Wing for aircraft and aircraft comprising same

Abstract

The utility model relates to a wing for an aircraft and the aircraft comprising the wing. The utility model provides a wing for an aircraft, the wing comprises a wing main body and a force bearing beam, and the force bearing beam is arranged on the surface of the wing main body along the length direction of the wing main body. The utility model further provides an aircraft comprising the wing.

Description

Technical Field

[0001] The present application belongs to the field of aircraft, and in particular, relates to a wing for an aircraft and an aircraft comprising the wing. Background Art

[0002] The background description provided here is used to generally introduce the background of this application. The work of the inventors currently named in this background section to the extent described, and the aspects of this description that do not constitute prior art at the time of application, are neither explicitly nor implicitly admitted to be prior art that conflicts with this application.

[0003] When an aircraft, such as a fixed-wing aircraft, is in flight, a pressure difference is generated between the upper and lower surfaces of the wing, causing the wing to be lifted upward, thereby balancing the gravity of the aircraft itself and ensuring that the aircraft remains in the air. When the wing is subjected to upward pressure, the wing will bend upward. At this time, the material on the lower surface of the wing will be stretched, and the material on the upper surface of the wing will be compressed. Therefore, the wing must have sufficient strength, so that the material on the upper surface of the wing must have good compressive resistance, and the material on the lower surface of the wing must have good tensile resistance.

[0004] In order to ensure the strength of the wing, composite materials such as aluminum alloy and titanium alloy are usually used to manufacture the wing. However, the density of these materials is usually high, which increases the weight of the aircraft and further increases energy consumption. However, if a material with a lower density is used to make the main load-bearing structure of the wing, it is difficult to ensure the required strength of the wing.

[0005] Moreover, in the prior art, the wing is usually only provided with a main beam at the center of the wing to enhance the strength of the wing, which makes the main beam insufficient to enhance the strength of the wing surface that is subjected to the greatest force. In addition, the structural beams used in the prior art usually need to be hot-pressed by a mold or processed by a CNC machine tool and then pressed again in a mold, and the processing process is highly dependent on manual experience, resulting in low production efficiency and poor molding consistency. In addition, the high price of these materials leads to high production costs for aircraft.

[0006] Therefore, a new wing is needed to solve the above problems. Utility Model Content

[0007] This section introduces a selection of innovative concepts in a simplified form that 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.

[0008] In view of the problems existing in the prior art, in one aspect of the present application, a wing for an aircraft is provided, wherein the wing comprises a wing body and a load-bearing beam, wherein the load-bearing beam is arranged on the surface of the wing body along the length direction of the wing body.

[0009] Preferably, the load-bearing beam is arranged at the upper surface of the wing body and is made of a compression-resistant material.

[0010] Preferably, the load-bearing beam is arranged at the lower surface of the wing body and is made of a tensile material.

[0011] Preferably, a first mounting hole is provided at the root of the wing body, a second mounting hole is provided at the end of the wing body, and both ends of the load-bearing beam are respectively inserted into the first mounting hole and the second mounting hole.

[0012] Preferably, the wing also includes a first insert arranged at the root, wherein the first insert includes a mounting panel and a first insert body arranged on one side of the mounting panel, a third mounting hole corresponding to the first mounting hole is arranged on the mounting panel, and the third mounting hole extends to the first insert body to form a first mounting groove.

[0013] Preferably, a recess is provided at the root, and one end of the first mounting hole is located in the recess, wherein after the first insert body is inserted into the recess, the load-bearing beam can pass through the first mounting hole and then extend in the first mounting groove and be inserted into the third mounting hole.

[0014] Preferably, a plurality of guide grooves are provided on the first insert body, wherein at least one guide groove is communicated with the first mounting groove.

[0015] Preferably, the guide grooves are interconnected.

[0016] Preferably, the first insert body is arc-shaped.

[0017] Preferably, the first insert is bonded to the recess by glue.

[0018] Preferably, the load-bearing beam is bonded to the first mounting groove, the third mounting hole and the second mounting hole by glue.

[0019] Preferably, the wing further comprises a second insert, the second insert is arranged in the wing body, and the second insert is provided with a main beam mounting hole for mounting the main beam.

