is [ + 45/0/0/-45/0/0/90 ]] s ；
8 layers of unidirectional carbon fiber prepreg are coated in a 3mm skin area of a wing surface framework, and the layering direction is [0/0/0/90 ]] s ；
Covering 16 layers of unidirectional carbon fiber prepreg in a skin area of 2mm of an airfoil framework, wherein the layering direction is [ + 45/0/0/-45/0/0/90 ]] s 。
6. Curing of airfoil surfaces
And (3) loading the airfoil into a forming die, hoisting the die onto a press, hoisting the die onto the press, setting the temperature of the press to be 100 ℃, pressurizing to be 3MPa when the temperature of the die reaches 80 ℃, and checking that the die closing gap is not more than 0.1mm. Setting the temperature of the press at 150 ℃, adjusting the temperature of the press to 120 ℃ when the temperature of the die reaches 120 ℃, preserving heat for 2h, and closing the press.
7. Airfoil demolding
And (5) demolding after the mold is naturally cooled to below 50 ℃.
The particular embodiments of the present invention disclosed above are illustrative only and not intended to be limiting as to the scope of the invention which is to be given the full breadth of the claims appended and any and all modifications and variations which may be apparent to those skilled in the art may be resorted to without departing from the spirit and scope of the invention. The invention should not be limited to the disclosure of the embodiments in the present specification, but the scope of the invention is defined by the appended claims.
Claims (10)
1. The composite material airfoil of the mortise and tenon joint is characterized by comprising an airfoil framework and an outer skin; the airfoil framework comprises a metal joint, a composite material solid area and foam which are sequentially connected; and the composite solid area and the foam are positioned and connected through a mortise and tenon structure.
2. The mortise and tenon jointed composite airfoil of claim 1, wherein one end of the composite solid area is provided with a plug, is connected with the slot on the metal joint through the plug, and is fixed by an adhesive; the other end of the composite material solid area is connected with the tenon structure of the foam through a mortise structure.
3. The mortise and tenon joint composite airfoil of claim 2, wherein the composite solid section comprises an upper cover having a mortise structure and a lower cover having a mortise structure, the upper cover and the lower cover being positionally joined by the mortise and tenon joint structure.
4. The mortise and tenon jointed composite airfoil of claim 3, wherein the plug at one end of the composite solid section alternately extends from the root portions of the upper shell and the lower shell and is inserted into the metal joint for limiting, so as to ensure the coordinated deformation of the upper shell and the lower shell during the bearing process.
5. The mortise and tenon jointed composite airfoil of claim 2, wherein the number of plugs at one end of the composite solid region is 3-10, and the length of the plug region is 50-150 mm; the number of the jacks of the mortise structure at the other end is 3-10, and the length of the mortise structure between the composite material solid area and the foam is 50-200 mm.
6. The mortise and tenon jointed composite airfoil of claim 1, wherein the foam is a reinforced foam; the outer skin and the composite solid area are made of fiber reinforced resin matrix composite materials.
7. The mortise and tenon joint composite material airfoil of claim 1, wherein the mortise and tenon joint structure is an isosceles trapezoid structure, and an apex angle of the isosceles trapezoid is 50-130 °.
8. The mortise and tenon joint composite material airfoil of claim 1, wherein the connecting end of the composite material solid area and the foam covers the root of the foam by 0-500 mm, so that the foam in a thick skin area is reinforced; the composite material layering of the solid area of the composite material is alternately and symmetrically designed at 0 degrees, +45 degrees and-45 degrees, wherein the 0 degree is not less than 50 percent.
9. A method for forming a mortise-tenon joint composite material airfoil is characterized by comprising the following steps of:
respectively carrying out layer laying and post-curing molding in molding tools of the upper cover and the lower shell of the composite material solid area to obtain the upper cover and the lower shell of the composite material solid area;
machining a foam core material into a theoretical shape, integrally wrapping the prepreg, and placing the prepreg in a foam reinforced forming mould for mould pressing, curing and forming;
polishing the surfaces of the composite solid area and the reinforced foam, coating an adhesive on a contact area, assembling the reinforced foam and the lower shell of the composite solid area through a mortise and tenon structure, and assembling the upper cover of the composite solid area through the root of the reinforced foam and the mortise and tenon structure of the lower shell of the composite solid area to obtain a composite solid area-reinforced foam assembly;
coating an adhesive on the surface of the metal joint, and inserting a plug of the composite material solid area into a groove of the metal joint to obtain an airfoil framework;
and (3) laying an outer skin outside the airfoil skeleton, and curing and forming by adopting a mould pressing method or a resin transfer molding method to obtain an airfoil product.
10. The method of claim 9, wherein the order of assembly of the airfoil skeleton is: the tenon structure at the root of the foam is arranged on the mortise structure of the lower shell of the composite solid area, the upper cover of the composite solid area is positioned and connected through the tenon structure of the upper cover, the mortise structure of the lower shell and the mortise structure connected with the foam, the assembled composite solid area-foam assembly is inserted into the groove of the metal joint through the plug of the composite solid area, a complete airfoil framework is obtained, and the rigidity transition from the foam to the composite solid area to the metal joint is realized.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211413672.6A CN115742343A (en) | 2022-11-11 | 2022-11-11 | Tenon-and-mortise connected composite material airfoil and forming method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211413672.6A CN115742343A (en) | 2022-11-11 | 2022-11-11 | Tenon-and-mortise connected composite material airfoil and forming method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116215592A (en) * | 2023-03-24 | 2023-06-06 | 新创碳谷集团有限公司 | Connection structure, connection method and railway traffic vehicle body |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116215592A (en) * | 2023-03-24 | 2023-06-06 | 新创碳谷集团有限公司 | Connection structure, connection method and railway traffic vehicle body |
| CN116215592B (en) * | 2023-03-24 | 2023-10-17 | 新创碳谷集团有限公司 | Connection structure, connection method and railway traffic vehicle body |
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