Folding wing structure of aircraft

Abstract

The utility model discloses a folding wing structure of an aircraft. The folding wing structure comprises wings and a folding and unfolding mechanism, the wings are hinged to two sides of a fuselage of the aircraft; the folding and unfolding mechanism comprises a control rod, a guide rod, a compression spring, a connector and a locking piece; a mounting groove is formed in the top of the machine body, the guide rod is fixedly connected into the mounting groove, and the connector is movably connected into the mounting groove and slidably connected with the guide rod; two ends of the compression spring are fixedly connected with the body and the connector respectively; two ends of the control rod are respectively hinged with the wings and the connector; a limiting groove is formed in the guide rod in the axial direction, a section of in-place groove is formed in the guide rod in the circumferential direction, the limiting groove is communicated with the in-place groove, the locking piece is connected with the connector, the inner side of the locking piece is slidably connected to the limiting groove, and the locking piece is used for entering the in-place groove from the limiting groove to lock the position of the connector. After the aircraft with the structure is launched, the wings can be automatically unfolded, extra power is not needed, and the launching efficiency is improved.

Description

Technical Field

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

[0002] With the rapid iteration of aerospace technology, aircraft are increasingly used in military reconnaissance, civilian aerial photography, and logistics transportation, placing higher demands on their portability, launch efficiency, and flight stability. Folding wing structures, due to their ability to effectively reduce the pre-launch volume of aircraft and facilitate loading into launch tubes, transport platforms, or UAV nests, have become a key design for improving space utilization. Currently, the automated deployment and reliable locking of folding wing mechanisms have become core directions for technological development in the industry, especially in scenarios such as UAVs and tactical missiles, where rapid deployment and stable locking of the wings after launch are required to ensure the integrity of the aerodynamic shape. Against this backdrop, folding wing systems with no additional power drive, smooth deployment, and reliable locking structures are gradually becoming a key area of ​​technological innovation in the industry.

[0003] Existing folding wing mechanisms still have some obvious technical problems in practical applications. Some designs rely on additional power sources such as motors and hydraulics to drive the deployment, which not only increases the system weight and energy consumption, but may also cause deployment failure due to power system failure. Especially in small aircraft that are sensitive to weight, the installation of additional power devices will significantly affect flight performance. On the other hand, the reliability of traditional locking structures is lacking, which can easily lead to the inability to lock the wings due to problems such as swaying and jamming during the deployment and locking process.

[0004] Patent application CN202421737702.3 discloses a folding-wing UAV for weather operations. Its front wing is positioned above the nose of the fuselage and rotatably connected to it; the vertical tail is positioned on opposite sides of the tail of the fuselage and rotatably connected to it; the electronic speed controller (ESC) is electrically connected to the drive motor and the battery, providing power to the drive motor for rotation. This type of folding-wing UAV relies entirely on the motor control system to unfold its folding wings after launch, thus requiring an additional power source, increasing system weight and energy consumption, and potentially causing unfolding failure due to power system malfunction. Utility Model Content

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

[0006] Modern aircraft folding wings rely on an additional power source to deploy, which increases system weight and energy consumption, and is also prone to deployment failure due to power system malfunctions.

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

[0008] A folding wing structure for an aircraft includes a wing and a folding / unfolding mechanism. The wing is hinged to both sides of the aircraft fuselage. The folding / unfolding mechanism includes a control rod, a guide rod, a compression spring, a connector, and a locking element. A mounting groove is provided on the top of the fuselage. The guide rod is fixedly connected to the mounting groove, and the connector is movably connected to the mounting groove and slidably connected to the guide rod. The two ends of the compression spring are fixedly connected to the fuselage and the connector, respectively. The two ends of the control rod are hinged to the wing and the connector, respectively. A limit groove is provided on the guide rod along the axial direction, and a positioning groove is provided on the guide rod along the circumferential direction. The limit groove and the positioning groove are interconnected. The locking element is connected to the connector, and its inner side is slidably connected to the limit groove. The locking element is used to enter the positioning groove from the limit groove to lock the position of the connector.

