A wing folding mechanism for unmanned aerial vehicle

Abstract

The present invention provides a wing folding mechanism for a drone, comprising a fixed axis, a left wing and a right wing, a first embedded part arranged in the left wing, a second embedded part arranged in the right wing, a torsion spring sleeved on the outside of the fixed axis, and a limit block. The first embedded part and the second embedded part are both sleeved on the outside of the fixed axis; one end of the torsion spring is connected to the first embedded part, and the other end is connected to the second embedded part. Protrusions are provided on both sides of the limit block, and matching parts are respectively provided on the left wing and the right wing. When the folding mechanism is in an unfolded state, when the left wing and the right wing are unfolded in a straight line relative to the fixed axis, the matching parts abut against the protrusions on both sides. A locking groove is also provided on the left wing or the right wing, and a locking assembly is provided on the limit block. When the left wing and the right wing are driven to overlap, the lock is clamped in the locking groove. The present invention can improve the stability of the unfolded and retracted states of the wing.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a wing folding mechanism of an unmanned aerial vehicle. Background Art

[0002] According to the flight platform configuration, drones can be divided into fixed-wing drones, rotary-wing drones, unmanned airships, paraglider drones, flapping-wing drones, etc. Fixed-wing drones play an important role in agriculture, geology, meteorology, disaster relief and other fields, but fixed-wing drones have long wings, occupy a large space, and are easily damaged during transportation, making the storage and transportation of drones inconvenient.

[0003] To solve this problem, folding-wing drones came into being. The folded drone is compact in size, which can effectively reduce the space occupied during transportation, launch, and delivery, and is convenient for transfer and deployment between different locations. For example, it can be quickly transported to a designated area during military operations; in the civilian field, it is easy to carry into complex terrain or space-constrained work sites. It can be adapted to a variety of launch platforms and methods, such as canister launch and aerial delivery, which increases the flexibility of use and tactical diversity. For example, in military missions, the appropriate launch method can be selected according to different combat environments and mission requirements; in some special civilian scenarios, such as monitoring operations in narrow spaces, the appropriate launch method can be selected to ensure that the drone takes off smoothly. The innovative folding mechanism design ensures that the wings are stable and reliable during the folding and unfolding process, and can quickly complete the state transition.

[0004] Tandem fixed wing is a special wing layout, which is particularly common in UAVs, especially tandem wing UAVs. This type of UAV usually has a front wing and a rear wing. The front wing is responsible for providing stability and control, and the rear wing is responsible for the main lift and propulsion. This layout enables the UAV to have better flight performance and stability in complex environments and is suitable for various mission requirements. Compared with the upper and lower double wings, the size and shape of the two wings of the tandem wing are relatively free. The front and rear wings can be pulled apart to reduce the adverse aerodynamic interference between the two wings, or they can be pulled closer to consciously utilize the lift-enhancing effect.

[0005] In the prior art, when the folding mechanism is unfolded and assembled on a drone, if the dihedral angles of the left and right wings are different, the lateral stability of the drone is affected, and the stall characteristics and wind resistance are affected. In addition, when the two wings are in the folded state, the two wings are tied with a strap, which is not only time-consuming, but also has the risk of failure of the strap, and the wings are easily damaged when they automatically pop open. Summary of the invention

[0006] In view of this, the present invention aims to provide a wing folding mechanism for a UAV, so as to ensure a constant dihedral angle when the wing is unfolded, and stability when the wing is folded.

[0007] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0008] A wing folding mechanism for a drone comprises a fixed shaft connected to the drone, a left wing and a right wing sleeved on the fixed shaft, a first embedded part arranged in the left wing, a second embedded part arranged in the right wing, a torsion spring sleeved on the outside of the fixed shaft, and a limit block connected to the fixed shaft;

[0009] The first embedded part and the second embedded part are both sleeved on the outside of the fixed shaft; one end of the torsion spring is connected to the first embedded part, and the other end is connected to the second embedded part;

[0010] The limit block is provided with protrusions on both sides, and the left wing and the right wing are respectively provided with matching parts. When the folding mechanism is in the unfolded state, the left wing and the right wing are in a straight line relative to the fixed axis, and the matching parts abut against the protrusions on both sides;

[0011] The limit block is provided with a locking assembly, and the left wing and the right wing are provided with locking grooves;

[0012] The locking assembly includes a locking tongue telescopically connected to the limit block; when the left wing and the right wing are driven to overlap up and down, the wings of the drone are in a retracted state, and the locking tongue moves toward the locking groove and is engaged.

