Bidirectional folding wing unfolding mechanism

Abstract

The bidirectional folding wing unfolding mechanism is suitable for unfolding wings of a small unmanned aerial vehicle at a preset angle, the unmanned aerial vehicle comprises a control steering engine and folding wings, the wings are assembled on mounting shafts, and each wing comprises a connecting rod and an unfolding assembly arranged between the opposite faces of the two wings, one end of the connecting rod is connected with the rotating end of the control steering engine, the other end of the connecting rod is connected with the unfolding assembly, and the unfolding assembly can swing around the connecting rod under the action of the control steering engine so as to relieve limiting of the wings in the initial state and convert swing rotation into rotation of the wings around the mounting shaft; and the wings are limited after rotating by the maximum angle, so that the space occupied by the design is reduced, and the aircraft is more miniaturized.

Description

Technical Field

[0001] This invention belongs to the technical field of unmanned aerial vehicle (UAV) wing structures, and particularly relates to a bidirectional folding wing deployment mechanism. Background Technology

[0002] Modern drones are gradually developing towards lightweight, miniaturization, and integration. The wings usually need to have folding function to facilitate the storage and transportation of the fuselage, and to unfold quickly after leaving the box / tube, so as to provide sufficient aerodynamic force to ensure flight stability.

[0003] The prior art discloses a torsion spring driven UAV wing deployment mechanism in patent application number "CN 214986024 U". This structure drives the folding wing structure through a torsion spring and crank, and a pin can lock the relevant position. However, this patent occupies a large space in the longitudinal direction, the locking form of the pin is relatively simple, and there is room for further improvement in the mechanical structure design of the locking device.

[0004] The patent disclosed in the prior art with publication number "CN215622654U" discloses a wing folding and unfolding mechanism for a small folding-wing drone. The mechanism controls the unfolding of the wings 1 on both sides through a retainer, torsion spring, and annular cavity. However, the design of this structure is relatively complex, and the metal parts are relatively thin. The structural strength is greatly affected by the metal material. There is still room for improvement in terms of structural strength optimization and reliability design.

[0005] The prior art discloses a low-cost folding wing deployment mechanism with the use of a drive motor and worm gear to drive the wings to deploy. However, the structure of this patent occupies a large amount of fuselage space and is slow to open and close, which cannot meet the needs of rapid deployment. The opening and closing speed of the folding mechanism may be further improved.

[0006] Given the above situation, the performance of unmanned vehicles is reduced due to the large folding space and poor locking and limiting ability of ordinary folding wing deployment mechanisms. Summary of the Invention

[0007] In view of this, the bidirectional folding wing deployment mechanism of the present invention aims to solve the technical problem of low performance of existing UAV wing deployment.

[0008] A bidirectional folding wing deployment mechanism is disclosed, suitable for deploying the wings of a small unmanned aerial vehicle (UAV) at a preset angle. The UAV includes control servos and folding wings, which are mounted on a mounting shaft. The mechanism includes a connecting rod and a deployment assembly disposed between the two facing wing surfaces. One end of the connecting rod is connected to the rotating end of the control servo motor, and the other end is connected to the deployment assembly; Under the control of the servo motor, the deployment assembly can swing around the connecting rod to release the initial restriction on the wing, and convert the swing rotation into the rotation of the wing around the mounting axis, and then restrict the wing after the maximum rotation angle.

[0009] The beneficial effects of the present invention are as follows: Under the control of the servo motor, the deployment assembly can swing around the connecting rod to release the initial restriction on the wing and convert the swing rotation into the rotation of the wing around the mounting axis. After the maximum rotation angle, the wing is restricted. The deployment assembly is designed using the space between the two wings, reducing the space required for the design. No additional drive equipment is needed, and the manufacturing cost of the UAV can be reduced. At the same time, the mechanism has the characteristics of small folding space, stable folding restriction, accurate wing deployment angle, and rapid deployment. It can reduce the launch space in the launch state and meet the requirements of tube-type or box-type launch of UAVs. Attached Figure Description