[0009] Furthermore, a mounting bracket is connected to one side of the fuselage by screws, the wing is hinged to the mounting bracket, and the wing is hinged to the fuselage via the mounting bracket.

[0010] Furthermore, stabilizing strips are fixed to both sides of the inner wall of the mounting groove, and stabilizing grooves are provided on both sides of the bottom of the connector, with the stabilizing strips and stabilizing grooves slidingly engaged.

[0011] Furthermore, the locking component includes a fixed ring, a rotating ring, a limiting block, and a power unit; wherein, the fixed ring is fixedly connected to the connector, the rotating ring is rotatably connected to the fixed ring, the limiting block is fixedly connected to the inner side of the rotating ring, one side of the limiting block is slidably connected in the limiting groove, and the power unit is connected to the connector, the power unit is used to drive the rotating ring to rotate so that the limiting block enters the positioning groove.

[0012] Furthermore, a limiting groove is provided on one side of the fixed ring, and a limiting protrusion is provided on the inner side of the rotating ring, with the limiting protrusion slidingly engaging with the limiting groove.

[0013] Furthermore, the power unit includes a mounting housing, a rotating column, a coil spring, a driving gear, and a driven gear ring; the mounting housing is fixedly connected to the connector, one side of the rotating column is rotatably connected to the mounting housing, both ends of the coil spring are fixedly connected to the rotating column and the mounting housing respectively, one side of the rotating column extends out of the mounting housing and is fixedly connected to the driving gear, the driven gear ring is fixedly connected to the rotating ring, and the driving gear meshes with the driven gear ring.

[0014] Furthermore, the mounting housing and connector are detachably and securely connected.

[0015] Furthermore, the connector has a T-shaped structure.

[0016] Furthermore, a compression spring is sleeved on the outside of the guide rod.

[0017] Furthermore, the wings are made of carbon fiber.

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

[0019] This invention's folding wing mechanism, through the cooperation of a compression spring and a folding and unfolding mechanism, can automatically unfold the wings after the aircraft is launched, improving launch efficiency. The limiting groove on the guide rod in this invention can improve the stability of the wing surface unfolding, and the positioning groove on the guide rod can realize the positioning and locking of the connector, thereby realizing the positioning and locking of the folding wing, ensuring wing stability during flight, and guaranteeing aerodynamic performance and flight safety. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0021] Figure 2 for Figure 1 Enlarged schematic diagram of part A;

[0022] Figure 3 This is a cross-sectional view of the present invention;

[0023] Figure 4 for Figure 3 Enlarged schematic diagram of part B;

[0024] Figure 5 This is a cross-sectional view of the connector portion of this utility model;

[0025] Figure 6 This is a partial structural diagram of the guide rod portion of this utility model.

[0026] The markings in the diagram are: 1-fuselage, 2-mounting slot, 3-connector, 4-control lever, 5-wing, 6-mounting bracket, 7-guide rod, 8-locking element, 9-compression spring, 10-mounting shell, 11-drive gear, 12-limiting block, 13-positioning slot, 14-limiting slot, 15-rotating ring, 16-driven gear ring, 17-fixed ring, 18-coil spring, 19-rotating column, 20-limiting protrusion, 21-limiting ring groove, 22-stabilizing groove, 23-stabilizing bar. Detailed Implementation

[0027] 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.

