Connecting structure of aileron and wing

Abstract

The utility model discloses a connecting structure of an aileron and a wing. The connecting structure comprises an outer aileron, a knuckle bearing, a detachable check block, a detachable rotating shaft, a hinge rotating shaft, a hinge fixing detachable support, an aileron driving pull rod, the wing, an inner aileron and a rotating shaft. The knuckle bearing is embedded into the outer end face of the inner aileron and the inner end face of the outer aileron; the detachable rotating shaft is mounted on the outer side of the outer aileron; the outer end of the outer aileron is close to the position area of the detachable rotating shaft; the hinge rotating shaft is mounted between the inner aileron and the outer aileron and is embedded into the wing end rib through the knuckle bearing; the wing end rib is embedded into the inner side close to the inner aileron; the hinge fixing detachable support is mounted on a wing rear beam; the aileron driving pull rod is mounted on the wing; the inner aileron and the outer aileron are positioned on the rear edge of the wing and close to the wing tip; and the rotating shaft is mounted on the inner side of the inner aileron. The aileron hinge is simple in structure, and the aileron hinge joint can be hidden to the maximum extent, so that the influence on the pneumatic surface of the aileron is reduced.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft assembly, and particularly relates to a connection structure between an aileron and a wing. Background Art

[0002] An aileron refers to a movable wing surface installed near the outer side of the trailing edge of a wing, which is the main control rudder surface of an aircraft. The rolling moment generated by differential deflection of the left and right ailerons can make the aircraft perform a rolling maneuver. The connection design between the aileron and the wing is a key issue in aileron design, mainly including the design of the aileron rotating shaft hinge and the design of the aileron drive mechanism. For the design of the aileron rotating shaft hinge, while ensuring reliable force transmission from the aileron to the wing, the assembly difficulty of the aileron should be reduced as much as possible, and at the same time, the impact on the integrity of the aileron aerodynamic surface should also be minimized.

[0003] Chinese Patent CN216332712U (published on April 19, 2022) discloses a wing structure, which includes a main wing having a wing box structure formed by a rib assembly, a spar assembly, and a skin; a flap hinged to the main wing, where the flap is a single-slotted flap; and an aileron hinged to the main wing. The wing structure provided by the embodiment of the present application replaces a simple flap with a single-slotted flap, optimizes the hinge rotating shaft position and the lowering angle, so that the flap obtains a larger lift coefficient and lift-to-drag ratio when lowered.

[0004] In the above-mentioned prior art, there are still problems such as complex assembly and the connection structure between the aileron and the wing affecting the integrity of the aileron aerodynamic surface. Therefore, it is necessary to propose a connection structure between the aileron and the wing, which can achieve a simple hinge structure for the aileron, light weight, and maximize the hiding of the aileron hinge joint, thereby reducing the impact on the aileron aerodynamic surface. Summary of the Utility Model

[0005] To solve the above problems, the purpose of the utility model is to design a connection structure between an aileron and a wing, which can achieve a simple hinge structure for the aileron, light weight, and maximize the hiding of the aileron hinge joint, thereby reducing the impact on the aileron aerodynamic surface.

[0006] To achieve the above purpose, the present application proposes a connection structure between an aileron and a wing, the structure includes an outer aileron, a spherical plain bearing, a removable stop block, a detachable rotating shaft, a hinge rotating shaft, a hinge fixed detachable support, an aileron drive rod, a wing, an inner aileron, a rotating shaft;

[0007] The spherical plain bearing is embedded on the outer end face of the inner aileron and the inner end face of the outer aileron;

[0008] The detachable rotating shaft is installed at the outer side position of the outer aileron;

[0009] The area near the detachable rotating shaft at the outer end of the outer aileron;

[0010] The hinge rotating shaft is installed at the middle position between the inner aileron and the outer aileron, and is embedded in the wing end rib through a spherical plain bearing;

[0011] The wing end rib is embedded closely inside the inner aileron;

[0012] The hinge fixed detachable support is installed on the rear wing beam;

[0013] The aileron drive link is installed on the wing;

[0014] The inner aileron and the outer aileron are located at the trailing edge of the wing near the wing tip;

[0015] The rotating shaft is installed inside the inner aileron.