[0020] Preferably, the load-bearing beam is arranged below the surface of the wing body.

[0021] Preferably, a fixing groove is provided on the second insert, and the load-bearing beam passes through the fixing groove.

[0022] Preferably, the main body of the load-bearing beam is arranged on the surface of the wing body, the other end of the first mounting hole is arranged on the surface of the wing body near the root, one end of the load-bearing beam near the root passes through the first mounting hole through the other end of the first mounting hole, and one end of the second mounting hole is arranged on the surface of the wing body near the end, and one end of the load-bearing beam near the end is inserted into the second mounting hole through one end of the second mounting hole.

[0023] Preferably, the main body of the load-bearing beam is bonded to the surface of the wing body.

[0024] Preferably, a torsion beam is arranged inside the wing body, and the torsion beam is arranged at an angle with the load-bearing beam.

[0025] Preferably, the second insert is provided with a fourth mounting hole, and the torsion beam passes through the fourth mounting hole.

[0026] Preferably, the tensile material is carbon fiber, and the compressive material is aluminum alloy.

[0027] In another aspect of the present application, an aircraft is provided, comprising the wing according to the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] 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:

[0029] Figure 1 Schematically showing a partial view of a wing according to the principles of the present application;

[0030] Figure 2 Schematically showing a partial cross-sectional view of a wing according to the principles of the present application;

[0031] Figure 3 Schematically shows a partial view of a wing from another perspective according to the principles of the present application;

[0032] Figure 4 A first insert according to the principles of the present application is schematically shown;

[0033] Figure 5 The root end surface of a wing body according to the principles of the present application is schematically shown;

[0034] Figure 6 Schematically shows a partial view of the interior of a wing according to the principles of the present application;

[0035] Figure 7 A second insert according to the principles of the present application is schematically shown. DETAILED DESCRIPTION

[0036] The following description is merely exemplary in nature and is not intended to limit the present application, application or use. Furthermore, there is no intention to be limited by any express or implied theory presented in the preceding technical field, background technology and utility model content or the following detailed description. It should be understood that throughout the drawings, corresponding reference numerals identify similar or corresponding parts or features.

[0037] The present application will now be further elaborated. In the following paragraphs, different aspects of the present application are defined in more detail. Unless clearly indicated to the contrary, each aspect so defined can be combined with any other (multiple) aspects. Especially, any feature indicated as preferred or advantageous can be combined with any other (multiple) features indicated as preferred or advantageous.

[0038] In order to solve the problems in the prior art, the present application provides a wing for an aircraft. Figure 1 The wing 10 includes a wing body 100 and a bearing beam 130, wherein the wing body 100 includes a root 110 connected to the fuselage and an end 120 away from the fuselage, and the wing body portion between the root 110 and the end 120 can be a hollow structure, or a pore structure, a hollow structure or a solid structure. The bearing beam 130 is arranged on the surface of the wing body 100 along the length direction of the wing body 100, thereby increasing the strength of the surface of the wing body 100. It is easy for those skilled in the art to understand that the surface of the wing body 100 can be either on the surface or below the surface.

[0039] Advantageously, the bearing beam 130 is respectively arranged at the upper surface and the lower surface of the wing body 100, wherein the bearing beam 130 located at the upper surface is made of a compression-resistant material, and the bearing beam 130 located at the lower surface is made of a tensile material, thereby respectively enhancing the compression resistance of the upper surface and the tensile resistance of the lower surface of the wing body 100, which enables the use of materials with lower density, such as foam materials or hollow materials, to reduce the weight of the wing in the process of manufacturing the wing 10, while ensuring that the wing has sufficient strength. The compression-resistant material used to make the bearing beam 130 can be a high-strength metal such as an aluminum alloy or a titanium alloy, and the tensile material used to make the bearing beam 130 can be a high-strength fiber such as carbon fiber, aramid fiber or glass fiber. It is easy for those skilled in the art to understand that, according to performance requirements, the bearing beam can be set only at the upper surface of the wing or only at the lower surface of the wing, and the bearing beam set at the upper surface and the bearing beam set at the lower surface can have different shapes and cross-sections, and the number of the bearing beams can also be different according to the size and performance requirements of the wing.

