A wing-to-fuselage docking device

Abstract

The utility model belongs to unmanned plane assembly technical field, concretely relates to a wing fuselage docking device. Wing fuselage docking device includes the first docking module and the second docking module respectively set on the wing and the fuselage, first docking module and second docking module are configured as can along the first direction mobile type docking, first direction with the length direction parallel of wing.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) assembly technology, specifically relating to a wing-fuselage docking device. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are becoming increasingly important in the modern aviation field. For ease of transport, storage, and maintenance, the wings and fuselage of fixed-wing UAVs are often designed as detachable, independent modules. Currently, the connection methods for these modules generally have shortcomings. For example, while traditional bolt connections offer high strength, installation and disassembly are cumbersome and time-consuming, requiring multiple tools and affecting rapid response capabilities in the field. Simple pin or snap-fit ​​connections are quick to operate, but manufacturing tolerances result in gaps, insufficient rigidity, and difficulty in ensuring docking accuracy. These also pose safety hazards during high-G flights, limiting UAV performance.

[0003] Therefore, it is necessary to propose a wing-body connection structure for UAVs that integrates rapid operation, precise positioning, high reliability, and lightweight design. Utility Model Content

[0004] To address the technical problems described above, this utility model aims to provide a wing-fuselage docking device. According to this utility model, a wing-fuselage docking device is provided, including a first docking module and a second docking module respectively disposed on the wing and the fuselage. The first docking module and the second docking module are configured to be movable and docked along a first direction, which is parallel to the length direction of the wing. The first docking module includes a first locking head disposed parallel to the first direction, and the second docking module includes a second locking head disposed parallel to the first direction and capable of docking with the first locking head. The first docking module also includes a guide rod disposed parallel to the first locking head, and the second docking module also includes a guide bushing adapted to the guide rod.

[0005] In one specific embodiment, the first locking head includes a locking female head, and a plurality of locking balls are evenly arranged circumferentially on the side wall of the locking female head; the second locking head includes a locking male head that can be inserted into the locking female head, and a groove that can engage with the locking balls is provided on the outer wall of the locking male head.

[0006] In one specific embodiment, a mounting groove for installing the locking ball is provided through the side wall of the locking nut. The dimensions of the inner and outer ends of the mounting groove are smaller than the dimensions of the middle part, and a plurality of mounting grooves are evenly distributed circumferentially.

[0007] In one specific embodiment, the locking ball is configured to move radially within the mounting groove. In a first state, the locking ball can move radially relative to the mounting groove, allowing the locking male head to move axially relative to the locking female head. In a second state, the locking ball cannot move radially relative to the mounting groove and is connected to the slot of the locking male head.

[0008] In one specific embodiment, a locking sleeve is provided on the outer wall of the locking nut. In the first state, the locking sleeve is not in radial contact with the locking ball; In the second state, the locking sleeve is located outside the locking ball, and the inner wall of the locking sleeve is in radial contact with the locking ball.

[0009] In one specific embodiment, the locking sleeve is axially movable and disposed on the outer wall of the locking nut.

[0010] In one specific embodiment, an elastic element is provided between the locking sleeve and the locking nut, the elastic element being configured to allow the locking sleeve to be in a second state.

[0011] In one specific embodiment, a limiting member is provided on the outer wall of the locking nut. In the second state, the locking sleeve abuts axially against the limiting member under the preload of the elastic member.

[0012] In one specific embodiment, the first docking module further includes a first frame, the first locking head and the guide rod are fixedly disposed on the first docking wall of the first frame, and an inspection port corresponding to the locking sleeve is provided on the second frame; the second docking module further includes a second frame, the second locking head and the guide bushing are fixedly disposed on the second docking wall of the second frame, and the shapes of the first docking wall and the second docking wall are adapted to each other.

[0013] In one specific embodiment, the first locking head is connected to the first frame via a first fastener, and the second locking head is connected to the second frame via a second fastener.

[0014] Compared with the prior art, this application has at least the following advantages.

[0015] This invention enables rapid docking of the wing and fuselage by setting a first docking module and a second docking module.

