UAV wing folding locking mechanism

Abstract

The present invention proposes a folding and spreading locking mechanism for unmanned aerial vehicles, comprising a fuselage, a driving device, a limiting device, a fixing seat, a wing and a reset device, wherein the driving device is fixedly mounted on the inner side of the fuselage, the fixing seat is rotatably mounted on the outer surface of the fuselage, the driving device drives the fixing seat to rotate, the rotation axis of the fixing seat is perpendicular to the length direction of the fuselage, a wing can be rotatably mounted on each fixing seat, the rotation axis of the wing is selectively perpendicular or parallel to the rotation axis of the fixing seat during the rotation of the fixing seat, the reset device is arranged on the fixing seat and can drive the wing to rotate around the fixing seat to a position where the plane where the wing is located is parallel to the rotation axis of the fixing seat, the limiting device is fixedly mounted on the outer surface of the fuselage, and the contact position between the wing and the limiting device is constantly changing during the process of the wing being converted from a folded state to an unfolded state. The present invention simplifies the driving structure, thereby making the wing unfold more quickly.

Description

Technical Field

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

[0002] With the continuous development of unmanned aerial vehicles, their application fields are also expanding, so the utilization rate of drones has been greatly improved. In the existing technology, drones have some structural defects that need to be overcome urgently.

[0003] Fixed-wing aircraft have the problem of occupying a large space, so they are inconvenient to carry and store. In order to solve this technical problem, a large number of folding-wing aircraft have appeared in the prior art. By folding the wings and storing them on the inner side or outer surface of the fuselage, the space occupancy rate of the aircraft is greatly reduced. However, the folded wings need to be unfolded in a controlled manner, which requires an additional wing unfolding or flipping structure. In order to simplify the wing unfolding drive structure as much as possible in the prior art, a torsion spring structure is often used for driving. The torsion spring is coaxially installed on the rotating shaft of the wing, which can greatly reduce the volume of the drive structure. However, simple rotary folding wings still have some structural defects. Since the wings are driven by torsion springs, the wings can only be arranged side by side after being folded, which greatly reduces the width of the wings and affects the flight power. If a stacked structure is used, it will affect the mechanical strength of the rotating part. In order to ensure both strength and power, the wings will occupy a large amount of space after being folded, and even reduce the space inside the aircraft. Therefore, there are wings on the market that can be folded and flipped at the same time. In this way, the wings can be installed on both sides of the aircraft without affecting each other, and can ensure the occupied space and flight performance at the same time.

[0004] However, using the flipping and folding methods at the same time will additionally increase the flipping drive structure and the folding drive structure, which will again cause problems with space occupancy. At the same time, more drive structures will also lead to lower reliability. Summary of the invention

[0005] In view of this, the present invention proposes a UAV wing folding locking mechanism with a simple driving structure, reasonable design, and relatively better reliability.

[0006] The technical solution of the present invention is implemented as follows: The present invention provides a UAV wing folding and locking mechanism, comprising:

[0007] The fuselage has a certain length and an inner cavity structure.

[0008] A driving device is arranged inside the fuselage to drive the wing to flip.

[0009] The limit device is used to assist the wing flipping and limit the posture of the wing during the flipping process.

[0010] The fixing seat is used to connect with the driving device and connect the wing to the fuselage.

[0011] The wing, as the flight power structure of the fuselage,

[0012] The reset device is used to assist the wing in unfolding and serves as the main driving power source for the wing unfolding.

[0013] The driving device is fixedly mounted on the inner side of the fuselage, and the fixing seat can be rotatably mounted on the outer surface of the fuselage. The driving device drives the fixing seat to rotate, and the rotation axis of the fixing seat is perpendicular to the length direction of the fuselage. A wing can be rotatably mounted on each fixing seat, and the rotation axis of the wing is selectively perpendicular or parallel to the rotation axis of the fixing seat during the rotation of the fixing seat. The reset device is arranged on the fixing seat and can drive the wing to rotate around the fixing seat to a position where the plane where the wing is located is parallel to the length direction of the fuselage and the plane where the wing is located is perpendicular to the rotation axis of the fixing seat. The limiting device is fixedly mounted on the outer surface of the fuselage. When the rotation axis of the wing is perpendicular to the length direction of the fuselage and the plane where the wing is located is perpendicular to the rotation axis of the fixing seat, the wing is in a folded state. When the rotation axis of the wing is parallel to the length direction of the fuselage and the plane where the wing is located is parallel to the rotation axis of the fixing seat, the wing is in an unfolded state. During the process of the wing being converted from the folded state to the unfolded state, the abutment position of the wing and the limiting device changes continuously.

