Folding wing structure

Abstract

The utility model discloses a folding wing structure. The folding wing structure comprises a wing surface and an unfolding locking piece, the airfoil is connected with the aircraft through the unfolding cable locking piece; the unfolding locking piece comprises a mounting plate, a connector, a middle connecting rod, a pushing piece, a fixing cylinder, an inner rod and a compression spring; wherein the mounting plate is fixedly connected with an aircraft, the airfoil is fixedly connected with the connector, the connector is hinged to the mounting plate, the fixing cylinder is fixedly connected with the mounting plate, one side of the inner rod is slidably connected into the fixing cylinder, and the compression spring is arranged in the fixing cylinder and connected with the fixing cylinder and the inner rod; the pushing piece is fixedly connected to one end of the inner rod outside the fixed cylinder; two ends of the middle connecting rod are respectively hinged with the pushing piece and the connector. According to the automatic unfolding mode depending on the potential energy of the spring, external continuous power supply or manual intervention is not needed, the wing surface unfolding action can be reliably and timely completed in the flight process, and smooth development of the flight task of the aircraft is guaranteed.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft component technology, specifically a folding wing structure. Background Technology

[0002] Folding wing technology, as a key innovation in the field of aircraft, has significant advantages in improving space utilization and enhancing mission adaptability, and has been widely applied in scenarios such as UAVs, missiles, and carrier-based aircraft. For example, carrier-based aircraft can increase their payload capacity by more than 50% by folding their wings, while missiles using folding wing designs can effectively reduce the diameter of the launch tube and increase the payload capacity of a single vehicle. For high-altitude long-endurance UAVs, folding wing technology can achieve compact storage of high-aspect-ratio wings, solving the problem of airport adaptability during takeoff and landing. In addition, folding wings have also shown potential in civilian fields such as emergency rescue and urban communications. As aircraft develop towards miniaturization and intelligence, the demand for lightweight and high reliability of folding wings is becoming increasingly prominent. Currently, the main drive methods for folding wings include spring energy storage, pyrotechnic drive, and electric motor transmission, but existing technologies still have bottlenecks in terms of structural complexity, deployment synchronization, and aerodynamic performance, which restricts their application in extreme environments and high-dynamic missions.

[0003] Currently, some folding wing structures have numerous shortcomings. On the one hand, some folding wings rely on complex external power units for deployment, which not only increases the overall structural complexity but also makes them prone to failure points, affecting the reliability of automatic deployment. For example, motor-driven systems may fail to deploy properly in harsh environments or due to mechanical failures. On the other hand, some folding wings are not easy to operate during folding and deployment, requiring cumbersome manual assistance or multiple mechanical adjustments, resulting in long preparation times. Furthermore, they are difficult to securely fix the wing surface after folding, making them unable to fully adapt to diverse launch and flight conditions and failing to meet the current requirements for efficient and stable mission execution by aircraft.

[0004] A double-folding wing fully sealed linkage folding and unfolding mechanism is disclosed in patent application number CN202411584516.5. It includes a double-folding deformable wing, a hinge mechanism, a wire rope assembly, a 90° reverse spiral mechanism, a 180° reverse spiral mechanism, and a rope mechanism. The 90° reverse spiral mechanism is installed at the middle position between the fixed inner wing 1a and the folding middle wing 1b, and is supported by the middle wing hinge 2a for rotation. The 180° reverse spiral mechanism is installed at the middle position between the folding middle wing 1b and the folding outer wing 1c, and is supported by the outer wing hinge 2b for rotation. The rope mechanism rotates and outputs, pulling the inner wing wire rope 3a to move back and forth, and causing the middle wing wire rope 3b and the outer wing wire rope 3c to move back and forth in linkage. This forces the right-hand rotating rod 4c, the left-hand rotating rod 5c1, and the right-hand rotating rod 5c2 to engage in linear-to-rotational rolling engagement, causing the folding middle wing 1b to rotate 90° and the folding outer wing 1c to rotate 180°. This achieves the full deployment and full folding effect of the double-folding deformable wing under single drive source and sealed power transmission conditions. The overall structure of this deployment mechanism is quite complex, and it also relies on a drive mechanism during deployment, which makes the operation not simple enough during the folding and deployment of the folding wing. Utility Model Content

