A flexible structure for an aircraft wing

Abstract

This utility model relates to the field of aircraft structural design technology, specifically to a flexible structure for an aircraft wing, including an adjustment structure, a skin, a wing frame, and an aileron frame. The wing frame and the aileron frame are hinged together. Multiple adjustment structures are symmetrically distributed on the upper and lower sides of the wing frame. Two skins are laid on the upper and lower sides of the connection between the wing and the aileron, respectively. The fixed end of each adjustment structure is located on the wing frame, and the movable end is connected to the skin. This utility model solves the problem of gaps at the connection between the wing and the aileron: through the coordinated action of multiple adjustment structures, the shape of the skin can be adjusted in real time according to the rotation of the aileron, ensuring that the skin remains smooth during aileron deflection, eliminating gaps at the connection, and guaranteeing the smoothness, continuity of deformation, and airtightness of the skin surface. This reduces the impact of airflow fluctuations on flight stability, lowers aerodynamic drag, and improves lift efficiency.

Description

Technical Field

[0001] This utility model relates to the field of aircraft structural design technology, specifically to a flexible structure for an aircraft wing. Background Technology

[0002] With the rapid development of aerospace technology, aircraft performance is constantly being challenged, and improving aircraft aerodynamic performance, flight efficiency, and safety has become a key research focus. In aircraft structure, the wing, as a crucial component for generating lift, has a vital impact on the overall performance of the aircraft.

[0003] In existing technologies, the wings and ailerons are hinged structures with gaps between them. During flight, these gaps introduce additional aerodynamic noise and vibration. Aerodynamic noise not only affects cabin comfort but can also cause fatigue damage to the fuselage structure; while vibration can be transmitted to the entire aircraft structure, affecting the normal operation of various components and even threatening flight safety.

[0004] Therefore, developing a flexible structure that can achieve seamless connection between the wing and aileron to solve the above problems has become an urgent issue to be addressed in the aviation field. Utility Model Content

[0005] This invention provides a flexible structure for an aircraft wing. This structure can adjust the curvature of the skin surface according to flight requirements, ensuring that the skin at the connection between the wing and aileron remains smooth. The aim is to overcome the problem in existing technologies where gaps exist at the connection between the aircraft wing and aileron, thus affecting the continuity and airtightness of the aircraft skin.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a flexible structure for an aircraft wing, installed at the connection between the wing and the aileron, comprising an adjustment structure, a skin, a wing frame, and an aileron frame; the wing frame and the aileron frame are hinged together; multiple adjustment structures are symmetrically distributed on the upper and lower sides of the wing frame; two skins are respectively laid on the upper and lower sides of the connection between the wing and the aileron; the fixed end of the adjustment structure is disposed on the wing frame, and the movable end is connected to the skin;

[0007] A single adjustment structure includes a wave spring, a motor support, a hinge, a telescopic rod, a collar, a motor, and a drive shaft;

[0008] The motor support is mounted on the wing frame, the motor is fixed on the motor support, and the drive shaft is connected to the motor; a collar is fixedly installed on the drive shaft; one end of the telescopic rod is connected to the drive shaft through the collar, and the other end is hinged to the skin through a hinge.

[0009] Furthermore, the collar is a ring-shaped structure, with the inner ring of the collar adapted to the drive shaft and the outer ring of the collar having an interface for connecting to the telescopic rod. The drive shaft drives the collar to rotate, which in turn drives the telescopic rod to rotate.

[0010] Furthermore, the wave spring is installed horizontally between the skin and the wing frame and aileron frame; the cross-section of the wave spring is triangular.

[0011] Furthermore, three adjustment structures are provided on each of the upper and lower sides of the wing frame.

[0012] Furthermore, the skin at the connection between the wing and the aileron is made of PEEK material reinforced with nylon 12.

[0013] Beneficial effects

[0014] This invention solves the problem of gaps at the connection between the wing and aileron: through the coordinated action of multiple adjustment structures, the shape of the skin can be adjusted in real time according to the rotation of the aileron, so that the skin remains smooth during the aileron deflection process, eliminating gaps at the connection, ensuring the smoothness of the skin surface, the continuity of deformation and airtightness, thereby reducing the impact of airflow fluctuations on flight stability, reducing aerodynamic drag and improving lift efficiency. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this utility model. For those skilled in the art, other drawings can be obtained based on these drawings.

