Self-supporting wing based on planar composite interlayer material

Abstract

The invention discloses a self-supporting wing based on a planar composite sandwich material. The self-supporting wing based on the planar composite sandwich material comprises a skin formed by bending a composite sandwich plate for multiple times, a plurality of webs and a self-supporting structure located in the skin. Each web plate comprises a first plate and a second plate which are stacked; the self-supporting structure comprises a plurality of first wing ribs, a plurality of second wing ribs and a plurality of third wing ribs which are arranged in an array along the extension direction of the wing; the plurality of first wing ribs are formed by cutting a first plate part of a web plate close to the leading edge of the wing; the plurality of second wing ribs are positioned between two adjacent webs and are formed by cutting the first plate parts of the webs close to the rear edge of the wing; and a plurality of third wing ribs are positioned between the web and the wing trailing edge and are formed by cutting the bottom wall part of the skin. The self-supporting wing based on the planar composite sandwich material is formed by bending and cutting the composite sandwich plate, so that the number of components of the wing is greatly reduced, and material redundancy is eliminated.

Description

Technical Field

[0001] This application relates to the field of wing technology, and in particular to a self-supporting wing based on a planar composite sandwich material. Background Technology

[0002] The wing is a key component of a fixed-wing aircraft, mounted on both sides of the fuselage to generate lift for flight. The wing structure includes components such as skin, spars, longitudinal walls, stringers, ribs, and fuselage joints. While the longitudinal walls, stringers, ribs, and other auxiliary load-bearing components effectively distribute the aerodynamic loads of the wing and ensure its load-bearing capacity, the large number and compact distribution of these components lead to material surplus and excessive assembly time, hindering the efficient utilization of structural materials.

[0003] To address these issues, some aircraft wings currently employ composite sandwich skin structures. These structures increase skin thickness, significantly improving the wing's load-bearing capacity and effectively reducing the number of longitudinal walls, stringers, ribs, and other auxiliary load-bearing components. This reduces the wing's structural weight and improves assembly efficiency. However, secondary load-bearing components used for conformal maintenance and load distribution still exhibit material redundancy. Summary of the Invention

[0004] This application provides a self-supporting wing based on a planar composite sandwich material, which solves the technical problem in the prior art of having a large number of secondary load-bearing components for shape preservation and load distribution in the wing.

[0005] This application provides a self-supporting wing based on a planar composite sandwich material. The self-supporting wing includes a skin formed by multiple bending of a composite sandwich panel and multiple webs, as well as a self-supporting structure located inside the skin. Each web includes a first plate and a second plate stacked together, with the first plate facing the leading edge of the wing and the second plate facing the trailing edge. The self-supporting structure includes multiple first ribs, multiple second ribs, and multiple third ribs arranged in an array along the wing's extension direction. The multiple first ribs are located near the leading edge of the wing. The first plate portion of the web of the wing is cut to form the first plate portion, and the front ends of the plurality of first wing ribs are connected to the inner side of the leading edge of the wing; the plurality of second wing ribs are located between two adjacent webs, and are formed by cutting the first plate portion of the web near the trailing edge of the wing, and the front ends of the plurality of second wing ribs are connected to the second plate of the web near the leading edge of the wing; the plurality of third wing ribs are located between the web and the trailing edge of the wing, and are formed by cutting the bottom wall portion of the skin, and the top ends of the plurality of third wing ribs are connected to the upper wall of the skin.

[0006] In one possible implementation, the inner surface of the leading edge of the wing is provided with a plurality of first fixing grooves, and the front ends of the plurality of first wing ribs extend into the plurality of first fixing grooves.

[0007] In one possible implementation, in two adjacent webs, the second plate of the web near the leading edge of the wing has a plurality of second fixing slots, and the front end of the second wing rib extends into the plurality of second fixing slots.

[0008] In one possible implementation, the upper wall of the skin is provided with a plurality of third fixing slots, the plurality of third fixing slots being located between the web and the trailing edge of the wing, and the top of the third wing rib extending into the plurality of third fixing slots.