[0005] The purpose of this invention is to provide a folding wing structure to solve the following technical problems mentioned in the background art:

[0006] The existing folding wing deployment mechanism has a high overall structural complexity and relies on a drive mechanism during deployment, resulting in inconvenient operation during folding and deployment.

[0007] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is as follows:

[0008] A folding wing structure includes a wing surface and a deployment locking component; the wing surface is connected to an aircraft via a deployment cable locking component; the deployment locking component includes a mounting plate, a connector, a central connecting rod, a pusher, a fixed cylinder, an inner rod, and a compression spring; wherein, the mounting plate is fixedly connected to the aircraft, the wing surface is fixedly connected to the connector, the connector is hinged to the mounting plate, the fixed cylinder is fixedly connected to the mounting plate, one side of the inner rod is slidably connected inside the fixed cylinder, and the compression spring is disposed inside the fixed cylinder and connected to the fixed cylinder and the inner rod; the pusher is fixedly connected to one end of the inner rod located outside the fixed cylinder, and both ends of the central connecting rod are hinged to the pusher and the connector, respectively.

[0009] Furthermore, there are two wing surfaces, which are symmetrically arranged on both sides of the mounting plate and hinged to the mounting plate through connectors respectively; there are two intermediate connecting rods, which are symmetrically arranged on both sides of the pusher and hinged to the pusher, and the intermediate connecting rods on both sides are hinged to the connectors on both sides respectively.

[0010] Furthermore, buffer rods are fixed to both sides of the mounting plate.

[0011] Furthermore, a limiting plate is fixedly attached to the mounting plate, the limiting plate is provided with a first limiting hole, and the connector is provided with a second limiting hole; a limiting pin is also provided, the limiting pin is inserted into the first limiting hole and the second limiting hole.

[0012] Furthermore, a pusher head is detachably connected to the pusher component, and the pusher head is detachably connected to the inner rod.

[0013] Furthermore, the pusher head and the inner rod are connected by threads.

[0014] Furthermore, the fixed cylinder is provided with interconnected circumferential limiting grooves and axial limiting grooves; one end of the inner rod located inside the fixed cylinder is fixedly connected to a top head, which is slidably connected to the fixed cylinder. The top head is also connected to a compression spring. A rotating groove is provided on the top head along the circumferential direction. A limiting block is slidably connected in the rotating groove. The limiting block is also slidably connected to the axial limiting groove. A torsion spring is also provided between the limiting block and the inner rod. The two ends of the torsion spring are respectively connected to the limiting block and the inner rod; the top side of the limiting block is slidably connected in the circumferential limiting groove or the axial limiting groove.

[0015] Furthermore, the spring constant is such that it provides a torsional torque of not less than 5 N·m when the limiting block slides from the axial limiting groove to the circumferential limiting groove.

[0016] Furthermore, the circumferential limiting groove is an arc-shaped groove, the center of which coincides with the axis of the inner rod, and the arc length of the circumferential limiting groove corresponds to an angle of 80°-150°.

[0017] Furthermore, the compression spring is made of alloy material.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] This invention utilizes an energy storage structure consisting of an inner rod, a compression spring, and a fixed cylinder. Before launch, when the wing surface is folded, the movement of the wing surface drives related components, compressing the spring to store energy. After launch, the constraint is released, and the spring's potential energy is automatically released, pushing the inner rod to extend. This, in turn, drives the pusher, intermediate connecting rod, and connector, ultimately achieving automatic wing deployment. This automatic deployment method, relying on spring potential energy, requires no continuous external power supply or manual intervention. It reliably and promptly completes the wing deployment during flight, ensuring the smooth execution of the aircraft's mission.

