Wing folding and unfolding device and unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a wing folding and unfolding device and an unmanned aerial vehicle, the wing folding and unfolding device comprises two wings, an elastic piece and a locking piece, the two wings are arranged in a staggered mode, the wings are configured to be connected with corresponding target installation pieces, the wings can rotate relative to the target installation pieces, and the locking piece is connected with the elastic piece. The folding mechanism is used for switching between a folding position and an unfolding position; the elastic piece is respectively connected with the two wings and is used for providing elastic acting force for the two wings, so that the wings have the tendency of rotating from the folding position to the unfolding position; the locking pieces are respectively connected with the corresponding wings and the target mounting piece, and the locking pieces are used for locking the wings rotating to the unfolding position. The wing folding and unfolding device and the unmanned aerial vehicle are simple in structure, high in space utilization rate, small in size, light in weight and high in wing synchronism and reliability.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a wing retractable and deployable device and a UAV. Background Art

[0002] In emergency rescue missions for natural disasters such as earthquakes, floods, and mudslides, timely delivery of emergency supplies is difficult due to the destruction of transportation routes. This leads to a shortage of emergency supplies in the affected areas, affecting the survival of the victims and the rescue capabilities of rescue workers. Therefore, air delivery has become the primary means of providing emergency relief supplies in the early stages.

[0003] Airdrop is a primary method of aerial delivery. Compared to air transport, which requires well-established airport facilities in disaster-stricken areas, it can deliver supplies to areas without runways or with poor runway conditions, making it more flexible and convenient. For example, a transport aircraft transports a drone to a drop zone and releases it. The drone then glides to the target area, where rescue workers and disaster-stricken residents receive the supplies in its cargo hold.

[0004] In the early stages of emergency rescue, there is a great demand for a large amount of supplies. To meet this demand, some existing gliding drones are equipped with wings that can be folded and unfolded. When a transport aircraft is transporting the drone, the wings are folded to reduce the size of the drone and increase the loading capacity of the transport aircraft; when the drone is deployed, the wings are unfolded for gliding.

[0005] Conventional gliding drones often use motors or servos to control the wing's rotation, folding, and unfolding. To ensure synchronized wing rotation, the transmission components between the actuator and the wing are complex, making the entire wing's folding and unfolding mechanism bulky and heavy, impacting drone performance. Summary of the Invention

[0006] To this end, the technical problem to be solved by the present invention is to overcome the problem that the existing wing extension and retraction device is large and heavy, which affects the performance of the UAV, and to provide a wing extension and retraction device and a UAV with a simple structure, high space utilization, small size, light weight, and high wing synchronization and reliability.

[0007] In a first aspect, the utility model provides a wing folding and unfolding device, comprising a wing, wherein two wings are provided, the two wings are staggered, the wings are configured to be connected to corresponding target mounting parts, and the wings can rotate relative to the target mounting parts to switch between a folded position and an unfolded position; an elastic member, wherein the elastic member is respectively connected to the two wings, and the elastic member is used to provide an elastic force for the two wings so that the wings have a tendency to rotate from the folded position to the unfolded position; and a locking member, wherein the locking member is respectively connected to the corresponding wing and the target mounting part, and the locking member is used to lock the wing rotated to the unfolded position.

[0008] In one embodiment of the present invention, the locking member includes a locking seat, which is fixedly connected to the target mounting member, and a locking hole is provided on the locking seat; and a locking pin, which includes a pin seat, a pin body and an elastic component; the pin seat is connected to the wing, and a mounting hole is provided on the pin seat, and the pin body is movably arranged in the mounting hole, and the elastic component is arranged in the mounting hole, and the elastic component is used to provide an elastic force for the pin body so that the pin body has a tendency to extend out of the mounting hole; wherein, when the wing is not rotated to the deployed position, the pin body is separated from the locking hole; when the wing is rotated to the deployed position, the pin body is inserted into the locking hole to lock the wing.

[0009] In one embodiment of the present invention, a guide groove is further provided on the locking seat, and the guide groove is connected to the mounting hole; wherein, when the wing is not rotated to the deployed position, the pin body abuts against the guide groove, and the pin body can slide relative to the guide groove.

[0010] In one embodiment of the present invention, a guide portion is provided on the end of the pin body facing away from the wing, wherein the diameter of the guide portion gradually decreases along the end facing away from the locking seat toward the locking seat.

[0011] In one embodiment of the present invention, the two wings rotate in opposite directions.

