CN217624074U

CN217624074U - A automatic shrink wing and unmanned aerial vehicle for unmanned aerial vehicle

Info

Publication number: CN217624074U
Application number: CN202222434917.5U
Authority: CN
Inventors: 韩迪; 罗乾
Original assignee: Beijing Aurora Vision Technology Co ltd
Current assignee: Beijing Aurora Vision Technology Co ltd
Priority date: 2022-09-15
Filing date: 2022-09-15
Publication date: 2022-10-21
Anticipated expiration: 2032-09-15

Abstract

The utility model provides an automatic shrink wing and unmanned aerial vehicle for unmanned aerial vehicle, include: a support portion; a main power part which is arranged on the supporting part and is used for providing power; a plurality of telescopic transmission components which are arranged around the main power part; the wing assemblies are respectively and correspondingly arranged with the telescopic transmission assemblies and movably connected at the edges of the supporting parts; wherein, flexible transmission assembly includes: one end of the transmission rod is in transmission connection with the main power part; the first gear is connected to the other end of the transmission rod; the first face gear is vertically arranged, fixedly connected with the wing assembly and meshed with the first gear; the first face gear drives the wing assembly to lift up or put down through the driving of the first gear. The utility model provides a current unmanned aerial vehicle adopt during the structure driven mode of oscilaltion the ascending volume of upper and lower side great, lead to occupation space big, use inconvenient problem.

Description

A automatic shrink wing and unmanned aerial vehicle for unmanned aerial vehicle

Technical Field

The utility model relates to an aircraft technical field, more specifically say, relate to an automatic shrink wing and unmanned aerial vehicle for unmanned aerial vehicle.

Background

Unmanned aerial vehicle mainly utilizes radio remote control equipment and self-contained program control device to control so that reach the purpose of flight, because unmanned aerial vehicle compares with manned aircraft and has small, the cost is low, convenient to use, to the low grade advantage of environmental requirement, unmanned aerial vehicle is by the wide application in tasks such as pesticide sprays, pollination, seeding, aerial shooting, air transportation.

But unmanned aerial vehicle all adopts fixed wing to produce, and traditional unmanned aerial vehicle's wing has adopted integral structure with the main part, and occupation space is very big, especially to the wing, to the fixed extension in all directions. Usually, the wings of the unmanned aerial vehicle do not have the functions of folding and unfolding, so that inconvenience is caused when the unmanned aerial vehicle is carried and stored for a user. Although some unmanned aerial vehicles's wing sets up to the extendible, what its adopted is to promote through the oscilaltion structure, and the oscilaltion structure needs very big stroke just can draw in the wing from the horizontality (expansion) in to vertical state (shrink), and its principle is similar to the expansion and the packing up of umbrella. But the oscilaltion structure needs the upper and lower direction to have sufficient space, leads to unmanned aerial vehicle vertical placing like this and when expanding the use, still has very big volume in the upper and lower direction, needs to occupy a large amount of spaces, leads to using inconveniently.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an automatic shrink wing and unmanned aerial vehicle for unmanned aerial vehicle to solve current unmanned aerial vehicle and adopt when the oscilaltion structure driven mode the ascending volume in upper and lower side great, lead to occupation space big, use inconvenient problem.

In order to achieve the above object, the utility model adopts the following technical scheme:

in one aspect, the utility model provides an automatic shrink wing for unmanned aerial vehicle, include:

a support portion;

the main power part is arranged on the supporting part and is used for providing power;

the plurality of telescopic transmission components are arranged around the main power part;

the wing assemblies and the telescopic transmission assemblies are respectively and correspondingly arranged, and the wing assemblies are movably connected at the edges of the supporting parts;

wherein, flexible drive assembly includes:

one end of the transmission rod is in transmission connection with the main power part;

the first gear is connected to the other end of the transmission rod;

the first face gear is vertically arranged, fixedly connected with the wing assembly and meshed with the first gear;

the first face gear drives the wing component to lift up or put down through the driving of the first gear.

Optionally, the main power part comprises: the main motor is connected to the supporting part along the vertical direction;

the driving bevel gear is connected to a rotating shaft of the main motor along the horizontal direction;

one end of the transmission rod is provided with a driven bevel gear, and the driven bevel gear is arranged along the vertical direction and meshed with the driving bevel gear.

Optionally, the transmission rod is rotatably connected to the support portion through a bearing seat;

the edge of the supporting part is provided with a hinged seat, the hinged seat is provided with a movable space, and one end of the wing assembly is positioned in the movable space and hinged on the hinged seat;

the transfer line extends to the activity space, and first gear and first face gear all are located the activity space.

