Airfoil locking structure

Abstract

The utility model discloses an airfoil locking structure which is arranged on an aircraft. The structure comprises a power mechanism and a fixing mechanism, wherein the power mechanism is arranged between the folding wing and the fuselage and is used for driving the folding wing to unfold; the fixing mechanism comprises an in-place block, a mounting block, a limiting pin, a first compression spring, a limiting plate, a contact rod and a second compression spring, a vertical first mounting hole is formed in one side of the bottom of the mounting block and matched with a machine body limiting hole, and the limiting pin is movably mounted in the hole and connected through the first compression spring; a mounting groove and a second mounting hole which are communicated are transversely formed in the other side of the mounting block, the limiting plate belt moves in the mounting groove through the hole, a plate body of the limiting plate belt can block the limiting pin, the limiting pin is released through the hole, and the contact rod is movably connected in the second mounting hole, fixedly connected with the limiting plate and connected through the second compression spring. According to the structure, the high-reliability unfolding and locking process is achieved through pure mechanical design, it is ensured that the folding wing is stably fixed under the aerodynamic load, and the overall structure is reasonable, small in size and light.

Description

Technical Field

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

[0002] Folding wing deployment and locking technology for aircraft has been continuously innovated in recent years with the rapid development of the aerospace field. Early aircraft mostly used fixed folding wings, which, while structurally stable, occupied a large space and could not meet the demands of modern aircraft for convenient storage and transportation and flexible launch. Therefore, folding wing technology has gradually become mainstream, using elastic elements such as springs and torsion springs to drive the folding wing deployment, combined with limiting and locking structures to achieve locking. For example, some solutions use torsion springs to store potential energy to drive the folding wing rotation, while simultaneously using wedge-shaped locking parts or spring-loaded locking pins to achieve mechanical locking, significantly improving the space utilization of the aircraft. However, traditional designs still suffer from complex structural force transmission and cumbersome debugging, and most solutions have not optimized key indicators such as folding wing deployment time and locking accuracy. With the popularization of drones and intelligent aircraft, lightweight, low-power, and highly reliable purely mechanical locking solutions have become an important direction for industry development.

[0003] Despite some progress in existing technologies, numerous technical bottlenecks remain. On one hand, traditional electric or hydraulically driven locking systems require continuous power, increasing the energy burden on the aircraft and significantly increasing its size and weight due to structural complexity, a problem particularly pronounced in small aircraft. For example, electric drives require high-torque motors and gearboxes with large transmission ratios, placing stringent demands on the structural strength of the folding wing root and incurring high maintenance costs. On the other hand, locking methods relying on electronic control systems have reliability vulnerabilities. For instance, servo mechanism locking is susceptible to electromagnetic interference or mechanical jamming, potentially leading to failure in emergencies. Furthermore, while some mechanical locking solutions simplify the structure, they require manual deployment or rely on complex multi-power source coordination, making them unsuitable for automated combat requirements. For example, traditional pin-puller locking requires additional hardware to monitor the unlocking status, and the pin can easily jam against the folding wing during retraction, causing locking failure. Therefore, achieving full automation of the folding wing deployment and locking process without additional energy, while simultaneously ensuring aerodynamic load resistance and ease of maintenance, has become a core technological challenge that urgently needs to be addressed. Utility Model Content

[0004] The purpose of this invention is to provide a wing surface locking structure to solve the following technical problems mentioned in the background art:

[0005] Traditional hydraulic or electric-driven locking systems require continuous power, increasing the energy burden on the aircraft and significantly increasing its size and weight due to their complex structure.