[0010] To more clearly illustrate the technical solutions of the embodiments of this disclosure, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0011] Figure 1 A schematic diagram of the overall structural assembly; Figure 2 This is a bottom view of the upper wing; Figure 3 This is a top view of the lower wing; Figure 4 A diagram illustrating the installation of the pin; Figure 5 This is a schematic diagram of two guide ramps; Figure 6 A schematic diagram of the servo motor connection; Figure 7 A schematic diagram for assembling a torsion spring; Figure 8 This is an exploded view of the overall structure; Figure 9 An exploded view of an assembly of two springs; Figure 10 This is a schematic diagram showing the first pin's long end sliding on the first guide ramp and the second pin's long end sliding on the second guide ramp. 1. Control servo; 2. Mounting shaft; 3. Upper wing; 4. First clip; 5. First spring; 6. Center limit clamp; 7. Second guide ramp; 8. Lower wing; 9. Torsion spring; 10. First guide ramp; 11. Second clip; 12. Second spring; 14. First arc-shaped hole; 16. First limit hole; 17. Second arc-shaped hole; 19. Second limit hole; 21. Short end of second pin; 22. Long end of first pin; 23. Long end of second pin; 24. Short end of first pin; 25. Connecting rod; 26. First non-enclosed arc-shaped component; 27. Second non-enclosed arc-shaped component; 28. First arc-shaped groove; 29. ​​Second arc-shaped groove; 30. First arc-shaped notch; 31. Second arc-shaped notch. Detailed Implementation

[0012] The embodiments of this disclosure will now be described in detail with reference to the accompanying drawings.

[0013] The following specific examples illustrate the implementation of this disclosure. Those skilled in the art can easily understand other advantages and effects of this disclosure from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this disclosure, and not all of them. This disclosure can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this disclosure. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this disclosure, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this disclosure.

[0014] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this disclosure, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using other structures and / or functionalities besides one or more of the aspects set forth herein.

[0015] like Figures 1 to 10The illustrated bidirectional folding wing deployment mechanism is suitable for deploying the wings of small unmanned aerial vehicles (UAVs) at a preset angle (mostly for single use, with a maximum deployment angle of 65°, meaning each wing can rotate a maximum of 32.5° backwards). The UAV includes a control servo motor 1 and folding wings. The wings are mounted on a mounting shaft 2, and a wing-limiting component is provided at the top of the mounting shaft 2. Existing technology can be used for wing assembly and mounting shaft assembly, which will not be elaborated further. The core of this invention is to improve the existing structure between two wings, reducing the overall installation space, eliminating the need for additional devices, minimizing costs, and utilizing the structure between the wings to achieve folding and deployment. This includes a connecting rod 25 and a deployment assembly positioned between the opposing surfaces of the two wings. One end of the connecting rod 25 is connected to the rotating end of the control servo motor 1, and the other end is connected to the deployment assembly; Under the control of the servo motor 1, the deployment assembly can swing around the connecting rod 25 to release the initial restriction on the wing, and convert the swing rotation into the rotation of the wing around the mounting axis 2, and then restrict the wing after the maximum rotation angle.

[0016] In one embodiment, the drone includes an upper wing 3 and a lower wing 8 (see...). Figure 2 or Figure 3 The assembly shown has a circular shape at one end and a rectangular shape at the other. The unfolding component includes a central limiting clamp 6. One end of the connecting rod 25 is connected to the central limiting clamp 6, enabling the central limiting clamp 6 to swing axially along the mounting shaft 2. Figure 4 Using the placement as a reference, the two ends swing up and down, where, In the initial state, the upper wing 3, the lower wing 8, and the center limiting clamp 6 are all parallel to the fuselage of the UAV. The deployment component converts the swing of the center limiting clamp 6 into the rotation of the upper wing 3 and the lower wing 8 around the mounting axis 2 at a preset angle.

[0017] In one embodiment, a first non-closed arc-shaped component 26 is provided on the bottom surface of the circular end of the upper wing 3 (the inner ring size is larger than the size of the mounting hole in the central area of ​​the upper wing 3, and the outer ring size is smaller than the circular part of the wing), and a second non-closed arc-shaped component 27 is provided on the bottom surface of the circular end of the lower wing 8. The openings of the first non-closed arc-shaped component 26 and the second non-closed arc-shaped component 27 are staggered (matching the arc angle between the two torsion arms of the torsion spring 9, respectively used for the embedding of the two torsion arms of the torsion spring 9, and in the initial state, the torsion spring 9 is at its maximum torque to drive the two wings to move in opposite or backward directions). The first non-enclosed arc-shaped component 26 has a first arc-shaped hole 14 located away from the free end of the upper wing 3, and a first arc-shaped groove 28 located near the free end of the upper wing 3. Both the first arc-shaped hole 14 and the first arc-shaped groove 28 are mounting holes facing the upper wing 3. One end of the first arc-shaped groove 28 has a first limiting hole 16 (for limiting the upper wing in its initial state). The second non-enclosed arc-shaped component 27 has a second arc-shaped groove 29 located away from the free end of the lower wing 8, and a second arc-shaped hole 17 located near the free end of the upper wing 3. Both the second arc-shaped hole 17 and the second arc-shaped groove 29 are mounting holes facing the lower wing 8. The end of the second arc-shaped groove 29 that is not corresponding to the first arc-shaped groove 28 with the first limiting hole 16 has a second limiting hole 19.

