CN216887192U

CN216887192U - Folding and unfolding locking mechanism for unmanned aerial vehicle wing

Info

Publication number: CN216887192U
Application number: CN202220571627.2U
Authority: CN
Inventors: 许冶; 范伯钧; 柏俊松; 万建武; 王培明
Original assignee: Wuhan Tiantuo Aerospace Intelligent Equipment Co ltd
Current assignee: Wuhan Tiantuo Aerospace Intelligent Equipment Co ltd
Priority date: 2022-03-16
Filing date: 2022-03-16
Publication date: 2022-07-05
Anticipated expiration: 2032-03-16

Abstract

The utility model provides an unmanned wing folding and unfolding locking mechanism which comprises a fuselage, a driving device, a limiting device, fixed seats, wings and a reset device, wherein the driving device is fixedly arranged at the inner side of the fuselage, the fixed seats are rotatably arranged on the outer surface of the fuselage, the driving device drives the fixed seats to rotate, the rotating shafts of the fixed seats are perpendicular to the length direction of the fuselage, each fixed seat can be rotatably provided with one wing, the rotating shafts of the wings are selectively perpendicular to or parallel to the rotating shafts of the fixed seats in the rotating process of the fixed seats, the reset device is arranged on the fixed seats and can drive the wings to rotate around the fixed seats to the position where the plane of the wings is parallel to the rotating shafts of the fixed seats, the limiting device is fixedly arranged on the outer surface of the fuselage, and the abutting positions of the wings and the limiting device are continuously changed in the process of converting the wings from a folding state to an unfolding state. The utility model simplifies the driving structure, thereby enabling the wing to be unfolded more quickly.

Description

Folding and unfolding locking mechanism for unmanned aerial vehicle wing

Technical Field

The utility model relates to the technical field of aircrafts, in particular to an unmanned aerial vehicle wing folding and unfolding locking mechanism.

Background

Along with the continuous development of unmanned vehicles, its application field is also continuously expanding, consequently unmanned aerial vehicle's rate of utilization has obtained improvement by a wide margin, and among the prior art, unmanned aerial vehicle has some structural defects that await the solution urgently.

The fixed wing aircraft has the problem of large occupied space, so the fixed wing aircraft is inconvenient to carry and store, in order to solve the technical problem, a large number of folding wing aircraft appear in the prior art, the wings are stored on the inner side or the outer surface of a fuselage in a folding mode, so the space occupancy rate of the aircraft is greatly reduced, but the folding wings need to be unfolded in a controlled manner, the unfolding or overturning structure of the wings needs to be additionally added, in order to simplify the unfolding driving structure of the wings as much as possible in the prior art, a torsion spring structure is mostly adopted for driving, a torsion spring is coaxially arranged on a rotating shaft of the wings, the volume of the driving structure can be greatly reduced, but the simple rotary folding wings still have some structural defects, because the wings are driven by the torsion spring, the folded wings can only be arranged side by side, and the width of the wings is greatly reduced, influence flight power, if adopt the structure that stacks then can influence the mechanical strength of rotating part, if in order to guarantee intensity and power simultaneously, then can occupy a large amount of spaces after the wing is folding, even reduce the inside space of aircraft. Therefore, wings which can be folded and turned over simultaneously appear on the market, so that the wings can be respectively installed on two sides of the aircraft, cannot influence each other, and can simultaneously ensure the occupied space and the flight performance.

But adopt the mode of upset and folding simultaneously then can additionally increase upset drive structure and folding drive structure, once more take up for the space and bring the problem, more drive structure also can bring lower reliability simultaneously.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model provides an unmanned aerial vehicle wing folding and unfolding locking mechanism which is simple in driving structure, reasonable in design and relatively better in reliability.

The technical scheme of the utility model is realized as follows: the utility model provides an unmanned aerial vehicle wing folding and unfolding locking mechanism, which comprises:

a machine body which has a certain length and is provided with an inner cavity structure,

a driving device which is arranged in the fuselage and is used for driving the wings to turn over,

the limiting device is used for assisting the turning of the wings and limiting the postures of the wings in the turning process,

a fixed seat which is used for being in driving connection with the driving device and connecting the wing with the fuselage,

the wings are used as the flying dynamic structural members of the fuselage,

and the resetting device is used for assisting the wing to be unfolded and is used as a main driving power source for unfolding the wing.