[0016] Furthermore, at the wing tip position, a detachable winglet is arranged.

[0017] Furthermore, one end of the inner hinge of the inner aileron, the outer aileron and the wing is installed on the rotating shaft, and the other end is installed on the spherical plain bearing on the wing end rib.

[0018] Furthermore, the hinge between the inner aileron and the outer aileron passes through the L-shaped hinge fixed detachable support and the stepped rotating shaft clamped on the hinge fixed detachable support, one end is embedded in the outer end face of the inner aileron, and the other end is connected to the spherical plain bearing on the inner end face of the outer aileron.

[0019] Furthermore, the outer end hinge of the outer aileron passes through the detachable rotating shaft from the outside to the inside of the wing through the detachable stop block and the spherical plain bearing at the outer end of the outer aileron for connection.

[0020] Furthermore, a mounting notch for the outer aileron is designed at a local position of the wing end rib, and the mounting notch for the outer aileron is filled with a detachable stop block.

[0021] Furthermore, the outer aileron can rotate; the spherical plain bearing at the inner end of the outer aileron can be clamped into the hinge rotating shaft.

[0022] Furthermore, ball head bearings are connected to the upper and lower ends of the hinge rotating shaft.

[0023] Furthermore, the outer surfaces of the inner aileron and the outer aileron are covered with aileron panels;

[0024] Furthermore, the outer surface of the aileron panel is covered with carbon fiber composite material;

[0025] Furthermore, the aileron panel is filled with aileron foam sandwich;

[0026] Furthermore, aileron aluminum alloy skeletons are installed on the outer sides of the inner aileron and the outer aileron.

[0027] Compared with the prior art, the advantages and effects of the present application are as follows:

[0028] 1. By applying the condition that the winglet on the outer side of the aileron is detachable, through a special hinge rotating shaft structure and a specific installation sequence, the hinge structure of the aileron can be made simple and lightweight, and the aileron hinge joint can be maximally hidden, thereby reducing the impact on the aerodynamic surface of the aileron.

[0029] 2. The inner and outer ailerons of the present application are installed in a manner of approaching from the outside to the inside along the aileron rotating shaft. At the same time, by embedding the spherical plain bearing of the hinge rotating shaft in the wing trailing edge rib adjacent to the aileron notch, the wing trailing edge rib can be used to replace the hinge joint, maximally reducing the number of joints. Through structure sharing, the purpose of weight reduction, cost reduction of manufacturing, and reduction of assembly workload can be achieved.

[0030] 3. The present application designs an aileron installation avoidance notch on the wing outside the outer aileron, then fills the notch with a detachable block through the installation notch of the outer aileron, and installs the outer aileron by rotating it by an angle and putting it in, and realizes the installation of the detachable rotating shaft on the outside of the outer aileron, so as to achieve the purpose of installing the aileron approaching from the outside to the inside.

[0031] 4. The integrated processing design of the aileron skeleton adopted in the present application can effectively ensure the coaxiality of key bearings and reduce the assembly difficulty.

[0032] The above description is only an overview of the technical solution of the present application. In order to be able to understand the technical means of the present application more clearly, so that it can be implemented in accordance with the content of the description, and in order to make the above and other purposes, features and advantages of the present application more obvious and understandable, the following describes in detail with reference to the preferred embodiments of the present application and the accompanying drawings.

[0033] Those skilled in the art will understand more clearly the above and other purposes, advantages and features of the present application according to the following detailed description of the specific embodiments of the present application in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings. In all the drawings, similar elements or parts are generally denoted by similar reference numerals. In the drawings, the elements or parts are not necessarily drawn to actual scale.

[0035] Among them:

[0036] Figure 1 is an overall view of the aileron and the wing;

[0037] Figure 2 Explosion diagram of inner and outer ailerons and their connection to the wing;

[0038] Figure 3 Cross-sectional view of the aileron hinge;

[0039] Figure 4 Explosion diagram of the aileron structure.