[0012] In one embodiment of the present invention, the elastic member is rotatably connected to the two wings respectively.

[0013] In one embodiment of the present invention, the wing is configured as a symmetrical structure; or / and the locking member is configured as a symmetrical structure.

[0014] In a second aspect, the utility model also provides a drone, comprising a body, the body being provided with an open cavity; and a cover, the cover being detachably connected to the body, the cover closing the opening of the open cavity, the cover being provided with a target mounting part, the target mounting part being provided with a wing retraction and extension device as described above.

[0015] In one embodiment of the present invention, the target mounting member is configured as a mounting rod, and two mounting rods and two wing retraction and extension devices are provided, and the two mounting rods are arranged in parallel and spaced apart; along the axial direction of the mounting rod, the two wing retraction and extension devices are arranged in sequence; in each of the wing retraction and extension devices, the two wings are connected to the two mounting rods in a one-to-one correspondence, wherein the rotation directions of the two wings on each mounting rod are opposite.

[0016] In one embodiment of the present invention, a binding member is further included, and the binding member is used to bind the wings so as to keep the wings in the folded position.

[0017] The above technical solution of the utility model has the following beneficial effects compared with the prior art:

[0018] The wing retraction and deployment device described in the present invention, by providing an elastic member, causes the elastic member to apply an elastic force to the wing to drive the wing to rotate. On the one hand, it can effectively replace the conventional drive motor, realize synchronous drive of the wing, and ensure high synchronization when the wing rotates. On the other hand, the elastic member is relatively small in size, has high space utilization, is light in weight, and has a simple overall structure. It can reduce the total weight of the drone, facilitate the drone to load more rescue supplies, and improve the performance of the drone. At the same time, by providing a locking member to lock the wing in the deployed position, the deployment of the wing is more stable and reliable. In addition, the elastic force applied by the elastic member to the wing can also prevent the wing from rotating to the retracted position after deployment to a certain extent, further improving the overall reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to make the content of the present invention more clearly understood, the present invention is further described in detail below based on the specific embodiments of the present invention and in conjunction with the accompanying drawings, wherein:

[0020] Figure 1 This is a structural diagram of the wing retracting and extending device when the wings are in the retracted position in a preferred embodiment of the present invention;

[0021] Figure 2 This is a schematic structural diagram of the wing retracting and extending device in a preferred embodiment of the present invention when the wing is in the extended position;

[0022] Figure 3This is one of the structural diagrams of the locking member in the preferred embodiment of the present utility model;

[0023] Figure 4 This is one of the cross-sectional structural diagrams of the locking member in the preferred embodiment of the present utility model;

[0024] Figure 5 This is the second structural diagram of the locking member in the preferred embodiment of the present utility model;

[0025] Figure 6 This is the second schematic cross-sectional view of the locking member in the preferred embodiment of the present utility model;

[0026] Figure 7 This is a schematic diagram of the connection structure of the elastic member in the preferred embodiment of the present utility model;

[0027] Figure 8 This is one of the cross-sectional structural diagrams of the UAV in the preferred embodiment of the present utility model;

[0028] Figure 9 This is the second schematic cross-sectional view of the UAV in the preferred embodiment of the present utility model;

[0029] Figure 10 Schematic diagram of the structure of the UAV in the preferred embodiment of the present invention.

[0030] Explanation of the reference numerals in the specification: 10, wing; 11, mounting seat; 111, servo; 12, wing body; 121, main wing; 122, flaperon; 12a, first wing; 12b, second wing; 12c, third wing; 12d, fourth wing; 20, elastic member; 21, tension spring; 22, connecting member; 30, locking member; 31, locking seat; 311, locking hole; 312, guide groove; 32, locking pin; 321, pin seat; 3211, mounting hole; 322, pin body; 3221, guide portion; 323, elastic member; 41, fuselage; 411, opening cavity; 42, cover; 421, mounting rod; 421a, first rod; 421b, second rod; 50, binding member. DETAILED DESCRIPTION

[0031] The present invention will be further described below with reference to the accompanying drawings and specific embodiments so that those skilled in the art can better understand the present invention and implement it. However, the embodiments are not intended to limit the present invention.

[0032] Reference Figure 1 and Figure 2 As shown, the utility model discloses a wing retracting and extending device, comprising a wing 10 , an elastic member 20 and a locking member 30 .