Optionally, a locking assembly is provided on the support portion, the locking assembly comprising:

a locking power part disposed on the support part;

the second gear is connected to the rotating shaft of the locking power part;

the surface of the face gear ring is provided with a tooth part and is meshed with the second gear through the tooth part, and the face gear ring is driven to rotate by the second gear;

the clamping portion is fixedly arranged on the face gear ring and enters or leaves the movable space through the rotation of the face gear ring so as to limit the wing assembly.

Optionally, a groove is arranged on the surface of the supporting part, and the face tooth ring is embedded into the groove;

a guide post is arranged in the groove, a guide waist-shaped hole is correspondingly arranged on the face tooth ring, and the guide post is embedded in the guide waist-shaped hole.

Optionally, the clamping portion includes: the upright post frame is connected to the face toothed ring;

the screens board, screens board fixed connection are on the stand frame, and the screens board rotates through the drive of face ring gear to get into the activity space and lean on spacing wing subassembly or leave the activity space and break away from unblock wing subassembly.

Optionally, the wing assembly has a deployed state by rotation;

when the wing assembly is in the unfolding state, the wing assembly is in the horizontal direction through rotation, and the clamping plate moves to be located in the moving space and abut against the wing assembly so as to limit the wing assembly in the vertical direction.

Optionally, a baffle is arranged in the movable space, and the baffle is positioned on one side of the wing assembly facing the main power part;

the wing assembly has a contracted state by rotation;

when the wing assembly is in a contraction state, the wing assembly abuts against the baffle plate through rotation, and the clamping plate moves to be located in the movable space and abuts against the wing assembly so as to limit the wing assembly in the radial direction.

Optionally, the wing assembly comprises: one end of the wing supporting arm is hinged on the supporting part;

the flying power part is connected to the other end of the wing supporting arm;

and the flying blade is connected to the flying power part and rotates by the driving of the flying power part.

On the other hand, the utility model provides an unmanned aerial vehicle, wherein include: an aircraft body, and a self-retracting wing as described above, wherein the support portion of the self-retracting wing is connected to the bottom of the aircraft body.

The utility model provides a pair of an automatic shrink wing and unmanned aerial vehicle's beneficial effect for unmanned aerial vehicle lies in at least: the utility model discloses a main power portion switches on and provides power after receiving the instruction, drives a plurality of flexible drive assembly and rotates, and a plurality of flexible drive assembly drive the wing subassembly respectively and rotate to make the wing subassembly can rotate and contract on the vertical direction, and rotate and expand on the horizontal direction, thereby realize the automatic flexible function of wing. When the wing assembly is in the vertical position, it is in a contracted state; the wing assembly is deployed when in the horizontal position. Under the expansion state, only be located the main power portion on the supporting part and taken up certain volume, and flexible drive assembly all sets up at the supporting part on the surface, and arrange along the horizontal direction, drive with adopting oscilaltion structure to compare among the current unmanned aerial vehicle, the structure volume under the expansion state that has significantly reduced occupies littleer vertical space, unmanned aerial vehicle when flying up, the interference influence of the object of the below that can significantly reduce, make things convenient for unmanned aerial vehicle's use more, do benefit to unmanned aerial vehicle's miniaturization.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

Fig. 1 is a schematic structural diagram of an automatic retractable wing for an unmanned aerial vehicle according to an embodiment of the present invention;

FIG. 2 is an enlarged view of the portion A of FIG. 1;

fig. 3 is a schematic structural view of the locking assembly for the unmanned aerial vehicle when the locking assembly is not limited in the unfolded state of the automatically retractable wing provided by the embodiment of the present invention;

fig. 4 is a cross-sectional view of an extended state of an automatically retractable wing for an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 5 is a schematic structural view of the locking assembly for limiting the position of the automatic retractable wing of the unmanned aerial vehicle in the retracted state according to the embodiment of the present invention;

fig. 6 is an exploded view of an automatic retraction wing removal wing assembly for a drone provided by an embodiment of the present invention.

Wherein, in the figures, the respective reference numerals:

100. a support portion; 110. a bearing seat; 120. a hinged seat; 121. an activity space; 122. a clamping hole; 123. a baffle plate; 130. a groove; 131. a guide post; 200. a main power section; 210. a main motor; 220. a drive bevel gear; 300. a telescopic transmission assembly; 310. a transmission rod; 311. a driven bevel gear; 320. a first gear; 330. a first face gear; 400. a wing assembly; 410. a wing support arm; 420. a flight power section; 430. a flight blade; 500. a locking assembly; 510. locking the power part; 520. a second gear; 530. a face gear ring; 531. a tooth portion; 532. a guide waist-shaped hole; 540. a clamping part; 541. a column frame; 542. a blocking plate.