[0013] Furthermore, the limit block includes a horizontal plate and a vertical plate connected vertically;

[0014] The transverse plate is provided with a first mounting portion for connecting the fixed shaft;

[0015] The protrusions are arranged on both sides of the vertical plate, and the protrusions are sharp corners protruding toward the fixed axis direction.

[0016] Furthermore, the protrusion includes an arc segment and an inclined surface segment, and the connection between the arc segment and the inclined surface segment forms the sharp angle.

[0017] Further, the locking assembly includes a body connected to the vertical plate, and an elastic member connected between the body and the locking tongue;

[0018] One end of the locking tongue is inserted through the vertical plate, and the other end is arranged in the cavity of the body;

[0019] A pressing piece is provided on the upper part of the lock tongue and slides along the height direction of the vertical plate. A push-up inclined surface is formed on the lock tongue, and a matching inclined surface matched with the push-up inclined surface is provided on the pressing piece.

[0020] When the pressing member is driven downward, the matching inclined surface abuts against the pushing inclined surface to drive the locking tongue away from the locking groove to disengage the left wing and the right wing, the wings of the UAV are in an unfolded state, and the elastic member is squeezed to store energy.

[0021] Furthermore, an anti-slip piece is connected above the main body, the upper part of the pressing piece passes through the anti-slip piece, and the lower part of the pressing piece is provided with step portions protruding to both sides thereof. When the pressing piece moves upward, the step portions abut against the anti-slip piece to limit the pressing piece from slipping out of the main body.

[0022] Furthermore, a first pad is provided between the first embedded part and the second embedded part, and a second pad is provided at the lower end of the second embedded part;

[0023] A first gap is formed between the left wing and the right wing, and a second gap is formed between the right wing and the limiting block.

[0024] Furthermore, the first embedded part includes a first annular frame sleeved on the outside of the fixed shaft, a first annular member connected to the outside of the first annular frame, and a first flange provided at the bottom of the annular member;

[0025] The second embedded part includes a second annular frame sleeved on the outside of the fixed shaft, a second annular member connected to the outside of the second annular frame, and a second flange provided at the bottom of the annular member;

[0026] The thickness of the first annular frame is smaller than that of the first annular member, and the thickness of the second annular member is smaller than that of the second annular member.

[0027] Furthermore, the first embedded part is provided with a first opening groove opening downward, the second embedded part is provided with a second opening groove opening upward, the first opening groove and the second opening groove are buckled to form an annular accommodation cavity, and the torsion spring is arranged in the accommodation cavity;

[0028] The first annular member is provided with a first long groove, and the second annular member is provided with a second long groove;

[0029] One end of the torsion spring is clamped in the first long slot, and the other end of the torsion spring is clamped in the second long slot.

[0030] Furthermore, the first annular member is provided with a first flange protruding in the radial direction, and the first flange is provided with a second mounting portion;

[0031] The second annular member is provided with a plurality of second flanges protruding in the radial direction, and the second flange is provided with a third mounting portion;

[0032] The second flange is also provided with a plurality of adjustment grooves evenly distributed around the circumference, and the second mounting portion is respectively connected to the third mounting portion or the adjustment grooves via bolts.

[0033] Furthermore, a circular arc recessed portion sunken toward the inner cavity of the left wing is provided at the bottom of the first flange, and a boss abutting against the circular arc recessed portion is formed on the left wing, and the shape of the boss is adapted to the circular arc recessed portion.