[0006] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is as follows:

[0007] A wing locking structure is installed on an aircraft. The wing locking structure includes a power mechanism and a fixing mechanism. The power mechanism is located between the folding wing and the fuselage of the aircraft and is used to drive the folding wing to unfold. The fixing mechanism includes a positioning block, a mounting block, a limiting pin, a first compression spring, a limiting plate, a contact rod, and a second compression spring. A first mounting hole is provided vertically on one side of the bottom of the mounting block, and a limiting hole that mates with the first mounting hole is provided on the fuselage. The limiting pin is movably disposed in the mounting hole, and both ends of the first compression spring are connected to the limiting pin and the mounting block, respectively. A mounting groove and a second mounting hole are provided horizontally on one side of the bottom of the mounting block, and the mounting groove communicates with the first mounting hole. The limiting plate is movably disposed in the mounting groove, and a through hole is provided on one side of the limiting plate. The plate body is used to block the limiting pin, and the through hole is used to release the limiting pin. The contact rod is movably connected in the second mounting hole, one end of the contact rod is fixedly connected to the limiting plate, and both ends of the second compression spring are connected to the contact rod and the mounting block, respectively.

[0008] Furthermore, the power mechanism includes a connector, a rotating head, a fixed column, a fixed rod, and a coil spring; wherein, the fixed column is fixedly connected to the fuselage, the connector is fixedly connected to the folding wing; the rotating head is fixedly connected to the connector and is also rotatably connected to the fixed column; the fixed rod is fixedly connected to the connector, one end of the coil spring is fixedly connected to the fixed column, and the other end is connected to the fixed rod.

[0009] Furthermore, a bearing is provided between the rotating head and the fixed column.

[0010] Furthermore, an extension is provided on the outer side of the bottom of the connector.

[0011] Furthermore, a mounting part is fixedly connected to the contact rod, and the second compression spring is connected to the mounting part.

[0012] Furthermore, a limiting part is provided on one side of the second mounting hole to limit the range of movement of the contact rod.

[0013] Furthermore, the diameter of the top side of the limiting pin is smaller than the diameter of the bottom side, and the top side of the limiting pin is inserted into the first compression spring.

[0014] Furthermore, the end of the contact rod furthest from the limiting plate has a rounded head structure.

[0015] Furthermore, the diameter of the through hole on the limiting plate is larger than the diameter of the bottom side of the limiting pin.

[0016] Furthermore, a release hole is provided at the bottom of the limiting hole.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] This invention achieves automatic supply of driving force for folding wing deployment through a power mechanism. With the mechanical triggering of the contact rod and the positioning block in the fixing mechanism, and the design of the spring-driven limit pin inserting into the limit hole, the automatic locking of the folding wing after deployment can be completed without additional energy. The highly reliable deployment and locking process is achieved with a purely mechanical structure, ensuring the stable fixation of the aircraft's folding wing under aerodynamic loads. The overall structure is reasonable and perfect, occupies less space, and is also lighter in weight. Attached Figure Description

[0019] Figure 1 This is one of the overall structural schematic diagrams of this utility model;

[0020] Figure 2 This is the second schematic diagram of the overall structure of this utility model;

[0021] Figure 3 This is a cross-sectional schematic diagram of the fixing mechanism part of this utility model;

[0022] Figure 4 This is a cross-sectional schematic diagram of the limiting plate and contact rod portion of this utility model;

[0023] Figure 5 This is a cross-sectional schematic diagram of the power mechanism part of this utility model.

[0024] The markings in the diagram are: 1-Power mechanism, 2-Folding wing, 3-Fuselage, 4-Positioning block, 5-Fixing mechanism, 6-Through hole, 7-First compression spring, 8-First mounting hole, 9-Mounting block, 10-Mounting part, 11-Limiting part, 12-Second mounting hole, 13-Contact rod, 14-Second compression spring, 15-Release hole, 16-Limiting hole, 17-Limiting pin, 18-Mounting groove, 19-Limiting plate, 20-Rotating head, 21-Connecting head, 22-Fixing rod, 23-Coil spring, 24-Fixing column, 25-Bearing. Detailed Implementation

[0025] 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.

