Small fixed-wing unmanned aerial vehicle disassembling and assembling structure

Abstract

The utility model discloses a small fixed-wing unmanned aerial vehicle dismounting structure which comprises a central wing, two outer wings, at least one connecting rod and a locking mechanism, and the central wing is used for providing lift force of an unmanned aerial vehicle; the two outer wings are respectively fixed on two sides of the central wing so as to expand the wingspan of the unmanned aerial vehicle; the connecting rod is used for connecting the central wing and the outer wing, one end of the connecting rod is provided with a locking joint, and the connecting rod is fixed in the central wing; the locking mechanism is arranged in the outer wing, the locking mechanism comprises a cover plate, a clamping groove and an elastic piece, and the locking connector can be clamped in the clamping groove to achieve connection of the central wing and the outer wing. Through the combination of the central wing, the two outer wings, the at least one connecting rod and the locking mechanisms arranged in the outer wings, stable connection between the central wing and the outer wings is achieved. By means of the design, the assembling process is simplified, an operator can quickly complete installation, and the maintainability of the unmanned aerial vehicle is greatly improved.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft manufacturing technology, and specifically relates to a disassembly and assembly structure for a small fixed-wing unmanned aerial vehicle. Background Technology

[0002] Currently, fixed-wing unmanned aerial vehicles (UAVs) are typically designed with either a one-piece molded structure or a traditional center wing and outer wing docking structure. While these two methods meet flight requirements to some extent, they have several drawbacks. First, one-piece molded wings are difficult to disassemble and assemble, which not only increases the difficulty of maintenance and repair but also requires replacing the entire wing when a damaged part needs to be replaced, leading to a significant increase in maintenance costs. Furthermore, because the wings cannot be disassembled, they require large transport vehicles during transportation, increasing transportation costs and making them susceptible to damage due to space constraints during transport, thus affecting flight safety.

[0003] Traditional integrated or docking structures also present storage inconveniences, as they occupy a significant amount of space and hinder warehouse management. For manufacturers, the complexity of mold making, the difficulty in processing, and the resulting high production costs are also significant issues. Furthermore, the design of these structures limits the flexibility and adaptability of unmanned aerial vehicles, especially in situations requiring frequent configuration adjustments or operation within confined spaces.

[0004] Therefore, to address the aforementioned issues, there is an urgent need to develop a new connection method between the central wing and outer wings of a fixed-wing UAV, in order to overcome the shortcomings of existing technologies and provide more convenient assembly and disassembly, lower maintenance costs, higher transportation efficiency, better storage performance, and more flexible configuration possibilities. This new structure should be able to significantly improve the maintainability and economy of UAVs without affecting flight performance. Utility Model Content

[0005] In order to overcome the shortcomings of the existing technology, the purpose of this utility model is to provide a disassembly and assembly structure for a small fixed-wing UAV, which aims to solve the problems of difficulty in disassembly and assembly, difficulty in storage, high maintenance costs, and inconvenience in transportation in the traditional connection structure between the central wing and the outer wing of a fixed-wing UAV.

[0006] To solve the above problems, the technical solution adopted by this utility model is as follows: a small fixed-wing unmanned aerial vehicle (UAV) assembly and disassembly structure, comprising: a central wing, wherein the central wing is used to provide lift for the UAV;

[0007] Two outer wings, which are respectively fixed to both sides of the central wing to extend the wingspan of the UAV;

[0008] At least one connecting rod is provided for connecting the central wing and the outer wing, and one end of the connecting rod is provided with a locking joint. The connecting rod is fixed inside the central wing.

[0009] A locking mechanism is provided inside the outer wing. The locking mechanism includes a cover plate, a slot, and an elastic element. The locking connector can be engaged with the slot to connect the central wing and the outer wing.

[0010] Compared to existing technologies, the advantages of this invention are as follows: a stable connection between the central wing and the outer wings is achieved through a combination of a central wing, two outer wings, at least one connecting rod, and a locking mechanism located inside the outer wings. This design not only simplifies the assembly process, allowing operators to quickly complete installation, but also greatly improves the maintainability of the UAV. Operators only need to insert the connecting rod into the corresponding hole and lock it with a simple mechanical action, without the need for complex tools or special skills, thus lowering the assembly threshold. When one outer wing is damaged, the user can directly disassemble and replace the damaged part, instead of replacing the entire wing as in the traditional method. This not only reduces material waste but also lowers maintenance costs.

[0011] The above-described disassembly and assembly structure includes a locking mechanism that further includes a connecting shaft. The slot is provided with a first card plate and a second card plate, and the connecting shaft is provided between the first card plate and the second card plate.

[0012] The above-described disassembly and assembly structure includes a locking mechanism that further comprises a housing and connecting bolts. The slot and elastic element are fixed in the housing, and the cover plate can be fixed to the outside of the housing.