[0034] Compared with the prior art, the present invention has the following advantages:

[0035] The wing folding mechanism of the unmanned aerial vehicle of the present invention is connected to a limited position block on a fixed axis. When the folding mechanism is in an unfolded state, the left wing and the right wing are unfolded in a straight line, and the mating part abuts against the protruding part, and the upper dihedral angles of the left wing and the right wing are made uniform by the elastic force of the torsion spring, so that there is no need to check and adjust the upper dihedral angle when the wing is installed on the unmanned aerial vehicle, thereby improving the convenience of installation. At the same time, by providing a locking groove on the left wing and the right wing, and providing a locking assembly on the limit block, by driving the left wing and the right wing to fold, the locking tongue is clamped in the locking groove, thereby achieving locking in the retracted state, improving the stability of the retracted state, and avoiding damage to the wing due to binding or ejection.

[0036] In addition, by providing the protruding portion with an arc segment and an inclined surface segment, the arc segment is used to avoid interference between the left wing and the right wing when they rotate. By providing the first pad and the second pad, a first gap is formed between the left wing and the right wing, and a second gap is formed between the right wing and the limit block, thereby avoiding friction between the left wing and the right wing during folding or unfolding, reducing the friction area, and improving the smoothness of movement. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0038] Figure 1 It is a schematic diagram of the three-dimensional structure of the wing folding mechanism of the UAV according to an embodiment of the present invention in a folded state;

[0039] Figure 2 It is a schematic diagram of the three-dimensional structure of the wing folding mechanism of the UAV according to an embodiment of the present invention in an unfolded state;

[0040] Figure 3 It is a top view schematic diagram of the wing folding mechanism of the UAV according to an embodiment of the present invention in an unfolded state;

[0041] Figure 4 for Figure 3 Schematic cross-sectional view at AA in the middle;

[0042] Figure 5 for Figure 1 A partial enlarged view of point I in the middle;

[0043] Figure 6 for Figure 2 A partial enlarged view of point E in the middle;

[0044] Figure 7 This is a three-dimensional structural view of the limit block according to an embodiment of the present invention;

[0045] Figure 8 for Figure 4 A partial enlarged view of position II in the middle;

[0046] Fig. 9 It is a partial schematic diagram of the left wing according to an embodiment of the present invention;

[0047] Fig.10 A schematic diagram of the three-dimensional structure of the first embedded component according to an embodiment of the present invention from a first viewing angle;

[0048] Fig.11 A schematic diagram of the three-dimensional structure of the first embedded component according to an embodiment of the present invention from a second viewing angle;

[0049] Fig.12 A schematic diagram of the three-dimensional structure of the second embedded component according to an embodiment of the present invention from a first viewing angle;

[0050] Fig.13 A schematic diagram of the three-dimensional structure of the second perspective of the second embedded member according to an embodiment of the present invention;

[0051] Fig.14 It is a schematic diagram of the three-dimensional structure of the pressing member according to an embodiment of the present invention.

[0052] Description of reference numerals:

[0053] 1. Fixed axis; 2. Left wing; 3. Right wing; 4. First embedded part; 5. Second embedded part; 6. Torsion spring; 7. Limit block; 8. Locking assembly; 10. Accommodating cavity; 11. First pad; 12. Second pad; 13. Fixed ring;

[0054] 201, matching portion; 202, locking groove; 203, boss;

[0055] 401, first annular frame; 402, first annular member; 403, first flange; 404, first opening groove; 405, first flange; 406, second mounting portion;

[0056] 501, second annular frame; 502, second annular member; 503, second flange; 504, second opening groove; 505, second flange; 506, third mounting portion; 507, adjustment groove;

[0057] 701, protruding portion; 702, horizontal plate; 703, vertical plate; 704, first mounting portion;

[0058] 801, locking tongue; 802, body; 803, elastic member; 804, pressing member; 805, anti-dropping member;

[0059] 4021, first long groove;

[0060] 4031, arc recessed portion;

[0061] 5021, the second long groove;

[0062] 7011, arc segment; 7012, inclined segment;

[0063] 8011, push ramp;

[0064] 8041, matching bevel; 8042, step portion. DETAILED DESCRIPTION

[0065] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0066] In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "upper", "lower", "inner", "back", etc. are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0067] In addition, in the description of the present invention, unless otherwise clearly defined, the terms "installed", "connected", "connected", and "connector" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood in combination with specific circumstances.