[0009] This application provides a self-supporting wing based on a planar composite sandwich material. The skin and multiple webs of this self-supporting wing are formed by repeatedly bending composite sandwich panels. The self-supporting structure includes multiple first ribs, multiple second ribs, and multiple third ribs. These ribs are formed by partially cutting the composite sandwich panel. The webs, first ribs, second ribs, and third ribs together constitute the conformal and load-bearing components of the wing. This self-supporting wing based on a planar composite sandwich material, formed by bending and cutting composite sandwich panels, significantly reduces the number of wing components and eliminates material redundancy. Attached Figure Description

[0010] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments of this application or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0011] Figure 1 This is a schematic diagram of the structure of a self-supporting wing based on planar composite sandwich material provided in an embodiment of this application; Figure 2 Left view of a self-supporting wing based on planar composite sandwich material provided in an embodiment of this application; Figure 3 A structural schematic diagram of a composite material sandwich panel for manufacturing an airfoil is provided for embodiments of this application; Figure 4 A schematic diagram showing the cutting of the composite sandwich panel that needs to be bent, as provided in the embodiments of this application; Figure 5 A schematic diagram of a bent composite sandwich panel provided in an embodiment of this application; Figure 6 A schematic diagram showing the cutting of the composite sandwich panel provided in the embodiments of this application, which requires bending to form a web; Figure 7 This is a schematic diagram of the web structure provided in an embodiment of this application; Figure 8 The airfoil pressure differential distribution diagram provided in the embodiments of this application; Figure 9 A schematic diagram of a single-piece wing designed based on traditional design methods; Figure 10 To Figure 9 A simplified schematic diagram of the wing with a modified midplane structure.

[0012] Reference numerals: 100-Skin; 110-First fixing groove; 120-Third fixing groove; 200-Web plate; 210-First plate; 220-Second plate; 221-Second fixing groove; 300-Self-supporting structure; 310-First wing rib; 320-Second wing rib; 330-Third wing rib; 400-Composite sandwich panel; 410-Upper panel; 420-Core panel; 430-Lower panel; 440-Slit. Detailed Implementation

[0013] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0014] In the description of the embodiments of this application, it should be noted that the terms "center," "upper," "lower," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the embodiments of this application and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components. The term "multiple" indicates two or more. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.

[0015] This application provides a self-supporting wing based on a planar composite sandwich material, such as... Figure 1 and Figure 2 As shown, the self-supporting wing based on planar composite sandwich material includes a skin formed by multiple bending of composite sandwich panels and multiple webs, as well as a self-supporting structure located inside the skin.

[0016] Figure 4 The diagram illustrates the cutting of a composite sandwich panel that requires bending. Specifically, cuts are made in the upper and core panels of the composite sandwich panel to create slits. Figure 4 The composite sandwich panel shown is bent to form Figure 5 The structure shown. When manufacturing the wing skin, the cutting angles on both sides of the cut are controlled according to the actual bending angle required.

[0017] Figure 6 The diagram illustrates the cutting of a composite sandwich panel to form a web. Specifically, three slits are cut into the composite sandwich panel to... Figure 6 Taking the orientation shown as an example, the cuts on both sides face upwards, and the cut in the middle faces downwards. The cuts on both sides are formed by cutting the upper and core panels of the composite sandwich panel, and the cut in the middle is formed by cutting the lower and core panels of the composite sandwich panel. Figure 6 The composite sandwich panel shown is bent to form Figure 7 The web shown.

[0018] For example, Figure 1 and Figure 2 The wing shown includes three webs located at 10%, 30%, and 50% of the wing chord length, respectively.

[0019] like Figure 2 and Figure 7 As shown, each web includes a first plate and a second plate stacked together, with the first plate facing the leading edge of the wing and the second plate facing the trailing edge of the wing.

