Tail assembly and fixed-wing drone

Abstract

The application discloses a tail wing assembly and a fixed-wing unmanned aerial vehicle. The tail wing assembly comprises a vertical wing arranged in a plate shape; a horizontal wing arranged in a plate shape and provided with a through hole; and an assembling structure fixed to the vertical wing and capable of being connected to a frame of the fixed-wing unmanned aerial vehicle through the through hole, so that the vertical wing presses and fixes the horizontal wing to the frame. The tail wing assembly provided by the application realizes detachable assembly, simplifies the complexity of the structure and reduces the deployment and transportation cost of the fixed-wing unmanned aerial vehicle.

Description

Technical Field

[0001] This application belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a tail fin assembly and a fixed-wing UAV. Background Technology

[0002] In related technologies, the tail fins of fixed-wing UAVs are mostly non-detachable, and the few detachable tail fin connection structures are mostly complex and costly. Summary of the Invention

[0003] This application aims to provide a tail fin assembly and a fixed-wing unmanned aerial vehicle, which at least solves one of the problems in the prior art.

[0004] To solve the above-mentioned technical problems, this application is implemented as follows: According to a first aspect of this application, a tail fin assembly is provided for use in a fixed-wing unmanned aerial vehicle, comprising: The vertical wings are designed in a plate-like shape. Flat wings, designed in a plate shape and having through holes; The assembly structure is fixed to the vertical wing and can be connected to the frame of the fixed-wing UAV through the through hole, so that the vertical wing presses and fixes the horizontal wing to the frame.

[0005] Optionally, the assembly structure includes a support portion and is fixed to the vertical wing via the support portion; The assembly structure further includes a plug-in portion that can be plugged into the frame through the through hole; and / or, the assembly structure further includes a snap-fit ​​portion that can be snapped into the frame through the through hole.

[0006] Optionally, the support portion is configured as a groove having a first support wall and a second support wall; The bottom end of the vertical wing is located in the groove, and the first support wall and the second support wall are respectively attached to the two side surfaces of the vertical wing.

[0007] Optionally, the first support wall and / or the second support wall are provided with a plurality of protruding ribs on the side surface away from the vertical wing, and the ribs extend along the insertion direction of the assembly structure.

[0008] Optionally, the assembly structure further includes a limiting part, which can press against the flat wing when the assembly structure is connected to the frame through the through hole.

[0009] Optionally, the limiting part is configured as a plate and perpendicular to the first support wall or the second support wall; The first support wall, the second support wall, the insertion part, and the snap-fit ​​part are separated from each other on both sides of the limiting part along the insertion direction of the assembly structure.

[0010] Optionally, the first support wall and / or the second support wall are provided with a plurality of V-shaped notches at the end away from the limiting portion; and / or, Multiple triangular ribs are provided at the positions where the first support wall and / or the second support wall intersect with the limiting part.

[0011] Optionally, two latching parts are provided, symmetrically located on both sides of the insertion part, and the through hole includes an insertion hole and two latching holes spaced apart on both sides of the insertion hole; The shape of the insertion hole matches the outer contour of the insertion part so that the insertion part can pass through the insertion hole and be inserted into the frame, and the two latching parts can pass through the two latching holes and be latched into the frame respectively.

[0012] Optionally, the planar surface of the horizontal wing is perpendicular to the planar surface of the vertical wing; and / or, The assembly structure is a one-piece molded structure; and / or, Both the horizontal wings and the vertical wings are made of foamed material; and / or, The assembly structure is made of engineering plastics; and / or, The surfaces of the horizontal wings and the vertical wings are coated.

[0013] According to a second aspect of this application, a fixed-wing unmanned aerial vehicle (UAV) is provided, comprising: The frame and the tail fin assembly described in the first aspect, wherein the mounting structure is capable of being connected to the frame through the through-hole.

[0014] Optionally, the assembly structure includes a plug-in part and a snap-fit ​​part, and the frame is provided with a plug-in part and a snap-fit ​​part; The plug-in part can be inserted into the frame through the through hole and the mating part, and the snap-fit ​​part can be snapped into the frame through the through hole and the snap-fit ​​part.

[0015] Optionally, the snap-fit ​​portion is configured as a protruding annular wall, the insertion portion is configured as a socket, and the socket is surrounded by a continuous or discontinuous baffle wall; and / or, The latching part is elastic, so that the latching part can engage or disengage with the latching part through deformation.