[0016] Figure 1 This is a schematic diagram of the flexible structure of an aircraft wing disclosed in this utility model.

[0017] Figure 2 This is a schematic diagram of the flexible structure of an aircraft wing in its normal state, as disclosed in this utility model.

[0018] Figure 3 This is a schematic diagram of the flexible structure of an aircraft wing in the upward deflection state disclosed in this utility model.

[0019] Figure 4 This is a top view of the flexible structure wing of an aircraft disclosed in this utility model.

[0020] In the picture:

[0021] 1-Wave spring; 2-Motor support; 3-Hinge; 4-Telescopic rod; 5-Collar ring; 6-Motor; 7-Drive shaft; 8-Skin; 9-Wing skeleton; 10-Aileron skeleton. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] To achieve the above objectives, this utility model provides the following technical solution, such as... Figure 1-4 As shown, a flexible structure for an aircraft wing is installed at the connection between the wing and the aileron. The structure mainly consists of an adjustment structure, a skin 8, a wing frame 9, and an aileron frame 10.

[0024] The wing frame 9 and the aileron frame 10 are hinged. During flight, the aileron frame 10 can rotate relative to the wing frame 9. In the prior art, the pilot can change the force on the aircraft by adjusting the angle of the aileron frame 10, thereby realizing the aircraft's turning, take-off and landing operations.

[0025] Multiple adjustment structures are symmetrically distributed on the upper and lower sides of the wing frame 9. In this application, three adjustment structures are provided on each of the upper and lower sides of the wing frame 9, which can ensure that uniform and effective control forces are applied to multiple parts of the skin 8, and ensure that the skin 8 remains in a smooth state during deformation.

[0026] There are two skin panels, one on the upper and one on the lower side of the wing-aileron junction. Skin panels 8 are designed to ensure smoothness, continuous deformation, and airtightness at the wing-aileron junction. Skin panels 8 are made of PEEK material reinforced with nylon 12. PEEK material has relatively soft molecular chains and an elongation of 80%-100%, allowing skin panels 8 to withstand flexible deformation without breaking due to repeated deformation. Furthermore, as a flexible material, PEEK's elastic deformation capacity allows it to better withstand vibrations and alternating loads generated during flight, reducing structural damage and further ensuring safe flight.

[0027] The individual adjustment structure includes: wave spring 1, motor support 2, hinge 3, telescopic rod 4, collar 5, motor 6, and drive shaft 7.

[0028] At the junction of the wing and aileron, the motor mount 2 is installed on the wing frame 9, providing a mounting base for the motor 6. The motor 6 is fixed to the motor mount 2 and serves as an adjustment mechanism providing driving force. The drive shaft 7 is connected to the motor 6; when the motor 6 operates, it drives the drive shaft 7 to rotate, transmitting the power from the motor 6 to subsequent components.

[0029] The telescopic rod 4 is a telescopic rod structure whose length can be adjusted according to needs. In this embodiment, an electric push rod is selected, which drives the telescopic rod 4 to extend and retract through an additional power source.

[0030] Furthermore, the collar 5 has a ring-shaped structure. The inner ring of the collar 5 is adapted to the drive shaft 7, and the outer ring of the collar 5 has an interface for connecting to the telescopic rod 4. The drive shaft 7 drives the collar 5 to rotate, thereby driving the deflection movement of the telescopic rod 4. The collar 5 connects the drive shaft 7 and the telescopic rod 4, transmitting the rotational motion of the drive shaft 7 to the telescopic rod 4. One end of the telescopic rod 4 is connected to the drive shaft 7 through the collar 5, and the other end is hinged to the skin 8 through the hinge 3. The hinge 3 allows relative rotation between the telescopic rod 4 and the skin 8, avoiding additional stress on the skin 8 during the deformation process of the skin 8, and ensuring the normal deformation of the skin 8.

[0031] The wave spring 1 is horizontally installed between the skin 8 and the wing frame 9 and aileron frame 10. Since the skin 8, wing frame 9, and aileron frame 10 form a triangular area, the cross-section of the wave spring 1 is also triangular. That is, the thickness of the wave spring 1 varies depending on the space between the skin 8 and the wing frame 9 and aileron frame 10. The wave spring 1, acting as filler between the skin 8 and the wing frame 9 and aileron frame 10, primarily supports the skin 8, ensuring that it maintains its basic shape even when not subjected to structural forces. Simultaneously, the wave spring 1 provides shock absorption for the skin 8, absorbing and buffering some vibration energy during flight, reducing the impact of vibration on the skin 8 and other structural components.