[0014] On the basis of the above technical solution, preferably, the driving device includes: a motor, a transmission device and a transmission rod, the motor and the transmission device are fixedly installed on the inner side of the fuselage, the output shaft of the motor is connected to the transmission rod through the transmission device, the end of the transmission rod away from the transmission device is fixedly connected to the fixed seat, and the transmission rod and the rotating axis of the fixed seat are coaxially arranged.

[0015] On the basis of the above technical solution, preferably, the motor can be a common motor, a servo motor, a stepper motor and any other motor that can realize rotation drive in the prior art.

[0016] On the basis of the above technical solution, preferably, the transmission device is a reducer, the reducer includes an input end and an output end, the output shaft of the motor is transmission-connected to the input end of the reducer, and the output end of the reducer is transmission-connected to the transmission rod.

[0017] Preferably, the reducer is a worm gear reducer, and the output shaft of the motor is coaxially connected to the input end of the reducer, or is connected through a coupling to achieve rotational transmission.

[0018] On the basis of the above technical solution, preferably, a coupling is further included, wherein the output end of the reducer is connected to one end of a transmission rod through the coupling, and the end of the transmission rod away from the reducer is fixedly connected to a fixed seat.

[0019] More preferably, the number of the fixing seats is not less than two, the number of the output ends of the reducer, the transmission rods and the fixing seats is the same, and each output end of the reducer is transmission-connected to a fixing seat via a transmission rod.

[0020] On the basis of the above technical solution, preferably, it further comprises a bearing, wherein the bearing is fixedly mounted on the machine body and the bearing is coaxially sleeved on the outer side of the transmission rod.

[0021] On the basis of the above technical solution, preferably, it also includes a rotating shaft and a sleeve, the sleeve is fixedly mounted on the side of the fixing seat, the rotating shaft is fixedly mounted on the side of one end of the wing along the length direction, the rotating shaft is sleeved in the sleeve, and the wing rotates around the rotating shaft.

[0022] On the basis of the above technical solution, preferably, it also includes a deployment pin, which is fixedly mounted on the surface of the rotating shaft or the wing, and the limiting device includes an arcuate abutting edge, which is spirally shaped, and the opening direction of the spiral is the same as the rotation direction of the wing when it is unfolded. When the wing is in a folded state, the deployment pin abuts against the surface of the arcuate abutting edge, and when the wing rotates from a folded state to an unfolded state, the deployment pin slides along the arcuate abutting edge toward the opening direction of the spiral, and when the wing reaches the unfolded state or before the wing reaches the unfolded state, the deployment pin detaches from the arcuate abutting edge and separates from the limiting device.

[0023] On the basis of the above technical solution, preferably, the sleeve can also be fixedly installed on the side surface of one end of the wing along the length direction, the rotating shaft is fixedly installed on the side surface of the fixed seat, the rotating shaft is sleeved in the sleeve, and the wing rotates around the rotating shaft. Based on this solution, the deployment pin is fixedly installed on the surface of the sleeve or the wing.

[0024] On the basis of the above technical solution, preferably, the reset device is a torsion spring, which is sleeved on the outside of the rotating shaft, and the two driving ends of the torsion spring are respectively abutted against the wing surface and the fixed seat surface, and have a tendency to drive the wing to move toward the unfolded state.

[0025] On the basis of the above technical solution, preferably, it also includes a hook, a groove is opened at one end of the wing close to the fixing seat, the hook is installed on the surface of the fixing seat, and when the wing is rotated to the unfolded state, the hook is engaged in the groove, thereby fixing the wing and the fixing seat.