Wherein the driving device is fixedly arranged at the inner side of the fuselage, the fixed seat is rotatably arranged at the outer surface of the fuselage, the driving device drives the fixed seat to rotate, the rotating shaft of the fixed seat is vertical to the length direction of the fuselage, each fixed seat is rotatably provided with a wing, the rotating shaft of each wing is selectively vertical or parallel to the rotating shaft of the fixed seat in the rotating process of the fixed seat, the resetting device is arranged on the fixed seat and can drive the wings to rotate around the fixed seat to the position where the plane where the wings are positioned is parallel to the rotating shaft of the fixed seat, the limiting device is fixedly arranged at the outer surface of the fuselage, the rotating shaft of each wing is vertical to the length direction of the fuselage, the folding state of each wing is realized when the plane where the wings are positioned is vertical to the rotating shaft of the fixed seat, and the unfolding state of each wing is realized when the rotating shaft of each wing is parallel to the length direction of the fuselage and the rotating shaft of the fixed seat is parallel to the rotating shaft of the fixed seat, in the process of converting the wings from the folded state to the unfolded state, the abutting positions of the wings and the limiting devices are constantly changed.

In addition to the above technical means, preferably, the driving device includes: the motor and the transmission device are fixedly mounted on the inner side of the machine body, an output shaft of the motor is in transmission connection with the transmission rod through the transmission device, one end, far away from the transmission device, of the transmission rod is fixedly connected with the fixing seat, and the transmission rod and the rotating shaft of the fixing seat are coaxially arranged.

On the basis of the above technical scheme, preferably, the motor can be one of a common motor, a servo motor, a stepping motor and any motor capable of realizing rotation driving in the prior art

On the basis of the above technical scheme, preferably, the transmission device is a speed reducer, the speed reducer comprises an input end and an output end, an output shaft of the motor is in transmission connection with the input end of the speed reducer, and the output end of the speed reducer is in transmission connection with the transmission rod.

Preferably, the speed reducer is a worm gear speed reducer, and an output shaft of the motor is coaxially connected with an input end of the speed reducer or connected through a coupling to realize rotational transmission.

On the basis of the technical scheme, the transmission device is preferred to further comprise a coupler, the output end of the speed reducer is connected with one end of the transmission rod through the coupler, and one end, far away from the speed reducer, of the transmission rod is fixedly connected with the fixing seat.

Preferably, the number of the fixing seats is not less than two, the number of the output ends of the speed reducer, the number of the transmission rods and the number of the fixing seats are the same, and each output end of the speed reducer is in transmission connection with one fixing seat through one transmission rod.

On the basis of the technical scheme, the bearing is preferably further included, the bearing is fixedly installed on the machine body, and the bearing is coaxially sleeved on the outer side of the transmission rod.

On the basis of the technical scheme, the wing aircraft further comprises a rotating shaft and a shaft sleeve, wherein the shaft sleeve is fixedly installed on the side face of the fixed seat, the rotating shaft is fixedly installed on the side face of one end of the wing along the length direction, the rotating shaft is sleeved in the shaft sleeve, and the wing rotates around the rotating shaft.

On the basis of the technical scheme, the wing unfolding and folding mechanism is preferred and further comprises an unfolding pin, the unfolding pin is fixedly installed on the surface of the rotating shaft or the wing, the limiting device comprises an arc abutting edge, the arc abutting edge is in a spiral shape, the opening direction of the spiral is the same as the rotating direction of the wing when the wing is unfolded, the unfolding pin abuts against the surface of the arc abutting edge when the wing is folded, the unfolding pin slides towards the opening direction of the spiral along the arc abutting edge when the wing rotates to the unfolding state from the folding state, and the unfolding pin is separated from the arc abutting edge and separated from the limiting device when the wing reaches the unfolding state or before the wing reaches the unfolding state.

On the basis of the technical scheme, preferably, the shaft sleeve can be further fixedly installed on the side face of one end of the wing in the length direction, the rotating shaft is fixedly installed on the side face of the fixed seat, the rotating shaft is sleeved in the shaft sleeve, the wing rotates around the rotating shaft, and on the basis of the scheme, the unfolding pin is fixedly installed on the surface of the shaft sleeve or the wing.

On the basis of the technical scheme, preferably, the reset device is a torsion spring, the torsion spring is sleeved outside the rotating shaft, and two driving ends of the torsion spring respectively abut against the surface of the wing and the surface of the fixed seat and have a tendency of driving the wing to move towards the unfolding state.