[0028] Example:

[0029] A folding wing structure for an aircraft, such as Figure 1As shown, the aircraft includes a wing 5 and a folding / unfolding mechanism. The wing 5 is hinged to both sides of the fuselage 1 of the aircraft. The folding / unfolding mechanism includes a control rod 4, a guide rod 7, a compression spring 9, a connector 3, and a locking element 8. A mounting groove 2 is provided on the top of the fuselage 1. The guide rod 7 is fixedly connected to the mounting groove 2, and the connector 3 is movably connected to the mounting groove 2 and slidably connected to the guide rod 7. The two ends of the compression spring 9 are fixedly connected to the fuselage 1 and the connector 3, respectively. The two ends of the control rod 4 are hinged to the wing 5 and the connector 3, respectively. A limit groove 14 is provided on the guide rod 7 along the axial direction, and a positioning groove 13 is provided on the guide rod 7 along the circumferential direction. The limit groove 14 and the positioning groove 13 are interconnected. The locking element 8 is connected to the connector 3, and the inner side of the locking element 8 is slidably connected to the limit groove 14. The locking element 8 is used to enter the positioning groove 13 from the limit groove 14 to lock the position of the connector 3.

[0030] Specifically, before launch, the wing 5 is folded and placed into the launch tube along with the fuselage 1. After launch, the compression spring 9 pushes the connector 3 to move, and the connector 3, through the control lever 4, causes the wing 5 to unfold. The connector 3 causes the locking member 8 to slide within the limiting groove 14. After the locking member 8 completes its travel in the limiting groove 14, it enters the positioning groove 13, thereby achieving axial movement of the connector 3, which means locking the folding wing. The locking member 8 can be designed as a protrusion and a tension spring. The protrusion is movably mounted on the connector 3, and the tension spring drives the protrusion to rotate and enter the positioning groove 13. Alternatively, the locking member 8 can be designed as a protrusion and a spring pin. A mounting hole is opened on the protrusion, and the spring pin is placed in the mounting hole. In the initial state, the spring pin is blocked by the groove wall of the limiting groove 14. When the protrusion moves to the positioning groove 13, the spring pin extends and enters the positioning groove 13.

[0031] In a preferred embodiment, such as Figure 1 As shown, a mounting bracket 6 is connected to one side of the fuselage 1 by screws. The wing 5 is hinged to the mounting bracket 6, and the wing 5 is hinged to the fuselage 1 via the mounting bracket 6. This design uses the mounting bracket 6 as an intermediate connecting component, which simplifies the assembly process of the fuselage 1 and the wing 5, and facilitates disassembly and maintenance. On the other hand, the structural design of the mounting bracket 6 optimizes the stress distribution at the hinge point of the wing 5, enhances the connection reliability, and makes the rotation axis of the wing 5 more precise when folding and unfolding, ensuring the stability of the folding and unfolding actions.

[0032] In a preferred embodiment, such as Figure 5 As shown, stabilizing strips 23 are fixed to both sides of the inner wall of the mounting groove 2, and stabilizing grooves 22 are provided on both sides of the bottom of the connector 3. The stabilizing strips 23 and the stabilizing grooves 22 slide in fit. By limiting the stabilizing grooves 22 with the stabilizing strips 23, the radial displacement and circumferential rotation of the connector 3 during the sliding process are constrained, ensuring that the connector 3 slides smoothly along the axial direction of the guide rod 7. This avoids uneven force on the control rod 4 or jamming of the locking component 8 due to offset, thereby improving the stability and reliability of the unfolding and locking process of the folding wing.

[0033] In a preferred embodiment, such as Figure 2 As shown, the locking component 8 includes a fixed ring 17, a rotating ring 15, a limiting block 12, and a power unit; wherein, the fixed ring 17 is fixedly connected to the connector 3, the rotating ring 15 is rotatably connected to the fixed ring 17, the limiting block 12 is fixedly connected to the inner side of the rotating ring 15, one side of the limiting block 12 is slidably connected in the limiting groove 14, and the power unit is connected to the connector 3. The power unit is used to drive the rotating ring 15 to rotate so that the limiting block 12 enters the positioning groove 13.

[0034] Further optimization, such as Figure 4 As shown, a limiting ring groove 21 is provided on one side of the fixed ring 17, and a limiting protrusion 20 is provided on the inner side of the rotating ring 15. The limiting protrusion 20 and the limiting ring groove 21 are in sliding engagement.