[0013] In the above-described disassembly and assembly structure, each outer wing is connected to the central wing by two connecting rods, and each connecting rod is provided with an independent locking joint.

[0014] In the above-described disassembly and assembly structure, the locking joint and the connecting rod are connected by adhesive bonding.

[0015] In the above-described disassembly and assembly structure, an auxiliary reinforcing device is also provided between the locking joint and the connecting rod.

[0016] In the above-described disassembly and assembly structure, the auxiliary reinforcing device is a rivet.

[0017] In the above-described disassembly and assembly structure, both the central wing and the outer wing are provided with docking holes, and the position of the docking hole of the central wing is determined by using a standard template of the docking hole of the outer wing.

[0018] During assembly of the above-described disassembly and assembly structure, the connecting rod is inserted into the outer wing, the gap between the central wing and the outer wing is adjusted to be within acceptable limits, and the outer wing is fixed to the central wing using the connecting bolts. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the disassembly and assembly structure of an embodiment of the present utility model. Figure 1 ;

[0020] Figure 2 This is a schematic diagram of the disassembly and assembly structure of an embodiment of the present utility model. Figure 2 ;

[0021] Figure 3 This is a schematic diagram of the disassembly and assembly structure of an embodiment of the present utility model. Figure 3 ;

[0022] Figure 4 This is a schematic diagram of the disassembly and assembly structure of an embodiment of the present utility model. Figure 4 ;

[0023] The reference numerals are as follows: 100 Central wing, 200 Outer wing, 300 Linkage rod, 310 Locking joint, 400 Locking mechanism, 410 Cover plate, 420 Slot, 421 First card plate, 422 Second card plate, 430 Connecting shaft, 440 Elastic element, 450 Box body, 460 Connecting screw. Detailed Implementation

[0024] The embodiments of this utility model are described in detail below, with reference to Figures 1 to 4This utility model provides a small fixed-wing unmanned aerial vehicle (UAV) assembly and disassembly structure, including: a central wing 100, two outer wings 200, at least one connecting rod 300, and a locking mechanism 400. The central wing 100 is used to provide lift for the UAV; the two outer wings 200 are respectively fixed to both sides of the central wing 100 to expand the wingspan of the UAV; the connecting rod 300 is used to connect the central wing 100 and the outer wings 200, and one end of the connecting rod 300 is provided with a locking connector 310, and the connecting rod 300 is fixed inside the central wing 100; the locking mechanism 400 is disposed inside the outer wings 200, and the locking mechanism 400 includes a cover plate 410, a slot 420, and an elastic element 440. The locking connector 310 can be engaged with the slot 420 to realize the connection between the central wing 100 and the outer wings 200. A stable connection between the central wing 100 and the outer wings 200 is achieved through a combination of the central wing 100, the two outer wings 200, at least one connecting rod 300, and a locking mechanism 400 located inside the outer wings 200. This design not only simplifies the assembly process, allowing operators to quickly complete installation, but also greatly improves the maintainability of the UAV. In traditional UAV designs, the central wing 100 and outer wings 200 are usually integrally molded or use a complex docking structure, which leads to the need to replace the entire wing during maintenance, resulting in high costs and low efficiency. The disassembly and assembly structure of this application allows users to replace only the damaged portion of the outer wing 200, reducing maintenance costs and time. Operators only need to insert the connecting rod 300 into the corresponding hole and lock it with a simple mechanical action, without the need for complex tools or special skills, lowering the assembly threshold; when one side of the outer wing 200 is damaged, the user can directly disassemble and replace the damaged part, instead of needing to replace the entire wing as in the traditional method. This not only reduces material waste but also lowers maintenance costs. Furthermore, refer to... Figure 2 Because one end of the connecting rod 300 is equipped with a locking connector 310, which can be engaged in the slot 420 within the outer wing 200, the stability and strength of the connection between the central wing 100 and the outer wing 200 are ensured, thereby guaranteeing the safety of the aircraft during flight. At the same time, this modular design also facilitates transportation and storage, as the drone can be disassembled into smaller parts before transport, reducing the space occupied, improving transportation efficiency, and reducing risks.

