Wing folding and unfolding device and unmanned aerial vehicle

Abstract

The invention 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 part and a locking part, the two wings are arranged in a staggered mode, the wings are configured to be connected with corresponding target mounting parts, the wings can rotate relative to the target mounting parts, and the locking part is connected with the elastic part. 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] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a wing extension / retraction device and an UAV. Background Technology

[0002] In emergency relief missions responding to natural disasters such as earthquakes, floods, and mudslides, damage to transportation routes often hinders the timely delivery of relief supplies to affected areas, leading to shortages that impact the survival of victims and the rescue capabilities of personnel. Therefore, airdrop has become a primary means of providing emergency relief supplies in the early stages.

[0003] Airdrop is one of the main methods of aerial delivery. Compared to air transport, which requires disaster-stricken areas to have complete airport facilities, it can deliver supplies in areas without runways or with poor runway conditions, making it more flexible and convenient. For example, in one type of airdrop, a transport aircraft carries a drone to the drop zone and drops it. The drone glides to the target delivery area, where rescue workers and disaster victims can then receive the supplies loaded in the drone's cargo hold.

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

[0005] Conventional gliding drones typically use motors or servos as actuators to control the rotation, folding, and unfolding of the wings. To ensure the synchronization of wing rotation, the transmission structure between the actuator and the wing is quite complex, resulting in a large and heavy wing retraction device that negatively impacts the drone's performance. Summary of the Invention

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

[0007] In a first aspect, the present invention provides a wing retraction and deployment device, comprising: two wings arranged in a staggered manner; each wing being configured to be connected to a corresponding target mounting member; the wings being rotatable relative to the target mounting member to switch between a retracted position and a deployed position; an elastic member connected to each of the two wings respectively, the elastic member being used to provide an elastic force to the two wings to give the wings a tendency to rotate from the retracted position to the deployed position; and a locking member connected to the corresponding wing and the target mounting member respectively, the locking member being used to lock the wing rotated to the deployed position.

[0008] In one embodiment of the present invention, the locking member includes a locking seat fixedly connected to the target mounting member, the locking seat having a locking hole; and a locking pin, the locking pin including a pin seat, a pin body, and an elastic member; the pin seat is connected to the wing, the pin seat having a mounting hole, the pin body being movably disposed within the mounting hole, the elastic member being disposed within the mounting hole, the elastic member being used 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.

[0009] In one embodiment of the present invention, the locking seat is further provided with a guide groove, the guide groove communicating with the mounting hole; wherein, when the wing is not rotated to the unfolded position, the pin abuts against the guide groove, and the pin 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 opposite to the wing, wherein the diameter of the guide portion gradually decreases along the end opposite to the locking seat toward the locking seat.

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

[0012] In one embodiment of the invention, the elastic element is rotatably connected to each of the two wings.

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

[0014] Secondly, the present invention also provides a drone, including a body having an opening; and a cover detachably connected to the body, the cover closing the opening of the opening, the cover having a target mounting component, and the target mounting component having a wing retraction device as described in any one of the above.

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

[0016] In one embodiment of the invention, a binding member is further included for binding the wing to keep the wing in the folded position.

[0017] Compared with the prior art, the above-described technical solution of the present invention has the following advantages: The wing deployment and retraction device described in this invention, by incorporating an elastic element, applies an elastic force to the wing to drive its rotation. On one hand, this effectively replaces conventional drive motors, achieving synchronous drive of the wing and ensuring high synchronization during rotation. On the other hand, the elastic element is relatively small, space-efficient, lightweight, and has a simple overall structure, reducing the overall weight of the drone, allowing it to carry more rescue supplies, and improving its performance. Simultaneously, by incorporating a locking element to lock the wing in the deployed position, wing deployment is more stable and reliable. Furthermore, the elastic force applied by the elastic element also prevents the wing from rotating back to the retracted position after deployment, further enhancing overall reliability. Attached Figure Description

