UAV wing limiting mechanism, UAV wing and UAV

Abstract

This application discloses a drone wing limiting mechanism, a drone wing, and a drone, belonging to the field of drone wings. The limiting mechanism includes at least two limiting seats; the limiting seats include a fixing plate and a limiting plate, with the limiting plate disposed perpendicularly to the fixing plate; the fixing plate of one limiting seat is fixed to the outer wall of the drone's first wing rotating shaft, and the fixing plate of the other limiting seat is fixed to the outer wall of the drone's second wing rotating shaft; the projections of one limiting plate and the other limiting plate on a vertical plane overlap; when the first and second wing rotating shafts rotate to fully deploy the wings, at least portions of the outer surfaces of the two limiting plates abut against each other. This application can effectively and timely prevent excessive wing deployment.

Description

Technical Field

[0001] The present application relates to the technical field of drone wings, and in particular to a drone wing limiting mechanism, a drone wing, and a drone. Background Art

[0002] A drone is an unmanned aircraft that is controlled by a radio remote control device and a self-contained program control device, or is operated completely or intermittently autonomously by an onboard computer. Currently, drones with retractable wings are widely used.

[0003] Existing large-scale retractable-wing drones use a motor to drive a rack or steel cable to deploy the wings. This mechanism relies on the number of motor revolutions to control wing extension, requiring high control requirements. Even the slightest error can cause the wings to over-expand. Summary of the Invention

[0004] The embodiments of the present application provide a drone wing limiting mechanism, a drone wing, and a drone, which can solve the problem that the existing drone wing deployment and extension mechanism relies on the number of motor rotations to control wing deployment, which has high control requirements and a slight error will cause the wings to be over-deployed.

[0005] In the first aspect, an embodiment of the present invention provides a wing limiting mechanism for a UAV, comprising at least two limiting seats; the limiting seat comprises a fixed plate and a limiting plate, and the limiting plate is vertically arranged on the fixed plate; the fixed plate of one limiting seat is fixed to the outer wall of the first wing rotating shaft of the UAV, and the fixed plate of the other limiting seat is fixed to the outer wall of the second wing rotating shaft of the UAV; the projections of one limiting plate and the other limiting plate on the vertical plane overlap; when the first wing rotating shaft and the second wing rotating shaft are rotated to unfold the wings into place, at least part of the outer surfaces of the two limiting plates are offset against each other.

[0006] In combination with the first aspect, in a possible implementation, the drone wing limiting mechanism further includes a latch and a cable; the latch includes a first pin and a second pin, and one end of the first pin is connected to the second pin; the limiting plate is provided with a mounting plate in parallel on the opposite side of the wing deployment direction, the limiting plate is at a preset distance from the mounting plate, and two pin holes are provided on the mounting plate and the limiting plate, and the positions of the two pin holes on the mounting plate correspond to the positions of the two pin holes on the limiting plate respectively; the first pin and the second pin are inserted into the relative positions on the limiting plate via the pin holes provided on the mounting plate. corresponding pin holes, and the difference between the length of the first pin and the length of the second pin is greater than the sum of the thickness of the limit plate and the preset distance; when the pins are inserted on the limit seats fixed on the first wing rotating shaft and the second wing rotating shaft, the parts of the second pins of the two pins located between the preset distances are respectively connected to a cable, and the other ends of the two cables are respectively connected to the first outer section of the wing and the second outer section of the wing; the limit plate area on the other limit seat corresponding to the first pin inserted on the limit seat, at least a part of the area is against the front end of the first pin during the wing expansion process.

[0007] In combination with the first aspect, in a possible implementation, the cross-sectional shape of the first pin and the second pin includes a closed figure composed of at least one of a line segment and a curve.

[0008] In combination with the first aspect, in a possible implementation, the latch further includes a connecting plate; and one end of the first pin and one end of the second pin are connected via the connecting plate.

[0009] In combination with the first aspect, in a possible implementation, the UAV wing limiting mechanism also includes a baffle; the baffle is arranged on the side of the mounting plate away from the limiting plate, and when the pin is inserted into the limiting seat, it is used to press the pin to prevent the pin from falling off.