[0033] Wings 10 are used to achieve gliding. Each wing retractable device is equipped with two wings 10, and the two wings 10 are staggered to facilitate folding and unfolding. The wings 10 are configured to connect to corresponding target mounting parts, wherein the wings 10 can rotate relative to the target mounting parts to switch between a folded position and an unfolded position. Those skilled in the art can adjust the rotation direction of the wings 10 relative to their target mounting parts according to actual needs. For example, in the same wing retractable device, the two wings 10 rotate in the same direction. Preferably, for example, using the device as an example, when the device is installed on a gliding drone, when the wings 10 are in the folded position, the wings 10 rotate relative to each other until their length is parallel to the length of the drone, thereby reducing the overall size of the drone, improving space utilization, and facilitating transport operations by transport aircraft. When the wings 10 are in the unfolded position, the wings 10 rotate relative to each other until their length is perpendicular to the length of the drone, enabling gliding.

[0034] The elastic member 20 is used to replace the conventional drive motor to achieve synchronous drive for the wings 10. Specifically, in each wing retraction and extension device, the elastic member 20 is respectively connected to the two wings 10 and provides an elastic force for the two wings 10 so that the wings 10 have a tendency to rotate from the folded position to the deployed position. Those skilled in the art can set the elastic member 20 according to actual needs. For example, when both wings 10 are in the folded position, the elastic member 20 is in a compressed state. After the force preventing the wings 10 from rotating is removed, the elastic member 20 recovers and pushes the wings 10 to rotate so that the wings 10 rotate to the deployed position; or, when both wings 10 are in the folded position, the elastic member 20 is in a stretched state. After the external force preventing the wings 10 from rotating is removed, the elastic member 20 recovers and pulls the wings 10 to rotate so that the wings 10 rotate to the deployed position. By providing elastic members 20, which apply an elastic force to wings 10 to drive their rotation, the elastic members 20 effectively replace conventional drive motors, achieving synchronous drive of wings 10 and ensuring high synchronization during their rotation. Furthermore, the elastic members 20 are relatively small, offer high space utilization, are lightweight, and have a simple overall structure. This reduces the drone's overall weight, facilitates loading of more rescue supplies, and improves its performance. Furthermore, the elastic force applied by the elastic members 20 to the wings 10 also prevents them from rotating to their retracted position after deployment, effectively improving overall reliability.

[0035] Locking members 30 are connected to the corresponding wing 10 and the target mounting member, respectively, and are used to lock the wing 10 in the deployed position. By providing locking members 30 to lock the wing 10, deployment of the wing 10 is more stable and reliable, allowing the wing 10 to glide smoothly. Those skilled in the art can configure locking members 30 according to actual needs, such as locking hooks. Accordingly, when the wing 10 is in the retracted position, those skilled in the art can configure corresponding components according to actual needs to apply force to the wing 10 and prevent its rotation, which will not be described in detail here.

[0036] The wing retraction and deployment device described in the present invention, by providing an elastic member 20, applies an elastic force to the wing 10 to drive the wing 10 to rotate. On the one hand, it can effectively replace the conventional drive motor to achieve synchronous drive of the wing 10, ensuring high synchronization when the wing 10 rotates. On the other hand, the elastic member 20 is relatively small in size, has high space utilization, is light in weight, and has a simple overall structure. It can reduce the total weight of the drone, facilitate the drone to load more rescue supplies, and improve the performance of the drone. At the same time, by providing a locking member 30 to lock the wing 10 in the deployed position, the deployment of the wing 10 is more stable and reliable. In addition, the elastic force applied by the elastic member 20 to the wing 10 can also, to a certain extent, prevent the wing 10 from rotating to the retracted position after deployment, further improving the overall reliability.

[0037] Reference Figure 2 As shown, preferably, the wing 10 includes a mounting seat 11 and a wing body 12. The mounting seat 11 is used to rotate and connect to the target mounting member; the wing body 12 is connected to the mounting seat 11, and the wing body 12 is used to achieve gliding. Among them, the wing body 12 includes a main wing 121 and a flaperon 122, the main wing 121 is fixedly connected to the mounting seat 11, and the flaperon 122 is rotatably connected to the main wing 121, so that during the gliding process, the gliding attitude is adjusted by rotating the flaperon 122 relative to the main wing 121 to ensure that it finally lands in the target delivery area. Exemplarily, a servo 111 is provided on the mounting seat 11, and the driving end of the servo 111 is connected to the flaperon 122 to drive it to rotate relative to the main wing 121. Preferably, a spring is connected to the mounting seat 11.