[0018] Under the control of the servo motor 1, the unfolding component rotates along the "first arc-shaped hole 14, first arc-shaped groove 28" and "second arc-shaped hole 17, second arc-shaped groove 29", driving the upper and lower wings 8 to rotate around the mounting shaft 2. When it moves to the first limiting hole 16 and the second limiting hole 19, it stops rotating, that is, after achieving the maximum rotation angle of the wing rotation, it is limited. Preferably, the end of the first non-closed arc-shaped component 26 away from the free end of the upper wing 3 is provided with a tetrahedral cross section, and the other end near the free end of the upper wing 3 is provided with a convex arc surface. The end of the second non-closed arc-shaped component 27 away from the free end of the lower wing 8 is provided with a tetrahedral cross section (to increase the contact area of ​​the torsion arm and improve the wing rotation performance), and the other end near the free end of the lower wing 8 is provided with a convex arc surface (to prevent the torsion arm from coming off and to facilitate installation).

[0019] Furthermore, the first arc-shaped groove 28 and the second arc-shaped groove 29 have the same shape and size, and the first arc-shaped hole 14 and the second arc-shaped hole 17 have the same shape and size.

[0020] In one embodiment, the deployment assembly further includes a first pin, a second pin, a first guide ramp 10, and a second guide ramp 7. A hole is opened in the central area of ​​the center limiting clamp 6 for the mounting base to pass through. One end of the first pin is fixedly installed along its length, and the other end is fixedly installed with the second pin. The length of the first pin extending beyond the top surface of the center limiting clamp 6 is less than the length of the second pin extending beyond the top surface of the center limiting clamp 6, and the length of the first pin extending beyond the bottom surface of the center limiting clamp 6 is greater than the length of the second pin extending beyond the bottom surface of the center limiting clamp 6. By utilizing the length difference between the two pins on the same top or bottom surface of the center limiting clamp 6, the functions of wing limiting and rotation are achieved. This replaces the use of additional equipment in the prior art with minimal structural components, effectively reducing space and miniaturizing the structure as much as possible. The top surface of the first guide ramp 10 is adapted to the shape of the first arc-shaped hole 14 and fixed inside the first arc-shaped hole 14, and its length is less than the arc length of the first arc-shaped hole 14 (difference from the radius of the first pin). The bottom surface of the first guide ramp 10 is set in an arc-shaped shape, and one end is set in a semi-cylindrical shape, and the other end is set in a first arc-shaped notch 30 that can partially engage the first pin. The first arc-shaped notch 30 is far away from the tetrahedral section of the first non-closed arc-shaped member 26 (the cylindrical shape is adjacent to the tetrahedral section of the first non-closed arc-shaped member 26 to ensure that it can move in the opposite direction, that is, the direction of rotation of the two wings). In its initial state, the long end 22 of the first pin is limited by one end of the first arc-shaped notch 30 and the first arc-shaped hole 14, and slides along the inclined surface of the first guide ramp 10 to the semi-cylindrical bottom surface of the first guide ramp 10 under the swing of the central limiting clip 6; the short end 21 of the second pin (its end face is flat or round) slides from the first limiting hole 16 to the other end of the first arc-shaped groove 28 under the swing of the central limiting clip 6, so as to limit the final movement position of the short end 21 of the second pin. That is, the swing of the central limiting clip 6 can release the initial state limitation of the upper wing. After the limitation is released, under the restoring force of the torsion spring, the upper wing rotates around the mounting axis. The end of the first arc-shaped groove 28 away from the first limiting hole 16 is the maximum rotation angle of the wing. Therefore, if the two wings need to rotate at different angles, the arc length of the first arc-shaped groove 28 can be adjusted appropriately.