[0040] Explanation of reference numerals in the drawings: 1 - outer aileron; 2 - spherical plain bearing; 3 - removable stop; 4 - removable rotating shaft; 5 - hinge rotating shaft; 6 - hinge fixed removable support; 7 - aileron drive tie rod; 8 - wing; 9 - inner aileron; 10 - rotating shaft; 11 - winglet; 12 - wing end rib; 13 - ball head bearing; 14 - aileron aluminum alloy skeleton; 15 - aileron panel; 16 - aileron foam sandwich. Specific embodiments

[0041] To make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are some, but not all, of the embodiments of the present application. In the following description, specific details such as specific configurations and components are provided only to assist in a comprehensive understanding of the embodiments of the present application. Therefore, those skilled in the art should understand that various changes and modifications can be made to the embodiments described herein without departing from the scope and spirit of the present application. In addition, descriptions of known functions and structures are omitted for clarity and conciseness in the embodiments.

[0042] It should be understood that the "one embodiment" or "this embodiment" mentioned throughout the specification means that specific features, structures or characteristics related to the embodiment are included in at least one embodiment of the present application. Therefore, the "one embodiment" or "this embodiment" that appears throughout the specification does not necessarily refer to the same embodiment. In addition, these specific features, structures or characteristics can be combined in one or more embodiments in any suitable manner.

[0043] In addition, the present application may repeat reference numerals and / or letters in different examples. This repetition is for the purpose of simplicity and clarity, and does not itself indicate the relationship between the various embodiments and / or arrangements discussed.

[0044] As used herein, the term "and / or" is merely a description of the relationship between associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, B exists alone, and both A and B exist simultaneously. The term " / and" as used herein describes another relationship between associated objects, indicating that there can be two relationships. For example, A / and B can represent: A exists alone, and both A and B exist. Additionally, in this text, the character " / " generally indicates that the associated objects before and after are in an "or" relationship.

[0045] As used herein, the term "at least one" is merely a description of the relationship between associated objects, indicating that there can be three relationships. For example, at least one of A and B can represent: A exists alone, both A and B exist simultaneously, and B exists alone.

[0046] It should also be noted that in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion.

[0047] Embodiment 1

[0048] This embodiment relates to a connection structure between an aileron and a wing. Please refer to Figure 1 As shown, the overall aileron and wing include an outer aileron 1, an inner aileron 9, a wing 8, and a winglet 11; the aileron is located near the wingtip position at the trailing edge of the wing 8. Considering redundancy, the aileron is divided into two parts: an inner aileron 9 and an outer aileron 1; the winglet 11 is arranged at the wingtip position, and the winglet 11 is detachable;

[0049] Please refer to Figure 2 As shown, the structure includes an outer aileron 1, a spherical plain bearing 2, a detachable stop 3, a detachable rotating shaft 4, a hinge rotating shaft 5, a hinge fixed detachable support 6, an aileron drive link 7, a wing 8, an inner aileron 9, and a rotating shaft 10;

[0050] The spherical plain bearing 2 is embedded in the outer end face of the inner aileron 9 and the inner end face of the outer aileron 1;

[0051] The detachable rotating shaft 4 is installed at the outer side position of the outer aileron;

[0052] The area near the outer end of the outer aileron 1 close to the detachable rotating shaft 4;

[0053] The hinge rotating shaft 5 is installed at the middle position between the inner aileron 9 and the outer aileron 1, and is embedded in the wing end rib 12 through the spherical plain bearing 2;

[0054] The wing tip rib 12 is embedded inside and adjacent to the inner aileron 9;

[0055] The hinge-fixed detachable support 6 is installed on the rear beam of the wing 8;

[0056] The aileron drive rod 7 is installed on the wing 8;

[0057] The inner aileron 9 and the outer aileron 1 are located at the trailing edge of the wing 8 near the wing tip;

[0058] The rotating shaft 10 is installed inside the inner aileron 9.

[0059] One end of the inner hinge of the inner aileron 9, the outer aileron 1 and the wing 8 is installed on the rotating shaft 10, and the other end is installed on the spherical plain bearing 2 on the wing tip rib 12.