[0026] Example:

[0027] A wing-mounted locking structure, installed on an aircraft, such as Figure 1 as well as Figure 2As shown, the wing locking structure includes a power mechanism 1 and a fixing mechanism 5; the power mechanism 1 is located between the folding wing 2 and the fuselage 3 of the aircraft, and the power mechanism 1 is used to drive the folding wing 2 to unfold; as Figure 3 as well as Figure 4 As shown, the fixing mechanism 5 includes a positioning block 4, a mounting block 9, a limiting pin 17, a first compression spring 7, a limiting plate 19, a contact rod 13, and a second compression spring 14. A first mounting hole 8 is vertically provided on one side of the bottom of the mounting block 9, and a limiting hole 16 that mates with the first mounting hole 8 is provided on the body 3. The limiting pin 17 is movably disposed within the mounting hole, and both ends of the first compression spring 7 are connected to the limiting pin 17 and the mounting block 9, respectively. A mounting groove 18 and a second mounting hole 12 are horizontally connected on one side of the bottom of the mounting block 9, and the mounting groove 18 communicates with the first mounting hole 8. The limiting plate 19 is movably disposed within the mounting groove 18, and a through hole 6 is provided on one side of the limiting plate 19. The plate body of the limiting plate 19 is used to block the limiting pin 17, and the through hole 6 is used to release the limiting pin 17. The contact rod 13 is movably connected within the second mounting hole 12, one end of the contact rod 13 is fixedly connected to the limiting plate 19, and both ends of the second compression spring 14 are connected to the contact rod 13 and the mounting block 9, respectively.

[0028] Specifically, in the initial state, the aircraft is placed inside the launch tube, the folding wing 2 is not deployed, and the locking structure is awaiting triggering. Under the elastic force of the first compression spring 7, the top of the limiting pin 17 abuts against the body of the limiting plate 19, and the bottom is not inserted into the limiting hole 16 of the fuselage 3. At this time, the folding wing 2 can move freely under the drive of the power mechanism 1. The contact rod 13 is not subjected to external force, the second compression spring 14 is in a naturally extended state, and the limiting plate 19 blocks the first mounting hole 8 to prevent the limiting pin 17 from moving downward.

[0029] After launch, the aircraft detaches from the launch tube, and the power mechanism 1 drives the folding wing 2 from the retracted state of the fuselage 3 to the unfolded state. During the unfolding process of the folding wing 2, the front end of the contact rod 13 contacts the positioning block 4, and the blocking force of the positioning block 4 pushes the contact rod 13 back into the second mounting hole 12. The contact rod 13 drives the limiting plate 19 to slide laterally in the mounting groove 18. At this time, the second compression spring 14 is compressed, and the through hole 6 on the limiting plate 19 gradually aligns with the first mounting hole 8 and the limiting hole 16 on the fuselage 3. When the folding wing 2 unfolds to the predetermined angle, the through hole 6 of the limiting plate 19 is completely aligned with the first mounting hole 8 and the limiting hole 16. The first compression spring 7 releases its elastic force, pushing the limiting pin 17 to slide downward along the first mounting hole 8, and its bottom inserts into the limiting hole 16 of the fuselage 3, forming a mechanical lock. After the limiting pin 17 is inserted, the position of the folding wing 2 is fixed, the power mechanism 1 stops working, and the locking structure maintains the attitude of the folding wing 2 by the cooperation of the limiting pin 17 and the limiting hole 16. If the folding wing 2 needs to be folded, external force can be used to push the limit pin 17 upward, and at the same time the contact rod 13 separates from the positioning block 4. The second compression spring 14 pushes the limit plate 19 to reset, blocking the limit pin 17, and the folding wing 2 can be folded up again.

[0030] In a preferred embodiment, such as Figure 5 As shown, the power mechanism 1 includes a connector 21, a rotating head 20, a fixed column 24, a fixed rod 22, and a coil spring 23; wherein, the fixed column 24 is fixedly connected to the fuselage 3, and the connector 21 is fixedly connected to the folding wing 2; the rotating head 20 is fixedly connected to the connector 21 and is also rotatably connected to the fixed column 24; the fixed rod 22 is fixedly connected to the connector 21, and one end of the coil spring 23 is fixedly connected to the fixed column 24, and the other end is connected to the fixed rod 22. In the power mechanism 1, the fixed column 24 is fixedly connected to the fuselage 3 to provide a support base, the connector 21 is fixedly connected to the folding wing 2 to realize power transmission, the rotating head 20 enables the connector 21 to rotate around the fixed column 24 to drive the folding wing 2 to rotate and unfold, the fixed rod 22 is connected to the connector 21 and cooperates with the coil spring 23, one end of the coil spring 23 is fixed to the fixed column 24 and the other end is connected to the fixed rod 22. After the aircraft is launched, the stored elastic potential energy is released to push the fixed rod 22 to drive the connector 21 and the folding wing 2 to rotate around the fixed column 24, realizing the automated drive of the folding wing 2 from the retracted state to the unfolded state, and providing a continuous and stable power source for the unfolding of the folding wing 2.

