Skin of aircraft component and aircraft comprising skin
By decomposing the skin of the aircraft into multiple skin units and forming a complete skin through the splicing structure, the problem of raising the skin to increase air resistance in existing technologies has been solved. Efficiency.
Patent Information
- Application Number
- CN202421380299.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-17
- Publication Date
- 2025-01-28
- Estimated Expiration
- 2034-06-17
AI Technical Summary
The skins of existing aircraft will form bumps during production and fixation, increasing air resistance, and using metal materials to increase load and manufacturing costs, reducing range.
Multiple skin units are adopted to form a skin module through the splicing structure, and then the modules are spliced along the axis into complete skin. The convex edges and groove structures and adhesives are used to enhance the stitching strength to reduce air resistance.
The air resistance of the aircraft during the flight was reduced, the skin weight was reduced, the cruise mileage of the aircraft was increased, and the processing process was simplified and the manufacturing cost was reduced.
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Figure CN222408558U_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of aircraft, and in particular to a skin of an aircraft component. Background Art
[0002] The background description provided herein is intended to generally present the context of the disclosure.
[0003] The skin of an aircraft refers to the outer shell covering the surface of the aircraft structure, and is the main load-bearing structure that bears air resistance during flight. The skin is usually designed to be streamlined to reduce the air resistance encountered during flight, reduce energy consumption and thus increase range. Aircraft in the prior art usually use metal materials to make the skin, and use riveting, welding and other fixing methods in the process of making the skin and fixing the skin to the aircraft frame. However, such fixing methods usually form bulges on the surface of the skin, thereby increasing the air resistance encountered by the aircraft during flight. At the same time, the process of making the skin using welding, riveting and other methods is relatively complicated, which increases manufacturing costs. In addition, the use of skin made of metal materials will also increase the load of the aircraft, thereby increasing flight energy consumption and reducing the range of the aircraft.
[0004] Therefore, it is desirable to provide a new aircraft skin. Utility Model Content
[0005] This section introduces the concepts of the present application in a simplified form, which are further reflected in the detailed description below. This section is not intended to identify key features or essential features of the claimed subject matter, nor is it intended to be used as an aid in determining the scope of the claimed subject matter.
[0006] According to a first aspect of the present application, a skin of an aircraft component is provided, which includes a plurality of skin units, wherein the edges of the skin units are provided with splicing structures extending along the edges, and wherein the skin units are spliced together along the circumference of the component through the splicing structure to form skin modules, and the skin modules are spliced together along the axial direction of the component through the splicing structure to form the skin.
[0007] Preferably, the splicing structure includes a first splicing structure, and at least one skin module is spliced by skin units through the first splicing structure, wherein the first splicing structure includes a first rib, a first groove, a second rib and a second groove, wherein the first rib and the first groove are located in the same skin unit, and the second rib and the second groove are located in another same skin unit, and wherein the first rib is close to the outside of the skin unit where it is located, the first groove is close to the inside of the skin unit where it is located, the second rib is close to the inside of the skin unit where it is located, and the second groove is close to the outside of the skin unit where it is located, and wherein the first rib is inserted into the second groove, and the second rib is inserted into the first groove.
[0008] Preferably, the splicing structure also includes a second splicing structure, and at least one skin module is spliced together by skin units through the second splicing structure, wherein the second splicing structure includes a third ridge and a third groove respectively arranged on the thickness plane of each two mutually spliced skin units, and the third ridge is inserted into the third groove.
[0009] Preferably, the splicing structure also includes a third splicing structure, and the skin modules are spliced together through the third splicing structure, wherein the third splicing structure includes a fourth ridge and a fourth groove arranged on every two skin modules spliced together, the bottoms of the fourth ridge and the fourth groove both protrude toward the inner side of the skin module, and the fourth ridge is inserted into the fourth groove.
[0010] Preferably, the side wall of the first groove close to the inner side of the skin unit and the second ridge both protrude toward the inner side of the skin unit where they are located.
[0011] Preferably, the side surfaces of the first rib and the second rib are respectively provided with a first mounting hole and a second mounting hole along the length direction of the first rib and the second rib, wherein the rod can be inserted into the first mounting hole and the second mounting hole.
[0012] Preferably, at least one skin module is provided with a third mounting hole, and the rod inserted into and passing through the first mounting hole can be inserted into the third mounting hole.
[0013] Preferably, the rod is a carbon fiber rod, an aluminum rod or a titanium alloy rod.
[0014] Preferably, adhesive is coated between the joining surfaces of the splicing structure.
[0015] Preferably, the interior of the skin unit has a hollow array.
[0016] Preferably, ribs are provided on the inner side of the skin unit.