[0040] It is easy for a person skilled in the art to understand that when a wing bends due to stress, it can be considered that the central layer of the wing is not stretched or compressed, while the upper and lower parts of the central layer of the wing are compressed and stretched respectively, wherein the position farther from the central layer is most obviously compressed or stretched, that is, the upper and lower surfaces of the wing are most severely compressed and stretched respectively. Based on this principle, the present application adds load-bearing beams as reinforcements at these locations to improve the compression and / or tensile properties of the wing, thereby improving the overall structural strength of the wing.

[0041] As is easy to understand, the moment of inertia of the section is an important parameter to measure the bending resistance of the section. The larger the moment of inertia, the better the bending resistance of the section. Figure 2 In the coordinate system YOZ established with the centroid O of the wing body 100 as the origin, assuming that when the load-bearing beam 130 is located at the centroid of the wing body 10, the moment of inertia of the single load-bearing beam 130 about the Z axis is:

[0042] Iz 1 =bh3 / 12.

[0043] Wherein, b is the width of the load-bearing beam 130 , and h is the height of the load-bearing beam 130 .

[0044] When the load-bearing beam 130 is located at Figure 2 When the wing main body surface is shown, the moment of inertia of the load-bearing beam 130 about the Z axis is: Iz 2 =Iz 1 +Aa 2 ,

[0045] Wherein A is the cross-sectional area of ​​the load-bearing beam 130 , and a is the distance from the centroid of the load-bearing beam 130 to the Z axis.

[0046] Since the cross-sectional area of ​​the load-bearing beam A = bh, Iz 1 It can be simplified to Ah2 / 12, Iz 2 It can be simplified to A(h2 / 12+a 2 ). It can be seen from this that when the load-bearing beam 130 is located on the surface of the wing body 100, the moment of inertia it provides is greater than when it is located at the centroid, so that the bending resistance of the wing body is stronger than when the load-bearing beam 130 is placed at the centroid of the wing body. At the same time, this also makes it possible to provide a greater moment of inertia than when the load-bearing beam 130 is located at the centroid of the wing body 100, even if the cross-sectional area of ​​the load-bearing beam 130 located on the surface of the wing body 100 is smaller than that located at the centroid of the wing body 100, thereby improving the bending resistance while also reducing the amount of material used for the load-bearing beam and reducing costs.

[0047] See attached Figure 1Advantageously, a first mounting hole 111 is provided at the root 110 of the wing body 100, and a second mounting hole 121 is provided at the end 120 of the wing body 100. The two ends of the load-bearing beam 130 are respectively inserted into the first mounting hole 111 and the second mounting hole 121, so that the load-bearing beam 130 can be arranged on the surface of the wing body 100. The first mounting hole 111 and the second mounting hole 121 can be through holes or blind holes. Advantageously, glue can be injected into the first mounting hole 111 and the second mounting hole 121 to bond the two ends of the load-bearing beam 130, so that the connection between the load-bearing beam 130 and the wing body 100 is more stable. Advantageously, the main body of the load-bearing beam 130 can be arranged on the surface of the wing body 100, and one end of the load-bearing beam 130 near the root 110 is inserted into the first mounting hole 111, and one end of the load-bearing beam 130 near the end 120 is inserted into the second mounting hole 121. In this embodiment, one end of the first mounting hole 111 and one end of the second mounting hole 121 are respectively located on the surface of the wing body 100 near the root and near the end, so that the two ends of the load-bearing beam 130 are inserted. Alternatively, the load-bearing beam 130 can also be arranged under the surface of the wing body 100, thereby making the surface of the wing body 100 flat and smooth, reducing wind resistance. In this embodiment, both ends of the first mounting hole 111 and the second mounting hole 121 are below the surface of the wing body 100, and the first mounting hole 111 and the second mounting hole 121 can be connected into one body.

[0048] See attached Figure 3 and attached Figure 4 The root of the wing body 100 may be provided with a first insert 140, the first insert 140 includes a mounting panel 141 and a first insert body 142 disposed on one side of the mounting panel 141, and the mounting panel 141 is provided with a third mounting hole 143 corresponding to the first mounting hole 111, that is, the first mounting hole 111 and the third mounting hole 143 can be aligned. The third mounting hole 143 extends to the first insert body 142 to form a first mounting groove 144. The first insert 140 may be connected to the wing body 100 by means of snap connection or bonding.