[0016] In the embodiments of this application, the vertical wing and the horizontal wing can be simultaneously fixed to the frame of the fixed-wing UAV by a single assembly structure that passes through the through hole of the horizontal wing. This achieves detachable assembly, simplifies the complexity of the structure, and reduces the deployment and transportation costs of the fixed-wing UAV.

[0017] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0018] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which: Figure 1 This is an assembly diagram of the tail fin assembly and the frame provided in this application; Figure 2 yes Figure 1 Cross-sectional view at point AA; Figure 3 yes Figure 2 A magnified view of a section at point E in the middle; Figure 4 yes Figure 1 Exploded view; Figure 5 yes Figure 4 A magnified view of a section at point B in the middle; Figure 6 yes Figure 4 A magnified view of a section at point C; Figure 7 yes Figure 4 A magnified view of a section at point D; Figure 8 This is a schematic diagram of the assembly structure provided in this application.

[0019] Figure label: 1. Vertical wing; 2. Horizontal wing; 21. Insertion hole; 22. Snap-fit ​​hole; 3. Assembly structure; 31. Support part; 311. First support wall; 312. Second support wall; 313. Rib; 314. V-shaped notch; 315. Rib plate; 32. Insertion part; 33. Snap-fit ​​part; 34. Limiting part; 4. Frame; 41. Snap-fit ​​part; 42. Insertion hole; 43. Baffle. Detailed Implementation

[0020] Embodiments of this application will now be described in detail. Examples of these embodiments are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments in this application are within the scope of protection of this application.

[0021] The terms "first" and "second" in the specification and claims of this application may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise stated, "multiple" means two or more. Furthermore, "and / or" in the specification and claims indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0022] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application 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 application.

[0023] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" 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 between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0024] The following is combined with Figures 1-8 This application describes a tail fin assembly and a fixed-wing unmanned aerial vehicle according to embodiments thereof.

[0025] like Figures 1 to 8 As shown, according to some embodiments of this application, a tail wing assembly is provided for use in a fixed-wing unmanned aerial vehicle (UAV), including: a vertical wing 1 configured as a plate; a horizontal wing 2 configured as a plate and having a through hole; and an assembly structure 3 fixed to the vertical wing 1 and capable of passing through the through hole and connecting to the frame 4 of the fixed-wing UAV, so that the vertical wing 1 presses and fixes the horizontal wing 2 to the frame 4.

[0026] Specifically, in this embodiment, the tail fin assembly mainly consists of a plate-shaped vertical wing 1, a plate-shaped horizontal wing 2, and an assembly structure 3. The horizontal wing 2 has a through hole for the assembly structure 3 to pass through, and the assembly structure 3 is pre-fixed to the vertical wing 1. During assembly, the assembly structure 3 passes through the through hole of the horizontal wing 2 and is directly connected to the UAV frame 4. During the assembly and fixing process, the vertical wing 1 simultaneously presses against and fixes the horizontal wing 2 to the frame 4, so that a single assembly structure 3 can simultaneously complete the fixed installation of the vertical wing 1 and the horizontal wing 2.

[0027] This structure eliminates the need for complex swivels, multiple sets of connectors, or additional fasteners. Its overall construction is simple and easy to assemble, effectively reducing the number of parts and processing costs. At the same time, it enables a detachable tail fin design, meeting the needs of drones for quick assembly and compact storage, significantly reducing deployment and transportation costs, and balancing lightweight, structural reliability, and ease of use.

[0028] The aforementioned tail fin assembly uses the assembly structure 3 on the vertical fin 1 as the core connector. The pre-drilled through-hole on the horizontal fin 2 enables rapid positioning and locking of the vertical fin 1, horizontal fin 2, and frame 4. After the assembly structure 3 passes through the through-hole on the horizontal fin 2 and connects to the frame 4, the vertical fin 1 itself forms a clamping surface, stably holding the horizontal fin 2 between the vertical fin 1 and the frame 4. This eliminates the need for separate fixing mechanisms for the vertical fin 1 and the horizontal fin 2, significantly simplifying the connection structure.