[0068] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0069] This embodiment relates to a wing folding mechanism for a drone, as a whole, Figures 1 to 4 As shown, the wing folding mechanism of the UAV includes a fixed shaft 1 connected to the UAV, a left wing 2 and a right wing 3 sleeved on the fixed shaft 1, a first embedded part 4 arranged in the left wing 2, a second embedded part 5 arranged in the right wing 3, a torsion spring 6 sleeved on the outside of the fixed shaft 1, and a limit block 7 connected to the fixed shaft 1. The first embedded part 4 and the second embedded part 5 are both sleeved on the outside of the fixed shaft 1; one end of the torsion spring 6 is connected to the first embedded part 4, and the other end is connected to the second embedded part 5.

[0070] Among them, the two sides of the limit block 7 are provided with protrusions 701, and the left wing 2 and the right wing 3 are respectively provided with matching parts 201. When the folding mechanism is in the unfolded state, the left wing 2 and the right wing 3 are in a straight line relative to the fixed axis 1, and the matching parts 201 abut against the protrusions 701 on both sides. The limit block 7 is provided with a locking assembly 8, and the left wing 2 and the right wing 3 are provided with locking grooves 202. The locking assembly 8 includes a locking tongue 801 telescopically connected to the limit block 7; when the left wing 2 and the right wing 3 are driven to overlap up and down, the wings of the drone are in a retracted state, and the locking tongue 801 is clamped in the locking groove 202.

[0071] The drone wing folding mechanism of this embodiment is connected to the limit block 7 on the fixed axis 1. When the folding mechanism is in the unfolded state, the left wing 2 and the right wing 3 are unfolded in a straight line, and the matching part 201 abuts against the protruding part 701, and the upper dihedral angles of the left wing 2 and the right wing 3 are made uniform by the elastic force of the torsion spring 6, so that there is no need to check and adjust the upper dihedral angle when the wing is installed on the drone, thereby improving the convenience of installation. At the same time, by setting a locking groove 202 on the left wing 2 and the right wing 3, and setting a locking assembly 8 on the limit block 7, by driving the left wing 2 and the right wing 3 to fold, the locking tongue 801 is clamped in the locking groove 202, thereby achieving locking in the retracted state, improving the stability of the retracted state, and avoiding damage to the wing due to binding or ejection.

[0072] Based on the above overall introduction, an exemplary structure of the drone folding mechanism of this embodiment is based on 1 to Figure 4 As shown, the left wing 2, the right wing 3, and the limit seat are arranged in sequence from top to bottom. When folding, the left wing 2 needs to be manually driven to rotate toward the right wing 3 until it rotates to the position shown in FIG. Figure 1 When the foldable device is in the folded state, the locking assembly 8 is pushed to slide to the side of the limiting block 7 so that the locking assembly 8 is engaged and fixed with the limiting block 7.

[0073] like Figures 5 to 7As shown, the limit block 7 includes a vertically connected horizontal plate 702 and a vertical plate 703, the horizontal plate 702 is provided with a first mounting portion 704 for connecting the fixed axis 1, and the protrusions 701 are provided on both sides of the vertical plate 703, and the protrusions 701 are sharp angles protruding toward the fixed axis 1. The horizontal plate 702 is provided with a threaded hole connected to the fixed axis 1, the bottom plate of the fixed axis 1 is provided below the limit plate, and the wing is connected to the drone through the fixed axis 1.

[0074] Furthermore, if Figure 7 As shown, the protrusion 701 includes an arc segment 7011 and an inclined surface segment 7012, and the connection between the arc segment 7011 and the inclined surface segment 7012 forms a sharp angle. Figure 7 and Fig. 9 As shown, the matching portion 201 and the locking groove 202 are both angular notches provided on the wing, and cooperate with the above-mentioned sharp corners. When the matching portion 201 abuts against the protruding portion 701, it can play a role in positioning the two wings. Due to the force of the torsion spring 6, the two wings are stably abutted against the limit block 7, thereby improving the stability of the two wings. In this embodiment, by providing the protruding portion 701 with an arc segment 7011 and a slope segment 7012, the arc segment 7011 is used to avoid interference when the left wing 2 and the right wing 3 rotate.