[0010] In combination with the first aspect, in a possible implementation, the area occupied by the pin hole covers the cross-sectional area of ​​the corresponding pin.

[0011] In combination with the first aspect, in a possible implementation, the limiting plate is provided at an edge of the fixing plate on one side in the deployment direction of the wing on which the limiting plate is located.

[0012] In combination with the first aspect, in a possible implementation, at least one of the limit plates is provided with a contact sensor on the side for abutting against each other, for generating a signal to control a servo that drives the wing to rotate when the two limit plates are in contact.

[0013] In a second aspect, another embodiment of the present invention provides a UAV wing, comprising the UAV wing limiting mechanism described above.

[0014] In a third aspect, another embodiment of the present invention provides a drone, comprising the drone wing limiting mechanism described above.

[0015] One or more technical solutions provided in the embodiments of the present invention have at least the following technical effects or advantages:

[0016] An embodiment of the present invention provides a wing limiting mechanism for a drone, comprising at least two limiting seats. The limiting seats comprise a fixed plate and a limiting plate, wherein the limiting plate is disposed perpendicularly to the fixed plate. The fixed plate of one limiting seat is fixed to the outer wall of the first wing rotating shaft of the drone, while the fixed plate of the other limiting seat is fixed to the outer wall of the second wing rotating shaft of the drone. The projections of one limiting plate and the other limiting plate on a vertical plane overlap. When the first wing rotating shaft and the second wing rotating shaft rotate to unfold the wings, at least portions of the outer surfaces of the two limiting plates abut against each other.

[0017] The drone wing limit mechanism provided in an embodiment of the present invention comprises a limit seat disposed on each of the first and second wing shafts. When the first and second outer wing sections are deployed, the first and second wing shafts rotate, respectively, and the spacing between the outer surfaces of the limit plates of the two limit seats disposed thereon gradually decreases. When the outer surfaces of the two limit plates abut against each other, the first and second wing shafts become stuck and no longer rotate, causing the motor current to increase, causing the motor to self-limit and stop operating. At this point, the drone's wings are fully deployed. Compared to existing drones, especially large, retractable-wing drones, whose wing deployment and extension mechanisms use motors to drive racks or cables for deployment, these mechanisms rely on the number of motor rotations to control wing deployment, requiring high control requirements. Even the slightest error can cause the wings to over-deploy. The drone wing limit mechanism of the present application allows the wings to fully deploy when the outer surfaces of the limit plates of the two limit seats abut against each other, effectively preventing over-deployment of the wings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0019] Figure 1 A schematic diagram of the structure of the limit seat provided in an embodiment of the present application;

[0020] Figure 2A schematic diagram of the structure of the first outer wing and the second outer wing in the folded state provided in an embodiment of the present application;

[0021] Figure 3 A schematic diagram of the structure of the first outer wing and the second outer wing provided in an embodiment of the present application before they are fully deployed;

[0022] Figure 4 This is a schematic diagram of the structure of the first outer wing and the second outer wing provided in an embodiment of the present application when they are fully deployed.

[0023] Icons: 1-limit seat; 11-fixing plate; 12-limit plate; 13-mounting plate; 14-pin hole; 2-latch pin; 21-first pin; 22-second pin; 23-connecting plate; 3-cable; 4-blocking plate; 5-first wing shaft; 6-second wing shaft; 7-first outer section wing; 8-second outer section wing; d-thickness; m-preset distance. DETAILED DESCRIPTION

[0024] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0025] In the description of the embodiments of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. The terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance. In addition, the terms "installed", "connected" and "connected" 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 an indirect connection through an intermediate medium, or it can be a communication between the internal parts of two components. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present invention can be understood according to the specific circumstances.

[0026] The UAV wing limiting mechanism provided by the present invention is applicable to UAVs whose wings need to be unfolded, and is illustratively applicable to large UAVs with unfolded retractable wings.

[0027] Please refer to Figures 1 to 4As shown, the UAV wing limiting mechanism provided by the embodiment of the present invention includes at least two limiting seats 1. The limiting seat 1 includes a fixing plate 11 and a limiting plate 12, and the limiting plate 12 is vertically arranged on the fixing plate 11.

