Wing folding detachable structure of fixed-wing unmanned aerial vehicle

Abstract

The utility model discloses a wing folding detachable structure of a fixed-wing unmanned aerial vehicle, which belongs to the field of unmanned aerial vehicles and comprises a wing assembly, a fuselage assembly and a folding assembly. The wing assembly comprises at least one wing sleeve, and the fuselage assembly comprises at least one fuselage sleeve; one end of the folding assembly is inserted into the wing sleeve and fixedly connected with the wing sleeve, the other end of the folding assembly can be movably inserted into the fuselage sleeve, the end of the folding assembly is limited outside the end, away from the fuselage sleeve, of the wing sleeve, and the middle of the folding assembly is a detachable bent part. The utility model has the beneficial effects that the folding scheme is simple, and the disassembly and assembly are convenient.

Description

Technical Field

[0001] This utility model relates to a drone, and more particularly to a drone wing. Background Technology

[0002] Unmanned aerial vehicles (UAVs), also known as drones, are unmanned aircraft controlled by radio remote control equipment and onboard program control devices. UAVs have a wide range of applications, including police work, urban management, agriculture, geology, meteorology, power, disaster relief, and video shooting.

[0003] Currently, most drones use a skin + frame structure for their wings. The wing folding effect is poor or the wings are not detachable. The disadvantages are that the wings and fuselage share the same frame, the wings are not detachable, the wings cannot be folded or are only folded halfway, resulting in the drone taking up a lot of space, making it inconvenient to transport, store and carry. Furthermore, if the wings are not easy to disassemble, they are not easy to replace after they are damaged.

[0004] The information disclosed in this background section is intended only to enhance the understanding of the overall background of this utility model and should not be construed as an admission or in any way implying that the information constitutes prior art known to those skilled in the art. Utility Model Content

[0005] The technical problem to be solved by this utility model is: how to solve the problem that the wings of current drones cannot be folded or are folded only halfway, resulting in the drones being too large or difficult to replace.

[0006] This utility model solves the above-mentioned technical problems through the following technical means:

[0007] A foldable and detachable wing structure for a fixed-wing unmanned aerial vehicle (UAV) includes a wing assembly, a fuselage assembly, and a folding assembly. The wing assembly includes at least one wing sleeve, and the fuselage assembly includes at least one fuselage sleeve. One end of the folding assembly is inserted into and fixedly connected to the wing sleeve, and the other end of the folding assembly is movably inserted into the fuselage sleeve. The end of the folding assembly is limited to the outside of the end of the wing sleeve away from the fuselage sleeve, and the middle part of the folding assembly is a detachable curved section.

[0008] In this invention, the wing assembly and fuselage assembly are connected via a folding assembly. This folding assembly is a detachable, curved component that allows the wing assembly to fold behind the fuselage assembly when needed, reducing the overall size of the drone. It also allows for easy disassembly and assembly when the wing needs replacement. This invention features a simple folding design, allows for manual folding, and enables detachable wings for easy replacement.

[0009] Preferably, both the wing sleeve and the fuselage sleeve are straight tubes, the outer diameter of the wing sleeve is smaller than the inner diameter of the fuselage sleeve, the position of the wing sleeve is aligned with the position of the fuselage sleeve, and the protruding part of the wing sleeve is inserted into or detached from the interior of the fuselage sleeve.

[0010] Preferably, both the wing sleeve and the fuselage sleeve are made of carbon fiber.

[0011] Preferably, the folding assembly includes a wing metal part, a fuselage metal part, a locking screw, a limiting tube, and a limiting rod; one end of the wing metal part is inserted into the limiting tube and fixedly connected thereto, one end of the fuselage metal part is inserted into the fuselage sleeve and fixedly connected thereto, and the wing metal part and the fuselage metal part are rotatably connected by the locking screw; the limiting tube is movably inserted into the fuselage sleeve, one end of the limiting rod is inserted into the fuselage sleeve and fixedly connected to the limiting tube, and the other end is limited to the outside of the fuselage sleeve.

[0012] Preferably, the wing metal part is a tubular structure, with one end of the tubular structure connected to a circular plate. A connecting plate for connecting with the locking screw is connected to the circular plate, and the connecting plate has a through hole.

[0013] Preferably, the metal body part is a tubular structure, with one end of the tubular structure connected to a circular plate. The metal body part is inserted into the limiting tube and fixedly connected to the circular plate. Two connecting plates for connecting with locking screws are connected to the circular plate, and the connecting plates are provided with through holes.

