CN222408558U - Skin of aircraft part and aircraft comprising skin - Google Patents

Abstract

The present application relates to aircraft skins. The application discloses a skin of an aircraft component, which comprises a plurality of skin units, wherein the edges of the skin units are provided with splicing structures extending along the edges, and the skin units are mutually spliced to form skin modules through the splicing structures along the circumferential direction of the component, and the skin modules are mutually spliced to form the skin through the splicing structures along the axial direction of the component. The application also discloses an aircraft comprising the skin.

Description

Skin of aircraft part and aircraft comprising skin

Technical Field

The application belongs to the field of aircrafts, and particularly relates to a skin of an aircraft component.

Background

The background description provided herein is for the purpose of generally presenting the context of the disclosure.

The skin of an aircraft refers to an outer shell covering the surface of an aircraft structure, and is the main stressed structure of the aircraft, which bears air resistance in the flight process. The skin is typically designed to be streamlined to reduce air drag experienced during flight, reduce energy consumption and thereby increase range. In the prior art, the aircraft generally uses metal materials to manufacture the skin, and uses fixing modes such as riveting and welding in the process of manufacturing the skin and fixing the skin on the frame of the aircraft, but the fixing modes usually form bulges on the surface of the skin, so that the air resistance of the aircraft in the flight process is increased, and meanwhile, the process of manufacturing the skin by using the modes such as welding and riveting is complex, and the manufacturing cost is increased. In addition, the skin made of the metal material can increase the load of the aircraft, so that the flight energy consumption is increased, and the range of the aircraft is reduced.

It is therefore desirable to provide a new aircraft skin.

Disclosure of utility model

This section presents in simplified form the concepts of the application, which are further described 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.

According to a first aspect of the application, there is provided a skin for an aircraft component, the skin comprising a plurality of skin elements, wherein edges of the skin elements are provided with a splice structure extending along the edges, and wherein the skin elements are spliced to each other along a circumferential direction of the component by the splice structure to form a skin module, the skin modules being spliced to each other along an axial direction of the component by the splice structure to form the skin.

Preferably, the splice structure comprises a first splice structure, and at least one skin module is spliced by skin units through the first splice structure, wherein the first splice structure comprises 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, 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 the first rib is located, the first groove is close to the inner side of the skin unit where the first groove is located, the second rib is close to the inner side of the skin unit where the second rib is located, the second groove is close to the outer side of the skin unit where the second rib is located, and the first rib is inserted into the second groove and the second rib is inserted into the first groove.

Preferably, the splicing structure further comprises a second splicing structure, and the at least one skin module is formed by splicing skin units through the second splicing structure, wherein the second splicing structure comprises a third rib and a third groove which are respectively arranged on thickness planes of every two skin units spliced with each other, and the third rib is inserted into the third groove.

Preferably, the splicing structure further comprises a third splicing structure, and the skin modules are spliced with each other through the third splicing structure, wherein the third splicing structure comprises a fourth rib and a fourth groove which are arranged on every two skin modules spliced with each other, bottoms of the fourth rib and the fourth groove are protruded towards the inner side of the skin module, and the fourth rib is inserted into the fourth groove.

Preferably, the side wall of the first groove near the inner side of the skin unit and the second convex rib are protruded towards the inner side of the skin unit where each is located.

Preferably, the side surfaces of the first rib and the second rib are provided with a first mounting hole and a second mounting hole along the length direction of the first rib and the second rib, respectively, wherein the rod can be inserted into the first mounting hole and the second mounting hole.

Preferably, at least one skin module is provided with a third mounting hole into which a rod inserted through the first mounting hole can be inserted.

Preferably, the rod member is a carbon fiber rod, an aluminum rod or a titanium alloy rod.

Preferably, an adhesive is coated between the bonding surfaces of the splice structure.

Preferably, the interior of the skin unit has a hollowed-out array.

Preferably, the skin unit is provided with ribs on the inside.

Preferably, the outer surface of the skin is coated with a fiberglass cloth.

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.

In another aspect of the application, there is also provided an aircraft comprising a skin according to the principles of the present application.