[0075] As a preferred implementation mode, Figures 1 to 5 As shown, the locking assembly 8 includes a body 802 connected to the vertical plate 703, and an elastic member 803 connected between the lock tongue 801 and the body 802. One end of the lock tongue 801 is inserted through the vertical plate 703, and the other end is set in the cavity of the body 802. A pressing member 804 is provided on the upper part of the lock tongue 801 to slide along the height direction of the vertical plate 703, and a push-up inclined surface 8011 is formed on the lock tongue 801. Fig.14 As described above, the pressing member 804 is provided with a matching inclined surface 8041 which matches the pushing inclined surface 8011 .

[0076] like Figures 1 to 5 As shown, when the pressing member 804 is driven to press down, the matching inclined surface 8041 abuts against the pushing inclined surface 8011 to drive the locking tongue 801 away from the locking groove 202 and disengage the left wing 2 and the right wing 3, and the wings of the drone are in an unfolded state, and the elastic member 803 squeezes and stores energy. When it is necessary to retract, the left wing 2 and the right wing 3 are manually rotated to the retracted state, and the locking tongue 801 is inserted into the locking groove 202 due to the release of energy of the elastic member 803, thereby achieving the locking of the left wing 2 and the right wing 3.

[0077] Furthermore, if Figures 1 to 5As shown, an anti-slip component 805 is also connected to the top of the main body 802, and the upper part of the pressing member 804 passes through the anti-slip component 805. The lower part of the pressing member 804 is provided with a step portion 8042 protruding to both sides thereof. When the pressing member 804 moves upward, the step portion 8042 abuts against the anti-slip component 805 to limit the pressing member 804 from slipping out of the main body 802.

[0078] like Figure 8 As shown, a first pad 11 is provided between the first embedded part 4 and the second embedded part 5, and a second pad 12 is provided at the lower end of the second embedded part 5. A first gap is formed between the left wing 2 and the right wing 3, and a second gap is formed between the right wing 3 and the stop block 7. By providing the first pad 11 and the second pad 12, a first gap is formed between the left wing 2 and the right wing 3, and a second gap is formed between the right wing 3 and the stop block 7, so as to avoid friction between the left wing 2 and the right wing 3 during folding or unfolding, reduce the friction area, and improve the smoothness of movement.

[0079] Preferably, if Figures 10 to 13 As shown, the first embedded part 4 includes a first annular frame 401 sleeved on the outside of the fixed shaft 1, a first annular member 402 connected to the outside of the first annular frame 401, and a first flange 403 provided at the bottom of the annular member. The second embedded part 5 includes a second annular frame 501 sleeved on the outside of the fixed shaft 1, a second annular member 502 connected to the outside of the second annular frame 501, and a second flange 503 provided at the bottom of the annular member. The thickness of the first annular frame 401 is less than that of the first annular member 402, and the thickness of the second annular member 502 is less than that of the second annular member 502.

[0080] In addition, Figures 10 to 13 As shown, the first embedded part 4 is provided with a first opening groove 404 opening downward, and the second embedded part 5 is provided with a second opening groove 504 opening upward. The first opening groove 404 and the second opening groove 504 are buckled into an annular accommodating cavity 10, and the torsion spring 6 is arranged in the accommodating cavity 10. The first annular part 402 is provided with a first long groove 4021, and the second annular part 502 is provided with a second long groove 5021. One end of the torsion spring 6 is clamped in the first long groove 4021, and the other end of the torsion spring 6 is clamped in the second long groove 5021.

[0081] Furthermore, if Figures 10 to 13 As shown, the first annular member 402 is provided with a first flange 405 protruding in the radial direction, the first flange 405 is provided with a second mounting portion 406, the second annular member 502 is provided with a plurality of second flanges 505 protruding in the radial direction, the second flange 505 is provided with a third mounting portion 506, the second flange 503 is also provided with a plurality of circumferentially evenly distributed adjusting grooves 507, and the third mounting portion 506 is respectively connected to the second mounting portion 406 or the adjusting groove 507 by bolts.

[0082] like Figures 10 to 13As shown, the second mounting portion 406 corresponds to the third mounting portion 506 at a different position, or the second mounting portion 406 corresponds to the adjustment slot 507, and the first embedded part 4 and the second embedded part 5 are connected by bolts to adjust the elastic force of the torsion spring 6, so as to meet the requirements of wings of different specifications and improve the versatility of the wing folding mechanism of the UAV.