[0018] To make the content of this invention easier to understand, the invention will be further described in detail below with reference to specific embodiments and accompanying drawings, wherein... Figure 1 This is a schematic diagram of the wing retraction / extension device in a preferred embodiment of the present invention when the wing is in the retracted position; Figure 2 This is a schematic diagram of the wing retraction / extension device in a preferred embodiment of the present invention when the wing is in the deployed position; Figure 3 This is one of the structural schematic diagrams of the locking member in a preferred embodiment of the present invention; Figure 4 This is one of the cross-sectional structural schematic diagrams of the locking member in a preferred embodiment of the present invention; Figure 5 This is a second schematic diagram of the locking component in a preferred embodiment of the present invention; Figure 6 This is a second cross-sectional view of the locking member in a preferred embodiment of the present invention; Figure 7 This is a schematic diagram of the connection structure of the elastic element in a preferred embodiment of the present invention; Figure 8 This is one of the cross-sectional structural schematic diagrams of the UAV in a preferred embodiment of the present invention; Figure 9 This is a second cross-sectional structural schematic diagram of the UAV in a preferred embodiment of the present invention; Figure 10 This is a schematic diagram of the structure of the UAV in a preferred embodiment of the present invention.

[0019] Explanation of reference numerals in the accompanying drawings: 10, Wing; 11, Mounting base; 111, Servo; 12, Wing body; 121, Main wing; 122, Aileron; 12a, First wing; 12b, Second wing; 12c, Third wing; 12d, Fourth wing; 20, Elastic element; 21, Tension spring; 22, Connecting component; 30, Locking element; 31, Locking seat; 311, Locking hole; 312, Guide groove; 32, Locking pin; 321, Pin seat; 3211, Mounting hole; 322, Pin body; 3221, Guide part; 323, Elastic element; 41, Fuselage; 411, Opening mouth; 42, Fuselage cover; 421, Mounting rod; 421a, First rod; 421b, Second rod; 50, Binding component. Detailed Implementation

[0020] 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 and implement the present invention. However, the embodiments described are not intended to limit the present invention.

[0021] Reference Figure 1 and Figure 2 As shown, the present invention discloses a wing retraction and extension device, including a wing 10, an elastic element 20 and a locking element 30.

[0022] The wings 10 are used for gliding. Each wing deployment / retraction device has two wings 10, which are staggered to allow for folding and unfolding. The wings 10 are configured to connect to a corresponding target mounting component, wherein the wings 10 can rotate relative to the target mounting component to switch between a folded position and an unfolded position. Those skilled in the art can set the rotation direction of the wings 10 relative to their target mounting component according to actual needs; for example, in the same wing deployment / retraction device, the two wings 10 rotate in the same direction. Preferably, taking the device installed on a gliding UAV as an example, when the wings 10 are in the folded position, the wings 10 rotate relative to each other until their length direction is parallel to the length direction of the UAV, thereby reducing the overall size of the UAV, 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 direction is perpendicular to the length direction of the UAV for gliding.

[0023] The elastic element 20 replaces the conventional drive motor to achieve synchronous drive of the wings 10. Specifically, in each wing retraction / extension device, the elastic element 20 connects two wings 10 respectively and provides an elastic force to the two wings 10, so that the wings 10 tend to rotate from the retracted position to the extended position. Those skilled in the art can configure the elastic element 20 according to actual needs. For example, when both wings 10 are in the retracted position, the elastic element 20 is in a compressed state. After the force preventing the rotation of the wings 10 is removed, the elastic element 20 recovers and pushes the wings 10 to rotate, so that the wings 10 rotate to the extended position; or, when both wings 10 are in the retracted position, the elastic element 20 is in a stretched state. After the external force preventing the rotation of the wings 10 is removed, the elastic element 20 recovers and pulls the wings 10 to rotate, so that the wings 10 rotate to the extended position. By incorporating the elastic element 20, an elastic force is applied to the wing 10 to drive its rotation. This effectively replaces conventional drive motors, ensuring synchronous drive of the wing 10 and guaranteeing high synchronization during rotation. Furthermore, the elastic element 20 is relatively small, space-efficient, lightweight, and has a simple overall structure, reducing the overall weight of the drone, allowing it to carry more rescue supplies, and improving its performance. In addition, the elastic force applied to the wing 10 by the elastic element 20 also prevents the wing 10 from rotating back to the folded position after deployment, effectively improving overall reliability.

[0024] Locking members 30 are connected to the corresponding wings 10 and target mounting parts, respectively, and are used to lock the wings 10 in the deployed position. By setting the locking members 30 to lock the wings 10, the deployment of the wings 10 is more stable and reliable, allowing the wings 10 to glide smoothly afterwards. Those skilled in the art can set the locking members 30 according to actual needs, such as locking hooks. Correspondingly, when the wings 10 are in the retracted position, those skilled in the art can set corresponding components according to actual needs to apply force to the wings 10 and prevent them from rotating, which will not be described in detail here.