[0017] Preferably, the outer surface of the skin is covered with fiberglass cloth.
[0018] Preferably, the skin is at least one of a nose skin, a fuselage skin, a tail skin, a wing skin, and a landing gear skin.
[0019] In another aspect of the present application, an aircraft is provided. The aircraft includes a skin according to the principles of the present application. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] Other or additional features, advantages and details are presented by way of example only in the following detailed description of the embodiments. In the drawings:
[0021] Figure 1 The nose skin according to the principles of the present application is schematically shown;
[0022] Figure 2 The first skin module of the nose skin according to the principles of the present application is schematically shown;
[0023] Figure 3 、 Figure 4 Schematically shows a first splicing structure according to the principles of the present application;
[0024] Figure 5 Schematically shows a cross-sectional view of a second skin module according to the principles of the present application;
[0025] Figure 6 、 Figure 7 Schematically illustrates a second splicing structure according to the principles of the present application;
[0026] Figure 8 、 Figure 9 Schematically illustrates a third splicing structure according to the principles of the present application;
[0027] Figure 10 The figure schematically shows the inner structure of the nose skin according to the principles of the present application;
[0028] Figure 11 Schematically illustrates a rib of a skin unit according to the principles of the present application; and
[0029] Figure 12 The internal hollow array of the skin unit according to the principles of the present application is schematically shown.
[0030] It should be understood that throughout the drawings, corresponding reference numerals identify similar or corresponding components or features. It should also be understood that the drawings are not necessarily drawn to scale and are merely schematic illustrations of exemplary embodiments of the present application and are not intended to limit the present application. DETAILED DESCRIPTION
[0031] The following describes exemplary embodiments of the present application in conjunction with the accompanying drawings. It should be understood that the following description is merely exemplary in nature and is not intended to limit the present application, application, or use.
[0032] The present application will now be further described. In the following paragraphs, different aspects of the present application are defined in more detail. Unless expressly indicated to the contrary, each aspect so defined may be combined with any other aspect(s). In particular, any feature indicated as preferred or advantageous may be combined with any other feature(s) indicated as preferred or advantageous.
[0033] In response to the problems in the prior art, the present application provides a new skin for an aircraft component, wherein the skin of the aircraft component is formed by splicing skin units together.
[0034] The following is an example of the skin of the nose of an aircraft to illustrate the principle of this application. Figure 1 , shows a skin 100 for the nose portion of a aircraft according to the principles of the present application. The skin 100 includes a plurality of skin units 110. The skin units 110 are curved and thin-walled. The edges of the skin units 110 are straight and provided with a splicing structure extending along the edges, so that the plurality of skin units 110 can be spliced together. Specifically, the plurality of skin units 110 are spliced together along the circumference of the component to form a first skin module 121 and a second skin module 122. The first skin module 121 and the second skin module 122 are spliced together along the axial direction of the component, that is, along the length of the component to form the skin 100.
[0035] The number of skin modules can be determined based on the size of the component and the size of the skin unit 110. For example, for a smaller component, only one skin module can be used as a complete skin. The skin unit 110 according to the principles of the present application can be triangular or quadrilateral, or substantially triangular or quadrilateral.
[0036] Refer to the attached Figure 2 , Attachment Figure 3 and attached Figure 4 The splicing structure may include a first splicing structure 130, and the first skin module 121 is spliced by the skin unit 110 through the first splicing structure 130. The first splicing structure 130 includes a first rib 131 and a first groove 132 provided on the first skin unit 110a, and a second rib 133 and a second groove 134 provided on the second skin unit 110b. The first rib 131 is close to the outer side of the first skin unit 110a, and the first groove 132 is close to the inner side of the first skin unit 110a; the second rib 133 is close to the inner side of the second skin unit 110b, and the second groove 134 is close to the outer side of the second skin unit 110b. The first rib 131 is inserted into the second groove 134, and the second rib 133 is inserted into the first groove 132, thereby splicing the first skin unit 110a and the second skin unit 110b.
[0037] Advantageously, the sidewall of the first groove 132 close to the inner side of the first skin unit 110a protrudes toward the inner side of the first skin unit 110a, and the second ridge 133 also protrudes toward the inner side of the second skin unit 110b. Figure 4 As shown, when the second ridge 133 is inserted into the first groove 132, ribs can be formed along the axial direction of the skin 100, thereby improving the strength of the skin module 121 and the skin 100, making it have better mechanical properties, and the ribs on the inner side of the skin unit 110 will not increase the air resistance encountered by the skin 100 during flight.