[0083] like Fig. 9 and Fig.11 As shown, a circular arc recessed portion 4031 is provided at the bottom of the first flange 403, which is sunken toward the inner cavity of the left wing 2. A boss 203 is formed on the left wing 2 to abut against the circular arc recessed portion 4031, and the shape of the boss 203 is adapted to the circular arc recessed portion 4031. With such arrangement, when the left wing 2 is rotated and folded, the circular arc recessed portion 4031 abuts against the boss 203, thereby preventing the first embedded part 4 from being misaligned with the left wing 2 during rotation, thereby ensuring the folding effect of the folding mechanism.

[0084] Preferably, the first embedded part 4 and the second embedded part 5 are made of 7075 aviation aluminum alloy, and are respectively bonded and fixed to the left wing 2 and the right wing 3. The first pad 11 and the second pad 12 are made of polytetrafluoroethylene, because it has an extremely low friction coefficient and can remain stable in a high temperature environment, effectively reducing the wear of the first embedded part 4 and the second embedded part 5 and extending their service life.

[0085] In addition, if Figure 8 As shown, a fixing ring 13 is provided at the upper end of the fixed shaft 1, and the fixing ring 13 is fixed to the fixed shaft 1 by bolts. The upper end of the fixing ring 13 is flush with the right wing 3, so as to increase the overall sealing of the UAV wing.

[0086] During use, when the UAV is transferred from single-unit storage and transportation to the launcher, the pressing piece 804 is pressed downward to unlock the locking assembly 8, and the locking tongue 801 disengages from the overlapping area of ​​the locking grooves 202 of the left wing 2 and the right wing 3. The wingtips of the left and right wings contact the inner wall of the launcher under the action of the torsion spring 6. At this time, the locking grooves 202 of the left wing 2 and the right wing 3 are at a certain angle and do not overlap, so the locking tongue 801 cannot be connected, and the locking state is switched to the pre-deployment state.

[0087] When the UAV is launched, the UAV is quickly ejected from the launcher. At the moment when the wing tips are separated from the inner wall of the launcher, the left wing 2 and the right wing 3 are quickly unfolded into a straight line under the force of the torsion spring 6, and the pre-expanded state is switched to the fully expanded state.

[0088] When the UAV is recovered, the left wing 2 and the right wing 3 are folded in half until the locking groove 202 overlaps, and the locking tongue 801 pops out and enters the overlapping area of ​​the locking groove 202 under the action of the spring. The pressing member 804 is pushed by the locking tongue 801 to return to the locked position, and the fully expanded state is switched to the locked state.

[0089] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A wing folding mechanism for a drone, characterized in that: It comprises a fixed axis (1) connected to the unmanned aerial vehicle, a left wing (2) and a right wing (3) sleeved on the fixed axis (1), a first embedded part (4) arranged in the left wing (2), a second embedded part (5) arranged in the right wing (3), a torsion spring (6) sleeved on the outside of the fixed axis (1), and a limit block (7) connected to the fixed axis (1); The first embedded part (4) and the second embedded part (5) are both sleeved on the outside of the fixed shaft (1); one end of the torsion spring (6) is connected to the first embedded part (4), and the other end is connected to the second embedded part (5); The limit block (7) is provided with protruding portions (701) on both sides, and the left wing (2) and the right wing (3) are respectively provided with matching portions (201); when the folding mechanism is in an unfolded state, the left wing (2) and the right wing (3) are in a straight line shape relative to the fixed axis (1), and the matching portions (201) abut against the protruding portions (701) on both sides; The limit block (7) is provided with a locking assembly (8), and the left wing (2) and the right wing (3) are provided with locking grooves (202); The locking assembly (8) comprises a locking tongue (801) telescopically connected to the limit block (7); when the left wing (2) and the right wing (3) are driven to overlap up and down, the wings of the drone are in a retracted state, and the locking tongue (801) is engaged in the locking groove (202); The limit block (7) comprises a horizontal plate (702) and a vertical plate (703) which are vertically connected; The transverse plate (702) is provided with a first mounting portion (704) for connecting to the fixed shaft (1); The protrusions (701) are arranged on both sides of the vertical plate (703), and the protrusions (701) are sharp corners protruding in the direction of the fixed axis (1); The locking assembly (8) comprises a body (802) connected to the vertical plate (703), and an elastic member (803) connected between the body (802) and the locking tongue (801); One end of the locking tongue (801) is inserted through the vertical plate (703), and the other end is arranged in the cavity of the body (802); A pressing piece (804) is provided on the upper part of the lock tongue (801) and is slidable along the height direction of the vertical plate (703); a push-up inclined surface (8011) is formed on the lock tongue (801); and a matching inclined surface (8041) matching the push-up inclined surface is provided on the pressing piece (804); When the pressing member (804) is driven to be pressed downward, the matching inclined surface (8041) abuts against the pushing inclined surface (8011) to drive the locking tongue (801) away from the locking groove (202) and disengage the left wing (2) and the right wing (3), the wings of the UAV are in an unfolded state, and the elastic member (803) is squeezed to store energy; The protrusion (701) comprises a circular arc segment (7011) and a slope segment (7012), and the connection between the circular arc segment (7011) and the slope segment (7012) forms the sharp angle.