[0029] This design allows for quick, manual assembly and disassembly without the need for specialized tools, resulting in high assembly efficiency and a low barrier to entry. Simultaneously, the overall structural strength and stability remain unaffected, making it suitable for mass production. Compared to existing detachable tail fin solutions, this component effectively simplifies the structure, reduces manufacturing costs and maintenance difficulty, and enhances the flexibility and portability of fixed-wing UAVs while ensuring secure installation.

[0030] Among them, the assembly structure 3 can adopt a variety of mechanical forms that facilitate quick assembly and disassembly, including a flexible snap-fit ​​structure, which relies on its own elasticity to snap into the frame 4 to achieve quick locking and release; a plug-in locking structure, which completes positioning and fixing through the cooperation of a pin and a lock; a threaded quick-release structure, which uses hand-tightening bolts or quick-release screws to achieve manual tightening and disassembly; a rotary snap-fit ​​structure, which can achieve locking and loosening by rotating a certain angle; and a magnetic attraction positioning post structure, which uses magnetic attraction to assist in fixing and cooperates with the positioning post to ensure connection accuracy. All of the above structures can pass through the through hole of the horizontal wing 2 to achieve synchronous and quick fixing of the vertical wing 1 and the horizontal wing 2.

[0031] Optionally, such as Figures 1 to 4 As shown, the assembly structure 3 includes a support part 31, which is fixed to the vertical wing 1; the assembly structure 3 also includes a plug-in part 32, which can be plugged into the frame 4 through the through hole; and / or, the assembly structure 3 also includes a snap-fit ​​part 33, which can be snapped into the frame 4 through the through hole.

[0032] Specifically, in this embodiment, the assembly structure 3 may include a support part 31 and a plug-in part 32. The support part 31 is firmly connected to the vertical wing 1, providing a reliable installation foundation and structural support for the overall assembly, and ensuring the connection strength between the vertical wing 1 and the assembly structure 3. The plug-in part 32 can be directly inserted into the UAV frame 4 through the through hole of the horizontal wing 2, realizing rapid positioning and docking of the vertical wing 1, the horizontal wing 2 and the frame 4. This structure completes the assembly by plugging in, which is simple to operate, accurate in positioning, and can be quickly assembled and disassembled without complex tools, effectively reducing the difficulty of installation and disassembly. At the same time, the plug-in mating structure is simple and has fewer parts, which can reduce processing and assembly costs and improve the lightweight level of the structure. The support part 31 and the plug-in part 32 work together to ensure that the tail wing is firmly and stably installed, and to simplify the connection structure, solving the problems of complex connection and inconvenient disassembly and assembly of traditional tail wing, and improving the deployment efficiency and transport portability of the UAV.

[0033] In one embodiment, when the assembly structure 3 includes a support portion 31 and a snap-fit ​​portion 33, the support portion 31 is firmly fixed to the vertical wing 1, providing a stable mounting carrier for the snap-fit ​​portion 33. The snap-fit ​​portion 33 can pass through the through hole of the horizontal wing 2 and directly engage with the frame 4, achieving tool-free, quick locking and unlocking through the snap-fit ​​structure, significantly improving assembly and disassembly efficiency. The snap-fit ​​connection method is reliable and not easily loosened, meeting the vibration and stress requirements of the UAV during flight and ensuring the stability of the tail wing installation. This structure requires no additional fasteners, has a simple overall construction, helps reduce production and maintenance costs, and allows for detachable storage of the tail wing, reducing transportation volume. The combination of the snap-fit ​​portion 33 and the support portion 31 simplifies the structure while improving connection reliability and ease of use, effectively overcoming the shortcomings of existing detachable tail wing structures that are complex, costly, and cumbersome to assemble and disassemble.

[0034] In one embodiment, the assembly structure 3 includes a support part 31, a plug-in part 32, and a snap-fit ​​part 33, which can be compatible with the advantages of plug-in positioning and snap-fit ​​locking. It can achieve quick and accurate alignment through the plug-in part 32 and complete a firm self-locking by relying on the snap-fit ​​part 33, thus providing double protection for connection reliability. At the same time, it retains all the technical advantages of tool-free quick disassembly, simple structure, low cost, lightweight, and easy storage and transportation, making it more versatile and practical.