[0049] See attached Figure 4 and attached Figure 5The root 110 of the wing body 100 is provided with a recess 112, the shape of which can be adapted to the shape of the first insert body 142, and the first mounting hole 111 is provided in the recess 112, that is, one end of the first mounting hole 111 is located in the recess 112. The first insert body 142 is inserted into the recess 112, so that the mounting panel 142 can be flush with the end surface of the root 110 or cover the end surface of the root 110, and after the bearing beam 130 is inserted into the first mounting hole 111, it passes through the first mounting hole 111 and extends in the first mounting groove 144 and is inserted into the third mounting hole 143. Since one end of the bearing beam 130 is provided in the first insert 140, the stress that may be generated by the bearing beam 130 is effectively dispersed, and the damage that may be caused to the wing body 100 by the bearing beam 130 due to stress concentration is avoided. Advantageously, the first insert body 142 is arc-shaped, so that the stress of the load-bearing beam 130 can be more effectively dispersed, thereby preventing the load-bearing beam 130 from damaging the wing body 100 and the first insert 140 due to stress concentration.

[0050] See attached Figure 4 , a plurality of guide grooves 145 are provided on the first insert body 142, so that glue, such as quick-drying glue or slow-drying glue, can be injected into the guide grooves 145, so that the first insert 140 is bonded to the recess 112. Advantageously, at least one guide groove 145 is connected to the first mounting groove 144, so that the glue injected from the third mounting hole 143 flows into the guide groove 145 through the first mounting groove 144, which enables the first insert body 141 to be inserted into the recess 112, and the glue can be injected from the third mounting hole 143, so that the first insert body 141 is bonded to the recess 112, and the bearing beam 130 is bonded to the third mounting hole 143, the first mounting groove 144 and the first mounting hole 111, simplifying the assembly procedure of the wing. Advantageously, the guide grooves 145 can be connected to each other, so that the glue can flow into each guide groove, so that the distribution of the glue is more uniform. Advantageously, the first insert 140 may also be provided with a main shaft mounting hole 146 for mounting the main shaft; the first insert 140 may also be provided with a wire-through hole 147 for mounting the control circuit in the wing.

[0051] It is easy for those skilled in the art to understand that if the stress concentration of the load-bearing beam at the end 120 of the wing body 100 is large, the first insert 140 and the corresponding recess may be provided at the end 120; if the stress concentration at the end 120 is small, they may not be provided.

[0052] See attached Figure 6 and attached Figure 7, the wing body 100 may also be provided with a second insert 150, the second insert 150 is provided with a main beam mounting hole 151 for installing a main beam (not shown), so that the wing and the fuselage are connected through the main beam. A boss 152 may also be provided in the main beam mounting hole 151, and when the main beam is tubular, the main beam can be sleeved on the boss 152, so that the connection between the main beam and the wing is more stable. The second insert 150 may also be provided with a fixing groove 153, and when the bearing beam 120 is arranged under the surface of the wing body 100, the bearing beam 130 can pass through the fixing groove 153 against the second insert 150, so as to provide support for the bearing beam 130 and disperse the stress of the bearing beam 130. The inside of the wing body 100 may also be provided with a torsion beam 160, and the torsion beam 160 is arranged at an angle with the bearing beam 130, such as an acute angle or a right angle, so as to provide torsion resistance for the wing body 100 and prevent the wing from twisting. Under the premise of being arranged at an angle with the load-bearing beam 130, the two ends of the torsion beam 160 can be arranged at any position of the wing body 100. Advantageously, the second insert 150 is provided with a fourth mounting hole 154, and the torsion beam 160 passes through the fourth mounting hole 154, so that the second insert 150 can provide support and fixation for the torsion beam 160 and disperse stress. It is easy to understand for those skilled in the art that different numbers of torsion beams 160 and their corresponding fourth mounting holes 154 can be arranged according to performance requirements.