[0031] Further optimization, such as Figure 5As shown, a bearing 25 is provided between the rotating head 20 and the fixed column 24. The bearing 25 between the rotating head 20 and the fixed column 24 can replace sliding friction with rolling friction, which can significantly reduce the resistance when the rotating head 20 rotates, making the unfolding process of the folding wing 2 smoother and reducing power loss. At the same time, the bearing 25 can improve the coaxiality and stability of the rotating connection, prevent the rotating head 20 from shaking and causing the unfolding angle of the folding wing 2 to deviate, enhance the reliability of the mechanism operation, and extend the service life of the power mechanism 1.

[0032] Furthermore, the connector 21 has an extension around its bottom outer side. This extension protects internal components such as the coil spring 23 and the fixing post 24.

[0033] In a preferred embodiment, such as Figure 3 As shown, a mounting part 10 is fixedly connected to the contact rod 13, and the second compression spring 14 is connected to the mounting part 10. The mounting part 10 and the second compression spring 14 are fixedly connected to the contact rod 13, which can provide a stable force point for the spring, ensuring that the spring force is evenly applied to the contact rod 13 and avoiding force deviation caused by direct connection of the spring; at the same time, the mounting part 10 can standardize the installation position of the spring, prevent the spring from tilting or jamming during compression or extension, ensure the action accuracy and reset reliability when the contact rod 13 drives the limit plate 19 to move, and improve the stability of the locking structure triggering.

[0034] In a preferred embodiment, such as Figure 3 As shown, a limiting part 11 is provided on one side of the second mounting hole 12. The limiting part 11 is used to limit the movement range of the contact rod 13. The limiting part 11 in the second mounting hole 12 can limit the movement range of the contact rod 13 and prevent the contact rod 13 from leaving the second mounting hole 12.

[0035] In a preferred embodiment, the diameter of the top side of the limiting pin 17 is smaller than the diameter of the bottom side, and the top side of the limiting pin 17 is inserted into the first compression spring 7. The smaller diameter of the top of the limiting pin 17, with the top inserted into the first compression spring 7, creates a stepped structure through this diameter difference. This allows the lower end of the spring to rest against the step, ensuring that the spring force is precisely applied along the axis of the limiting pin 17 and preventing spring misalignment. Simultaneously, the smaller top diameter facilitates spring installation and positioning, while the larger bottom diameter matches the limiting hole 16 to form a reliable lock. This stepped design ensures the stability of the spring drive and enhances the resistance to pull-out after the limiting pin 17 is inserted into the limiting hole 16, thereby improving the reliability of the locking structure.

[0036] In a preferred embodiment, the end of the contact rod 13 furthest from the limiting plate 19 has a rounded head. This rounded head reduces frictional resistance when contacting the positioning block 4, preventing sharp edges from wearing down the positioning block 4 or the contact rod 13 itself. Simultaneously, the rounded head buffers impact when colliding with the positioning block 4, reducing vibration and noise, ensuring a smooth contact triggering process, and preventing stress concentration from causing deformation at the end of the contact rod 13, thus ensuring the reliability and durability of the locking structure's triggering action.

[0037] In a preferred embodiment, the diameter of the through hole 6 on the limiting plate 19 is larger than the diameter of the bottom side of the limiting pin 17. The larger diameter of the through hole 6 on the limiting plate 19 provides sufficient space for the limiting pin 17 to be inserted, preventing jamming due to machining errors or assembly deviations, and ensuring smooth passage of the limiting pin 17.