Detailed Description

In order to make the technical problem, technical solution and advantageous effects to be solved by the present invention more clearly understood, the following description is given in conjunction with the accompanying drawings and embodiments to illustrate the present invention in further detail. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention.

It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly or indirectly disposed on the other element. When an element is referred to as being "connected to" another element, it can be directly or indirectly connected to the other element. The terms "upper", "lower", "left", "right", "front", "back", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positions based on the orientations or positions shown in the drawings, and are for convenience of description only and not to be construed as limiting the technical solution. The terms "first", "second" and "first" are used merely for descriptive purposes and are not to be construed as indicating or implying relative importance or to implicitly indicate a number of technical features. The meaning of "plurality" is two or more unless specifically limited otherwise.

Referring to fig. 1, 4 and 5, the present embodiment provides an automatic retraction wing for a drone, for connecting to an aircraft body to form the drone. The automatic contraction wing specifically comprises: a support portion 100, a main power portion 200, a plurality of telescopic drive assemblies 300, and a plurality of wing assemblies 400. The support portion 100 may be a circular support plate, which primarily serves as a support attachment structure to provide a mounting location for each workpiece. For the convenience of structural description, the circular support plate is horizontally arranged, the axial direction is the vertical direction, the direction towards the circle center of the circular support plate is inward, and the direction far away from the circle center of the circular support plate is outward. The main power part 200 is disposed on the support part 100 and located at the center of the support part 100, and the main power part 200 is used for providing power after being electrified. The plurality of telescopic transmission assemblies 300 are arranged around the main power part 200, the plurality of wing assemblies 400 and the plurality of telescopic transmission assemblies 300 are respectively arranged correspondingly, and the wing assemblies 400 are movably connected at the edge of the outer side of the support part 100.

For convenience of structural description, in this embodiment, the wing assembly 400 is lifted up and then positioned in a vertical state as a contracted state, and the wing assembly 400 is rotated down to a horizontal state as an expanded state. For making unmanned aerial vehicle more stable at the flight in-process, wing subassembly 400 is provided with four, and the flexible transmission assembly 300 that corresponds is provided with four, drives for four flexible transmission assemblies 300 simultaneously through main power portion 200 to drive four wing subassemblies 400 and rotate in step and expand and contract, four wing subassemblies 400 are around circumference evenly distributed, thereby make unmanned aerial vehicle more stable at the flight in-process.

The telescopic driving assembly 300 in this embodiment specifically includes: a drive link 310, a first gear 320, and a first face gear 330. The transmission rod 310 extends in a radial direction and is rotatably disposed on the support portion 100, and one inward end of the transmission rod 310 is in transmission connection with the main power portion 200 and is driven by the main power portion 200 to rotate. The first gear 320 is connected to one end of the transmission rod 310 facing outward, the first face gear 330 is vertically arranged and rotatably arranged on the support portion 100, that is, the rotation central axis of the first face gear 330 is perpendicular to the axis of the transmission rod 310, and the first face gear 330 is fixedly connected with the wing assembly 400 and meshed with the first gear 320. The first face gear 330 drives the wing assembly 400 to lift or lower through the driving of the first gear 320.

In this embodiment, the main power unit 200 is powered on and provides power after receiving the instruction, so as to drive the plurality of telescopic transmission assemblies 300 to rotate, and the plurality of telescopic transmission assemblies 300 respectively drive the wing assembly 400 to rotate, so that the wing assembly 400 can rotate to the vertical direction to be contracted and rotate to the horizontal direction to be expanded, thereby achieving the function of automatic wing expansion. In the transmission process of the telescopic transmission assembly 300, the rotating transmission rod 310 drives the first gear 320 to rotate, the first gear 320 is meshed with the first face gear 330, and the first face gear 330 is arranged in the vertical direction, so that the first face gear 330 can rotate clockwise or counterclockwise on the vertical plane under the driving of the first gear 320, and then after the wing assembly 400 is fixedly connected with the first face gear 330, the first face gear 330 drives the wing assembly 400 to lift or lower through the driving of the first gear 320. When the wing assembly 400 is in the vertical position, it is in a contracted state; when the wing assembly 400 is in the horizontal position, it is in the deployed state. In the unfolding state, the main power part 200 on the supporting part 100 occupies a certain volume in the up-down direction, and the telescopic transmission assemblies 300 are all arranged on the surface of the supporting part 100 and arranged along the horizontal direction, so that the structural volume in the unfolding state is greatly reduced, and a smaller vertical space is occupied.