[0026] The UAV wing folding locking mechanism of the present invention has the following beneficial effects compared with the prior art:

[0027] (1) The present invention provides a wing folding and locking mechanism for a drone with a more reasonable structural design, so that the drive mechanism occupies less space. At the same time, the wing occupies less space when in a folded state, has little impact on the performance of the wing, and has a faster unfolding process. Specifically, the wing is folded and stored on the outer surface of the fuselage. When unfolding, the wing is unfolded as a whole while being flipped at an angle. The overall driving process is completed by a built-in drive mechanism. The overall structure is simple and occupies less space.

[0028] (2) The present invention associates the lateral expansion action of the wing with the angular rotation action of the wing, and realizes the linkage between the two by setting a limit device and a reset device. The reset device has the action tendency to expand the wing, and the specific expansion action range of the wing is limited by the limit device. The degree of limitation of the wing by the limit device is related to the angular rotation of the wing. Finally, the expansion range of the wing is achieved by adjusting the angle of the wing. Since the reset device does not need to be driven by additional electronic control equipment, the structure is simpler. (3) The present invention is also provided with a hook and a groove structure, so that the wing can be fixed after it is fully expanded, thereby ensuring the stability of the wing after expansion. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0030] Figure 1 It is an axonometric diagram of the wing folding and locking mechanism of the drone of the present invention;

[0031] Figure 2 for Figure 1 Exploded diagram of

[0032] Figure 3 It is a partial enlarged view of the wing folding and locking mechanism of the UAV of the present invention;

[0033] Figure 4 It is a partial enlarged view of the wing folding and locking mechanism of the UAV of the present invention;

[0034] Figure 5 It is a front view of the limiting device in the wing folding and locking mechanism of the drone of the present invention;

[0035] Figure 6 It is an exploded view of the rotating shaft and the sleeve part of the UAV wing folding and locking mechanism of the present invention.

[0036] In the figure: 1-fuselage, 2-driving device, 3-limiting device, 4-fixing seat, 5-wing, 6-resetting device, 21-motor, 22-transmission device, 23-transmission rod, 24-coupling, 25-bearing, 7-rotating shaft, 8-shaft sleeve, 9-expanding pin, 31-arc-shaped supporting edge, 10-hook, 51-groove. DETAILED DESCRIPTION

[0037] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0038] like Figure 1 As shown, combined Figure 2-6 As shown, the wing folding and locking mechanism of the unmanned aerial vehicle of the present invention comprises a fuselage 1, a driving device 2, a limiting device 3, a fixing seat 4, a wing 5 and a reset device 6, wherein the fuselage 1 is a cavity structure with a certain length, the driving device 2 is installed inside the fuselage 1, the fixing seat 4 is rotatably installed on the outer surface of the fuselage 1, the wing 5 is installed on the fixing seat 4 and can rotate relative to the fixing seat 4, the reset device 6 is arranged on the fixing seat 4, the limiting device 3 is fixedly installed on the outer surface of the fuselage 1, the rotation axis of the fixing seat 4 is perpendicular to the length direction of the fuselage 1, and the rotation axis of the wing 5 relative to the fixing seat 4 is perpendicular to the length direction of the fuselage 1. The wing 5 is perpendicular to the rotation axis of the fixing seat 4, and during the rotation of the fixing seat 4, the rotation axis of the wing 5 relative to the fixing seat 4 is selectively parallel or perpendicular to the length direction of the fuselage 1. When the rotation axis of the wing 5 is perpendicular to the length direction of the fuselage 1 and the plane where the wing 5 is located is perpendicular to the rotation axis of the fixing seat 4, the wing 5 is in a folded state. When the rotation axis of the wing 5 is parallel to the length direction of the fuselage 1 and the plane where the wing 5 is located is parallel to the rotation axis of the fixing seat 4, the wing 5 is in an unfolded state. During the process of the wing 5 being converted from the folded state to the unfolded state, the abutment position of the wing 5 and the limiting device 3 is continuously changed.