[0014] Preferably, the limiting tube is a straight tube, the outer diameter of the limiting tube is smaller than the inner diameter of the fuselage sleeve, and the limiting tube is inserted into the fuselage sleeve.

[0015] Preferably, the limiting rod includes a straight rod, with a small circular plate and a large circular plate connected to its two ends respectively. The small circular plate extends into the right end of the limiting tube and is fixedly connected thereto, while the large circular plate is located outside the limiting rod, and the outer diameter of the large circular plate is larger than the outer diameter of the fuselage sleeve.

[0016] The limiting rod is used to ensure that the wing assembly does not completely detach from the fuselage assembly, while also meeting the requirement for the wing assembly to be pulled out when folding.

[0017] Preferably, it also includes a locking device, and the fuselage assembly and the wing assembly are connected by multiple locking devices.

[0018] The locking device ensures the reliability of the connection between the wing assembly and the fuselage assembly.

[0019] Preferably, the wing assembly includes two wing sleeves, and the fuselage assembly includes two fuselage sleeves; one pair of wing sleeves is connected to one end of the folding assembly, and the other end of the folding assembly is inserted into the fuselage sleeve; the other pair of wing sleeves is directly inserted into the fuselage sleeve.

[0020] Adding an extra set of wing sleeves and fuselage sleeves can improve the stability of the connection between the wing assembly and the fuselage assembly.

[0021] The advantages of this utility model are:

[0022] This utility model has a simple folding scheme, which can be manually folded using only carbon tubes and metal parts; it also allows for the disassembly of the wing assembly, making disassembly and assembly convenient; it is low-cost, with fewer wing folding components, low price, and easy to implement. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of a fixed-wing unmanned aerial vehicle (UAV) wing folding and detachable structure according to an embodiment of the present invention;

[0024] Figure 2 This is an exploded view of a fixed-wing UAV wing folding and detachable structure according to an embodiment of this utility model;

[0025] Figure 3 This is a schematic diagram of the wing assembly according to an embodiment of the present invention;

[0026] Figure 4 This is a schematic diagram of the fuselage assembly according to an embodiment of the present utility model;

[0027] Figure 5 This is a schematic diagram of the folding assembly according to an embodiment of the present invention;

[0028] Figure 6 This is an exploded view of the folding assembly according to an embodiment of the present invention;

[0029] Figure 7 This is a cross-sectional view of the folding assembly during installation according to an embodiment of this utility model;

[0030] Figure 8 This is a schematic diagram of the operation of the wing assembly during rotation according to an embodiment of this utility model;

[0031] Figure 9 This is a schematic diagram of the wing assembly folding during operation according to an embodiment of this utility model;

[0032] Numbering on the map:

[0033] 1. Wing assembly; 11. Wing sleeve;

[0034] 2. Fuselage assembly; 21. Fuselage sleeve;

[0035] 3. Folding assembly; 31. Wing metal parts; 32. Fuselage metal parts; 33. Locking screws; 34. Limiting tubes; 35. Limiting rods;

[0036] 4. Locking device. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below in conjunction with the embodiments of this utility model. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0038] Example 1:

[0039] like Figure 1 , Figure 2 As shown in the figure, part of the skin is hidden. A fixed-wing UAV folding and detachable wing structure includes a wing assembly 1, a fuselage assembly 2, a folding assembly 3, and a locking device 4. The wing assembly 1 includes a wing sleeve 11, and the fuselage assembly 2 includes a fuselage sleeve 21. One end of the folding assembly 3 is inserted into and fixedly connected to the wing sleeve 11, while the other end of the folding assembly 3 is movably inserted into the fuselage sleeve 21, and the end of the folding assembly 3 is limited to the outside of the end of the wing sleeve 11 away from the fuselage sleeve 21. The middle part of the folding assembly 3 is a curved section. The locking device 4 connects the wing assembly 1 and the fuselage assembly 2.

[0040] Specifically, for ease of display, combined with Figure 2 , Figure 3 As shown, the wing assembly 1 is connected to the wing sleeve 11 on the side near the fuselage assembly 2. The wing sleeve 11 is a straight tube with one end extending outward. The opening ends of both wing sleeves 11 face the fuselage assembly 2.

[0041] Figure 4 Part of the skin is hidden in the middle, combined with Figure 2 , Figure 4 As shown, the fuselage assembly 2 is connected to two fuselage sleeves 21 on the side near the wing assembly 1. The fuselage sleeves 21 are straight tubes, and the open ends of both fuselage sleeves 21 face the wing assembly 1. The other parts of the fuselage assembly 2, except for the fuselage sleeves 21, can refer to the prior art.