[0035] Further optimization, such as Figure 4 as well as Figure 6 As shown, the power unit includes a mounting housing 10, a rotating column 19, a coil spring 18, a driving gear 11, and a driven gear ring 16. The mounting housing 10 is fixedly connected to the connector 3. One side of the rotating column 19 is rotatably connected to the mounting housing 10. Both ends of the coil spring 18 are fixedly connected to the rotating column 19 and the mounting housing 10, respectively. One side of the rotating column 19 extends out of the mounting housing 10 and is fixedly connected to the driving gear 11. The driven gear ring 16 is fixedly connected to the rotating ring 15. The driving gear 11 meshes with the driven gear ring 16.

[0036] In a further optimized manner, the mounting housing 10 and the connector 3 are detachably and fixedly connected.

[0037] When using the locking member 8 of this embodiment, before launch, the rotating column 19 twists the coil spring 18 under the action of an external tool, storing elastic potential energy. When the wing 5 unfolds, the limiting block 12 slides axially along the limiting groove 14 of the guide rod 7 with the connector 3. At this time, the limiting block 12 is constrained by the limiting groove 14 and cannot rotate. When the limiting block 12 slides to the entrance of the positioning groove 13, the coil spring 18 releases energy to drive the rotating column 19 to rotate. The driving gear 11 drives the driven gear ring 16, causing the rotating ring 15 to rotate relative to the fixed ring 17. The rotating ring 15 then drives the limiting block 12 into the positioning groove 13, realizing the locking of the wing 5 in the unfolded state.

[0038] The rotating ring 15 is embedded in the limiting ring groove 21 of the fixed ring 17 through the limiting protrusion 20 on the inner side, ensuring that the rotating ring 15 can only rotate around the axis, limiting its axial displacement, ensuring that the rotation process is smooth and the limiting block 12 is accurately positioned in the groove 13.

[0039] This design utilizes energy storage in the coil spring 18 and mechanical transmission to achieve automatic locking of the wing 5 after it has fully deployed, eliminating the need for a continuous external power supply and improving system reliability. The use of gear ring drive and energy storage in the coil spring 18 integrates the power unit onto the connector 3, saving space and adapting to the miniaturization requirements of aircraft. The mounting housing 10 and connector 3 are detachably connected, facilitating replacement of the coil spring 18 or maintenance of transmission components, thus reducing maintenance costs.

[0040] In a preferred embodiment, such as Figure 5 As shown, connector 3 has a T-shaped structure. This type of connector 3 has a larger top area, which facilitates connection with control rod 4, ensuring the stability of the connection between control rod 4 and connector 3, thereby ensuring the stability and reliability of the folding wing deployment action.

[0041] In a preferred embodiment, the compression spring 9 is sleeved on the outside of the guide rod 7. The compression spring 9 is sleeved on the outside of the guide rod 7, which serves as a support shaft for the spring, preventing radial bending or displacement of the spring under compression and ensuring that the spring thrust is stably transmitted axially along the guide rod 7 to the connector 3. Simultaneously, the limiting effect of the guide rod 7 on the spring makes the spring's charging and releasing process smoother. Combined with the sliding trajectory of the connector 3 along the guide rod 7, this ensures the consistency and reliability of power output when the folding wing unfolds.

[0042] In a preferred embodiment, the wing 5 is made of carbon fiber. The use of carbon fiber in the wing 5 leverages its high strength and lightweight properties to significantly reduce the overall weight of the aircraft while ensuring structural strength and resistance to deformation, thereby improving thrust-to-weight ratio and flight efficiency. Furthermore, carbon fiber exhibits excellent corrosion resistance and fatigue resistance, allowing it to adapt to complex flight environments and extending the service life of the folding wing. Its good formability also facilitates the design of a folding structure for the wing 5, ensuring the reliability of both deployment and folding operations.