[0039] In the above embodiment, when the wing 5 is in the folded state, the limiting device 3 limits the wing 5, and the driving device 2 drives the fixing seat 4 to rotate. When the driving seat 4 rotates, it also drives the wing 5 connected to it to flip over. At this time, the positions of the fixing seat 4 and the wing 5 relative to the limiting device 3 are changed, thereby changing the limiting effect of the limiting device 3 on the wing 5. As the fixing seat 4 flips, the wing 5 is gradually unfolded by the action of the resetting device 6 and finally obtains the unfolded state. It can be seen that in the above embodiment, only one driving device 2 is located in the fuselage 1, which occupies little space in the fuselage 1, and the unfolding of the wing only needs to be controlled by the driving device 2. The structural design is reasonable. At the same time, since the wing is directly driven by the rotation of the fixing seat 4, the structure of the wing 5 itself will not be affected by the driving device 2, thereby not affecting the structural performance of the wing 5. In the folded state, the wing 5 occupies little space on the surface of the fuselage 1.

[0040] In a specific embodiment, the driving device 2 also 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 on the inner side of the fuselage 1. The output shaft of the motor 21 is connected to the transmission rod 23 through the transmission device 22. The end of the transmission rod 23 away from the transmission device 22 is fixedly connected to the fixed seat 4, and the transmission rod 23 is coaxially arranged with the rotation axis of the fixed seat 4.

[0041] In the above embodiment, the driving device 2 is used to drive the fixed seat 4 to rotate. As a specific and feasible driving structure, the fixed seat 4 is driven to rotate by the motor 21. Specifically, the output shaft of the motor 21 is connected to the transmission device 22, and the transmission device 22 drives the transmission rod 23 to rotate again. The end of the transmission rod 23 is fixed to the fixed seat 4 to achieve driving the fixed seat 4 to rotate. The transmission device 22 is used to convert the rotation direction of the motor 21 and transmit it to the fixed seat 4 through the transmission rod 23. Specifically, the transmission rod 23 passes through the shell of the fuselage 1 and is coaxially fixedly connected to the fixed seat 4.

[0042] In a specific embodiment, the transmission device 22 is a reducer, which includes an input end and an output end. The output shaft of the motor 21 is transmission-connected to the input end of the reducer, and the output end of the reducer is transmission-connected to the transmission rod 23 .

[0043] In the above embodiment, as a preferred embodiment, the transmission device 22 can be a reducer, specifically, a worm gear reducer. The reducer can change the direction of rotation and the speed ratio, and has a locking function, which has a certain auxiliary control effect on the stability of the wing 5 posture.

[0044] In the above technical scheme, as a specific feasible implementation method, the motor 21 can be a servo motor, a stepper motor, a brushless motor or other conventional motors that can provide rotational drive. As a preferred implementation method, the motor 21 is a servo motor, which can achieve precise angle control. After the wing 5 is fully unfolded, the wing can also be driven by the motor 21 to adjust the angle.

[0045] In a specific implementation, a coupling 24 is further included. The output end of the reducer is connected to one end of a transmission rod 23 through the coupling 24. The end of the transmission rod 23 away from the reducer is fixedly connected to a fixed seat.

[0046] In the above embodiments, the coupling 24 can avoid the problem of different axes of the two rotating shafts or poor matching between the axes during the rotation transmission process, thereby achieving the purpose of adapting to errors.

[0047] In a specific implementation, the number of the fixing seats 4 is not less than two, the number of the output ends of the reducer, the transmission rods 23 and the fixing seats 4 is the same, and each output end of the reducer is transmission-connected to a fixing seat 4 via a transmission rod 23 .

[0048] In the above embodiments, different numbers of wings 5 ​​are provided for different aircrafts. The present application can be used for aircrafts with different numbers of wings 5. By changing the signal of the reducer and the number of corresponding transmission rods 23, the coordination problem for different numbers of wings can be achieved.

[0049] In a specific implementation, a bearing 25 is further included. The bearing 25 is fixedly mounted on the fuselage 1 , and the bearing 25 is coaxially sleeved on the outer side of the transmission rod 23 .

[0050] In the above embodiments, the bearing 25 is used to perform transition connection at the connection position between the transmission rod 23 and the fuselage 1 , so as to ensure smooth rotation of the transmission rod 23 relative to the fuselage 1 .

[0051] In a specific implementation, it also includes a rotating shaft 7 and a sleeve 8. The sleeve 8 is fixedly mounted on the side of the fixing seat 4. The rotating shaft 7 is fixedly mounted on the side of one end of the wing 5 along the length direction. The rotating shaft 7 is sleeved in the sleeve 8, and the wing 5 rotates around the rotating shaft 7.