[0016] The first and second docking modules of this invention are locked together by multiple locking balls interlocking with slots, and a locking sleeve prevents the locking balls from moving. With a large bearing area, they can withstand axial tensile force, shear force, and vibration loads several times greater than conventional snap-fit ​​devices, meeting the connection strength requirements of UAVs under high-G maneuvers. The locking sleeve provides radial-inward pressure to the locking balls, ensuring a tight fit between the balls and the slots, eliminating axial and radial gaps and creating a "zero-play" rigid connection. This is crucial for ensuring the stability of the UAV's aerodynamic shape and the precision of its flight control. By moving the locking sleeve, convenient installation and quick disassembly of the fuselage and wings can be achieved.

[0017] This invention provides a precise and rapid guarantee for the docking process of the device by setting a precision guiding structure with guide rods and guide bushings, as well as an end face positioning structure (first docking wall and second docking wall) between the first frame and the second frame.

[0018] The highly integrated design of this utility model with multiple functions significantly improves the deployment efficiency, connection reliability and field maintainability of UAVs. At the same time, the device is relatively refined and has good promotional value and economic benefits. Attached Figure Description

[0019] The present invention will now be described with reference to the accompanying drawings.

[0020] Figure 1 This diagram shows an embodiment of connecting the fuselage and wing of a UAV using a wing-fuselage docking device according to the present invention (only a portion of the fuselage and wing is shown). Figure 2 The diagram shows an embodiment of the wing-fuselage docking device according to the present invention, in which the first docking module and the second docking module are separated from each other. Figure 3 The diagram shows an embodiment in which the first docking module and the second docking module of the wing-fuselage docking device according to the present invention are connected to each other. Figure 4 An enlarged schematic diagram showing the interconnection of the first locking head of the first docking module and the second locking head of the second docking module according to the present invention is shown.

[0021] The reference numerals in the figure are as follows: 1. Wings; 2. First docking module; 21. First locking head; 211. Locking female head; 212. Locking ball; 213. Mounting groove; 214. Locking sleeve; 215. Locking boss; 216. Elastic element; 217. Limiting element; 22. First frame; 222. First docking wall; 23. Guide rod; 24. First fixing element; 3. Fuselage; 31. Maintenance hatch; 4. Second docking module; 41. Second locking head; 411. Locking male head; 412. Slot; 42. Second frame; 421. Inspection port; 422. Second docking wall; 43. Guide bushing; 44. Second fastener; 100. Wing-fuselage docking device.

[0022] In this application, all the accompanying drawings are schematic drawings, used only to illustrate the principle of the present invention, and are not drawn to scale. Detailed Implementation

[0023] The present invention will now be described with reference to the accompanying drawings.

[0024] It should be noted that the directional terms or qualifiers "before" and "after" used in this application refer to... Figure 1 "Below" and "above" in the middle; "left" and "right" refer to... Figure 1 The left and right sides. These are not used to define the absolute position of the parts involved, but can vary depending on the specific circumstances.

[0025] In this application, the directional term or qualifier “axial” refers to the direction indicated by the central axis of the first locking head of the wing-fuselage docking device 100; “radial” refers to the direction perpendicular to the central axis of the first locking head of the wing-fuselage docking device 100.

[0026] Figure 1 The structure of the wing-fuselage docking device 100 according to this utility model is shown. For example... Figure 1 As shown, the wing-fuselage docking device 100 includes a first docking module 2 and a second docking module 4. According to this utility model, the first docking module 2 can be fixedly mounted on the wing 1 or the fuselage 3, and correspondingly, the second docking module 4 is fixedly mounted on the fuselage 3 or the wing 1.

[0027] In this embodiment, the first docking module 2 is fixedly mounted on the wing 1, and the second docking module 4 is fixedly mounted on the fuselage 3. The first docking module 2 and the second docking module 4 are configured to be movable for docking along a first direction. The first direction is parallel to the length direction of the wing 1, i.e. Figure 1 The left and right directions.

[0028] like Figures 1-3 As shown, the first docking module 2 includes a first frame 22, a first locking head 21, and a guide rod 23. The second docking module 4 includes a second frame 42, a second locking head 41, and a guide bushing 43. When the first docking module 2 and the second docking module 4 are docked, the first guide rod 23 is coaxially inserted into the guide bushing 43 to provide guidance; the first locking head 21 can be inserted and fixed with the second locking head 41, thereby fixing the first docking module 2 and the second docking module 4 together.