[0021] The principle is the same as above. The shape of the bottom surface of the second guide ramp 7 is adapted to the shape of the second arc-shaped hole 17 and fixed inside the second arc-shaped hole 17, and its length is less than the arc length of the second arc-shaped hole 17 (difference from the radius of the second pin). The top surface of the second guide ramp 7 is set in the shape of an arc surface, and one end of it is set in the shape of a semi-cylindrical shape, and the other end is set in the shape of a second arc-shaped notch 31 that can partially engage the second pin. The second arc-shaped notch 31 is far away from the tetrahedral section of the second non-closed arc-shaped member 27 (the cylindrical shape is adjacent to it). The second non-closed arc-shaped component 27 has a tetrahedral cross-section. In its initial state, the long end 23 of the second pin is limited by one end of the second arc-shaped notch 31 and the second arc-shaped hole 17. Under the swing of the central limiting clip 6, it slides along the inclined arc surface of the second guide ramp 7 to the top surface of the semi-cylindrical part of the second guide ramp 7. The short end 24 of the first pin slides from the second limiting hole 19 to the other end of the second arc-shaped groove 29 under the swing of the central limiting clip 6 to limit the short end 24 of the first pin.

[0022] In the above, the arc angles of the first arc-shaped hole 14 and the first arc-shaped groove 28 are both directed toward the center of the circular part of the upper wing, and the arc angles of the second arc-shaped hole 17 and the second arc-shaped groove 29 are both directed toward the center of the circular part of the upper wing, ensuring that the two wings can rotate in opposite directions.

[0023] In one embodiment, the unfolding assembly further includes a torsion spring 9, a first spring 5, a second spring 12, a first card 4, and a second card 11, wherein... The torsion spring 9 is mounted on the mounting shaft 2 in a manner that limits its axial position and allows it to rotate circumferentially (the assembly method when it is in the slot). When the torsion spring 9 is in maximum torsion, the two torsion arms of the torsion spring 9 are respectively embedded in the openings of the first non-closed arc-shaped part 26 and the second non-closed arc-shaped part 27. After the initial limit of the wing is released, it can provide the driving force to drive the two wings to rotate (contacting the quadrilateral section at one end of the closed arc-shaped part, storing or storing the maximum torque).

[0024] The first spring 5 is nested at the short end 21 of the second pin, and the bottom end of the first spring 5 is fixed on the central limiting clip 6. The top end of the first clip 4 with a central opening is fixed on it. The outer diameter of the first clip 4 is larger than the groove width of the first arc groove 28, and the inner diameter is slightly larger than the short end 21 of the second pin. When the control servo 1 drives the central limiting clip 6 to swing, the initial limiting of the upper wing 3 can be released. The long end 22 of the first pin slides along the arc-shaped inclined surface of the first guide ramp 10 in the first arc hole 14 and the short end 21 of the second pin slides along the first arc hole 14 (the swing of the central limiting clip 6 causes the short end 21 of the second pin to move out of the first limiting hole 16, and the restoring force of the torsion spring 9 drives the upper wing 3 to rotate). This can drive the first clip 4 to press down the first spring 5. The first spring 5 can press down the central limiting clip 6 to keep it tilted and maintain the wing's unfolded position. At the same time, it can also provide a restoring force to facilitate the folding or retraction of the wing. The second spring 12 is nested at the short end 24 of the first pin, and the top end of the second spring 12 is fixed to the center limiting clip 6. Its bottom end is fixed to the second card 11 with a central opening. The outer diameter of the second card 11 is larger than the width of the second arc-shaped groove 29, and its inner diameter is slightly larger than the short end 24 of the first pin. When the control servo 1 drives the center limiting clip 6 to swing, the initial limiting of the lower wing 8 can be released. The long end 23 of the second pin moves along the second guide ramp 7 within the second arc-shaped hole 17. The curved inclined surface slides and the short end 24 of the first pin slides along the second curved hole 17 (the swing of the center limiting clip 6 causes the short end 24 of the first pin to move out of the second limiting hole 19, and the restoring force of the torsion spring 9 drives the lower wing 8 to rotate), which can drive the second card 11 to press down the second spring 12. The second spring 12 can press down the center limiting clip 6 to keep it tilted (it is always parallel to the fuselage), maintain the wing in the deployed state, and at the same time, provide a restoring force to facilitate the folding or retraction of the wing.