[0028] like Figures 2 to 4 As shown, a fixing plate 11 of a limiting seat 1 is fixed to the outer side wall of the first wing shaft 5 of the UAV. Furthermore, the first outer wing 7 and the limiting seat 1 are relatively arranged on the outer side wall of the first wing shaft 5. Specifically, the first outer wing 7 has an arc-shaped mounting surface for mounting the first outer wing 7 on the first wing shaft 5. The outer surface of the limiting plate 12 of the limiting seat 1 has a projection line on the first wing shaft 5, and the radial midline of the arc-shaped surface is opposite to the projection line. Figure 1 As shown, two fixing holes are provided above the fixing plate 11 , and the fixing plate 11 is fixed to the first wing shaft 5 through the fixing holes and bolts.

[0029] Continue to refer to Figures 2 to 4 The fixing plate 11 of the other stopper 1 is fixed to the outer sidewall of the drone's second wing shaft 6. Furthermore, the second outer wing 8 and the stopper 1 are located on the same side of the second wing shaft 6. Specifically, the second outer wing 8 has a curved mounting surface for attaching it to the second wing shaft 6. The outer surface of the stopper plate 12 of the stopper 1 has a projection line on the second wing shaft 6, and the radial midline of this curved surface is aligned with this projection line.

[0030] The projections of one limiting plate 12 and another limiting plate 12 on the vertical plane overlap. Figure 3 As shown, the vertical plane refers to the XOZ plane or the YOZ plane. When the first wing shaft 5 and the second wing shaft 6 rotate to unfold the wings, at least part of the outer surfaces of the two limiting plates 12 abut against each other.

[0031] The drone wing limiting mechanism provided by the present invention comprises a limiting seat 1 disposed on each of the first and second wing shafts 5 and 6. When the first and second outer wing sections 7 and 8 are deployed, the first and second wing shafts 5 and 6 rotate, respectively, and the distance between the outer surfaces of the limiting plates 12 of the two limiting seats 1 disposed thereon gradually decreases. When the outer surfaces of the two limiting plates 12 abut against each other, the first and second wing shafts 5 and 6 become stuck and no longer rotate, increasing the motor current. The motors automatically limit their current and stop operating, effectively allowing the drone's wings to fully deploy. This is in contrast to existing drones, particularly large drones with retractable wings, whose wing deployment and extension mechanisms utilize motors to drive racks or cables for deployment. These mechanisms rely on the number of motor rotations to control wing deployment, requiring high control requirements. Even the slightest error can cause the wings to over-deploy. The drone wing limiting mechanism of the present invention effectively prevents over-deployment by effectively preventing the wings from over-deploying when the outer surfaces of the limiting plates 12 of the two limiting seats 1 abut against each other.

[0032] Continue to refer to Figures 1 to 4 As shown, the UAV wing limiting mechanism also includes a latch 2 and a cable 3. The cable 3 can be a pull rope, an iron chain, etc. The latch 2 includes a first pin 21 and a second pin 22, and one end of the first pin 21 and the second pin 22 are connected. The limiting plate 12 is provided with a mounting plate 13 in parallel on the opposite side of the wing deployment direction. The limiting plate 12 is separated from the mounting plate 13 by a preset distance m, and two pin holes 14 are provided on the mounting plate 13 and the limiting plate 12. The positions of the two pin holes 14 on the mounting plate 13 correspond to the positions of the two pin holes 14 on the limiting plate 12. Generally, in order to facilitate production, such as Figure 1 As shown, a groove is cut into a block to form a mounting plate 13 and a limiting plate 12. The lower ends of the mounting plate 13 and the limiting plate 12 are integrally connected, making the mounting plate 13 and the limiting plate 12 more stable. At the same time, in order to ensure the structural firmness, the mounting plate 13, the limiting plate 12 and the fixing plate 11 are also integrally formed.