[0038] Reference Figure 3 、 Figure 4 、 Figure 5 and Figure 6As shown, in the wing retraction and deployment device described in the present invention, in some embodiments, the locking member 30 includes a locking seat 31 and a locking pin 32. The locking seat 31 is fixedly connected to the target mounting member. A locking hole 311 is provided on the locking seat 31 to cooperate with the locking pin 32 to achieve locking of the wing 10. The locking pin 32 includes a pin seat 321, a pin body 322 and an elastic component 323. The pin seat 321 is connected to the wing 10; preferably, the pin seat 321 is connected to the mounting seat 11. A mounting hole 3211 is provided on the pin seat 321, and the pin body 322 is movably arranged in the mounting hole 3211. The elastic component 323 is arranged in the mounting hole 3211, and the elastic component 323 is used to provide an elastic force to the pin body 322 so that the pin body 322 has a tendency to extend out of the mounting hole 3211. Preferably, the elastic component 323 is set as a spring. When the wing 10 is not rotated to the deployed position, the pin 322 is disengaged from the locking hole 311, allowing the wing 10 to rotate relative to the target mounting member. When the wing 10 is rotated to the deployed position, the pin 322 is inserted into the locking hole 311 to lock the wing 10 and prevent rotation. This structure effectively locks the wing 10, while maintaining a simple overall structure, compact size, and light weight. Preferably, those skilled in the art can adjust the relative position of the locking hole 311 according to actual needs to adjust the sweep angle of the wing 10.

[0039] Reference Figure 3 As shown, in some embodiments of the wing retraction and deployment device of the present invention, a guide slot 312 is further provided on the locking seat 31. The guide slot 312 communicates with the mounting hole 3211 and serves to guide and retain a pin 322. When the wing 10 is not rotated to the deployed position, the pin 322 abuts against the guide slot 312 and can slide relative to the guide slot 312. When the wing 10 is rotated to the deployed position, the pin 322 disengages from the guide slot 312 and inserts into the locking hole 311, locking the wing 10. This structure effectively enhances the stability and reliability of the device.

[0040] Further, refer to Figure 4 As shown, the locking member 30 is configured as a symmetrical structure to increase versatility and facilitate interchangeability between the locking members 30 of the two wings 10 by changing the installation method during assembly and maintenance. For example, the locking seat 31 is configured as a plate-like structure, with a locking hole 311 extending through the locking seat 31, and guide grooves 312 are provided on two opposing surfaces of the locking seat 31.

[0041] Further, refer to Figure 4As shown, in some embodiments of the wing retraction and deployment device of the present invention, a guide portion 3221 is provided on the end of the pin body 322 facing away from the wing 10. The diameter of the guide portion 3221 gradually decreases toward the locking seat 31 from the end facing away from the locking seat 31, forming a cone-like structure. The provision of the guide portion 3221 facilitates the insertion of the pin body 322 into the locking hole 311, achieving rapid locking of the wing 10.

[0042] Reference Figure 2 As shown, in some embodiments of the wing retraction and deployment device of the present invention, the two wings 10 rotate in opposite directions. Compared to rotating in the same direction, counter-rotating wings 10 can reduce the possibility of interference between the two wings 10. In a drone equipped with two target mountings and four wings 10, the relative positions of the wings 10 relative to the target mountings can also be adjusted to improve the stability of the drone.

[0043] Reference Figure 7 As shown, in some embodiments of the wing retraction and deployment device of the present invention, elastic members 20 are rotatably connected to the two wings 10. Preferably, the elastic members 20 are configured as tension springs 21, each end of which is fixedly connected to a corresponding connecting member 22, which is rotatably connected to the mounting base 11. This structure allows for smoother rotation of the wings 10, allowing for rapid deployment and gliding.

[0044] In some embodiments of the wing retraction and deployment device described in the present invention, the wing 10 is set to a symmetrical structure, which facilitates the interchange of the wings 10 between different devices and the interchange of the wings 10 in the same device, improves the maintenance and assembly efficiency, and reduces production costs.

[0045] Reference Figure 8 、 Figure 9 and Figure 10As shown, the present invention discloses a drone, comprising a body 41 and a canopy 42. The body 41 is provided with an open cavity 411, which is used to accommodate supplies or wings 10. The canopy 42 is detachably connected to the body 41, and those skilled in the art can set the method of detachable connection between the canopy 42 and the body 41 according to actual needs. When the canopy 42 is set on the body 41, the canopy 42 closes the opening of the open cavity 411. A target mounting part is provided on the canopy 42, and a wing retraction and extension device as described in any of the above embodiments is provided on the target mounting part. Those skilled in the art can set the number, installation position, etc. of the wing retraction and extension devices according to actual needs; illustratively, four target mounting parts and two wing retraction and extension devices are provided on the canopy 42, and each target mounting part is correspondingly provided with a wing 10. Since the drone described in the present invention includes the wing retraction and extension device described in the above embodiments, the drone also has all the beneficial effects thereof, which will not be repeated here.