[0025] The wing deployment and retraction device of this invention, by incorporating an elastic element 20, applies an elastic force to the wing 10 to drive its rotation. On one hand, this effectively replaces conventional drive motors, achieving synchronous drive of the wing 10 and ensuring high synchronization during rotation. On the other hand, the elastic element 20 is relatively small, space-efficient, lightweight, and has a simple overall structure, reducing the overall weight of the drone, facilitating the loading of more rescue supplies, and improving the drone's performance. Simultaneously, by incorporating a locking element 30 to lock the wing 10 in the deployed position, the deployment of the wing 10 is more stable and reliable. Furthermore, the elastic force applied by the elastic element 20 to the wing 10 can also, to some extent, prevent the wing 10 from rotating back to the retracted position after deployment, further improving overall reliability.

[0026] Reference Figure 2 As shown, preferably, the wing 10 includes a mounting base 11 and a wing body 12. The mounting base 11 is used to rotatably connect to the target mounting component; the wing body 12 is connected to the mounting base 11 and is used for gliding. The wing body 12 includes a main wing 121 and a flaperon 122. The main wing 121 is fixedly connected to the mounting base 11, and the flaperon 122 is rotatably connected to the main wing 121 so that during gliding, the gliding attitude can be adjusted by rotating the flaperon 122 relative to the main wing 121 to ensure a final landing in the target delivery area. For example, a servo motor 111 is provided on the mounting base 11, and the drive end of the servo motor 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 base 11.

[0027] Reference Figure 3 , Figure 4 , Figure 5 and Figure 6As shown, in some embodiments of the wing retraction device of the present invention, 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. The locking seat 31 is provided with a locking hole 311 to cooperate with the locking pin 32 to lock the wing 10. The locking pin 32 includes a pin seat 321, a pin body 322, and an elastic member 323. The pin seat 321 is connected to the wing 10; preferably, the pin seat 321 is connected to the mounting base 11. The pin seat 321 is provided with a mounting hole 3211, and the pin body 322 is movably disposed within the mounting hole 3211. The elastic member 323 is disposed within the mounting hole 3211, and the elastic member 323 is used to provide an elastic force to the pin body 322 so that the pin body 322 tends to extend out of the mounting hole 3211. Preferably, the elastic member 323 is a spring. When the wing 10 is not in the deployed position, the pin 322 separates from the locking hole 311, allowing the wing 10 to rotate relative to the target mounting component. When the wing 10 is in the deployed position, the pin 322 inserts into the locking hole 311 to lock the wing 10 and prevent it from rotating. This structure effectively locks the wing 10, and the overall structure is simple, compact, and lightweight. 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.

[0028] Reference Figure 3 As shown, in some embodiments of the wing retraction and deployment device of the present invention, the locking seat 31 is further provided with a guide groove 312, which connects to the mounting hole 3211. The guide groove 312 is used to guide and limit the pin 322. When the wing 10 is not rotated to the deployed position, the pin 322 abuts against the guide groove 312 and can slide relative to the guide groove 312. When the wing 10 is rotated to the deployed position, the pin 322 disengages from the guide groove 312 and inserts into the locking hole 311 to lock the wing 10. By setting this structure, the stability and reliability of the device can be effectively enhanced.

[0029] Furthermore, refer to Figure 4 As shown, the locking element 30 is configured with a symmetrical structure to increase versatility and facilitate the interchangeability of the locking elements 30 of the two wings 10 by changing the installation method during assembly and maintenance. For example, the locking seat 31 is configured with a plate-like structure, the locking hole 311 passes through the locking seat 31, and guide grooves 312 are provided on both opposite sides of the locking seat 31.

[0030] Furthermore, refer to Figure 4As shown, in some embodiments of the wing retraction device of the present invention, a guide portion 3221 is provided on the end of the pin 322 facing away from the wing 10. The diameter of the guide portion 3221 gradually decreases along the end facing away from the locking seat 31, forming a cone-shaped structure. By providing the guide portion 3221, the pin 322 can be more easily inserted into the locking hole 311, achieving rapid locking of the wing 10.

[0031] Reference Figure 2 As shown, in some embodiments of the wing retraction device of the present invention, the two wings 10 rotate in opposite directions. Compared with rotation in the same direction, the opposite rotation of the wings 10 can reduce the possibility of interference between the two wings 10. In a UAV with two target mounting parts and four wings 10, it is also convenient to improve the stability of the UAV by setting the relative position of the wings 10 with respect to the target mounting parts.

