Quick assembly structure of nozzle for unmanned aerial vehicle

Abstract

The utility model discloses a kind of for the quick assembly structure of spray pipe of unmanned plane, including the spray pipe component assembled on the main body of unmanned plane, spray pipe component is by pipe body, and with the shunt control box of the end communication of pipe body constitutes, pipe body and shunt control box respectively through first locking mechanism and second locking structure and the main body of unmanned plane realize detachable quick assembly structure.The utility model solves the problem that the existing technology lacks quick assembly structure, assembly process is complicated and the structure strength is not high in spraying type unmanned plane.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicles (UAVs), and in particular to a rapid assembly structure for the nozzle of an UAV. Background Technology

[0002] With the rapid development of drone technology, today's drones are not only multifunctional but also increasingly streamlined and robust in structure. Among them, drones used for spraying operations have received widespread acclaim due to their suitability for low- and medium-altitude spraying.

[0003] Structurally, existing spraying drones are mainly assembled from spraying components and the drone body. Currently, the assembly structure between the spraying components and the drone body is generally achieved through direct welding or by aligning screw holes and bolts. While welding maximizes structural strength, it makes disassembly and modification impossible once welded. Using screws and bolt holes requires creating multiple holes, reducing structural strength and complicating the assembly process. Therefore, traditional spraying components currently lack a quick and robust assembly structure with the drone body.

[0004] In view of this, this technical solution proposes a quick assembly structure for the nozzle of a drone. It adopts two sets of locking mechanisms to quickly fix the pipe body and control box of the water spray component to the main body of the drone. It uses a special base for connection, has few openings, a fast assembly process, high rigidity after assembly, and is easy to disassemble and modify. Utility Model Content

[0005] The present invention aims to at least partially solve one of the technical problems in the related art. Therefore, the main objective of this invention is to provide a quick-assembly structure for a nozzle used in unmanned aerial vehicles (UAVs), addressing the issues of existing spraying UAVs lacking quick-assembly structures, having cumbersome assembly processes, and exhibiting low structural strength.

[0006] To achieve the above objectives, this utility model provides a quick assembly structure for a nozzle of an unmanned aerial vehicle (UAV), including a nozzle assembly mounted on the main body of the UAV. The nozzle assembly consists of a pipe body and a flow splitting control box connected to the end of the pipe body. The pipe body and the flow splitting control box are respectively connected to the UAV body through a first locking mechanism and a second locking structure to achieve a detachable and quick-assembly structure. The first locking mechanism includes a limiting sleeve frame that is tightly clamped onto the tube body, and a first insert plate connected to the bottom of the limiting sleeve frame. A first base is provided on the main body of the drone in the insertion direction of the first insert plate. A first frame is provided on the first base, and a first slot for inserting the first insert plate is formed between the top of the first frame and the surface of the first base. The second locking mechanism includes a second insert plate extending from one side of the diversion control box. A second base is provided on the drone body in the insertion direction of the second insert plate. A second frame is provided on the second base, and a second slot for inserting the second insert plate is formed between the top of the second frame and the surface of the second base. Both the first frame and the second frame are provided with locking holes for further fixing after insertion.

[0007] As a further embodiment of this utility model, the nozzle assembly is mounted on the landing gear crossbeam at the bottom of the UAV body. The landing gear crossbeam consists of two parallel rods, and the first locking mechanism and the second locking structure are respectively mounted on the two rods.

[0008] As a further embodiment of this utility model, the limiting sleeve includes an upper sleeve and a lower sleeve, the two sleeves are mirror-assembled, and a groove matching the outline of the tube is formed in the middle, and fastening holes are correspondingly opened on the upper sleeve and the lower sleeve.

[0009] As a further improvement of this utility model, the number of limiting sleeves fastened to the pipe body is at least two.

[0010] As a further improvement of this utility model, both the first base and the second base are provided with assembly holes.

[0011] As a further embodiment of this utility model, the second insert plate is an extruded structure formed by the housing of the diversion control box to one side.

[0012] As a further embodiment of this invention, the insertion directions of the first insert plate and the second insert plate are the same.

[0013] The beneficial effects of this utility model are as follows: The nozzle assembly, consisting of a tube body and a flow control box, is quickly and easily connected to the UAV body using a first and a second locking mechanism. Assembly is simple: insert the first insert plate, connected to the limiting sleeve on the tube body, into the first slot of the first base on the UAV body; simultaneously, insert the second insert plate extending from one side of the flow control box into the second slot of the second base; and finally, secure it using the locking holes on the frame. This avoids the non-removable nature of traditional welding or the cumbersome assembly with numerous screws, greatly improving maintenance and modification efficiency. Because the load is primarily supported by the base and slots, and only a few locking holes are used in key locations, the number of openings on the UAV body is minimized, effectively ensuring the integrity of the main structure. This achieves faster assembly and disassembly while providing higher connection strength and reliability than traditional methods, making the nozzle assembly more stable during operation. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the technical solutions of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0015] Figure 1 This is a three-dimensional view of the drone body and nozzle assembly after assembly in this utility model.