[0020] Continue to refer to Figure 1 and Figure 2 The self-supporting structure includes multiple first ribs, multiple second ribs, and multiple third ribs arranged in an array along the wing's extension direction. The multiple first ribs are formed by cutting a portion of the first plate of the web near the wing's leading edge, and the front ends of the multiple first ribs are connected to the inner surface of the wing's leading edge. The multiple second ribs are located between two adjacent webs, formed by cutting a portion of the first plate of the web near the wing's trailing edge, and the front ends of the multiple second ribs are connected to the second plate of the web near the wing's leading edge. The multiple third ribs are located between the web and the wing's trailing edge, formed by cutting a portion of the bottom wall of the skin, and the top ends of the multiple third ribs are connected to the top wall of the skin.

[0021] Multiple first, second, and third ribs are used to engage with the web to maintain the shape of the wing skin and bear loads, ensuring wing stability during aircraft operation. Compared to existing wing structures, this self-supporting wing based on planar composite sandwich materials is formed by bending and cutting composite sandwich panels, significantly reducing the number of wing components, eliminating material redundancy, simplifying assembly, and facilitating rapid wing prototyping.

[0022] Reference Figure 4 The inner surface of the wing leading edge has multiple first fixing slots, and the front ends of multiple first wing ribs extend into these slots. These first fixing slots secure the front ends of the multiple first wing ribs, making the connection between the web and the wing leading edge more robust and secure.

[0023] In some other embodiments of this application, the front ends of the plurality of first ribs can be directly bonded to the inner side of the leading edge of the wing.

[0024] Reference Figure 4 In two adjacent webs, the second plate of the web closest to the wing leading edge has multiple second fixing slots, and the front ends of the second wing ribs extend into these slots. These multiple fixing slots secure the front ends of the multiple second wing ribs, making the connection between the webs more robust.

[0025] In some other embodiments of this application, the front end of the second wing rib can be directly bonded to the first plate of the adjacent web.

[0026] Reference Figure 4 The upper wall of the wing skin has multiple third fixing slots located between the web and the trailing edge of the wing. The tips of the third wing ribs extend into these slots. These slots secure the tips of the third wing ribs, making the connection between the top and bottom of the wing skin more robust.

[0027] In some other embodiments of this application, the top of the third rib can be directly bonded to the upper wall of the skin.

[0028] In manufacturing the self-supporting wing based on planar composite sandwich material in the embodiments of this application, a composite sandwich panel is cut, then bent and bonded. Figure 3 A schematic diagram of the cut composite sandwich panel is shown.

[0029] In addition, thin plastic sheets can be glued to the joints and gaps of the self-supporting wing based on planar composite sandwich material to achieve continuous closure of the wing shape.

[0030] The following design example illustrates the design process and specific structure of a self-supporting wing based on planar composite sandwich materials.

[0031] The first step is to determine the wing size and related airfoil parameters based on the mission requirements of a certain type of UAV. The parameter indicators are shown in Table 1. A straight wing with a large aspect ratio can be obtained, and the wing adopts a high-wing configuration.

[0032] Table 1 parameter Parameter value <![CDATA[Reference area / m 2 > 0.72 <![CDATA[Wing loading / kg / m 2 > 6.97 Aspect Ratio 8 Trapezoid ratio 1 Exhibition length / m 2.4 Mean aerodynamic chord length (root chord length) / m 0.3 Leading edge sweep angle / ° 0 diagonal / ° 0 Airfoil AG34 (15%) Installation angle / ° 1 Twist angle / ° 0 The second step involves adopting a hybrid wing structure combining multi-web and single-piece designs, based on the structural characteristics of the composite sandwich panel. This structure features a thicker skin to distribute the load-bearing material while also having a single-piece internal rib structure to strengthen the chordal load-bearing capacity of the wing.

[0033] The maximum relative thickness of this aircraft's airfoil is located at 30% of the wing chord length, such as... Figure 8 As shown, based on the simulated airfoil pressure differential distribution and traditional empirical design methods, the main load-bearing web is determined to be three pieces, located at 10%, 30%, and 50% of the wing chord length, respectively.