[0032] Reference Figure 7 As shown, in some embodiments of the wing retraction and deployment device of the present invention, the elastic element 20 is rotatably connected to each of the two wings 10. Preferably, the elastic element 20 is a tension spring 21, both ends of which are fixedly connected to corresponding connecting parts 22, and the connecting parts 22 are rotatably connected to the mounting base 11. By setting this structure, the rotation of the wings 10 can be made smoother, so that the wings 10 can quickly deploy and achieve gliding.

[0033] In some embodiments of the wing retraction and extension device of the present invention, the wing 10 is configured as a symmetrical structure, which facilitates the interchangeability of the wing 10 between different devices and the interchangeability of the wing 10 in the same device, thereby improving maintenance and assembly efficiency and reducing production costs.

[0034] Reference Figure 8 , Figure 9 and Figure 10As shown, this invention discloses a drone, including a body 41 and a canopy 42. The body 41 has an opening 411 for accommodating materials or wings 10. The canopy 42 is detachably connected to the body 41, and those skilled in the art can configure the detachment and connection method between the canopy 42 and the body 41 according to actual needs. When the canopy 42 is mounted on the body 41, it closes the opening of the opening 411. The canopy 42 has target mounting parts, and the target mounting parts are provided with wing retraction devices as described in any of the above embodiments. Those skilled in the art can configure the number and installation position of the wing retraction devices according to actual needs; for example, the canopy 42 has four target mounting parts and two wing retraction devices, and each target mounting part has a corresponding wing 10. Since the drone of this invention includes the wing retraction devices described in the above embodiments, it also possesses all the beneficial effects described herein, which will not be repeated here.

[0035] Preferably, when not in use, the wings 10 are folded and placed in the opening 411 of the fuselage 41 to reduce the overall size of the drone, facilitate storage, and effectively protect the wings 10. When supplies need to be airdropped, the canopy 42 and fuselage 41 are disassembled, the corresponding supplies are loaded into the opening 411 of the fuselage 41, and then the canopy 42 and fuselage 41 are reassembled. Next, the drones are transported to the airdrop area by means of a transport aircraft swarm, and then dropped. The wings 10 of the dropped drone rotate and unfold under the elastic force of the elastic element 20 for gliding.

[0036] Reference Figure 10 As shown, in some embodiments of the UAV described in this invention, the target mounting component is configured as a mounting rod 421, and two mounting rods 421 and two wing retraction / extension devices are each 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 fuselage 41. Preferably, the length of the wing 10 is less than the distance between the two mounting rods 421 to facilitate the smooth retraction and extension of the wing 10. The two wing retraction / extension devices are arranged sequentially along the axial direction of the mounting rods 421 to prevent interference between the wing 10 and the elastic element 20. In each wing retraction / extension device, two wings 10 are connected to two mounting rods 421 in a one-to-one correspondence, and the two wings 10 on each mounting rod 421 rotate in opposite directions.

[0037] To facilitate the identification of each mounting rod 421 and wing 10, the two mounting rods 421 are designated as first rod 421a and second rod 421b, with first rod 421a positioned closer to the nose of the fuselage 41 and second rod 421b positioned closer to the tail of the fuselage 41. The two wings 10 of one wing retraction device are designated as first wing 12a and second wing 12b, and the two wings 10 of the other wing retraction device are designated as third wing 12c and fourth wing 12d. The configuration includes at least the following arrangements: Facing away from the cover 42, the first wing 12a, the second wing 12b, the third wing 12c, and the fourth wing 12d are arranged sequentially. 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.

[0038] Alternatively, the first wing 12a, the second wing 12b, the third wing 12c, and the fourth wing 12d are arranged sequentially in a direction away from the cover 42. Among them, 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.

[0039] Alternatively, facing away from the cover 42, the first wing 12a, the second wing 12b, the third wing 12c, and the fourth wing 12d are arranged sequentially. Among them, 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.

[0040] Alternatively, facing away from the cover 42, the first wing 12a, the second wing 12b, the third wing 12c, and the fourth wing 12d are arranged sequentially. Among them, 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.