[0035] Optionally, such as Figure 3 and Figure 8 As shown, the support part 31 is configured as a groove with a first support wall 311 and a second support wall 312; the bottom end of the vertical wing 1 is located in the groove, and the first support wall 311 and the second support wall 312 are respectively attached to the two side surfaces of the vertical wing 1.

[0036] Specifically, in this embodiment, the support portion 31 of the assembly structure 3 is designed as a groove structure with a first support wall 311 and a second support wall 312. The bottom end of the vertical wing 1 is directly embedded in the groove, and the two support walls are tightly fitted to the front and back sides of the vertical wing 1, forming a double-sided clamping fixation. This structure can significantly increase the contact area and fit between the support portion 31 and the vertical wing 1, avoid unilateral force or local stress concentration, significantly enhance the connection strength and structural stability between the vertical wing 1 and the assembly structure 3, and effectively resist vibration, torsion and lateral loads during flight. The groove-type support can achieve precise positioning and assembly of the vertical wing 1 and the assembly structure 3, reduce installation deviation, and improve assembly consistency. The double-sided support wall fit fixation does not require additional fasteners, the structure is simple and easy to process, which is conducive to lightweight design and cost control.

[0037] Meanwhile, this clamping installation method is firm, reliable, and not easy to loosen. It ensures the overall rigidity of the tail fin and can adapt to the need for quick assembly and disassembly. While simplifying the structure, it improves the overall reliability and durability of the tail fin assembly, providing solid support for the stable flight of the UAV.

[0038] Optionally, such as Figures 7 to 8 As shown, the first support wall 311 and / or the second support wall 312 are provided with a plurality of protruding ribs 313 on the side surface away from the vertical wing 1, and the ribs 313 extend along the insertion direction of the assembly structure 3 (refer to the Z direction in the attached figure).

[0039] Specifically, in this embodiment, multiple protruding ribs 313 extending along the assembly insertion direction are provided on the outer side of the first support wall 311 and the second support wall 312 of the support part 31. This can significantly improve the bending, torsion and deformation resistance of the support wall without significantly increasing the structural weight, and strengthen the overall rigidity of the assembly structure 3.

[0040] Ribs 313 extend along the interlocking direction, aligning with the direction of assembly forces. This effectively disperses vibrations, lateral forces, and insertion / extraction stresses generated during flight, preventing excessive localized stress on the support wall and thus avoiding deformation or breakage. This enhances the long-term reliability of the tail fin connection. Multiple ribs 313 form a uniformly reinforced structure, reducing material usage while balancing lightweight design with strength requirements, aligning with the trend towards lightweight UAV design. Furthermore, the raised structure of ribs 313 does not affect the assembly path or the precision of snap-fit ​​and insertion connections, does not increase assembly / disassembly resistance, and maintains ease of quick assembly and disassembly.

[0041] This design significantly improves the durability and structural stability of the support part 31 through a simple reinforcement method using ribs 313, with low cost and easy processing structural optimization, ensuring that the tail fin is stable and reliable under complex flight conditions, and further enhancing the overall safety of the UAV.

[0042] Optionally, such as Figure 3 , Figure 7 and Figure 8 As shown, the assembly structure 3 also includes a limiting part 34, which can press against the flat wing 2 when the assembly structure 3 is connected to the frame 4 through the through hole.

[0043] Specifically, in this embodiment, the assembly structure 3 is equipped with a limiting part 34. When the assembly structure 3 passes through the through hole of the flat wing 2 and completes the connection with the frame 4, the limiting part 34 can directly press against the surface of the flat wing 2, forming a clear positioning and clamping constraint. The limiting part 34 can accurately limit the insertion depth of the assembly structure 3, avoiding excessive insertion that could cause the tail wing position to shift, the flat wing 2 to deform under pressure, or the connection to loosen, ensuring that the vertical wing 1, the flat wing 2, and the frame 4 are in the same assembly position and have stable installation accuracy.

[0044] During the drone's flight, the limiting part 34 continuously presses against the horizontal wing 2, effectively limiting its vertical movement and lateral sway, thus improving the overall vibration resistance and structural stability of the tail fin. Simultaneously, the limiting part 34 and the horizontal wing 2 form a surface contact and clamping mechanism, eliminating the need for additional clamping parts and maintaining the advantages of a simple overall structure, efficient assembly and disassembly, and quick manual disassembly. This design achieves reliable limiting and clamping functions with a simple structure, improving assembly consistency and installation efficiency while enhancing the tail fin assembly's robustness under complex operating conditions, reducing the risk of failure, and balancing low cost, lightweight design, and high reliability.