[0033] The first pin 21 and the second pin 22 penetrate the corresponding pin holes 14 on the limit plate 12 through the pin holes 14 provided on the mounting plate 13, and the difference between the lengths of the first pin 21 and the second pin 22 is greater than the sum of the thickness d of the limit plate 12 and the preset distance m. When the latches 2 are inserted into the limit seats 1 fixed to the first wing shaft 5 and the second wing shaft 6, the portions of the second pins 22 of the two latches 2 located between the preset distance m are connected to a cable 3, respectively. The other ends of the two cables 3 are connected to the first outer wing 7 and the second outer wing 8, respectively. During the wing deployment process, at least a portion of the area of ​​the limit plate 12 on the other limit seat 1 corresponding to the first pin 21 inserted into the limit seat 1 abuts against the front end of the first pin 21. Therefore, when the outer surfaces of the limit plates 12 of the two limit seats 1 abut against each other, the front end of the first pin 21 is flush with the outer surface of the limit plate 12, and the front end of the second pin 22 withdraws from the gap between the preset distance m. Since one end of the cable 3 is connected to the second pin 22 between the preset distance m, it can ensure that when the first outer section wing 7 and the second outer section wing 8 are unfolded into place, the cable 3 can be quickly disengaged from the second pin 22.

[0034] Optional, such as Figure 3 As shown, the height of the limit plate 12 is consistent with the height of the fixed plate 11. In practice, in order to make the limit seat 1 more convenient to process, a limit seat 1 with the same structure is set on the first wing shaft 5 and the second wing shaft 6. Figure 3 As shown, since the position of the limit seat 1 arranged on the first wing rotating shaft 5 is higher than the position of the limit seat 1 arranged on the second wing rotating shaft 6, when the height of the limit plate 12 is consistent with the height of the fixing plate 11, especially the height of the limit plate 12 of the limit seat 1 arranged on the second wing rotating shaft 6 is consistent with the height of the fixing plate 11, it can be ensured that during the rotation of the second wing rotating shaft 6 and the first wing rotating shaft 5, the front end of the latch 2 on the first wing rotating shaft 5 can abut against the outer surface of the limit plate 12 of the limit seat 1 on the second wing rotating shaft 6, and will not hit the air, so that the latch 2 on the first wing rotating shaft 5 can be more smoothly and accurately disengaged.

[0035] In practice, the first outer wing 7 and the second outer wing 8 of the UAV are prone to freely extend during the deployment process, which will increase the torque required for deployment and cause the wing deployment and extension mechanism to get stuck. The first outer wing 7 and the second outer wing 8 cannot be deployed. In actual applications, the reliability is low and it cannot be widely used.

[0036] The drone wing limiting mechanism provided in an embodiment of the present invention connects the first outer wing 7 and the second outer wing 8 to their corresponding second pins 22 respectively through a cable 3. During the deployment of the first outer wing 7 and the second outer wing 8, the pin 2 does not move, the position of the cable 3 is locked, and the first outer wing 7 and the second outer wing 8 cannot be extended at will. When the first outer section wing 7 and the second outer section wing 8 are unfolded into place, the two limit plates 12 corresponding to them reach a state of outer surfaces abutting each other, and the pin 2 set on the limit seat 1 continuously moves from the direction of the limit plate 12 to the direction of the mounting plate 13 until the front end face of the first pin 21 is flush with the outer surface of the limit plate 12. Since the difference between the length of the first pin 21 and the length of the second pin 22 is greater than the sum of the thickness d of the limit plate 12 and the preset distance m, the cable 3 is connected to the position of the second pin 22 located between the preset distance m, and the cable 3 is detached from the second pin 22, and the first outer section wing 7 and the second outer section wing 8 can be extended, so that the limiting mechanism realizes the extension limit and unlocking of the first outer section wing 7 and the second outer section wing 8.

[0037] The UAV wing limiting mechanism provided in the embodiment of the present invention can effectively prevent the first outer wing 7 and the second outer wing 8 from over-expanding, and can also prevent the first outer wing 7 and the second outer wing 8 from freely extending during the expansion process, thereby improving the reliability of wing expansion. The structure is simple and reliable, and no additional motors or pyrotechnics are required for actuation and unlocking, which can reduce control logic and save costs.