[0043] 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.

[0044] 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.

[0045] 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 for an aircraft, characterized in that: It includes wings (5) and a folding and unfolding mechanism; the wings (5) are hinged to both sides of the fuselage (1) of the aircraft; the folding and unfolding mechanism includes a control rod (4), a guide rod (7), a compression spring (9), a connector (3) and a locking element (8); The top of the fuselage (1) is provided with a mounting groove (2), the guide rod (7) is fixedly connected in the mounting groove (2), and the connector (3) is movably connected in the mounting groove (2) and slidably connected to the guide rod (7); the two ends of the compression spring (9) are fixedly connected to the fuselage (1) and the connector (3) respectively; the two ends of the control rod (4) are hinged to the wing (5) and the connector (3) respectively. A limiting groove (14) is provided on the guide rod (7) along the axial direction, and a positioning groove (13) is provided on the guide rod (7) along the circumferential direction. The limiting groove (14) and the positioning groove (13) are connected to each other. The locking member (8) is connected to the connector (3). The inner side of the locking member (8) is slidably connected to the limiting groove (14). The locking member (8) is used to enter the positioning groove (13) from the limiting groove (14) to lock the position of the connector (3).

2. The folding wing structure of an aircraft according to claim 1, characterized in that: A mounting bracket (6) is connected to one side of the fuselage (1) by screws. The wing (5) is hinged to the mounting bracket (6) and the fuselage (1) is hinged to the mounting bracket (6).

3. The folding wing structure of an aircraft according to claim 1, characterized in that: The mounting groove (2) has stabilizing strips (23) fixed on both sides of the inner wall, and the connector (3) has stabilizing grooves (22) on both sides of the bottom. The stabilizing strips (23) and the stabilizing grooves (22) slide together.

4. The folding wing structure of an aircraft according to claim 1, characterized in that: The locking component (8) includes a fixed ring (17), a rotating ring (15), a limiting block (12), and a power unit; wherein, the fixed ring (17) is fixedly connected to the connector (3), the rotating ring (15) is rotatably connected to the fixed ring (17), the limiting block (12) is fixedly connected to the inner side of the rotating ring (15), one side of the limiting block (12) is slidably connected to the limiting groove (14), and the power unit is connected to the connector (3). The power unit is used to drive the rotating ring (15) to rotate so that the limiting block (12) enters the positioning groove (13).

5. The folding wing structure of an aircraft according to claim 4, characterized in that: A limiting ring groove (21) is provided on one side of the fixed ring (17), and a limiting protrusion (20) is provided on the inner side of the rotating ring (15). The limiting protrusion (20) slides in conjunction with the limiting ring groove (21).

6. The folding wing structure of an aircraft according to claim 4, characterized in that: The power unit includes a mounting housing (10), a rotating column (19), a coil spring (18), a driving gear (11), and a driven gear ring (16). The mounting housing (10) is fixedly connected to the connector (3). One side of the rotating column (19) is rotatably connected to the mounting housing (10). Both ends of the coil spring (18) are fixedly connected to the rotating column (19) and the mounting housing (10) respectively. One side of the rotating column (19) extends out of the mounting housing (10) and is fixedly connected to the driving gear (11). The driven gear ring (16) is fixedly connected to the rotating ring (15). The driving gear (11) meshes with the driven gear ring (16).

7. The folding wing structure of an aircraft according to claim 6, characterized in that: The mounting shell (10) and the connector (3) are detachably and fixedly connected.

8. The folding wing structure of an aircraft according to claim 1, characterized in that: The connector (3) has a T-shaped structure.

9. The folding wing structure of an aircraft according to claim 1, characterized in that: A compression spring (9) is sleeved on the outside of the guide rod (7).

10. The folding wing structure of an aircraft according to claim 1, characterized in that: The wings (5) are made of carbon fiber.

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