[0020] This invention utilizes a hinged design between the connector and the mounting plate, allowing the wing surface to rotate flexibly relative to the mounting plate, enabling easy folding of the wing surface before launch. During folding, the wing surface drives the connector, intermediate connecting rod, and pusher components in coordinated motion, allowing the inner rod to smoothly enter the fixed cylinder for energy storage. The entire folding operation conforms to mechanical principles and is relatively natural and smooth, requiring no complex auxiliary tools or cumbersome steps, facilitating pre-launch preparations for the aircraft. Attached Figure Description

[0021] Figure 1 This is a top view of the present invention;

[0022] Figure 2 This is a schematic diagram of the overall structure of this utility model;

[0023] Figure 3 This is a schematic diagram of the internal structure of the fixed cylinder of this utility model;

[0024] Figure 4 This is a cross-sectional view of the present invention.

[0025] The markings in the diagram are: 1-wing surface, 2-push head, 3-fixed cylinder, 4-mounting plate, 5-limiting pin, 6-buffer rod, 7-connector, 8-intermediate connecting rod, 9-push component, 10-limiting plate, 11-circumferential limiting groove, 12-axial limiting groove, 13-inner rod, 14-rotation groove, 15-top head, 16-limiting block, 17-torsion spring, 18-compression spring. Detailed Implementation

[0026] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. 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.

[0027] Example:

[0028] A folding wing structure includes a wing surface 1 and a deployment locking component; the wing surface 1 is connected to an aircraft via a deployment cable locking component; the deployment locking component includes a mounting plate 4, a connector 7, an intermediate connecting rod 8, a pusher 9, a fixed cylinder 3, an inner rod 13, and a compression spring 18; wherein, the mounting plate 4 is fixedly connected to the aircraft, the wing surface 1 is fixedly connected to the connector 7, the connector 7 is hinged to the mounting plate 4, the fixed cylinder 3 is fixedly connected to the mounting plate 4, one side of the inner rod 13 is slidably connected inside the fixed cylinder 3, and the compression spring 18 is disposed inside the fixed cylinder 3 and connected to the fixed cylinder 3 and the inner rod 13; the pusher 9 is fixedly connected to one end of the inner rod 13 located outside the fixed cylinder 3, and the two ends of the intermediate connecting rod 8 are respectively hinged to the pusher 9 and the connector 7.

[0029] The mounting plate 4 is fixed to the aircraft to provide a mounting base. The connector 7 is hinged to the mounting plate 4 to achieve folding of the wing surface 1. The wing surface 1 is folded before launch and unfolded after launch. The inner rod 13, compression spring 18, and fixed cylinder 3 form an energy storage structure that stores spring potential energy. After launch, the spring potential energy pushes the inner rod 13 to extend, which in turn moves the pusher 9. The pusher 9 then rotates the wing surface 1 through the intermediate connection to unfold it. Specifically, in use, the wing surface 1 is first folded. During folding, the wing surface 1 moves the pusher 9 through the connector 7 and intermediate connecting rod 8, causing the inner rod 13 to enter the fixed cylinder 3, thus storing energy. The folded wing surface 1 is then constrained. After launch, the constraint on the wing surface 1 is released, allowing it to unfold automatically.

[0030] In a preferred embodiment, two wing surfaces 1 are provided, symmetrically arranged on both sides of the mounting plate 4 and hinged to the mounting plate 4 via connectors 7 respectively; two intermediate connecting rods 8 are provided, symmetrically arranged on both sides of the pusher 9 and hinged to the pusher 9, with the intermediate connecting rods 8 on both sides respectively hinged to the connectors 7 on both sides. The symmetrical arrangement of the wing surfaces 1 enables the simultaneous deployment or folding of the two wing surfaces 1, balances the load distribution, avoids structural stress and aircraft attitude imbalance caused by off-center loading, and improves deployment stability and reliability.