[0029] The first frame 22 is a rectangular hollow frame structure with multiple weight-reducing holes on its walls to lower gravity and facilitate flight. The first frame 22 is fixedly bonded to the interior of the wing root of the wing 1 using structural adhesive or similar methods. It should be noted that although the first frame 22 is fixedly connected to the wing 1 by adhesive in this embodiment, this does not limit the scope of protection of this utility model. Other connection methods of the first frame 22 and the wing 1 in the prior art should also be within the scope of protection of this utility model. For example, the first frame 22 and the wing 1 can also be fixedly connected by welding, bolting, or other methods. The end face of the first frame 22 facing the fuselage 3 is a first mating wall 222, used to dock with the second mating wall 422 of the second frame 42 (see below for details). Similarly, the second frame 42 is a rectangular hollow frame structure with multiple weight-reducing holes on its walls to lower gravity and facilitate flight. The second frame 42 is fixedly bonded to the interior of the side wall of the fuselage 3 using structural adhesive or similar methods. It should be noted that although the second frame 42 in this embodiment is fixedly connected to the fuselage 3 by adhesive bonding, this is not intended to limit the scope of protection of this utility model. Other connection methods of the second frame 42 and the fuselage 3 in the prior art should also be within the scope of protection of this utility model. For example, the second frame 42 and the fuselage 3 can also be fixedly connected by welding, bolting, etc. The end face of the second frame 42 facing the wing 1 is the second docking wall 422. The first docking wall 222 and the second docking wall 422 are mutually adapted. When the first docking module 2 and the second docking module 4 are docked, the first docking wall 222 and the second docking wall 422 are in contact with each other and fit tightly together, forming a docking shear surface that resists flight shear forces. In this embodiment, both the first docking wall 222 and the second docking wall 422 are constructed as planes.

[0030] Multiple guide rods 23 are fixedly mounted on the first frame 22. In this embodiment, two guide rods 23 are symmetrically arranged in the front and rear portions of the first frame 22. The central axis of the guide rod 23 is parallel to the first direction, and the left end of the guide rod 23 extends beyond the first mating wall 222 of the first frame 22, reaching the outside of the first frame 22. Multiple guide bushings 43 are fixedly mounted in the second frame 42, and the number and position of the guide bushings 43 correspond to the guide rods 23. Therefore, in this embodiment, two guide bushings 43 are symmetrically arranged in the front and rear portions of the second frame 42. The central axis of the guide bushing 43 is parallel to the first direction and coincides with the central axis of its corresponding guide rod 23. After the guide rod 23 is inserted into the guide bushing 43, the guide bushing 43 can circumferentially limit the guide rod 23, so that the guide rod 23 can only move coaxially relative to the guide bushing 43.

[0031] During the docking process of the first docking module 2 and the second docking module 4, the guide rod 23 and the guide bushing 43 can dock before the first locking head 21 and the second locking head 41. That is, the guide rod 23 is already inserted into the guide bushing 43 before the first locking head 21 and the second locking head 41 are inserted. The guide rod 23 and the guide bushing 43 are mutually adapted, so that the first docking module 2 and the second docking module 4 can only move relative to each other along the first direction, ultimately ensuring the precise docking of the first docking module 2 and the second docking module 4. In addition, the guide rod 23 and the guide bushing 43 can also act as reinforcing rods, enhancing the load-bearing capacity of the wing-fuselage docking device 100 in the direction perpendicular to the central axis of the guide rod 23.

[0032] Although this embodiment is provided with two guide rods 23 and two guide bushings 43, this is not intended to limit the scope of protection of this utility model. Structures with any other number of guide rods 23 and guide bushings 43 should also be within the scope of protection of this utility model.

[0033] The first locking head 21 is fixedly disposed on the first mating wall 222 of the first frame 22 along the first direction, that is, the central axis of the first locking head 21 is parallel to the first direction. The left end of the first locking head 21 (the end facing the body 3) extends out of the first frame 22. The second locking head 41 is fixedly disposed inside the second frame 42 along the first direction, that is, the central axis of the second locking head 41 is parallel to the first direction. A connection hole is provided on the second mating wall 422 of the second frame 42 corresponding to the position of the second locking head 41, allowing the first locking head 21 to be inserted. During the docking process of the first docking module 2 and the second docking module 4, the first locking head 21 can be inserted into the second frame 42 through the connection hole on the second mating wall 422 of the second frame 42 and dock with the second locking head 41.