[0038] Refer to the attached Figure 3 and attached Figure 4Advantageously, the side surfaces of the first and second ribs 131, 133 are respectively provided with first and second mounting holes 135, 136 along the length of the first and second ribs 131, 133. Rods 137 can be inserted into the first and second mounting holes 135, 136 to further strengthen the strength of the splicing structure and the ribs, while also preventing the splicing structure and the skin unit from cracking when subjected to external forces. Advantageously, rods 137 can be assembled with the first and second mounting holes 135, 136 by interference fit, or bonded to the first and second mounting holes 135, 136 via an adhesive, thereby further strengthening the connection between rods 137 and the first and second mounting holes 135, 136. Furthermore, rods 137 can extend beyond / expose the first and second mounting holes 135, 136 to facilitate connection to other skin modules or other skins, such as connecting the nose skin 100 to the fuselage skin. The rod 137 can be a metal rod, such as an aluminum rod or a titanium alloy rod, or a carbon fiber rod, and is preferably a carbon fiber rod, so as to reduce the weight of the skin 100 while meeting the mechanical strength requirements. It should be understood that the rod 137 can be either solid or hollow.
[0039] Refer to the attached Figure 5 , Attachment Figure 6 and attached Figure 7 The splicing structure may also include a second splicing structure 140. The second skin module 122 is formed by splicing the skin units 110 together through the second splicing structure 140. The second splicing structure 140 includes a third ridge 141 provided on the third skin unit 110c and a third groove 142 provided on the fourth skin unit 110d. The third ridge 141 and the third groove 142 are respectively provided on the thickness planes of the third skin unit 110c and the fourth skin unit 110d, that is, on the planes along the thickness direction of the skin units. The third ridge 141 is inserted into the third groove 142, thereby splicing the third skin unit 110c and the fourth skin unit 110d.
[0040] Refer to the attached Figure 8 and attached Figure 9 The splicing structure may further include a third splicing structure 150. The first skin module 121 and the second skin module 122 are spliced together by the third splicing structure 150. The third splicing structure 150 includes a fourth groove 151 provided on the first skin module 121 and a fourth ridge 152 provided on the second skin module 122. The fourth ridge 152 is inserted into the fourth groove 151 to splice the first skin module 121 and the second skin module 122. Advantageously, the bottom of the fourth groove 151 and the fourth ridge 152 both protrude toward the inner side of the skin module, as shown in the attached figure. Figure 9 As shown, when the fourth rib 152 is inserted into the fourth groove 151 , ribs along the circumference of the skin 100 can be formed, thereby increasing the connection strength between the skin modules.
[0041] Refer to the attached Figure 10 The second skin module 122 may be provided with a third mounting hole (not shown), and the rod inserted into and passing through the first mounting hole 137 may be inserted into the third mounting hole, so that the first skin module 121 and the second skin module 122 can be further connected by the rod.
[0042] Refer to the attached Figure 11 Advantageously, at least one rib 111 may also be disposed on the inner side of the skin unit 110. The rib 111 may be disposed along the circumference of the skin 100 or along the axial direction of the skin 100. When there are multiple ribs 111, i.e., two or more, the multiple ribs 111 may be disposed crosswise. It should be understood that the ribs 111 disposed on the inner side of the skin unit 100 are inherent to the skin unit 110, and are not formed by splicing two skin units 110 together.
[0043] It is easy for those skilled in the art to understand that, in the process of splicing the skin, a specific splicing structure can be selected according to the shape of each part of the skin. For example, in the skin 100 at the nose part, the axial curvature of the first skin module 121 is relatively small, so that it can be inserted with rods to increase the strength, and thus it can be spliced using the first splicing structure; the axial curvature of the second skin module 122 is relatively large, making it difficult to insert rods to provide strength, and thus it can be spliced using the second splicing structure. For another example, for the fuselage modules of some aircraft, the axial curvature changes little, and thus its skin modules can all be spliced using the second splicing structure.
[0044] Advantageously, an adhesive can be applied between the mating surfaces of the splicing structure, such as the mating surfaces between the first ridge 131 and the second groove 134, and between the mating surfaces between the second ridge 133 and the first groove 132, to further strengthen the splicing strength between the skin units. The adhesive in this application can be epoxy resin, 502 glue, or other types of adhesives, and this application does not limit this.
[0045] Refer to the attached Figure 12 The skin unit according to the principles of the present application may have an internal hollow array, comprising a plurality of closed hollows 200. The hollows may be of any shape, preferably a cubic shape. This hollow array ensures that the skin unit has sufficient mechanical properties while reducing the overall weight of the skin, thereby increasing the aircraft's cruising range. The skin unit can be manufactured using, for example, 3D printing.