[0016] Figure 2 This is a planar view of the insertion action of the nozzle assembly during assembly in this utility model.

[0017] Figure 3 This is a side view of the nozzle assembly and the main body of the UAV after assembly.

[0018] Figure 4 This is a schematic diagram showing the positions of the first locking mechanism and the second locking mechanism in this utility model.

[0019] Figure 5 This is a magnified schematic diagram of a portion of the structure of the first insert plate and the first base in this utility model.

[0020] Figure 6 This is a schematic diagram of the components of the first locking mechanism in this utility model before and after insertion.

[0021] Figure 7 This is a partially enlarged schematic diagram of the second locking mechanism in this utility model after assembly.

[0022] Figure 8 This is a partially enlarged schematic diagram of the components of the second locking mechanism in this utility model when it is not assembled.

[0023] Figure 9 This is a schematic diagram of the second base, second frame, and second slot structure in this utility model.

[0024] Figure 10 This is a schematic diagram of the components of the first base in this utility model after assembly on one side of the landing gear crossbeam.

[0025] Figure 11 This is a schematic diagram showing the components of the second base in this utility model assembled on the other side of the landing gear crossbeam.

[0026] 1 drone body 311 First insert 10 Landing gear crossbeam 312 First base 2 Nozzle assembly 3120 First frame 20 tube body 3121 First slot 21 shunt control box 3122 Locking hole 31 First locking mechanism 32 Second locking mechanism 310 Limiting frame 320 Second insert plate 3101 upper frame 321 Second base 3102 Lower frame 3210 Second frame 3103 groove 3211 Second slot 3104 Fastening hole 33 Assembly holes Detailed Implementation

[0027] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] The term "one embodiment" or "implementation" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of this utility model. In the description of this utility model, it should be understood that the terms "upper," "lower," "left," "right," "top," "bottom," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. Furthermore, 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. Thus, a feature defined with "first" and "second" may explicitly or implicitly include one or more of that feature. Moreover, the terms "first," "second," etc., are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this utility model described herein can be implemented in orders other than those illustrated or described herein.

[0029] Please see the appendix Figure 1-11 , The nozzle quick assembly structure of this solution includes a nozzle assembly (2) mounted on the main body (1) of the UAV. The nozzle assembly (2) consists of a pipe body (20) and a flow control box (21) connected to the end of the pipe body (20). The pipe body (20) is connected to the main body (1) of the UAV through a first locking mechanism (31), and the flow control box (21) is connected to the main body (1) of the UAV through a second locking mechanism (32), so as to realize detachable quick assembly. The first locking mechanism (31) includes a limiting sleeve (310) that is fastened to the tube body (20) and a first insert plate (311) connected to the bottom of the limiting sleeve (310). A first base (312) is set on the main body of the drone (1). A first frame (3120) is installed on the first base (312). A first slot (3121) is formed between the top of the first frame (3120) and the surface of the first base (312). During assembly, the first insert plate (311) slides into the first slot (3121) along the insertion direction to achieve initial fixation. The second locking mechanism (32) includes a second insert plate (320) extending from one side of the diversion control box (21), a second base (321) on the drone body (1), a second frame (3210) mounted on the second base (321), and a second slot (3211) formed between the top of the second frame (3210) and the surface of the second base (321). During assembly, the second insert plate (320) slides into the second slot (3211) along the insertion direction, thus achieving initial fixation. To further reinforce the mechanism, locking holes (3122) are provided on both the first frame (3120) and the second frame (3210). After insertion, fasteners such as screws can be used to lock the mechanism through the locking holes (3122) to prevent loosening.

[0030] The rapid assembly structure provided by this solution is very simple and quick to assemble. Specifically, during assembly, simply insert the first insert plate (311) and the second insert plate (320) into their respective slots and then fix them with fasteners. No complicated alignment or welding operations are required, which greatly improves assembly efficiency. Furthermore, by reducing the number of holes on the UAV body (1), the structural integrity is maintained, the overall strength is improved, and the weakness caused by multiple holes is avoided. The limiting sleeve (310) clamps the pipe body (20) to ensure that the pipe body (20) is stable and does not shake. The diversion control box (21) is directly fixed by the second insert plate (320), which is also firm and reliable. After the overall assembly, it can effectively withstand the vibration during flight, ensuring the stability and safety of the spraying operation. Moreover, it is easy to disassemble and modify, and adapts to a variety of usage scenarios.