On the basis of the technical scheme, the wing fixing device is preferred to further comprise a hook, a groove is formed in one end, close to the fixing seat, of the wing, the hook is installed on the surface of the fixing seat, and when the wing rotates to the unfolding state, the hook is clamped in the groove, so that the wing and the fixing seat are fixedly connected.

Compared with the prior art, the folding and unfolding locking mechanism of the unmanned aerial vehicle wing has the following beneficial effects:

(1) the utility model provides an unmanned wing folding and unfolding locking mechanism which has more reasonable structural design, so that the driving mechanism occupies less space, occupies less space in a wing folding state, has little influence on the performance of the wing, and has a quicker unfolding process;

(2) the wing unfolding mechanism is characterized in that the transverse wing unfolding action is associated with the angle rotation action of the wing, the wing unfolding action and the angle rotation action are linked by arranging the limiting device and the resetting device, the resetting device has the action trend of unfolding the wing, the action amplitude of the limiting device for unfolding the wing is limited, the limiting degree of the limiting device for the wing is related to the angle rotation of the wing, and finally the unfolding amplitude of the wing is realized by adjusting the angle of the wing;

(3) the wing fixing device is also provided with a hook and groove structure, so that the completely unfolded wing can be fixed, and the stability of the unfolded wing is ensured.

Drawings

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

FIG. 1 is an isometric view of an unmanned wing fold-out locking mechanism of the present invention;

FIG. 2 is an exploded view of FIG. 1;

FIG. 3 is an enlarged view of a portion of the fold-out locking mechanism of the unmanned aerial vehicle wing of the present invention;

FIG. 4 is an enlarged view of a portion of the fold-out locking mechanism of the unmanned aerial vehicle wing of the present invention;

FIG. 5 is a front view of a position limiting device in the folding and unfolding locking mechanism of the unmanned aerial vehicle wing;

fig. 6 is an exploded view of the shaft and sleeve portion of the folding and unfolding locking mechanism of the unmanned aerial vehicle wing.

In the figure: the airplane comprises a fuselage 1, a driving device 2, a limiting device 3, a fixed seat 4, a wing 5, a resetting device 6, a motor 21, a transmission device 22, a transmission rod 23, a coupling 24, a bearing 25, a rotating shaft 7, a shaft sleeve 8, an expansion pin 9, an arc-shaped abutting edge 31, a hook 10 and a groove 51.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.

As shown in fig. 1 and shown in fig. 2-6, the folding and unfolding locking mechanism of unmanned aerial vehicle of the present invention comprises a vehicle body 1, a driving device 2, a limiting device 3, a fixing seat 4, a vehicle wing 5 and a resetting device 6, wherein the vehicle body 1 is a cavity structure with a certain length, the driving device 2 is installed inside the vehicle body 1, the fixing seat 4 is rotatably installed on the outer surface of the vehicle body 1, the vehicle wing 5 is installed on the fixing seat 4 and can rotate relative to the fixing seat 4, the resetting device 6 is arranged on the fixing seat 4, the limiting device 3 is fixedly installed on the outer surface of the vehicle body 1, the rotation axis of the fixing seat 4 is perpendicular to the length direction of the vehicle body 1, the rotation axis of the vehicle wing 5 relative to the fixing seat 4 is perpendicular to the rotation axis of the fixing seat 4, and in the process of rotating the fixing seat 4, the rotation axis of the vehicle wing 5 relative to the fixing seat 4 is selectively parallel or perpendicular to the length direction of the vehicle body 1, the rotation axis of wing 5 is the folded state of wing 5 with fuselage 1 length direction is perpendicular and wing 5 place plane and fixing base 4's pivot mutually perpendicular, is the expansion state of wing 5 when wing 5's rotation axis is parallel with fuselage 1 length direction and wing 5 place plane and fixing base 4's pivot is parallel to each other, and wing 5 changes the in-process to the expansion state from folded state, and wing 5 and stop device 3's butt position constantly changes.

In the above embodiment, when the wing 5 is in the folded state, the limiting device 3 limits the wing 5, the driving device 2 drives the fixing seat 4 to rotate, the driving seat 4 rotates and simultaneously drives the wing 5 rotationally connected with the fixing seat to turn over, at this time, the positions of the fixing seat 4 and the wing 5 relative to the limiting device 3 are changed, so as to change the limiting effect of the limiting device 3 on the wing 5, the wing 5 gradually expands under the action of the resetting device 6 while turning over along with the fixing seat 4, and finally obtains the expanded state, it can be seen that, in the above embodiment, only one driving device 2 is located in the fuselage 1, the space occupied in the fuselage 1 is small, and the wing expansion only needs to be carried out by controlling the driving device 2, the structural design is reasonable, and meanwhile, because the wing is directly driven by the rotation of the fixing seat 4, the structure of the wing 5 is not influenced by the driving device 2, so that the structural performance of the wing 5 is not influenced, and the wing 5 occupies small space on the surface of the fuselage 1 when in a folded state.