[0031] In a preferred embodiment, buffer rods 6 are fixed to both sides of the mounting plate 4. The buffer rods 6 are used to block and buffer the wing surface 1 when it is fully deployed, so as to prevent damage to the deployment locking mechanism.

[0032] In a preferred embodiment, a limiting plate 10 is fixedly connected to the mounting plate 4. The limiting plate 10 has a first limiting hole, and the connector 7 has a second limiting hole. A limiting pin 5 is also provided, which is inserted into the first limiting hole and the second limiting hole. After folding the wing surface 1, the wing surface 1 can be positioned by inserting the limiting pin 5, thereby facilitating the loading of the wing surface 1 and the aircraft into a launch structure such as a launch tube that can constrain the wing surface 1.

[0033] In a preferred embodiment, a pusher head 2 is detachably connected to the pusher 9, and the pusher head 2 is detachably connected to the inner rod 13. Further optimized, the pusher head 2 and the inner rod 13 are connected by threads. The detachable pusher head 2 facilitates installation, maintenance, and replacement of vulnerable parts, while the threaded connection ensures a stable connection, adapts to the stress requirements during deployment, and improves structural flexibility.

[0034] In a preferred embodiment, the fixed cylinder 3 is provided with a circumferential limiting groove 11 and an axial limiting groove 12 that are interconnected. A top head 15 is fixedly connected to one end of the inner rod 13 inside the fixed cylinder 3. The top head 15 is slidably connected to the fixed cylinder 3 and is also connected to a compression spring 18. A rotating groove 14 is provided on the top head 15 along the circumferential direction. A limiting block 16 is slidably connected within the rotating groove 14. The limiting block 16 is also slidably connected to the axial limiting groove 12. A torsion spring 17 is also provided between the limiting block 16 and the inner rod 13, with both ends of the torsion spring 17 connected to the limiting block 16 and the inner rod 13 respectively. The top side of the limiting block 16 is slidably connected to either the circumferential limiting groove 11 or the axial limiting groove 12. Through the cooperation of the circumferential limiting groove 11, the axial limiting groove 12, the limiting block 16, and the torsion spring 17, the inner rod 13 is circumferentially locked to prevent retraction after unfolding, and axially slides to store energy during folding, ensuring the stability of the unfolded state of the wing surface 1 and the controllability of the folding process. Specifically, during launch, after the constraint is released, the spring pushes the inner rod 13 to extend axially. When the limiting block 16 reaches the connection between the axial limiting groove 12 and the circumferential limiting groove 11, the torsion spring 17 drives the limiting block 16 to rotate into the circumferential limiting groove 11, the inner rod 13 is axially locked, and the wing surface 1 remains in the deployed state.

[0035] Furthermore, the spring constant of the torsion spring 17 is designed to provide a torsional torque of not less than 5 N·m when the limiting block 16 slides from the axial limiting groove 12 to the circumferential limiting groove 11. This design ensures that the limiting block 16 can overcome external forces such as friction and vibration, reliably rotate into the circumferential limiting groove 11 and remain locked, preventing the inner rod 13 from accidentally retracting and causing the wing surface 1 to fail to deploy, thus improving the stability of the mechanism.

[0036] In a preferred embodiment, the circumferential limiting groove 11 is an arc-shaped groove, the center of which coincides with the axis of the inner rod 13, and the arc length of the circumferential limiting groove 11 corresponds to an angle of 80°-150°. This design ensures smooth circumferential rotation of the limiting block 16, while the arc length angle of 80°-150° balances locking stability and rotation range. This ensures that the limiting block 16 can reliably engage in the groove after unfolding to prevent loosening, while avoiding an angle that is too small, resulting in an unstable lock, or too large, increasing rotational resistance.

[0037] In a preferred embodiment, the compression spring 18 is made of an alloy material. Using an alloy material to make the compression spring 18 improves the spring's strength, toughness, and fatigue resistance, enabling it to better withstand stress during compression and extension.