[0038] In a preferred embodiment, a release hole 15 is provided at the bottom of the limiting hole 16. The release hole 15 at the bottom of the limiting hole 16 allows a tool to be inserted through the release hole 15 to push the bottom of the limiting pin 17 when unlocking is required, overcoming the elastic force of the first compression spring 7 to move it upward and disengage it from the limiting hole 16, providing an operating channel for manual or mechanical unlocking, and facilitating the folding wing 2 to be folded and retracted.

[0039] 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.

[0040] 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.

[0041] 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 wing surface locking structure, installed on an aircraft, characterized in that: The wing locking structure includes a power mechanism (1) and a fixing mechanism (5); the power mechanism (1) is located between the folding wing (2) and the fuselage (3) of the aircraft, and the power mechanism (1) is used to drive the folding wing (2) to unfold; the fixing mechanism (5) includes a positioning block (4), a mounting block (9), a limiting pin (17), a first compression spring (7), a limiting plate (19), a contact rod (13) and a second compression spring (14); The mounting block (9) has a first mounting hole (8) vertically arranged on one side of its bottom, and a limiting hole (16) that mates with the first mounting hole (8) is provided on the body (3); a limiting pin (17) is movably arranged in the mounting hole, and the two ends of the first compression spring (7) are respectively connected to the limiting pin (17) and the mounting block (9); the mounting block (9) has a mounting groove (18) and a second mounting hole (12) that are interconnected in the horizontal direction on one side of its bottom, and the mounting groove (18) and the first mounting hole (8) are connected in the horizontal direction. The limiting plate (19) is movably set in the mounting groove (18), and a through hole (6) is provided on one side of the limiting plate (19); the plate body of the limiting plate (19) is used to block the limiting pin (17), and the through hole (6) is used to release the limiting pin (17); the contact rod (13) is movably connected in the second mounting hole (12), one end of the contact rod (13) is fixed to the limiting plate (19), and the two ends of the second compression spring (14) are respectively connected to the contact rod (13) and the mounting block (9).

2. The wing surface locking structure according to claim 1, characterized in that: The power mechanism (1) includes a connector (21), a rotating head (20), a fixed column (24), a fixed rod (22), and a coil spring (23); wherein, the fixed column (24) is fixedly connected to the fuselage (3), the connector (21) is fixedly connected to the folding wing (2); the rotating head (20) is fixedly connected to the connector (21) and the rotating head (20) is also rotatably connected to the fixed column (24); the fixed rod (22) is fixedly connected to the connector (21), one end of the coil spring (23) is fixedly connected to the fixed column (24), and the other end is connected to the fixed rod (22).

3. The wing surface locking structure according to claim 2, characterized in that: A bearing (25) is provided between the rotating head (20) and the fixed column (24).

4. The wing surface locking structure according to claim 2, characterized in that: The connector (21) has an extension ring on the outer side of its bottom.

5. The wing surface locking structure according to claim 1, characterized in that: A mounting part (10) is fixedly connected to the contact rod (13), and the second compression spring (14) is connected to the mounting part (10).

6. The wing surface locking structure according to claim 1, characterized in that: A limiting part (11) is provided on one side inside the second mounting hole (12), and the limiting part (11) is used to limit the movement range of the contact rod (13).

7. The wing surface locking structure according to claim 1, characterized in that: The diameter of the top side of the limiting pin (17) is smaller than the diameter of the bottom side, and the top side of the limiting pin (17) is inserted into the first compression spring (7).

8. The wing surface locking structure according to claim 1, characterized in that: The end of the contact rod (13) away from the limiting plate (19) has a round head structure.

9. The wing surface locking structure according to claim 1, characterized in that: The diameter of the through hole (6) on the limiting plate (19) is larger than the diameter of the bottom side of the limiting pin (17).

10. A wing surface locking structure according to claim 1, characterized in that: A release hole (15) is provided at the bottom of the limiting hole (16).

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