2. The UAV wing folding mechanism according to claim 1, characterized in that: An anti-slipping piece (805) is also connected to the top of the main body (802); the upper portion of the pressing piece (804) passes through the anti-slipping piece (805); and the lower portion of the pressing piece (804) is provided with step portions (8042) protruding toward both sides thereof; when the pressing piece (804) moves upward, the step portions (8042) abut against the anti-slipping piece (805) to prevent the pressing piece (804) from slipping out of the main body (802).

3. The drone wing folding mechanism according to claim 1, characterized in that: A first pad (11) is provided between the first embedded part (4) and the second embedded part (5), and a second pad (12) is provided at the lower end of the second embedded part (5); A first gap is formed between the left wing (2) and the right wing (3), and a second gap is formed between the right wing (3) and the limiting block (7).

4. The UAV wing folding mechanism according to claim 3 is characterized in that: The first embedded part (4) comprises a first annular frame (401) sleeved on the outside of the fixed shaft (1), a first annular part (402) connected to the outside of the first annular frame (401), and a first flange (403) provided at the bottom of the annular part; The second embedded part (5) comprises a second annular frame (501) sleeved on the outside of the fixed shaft (1), a second annular part (502) connected to the outside of the second annular frame (501), and a second flange (503) provided at the bottom of the annular part; The thickness of the first annular frame (401) is smaller than that of the first annular member (402), and the thickness of the second annular member (502) is smaller than that of the second annular member (502).

5. The UAV wing folding mechanism according to claim 4, characterized in that: The first embedded part (4) is provided with a first opening groove (404) opening downwards, and the second embedded part (5) is provided with a second opening groove (504) opening upwards, the first opening groove (404) and the second opening groove (504) are buckled together to form an annular accommodating cavity (10), and the torsion spring (6) is arranged in the accommodating cavity (10); The first annular member (402) is provided with a first long groove (4021), and the second annular member (502) is provided with a second long groove (5021); One end of the torsion spring (6) is clamped in the first long slot (4021), and the other end of the torsion spring (6) is clamped in the second long slot (5021).

6. The drone wing folding mechanism according to claim 5, characterized in that: The first annular member (402) is provided with a first flange (405) protruding in the radial direction, and the first flange (405) is provided with a second mounting portion (406); The second annular member (502) is provided with a plurality of second flanges (505) protruding in the radial direction, and the second flanges (505) are provided with a third mounting portion (506); The second flange (503) is also provided with a plurality of adjustment grooves (507) evenly distributed around the circumference, and the second mounting portion (406) is respectively connected to the third mounting portion (506) or the adjustment grooves (507) via bolts.

7. The UAV wing folding mechanism according to claim 6, characterized in that: A circular arc recessed portion (4031) is provided at the bottom of the first flange (403) and is sunken toward the inner cavity of the left wing (2). A boss (203) is formed on the left wing (2) and abuts against the circular arc recessed portion (4031). The shape of the boss (203) is adapted to match the circular arc recessed portion (4031).

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