The automatic wing that contracts for unmanned aerial vehicle that this embodiment provided lies in at least: adopt the oscilaltion structure to drive to compare among the current unmanned aerial vehicle, the structure volume under the expansion state that has significantly reduced occupies littleer vertical space, and unmanned aerial vehicle when flying, the interference influence of the object of the below that has significantly reduced makes things convenient for unmanned aerial vehicle's use more, does benefit to unmanned aerial vehicle's miniaturization.

As shown in fig. 4, the main power unit 200 in the present embodiment specifically includes: a main motor 210 and a drive bevel gear 220. As shown in fig. 1, 2 and 4, the main motor 210 is connected to the support part 100 along a vertical direction, and in a specific structure, a through hole is formed in the center of the support part 100, the main motor 210 is disposed on the bottom surface of the support part 100, and a rotating shaft of the main motor 210 passes through the through hole and protrudes out of the upper surface of the support part 100. The drive bevel gear 220 is located above the upper surface of the support part 100, and the drive bevel gear 220 is connected to the rotation shaft of the main motor 210 in a horizontal direction. An inward end of the driving lever 310 is provided with a driven bevel gear 311, and the driven bevel gear 311 is disposed in a vertical direction and engaged with the drive bevel gear 220. The drive bevel gear 220 has a large diameter and the driven bevel gear 311 has a small diameter. Therefore, the driving bevel gears 220 can be engaged with the driven bevel gears 311 of the four telescopic transmission assemblies 300 in four directions simultaneously to synchronously drive the transmission rods 310 in the four directions to rotate, so that the rotation of the transmission rods 310 drives the first gear 320 and the first face gear 330 to rotate, thereby driving the wing assembly 400 to be lifted or lowered. And set up main motor 210 on the bottom surface of supporting part 100, the space that main motor 210 took is little, and the length that the bottom only set up a motor, compares in the form that adopts elevation structure, can effectively reduce vertical direction's size. If the size of the unmanned aerial vehicle is further reduced, the main motor 210 can be arranged at the bottom of the supporting part 100 along the horizontal direction, and then the main motor is meshed through the gear set and then power is transmitted to the driving bevel gear 220, so that the size of the unmanned aerial vehicle is further reduced, more parts are added, and the cost is increased.

As shown in fig. 1, 2 and 3, the driving rod 310 in this embodiment is rotatably connected to the support portion 100 through a bearing housing 110, the bearing housing 110 is disposed on the upper surface of the support portion 100, and the driving rod 310 is inserted into the bearing housing 110 so that the driving rod 310 can rotate. The edge of the support part 100 is provided with a hinge seat 120, and the hinge seat 120 is arranged corresponding to the wing assembly 400. The hinge base 120 has a movable space 121, and one end of the wing assembly 400 is located in the movable space 121 and is hinged to the hinge base 120. The driving rod 310 extends to the movable space 121, and the first gear 320 and the first face gear 330 are both located in the movable space 121. One end of the wing assembly 400 can be hinged to the supporting portion 100 through the hinge base 120, so that the wing assembly 400 rotates around the hinge, the first face gear 330 is fixed to the wing assembly 400 at the hinge, and when the first gear 320 rotates, the first face gear 330 is driven to rotate, so that the wing assembly 400 can be driven to be lifted and lowered.