[0034] In this embodiment, the first locking head 21 includes a locking female head 211, and the second locking head 41 includes a locking male head 411. When the first docking module 2 and the second docking module 4 complete docking, the locking male head 411 can be inserted into the locking female head 211, and the locking male head 411 can be fixedly connected to the locking female head 211.

[0035] like Figure 3 and 4 As shown, both the locking female head 211 and the locking male head 411 are cylindrical in shape. The locking female head 211 is fixedly mounted on the first mating wall 222 of the first frame 22 by the first fixing member 24. The locking male head 411 is fixedly mounted on the second mating wall 422 of the second frame 42 by the second fixing member 44.

[0036] In one embodiment, the inner wall of the right end (the end furthest from the body 3) of the locking nut 211 is threaded, and the first fixing member 24 is a bolt. The right end of the locking nut 211 abuts against the left end face of the first mating wall 222 of the first frame 22. The first fixing member 24 passes through the first mating wall 222 from the right side to the left and is threaded to the inner wall of the right end of the locking nut 211, so that the left and right sides of the first mating wall 222 abut against the locking nut 211 and the first fixing member 24 axially, respectively. In this way, the locking nut 211 is fixedly mounted on the first mating wall 222 of the first frame 22 by the first fixing member 24.

[0037] Similarly, the inner wall of the left end (the end away from wing 1) of the locking male head 411 is threaded, and the second fastener 44 is a bolt. The left end of the locking male head 411 abuts against the right end face of the left end wall of the second frame 42 (the side wall of the second frame 42 opposite to the second mating wall 422). The second fastener 44 passes through the left end wall of the second frame 42 from the left side to the right and is fixedly connected to the locking male head 411 by threads, so that the left and right sides of the left end wall of the second frame 42 abut against the second fastener 44 and the locking male head 411 axially, respectively. In this way, the locking male head 411 is fixedly mounted on the left end wall of the second frame 42 by the second fastener 44.

[0038] Although the locking female head 211 and the locking male head 411 in this embodiment are connected to the first frame 22 and the second frame 42 respectively by bolts, this is not intended to limit the scope of protection of this utility model. The locking female head 211 and the locking male head 411 can also be connected to the first frame 22 and the second frame 42 by welding or other means.

[0039] In one specific embodiment, the locking female head 211 is fastened to the first docking wall 222 of the first docking module 2 by a high-strength M16 bolt. The locking male head 411 is firmly fixed inside the cavity of the second docking module 4 by welding.

[0040] In this embodiment, a mounting groove 213 is provided through the left sidewall of the locking nut 211, and multiple mounting grooves 213 are evenly arranged on the locking nut 211 along the circumferential direction. A locking ball 212 is provided in the mounting groove 213, and the locking ball 212 can move in the mounting groove 213 along the diameter direction of the locking nut 211.

[0041] Furthermore, the dimensions of both the inner and outer ends of the mounting groove 213 are smaller than the dimensions of the middle part. The inner end of the mounting groove 213 refers to its position near the central axis of the locking nut 211, the outer end refers to its position away from the central axis of the locking nut 211, and the middle part of the mounting groove 213 refers to the area between the inner and outer ends. The dimensions of both the inner and outer ends of the mounting groove 213 are smaller than the diameter of the locking ball 212, while the dimensions of the middle part of the mounting groove 213 are larger than the diameter of the locking ball 212. This allows the locking ball 212 to move radially along the locking nut 211 within the mounting groove 213 without disengaging from the mounting groove 213. When the locking ball 212 moves radially along the locking nut 211 to its innermost position within the mounting groove 213, it can extend inward beyond the inner wall of the locking nut 211, thereby engaging with the slot 412 provided on the right outer wall of the locking male head 411. When the locking ball 212 moves radially outward within the mounting groove 213 along the locking female head 211, the locking ball 212 can move to the outside of the inner wall of the locking female head 211, thereby enabling the locking male head 411 to move axially within the locking female head 211.