[0038] Furthermore, if Figure 1 As shown, the cross-sectional shape of the first pin 21 and the second pin 22 includes a closed figure composed of at least one of a line segment and a curve. For example, the cross-sectional shape of the first pin 21 and the second pin 22 can be circular, triangular, or rectangular, and correspondingly, the first pin 21 and the second pin 22 can be cylindrical, triangular, or quadrangular.

[0039] Optional, such as Figure 1 As shown, the first and second pins 21, 22 have rectangular cross-sections with chamfered corners. The rectangular cross-sections of the first and second pins 21, 22 are easier to machine, and their longer cross-sections provide a larger contact surface with the pinhole 14. This ensures a more secure insertion of the latch 2 into the pinhole 14, and a more stable movement rate.

[0040] Continue to refer to Figure 1 As shown, the latch 2 also includes a connecting plate 23. The first pin 21 and the second pin 22 are connected at one end by the connecting plate 23. The connecting plate 23 allows the bottom surface of the gap at the junction of the first pin 21 and the second pin 22 to be flat. When the latch 2 is inserted into the retaining seat 1, the latch 2 fits better with the outer surface of the mounting surface and is less likely to fall off.

[0041] like Figure 2 As shown, the UAV wing limiting mechanism further includes a baffle 4. The baffle 4 is arranged on the side of the mounting plate 13 away from the limiting plate 12, and is used to press the pin 2 when the pin 2 is inserted into the limiting seat 1 to prevent the pin 2 from falling off.

[0042] In practice, since the stopper 1 is used in drones, its safety must be enhanced. When the first and second outer wings 7, 8 are deployed, the first and second wing shafts 5, 6 rotate, causing the latch 2 to continuously move until it is ejected. To facilitate the movement of the latch 2, a gap is preferably provided between the latch 2 and the pinhole 14. However, during drone operation, the latch 2 must be prevented from falling out. The baffle 4 is designed to support the latch 2 before it moves, preventing it from falling out. Of course, the baffle 4 is designed to be relatively thin. When the latch 2 needs to move, the front end of the latch 2 receives a thrust, which pushes the baffle 4 at the rear end out, preventing the latch 2 from restricting its movement. When the outer surfaces of the two stopper plates 12 of the stopper 1 abut against each other, the baffle 4 is deformed but remains fixed to the mounting plate 13, thus preventing the ejected latch 2 from falling out. One end of the first pin 21 and the second pin 22 are connected via a connecting plate 23 . The arrangement of the connecting plate 23 also facilitates the arrangement of the blocking piece 4 .

[0043] The area occupied by the pin hole 14 covers the cross-sectional area of ​​the corresponding pin, so that the first pin 21 and the second pin 22 can be more firmly arranged on the limit seat 1.

[0044] The limiting plate 12 is arranged at the edge of the fixed plate 11 on one side in the expansion direction of the wing, thereby reducing the surface area of ​​the limiting plate 12 and further reducing the weight of the limiting plate 12. At the same time, it can also make the contact surface larger during the limiting process and make the wing expansion control more precise. In addition, if Figure 1 As shown, in practice, in order to set the fixing hole, the surface area of ​​the fixing plate 11 is larger, and the limiting plate 12 is set at the edge of one side of the fixing plate 11. The opposite side of the fixing plate 11 where the limiting plate 12 is set can be beveled at an angle to reduce the weight of the limiting seat 1.

[0045] The drone wing limiting mechanism has at least one limiting plate 12 provided with a contact sensor on the side for abutting against each other, which is used to generate a signal when the two limiting plates 12 contact to control the servo that drives the wing to rotate, thereby making the position control of the wing deployment more precise and sensitive.

[0046] Another embodiment of the present invention provides a drone wing including the aforementioned drone wing limiting mechanism. Due to the aforementioned drone wing limiting mechanism, the drone wing effectively prevents the first and second outer wing sections 7, 8 from over-expanding and prevents the first and second outer wing sections 7, 8 from freely extending during deployment. This improves the reliability of wing deployment, provides a simple and reliable structure, and eliminates the need for additional motors or pyrotechnics for actuation and unlocking, thereby reducing control logic and saving costs.