[0032] Wave spring 1 can be manufactured by molding, specifically by preparing the composite wave spring body using carbon fiber prepreg. Carbon fiber prepreg has the characteristics of high strength and light weight, which makes the wave spring 1 not only provide sufficient support force, but also effectively reduce the weight of the overall structure, making it more suitable for the weight-sensitive aerospace field.

[0033] There are gaps near the drive shaft 7 and the telescopic rod 4. These gaps are to provide enough space for the motor 6 to drive the telescopic rod 4 to rotate, to avoid collisions or interference with other components during the rotation of the telescopic rod 4, and to ensure the normal operation of the adjustment structure.

[0034] The adjustment structure is used as follows: When the aileron deflects upward, at the connection between the wing and the aileron, the telescopic rod 4 above the wing will be driven by the motor 6 and deflected away from the wing via the drive shaft 7 and the collar 5. At the same time, the telescopic rod 4 will change its length appropriately, applying an outward pulling force to the skin 8 through the hinge 3, so that the upper part of the skin 8 can extend outward with the rotation of the aileron and maintain a smooth state. Meanwhile, the telescopic rod 4 below the wing will deflect towards the wing and change its length appropriately, applying an inward pushing force to the skin 8 through the hinge 3, so that the lower part of the skin 8 can retract, cooperating with the extension of the upper part, to ensure that the entire skin 8 achieves a flexible and smooth transition when the aileron deflects, without wrinkles or gaps.

[0035] By adjusting the different angles of the drive shaft 7 and the different lengths of the telescopic rod 4, the shape of the skin 8 is controlled, keeping the skin 8 in a smooth state and preventing wrinkles from appearing as the aileron frame 10 rotates. This ensures the surface smoothness, deformation continuity, and airtightness of the connection between the wing and the aileron.

[0036] The embodiments of this utility model are given for illustrative and descriptive purposes only, and are not intended to be exhaustive or to limit the utility model to the forms disclosed. Many modifications and variations will be apparent to those skilled in the art. The embodiments were chosen and described in order to better illustrate the principles and practical applications of this utility model, and to enable those skilled in the art to understand this utility model and design various embodiments with various modifications suitable for a particular purpose.

Claims

1. A flexible structure for an aircraft wing, installed at the junction of the wing and aileron, characterized in that: It includes an adjustment structure, a skin (8), a wing frame (9), and an aileron frame (10); the wing frame (9) is hinged to the aileron frame (10); there are multiple adjustment structures symmetrically distributed on the upper and lower sides of the wing frame (9); there are two skins (8), which are respectively laid on the upper and lower sides of the connection between the wing and the aileron; the fixed end of the adjustment structure is set on the wing frame (9), and the movable end is connected to the skin (8); A single adjustment structure includes a wave spring (1), a motor support (2), a hinge (3), a telescopic rod (4), a collar (5), a motor (6), and a drive shaft (7); The motor support (2) is mounted on the wing frame (9), the motor (6) is fixed on the motor support (2), and the transmission shaft (7) is connected to the motor (6); a collar (5) is fixedly installed on the transmission shaft (7); one end of the telescopic rod (4) is connected to the transmission shaft (7) through the collar (5), and the other end is hinged to the skin (8) through a hinge (3).

2. The flexible structure for an aircraft wing according to claim 1, characterized in that: The collar (5) is a ring structure. The inner ring of the collar (5) is adapted to the drive shaft (7). The outer ring of the collar (5) is provided with an interface for connecting to the telescopic rod (4). The drive shaft (7) drives the collar (5) to rotate, thereby driving the telescopic rod (4) to rotate.

3. The flexible structure for an aircraft wing according to claim 1, characterized in that: The wave spring (1) is installed horizontally between the skin (8) and the wing frame (9) and aileron frame (10); the cross section of the wave spring (1) is triangular.

4. The flexible structure for an aircraft wing according to claim 1, characterized in that: The adjustment structure is provided in three on each of the upper and lower sides of the wing frame (9).

5. The flexible structure for an aircraft wing according to claim 1, characterized in that: The skin (8) at the connection between the wing and the aileron is made of PEEK material reinforced nylon 12.

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