[0042] In this embodiment, a locking sleeve 214 is provided on the outer wall of the locking female head 211. In the first state, the locking sleeve 214 is not in radial contact with the locking ball 212. At this time, the locking ball 212 can move radially outward relative to the mounting groove 213 along the locking female head 211, allowing the locking male head 411 to move axially within the locking female head 211. In the second state, the locking sleeve 214 is located outside the locking ball 212, and the inner wall of the locking sleeve 214 is in radial contact with the locking ball 212. At this time, the locking ball 212 cannot move radially outward relative to the mounting groove 213 along the locking female head 211, and the locking ball 212 is located at the innermost side of the mounting groove 213, connected to the slot 412 of the locking male head 411.

[0043] In one embodiment of the present invention, the locking sleeve 214 is axially movable and disposed on the outer wall of the locking nut 211, and an inwardly protruding locking boss 215 is provided on the inner wall of the locking sleeve 214. An elastic element 216 and a limiting element 217 are also provided on the outer wall of the locking nut 211. Figure 4As shown, the limiting member 217 is fixedly mounted on the outer wall of the locking nut 211 and located on the left side of the locking sleeve 214. The right end of the elastic member 216 is connected to the locking nut 211, and the left end of the elastic member 216 abuts axially against the locking sleeve 214, providing a leftward preload force to the locking sleeve 214. In the first state, the locking sleeve 214 can be pushed to the right by an external force, causing the locking sleeve 214 to move to the right relative to the locking nut 211, compressing the elastic member 216, until the locking boss 215 on the inner wall of the locking sleeve 214 moves to the right side of the locking ball 212. The locking ball 212 can then move radially outward relative to the locking nut 211, at which point the locking male head 411 can be smoothly inserted into the locking nut 211. In the second state, the locking sleeve 214 moves to the left relative to the locking female head 211 under the pre-tightening force of the elastic member 216. Finally, the locking boss 215 of the locking sleeve 214 axially abuts against the limiting member 217, and the inner wall of the locking boss 215 radially abuts against the locking ball 212. At this time, the locking ball 212 can enter the groove 412 of the locking male head 411 under the radial pressure of the locking boss 215, and complete the docking.

[0044] In one specific embodiment, an access port 421 is provided above the second frame 42. Through the access port 421, the locking sleeve 214 can be moved relative to the locking nut 211 by hand or with the aid of tools. Furthermore, a maintenance cover 31 is provided on the skin of the fuselage 3, and the maintenance cover 31 corresponds to the location of the access port 421 on the second frame 42.

[0045] The process of using the wing-fuselage docking device 100 is as follows.

[0046] During the assembly of the fuselage 3 and wing 1, the operator simply aligns the guide rod 23 of the first docking module 2 on the wing 1 with the guide bushing 43 of the second docking module 4 on the fuselage 3, inserting the guide rod 23 into the guide bushing 43, and then smoothly pushes the wing 1 toward the fuselage 3. Under the precise guidance of the guide rod 23 and the guide bushing 43, the first docking module 2 and the second docking module 4 will accurately align to the predetermined position. During this process, the locking male head 411 of the second docking module 4 will insert into the locking female head 211 of the first docking module 2 and automatically lock, thus completing the entire installation process.

[0047] The locking process of male locking head 411 and female locking head 211 is as follows: The maintenance hatch 31 on fuselage 3 and the access port 421 on the second frame 42 are manually opened. As wing 1 is pushed towards fuselage 3, male locking head 411 inserts into female locking head 211, and the two continuously move closer together. Using manual force or tools, locking sleeve 214 is moved relative to female locking head 211, so that locking boss 215 of locking sleeve 214 no longer radially abuts against locking ball 212. When male locking head 411 moves to the position of locking ball 212, male locking head 411 can push locking ball 212 radially outward relative to female locking head 211. When the groove 412 of the locking male connector 411 moves to the position of the locking ball 212, the hand or tool pushing the locking sleeve 214 is released. The locking sleeve 214 returns to its original position under the action of the elastic element 216 until the locking boss 215 of the locking sleeve 214 radially abuts against the locking ball 212, causing part of the locking ball 212 to enter the groove 412 of the locking male connector 411. Figure 4 As shown. Finally, close the access port 421 on the second frame 42 and the maintenance hatch 31 on the fuselage 3.