[0025] Furthermore, referring to Figure 4The locking mechanism 400 also includes a connecting shaft 430. The slot 420 is provided with a first card plate 421 and a second card plate 422, and the connecting shaft 430 is provided between the first card plate 421 and the second card plate 422. Of course, this application does not limit the specific connection method of the first card plate 421 and the second card plate 422. Preferably, the first card plate 421 and the second card plate 422 are integrally formed. When the locking connector 310 is engaged in the slot 420, that is, engaged between the first card plate 421 and the second card plate 422, further, both the first card plate 421 and the second card plate 422 are provided with through holes. The connecting shaft 430 can pass through the through holes to fix the distance between the first card plate 421 and the second card plate 422. The structural design of the slot 420 significantly enhances the fitting accuracy and stability between the locking connector 310 and the slot 420. Specifically, the connecting shaft 430, as an intermediate part, provides an additional support point, making the locking connector 310 more smooth and stable when inserted into the slot 420, reducing the possibility of loosening caused by vibration or other external factors. The arrangement between the first locking plate 421 and the second locking plate 422 forms a stable frame structure, which can both guide the locking connector 310 accurately into the slot 420 and provide sufficient friction after locking to prevent it from accidentally disengaging. This improvement is crucial for enhancing the overall performance of the UAV, as it directly relates to the safety and reliability of the wing connection during flight. Furthermore, this design simplifies the manufacturing process of the locking mechanism 400, reduces production costs, and also facilitates subsequent maintenance and inspection. Further, referring to... Figure 3The locking mechanism 400 also includes a housing 450 and connecting bolts 460. The slot 420 and elastic element 440 are fixed within the housing 450, and the cover plate 410 can be fixed to the outside of the housing 450. During final assembly, the central wing 100 is aligned with the outer wing 200. After determining the position of the outer wing 200 and the locking mechanism 400 by locking the connector 310 at the end of the connecting rod 300, it is fixed to the outer wing 200 using the connecting bolts 460. Of course, this invention does not limit the specific fixing method between the locking connector 310 and the connecting rod 300. Preferably, the locking connector 310 and the connecting rod 300 are connected by adhesive bonding. Adhesive bonding is a simple and effective fixing method. The application of adhesive bonding technology here has several obvious advantages. First, it provides good bonding strength, ensuring a tight connection between the locking connector 310 and the connecting rod 300, preventing it from easily falling off. This is especially important during the flight of a drone, as any loosening of the connection can lead to serious safety hazards. Secondly, the adhesive bonding process is relatively simple, requiring no complex tools or equipment, thus reducing manufacturing costs. Furthermore, the choice of adhesive material can be adjusted according to specific needs; for example, adhesives with good weather resistance can be selected to cope with various harsh weather conditions. Of course, an auxiliary reinforcing device is also provided between the locking joint 310 and the connecting rod 300. Although adhesive bonding technology can provide a certain connection strength, in some high-strength application scenarios, relying solely on adhesive bonding may not fully meet design requirements. Therefore, the introduction of auxiliary reinforcing devices becomes a necessary supplementary measure. The main function of these reinforcing devices is to enhance the bonding force between the locking joint 310 and the connecting rod 300, preventing connection failure due to extreme conditions (such as high impact, high-frequency vibration). Of course, this utility model does not limit the specific type of auxiliary reinforcing device; preferably, the auxiliary reinforcing device is a rivet. Specifically, the auxiliary reinforcing device can provide additional support through physical means, such as reinforcing the connection part with rivets, screws, or other types of fasteners. Simultaneously, the presence of the housing 450 provides protection and positioning for the slot 420 and the elastic element 440, ensuring that they do not shift or deform during use, thereby maintaining the working performance of the locking mechanism 400. Meanwhile, the housing 450 also serves as a waterproof and dustproof unit, extending the service life of the locking mechanism 400. The connecting bolts 460 are used to fix the cover plate 410 to the outside of the housing 450, forming a closed unit to prevent external environmental factors from affecting the internal components. More importantly, the connecting bolts 460 can also be used to adjust the tightness of the locking mechanism 400, flexibly adjusting the connection strength between the central wing 100 and the outer wing 200 according to actual conditions.

[0026] Furthermore, the outer wing 200 is connected to the central wing 100 via two connecting rods 300, each of which has an independent locking connector 310. The dual-link system offers several advantages over a single-link system. First, the dual-link system distributes the load, reducing the pressure on each link 300 and improving the durability and reliability of the connection. Second, the two independent locking connectors 310 can each match the slots 420 on the outer wing 200, ensuring precise docking between the central wing 100 and the outer wing 200 and avoiding deviations that might occur due to a single connection point. Third, the dual-link design provides a more even distribution of force between the central wing 100 and the outer wing 200, helping to maintain the overall balance and stability of the UAV structure, which has a positive impact on flight performance. Furthermore, both the central wing 100 and the outer wing 200 have mating holes, and the position of the mating hole on the central wing 100 is determined using a standard template for the mating hole on the outer wing 200. The outer wing 200 mating hole standard template is a template or model precisely manufactured according to design specifications. It defines the specific dimensions, shape, and position of the mating holes on the outer wing 200 used to connect to the central wing 100. The template serves as a reference point, ensuring that the mating holes on all manufactured outer wing 200 components have the same positional accuracy. When manufacturing the central wing 100, space needs to be reserved inside the central wing 100 for installing connecting rods 300, the ends of which will be inserted into the mating holes of the outer wing 200. To ensure accurate connection between the central wing 100 and the outer wing 200, the installation position of the connecting rods 300 within the central wing 100 must perfectly match the mating holes on the outer wing 200. Therefore, by using the outer wing 200 mating hole standard template, the exact installation position of the connecting rods 300 can be marked on the molding die of the central wing 100.