Drawings

Other or additional features, advantages and details are presented in the following detailed description of the embodiments by way of example only. In the drawings:

FIG. 1 schematically illustrates an nose skin according to principles of the present application;

Figure 2 schematically illustrates a first skin module of an nose skin according to principles of the present application;

figures 3, 4 schematically illustrate a first splice structure according to principles of the present application;

Figure 5 schematically illustrates a cross-sectional view of a second skin module according to principles of the present application;

FIGS. 6 and 7 schematically illustrate a second splice structure according to principles of the present application;

Fig. 8, 9 schematically illustrate a third splice structure according to principles of the present application;

FIG. 10 schematically illustrates an inboard construction of an nose skin according to principles of the present application;

Figure 11 schematically illustrates ribs of a skin unit according to principles of the present application, and

Figure 12 schematically illustrates an internal hollowed-out array of skin units according to principles of the present application.

It should be understood that throughout the drawings, corresponding reference numerals indicate like or corresponding parts or features. It should also be understood that the drawings are not necessarily to scale and that they are merely schematic illustrations of exemplary embodiments of the application, and are not limiting of the application.

Detailed Description

Exemplary embodiments of the present application are described below with reference to the accompanying drawings. It should be appreciated that the following description is merely exemplary in nature and is not intended to limit the present application, application, or uses.

The application will now be further elucidated. In the following paragraphs, the different aspects of the application are defined in more detail. Each aspect so defined may be combined with any other aspect(s) unless clearly indicated to the contrary. In particular, any feature indicated as being preferred or advantageous may be combined with any other feature(s) indicated as being preferred or advantageous.

The application provides a new skin of an aircraft component, which is formed by mutually splicing skin units.

The principle of the application is explained below by taking the skin of the nose part of an aircraft as an example. Referring to fig. 1, a nose portion skin 100 is shown in accordance with 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, and edges of the skin units 110 are straight and are provided with a splicing structure extending along the edges, so that the skin units 110 can be spliced with each other. The plurality of skin units 110 are spliced with each other along the circumferential direction of the component to form a first skin module 121 and a second skin module 122, and the first skin module 121 and the second skin module 122 are spliced with each other along the axial direction of the component, that is, the length direction of the component to form the skin 100.

The number of skin modules may be determined according to the size of the component and the size of the skin unit 110, for example, for a smaller size component, only one skin module may be used as a complete skin. The skin unit 110 according to the principles of the present application may be triangular and quadrilateral, or generally triangular, quadrilateral.

Referring to fig. 2, 3 and 4, the spliced structure may include a first spliced structure 130, and the first skin module 121 is spliced by the skin unit 110 through the first spliced structure 130. The first splice structure 130 includes a first rib 131 and a first groove 132 provided in the first skin unit 110a, and a second rib 133 and a second groove 134 provided in the second skin unit 110 b. Wherein the first rib 131 is adjacent to the outer side of the first skin unit 110a, the first groove 132 is adjacent to the inner side of the first skin unit 110a, the second rib 133 is adjacent to the inner side of the second skin unit 110b, and the second groove 134 is adjacent to the outer side of the second skin unit 110 b. 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 110 b.

Advantageously, the side wall of the first groove 132 near the inside of the first skin unit 110a projects toward the inside of the first skin unit 110a, and the second rib 133 also projects toward the inside of the second skin unit 110 b. As shown in fig. 4, when the second rib 133 is inserted into the first groove 132, ribs along the axial direction of the skin 100 can be formed, so that the strength of the skin module 121 and the skin 100 is improved, the skin module 121 and the skin 100 have better mechanical properties, and the ribs on the inner side of the skin unit 110 do not increase the air resistance encountered by the skin 100 during the flight.