[0042] The outer diameter of the wing sleeve 11 is smaller than the inner diameter of the fuselage sleeve 21, and the position of the wing sleeve 11 is aligned with the position of the fuselage sleeve 21, so that the protruding part of the wing sleeve 11 can be inserted into the interior of the fuselage sleeve 21.

[0043] Both the wing sleeve 11 and the fuselage sleeve 21 can be made of carbon steel.

[0044] like Figure 5 , Figure 6As shown, the folding assembly 3 includes a wing metal part 31, a fuselage metal part 32, a locking screw 33, a limiting tube 34, and a limiting rod 35. The wing metal part 31 is a tubular structure with a circular plate connected to its right end. The tubular structure is inserted into the wing sleeve 11 and limited by the circular plate. The circular plate is fixedly connected to the wing sleeve 11, and the connection method can be welding or adhesive bonding. A connecting plate for connecting with the locking screw 33 is connected to the circular plate, and the connecting plate has a through hole. The fuselage metal part 32 is also a tubular structure with a circular plate connected to its left end. The fuselage metal part 32 is inserted into the limiting tube 34 and limited by the circular plate. The circular plate is fixedly connected to the end of the limiting tube 34, and the connection method can be welding or adhesive bonding. Two connecting plates for connecting with the locking screw 33 are connected to the circular plate, and the connecting plates have through holes. The limiting tube 34 is a straight tube that can be inserted into the fuselage sleeve 21 and can move axially along the fuselage sleeve 21. The limiting rod 35 includes a straight rod with a small circular plate and a large circular plate connected to its two ends, respectively. The small circular plate extends into and is fixedly connected to the right end of the limiting tube 34, while the large circular plate is located outside the limiting rod 35. The outer diameter of the large circular plate is larger than the outer diameter of the fuselage sleeve 21, thus limiting the large circular plate to the outside of the fuselage sleeve 21. The locking screw 33 is connected to the circular plates of the wing metal part 31 and the fuselage metal part 32, allowing the wing metal part 31 and the fuselage metal part 32 to rotate circumferentially along the axis of the locking screw 33.

[0045] like Figure 7 As shown, the wing metal part 31 is inserted into the wing sleeve 11 and fixedly connected thereto, while the fuselage metal part 32 is inserted into the limiting tube 34 and fixedly connected thereto. The limiting tube 34 slides axially within the fuselage sleeve 21. The small circular plate of the limiting rod 35 is fixed within the limiting tube 34, and the large circular plate of the limiting rod 35 is limited to the right end of the fuselage sleeve 21.

[0046] In this embodiment, the bent portion is achieved by locking screw 33.

[0047] In this embodiment, the outer diameter of the entire folding assembly 3 is smaller than the inner diameter of the fuselage sleeve 21, so that the folding assembly 3 can be inserted into the fuselage sleeve 21 and move axially within the fuselage sleeve 21.

[0048] The ribs of the wing assembly 1 near the fuselage assembly 2, and the ribs of the fuselage assembly 2 near the wing assembly 1, are provided with slots to facilitate the subsequent processing and assembly of the locking device 4, thereby achieving a reinforced connection between the wing and the fuselage in the working state.

[0049] The folding process in this embodiment:

[0050] 1) Combining Figure 1 , Figure 2As shown, open the locking device 4 and pull the wing assembly 1 out of the fuselage assembly 2. When pulling it out, check that the rotation direction of the locking screw 33 is consistent with the vertical direction.

[0051] 2) Rotary wing assembly 1; combined with Figure 8 As shown, manually rotate the wing assembly 1 so that the limiting tube 34 rotates around the fuselage sleeve 21. The wing assembly 1 rotates clockwise so that the wing assembly and the fuselage assembly 2 are at a perpendicular angle.

[0052] 3) Combining Figure 9 As shown, the folding wing assembly 1 allows the wing assembly 1 to rotate circumferentially along the axis of the locking screw 33, thereby achieving the folding of the wing assembly 1.

[0053] If wing assembly 1 needs to be disassembled, pull out wing assembly 1, remove locking screw 33, and then install the replacement wing assembly 1.

[0054] Example 2:

[0055] In this embodiment, the wing assembly 1 includes two wing sleeves 11, and the fuselage assembly 2 includes two fuselage sleeves 21; the two wing sleeves 11 are spaced apart, and the two fuselage sleeves 21 are spaced apart.