[0027] Furthermore, during assembly, the connecting rod 300 is inserted into the outer wing 200, and the gap between the central wing 100 and the outer wing 200 is adjusted to the acceptable level. The outer wing 200 is then fixed to the central wing 100 using connecting bolts 460. This process design fully considers the feasibility and efficiency of actual operation. First, inserting the connecting rod 300 is a straightforward and easy process; operators simply need to align the connecting rod 300 with the mating holes on the outer wing 200 according to the standard template to successfully complete the initial connection. Next, adjusting the gap between the central wing 100 and the outer wing 200 is crucial for ensuring proper alignment. Fine-tuning allows for a tighter and smoother connection between the central wing 100 and the outer wing 200, eliminating any potential gaps, which directly impacts the aircraft's aerodynamic performance. Finally, the connection is secured using connecting bolts 460, providing sufficient mechanical strength while allowing operators to flexibly adjust the tightness of the connection as needed. This feature is extremely useful in practical applications, such as when performing special missions or under varying climatic conditions, allowing for adjustments to the connection's strength to suit different flight requirements.

[0028] It should be noted that in the description of this utility model, any descriptions of orientation, such as up, down, front, back, left, right, etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings. They 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, be constructed or operated in a specific orientation, and should not be construed as a limitation of this utility model.

[0029] In the description of this utility model, "several" means one or more, "more than" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. If "first" or "second" is mentioned, it is only for distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0030] In the description of this utility model, unless otherwise explicitly defined, terms such as "setting," "installation," and "connection" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this utility model in conjunction with the specific content of the technical solution.

[0031] The above embodiments are merely preferred embodiments of this utility model and should not be construed as limiting the scope of protection of this utility model. Any non-substantial changes and substitutions made by those skilled in the art based on this utility model shall fall within the scope of protection claimed by this utility model.

Claims

1. A disassembly and assembly structure for a small fixed-wing unmanned aerial vehicle (UAV), characterized in that, include: A central wing (100) is used to provide lift for the UAV; Two outer wings (200) are respectively fixed to both sides of the central wing (100) to extend the wingspan of the UAV; At least one connecting rod (300) is used to connect the central wing (100) and the outer wing (200), one end of the connecting rod (300) is provided with a locking joint (310), and the connecting rod (300) is fixed inside the central wing (100); A locking mechanism (400) is disposed inside the outer wing (200). The locking mechanism (400) includes a cover plate (410), a slot (420), and an elastic element (440). The locking connector (310) can be engaged with the slot (420) to realize the connection between the central wing (100) and the outer wing (200).

2. The disassembly and assembly structure according to claim 1, characterized in that, The locking mechanism (400) further includes a connecting shaft (430), and the slot (420) is provided with a first card plate (421) and a second card plate (422), with the connecting shaft (430) between the first card plate (421) and the second card plate (422).

3. The disassembly and assembly structure according to claim 2, characterized in that, The locking mechanism (400) also includes a housing (450) and connecting bolts (460). The slot (420) and elastic element (440) are both fixed in the housing (450), and the cover plate (410) can be fixed to the outside of the housing (450).

4. The disassembly and assembly structure according to claim 1, characterized in that, Each of the outer wings (200) is connected to the central wing (100) by two connecting rods (300), and each connecting rod (300) is provided with an independent locking joint (310).

5. The disassembly and assembly structure according to claim 1, characterized in that, The locking joint (310) and the connecting rod (300) are connected by adhesive bonding.

6. The disassembly and assembly structure according to claim 1, characterized in that, An auxiliary reinforcing device is also provided between the locking joint (310) and the connecting rod (300).

7. The disassembly and assembly structure according to claim 6, characterized in that, The auxiliary reinforcing device is a rivet.

8. The disassembly and assembly structure according to claim 1, characterized in that, Both the central wing (100) and the outer wing (200) are provided with docking holes, and the position of the docking hole of the central wing (100) is determined by using the standard template of the docking hole of the outer wing (200).

9. The disassembly and assembly structure according to claim 3, characterized in that, During assembly, the connecting rod (300) is inserted into the outer wing (200), the gap between the central wing (100) and the outer wing (200) is adjusted to be acceptable, and the outer wing (200) is fixed to the central wing (100) by the connecting bolt (460).

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