[0025] In one embodiment, the system also includes an outer jacket. The central region of the outer jacket has a waist-shaped hole (clear fit, not affecting the swing of the central limiting clip 6) adapted to the shape of the central limiting clip 6 to prevent dust from entering. It also serves to block lateral impacts, prevent uneven wear, and protect the core mechanism. The size of the opening in the central region of the central limiting clip 6 is larger than the size of the opening at the wing mounting end, without affecting the swing of the central limiting clip 6. For example, the outer circumferential dimension of the outer jacket is larger than the outer circumferential dimension of the first non-closed arc-shaped member 26, but smaller than the outer ring dimension of the circular portion of the upper wing 3 or the lower wing 8.

[0026] Secondly, a small drone is provided, which is equipped with the aforementioned bidirectional folding wing deployment mechanism, significantly reducing the design space required for the drone and improving its miniaturization performance.

[0027] The above are merely specific embodiments of this disclosure, but the scope of protection of this disclosure is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this disclosure should be included within the scope of protection of this disclosure. Therefore, the scope of protection of this disclosure should be determined by the scope of the claims.

Claims

1. A bidirectional folding wing deployment mechanism, suitable for deploying the wings of a small unmanned aerial vehicle (UAV) at a preset angle, the UAV including a control servo motor and a folding wing, the wing being mounted on a mounting shaft, characterized in that, This includes a connecting rod and a deployment assembly positioned between the opposing surfaces of the two wings, wherein... One end of the connecting rod is connected to the rotating end of the control servo motor, and the other end is connected to the deployment assembly; Under the control of the servo motor, the deployment assembly can swing around the connecting rod to release the initial restriction on the wing, and convert the swing rotation into the rotation of the wing around the mounting axis, and then restrict the wing after the maximum rotation angle.

2. The bidirectional folding wing deployment mechanism according to claim 1, characterized in that, The drone includes an upper wing and a lower wing. The deployment assembly includes a central limiting clamp. One end of the connecting rod is connected to the central limiting clamp, enabling the central limiting clamp to swing axially along the mounting axis. In the initial state, the upper wing, lower wing, and center limiting clamp are all parallel to the fuselage of the UAV. The deployment assembly converts the swing of the center limiting clamp into the rotation of the upper wing and lower wing around the installation axis at a preset angle.

3. The bidirectional folding wing deployment mechanism according to claim 2, characterized in that, The bottom surface of the rounded end of the upper wing is provided with a first non-closed arc-shaped component, and the bottom surface of the rounded end of the lower wing is provided with a second non-closed arc-shaped component. The openings of the first non-closed arc-shaped component and the openings of the second non-closed arc-shaped component are staggered. The first non-closed arc-shaped component has a first arc-shaped hole at a position away from the free end of the upper wing and a first arc-shaped groove at a position close to the free end of the upper wing. Both the first arc-shaped hole and the first arc-shaped groove face the mounting hole opened on the upper wing. A first limiting hole is opened at one end of the first arc-shaped groove. The second non-closed arc-shaped component is provided with a second arc-shaped groove at a position away from the free end of the lower wing, and a second arc-shaped hole is provided at a position close to the free end of the upper wing. Both the second arc-shaped hole and the second arc-shaped groove face the mounting hole opened on the lower wing. The second arc-shaped groove and the first arc-shaped groove are provided with a second limiting hole at the end that is not provided with the first limiting hole.

4. The bidirectional folding wing deployment mechanism according to claim 3, characterized in that, The first non-closed arc-shaped component has a tetrahedral cross-section at one end away from the free end of the upper wing and a convex arc surface at the other end adjacent to the free end of the upper wing. The second non-closed arc-shaped component has a tetrahedral cross-section at one end away from the free end of the lower wing, and a convex arc surface at the other end adjacent to the free end of the lower wing.

5. The bidirectional folding wing deployment mechanism according to claim 3, characterized in that, The first arc-shaped groove and the second arc-shaped groove have the same shape and size, and the first arc-shaped hole and the second arc-shaped hole have the same shape and size.