As shown in fig. 1, 3 and 5, the support portion 100 in this embodiment is provided with a locking assembly 500, when the wing assembly 400 rotates to a horizontal state, the locking assembly 500 is activated to limit the wing assembly 400 to the horizontal state, so that the deployed wing assembly 400 is activated to enable the unmanned aerial vehicle to take off. When wing subassembly 400 rotated to vertical state, start locking assembly 500, can be spacing at vertical state with wing subassembly 400, realize the wing shrink to unmanned aerial vehicle, be convenient for unmanned aerial vehicle's accomodation. The locking assembly 500 in this embodiment specifically includes: the locking power part 510, the second gear 520, the face ring gear 530, and the snap-in part 540. The locking power part 510 is disposed on the support part 100, and the locking power part 510 may be a motor, and may realize forward rotation and reverse rotation when being powered on. The second gear 520 is coupled to a rotation shaft of the locking power part 510, and the locking power part 510 is disposed in a radial direction, and thus the second gear 520 is also disposed in a radial direction. The face gear ring 530 has a tooth portion 531 on a surface thereof and is engaged with the second gear 520 through the tooth portion 531, the face gear ring 530 is rotated by driving of the second gear 520, the tooth portion 531 is located on an upper surface, and the second gear 520 is installed just above the face gear ring 530 due to a certain installation height of the locking power portion 510 to be engaged with the tooth portion 531 on the upper surface. The locking power unit 510 is energized to rotate the second gear 520, thereby rotating the face gear ring 530. The face gear ring 530 is disposed at an edge of the support portion 100, and a rotation center thereof may be the same as that of the main power portion 200. The clamping part 540 is fixedly arranged on the face gear ring 530 and enters or leaves the movable space 121 through the rotation of the face gear ring 530 so as to limit the wing assembly 400.

As shown in fig. 1 and 6, in the present embodiment, the surface of the supporting portion 100 is provided with the groove 130, the face gear ring 530 is embedded in the groove 130, and the groove 130 is disposed below the hinge seat 120, so that the face gear ring 530 rotates in the groove 130, firstly, the face gear ring 530 is limited by the groove 130, secondly, the size of the face gear ring 530 protruding out of the upper surface of the supporting portion 100 is reduced, and the size and thickness of the drone are reduced. The groove 130 is internally provided with a guide column 131, the face gear ring 530 is correspondingly provided with a guide waist-shaped hole 532, and the guide column 131 is embedded in the guide waist-shaped hole 532. The guide column 131 is matched with the guide waist-shaped hole 532, so that the rotation of the face gear ring 530 can be stably guided, and the rotation is more stable. In addition, a limiting head (not shown in the figures) can be arranged at the upper end of the guide column 131, and the diameter of the limiting head is larger than the width of the guide kidney-shaped hole 532, so that the guide kidney-shaped hole 532 can be limited in the groove 130 to move stably.

As shown in fig. 1, 3 and 5, the clip part 540 in the present embodiment includes: a post frame 541 and a blocking plate 542. The upright post frame 541 is fixedly connected to the face gear ring 530 through welding, the blocking plate 542 is fixedly connected to the upright post frame 541, and the blocking plate 542 is driven by the face gear ring 530 to rotate and enters the movable space 121 to abut against the limiting wing assembly 400 or leave the movable space 121 to separate from the unlocking wing assembly 400. In a specific structure, the locking plate 542 is arc-shaped, and the rotation process of the locking plate is synchronized with the rotation of the face gear ring 530. The side surface of the hinged seat 120 is provided with a through clamping hole 122, and the clamping plate 542 can enter the clamping hole 122 or move out of the clamping hole 122 through rotation, so that the lower or inner side wing assembly 400 can be limited.

The wing assembly 400 in this embodiment has an extended state, and a retracted state, by rotation. The locking plate 542 can limit and fix the wing assembly 400 in the extended state and the retracted state by rotating, so that the wing assembly 400 is not easy to loosen.

As shown in fig. 1 and 2, when the wing assembly 400 is in the deployed state, the wing assembly 400 is in the horizontal direction by rotation, the locking plate 542 is moved by rotation of the face gear ring 530, when the locking plate 542 passes through the locking hole 122 and enters the moving space 121, the wing assembly 400 is located below the locking plate 542, the locking plate 542 abuts against the wing assembly 400 above, and the support portion 100 abuts against the wing assembly 400 below, so that the wing assembly 400 is limited from the vertical direction, and the wing assembly 400 cannot swing in the up-and-down direction. So that the wing assembly 400 can be stably deployed and drive the aircraft body to perform flying work. When the wing needs to be retracted after the operation is completed, the face toothed ring 530 is rotated reversely to drive the blocking plate 542 to exit from the blocking hole 122, so that the movable space 121 is opened, and the wing assembly 400 can swing upwards and retract.

As shown in fig. 5, a baffle 123 (refer to fig. 3) is disposed in the movable space 121, the baffle 123 is fixedly connected to the hinge base 120, and the baffle 123 is located on a side (inner side) of the wing assembly 400 facing the main power portion 200. The wing assembly 400 is pivoted upward to the vertical to achieve the retracted state. When the wing assembly 400 is in the contracted state, the wing assembly 400 abuts against the baffle 123 through rotation, and the clamping plate 542 moves to be located in the moving space 121 and abuts against the wing assembly 400, so that the wing assembly 400 is limited on the inner side and the outer side of the wing assembly 400, the wing assembly 400 cannot swing in the inner and outer directions, the wing assembly 400 is limited in the radial direction, and the wing assembly 400 cannot loosen in the contracted state. When the unmanned aerial vehicle is started and the wing needs to be unfolded, the face toothed ring 530 is rotated reversely to drive the clamping plate 542 to exit from the clamping hole 122, so that the movable space 121 is opened, and the wing assembly 400 can swing downwards and be unfolded.