[0038] In the description of this utility model, it should be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "other end", "upper", "side", "top", "inner", "front", "center", "both ends", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0039] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "setting," "connection," "fixing," "screw connection," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Unless otherwise explicitly limited, those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0040] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A folding wing structure, characterized in that: It includes a wing surface (1) and a deployment locking component; the wing surface (1) is connected to the aircraft via a deployment cable locking component; the deployment locking component includes a mounting plate (4), a connector (7), an intermediate connecting rod (8), a pusher (9), a fixing cylinder (3), an inner rod (13), and a compression spring (18); Among them, the mounting plate (4) is fixed to the aircraft, the wing surface (1) is fixed to the connector (7), the connector (7) is hinged to the mounting plate (4), the fixed cylinder (3) is fixed to the mounting plate (4), one side of the inner rod (13) is slidably connected to the fixed cylinder (3), the compression spring (18) is set in the fixed cylinder (3) and connected to the fixed cylinder (3) and the inner rod (13); the pusher (9) is fixed to the inner rod (13) at one end located outside the fixed cylinder (3), and the two ends of the intermediate connecting rod (8) are hinged to the pusher (9) and the connector (7) respectively.

2. The folding wing structure according to claim 1, characterized in that: There are two wing surfaces (1). The two wing surfaces (1) are symmetrically arranged on both sides of the mounting plate (4) and are respectively hinged to the mounting plate (4) through the connector (7). There are two intermediate connecting rods (8). The two intermediate connecting rods (8) are symmetrically arranged on both sides of the pusher (9) and are hinged to the pusher (9). The intermediate connecting rods (8) on both sides are respectively hinged to the connectors (7) on both sides.

3. The folding wing structure according to claim 1, characterized in that: Buffer rods (6) are fixed to both sides of the mounting plate (4).

4. A folding wing structure according to claim 1, characterized in that: A limiting plate (10) is fixedly attached to the mounting plate (4). The limiting plate (10) is provided with a first limiting hole, and the connector (7) is provided with a second limiting hole. A limiting pin (5) is also provided, which is inserted into the first limiting hole and the second limiting hole.

5. A folding wing structure according to claim 1, characterized in that: The pusher (9) is detachably connected to the push head (2), and the push head (2) is detachably connected to the inner rod (13).

6. A folding wing structure according to claim 5, characterized in that: The pusher (2) and the inner rod (13) are connected by threads.

7. A folding wing structure according to claim 1, characterized in that: The fixed cylinder (3) is provided with a circumferential limiting groove (11) and an axial limiting groove (12) that are interconnected; the inner rod (13) is fixedly connected to a top head (15) at one end inside the fixed cylinder (3), the top head (15) is slidably connected to the fixed cylinder (3), the top head (15) is also connected to a compression spring (18), the top head (15) is provided with a rotating groove (14) along the circumferential direction, the rotating groove (14) is slidably connected to a limiting block (16), the limiting block (16) is also slidably connected to the axial limiting groove (12), the limiting block (16) and the inner rod (13) are also provided with a torsion spring (17), the two ends of the torsion spring (17) are respectively connected to the limiting block (16) and the inner rod (13); the top side of the limiting block (16) is slidably connected to the circumferential limiting groove (11) or the axial limiting groove (12).

8. A folding wing structure according to claim 7, characterized in that: The spring constant of the torsion spring (17) is such that when the limiting block (16) slides from the axial limiting groove (12) to the circumferential limiting groove (11), it provides a torsional torque of not less than 5 N·m.

9. A folding wing structure according to claim 7, characterized in that: The circumferential limiting groove (11) is an arc-shaped groove, the center of which coincides with the axis of the inner rod (13), and the arc length of the circumferential limiting groove (11) corresponds to an angle of 80°-150°.

10. A folding wing structure according to claim 1, characterized in that: The compression spring (18) is made of alloy material.

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