[0045] Optionally, such as Figure 8 As shown, the limiting part 34 is plate-shaped and perpendicular to the first support wall 311 or the second support wall 312; the first support wall 311, the second support wall 312, the insertion part 32, and the snap-fit ​​part 33 are separated from the limiting part 34 on both sides along the insertion direction of the assembly structure 3.

[0046] Specifically, in this embodiment, the limiting part 34 is designed as a plate-like structure and is perpendicular to the first support wall 311 or the second support wall 312. Simultaneously, the support wall, the insertion part 32, and the snap-fit ​​part 33 are positioned on both sides of the limiting part 34 along the assembly insertion direction, forming functional partitions and force isolation. The plate-like limiting part 34 provides a stable and uniform pressing surface, reliably fitting with the flat wing 2, ensuring a balanced distribution of pressing force and preventing deformation or damage to the flat wing 2 due to localized stress concentration. This functional partition layout ensures that the support and connection parts do not interfere with each other, guaranteeing smooth insertion and snap-fit ​​into the through hole while allowing for quick positioning and stopping via the limiting part 34, thus improving assembly efficiency and consistency.

[0047] This structure is easy to manufacture, and while maintaining a lightweight design, it enhances structural rigidity, effectively resisting flight vibrations and lateral loads, and preventing displacement of the assembled structure. Through clear spatial division and vertical positioning design, it further improves the tail fin's installation accuracy, connection reliability, and structural stability, maintaining its core advantages of rapid assembly and disassembly, low cost, and high stability.

[0048] Optionally, such as Figures 7 to 8 As shown, a plurality of V-shaped notches 314 are respectively provided on the first support wall 311 and / or the second support wall 312 at the end away from the limiting part 34; and / or, a plurality of triangular ribs 315 are provided at the position where the first support wall 311 and / or the second support wall 312 intersects with the limiting part 34.

[0049] Specifically, in this embodiment, multiple V-shaped notches 314 are provided at the ends of the first support wall 311 and / or the second support wall 312 away from the limiting part 34. This can reduce the weight of the support wall ends while ensuring support strength, thus optimizing the lightweight structure. At the same time, the V-shaped notches 314 can reduce the stiffness of the support wall ends, improve the elastic deformation capability of the assembly structure 3 when it is inserted, make the insertion or snapping process smoother, reduce insertion and extraction resistance, and avoid jamming. In addition, the V-shaped notches 314 can guide the assembly structure 3 to accurately align with the socket 42 of the frame 4, improve assembly guidance and alignment efficiency, and also disperse end stress, avoid stress concentration leading to cracking, and improve structural durability.

[0050] In one embodiment, multiple triangular ribs 315 are provided at the intersection of the first support wall 311 and / or the second support wall 312 and the limiting part 34. This can enhance the connection stiffness and torsional strength between each support wall and the limiting part 34, effectively resist bending and deformation caused by flight vibration and lateral loads, and prevent the connection from breaking or loosening. The triangular ribs 315 can uniformly transmit the clamping force and assembly force, improving the overall structural stability. At the same time, the rib structure 315 occupies little space and does not affect the assembly path. It strengthens the key stress area without significantly increasing the weight, thereby improving the reliability and safety of the tail fin assembly for long-term use.

[0051] When the V-shaped notch 314 is combined with the triangular rib 315, it can optimize the elastic guidance, reduce insertion and extraction resistance, and reduce the end weight, while significantly improving the structural stiffness, torsional strength and fatigue resistance at the junction of the support wall and the limiting part 34. This ensures that the assembly structure 3 can be smoothly inserted, accurately aligned and not easily jammed, and can effectively disperse stress, avoid stress concentration and deformation and fracture at the connection. It achieves a synergistic improvement in lightweight, easy disassembly and assembly, and high rigidity and high reliability, allowing the tail wing assembly to further enhance structural stability and durability on the basis of quick disassembly and assembly, and better adapt to the vibration and complex load conditions during UAV flight.

[0052] The multiple V-shaped notches 314 and multiple triangular ribs 315 can be spaced apart along the front-back direction of the UAV (refer to the Y direction in the attached figure).