In a specific embodiment, the driving device 2 further includes a motor 21, a transmission device 22 and a transmission rod 23, the motor 21 and the transmission device 22 are both fixedly installed inside the body 1, an output shaft of the motor 21 is in transmission connection with the transmission rod 23 through the transmission device 22, one end of the transmission rod 23, which is far away from the transmission device 22, is fixedly connected with the fixed seat 4, and the transmission rod 23 is coaxially arranged with a rotation shaft of the fixed seat 4.

In the above embodiment, the driving device 2 is configured to drive the fixing base 4 to rotate, as a practical and feasible driving structure, the fixing base 4 is driven to rotate by the motor 21, specifically, an output shaft of the motor 21 is in transmission connection with the transmission device 22, and the transmission rod 23 is driven to rotate by the transmission device 22 again, a tail end of the transmission rod 23 is fixed to the fixing base 4 to realize rotation of the driving fixing base 4, the transmission device 22 is configured to convert a rotation direction of the motor 21 and transmit the rotation direction to the fixing base 4 through the transmission rod 23, and specifically, the transmission rod 23 penetrates through a shell of the body 1 and is coaxially and fixedly connected with the fixing base 4.

In a specific embodiment, the transmission device 22 is a speed reducer, the speed reducer includes an input end and an output end, an output shaft of the motor 21 is in transmission connection with the input end of the speed reducer, and the output end of the speed reducer is in transmission connection with the transmission rod 23.

In the above embodiment, as a preferred embodiment, the transmission device 22 may be a speed reducer, specifically, a worm and gear speed reducer, where the speed reducer can change the rotation direction, change the rotation speed ratio, and have a locking function, and has a certain auxiliary control effect on the stability of the posture of the wing 5.

In the above technical solution, as a practical and feasible implementation manner, the motor 21 may be a servo motor, a stepping motor, a brushless motor or other motor that can provide a rotation drive conventionally, as a preferred implementation manner, the motor 21 is a servo motor, which can realize accurate angle control, and after the wing 5 is completely deployed, the motor 21 can drive the wing to perform angle adjustment.

In a specific embodiment, the device further comprises a coupler 24, the output end of the speed reducer is connected with one end of the transmission rod 23 through the coupler 24, and one end, far away from the speed reducer, of the transmission rod 23 is fixedly connected with the fixed seat.

In the above embodiment, the coupler 24 can avoid the problem that the axes of the two rotating shafts are different or the axis of the two rotating shafts is not well matched in the rotation transmission process, so as to achieve the purpose of error adaptation.

In the specific embodiment, the number of the fixing seats 4 is not less than two, the number of the output ends of the speed reducer, the number of the transmission rods 23 and the number of the fixing seats 4 are the same, and each output end of the speed reducer is in transmission connection with one fixing seat 4 through one transmission rod 23.

In the above embodiment, the number of the set wings 5 is different for different aircrafts, and the application can be applied to aircrafts with different numbers of wings 5, and the matching problem for different numbers of wings is achieved by changing the signals of the speed reducer and the number of the corresponding transmission rods 23.

In the specific embodiment, the device further comprises a bearing 25, wherein the bearing 25 is fixedly installed on the machine body 1, and the bearing 25 is coaxially sleeved on the outer side of the transmission rod 23.

In the above embodiment, the bearing 25 is used to perform transition connection at the connection position between the transmission rod 23 and the body 1, so as to ensure smooth rotation of the transmission rod 23 relative to the body 1.

In a specific embodiment, the wing aircraft further comprises a rotating shaft 7 and a shaft sleeve 8, the shaft sleeve 8 is fixedly installed on the side surface of the fixed seat 4, the rotating shaft 7 is fixedly installed on the side surface of one end of the wing 5 along the length direction, the rotating shaft 7 is sleeved in the shaft sleeve 8, and the wing 5 rotates around the rotating shaft 7.