[0052] In the above embodiment, as one of the feasible connection modes for the rotation of the wing 5 relative to the fixing seat 4, the rotating shaft 7 and the shaft sleeve 8 are used to realize the rotation connection between the wing 5 and the fixing seat 4. Through the rotating shaft 7 and the shaft sleeve 8, the wing 5 and the fixing seat 4 can cooperate with each other to form a hinge-like structure.

[0053] In a specific embodiment, it also includes a deployment pin 9, which is fixedly mounted on the surface of the rotating shaft 7 or the wing 5. The limiting device 3 includes an arcuate supporting edge 31, and the arcuate supporting edge 31 is spiral. The opening direction of the spiral is the same as the rotation direction of the wing 5 when it is deployed. When the wing 5 is in a folded state, the deployment pin 9 is abutted against the surface of the arcuate supporting edge 31. When the wing 5 rotates from a folded state to an unfolded state, the deployment pin 9 slides along the arcuate supporting edge 31 toward the opening direction of the spiral. When the wing 5 reaches the unfolded state or before it reaches the unfolded state, the deployment pin 9 breaks away from the arcuate supporting edge 31 and is separated from the limiting device 3.

[0054] In the above embodiments, the arcuate abutting edge 31 is a structure on the surface of the limiting device 3, and does not limit the specific structure of the limiting device 3. As a specific embodiment, the arcuate abutting edge 31 can be one of the side surfaces of the groove provided on the surface of the limiting device 3, or one of the side surfaces of the through hole provided on the surface of the limiting device 3. When the wing 5 is in the folded state, the deployment pin 9 abuts against one point of the arcuate abutting edge 31. When the wing 5 rotates from the folded state to the deployed state, the deployment pin 9 moves from the position of the spiral of the arcuate abutting edge 31 close to the center of the circle to the position away from the center of the circle, and during this movement, the position of the arcuate abutting edge 31 abutting against the deployment pin 9 also changes. Since the distance between the arcuate abutting edge 31 and the deployment pin 9 increases during the rotation of the fixing seat 4, the limiting effect on the deployment pin 9 becomes weaker, so that the wing 5 is deployed under the resetting effect of the resetting device 6 until the deployment pin 9 is separated from the arcuate abutting edge 31 and separated from the limiting device 3, and the wing 5 reaches the deployed state.

[0055] It should be understood that, in another feasible implementation, the rotating shaft 7 can also be installed on the fixing seat 4 , and the shaft sleeve 8 is correspondingly installed on the wing 5 , and correspondingly, the deployment pin 9 is arranged on the wing 5 or the shaft sleeve 8 .

[0056] In a specific embodiment, the reset device 6 is a torsion spring, which is sleeved on the outside of the rotating shaft 7. The two driving ends of the torsion spring are respectively against the surface of the wing 5 and the surface of the fixing seat 4, and have a tendency to drive the wing 5 to move toward the unfolded state.

[0057] In the above embodiment, the torsion spring is sleeved on the outside of the rotating shaft 7, which occupies little space.

[0058] In a specific embodiment, a hook 10 is also included. A groove 51 is opened at one end of the wing 5 close to the fixing seat 4. The hook 10 is installed on the surface of the fixing seat 4. When the wing 5 is rotated to the unfolded state, the hook 10 is engaged in the groove 51, thereby fixing the wing 5 and the fixing seat 4.

[0059] In the above embodiments, the hook 10 is used to fix the wing 5 and the fixing seat 4. The driving force of the reset device 6 and the inclined surface of the hook 10 are used to drive the hook 10 to embed into the groove 51 to achieve the connection.