Referring to fig. 3 and 4, advantageously, the side surfaces of the first and second ribs 131 and 133 are provided with first and second mounting holes 135 and 136, respectively, along the length directions of the first and second ribs 131 and 133, and the rod 137 may be inserted into the first and second mounting holes 135 and 136 so as to further strengthen the strength of the splice structure and the rib, while preventing the splice structure and the skin unit from being cracked when external force is applied thereto. Advantageously, the rod 137 may be interference fit with the first and second mounting holes 135 and 136 or adhered to the first and second mounting holes 135 and 136 by an adhesive, thereby making the connection of the rod 137 with the first and second mounting holes 135 and 136 more firm. In addition, the bar 137 may extend/expose the first and second mounting holes 135 and 136 for connecting other skin modules or other skins, such as connecting the nose skin 100 and the fuselage skin. The bar 137 may be a metal bar, such as an aluminum bar or a titanium alloy bar, or a carbon fiber bar, and preferably a carbon fiber bar, in order to reduce the weight of the skin 100 while satisfying mechanical strength. It should be appreciated that the bar 137 may be either solid or hollow.

Referring to fig. 5, 6 and 7, the splice structure may further include a second splice structure 140. The second skin module 122 is formed by splicing the skin units 110 through the second splicing structure 140. The second splice structure 140 includes a third rib 141 provided at the third skin unit 110c and a third groove 142 provided at the fourth skin unit 110d, and the third rib 141 and the third groove 142 are provided on the thickness planes of the third skin unit 110c and the fourth skin unit 110d, respectively, that is, on the plane of the skin units in the thickness direction. The third rib 141 is inserted into the third groove 142, thereby splicing the third skin unit 110c and the fourth skin unit 110 d.

Referring to fig. 8 and 9, the splice structure may further include a third splice structure 150. The first skin module 121 and the second skin module 122 are spliced to each other by the third splicing structure 150. The third splicing structure 150 includes a fourth groove 151 provided at the first skin module 121 and a fourth rib 152 provided at the second skin module 122, the fourth rib 152 being inserted into the fourth groove 151 to splice the first skin module 121 and the second skin module 122. Advantageously, both the bottom of the fourth groove 151 and the fourth rib 152 protrude toward the inside of the skin module, as shown in fig. 9, when the fourth rib 152 is inserted into the fourth groove 151, ribs along the circumferential direction of the skin 100 can be formed, thereby reinforcing the connection strength between the skin modules.

Referring to fig. 10, second skin module 122 may be provided with a third mounting hole (not shown), and a rod inserted through first mounting hole 137 may be inserted into the third mounting hole, thereby enabling first skin module 121 and second skin module 122 to be further connected through the rod.

Referring to fig. 11, at least one rib 111 may also be advantageously provided on the inside of the skin unit 110. The ribs 111 may be provided along the circumferential direction of the skin 100 or may be provided along the axial direction of the skin 100. When the number of the ribs 111 is plural, that is, more than two, the ribs 111 may be disposed to intersect each other. It should be understood that the ribs 111 provided inside the skin units 100 are ribs inherent to the skin units 110, and are not formed by the two skin units 110 being spliced to each other.

Those skilled in the art will readily appreciate that in the process of splicing skins, the particular splice structure may be selected according to the shape of each portion of the skin. For example, in the skin 100 at the nose portion, the axial curvature of the first skin module 121 is small so that it can be inserted with a rod to improve the strength, and thus the skin may be spliced by a first splicing structure, and the axial curvature of the second skin module 122 is large so that it is difficult to be inserted with a rod to provide the strength, and thus the skin may be spliced by a second splicing structure. For another example, for some aircraft fuselage modules, the axial curvature of the fuselage modules may vary less, and thus the skin modules may all be spliced using a second splice structure.

Advantageously, an adhesive may be applied between the bonding surfaces of the splice structure, for example, between the bonding surfaces of the first rib 131 and the second groove 134, and between the bonding surfaces of the second rib 133 and the first groove 132, to further enhance the splice strength between the skin units. The adhesive of the present application may be an epoxy or 502 glue, as well as other types of adhesives, to which the present application is not limited.

Referring to fig. 12, a skin unit according to the principles of the present application may have a hollowed-out array inside, which includes a plurality of closed hollowed-out portions 200, which may be any shape, preferably a cube shape. The hollowed-out array enables the skin units to have enough mechanical properties, and the overall weight of the skin can be reduced, so that the cruising mileage of the aircraft is increased. The skin units may be manufactured using, for example, 3D printing.