[0060] The hinge between the inner aileron 9 and the outer aileron 1 passes through the L-shaped hinge-fixed detachable support 6 and the stepped rotating shaft clamped on the hinge-fixed detachable support 6. One end is embedded in the outer end face of the inner aileron 9, and the other end is connected to the spherical plain bearing 2 on the inner end face of the outer aileron 1.

[0061] The outer hinge of the outer aileron 1 passes through the detachable rotating shaft 4 from the outside to the inside of the wing 8 through the detachable block 3 and the spherical plain bearing 2 at the outer end of the outer aileron 1 for connection.

[0062] Please refer to Figure 3 As shown, a mounting notch for the outer aileron is designed at a local position of the wing tip rib 12, and the mounting notch for the outer aileron is filled with the detachable block 3.

[0063] The outer aileron 1 can rotate; the spherical plain bearing 2 at the inner end of the outer aileron 1 can be snapped into the hinge rotating shaft 5.

[0064] The upper and lower ends of the hinge rotating shaft 5 are connected to the ball head bearings 13.

[0065] Please refer to Figure 4 As shown, the outer surfaces of the inner aileron 9 and the outer aileron 1 are covered with the aileron panel 15;

[0066] The outer surface of the aileron panel 15 is covered with carbon fiber composite material;

[0067] The aileron panel 15 is filled with the aileron foam sandwich 16;

[0068] The inner aileron 9 and the outer aileron 1 are installed with the aileron aluminum alloy skeleton 14 on the outside.

[0069] Technical effects of this embodiment: In this application, the inner and outer ailerons are installed in a manner that they approach the inside from the outside along the aileron rotation axis. At the same time, the spherical plain bearing of the hinge rotation axis is embedded in the wing trailing edge rib adjacent to the aileron notch. In this way, the wing trailing edge rib can be used to replace the hinge joint, maximizing the reduction of the number of joints. Through the sharing of structures, weight reduction, cost reduction in manufacturing, and reduction of assembly workload can be achieved.

[0070] Embodiment 2

[0071] This embodiment relates to an installation method for the connection structure between the aileron and the wing. Based on Embodiment 1, it is further introduced. The installation method includes:

[0072] When installing the aileron, all spherical plain bearings 2 are installed separately. Then, the L-shaped fixed detachable support 6 for the middle hinge of the inner and outer ailerons is installed. Next, the middle hinge rotation axis 5 of the inner and outer ailerons is installed. Then, the detachable block 3 for filling the installation notch of the outer aileron is installed. Finally, the detachable rotation axis 4 on the outer side of the outer aileron is installed.

[0073] When installing the outer aileron 1, in the area near the detachable rotation axis 4 on the outer side of the outer aileron 1 at the outer end of the outer aileron 1, a local installation notch for the outer aileron is designed on the trailing edge wing tip rib 12 of the wing 8. After the outer aileron 1 needs to rotate an angle, the area near the detachable rotation axis 4 on the outer side of the outer aileron 1 is placed into the installation notch for the outer aileron, and then it is moved inward so that the spherical plain bearing 2 at the inner end of the outer aileron 1 is stuck into the middle hinge rotation axis 5 of the inner and outer ailerons. To fill the installation notch for the outer aileron, the detachable block 3 for filling the installation notch of the outer aileron is designed.

[0074] To achieve the installation of the detachable rotation axis 4 on the outer side of the outer aileron, it is realized by removing the winglet 11 at the wing tip on the outer side of the aileron.

[0075] For the inner and outer ailerons in this application, a framework made of an aluminum alloy integrated machine is used, and the outer surface is covered with a carbon fiber composite aileron panel 15, with an aileron foam sandwich 16 enclosed within the aileron panel 15. The use of the aileron aluminum alloy framework 14 facilitates the embedding of the spherical plain bearing 2 of the aileron and can ensure the position accuracy after the installation of the spherical plain bearing 2.

[0076] The operation sequence for aileron disassembly is opposite to the installation operation sequence.