In the above embodiment, as one of the feasible connection modes for the rotation of the wing 5 relative to the fixed seat 4, the rotation connection between the wing 5 and the fixed seat 4 is realized by using the rotating shaft 7 and the shaft sleeve 8, and the wing 5 and the fixed seat 4 can be matched with each other through the rotating shaft 7 and the shaft sleeve 8 to form a structure similar to a hinge.

In a specific embodiment, the wing unfolding and folding device further comprises an unfolding and folding part 9, the unfolding and folding part 9 is fixedly installed on the surface of the rotating shaft 7 or the surface of the wing 5, the limiting device 3 comprises an arc abutting edge 31, the arc abutting edge 31 is spiral-shaped, the opening direction of the spiral is the same as the rotating direction of the wing 5 when the wing 5 is unfolded, when the wing 5 is folded, the unfolding and folding pin 9 abuts against the surface of the arc abutting edge 31, when the wing 5 rotates from the folded state to the unfolded state, the unfolding and folding pin 9 slides towards the opening direction of the spiral along the arc abutting edge 31, and when the wing 5 reaches the unfolded state or before the wing reaches the unfolded state, the unfolding and folding pin 9 is separated from the arc abutting edge 31 and separated from the limiting device 3.

In the above embodiments, the arc abutting edge 31 is used as the structure of the surface of the limiting device 3, and the specific structure of the limiting device 3 is not limited, as a specific embodiment, the arc abutting edge 31 may be one of the side surfaces of a groove formed on the surface of the limiting device 3, or one of the side surfaces of a through hole formed on the surface of the limiting device 3, when the wing 5 is in the folded state, the unfolding pin 9 abuts against one point of the arc abutting edge 31, when the wing 5 rotates from the folded state to the unfolded state, the unfolding pin 9 moves from the position of the spiral of the arc abutting edge 31 close to the center of the circle to the position far from the center of the circle, and during the moving process, the position of the arc abutting edge 31 abutting against the unfolding pin 9 also changes, because the distance between the arc abutting edge 31 and the unfolding pin 9 increases during the rotation of the fixing base 4, the limiting effect on the unfolding pin 9 weakens, therefore, under the reset action of the reset device 6, the wing 5 is unfolded until the unfolding pin 9 is separated from the arc-shaped abutting edge 31 and separated from the limiting device 3, and the wing 5 reaches the unfolding state.

It should be understood that in another possible embodiment, the rotating shaft 7 may also be mounted on the fixed seat 4, the bushing 8 is correspondingly mounted on the wing 5, and the deploying pin 9 is correspondingly arranged on the wing 5 or the bushing 8.

In a specific embodiment, the reset device 6 is a torsion spring, the torsion spring is sleeved outside the rotating shaft 7, two driving ends of the torsion spring respectively abut against the surface of the wing 5 and the surface of the fixed seat 4, and the torsion spring has a tendency of driving the wing 5 to move towards the unfolding state.

In the above embodiment, the torsion spring is sleeved outside the rotating shaft 7, so that the occupied space is small.

In a specific embodiment, the aircraft wing structure further comprises a hook 10, a groove 51 is formed in one end, close to the fixed seat 4, of the aircraft wing 5, the hook 10 is installed on the surface of the fixed seat 4, and when the aircraft wing 5 rotates to the unfolding state, the hook 10 is clamped in the groove 51, so that the aircraft wing 5 and the fixed seat 4 are fixedly connected.

In the above embodiment, the hook 10 is used to fixedly connect the wing 5 and the fixing seat 4, and the hook 10 is driven to be embedded into the groove 51 by the driving force of the resetting device 6 and the slope action of the hook 10, so as to realize hooking.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the utility model, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

Claims

1. An unmanned wing folding and unfolding locking mechanism is characterized by comprising: fuselage (1), drive arrangement (2), stop device (3), fixing base (4), wing (5) and resetting means (6), drive arrangement (2) fixed mounting is inboard in fuselage (1), fixing base (4) rotatable mounting is in fuselage (1) surface, drive arrangement (2) drive fixing base (4) rotate, the axis of rotation of fixing base (4) is perpendicular with fuselage (1) length direction, all rotatable mounting is equipped with a wing (5) on every fixing base (4), the axis of rotation of wing (5) is perpendicular or parallel with the axis of rotation of fixing base (4) selectively in the rotatory in-process of fixing base (4), resetting means (6) set up on fixing base (4) and can drive wing (5) to rotate to the position that the axis of rotation of plane and fixing base (4) of wing (5) place is parallel around fixing base (4), stop device (3) fixed mounting is in fuselage (1) surface, the folding state of wing (5) is when the axis of rotation of wing (5) is perpendicular with fuselage (1) length direction and wing (5) place plane and the pivot mutually perpendicular of fixing base (4), the axis of rotation of wing (5) is parallel with fuselage (1) length direction and wing (5) place plane is the expansion state of wing (5) when being parallel with the pivot of fixing base (4) each other, in-process that wing (5) are converted to the expansion state from folding state, the butt position of wing (5) and stop device (3) constantly changes.