6. The bidirectional folding wing deployment mechanism according to claim 4, characterized in that, The unfolding assembly further includes a first pin, a second pin, a first guide ramp, and a second guide ramp. The central limiting clamp has an opening in its central region for the mounting base to pass through. One end of the first pin is fixedly installed along its length, and the other end is fixedly installed with the second pin. The length of the first pin extending beyond the top surface of the central limiting clamp is less than the length of the second pin extending beyond the top surface of the central limiting clamp, and the length of the first pin extending beyond the bottom surface of the central limiting clamp is greater than the length of the second pin extending beyond the bottom surface of the central limiting clamp. The shape of the top surface of the first guide ramp is adapted to the shape of the first arc-shaped hole and fixed inside the first arc-shaped hole, and its length is less than the arc length of the first arc-shaped hole. The bottom surface of the first guide ramp is set in an arc-shaped shape, and one end of it is set in a semi-cylindrical shape, and the other end is set in a first arc-shaped notch that can partially engage the first pin. The first arc-shaped notch is far away from the tetrahedral cross-section of the first non-closed arc-shaped component. The short end of the second pin slides from the first limiting hole to the other end of the first arc-shaped groove under the swing of the central limiting clip to limit the short end of the second pin. The shape of the bottom surface of the second guide ramp is adapted to the shape of the second arc-shaped hole and fixed inside the second arc-shaped hole, and its length is less than the arc length of the second arc-shaped hole. The top surface of the second guide ramp is set in the shape of an arc surface, and one end of it is set in the shape of a semi-cylindrical shape, and the other end is set in the shape of a second arc-shaped notch that can partially engage the second pin. The second arc-shaped notch is far away from the tetrahedral cross-section of the second non-closed arc-shaped component. In the initial state, the long end of the second pin is limited by the second arc-shaped notch and one end of the second arc-shaped hole. Under the swing of the central limiting clip, it slides along the arc surface of the second guide ramp to the top surface of the semi-cylindrical part of the second guide ramp. Under the swing of the central limiting clip, the short end of the first pin slides from the second limiting hole to the other end of the second arc-shaped groove to limit the short end of the first pin.

7. The bidirectional folding wing deployment mechanism according to claim 6, characterized in that, The unfolding assembly further includes a torsion spring, a first spring, a second spring, a first card, and a second card, wherein, The torsion spring is mounted on the mounting shaft in a manner that limits its axial position and allows it to rotate circumferentially. When the torsion spring is in maximum torsion, the two torsion arms of the torsion spring are respectively embedded in the openings of the first non-closed arc-shaped component and the second non-closed arc-shaped component. After the initial limiting of the wing is released, it can provide a driving force to drive the two wings to rotate. The first spring is nested at the short end of the second pin, and the bottom end of the first spring is fixed on the center limiting clip. The top end of the spring is fixed on the first card with a central opening. The diameter of the first card is larger than the width of the first arc groove. When the control servo drives the center limiting clip to swing, the initial limit of the upper wing can be released. The long end of the first pin slides along the arc-shaped inclined surface of the first guide ramp in the first arc hole, and the short end of the second pin slides along the first arc hole, so as to keep the tilt and maintain the wing in the unfolded position. At the same time, it can also provide a restoring force to facilitate the folding or retraction of the wing. The second spring is nested at the short end of the first pin, and the top end of the second spring is fixed to the center limiting clip. Its bottom end is fixed to the second card with a central opening. The diameter of the second card is larger than the width of the second arc-shaped groove. When the control servo drives the center limiting clip to swing, the initial limiting of the lower wing can be released. The long end of the second pin slides along the arc-shaped inclined surface of the second guide ramp in the second arc-shaped hole, and the short end of the first pin slides along the second arc-shaped hole. This can drive the second card to press down on the second spring. The second spring can press down on the center limiting clip to keep it tilted and maintain the wing in the deployed state. At the same time, it can also provide a restoring force to facilitate the folding or retraction of the wing.

8. The bidirectional folding wing deployment mechanism according to claim 7, characterized in that, It also includes an outer cover, the central area of ​​which has a waist-shaped hole that matches the shape of the central limiting clip. This hole is used to block dust from entering and also serves to block lateral impacts and prevent uneven wear.

9. The bidirectional folding wing deployment mechanism according to claim 8, characterized in that, The outer circumferential dimension of the outer jacket is greater than the outer circumferential dimension of the first non-closed arc-shaped component or the second non-closed arc-shaped component, and smaller than the outer ring dimension of the circular portion of the upper wing or the lower wing.

10. A small unmanned aerial vehicle, characterized in that, It is provided with a bidirectional folding wing deployment mechanism as described in any one of claims 1 to 9.

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