[0053] Optionally, such as Figure 3 and Figure 8As shown, there are two latching parts 33, which are symmetrically located on both sides of the insertion part 32. The through hole includes an insertion hole 21 and two latching holes 22 spaced apart on both sides of the insertion hole 21. The shape of the insertion hole 21 matches the outer contour of the insertion part 32 so that the insertion part 32 can pass through the insertion hole 21 and be inserted into the frame 4. The two latching parts 33 can pass through the two latching holes 22 and be latched onto the frame 4 respectively.

[0054] Specifically, in this embodiment, two latching parts 33 are provided and symmetrically distributed on both sides of the insertion part 32 (i.e., on both sides along the left and right direction of the UAV, referring to the X direction in the attached figure). At the same time, the through hole of the flat wing 2 is divided into a middle insertion hole 21 and two side latching holes 22. The shape of the insertion hole 21 matches the outer contour of the insertion part 32, and the two side latching holes 22 cooperate with the symmetrical latching parts 33. This can achieve a double fixing effect of precise positioning and symmetrical locking during tail wing assembly.

[0055] The insertion part 32, in conjunction with the insertion hole 21, enables rapid alignment and ensures accurate assembly direction and position, preventing installation misalignment. The symmetrical locking parts 33 on both sides pass through the locking holes 22 and engage with the frame 4, forming a balanced and symmetrical locking force. This effectively avoids issues such as uneven loading, loosening, or torsion caused by unilateral locking, significantly improving connection stability and vibration resistance. This symmetrical layout distributes stress evenly, reducing local stress concentration between the horizontal wing 2 and the assembly structure 3, lowering the risk of deformation. Simultaneously, the assembly path is clear and alignment is intuitive, enabling quick manual assembly and disassembly without increasing operational complexity. The overall structure is simple and easy to manufacture, significantly improving tail wing installation accuracy, connection reliability, and structural integrity without increasing cost or weight, better meeting the strength and safety requirements of the UAV during flight.

[0056] Optionally, such as Figures 1 to 8 As shown, the plate-shaped surface of the horizontal wing 2 is perpendicular to the plate-shaped surface of the vertical wing 1; and / or, the assembly structure 3 is an integrally molded structure; and / or, both the horizontal wing 2 and the vertical wing 1 are made of foamed material; and / or, the assembly structure 3 is made of engineering plastic; and / or, the surfaces of the horizontal wing 2 and the vertical wing 1 are coated.

[0057] Specifically, in this embodiment, the horizontal wing 2 and the vertical wing 1 are arranged vertically, which conforms to the conventional aerodynamic layout of fixed-wing UAVs and can ensure the tail control efficiency and flight stability. The vertical fit makes it easy for the assembly structure 3 to pass through and press the two together at the same time. The positioning is intuitive and the assembly error is small. It can improve the overall rigidity and force uniformity of the tail assembly and avoid relative deflection.

[0058] One-piece molding eliminates welding, bonding, and bolting processes, reducing the number of parts and assembly errors. It also results in higher structural strength and less susceptibility to loosening and failure. The process consistency is good, making it suitable for mass production. At the same time, it reduces weight, simplifies disassembly and assembly logic, and further improves reliability and durability.

[0059] Foamed materials are lightweight and easy to mold, which can significantly reduce the weight of the tail fin and improve the drone's endurance and payload capacity. The material has a certain degree of toughness, which can buffer flight vibrations and has good impact resistance. It is also low in cost and high in processing efficiency, making it suitable for use in lightweight drone structures.

[0060] Engineering plastics are high in strength, wear-resistant, anti-aging, and tough, meeting the mechanical requirements of snap-fit, plug-in, and support; they are lightweight and corrosion-resistant, making them suitable for lightweight design of drones; the injection molding process is mature, low in cost, and highly consistent, enabling stable and quick-release structures.

[0061] Surface coating can seal the pores of foam material, improve surface smoothness and aerodynamic smoothness; enhance moisture resistance, water resistance, and oil resistance, and extend service life; at the same time, it can improve surface rigidity and scratch resistance, protect the wing surface from deformation and damage, and improve the overall structural reliability.