[0041] By designing this structure, the area of ​​the canopy 42 can be fully utilized. With a fixed wing length and without occupying extra space when folded, the wing 10 can be made wider. Therefore, the larger wing area allows the drone to generate greater lift during gliding, facilitating the loading of heavier cargo. Preferably, the arrangement of "first wing 12a, second wing 12b, third wing 12c, and fourth wing 12d arranged sequentially in a direction away from the canopy 42, with first wing 12a and fourth wing 12d mounted on first rod 421a, and second wing 12b and third wing 12c mounted on second rod 421b" minimizes aerodynamic impact on the drone compared to other arrangements, resulting in better synchronization and stability.

[0042] Reference Figure 8 and Figure 9 As shown, in some embodiments of the drone described in this invention, a binding member 50 is further included. The binding member 50 is used to bind the wing 10 so that the wing 10 is kept in the folded position. Preferably, the binding member 50 is a binding rope. Those skilled in the art can set the binding rope to bind the wing 10 according to actual needs. For example, the binding rope is set to automatically unbind after being pulled so that the wing 10 can quickly unfold and glide.

[0043] Working principle: When not in use, the wings 10 are folded up and placed in the opening 411 of the fuselage 41 to reduce the overall size of the UAV and facilitate storage and protection of the wings 10.

[0044] When supplies need to be airdropped, the hatch 42 and fuselage 41 are disassembled, and the corresponding supplies are loaded into the opening 411 of the fuselage 41. Then, the hatch 42 and fuselage 41 are reassembled. Next, the drones are transported to the airdrop area by a swarm of transport aircraft.

[0045] Upon reaching the airdrop area, the tethering device 50 is released and the drone is deployed. With the tethering device 50 no longer in effect, the elastic element 20 provides elastic force to the wings 10, causing them to rotate and unfold. During wing rotation, the pin 322 of the locking element 30 slides along the guide groove 312. Once the wings 10 are in position, the pin 322, under the force of the elastic element 323, inserts into the locking hole 311 to lock the wings 10 and prevent further rotation. The unfolded wings 10 glide to the target delivery area so that rescue personnel and disaster victims can receive the supplies carried by the drone.

[0046] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A wing retraction and deployment device, characterized in that, include: The aircraft has two wings that are staggered and configured to connect to corresponding target mounting components. The wings are rotatable relative to the target mounting components to switch between a folded position and a unfolded position. An elastic element is provided, which is connected to the two wings respectively. The elastic element is used to provide an elastic force to the two wings so that the wings tend to rotate from the folded position to the unfolded position. as well as A locking element is provided, which is connected to the corresponding wing and the target mounting element respectively, and is used to lock the wing when it is rotated to the deployed position.

2. The wing retraction and extension device according to claim 1, characterized in that: The locking element includes A locking seat, which is fixedly connected to the target mounting component, and having a locking hole on it; and A locking pin, comprising a pin seat, a pin body, and an elastic component; the pin seat is connected to the wing, and the pin seat is provided with a mounting hole; the pin body is movably disposed within the mounting hole; the elastic component is disposed within the mounting hole, and the elastic component is used to provide an elastic force to the pin body so that the pin body tends to extend out of the mounting hole; Specifically, when the wing is not rotated to the deployed position, the pin is separated from the locking hole; when the wing is rotated to the deployed position, the pin 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 also provided with a guide groove, which is connected to the mounting hole; wherein, when the wing is not rotated to the unfolded position, the pin abuts against the guide groove, and the pin 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 that is away from the wing, wherein the diameter of the guide portion gradually decreases along the end away from the locking seat toward the locking seat.

5. The wing retraction and deployment 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 element is rotatably connected to each of the two wings.

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 element is configured as a symmetrical structure.

8. A drone, characterized in that, include: The body, wherein an opening is provided on the body; as well as The cover is detachably connected to the fuselage and closes the opening of the oral cavity. The cover is provided with a target mounting component and the target mounting component is provided with a wing retraction device as described in any one of claims 1 to 7.

9. The UAV according to claim 8, characterized in that: The target mounting component is configured as a mounting rod, and there are two mounting rods and two wing retraction / extension devices. The two mounting rods are arranged in parallel and spaced apart. Along the axial direction of the mounting rod, the two wing retraction / extension devices are arranged sequentially. In each wing retraction / extension device, the two wings are connected to the two mounting rods in a one-to-one correspondence, wherein the two wings on each mounting rod rotate in opposite directions.

10. The UAV according to claim 8, characterized in that, Also includes: A lashing element for securing the wing to keep it in the folded position.

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