[0046] Preferably, when not in use, the wings 10 are folded and placed in the opening 411 of the body 41 to reduce the size of the entire drone, facilitate storage, and effectively protect the wings 10. When supplies are required for airdrop, the canopy 42 and body 41 are disassembled and separated, the corresponding supplies are loaded into the opening 411 of the body 41, and then the canopy 42 and body 41 are reassembled. Next, the drones are loaded in a cluster, such as by a transport aircraft, and transported to the airdrop area for release. The wings 10 of the released drone are rotated and unfolded by the elastic force of the elastic member 20 to glide.

[0047] Reference Figure 10 As shown, in the drone described in the utility model, in some embodiments, the target mounting part is set as a mounting rod 421, and two mounting rods 421 and two wing retracting and extending devices are provided. The two mounting rods 421 are arranged in parallel and spaced apart. Preferably, the arrangement direction of the two mounting rods 421 is parallel to the length direction of the body 41. Preferably, the length of the wing 10 is less than the distance between the two mounting rods 421, so that the wing 10 can be folded and unfolded smoothly. The two wing retracting and extending devices are arranged in sequence along the axial direction of the mounting rod 421 to prevent the wings 10 and the elastic member 20 from interfering with each other. In each wing retracting and extending device, the two wings 10 are connected to the two mounting rods 421 in a one-to-one correspondence, and the two wings 10 on each mounting rod 421 have opposite rotation directions.

[0048] To facilitate the separation of the mounting rods 421 and wings 10, the two mounting rods 421 are designated as a first rod 421a and a second rod 421b, with the first rod 421a being relatively close to the head of the fuselage 41 and the second rod 421b being relatively close to the tail of the fuselage 41. The two wings 10 of one wing retractable device are designated as a first wing 12a and a second wing 12b, and the two wings 10 of the other wing retractable device are designated as a third wing 12c and a fourth wing 12d. The following configurations are included:

[0049] The first wing 12a, the second wing 12b, the third wing 12c and the fourth wing 12d are sequentially arranged in a direction away from the cover 42. The first wing 12a and the fourth wing 12d are arranged on the first rod 421a, and the second wing 12b and the third wing 12c are arranged on the second rod 421b.

[0050] Alternatively, the first wing 12a, the second wing 12b, the third wing 12c and the fourth wing 12d are sequentially arranged in a direction away from the cover 42. The first wing 12a and the fourth wing 12d are arranged on the second rod 421b, and the second wing 12b and the third wing 12c are arranged on the first rod 421a.

[0051] Alternatively, the first wing 12a, the second wing 12b, the third wing 12c and the fourth wing 12d are sequentially arranged in a direction away from the cover 42. The first wing 12a and the third wing 12c are arranged on the first rod 421a, and the second wing 12b and the fourth wing 12d are arranged on the second rod 421b.

[0052] Alternatively, the first wing 12a, the second wing 12b, the third wing 12c and the fourth wing 12d are sequentially arranged in a direction away from the cover 42. The first wing 12a and the third wing 12c are arranged on the second rod 421b, and the second wing 12b and the fourth wing 12d are arranged on the first rod 421a.

[0053] By setting up this structure, the area of the canopy 42 can be fully utilized. Under the premise that the length of the wing 10 is certain and the wing 10 is folded and does not occupy additional space, the width of the wing 10 can be set wider. Therefore, the area of the wing 10 is larger, so that the drone can obtain greater lift during gliding, thereby facilitating the loading of heavier materials. Preferably, the method of "facing away from the canopy 42, the first wing 12a, the second wing 12b, the third wing 12c and the fourth wing 12d are arranged in sequence. Among them, the first wing 12a and the fourth wing 12d are arranged on the first rod 421a, and the second wing 12b and the third wing 12c are arranged on the second rod 421b" is selected. Compared with other methods, the wings arranged in this way can minimize the aerodynamic impact on the drone and have good synchronization and stability.