[0034] The third step, based on the wing dimensions, incorporates the design features of a single-piece wing, adding wing rib support structures. Building upon traditional design experience, the spanwise distribution of the wing ribs is designed, using 30% of the chord length as the rib spacing. The design effect is as follows: Figure 9 As shown.

[0035] Step 4: Based on the determined internal structure of the wing, simplify the redundant materials and complete the self-supporting structure design.

[0036] First, such as Figure 10 As shown, based on the integrated forming concept of wing components, the web structure is simplified and split in a plane to achieve continuous bending forming of the flat plate structure, thus completing the design of the wing spanwise support structure.

[0037] Secondly, based on the distribution of the wing ribs, a self-supporting structure for the wing ribs was designed. This self-supporting structure includes multiple first ribs, multiple second ribs, and multiple third ribs. The main load-bearing components are the upper and lower skins. Multiple webs inside the skins and the self-supporting structure achieve wing conformity preservation and internal force transmission.

[0038] Finally, a mortise and tenon joint design method is introduced. Multiple first ribs are formed by cutting the first plate portion of the web near the wing's leading edge. Multiple first fixing grooves are formed on the inner side of the wing's leading edge, and the front ends of the multiple first ribs extend into these grooves. Multiple second ribs are located between adjacent webs. Multiple second ribs are formed by cutting the first plate portion of the web near the wing's trailing edge. Multiple second fixing grooves are formed on the second plate portion of the web near the wing's leading edge, and the front ends of the second ribs extend into these grooves. Multiple third ribs are located between the web and the wing's trailing edge. Multiple third ribs are formed by cutting the bottom wall portion of the skin. Multiple third fixing grooves are formed on the upper wall of the skin. These grooves are located between the web and the wing's trailing edge, and the top ends of the third ribs extend into these grooves.

[0039] Step 5: Use planar cutting technology to trim the airfoil bending creases and the folding and assembly interface creases of the self-supporting structure. By leaving gaps for the trimming creases, the bending design of the wing structure is completed. The planar design diagram is shown below. Figure 3 As shown.

[0040] Step 6: Glue thin plastic sheets to the openings and gaps to achieve continuous closure of the wing shape.

[0041] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0042] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.

Claims

1. A self-supporting wing based on a planar composite sandwich material, characterized in that, It includes a skin formed by multiple bending of a composite sandwich panel and multiple webs, as well as a self-supporting structure located inside the skin; Each of the webs includes a first plate and a second plate stacked together, the first plate facing the leading edge of the wing and the second plate facing the trailing edge of the wing; The self-supporting structure includes multiple first wing ribs, multiple second wing ribs, and multiple third wing ribs arranged in an array along the wing extension direction. The plurality of first ribs are formed by cutting a portion of the first plate of the web near the leading edge of the wing, and the front ends of the plurality of first ribs are connected to the inner surface of the leading edge of the wing. The plurality of second wing ribs are located between two adjacent webs, and are formed by cutting a portion of the first plate of the web near the trailing edge of the wing, and the front ends of the plurality of second wing ribs are connected to the second plate of the web near the leading edge of the wing; The plurality of third ribs are located between the web and the trailing edge of the wing, are formed by cutting the bottom wall portion of the skin, and the top ends of the plurality of third ribs are connected to the upper wall of the skin.

2. The self-supporting wing based on planar composite sandwich material according to claim 1, characterized in that, The inner side of the leading edge of the wing is provided with a plurality of first fixing grooves, and the front ends of the plurality of first wing ribs extend into the plurality of first fixing grooves respectively.

3. The self-supporting wing based on planar composite sandwich material according to claim 1, characterized in that, In two adjacent webs, the second plate of the web near the leading edge of the wing is provided with a plurality of second fixing slots, and the front end of the second wing rib extends into the plurality of second fixing slots.

4. The self-supporting wing based on planar composite sandwich material according to claim 1, characterized in that, The upper wall of the skin is provided with a plurality of third fixing grooves, which are located between the web and the trailing edge of the wing, and the top of the third wing rib extends into the plurality of third fixing grooves.

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