[0031] Optionally, the insertion directions of the first locking mechanism (31) and the second locking mechanism (32) can be the same or different. For example, if the first locking mechanism (31) is inserted and fixed towards the X-axis, and the tube (20) is a flexible tube, the second locking mechanism (32) can be fixed after bending. Another form is that the second locking mechanism (32) is inserted in the opposite direction to the first locking mechanism (31). For example, after the first locking mechanism (31) is assembled and fixed, the second locking mechanism (32) is inserted backward, that is, inserted in the opposite direction to the first locking mechanism (31). Therefore, it can be understood that the arrangement, insertion direction, and sequence of the first locking mechanism (31) and the second locking mechanism (32) in this solution can vary according to the structure, model, or function to be achieved of the UAV.

[0032] In addition, the locking mechanism of this solution is not limited to the assembly of the tube body 20 and the diversion control box 21. It can also be assembled only on the tube body 20 or only on the diversion control box 21. It can also be assembled in different positions according to the structure and purpose of the actual UAV body 1.

[0033] Reference Appendix Figure 2 , 10 -11, In this technical solution, the nozzle assembly (2) is mounted on the landing gear crossbeam (10) at the bottom of the UAV body (1). The landing gear crossbeam (10) is composed of two parallel rods. The first locking mechanism (31) is installed on one of the rods to fix the tube (20), while the second locking mechanism (32) is installed on the other rod to fix the diversion control box (21). Since the landing gear crossbeam (10) itself is sturdy and has a large bottom space, after the two ends of the nozzle assembly (2) are assembled, the weight distribution is uniform, and the overall structure is more compact and stable.

[0034] Of course, the nozzle assembly (2) is not necessarily installed here. It can also be installed on other load-bearing structures of the fuselage, such as brackets on both sides of the fuselage or other dedicated mounting points under the fuselage, depending on the specific design and mission requirements of the UAV.

[0035] Reference Appendix Figure 6As a preferred embodiment of this utility model, in this technical solution, the limiting sleeve (310) is composed of an upper sleeve (3101) and a lower sleeve (3102). The two sleeves are assembled in a mirror manner. After assembly, a groove (3103) matching the outer contour of the tube body (20) will be formed in the middle, tightly clamping the tube body (20) in the middle. Fastening holes (3104) are correspondingly opened on the upper sleeve (3101) and the lower sleeve (3102). Fasteners such as bolts can be used to fix the tube body (20) through these holes. It is convenient to install and disassemble the tube body (20). It is only necessary to loosen or tighten the fasteners. At the same time, it can also adapt well to tube bodies (20) of different diameters or shapes.

[0036] Reference Appendix Figure 5 As a preferred embodiment of the present invention, in order to more securely fix the tube body (20), a preferred implementation is to fasten at least two limiting sleeves (310) on the tube body (20), which can lock the tube body (20) in different positions in sections, making the force distribution of the clamping more uniform, effectively preventing the tube body (20) from shaking or twisting at a single fixed point, thereby greatly improving the overall strength of the connection between the tube body (20) and the UAV body (1).

[0037] Of course, it is understandable that the number of limiting sleeves (310) involved in this scheme is not fixed. For example, for shorter pipe sections, a single reinforced limiting sleeve (310) may meet the requirements, while for longer or heavier pipes (20), three or more limiting sleeves (310) can be used for multi-point fixation to adapt to different structural strength and stability requirements.

[0038] Reference Appendix Figure 6 , 8 As a preferred embodiment of this utility model, the first base (312) and the second base (321) of this solution are preferably provided with mounting holes (33). The mounting holes (33) can be used to securely install the base itself onto the drone body (1) using fasteners such as screws. Although it is necessary to open holes on the drone body (1) when installing the base, compared with the traditional method which requires opening a large number of screw holes for each fixing point of the tube (20) and the control box, this solution uses the base for centralized connection, which significantly reduces the number and size of the holes and preserves the integrity of the lower main structure to the greatest extent. Thus, while achieving quick disassembly and assembly, it can still ensure that the connection point has high structural strength.

[0039] Of course, in practical applications, the way to fix the base to the drone body (1) is not limited to screw connection. For example, depending on the body material and usage scenario, other methods such as special adhesive bonding or embedded buckle can be used for fixing.

[0040] Reference Appendix Figure 8 As a preferred embodiment of the present invention, in this solution, a preferred manufacturing method for the second insert plate (320) is to make it a structure that is directly extruded to one side as the shell of the diversion control box (21). Therefore, the second insert plate (320) and the shell of the diversion control box (21) can be a complete whole, which simplifies the production process, reduces the number of parts, and enhances the structural integrity and reliability of the second locking mechanism (32).