[0046] Advantageously, the outer surface of the skin 100 may be coated with fiberglass cloth to make the outer surface of the skin 100 smoother and have good heat and corrosion resistance. The outer surface of the skin 100 may also be polished or painted to make the outer surface of the skin 100 smoother and more delicate, thereby having good surface quality.
[0047] It is easy for those skilled in the art to understand that although the present invention is described using the nose skin 100 of an aircraft as an example, the skin according to the principles of the present application can be any one or more of the fuselage skin, wing skin, tail skin, landing gear skin, or the skin of various parts of other aircraft such as rockets, flying cars, etc.
[0048] The present application also provides an aircraft including a skin according to the principles of the present application. The aircraft according to the principles of the present application can be a manned aircraft, such as a manned airplane, or an unmanned aircraft, such as an unmanned aircraft, also known as a drone, a rocket, etc.
[0049] The aircraft component skins based on the principles of this application do not have surface protrusions and can have a hollow structure, effectively reducing air resistance during flight, reducing the skin weight, and increasing the aircraft's cruising range. Furthermore, this skin assembly is simple, simplifying the aircraft's manufacturing process and improving production efficiency.
[0050] Although at least one exemplary embodiment has been described in the foregoing detailed description, it should be understood that there are a large number of variations. It should also be understood that the exemplary embodiment or embodiments described herein are merely examples and are not intended to limit the scope, applicability, or configuration of the present application in any way. On the contrary, the foregoing detailed description will provide a convenient guide for those skilled in the art to implement an exemplary embodiment or embodiments. It should be understood that various changes, modifications, or alterations may be made to the functions and arrangements of the elements without departing from the scope of the present application as set forth in the appended claims and their equivalents.
Claims
1. A skin of an aircraft component, characterized in that: The skin includes a plurality of skin units, wherein the edges of the skin units are provided with splicing structures extending along the edges, and wherein the skin units are spliced together through the splicing structures along the circumference of the component to form skin modules, and the skin modules are spliced together through the splicing structures along the axial direction of the component to form the skin.
2. The skin according to claim 1, characterized in that The splicing structure includes a first splicing structure, and at least one of the skin modules is spliced by the skin units through the first splicing structure, wherein the first splicing structure includes a first rib, a first groove, a second rib and a second groove, wherein the first rib and the first groove are located in the same skin unit, and the second rib and the second groove are located in another same skin unit, and wherein the first rib is close to the outer side of the skin unit where it is located, the first groove is close to the inner side of the skin unit where it is located, the second rib is close to the inner side of the skin unit where it is located, and the second groove is close to the outer side of the skin unit where it is located, and wherein the first rib is inserted into the second groove, and the second rib is inserted into the first groove.
3. The skin according to claim 2, characterized in that The splicing structure also includes a second splicing structure, and at least one of the skin modules is spliced by the skin units through the second splicing structure, wherein the second splicing structure includes a third ridge and a third groove respectively arranged on the thickness plane of each two mutually spliced skin units, and the third ridge is inserted into the third groove.
4. The skin according to claim 3, characterized in that The splicing structure also includes a third splicing structure, and the skin modules are spliced together through the third splicing structure, wherein the third splicing structure includes a fourth ridge and a fourth groove arranged on every two mutually spliced skin modules, the bottoms of the fourth ridge and the fourth groove both protrude toward the inner side of the skin module, and the fourth ridge is inserted into the fourth groove.
5. The skin according to claim 4, characterized in that The side wall of the first groove close to the inner side of the skin unit and the second ridge both protrude toward the inner side of the skin unit where they are located.
6. The skin according to claim 5, characterized in that The side surfaces of the first convex rib and the second convex rib are respectively provided with a first mounting hole and a second mounting hole along the length direction of the first convex rib and the second convex rib, wherein the rod can be inserted into the first mounting hole and the second mounting hole.
7. The skin according to claim 6, characterized in that At least one of the skin modules is provided with a third mounting hole, and the rod inserted through the first mounting hole can be inserted into the third mounting hole.
8. The skin according to claim 7, characterized in that The rod is a carbon fiber rod, an aluminum rod or a titanium alloy rod.
9. The skin according to claim 8, characterized in that Adhesive is coated between the bonding surfaces of the splicing structure.
10. The skin according to claim 9, characterized in that The skin unit has a hollow array inside.
11. The skin according to claim 10, characterized in that Ribs are arranged on the inner side of the skin unit.
12. The skin according to claim 11, characterized in that The outer surface of the skin is covered with glass fiber cloth.
13. The skin according to claim 12, characterized in that The skin is at least one of a nose skin, a fuselage skin, a tail skin, a wing skin, and a landing gear skin.
14. An aircraft, characterized in that: The aircraft comprises a skin as claimed in any one of claims 1-13.