2. The mechanism of claim 1, wherein the drive means (2) comprises: motor (21), transmission (22) and transfer line (23), motor (21) and the equal fixed mounting of transmission (22) are inboard in fuselage (1), and the output shaft of motor (21) passes through transmission (22) and is connected with transfer line (23) transmission, and one end and fixing base (4) fixed connection and transfer line (23) of keeping away from transmission (22) of transfer line (23) set up with the axis of rotation is coaxial with fixing base (4) the axis of rotation.

3. The folding and unfolding locking mechanism of the unmanned aerial vehicle wing as claimed in claim 2, wherein the transmission device (22) is a speed reducer, the speed reducer comprises an input end and an output end, the output shaft of the motor (21) is in transmission connection with the input end of the speed reducer, and the output end of the speed reducer is in transmission connection with the transmission rod (23).

4. The folding and unfolding locking mechanism of the unmanned aerial vehicle wing is characterized by further comprising a coupler (24), wherein the output end of the speed reducer is connected with one end of the transmission rod (23) through the coupler (24), and one end, far away from the speed reducer, of the transmission rod (23) is fixedly connected with the fixed seat.

5. The folding and unfolding locking mechanism of the unmanned aerial vehicle wing is characterized in that the number of the fixed seats (4) is not less than two, the number of the output ends of the speed reducer, the number of the transmission rods (23) and the number of the fixed seats (4) are the same, and each output end of the speed reducer is in transmission connection with one fixed seat (4) through one transmission rod (23).

6. The folding and unfolding locking mechanism of the unmanned aerial vehicle wing is characterized by further comprising a bearing (25), wherein the bearing (25) is fixedly arranged on the fuselage (1), and the bearing (25) is coaxially sleeved outside the transmission rod (23).

7. The folding and unfolding locking mechanism of the unmanned aerial vehicle wing is characterized by further comprising a rotating shaft (7) and a shaft sleeve (8), wherein the shaft sleeve (8) is fixedly arranged on the side surface of the fixed seat (4), the rotating shaft (7) is fixedly arranged on the side surface of one end of the wing (5) along the length direction, the rotating shaft (7) is sleeved in the shaft sleeve (8), and the wing (5) rotates around the rotating shaft (7).

8. The folding and unfolding locking mechanism of the unmanned aerial vehicle wing is characterized by further comprising an unfolding pin (9), wherein the unfolding pin (9) is fixedly installed on the surface of the rotating shaft (7) or the wing (5), the limiting device (3) comprises an arc-shaped abutting edge (31), the arc-shaped abutting edge (31) is in a spiral shape, the opening direction of the spiral is the same as the rotating direction of the wing (5) during unfolding, when the wing (5) is in a folded state, the unfolding pin (9) abuts against the surface of the arc-shaped abutting edge (31), when the wing (5) rotates from the folded state to the unfolded state, the unfolding pin (9) slides along the arc-shaped abutting edge (31) towards the opening direction of the spiral, and when the wing (5) reaches the unfolded state or before reaching the unfolded state, the unfolding pin (9) is separated from the arc-shaped abutting edge (31) and separated from the limiting device (3).

9. The folding and unfolding locking mechanism of the unmanned aerial vehicle wing according to claim 7, wherein the resetting device (6) is a torsion spring, the torsion spring is sleeved outside the rotating shaft (7), two driving ends of the torsion spring respectively abut against the surface of the wing (5) and the surface of the fixed seat (4), and the torsion spring has a tendency of driving the wing (5) to move towards the unfolding state.

10. The folding and unfolding locking mechanism of the unmanned aerial vehicle wing is characterized by further comprising a hook (10), wherein a groove (51) is formed in one end, close to the fixed seat (4), of the wing (5), the hook (10) is installed on the surface of the fixed seat (4), and when the wing (5) rotates to the unfolded state, the hook (10) is clamped in the groove (51), so that the wing (5) and the fixed seat (4) are fixedly connected.