[0053] It is easy for those skilled in the art to understand that the load-bearing beam 130 according to the principle of the present application can be in the shape of strips, plates, tubes, prisms, etc., and existing commercially available products can be directly purchased according to the performance requirements of the wing, thereby simplifying the processing flow of the wing, improving the processing efficiency of the wing, and reducing production costs.

[0054] The present application also provides an aircraft, such as an unmanned aerial vehicle, which includes a wing based on the principles of the present application, thereby having the technical effects brought by the wing based on the principles of the present application.

[0055] Although at least one exemplary embodiment is described in the foregoing detailed description, it should be understood that there are a large number of variations. It should also be understood that an exemplary embodiment or multiple exemplary 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 convenient guidance for those skilled in the art to implement an exemplary embodiment or multiple exemplary embodiments. It should be understood that various changes, modifications or changes, etc. can be made to the functions and arrangements of elements without departing from the scope of the present application as set forth in the attached claims and their equivalents.

Claims

1. A wing for an aircraft, characterized in that: The wing includes a wing body and a load-bearing beam, wherein the load-bearing beam is arranged on the surface of the wing body along the length direction of the wing body, and a first mounting hole is arranged at the root of the wing body, and a second mounting hole is arranged at the end of the wing body, and both ends of the load-bearing beam are respectively inserted into the first mounting hole and the second mounting hole.

2. The wing according to claim 1, characterized in that The load-bearing beam is arranged on the upper surface of the wing body and is made of a pressure-resistant material.

3. The wing according to claim 1, characterized in that The load-bearing beam is arranged at the lower surface of the wing body and is made of a tensile material.

4. The wing according to claim 2, characterized in that The pressure-resistant material is aluminum alloy.

5. The wing according to claim 3, characterized in that The tensile material is carbon fiber.

6. The wing according to claim 4 or 5, characterized in that It also includes a first insert arranged at the root, wherein the first insert includes a mounting panel and a first insert body arranged on one side of the mounting panel, a third mounting hole corresponding to the first mounting hole is arranged on the mounting panel, and the third mounting hole extends to the first insert body to form a first mounting groove.

7. The wing according to claim 6, characterized in that A recess is provided at the root, and one end of the first mounting hole is located in the recess. After the first insert body is inserted into the recess, the load-bearing beam can pass through the first mounting hole and then extend in the first mounting groove and be inserted into the third mounting hole.

8. The wing according to claim 7, characterized in that A plurality of guide grooves are arranged on the first insert body, wherein at least one guide groove is communicated with the first mounting groove.

9. The wing according to claim 8, characterized in that The guide grooves are communicated with each other.

10. The wing according to claim 9, characterized in that The first insert body is arc-shaped.

11. The wing according to claim 10, characterized in that The first insert is bonded to the recess by glue.

12. The wing according to claim 11, characterized in that The load-bearing beam is bonded to the first mounting groove, the third mounting hole and the second mounting hole by glue.

13. The wing according to claim 12, characterized in that It also includes a second insert, which is arranged in the wing body and is provided with a main beam mounting hole for mounting the main beam.

14. The wing according to claim 13, characterized in that The load-bearing beam is arranged under the surface of the wing body.

15. The wing according to claim 14, characterized in that The second insert is provided with a fixing groove, and the load-bearing beam passes through the fixing groove.

16. The wing according to claim 15, characterized in that The main body of the load-bearing beam is arranged on the surface of the wing body, the other end of the first mounting hole is arranged on the surface of the wing body near the root, one end of the load-bearing beam near the root passes through the first mounting hole through the other end of the first mounting hole, and one end of the second mounting hole is arranged on the surface of the wing body near the end, and one end of the load-bearing beam near the end is inserted into the second mounting hole through one end of the second mounting hole.

17. The wing according to claim 16, characterized in that The main body of the load-bearing beam is bonded to the surface of the wing main body.

18. The wing according to any one of claims 13 to 17, characterized in that An anti-torsion beam is arranged inside the wing body, and the anti-torsion beam is arranged at an angle with the load-bearing beam.

19. The wing according to claim 18, characterized in that The second insert is provided with a fourth mounting hole, and the torsion beam passes through the fourth mounting hole.

20. An aircraft, characterized in that: The aircraft comprises a wing according to any one of claims 1-19.

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