[0054] Reference Figure 8and Figure 9 As shown, the drone of the present invention, in some embodiments, further includes a binding member 50 for binding the wings 10 to maintain the wings 10 in the folded position. Preferably, the binding member 50 is configured as a binding rope. Those skilled in the art can configure the binding rope to bind the wings 10 according to actual needs. For example, the binding rope is configured to automatically release upon being pulled, allowing the wings 10 to quickly unfold and glide.

[0055] Working principle:

[0056] When not in use, the wings 10 are folded and placed in the opening 411 of the body 41 to reduce the volume of the entire drone and facilitate storage and protection of the wings 10.

[0057] When airdropping supplies is required, the cover 42 and the body 41 are disassembled and separated, and the corresponding supplies are loaded into the opening 411 of the body 41, and then the cover 42 and the body 41 are assembled. Then, the drones are loaded in a cluster by transport aircraft and transported to the airdrop area.

[0058] After reaching the airdrop area, the binding members 50 are released and the drone is deployed. Without the force of the binding members 50, the elastic members 20 provide elastic force to the wings 10, causing them to rotate and unfold toward the deployed position. As the wings 10 rotate, the pins 322 of the locking members 30 slide along the guide grooves 312. Once the wings 10 are fully rotated, the pins 322, acting under the force of the elastic members 323, insert into the locking holes 311, locking the wings 10 and preventing them from rotating. The deployed wings 10 glide to the target delivery area, allowing rescue workers and disaster-stricken residents to receive the supplies loaded by the drone.

[0059] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will readily appreciate that other variations or modifications based on the above descriptions are possible. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications arising therefrom remain within the scope of protection of the present invention.

Claims

1. A wing retraction and extension device, characterized in that: include: Wings, two of which are provided, the two wings being staggered, the wings being configured to be connected to corresponding target mounting members, the wings being rotatable relative to the target mounting members to switch between a folded position and an extended position; an elastic member, the elastic member being connected to the two wings respectively, and being used for providing an elastic force to the two wings so that the wings have a tendency to rotate from the folded position to the deployed position; as well as A locking member is connected to the corresponding wing and the target mounting member, and is used to lock the wing rotated to the deployed position.

2. The wing retraction and extension device according to claim 1, characterized in that: The locking member includes a locking seat, the locking seat being fixedly connected to the target mounting member and having a locking hole provided thereon; and A locking pin, the locking pin comprising a pin seat, a pin body, and an elastic component; the pin seat being connected to the wing, the pin seat being provided with a mounting hole, the pin body being movably disposed within the mounting hole, the elastic component being disposed within the mounting hole, the elastic component being configured to provide an elastic force to the pin body so that the pin body tends to extend out of the mounting hole; Wherein, when the wing is not rotated to the deployed position, the pin body is separated from the locking hole; when the wing is rotated to the deployed position, the pin body is inserted into the locking hole to lock the wing.

3. The wing retraction and deployment device according to claim 2, characterized in that: The locking seat is further provided with a guide groove, which is connected to the mounting hole; wherein, when the wing is not rotated to the deployed position, the pin body abuts against the guide groove, and the pin body can slide relative to the guide groove.

4. The wing retraction and deployment device according to claim 2, characterized in that: A guide portion is provided on the end of the pin body facing away from the wing, wherein the diameter of the guide portion gradually decreases along the end facing away from the locking seat toward the locking seat.

5. The wing retraction and extension device according to claim 1, characterized in that: The two wings rotate in opposite directions.

6. The wing retraction and deployment device according to claim 1, characterized in that: The elastic members are rotatably connected to the two wings respectively.

7. The wing retraction and deployment device according to claim 1, characterized in that: The wing is configured as a symmetrical structure; or / and The locking member is configured as a symmetrical structure.

8. A drone, characterized in that: include: a machine body, wherein the machine body is provided with an open cavity; as well as A machine cover, the machine cover is detachably connected to the machine body, the machine cover closes the opening of the opening cavity, the machine cover is provided with a target mounting part, and the target mounting part is provided with the wing retracting and extending device according to any one of claims 1 to 7.

9. The drone according to claim 8, characterized in that: The target mounting part is configured as a mounting rod, and two mounting rods and two wing retraction and extension devices are provided, and the two mounting rods are arranged in parallel and spaced apart; along the axial direction of the mounting rod, the two wing retraction and extension devices are arranged in sequence; in each of the wing retraction and extension devices, the two wings are connected to the two mounting rods in a one-to-one correspondence, wherein the rotation directions of the two wings on each mounting rod are opposite.

10. The drone according to claim 8, characterized in that: Also includes: A binding member is used to bind the wing so as to keep the wing in the folded position.

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