As shown in fig. 1, the wing assembly 400 in this embodiment specifically includes: wing support arms 410, a flight power section 420, and flight blades 430. One end of the wing support arm 410 is hinged on the support part 100, and the other end is fixedly connected with the flight power part 420. The flight motor unit is a motor, and the flight blade 430 is connected to the flight power unit 420 and rotated by driving of the flight power unit 420. After the wing assembly 400 is deployed, the flight blades 430 are rotated, thereby enabling the drone to perform flight operations.

Based on the same concept, the present application also proposes an unmanned aerial vehicle (not shown in the drawings), which includes: an aircraft body, and a self-retracting wing as described above, wherein the support portion of the self-retracting wing is connected to the bottom of the aircraft body.

The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.

Claims

1. An auto-retracting wing for a drone, comprising:

a support portion;

a plurality of telescopic transmission components arranged around the main power part;

wherein, the flexible transmission subassembly includes:

the first gear is connected to the other end of the transmission rod;

the first face gear drives the wing assembly to lift up or put down through the driving of the first gear.

2. The auto-retracting wing for a drone of claim 1, wherein the main power section includes: a main motor connected to the support part in a vertical direction;

and one end of the transmission rod is provided with a driven bevel gear, and the driven bevel gear is arranged along the vertical direction and meshed with the driving bevel gear.

3. The automatic retraction wing for a drone according to claim 2, characterized in that said transmission rod is rotatably connected to said support through a bearing housing;

a hinge seat is arranged at the edge of the support part, the hinge seat is provided with a movable space, and one end of the wing assembly is positioned in the movable space and is hinged on the hinge seat;

the drive link extends to the activity space, first gear with first face gear all is located in the activity space.

4. The auto-retracting wing for a drone of claim 3, wherein a locking assembly is provided on the support, the locking assembly comprising:

a locking power part provided on the support part;

the second gear is connected to the rotating shaft of the locking power part;

a face gear ring having a surface provided with teeth and engaged with a second gear by the teeth, the face gear ring being rotated by driving of the second gear;

the clamping portion is fixedly arranged on the face gear ring and enters or leaves the movable space through rotation of the face gear ring so as to limit the wing assembly.

5. The auto-retracting wing for a drone of claim 4, wherein the support portion has a groove provided on a surface thereof, the face ring being embedded in the groove;

the groove is internally provided with a guide column, the face gear ring is correspondingly provided with a guide waist-shaped hole, and the guide column is embedded in the guide waist-shaped hole.

6. The auto-retracting wing for a drone of claim 4, wherein the snap-in portion includes: the upright post frame is connected to the face toothed ring;

the clamping plate is fixedly connected to the upright post frame, the clamping plate rotates under the driving of the face gear ring and enters the movable space to abut against and limit the wing assembly or leave the movable space to separate from and unlock the wing assembly.

7. The auto-retracting wing for a drone of claim 6, wherein the wing assembly has a deployed state by rotating;

when the wing assembly is in a spreading state, the wing assembly is in a horizontal direction through rotation, and the clamping plate moves to be located in the moving space and abut against the wing assembly so as to limit the wing assembly from a vertical direction.

8. The automatic retraction wing for a drone of claim 6, wherein a baffle is provided within the active space, the baffle being located on a side of the wing assembly facing the primary power section;

the wing assembly having a retracted state by rotation;

when the wing assembly is in a contraction state, the wing assembly abuts against the baffle plate through rotation, and the clamping plate moves to be located in the movable space and abuts against the wing assembly so as to limit the wing assembly from the radial direction.

9. The auto-retracting wing for a drone of claim 1, the wing assembly comprising: the wing supporting arm is hinged to the supporting part at one end;

the flight power part is connected to the other end of the wing supporting arm;

and the flying blade is connected to the flying power part and is driven by the flying power part to rotate.

10. An unmanned aerial vehicle, comprising: an aircraft body, and a self-retracting wing as claimed in any of claims 1 to 9, wherein a support portion of the self-retracting wing is attached to a bottom of the aircraft body.