[0077] Technical effects of this embodiment: This application utilizes the condition that the winglet on the outer side of the aileron is detachable. Through a special hinge rotation axis structure and a specific installation sequence, the hinge structure of the aileron can be made simple and lightweight, and the aileron hinge joints can be maximally hidden, thereby reducing the impact on the aileron aerodynamic surface.

[0078] The above are only the preferred embodiments of the present utility model, and thus do not limit the protection scope of the present utility model. For those skilled in the art, the present utility model can have various changes and modifications. Any changes, modifications, substitutions, integrations, and parameter changes made to these embodiments by means of conventional substitutions or capable of achieving the same functions without departing from the principle and spirit of the present utility model fall within the protection scope of the present utility model.

Claims

1. A connection structure between an aileron and a wing, characterized in that: The structure comprises an outer aileron (1), a joint bearing (2), a detachable stopper (3), a detachable rotating shaft (4), a hinge rotating shaft (5), a hinge fixed detachable support (6), an aileron driving rod (7), a wing (8), an inner aileron (9), and a rotating shaft (10); The joint bearing (2) is embedded in the outer end surface of the inner aileron (9) and the inner end surface of the outer aileron (1); The detachable rotating shaft (4) is installed at the outer side of the outer aileron; The outer end of the outer aileron (1) is close to the position area of ​​the detachable rotating shaft (4); The hinge shaft (5) is installed at the middle position between the inner aileron (9) and the outer aileron (1), and is embedded in the wing end rib (12) through the joint bearing (2); The wing end rib (12) is embedded in the inner side of the inner aileron (9); The hinged fixed detachable support (6) is mounted on the rear beam of the wing (8); The aileron driving rod (7) is mounted on the wing (8); The inner aileron (9) and the outer aileron (1) are located at the trailing edge of the wing (8) close to the wing tip; The rotating shaft (10) is installed on the inner side of the inner aileron (9).

2. The connection structure between an aileron and a wing according to claim 1, characterized in that: A detachable wingtip winglet (11) is arranged at the wing tip of the wing (8).

3. The connection structure between an aileron and a wing according to claim 1, characterized in that: One end of the inner hinge of the inner aileron (9), the outer aileron (1) and the wing (8) is mounted on the rotating shaft (10), and the other end is mounted on the joint bearing (2) on the wing end rib (12).

4. The connection structure between an aileron and a wing according to claim 3, characterized in that: The hinge between the inner aileron (9) and the outer aileron (1) passes through an L-shaped hinge fixed detachable support (6) and a stepped shaft clamped on the hinge fixed detachable support (6), one end of which is embedded in the outer end surface of the inner aileron (9), and the other end is connected to the joint bearing (2) on the inner end surface of the outer aileron (1).

5. The connection structure between an aileron and a wing according to claim 3, characterized in that: The outer end hinge of the outer aileron (1) is connected along a detachable rotating shaft (4) from the outer side of the wing (8) to the inner side through a detachable stopper (3) and a joint bearing (2) at the outer end of the outer aileron (1).

6. The connection structure between an aileron and a wing according to claim 3, characterized in that: An outer aileron installation notch is designed at a local position of the wing end rib (12), and the outer aileron installation notch is filled with a detachable stopper (3).

7. The connection structure between an aileron and a wing according to claim 1, characterized in that: The outer aileron (1) can rotate at an angle; and the joint bearing (2) at the inner end of the outer aileron (1) can be inserted into the hinge shaft (5).

8. The connection structure between an aileron and a wing according to claim 7, characterized in that: The upper and lower ends of the hinge shaft (5) are connected to ball bearings (13).

9. The connection structure between an aileron and a wing according to claim 1, characterized in that: The outer surfaces of the inner aileron (9) and the outer aileron (1) are covered with an aileron panel (15); The outer surface of the aileron panel (15) is covered with a carbon fiber composite material; The aileron panel (15) is filled with an aileron foam sandwich (16); An aileron aluminum alloy frame (14) is installed on the outer sides of the inner aileron (9) and the outer aileron (1).

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