[0056] One set of wing sleeves 11 is connected to the fuselage sleeve 21 via a folding assembly 3. The other set of wing sleeves 11' and fuselage sleeve 21' is not connected to the folding assembly 3, but the wing sleeves 11' and fuselage sleeve 21' are still in a matching relationship, that is, the outer diameter of the wing sleeve 11' is smaller than the inner diameter of the fuselage sleeve 21', and the wing sleeve 11' can be inserted into the fuselage sleeve 21'.

[0057] In this embodiment, setting an additional set of wing sleeve 11' and fuselage sleeve 21' can improve the stability when the wing assembly 1 is connected to the fuselage assembly 2.

[0058] When the wing assembly 1 is pulled out from the fuselage assembly 2, the wing sleeve 11' and the fuselage sleeve 21' can be detached.

[0059] The above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A fixed-wing unmanned aerial vehicle wing folding detachable structure, characterized in that, It includes a wing assembly, a fuselage assembly, and a folding assembly; the wing assembly includes at least one wing sleeve, and the fuselage assembly includes at least one fuselage sleeve; one end of the folding assembly is inserted into and fixedly connected to the wing sleeve, the other end of the folding assembly is movably inserted into the fuselage sleeve, and the end of the folding assembly is limited to the outside of the end of the wing sleeve away from the fuselage sleeve, and the middle part of the folding assembly is a detachable curved part.

2. The fixed-wing UAV wing folding detachable structure according to claim 1, characterized in that, Both the wing sleeve and the fuselage sleeve are straight tubes. The outer diameter of the wing sleeve is smaller than the inner diameter of the fuselage sleeve. The wing sleeve is aligned with the fuselage sleeve. The protruding part of the wing sleeve is inserted into or detached from the interior of the fuselage sleeve.

3. The fixed-wing UAV wing folding detachable structure according to claim 1, characterized in that, Both the wing sleeves and the fuselage sleeves are made of carbon fiber.

4. The fixed-wing UAV wing folding detachable structure according to claim 1, characterized in that, The folding assembly includes a wing metal part, a fuselage metal part, a locking screw, a limiting tube, and a limiting rod. One end of the wing metal part is inserted into the limiting tube and fixedly connected thereto, and one end of the fuselage metal part is inserted into the fuselage sleeve and fixedly connected thereto. The wing metal part and the fuselage metal part are rotatably connected by the locking screw. The limiting tube is movably inserted into the fuselage sleeve, and one end of the limiting rod is inserted into the fuselage sleeve and fixedly connected to the limiting tube, while the other end is limited to the outside of the fuselage sleeve.

5. The fixed-wing UAV wing folding detachable structure according to claim 4, characterized in that, The wing metal parts are tubular structures, with a circular plate connected to one end. A connecting plate for connecting with locking screws is connected to the circular plate, which has through holes.

6. The fixed-wing UAV wing folding detachable structure according to claim 4, characterized in that, The metal body is a tubular structure. One end of the tubular structure is connected to a circular plate. The metal body is inserted into the limiting tube and fixedly connected to the circular plate. Two connecting plates for connecting with the locking screws are connected to the circular plate. The connecting plates have through holes.

7. The fixed-wing UAV wing folding detachable structure according to claim 4, characterized in that, The limiting tube is a straight tube, and its outer diameter is smaller than the inner diameter of the fuselage sleeve. The limiting tube is inserted into the fuselage sleeve.

8. The fixed-wing UAV wing folding detachable structure according to claim 4, characterized in that, The limiting rod includes a straight rod, with a small circular plate and a large circular plate connected to its two ends respectively. The small circular plate extends into the right end of the limiting tube and is fixedly connected to it, while the large circular plate is located outside the limiting rod, and the outer diameter of the large circular plate is larger than the outer diameter of the fuselage sleeve.

9. The fixed-wing UAV wing folding detachable structure according to claim 1, wherein, It also includes locking devices, with the fuselage assembly and wing assembly connected by multiple locking devices.

10. The fixed-wing UAV wing folding detachable structure according to claim 1, wherein, The wing assembly includes two wing sleeves, and the fuselage assembly includes two fuselage sleeves; one pair of wing sleeves is connected to one end of the folding assembly, and the other end of the folding assembly is inserted into the fuselage sleeve; the other pair of wing sleeves is directly inserted into the fuselage sleeve.

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