[0060] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A wing folding locking mechanism for a drone, characterized in that: include: A fuselage (1), a driving device (2), a limiting device (3), a fixing seat (4), a wing (5) and a reset device (6), wherein the driving device (2) is fixedly mounted on the inner side of the fuselage (1), the fixing seat (4) is rotatably mounted on the outer surface of the fuselage (1), the driving device (2) drives the fixing seat (4) to rotate, the rotation axis of the fixing seat (4) is perpendicular to the length direction of the fuselage (1), each fixing seat (4) is rotatably mounted with a wing (5), the rotation axis of the wing (5) is perpendicular to the rotation axis of the fixing seat (4) during the rotation of the fixing seat (4), and the reset device (6) is arranged on the fixing seat (4) and can drive the wing (5) to rotate around the fixing seat (4) rotating to a position where the plane where the wing (5) is located is parallel to the rotation axis of the fixing seat (4), the limiting device (3) is fixedly mounted on the outer surface of the fuselage (1), the rotation axis of the wing (5) is perpendicular to the length direction of the fuselage (1) and the plane where the wing (5) is located is perpendicular to the rotation axis of the fixing seat (4), the wing (5) is in a folded state, and the rotation axis of the wing (5) is parallel to the length direction of the fuselage (1) and the plane where the wing (5) is located is parallel to the rotation axis of the fixing seat (4), the wing (5) is in an unfolded state, and in the process of the wing (5) being transformed from the folded state to the unfolded state, the contact position between the wing (5) and the limiting device (3) is constantly changing; It also comprises a rotating shaft (7) and a shaft sleeve (8), wherein the shaft sleeve (8) is fixedly mounted on a side surface of a fixing seat (4), the rotating shaft (7) is fixedly mounted on a 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); It also comprises an unfolding pin (9), the unfolding pin (9) being fixedly mounted on the rotating shaft (7) or the surface of the wing (5); the limiting device (3) comprising an arcuate abutting edge (31), the arcuate abutting edge (31) being in a spiral shape, the opening direction of the spiral being the same as the rotation direction of the wing (5) when unfolded; when the wing (5) is in a folded state, the unfolding pin (9) abuts against the surface of the arcuate abutting edge (31); when the wing (5) rotates from the folded state to the unfolded state, the unfolding pin (9) slides along the arcuate abutting edge (31) toward the opening direction of the spiral; when the wing (5) reaches the unfolded state or before reaching the unfolded state, the unfolding pin (9) is separated from the arcuate abutting edge (31) and is separated from the limiting device (3); The reset device (6) is a torsion spring, which is sleeved on the outside of the rotating shaft (7). The two driving ends of the torsion spring are respectively abutted against the surface of the wing (5) and the surface of the fixing seat (4), and have a tendency to drive the wing (5) to move toward the unfolded state.

2. The UAV wing folding locking mechanism according to claim 1, characterized in that: The driving device (2) comprises: a motor (21), a transmission device (22) and a transmission rod (23); the motor (21) and the transmission device (22) are both fixedly mounted on the inner side of the machine body (1); the output shaft of the motor (21) is transmission-connected to the transmission rod (23) via the transmission device (22); one end of the transmission rod (23) away from the transmission device (22) is fixedly connected to a fixed seat (4); and the transmission rod (23) and the rotating shaft of the fixed seat (4) are coaxially arranged.

3. The UAV wing folding locking mechanism according to claim 2, characterized in that: The transmission device (22) is a reducer, which comprises an input end and an output end. The output shaft of the motor (21) is transmission-connected to the input end of the reducer, and the output end of the reducer is transmission-connected to the transmission rod (23).

4. The UAV wing folding locking mechanism according to claim 3, characterized in that: It also includes a coupling (24), wherein the output end of the reducer is connected to one end of a transmission rod (23) through the coupling (24), and the end of the transmission rod (23) away from the reducer is fixedly connected to a fixed seat.

5. The UAV wing folding locking mechanism according to claim 3, characterized in that: The number of the fixed seats (4) is not less than two, the number of the output ends of the reducer, the transmission rods (23) and the fixed seats (4) is the same, and each output end of the reducer is transmission-connected to a fixed seat (4) via a transmission rod (23).

6. The drone wing folding locking mechanism according to claim 2, characterized in that: It also includes a bearing (25), which is fixedly mounted on the machine body (1), and the bearing (25) is coaxially sleeved on the outer side of the transmission rod (23).

7. The UAV wing folding locking mechanism according to claim 1, characterized in that: The invention also comprises a hook (10), wherein a groove (51) is formed at one end of the wing (5) close to the fixing seat (4), and the hook (10) is mounted on the surface of the fixing seat (4). When the wing (5) is rotated to an unfolded state, the hook (10) is engaged in the groove (51), thereby fixing the wing (5) and the fixing seat (4).

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