[0062] According to the second aspect of this application, reference to Figure 1 and Figure 4 A fixed-wing unmanned aerial vehicle is provided, including: a frame 4 and a tail fin assembly in the first aspect, wherein an assembly structure 3 is capable of being connected to the frame 4 through a through hole.

[0063] Specifically, in this embodiment, a fixed-wing UAV including the aforementioned tail fin assembly is provided. By connecting the assembly structure 3 of the tail fin assembly to the frame 4 through the through hole of the horizontal wing 2, the vertical wing 1 and the horizontal wing 2 can be directly and synchronously installed in one go, effectively simplifying the UAV tail fin assembly process and reducing the difficulty of overall assembly and maintenance. This design gives the tail fin the advantages of being detachable, easy to store, and convenient for transportation and deployment. At the same time, the stable and reliable connection structure ensures that the tail fin does not loosen or deform during flight, maintaining good aerodynamic performance and flight stability. The UAV using this tail fin assembly has a simpler overall structure, is lighter, and has lower cost, which can significantly improve the practicality, portability, and market competitiveness of the entire aircraft, making it suitable for mass production and actual operation scenarios.

[0064] Optionally, such as Figures 4 to 7 As shown, the assembly structure 3 includes a plug-in part 32 and a snap-fit ​​part 33, and the frame 4 is provided with a plug-in part and a snap-fit ​​part 41; the plug-in part 32 can pass through the through hole and be plugged into the frame 4 through the plug-in part, and the snap-fit ​​part 33 can pass through the through hole and be snapped into the frame 4 through the snap-fit ​​part 41.

[0065] Specifically, in this embodiment, by providing a plug-in part 32 and a snap-fit ​​part 33 on the assembly structure 3, and correspondingly configuring a mating part and a snap-fit ​​part 41 on the frame 4, the plug-in part 32 can pass through the through hole of the flat wing 2 and achieve precise alignment and plugging with the mating part of the frame 4, and the snap-fit ​​part 33 can simultaneously pass through the through hole and complete locking and fixing with the snap-fit ​​part 41 of the frame 4, forming a dual reliable connection of plug-in positioning and snap-fit ​​locking.

[0066] This assembly method not only enables rapid guidance and prevents installation misalignment through the plug-in part 32, but also allows for quick disassembly and self-locking without tools through the snap-fit ​​part 33, significantly improving the efficiency and stability of tail assembly and disassembly. At the same time, the plug-in and snap-fit ​​work together to effectively resist vibration, torsion and lateral loads during flight, preventing the tail from loosening or falling off. The overall structure is simple and the stress is evenly distributed. Under the premise of ensuring lightweight and low cost, it significantly improves the installation accuracy, structural reliability and safety of UAV tail.

[0067] Optionally, such as Figures 5 to 8 As shown, the snap-fit ​​portion 41 is configured as a protruding annular wall, the insertion portion is configured as an insertion hole 42, and the periphery of the insertion hole 42 is provided with a continuous or discontinuous baffle wall 43; and / or, the snap-fit ​​portion 33 is elastic so that the snap-fit ​​portion 33 can engage or disengage with the snap-fit ​​portion 41 by deformation.

[0068] Specifically, in this embodiment, the snap-fit ​​part 41 on the frame 4 is configured as a protruding annular wall, the insertion part is configured as an insertion hole 42, and continuous or discontinuous baffles 43 are provided on the periphery. At the same time, the snap-fit ​​part 33 is made elastic, which allows the insertion part 32 to be precisely aligned with the insertion hole 42 and the baffles 43 to provide limiting support. The elastic snap-fit ​​part 33 smoothly engages or disengages with the annular wall through its own deformation, realizing a dual stable cooperation of insertion positioning and elastic locking. The annular wall and the elastic snap-fit ​​are firmly engaged, prevent loosening, and have strong vibration resistance. The insertion hole 42 and the baffles 43 ensure assembly accuracy and structural strength. The elastic deformation design allows for quick and easy installation and disassembly by hand without tools. The overall structure is simple, reliable, and has balanced force, which can improve the efficiency and stability of tail fin assembly and disassembly, and reduce structural complexity and production costs, fully meeting the usage requirements of lightweight, quick disassembly, and high reliability of UAV tail fins.

[0069] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "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 this application. 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.

[0070] Although embodiments of this application have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of this application, the scope of which is defined by the claims and their equivalents.