[0048] The process of disassembling the fuselage 3 and wing 1 is as follows: Manually open the maintenance hatch 31 on the fuselage 3 and the inspection port 421 on the second frame 42. Use your hands or tools to push the locking sleeve 214 relative to the locking nut 211 so that the locking boss 215 of the locking sleeve 214 is no longer radially abutting against the locking ball 212. Then apply a force away from the fuselage 3 to the wing 1 to remove the wing 1 from the fuselage 3.

[0049] The process of assembling or disassembling fuselage and wings using the wing-fuselage docking device 100 provided according to this utility model can be done without any tools, and is fast and precise.

[0050] In the description of this utility model, it should be understood that the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0051] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0052] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0053] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and does not constitute any limitation on this utility model. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A wing-fuselage docking device, characterized in that, It includes a first docking module (2) and a second docking module (4) respectively disposed on the wing (1) and the fuselage (3). The first docking module (2) and the second docking module (4) are configured to be able to dock in a movable manner along a first direction, which is parallel to the length direction of the wing (1). The first docking module (2) includes a first locking head (21) arranged parallel to the first direction, and the second docking module (4) includes a second locking head (41) arranged parallel to the first direction and capable of docking with the first locking head (21). The first docking module (2) further includes a guide rod (23) arranged parallel to the first locking head (21), and the second docking module (4) further includes a guide bushing (43) adapted to the guide rod (23).

2. The wing-fuselage docking device according to claim 1, characterized in that, The first locking head (21) includes a locking female head (211), and a plurality of locking balls (212) are evenly arranged circumferentially on the side wall of the locking female head (211). The second locking head (41) includes a locking male head (411) that can be inserted into the locking female head (211), and a slot (412) that can engage with the locking ball (212) is provided on the outer wall of the locking male head (411).

3. The wing-fuselage docking device according to claim 2, characterized in that, A mounting groove (213) for mounting the locking ball (212) is provided through the side wall of the locking nut (211). The dimensions of the inner and outer ends of the mounting groove (213) are smaller than the dimensions of the middle part, and multiple mounting grooves (213) are evenly distributed circumferentially.

4. The wing-fuselage docking device according to claim 3, characterized in that, The locking ball (212) is configured to move radially within the mounting groove (213). In the first state, the locking ball (212) is able to move radially relative to the mounting groove (213), so that the locking male head (411) is able to move axially relative to the locking female head (211); In the second state, the locking ball (212) cannot move radially relative to the mounting groove (213) and is connected to the slot (412) of the locking male (411).

5. The wing-fuselage docking device according to claim 4, characterized in that, A locking sleeve (214) is provided on the outer wall of the locking nut (211). In the first state, the locking sleeve (214) is not in radial contact with the locking ball (212); In the second state, the locking sleeve (214) is located outside the locking ball (212), and the inner wall of the locking sleeve (214) is in radial contact with the locking ball (212).

6. The wing-fuselage docking device according to claim 5, characterized in that, The locking sleeve (214) is axially movable and disposed on the outer wall of the locking nut (211).

7. The wing-fuselage docking device according to claim 6, characterized in that, An elastic element (216) is provided between the locking sleeve (214) and the locking nut (211), the elastic element (216) being configured to allow the locking sleeve (214) to be in a second state.

8. The wing-fuselage docking device according to claim 7, characterized in that, A limiting member (217) is provided on the outer wall of the locking nut (211). In the second state, the locking sleeve (214) abuts axially against the limiting member (217) under the pre-tightening force of the elastic member (216).

9. The wing-fuselage docking device according to any one of claims 1 to 8, characterized in that, The first docking module (2) further includes a first frame (22), the first locking head (21) and the guide rod (23) are fixedly installed on the first docking wall (222) of the first frame (22), and an inspection port (421) corresponding to the locking sleeve (214) is provided on the first frame (22). The second docking module (4) also includes a second frame (42), the second locking head (41) and the guide bushing (43) are fixedly disposed on the second docking wall (422) of the second frame (42), and the shapes of the first docking wall (222) and the second docking wall (422) are adapted to each other.

10. The wing-fuselage docking device according to claim 9, characterized in that, The first locking head (21) is connected to the first frame (22) via the first fastener (218), and the second locking head (41) is connected to the second frame (42) via the second fastener (44).

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