[0047] Yet another embodiment of the present invention provides a UAV, comprising the UAV wing limiting mechanism described above.

[0048] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referenced to each other. Each embodiment focuses on the differences from other embodiments.

[0049] The above embodiments are intended only to illustrate the technical solutions of this application and are not intended to limit this application. Although this application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they may modify the technical solutions described in the aforementioned embodiments or replace some or all of the technical features therein with equivalents. Such modifications or replacements do not deviate from the essence of the corresponding technical solutions within the scope of this application.

Claims

1. A wing limiting mechanism for a UAV, characterized in that: Includes at least two limit seats; The limiting seat includes a fixed plate and a limiting plate, and the limiting plate is vertically arranged on the fixed plate; The fixing plate of one of the limit seats is fixed to the outer side wall of the first wing shaft of the drone, and the fixing plate of the other limit seat is fixed to the outer side wall of the second wing shaft of the drone; The projections of one limiting plate and another limiting plate on the vertical plane overlap; When the first wing rotating shaft and the second wing rotating shaft rotate to unfold the wings, at least parts of the outer surfaces of the two limiting plates abut against each other; Also includes latches and cables; When the latches are inserted into the limit seats fixed on the first wing rotating shaft and the second wing rotating shaft, the two latches are respectively connected to one of the cables, and the other ends of the two cables are respectively connected to the first outer wing section and the second outer wing section; The latch is used to limit the free extension of the first outer wing and the second outer wing during the wing deployment process, and to release the restriction on the first outer wing and the second outer wing when the limit plates abut against each other.

2. The UAV wing limiting mechanism according to claim 1, characterized in that: The latch includes a first pin and a second pin, and one end of the first pin is connected to one end of the second pin; The limiting plate is provided with a mounting plate in parallel on the side opposite to the wing deployment direction, the limiting plate is spaced a preset distance from the mounting plate, and both the mounting plate and the limiting plate are provided with two pin holes, the positions of the two pin holes on the mounting plate respectively corresponding to the positions of the two pin holes on the limiting plate; The first pin and the second pin are inserted into corresponding pin holes on the limiting plate through pin holes provided on the mounting plate, and the difference between the length of the first pin and the length of the second pin is greater than the sum of the thickness of the limiting plate and the preset distance; When the latches are inserted into the limit seats fixed on the first wing rotating shaft and the second wing rotating shaft, the second pins of the two latches are respectively connected to one of the cables at the locations between the preset distances; At least a portion of the limiting plate area on the other limiting seat corresponding to the first pin inserted on the limiting seat abuts against the front end of the first pin during the wing unfolding process.

3. The UAV wing limiting mechanism according to claim 2, characterized in that: The cross-sectional shapes of the first pin and the second pin include closed figures composed of at least one of line segments and curves.

4. The UAV wing limiting mechanism according to claim 2 or 3, characterized in that: The latch also includes a connecting plate; One ends of the first pin and the second pin are connected via a connecting plate.

5. The UAV wing limiting mechanism according to claim 2, characterized in that: Also includes a baffle; The blocking piece is arranged on a side of the mounting plate away from the limiting plate, and is used to press the pin when the pin is inserted into the limiting seat to prevent the pin from falling off.

6. The UAV wing limiting mechanism according to claim 2, characterized in that: The area occupied by the pin hole covers the cross-sectional area of ​​the corresponding pin.

7. The UAV wing limiting mechanism according to claim 1, characterized in that: The limiting plate is arranged at an edge of the fixing plate on one side in the expansion direction of the wing where the limiting plate is located.

8. The UAV wing limiting mechanism according to claim 1, characterized in that: At least one of the limit plates is provided with a contact sensor on the side for abutting against each other, for generating a signal to control a steering gear that drives the wing to rotate when the two limit plates are in contact.

9. A drone wing, characterized in that: It comprises the UAV wing limiting mechanism according to any one of claims 1 to 8.

10. A drone, characterized in that: It comprises the UAV wing limiting mechanism according to any one of claims 1 to 8.

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