[0041] Reference Appendix Figure 2 As a preferred embodiment of this utility model, the insertion directions of the first insert plate (311) and the second insert plate (320) in this solution can be the same. When installing the nozzle assembly (2), the operator can slide the first insert plate (311) connecting the tube body (20) and the second insert plate (320) connecting the diversion control box (21) into the corresponding first slot (3121) and second slot (3211) in the same direction, either sequentially or simultaneously. This simplifies the operation process, makes the assembly action smoother and more intuitive, and eliminates the need to change angles or postures, thereby improving assembly efficiency and reducing the difficulty of operation. It is especially convenient for quick assembly and disassembly in the field or under poor lighting conditions.

[0042] However, setting the insertion direction of both to be the same is only one preferred embodiment. In practical applications, it can be flexibly adjusted according to the specific fuselage structure, pipeline layout or special functional requirements of the UAV.

[0043] Specifically, for example, when the tube body (20) is made of flexible material, the first insert plate (311) can be inserted forward and fixed first, then the tube body (20) can be bent, and then the second insert plate (320) can be inserted into its corresponding slot from the side or vertical direction. Alternatively, in some compact fuselage designs, in order to optimize space utilization, the insertion directions of the first insert plate (311) and the second insert plate (320) can be designed to be completely opposite, that is, one is inserted forward and the other is inserted backward, forming a plug-in structure.

[0044] Therefore, it is understandable that the specific arrangement, insertion direction, and even assembly sequence of the first locking mechanism (31) and the second locking mechanism (32) can be designed and varied in a diverse manner according to the UAV's model structure, maintenance convenience, or specific functions to be achieved.

[0045] The following points need to be explained: (1) The accompanying drawings of the embodiments of this disclosure only involve the structures involved in the embodiments of this disclosure. Other structures can be referred to the general design.

[0046] (2) Where there is no conflict, features of the same embodiment and different embodiments of this disclosure can be combined with each other.

[0047] The above are merely specific embodiments of this disclosure, but the scope of protection of this disclosure is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this disclosure should be included within the scope of protection of this disclosure. Therefore, the scope of protection of this disclosure should be determined by the scope of the claims.

Claims

1. A quick assembly structure for a nozzle of an unmanned aerial vehicle (UAV), characterized in that, include The nozzle assembly mounted on the main body of the drone. The nozzle assembly consists of a pipe body and a flow splitting control box connected to the end of the pipe body. The pipe body and the flow splitting control box are respectively connected to the main body of the UAV through a first locking mechanism and a second locking mechanism to achieve a detachable and quick-assembly structure. The first locking mechanism includes a limiting sleeve frame that is tightly clamped onto the tube body, and a first insert plate connected to the bottom of the limiting sleeve frame. A first base is provided on the main body of the drone in the insertion direction of the first insert plate. A first frame is provided on the first base, and a first slot for inserting the first insert plate is formed between the top of the first frame and the surface of the first base. The second locking mechanism includes a second insert plate extending from one side of the diversion control box. A second base is provided on the drone body in the insertion direction of the second insert plate. A second frame is provided on the second base, and a second slot for inserting the second insert plate is formed between the top of the second frame and the surface of the second base. Both the first frame and the second frame are provided with locking holes for further fixing after insertion.

2. The rapid assembly structure for a nozzle of an unmanned aerial vehicle according to claim 1, characterized in that, The nozzle assembly is mounted on the landing gear crossbeam at the bottom of the UAV body. The landing gear crossbeam consists of two parallel rods, and the first locking mechanism and the second locking mechanism are respectively mounted on the two rods.

3. The rapid assembly structure for a nozzle of a drone according to claim 1, characterized in that, The limiting sleeve includes an upper sleeve and a lower sleeve, which are mirror images of each other and have a groove in the middle that matches the outline of the tube. Fastening holes are provided on the upper sleeve and the lower sleeve respectively.

4. The rapid assembly structure for a nozzle of a UAV according to claim 1, characterized in that, The number of limiting sleeves fastened to the pipe body is at least two.

5. The quick assembly structure for a nozzle of a drone according to claim 1, characterized in that, Both the first base and the second base have assembly holes.

6. The quick assembly structure for a nozzle of an unmanned aerial vehicle according to claim 1, characterized in that, The second insert plate is a structure formed by extruding the housing of the diversion control box to one side.

7. The rapid assembly structure for a nozzle of an unmanned aerial vehicle according to claim 1, characterized in that, The insertion direction of the first insert plate and the second insert plate is the same.

Images