Advantageously, the outer surface of the skin 100 may also be coated with fiberglass cloth, so that the outer surface of the skin 100 is smoother and has good heat and corrosion resistance. The outer surface of the skin 100 may also be polished and painted to make the outer surface of the skin 100 smoother and finer, thereby having good surface quality.

Those skilled in the art will readily appreciate that while the present utility model has been described with respect to an aircraft nose skin 100, the skin in accordance with the principles of the present utility model may be any one or more of a fuselage skin, a wing skin, a tail skin, a landing gear skin, or the skin of various portions of other aircraft such as rockets, aircraft automobiles, and the like.

The present application also provides an aircraft comprising a skin according to the principles of the present application. The aircraft according to the principles of the present application may be either a manned aircraft, such as a manned aircraft, or an unmanned aircraft, such as an unmanned aircraft, i.e., an unmanned aircraft, rocket, or the like.

The component skin of the aircraft according to the principle of the application does not form bulges on the surface and can have a hollowed-out structure, so that the air resistance in the flight process can be effectively reduced, the skin weight is reduced, and the cruising mileage of the aircraft is improved. The skin is simple to assemble, so that the processing process of the aircraft is simplified, and the production efficiency is improved.

While at least one exemplary embodiment has been presented in the foregoing detailed description, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments described herein are only examples, and are not intended to limit the scope, applicability, or configuration of the application in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing the exemplary embodiment or exemplary embodiments. It should be understood that various changes, modifications, or alterations can be made in the function and arrangement of elements without departing from the scope of the application as set forth in the appended claims and the equivalents thereof.

Claims (14)

1. A skin of an aircraft component, characterized in that the skin comprises a plurality of skin units, wherein edges of the skin units are provided with a splice structure extending along the edges, and wherein the skin units are spliced to each other along a circumferential direction of the component by the splice structure to form skin modules, which are spliced to each other along an axial direction of the component by the splice structure to form the skin.

2. The skin of claim 1, wherein the splice structure comprises a first splice structure and at least one of the skin modules is spliced by the skin units by the first splice structure, wherein the first splice structure comprises 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 located adjacent to the outside of the skin unit where it is located, the first groove is located adjacent to the inside of the skin unit where it is located, the second rib is located adjacent to the inside of the skin unit where it is located, the second groove is located adjacent 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.

3. The skin according to claim 2, wherein the splice structure further comprises a second splice structure, and at least one of the skin modules is spliced by the skin units through the second splice structure, wherein the second splice structure comprises a third rib and a third groove respectively provided in a thickness plane of each two mutually spliced skin units, the third rib being inserted into the third groove.

4. The skin of claim 3, wherein the splice structure further comprises a third splice structure, and the skin modules are spliced to each other by the third splice structure, wherein the third splice structure comprises a fourth rib and a fourth groove provided at every two mutually spliced skin modules, the bottoms of the fourth rib and the fourth groove each protrude inward of the skin modules, and the fourth rib is inserted into the fourth groove.

5. The skin of claim 4, wherein the side wall of the first groove adjacent to the inner side of the skin unit and the second rib each protrude toward the inner side of the skin unit where each is located.

6. The skin of claim 5, wherein the sides of the first and second ribs are provided with first and second mounting holes along the length of the first and second ribs, respectively, wherein the bar is insertable into the first and second mounting holes.

7. The skin of claim 6, wherein at least one of the skin modules is provided with a third mounting hole into which a rod inserted through the first mounting hole can be inserted.

8. The skin of claim 7, wherein the rods are carbon fiber rods, aluminum rods, or titanium alloy rods.

9. The skin of claim 8, wherein the bonding surfaces of the splice are coated with an adhesive.

10. The skin of claim 9, wherein the interior of the skin unit has an array of hollows.

11. The skin of claim 10, wherein the skin unit is internally provided with ribs.

12. The skin of claim 11, wherein an outer surface of the skin is coated with fiberglass cloth.

13. The skin of claim 12, wherein 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 it comprises a skin according to any one of claims 1-13.