Claims

1. A tail fin assembly for use in a fixed-wing unmanned aerial vehicle, characterized in that, include: The vertical wing (1) is plate-shaped; Flat wing (2), configured as a plate and having through holes; The assembly structure (3) is fixed to the vertical wing (1) and can be connected to the frame (4) of the fixed-wing UAV through the through hole, so that the vertical wing (1) presses and fixes the horizontal wing (2) to the frame (4).

2. The tail fin assembly according to claim 1, characterized in that, The assembly structure (3) includes a support (31) and is fixed to the vertical wing (1) by the support (31); The assembly structure (3) further includes a plug-in part (32) which can be plugged into the frame (4) through the through hole; and / or, the assembly structure (3) further includes a snap-fit ​​part (33) which can be snapped into the frame (4) through the through hole.

3. The tail fin assembly according to claim 2, characterized in that, The support portion (31) is configured as a groove having a first support wall (311) and a second support wall (312); The bottom end of the vertical wing (1) is located in the groove, and the first support wall (311) and the second support wall (312) are respectively attached to the two side surfaces of the vertical wing (1).

4. The tail fin assembly according to claim 3, characterized in that, The first support wall (311) and / or the second support wall (312) are provided with a plurality of protruding ribs (313) on the side surface away from the vertical wing (1), and the ribs (313) extend along the insertion direction of the assembly structure (3).

5. The tail fin assembly according to claim 3, characterized in that, The assembly structure (3) also includes a limiting part (34), which can press against the flat wing (2) when the assembly structure (3) is connected to the frame (4) through the through hole.

6. The tail fin assembly according to claim 5, characterized in that, The limiting part (34) is plate-shaped and perpendicular to the first support wall (311) or the second support wall (312). The first support wall (311), the second support wall (312), the insertion part (32), and the snap-fit ​​part (33) are separated from the limiting part (34) on both sides along the insertion direction of the assembly structure (3).

7. The tail fin assembly according to claim 6, characterized in that, The first support wall (311) and / or the second support wall (312) are respectively provided with a plurality of V-shaped notches (314) at the end away from the limiting part (34); and / or, Multiple triangular ribs (315) are provided at the positions where the first support wall (311) and / or the second support wall (312) intersect with the limiting part (34).

8. The tail fin assembly according to claim 2, characterized in that, The latching part (33) is provided in two, respectively symmetrically located on both sides of the insertion part (32). The through hole includes an insertion hole (21) and two latching holes (22) spaced apart on both sides of the insertion hole (21). The shape of the insertion hole (21) matches the outer contour of the insertion part (32) so that the insertion part (32) can pass through the insertion hole (21) and be inserted into the frame (4), and the two latching parts (33) can pass through the two latching holes (22) and be latched into the frame (4).

9. The tail fin assembly according to claim 1, characterized in that, The plate-shaped surface of the horizontal wing (2) is perpendicular to the plate-shaped surface of the vertical wing (1); and / or, The assembly structure (3), the vertical wing (1), and the horizontal wing (2) are all integrally formed structures; and / or, Both the horizontal wing (2) and the vertical wing (1) are made of foam material; and / or, The assembly structure (3) is made of engineering plastic; and / or, The surfaces of the horizontal wing (2) and the vertical wing (1) are coated.

10. A fixed-wing unmanned aerial vehicle, characterized in that, include: The frame (4) and the tail fin assembly according to any one of claims 1-9, wherein the assembly structure (3) is capable of being connected to the frame (4) through the through hole.

11. The fixed-wing UAV according to claim 10, characterized in that, The assembly structure (3) includes a plug-in part (32) and a snap-fit ​​part (33), and the frame (4) is provided with a plug-in part and a snap-fit ​​part (41). The plug-in part (32) can be inserted into the frame (4) through the through hole and the plug-in part, and the snap-fit ​​part (33) can be snapped into the frame (4) through the through hole and the snap-fit ​​part (41).

12. The fixed-wing UAV according to claim 11, characterized in that, The snap-fit ​​portion (41) is configured as a protruding annular wall, the insertion portion is configured as an insertion hole (42), and the periphery of the insertion hole (42) is surrounded by a continuous or discontinuous baffle wall (43); and / or, The latching part (33) is elastic so that the latching part (33) can engage or disengage with the latching part (41) by deformation.

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