Shell structure of unmanned aerial vehicle

Abstract

The shell structure of the unmanned aerial vehicle comprises an upper shell, a bottom shell, a vehicle arm and a fastening piece, the upper shell is provided with a first extending part, the bottom shell is provided with a second extending part, after the upper shell is connected with the bottom shell, the first extending part and the second extending part are overlapped to form an inserting part, the vehicle arm is provided with an inserting hole and is connected to the inserting part in a sleeved mode through the inserting hole, and the fastening piece is arranged on the vehicle arm. The vehicle arm, the first extension part and the second extension part are connected through a fastener; according to the shell structure of the unmanned aerial vehicle, a novel mechanical interlocking structure is achieved through the insertion part formed by overlapping the first extension part of the upper shell and the second extension part of the bottom shell, and the stability and integrity of the shell of the unmanned aerial vehicle are enhanced. By means of the design, the assembling process is simplified, dependence on traditional fasteners is reduced, and therefore assembling cost and maintenance difficulty are reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a shell structure of a unmanned aerial vehicle. Background Art

[0002] As an advanced aircraft, the outer shell structure of a drone is crucial to ensuring flight performance and the safety of internal components. However, the outer shell structure of a drone in the prior art, especially in the connection between the upper shell, the bottom shell and the arm, has some obvious stability problems.

[0003] Limitations of connection methods: The upper and lower shells of existing drones are usually connected to the arms using traditional screws or rivets. Although this connection method ensures structural integrity to a certain extent, the dynamic loads during flight may cause the connection parts to loosen or be damaged, affecting the overall stability.

[0004] Stress concentration problem: In existing designs, the connection points between the upper and lower shells and the arms are often areas of stress concentration. Vibration and external impact during flight may cause the stress at these connection points to exceed the material's tolerance, thus causing structural failure.

[0005] Insufficient durability: Due to the limitations of existing connection methods, after long-term use or exposure to harsh environments, fatigue cracks or material degradation may occur at the connection points between the upper shell, bottom shell and the arm of the drone, reducing the durability and reliability of the drone.

[0006] Difficult maintenance and repair: When the upper shell, bottom shell or arm of the drone needs to be repaired or replaced, the disassembly process of the existing connection method is complicated and requires professional tools and skills, which not only increases maintenance costs but also prolongs maintenance time.

[0007] Impact on rapid deployment: In application scenarios where drones need to be deployed quickly, stability issues with existing connection methods may lead to additional inspections and maintenance before deployment, affecting the drone's ability to respond quickly.

[0008] Although there are some improvement measures on the market to address these problems, most solutions still fail to effectively solve the stability problem of the connection between the upper shell, bottom shell and the arm. Therefore, developing a new connection method to improve the overall stability and reliability of the UAV shell structure is of great significance to improving the performance and application range of UAVs. Utility Model Content

[0009] The technical problem to be solved by the utility model is to provide a shell structure of a UAV with good stability.

[0010] In order to solve the above technical problems, the technical solution adopted by the utility model is: a shell structure of an unmanned aerial vehicle, including an upper shell, a bottom shell, an arm and a fastener, the upper shell is provided with a first extension portion, the bottom shell is provided with a second extension portion, after the upper shell is connected to the bottom shell, the first extension portion and the second extension portion overlap to form a plug-in portion, the arm is provided with a plug-in hole and is sleeved on the plug-in portion through the plug-in hole, and the arm, the first extension portion and the second extension portion are connected by the fastener.

[0011] Furthermore, the first extension portion and / or the second extension portion is provided with a guide protrusion, and the side wall of the plug-in hole is provided with a guide groove that slidably cooperates with the guide protrusion.

[0012] Furthermore, the first extension portion and / or the second extension portion is provided with a guide groove, and the side wall of the plug-in hole is provided with a guide protrusion that slidably cooperates with the guide groove.

[0013] Furthermore, the first extension portion and / or the second extension portion is made of metal.

[0014] Furthermore, the fastener is a fastening bolt.

[0015] Furthermore, the plug-in portion is provided with a fixing hole, a through hole is provided on one side of the arm at a position corresponding to the fixing hole, and a threaded hole is provided on the other side of the arm at a position corresponding to the fixing hole, and the fastening bolt passes through the through hole and the fixing hole in sequence and is threadedly connected to the threaded hole.

[0016] Furthermore, there are multiple fixing holes, and the multiple fixing holes are evenly spaced and distributed along the plug-in direction of the plug-in portion.

[0017] Furthermore, the first extension portion is provided with a fixing hole, the second extension portion is provided with a threaded hole at a position corresponding to the fixing hole, the arm is provided with a through hole at a position corresponding to the fixing hole, and the fastening bolt passes through the through hole and the fixing hole in sequence and is threadedly connected to the threaded hole.

[0018] Furthermore, the first extension portion is provided with a threaded hole, the second extension portion is provided with a fixing hole at a position corresponding to the threaded hole, the arm is provided with a through hole at a position corresponding to the fixing hole, and the fastening bolt passes through the through hole and the fixing hole in sequence and is threadedly connected to the threaded hole.

[0019] Furthermore, a threaded joint is provided in the threaded hole, and the threaded joint is threadedly connected to the fastening bolt.

[0020] The beneficial effects of the utility model are:

[0021] 1. Solve the limitations of the connection method: By designing the first extension of the upper shell and the second extension of the bottom shell to overlap to form a plug-in part, a new mechanical interlocking connection method is created, reducing the reliance on traditional screws or rivets. This connection method not only simplifies the assembly process, but also reduces the possibility of loosening of the connection parts due to the reduction of the use of fasteners, thereby improving the stability of the overall structure;

[0022] 2. Alleviate stress concentration problem: The design of the plug-in part makes the force more evenly distributed in the connection area, reducing stress concentration. Due to the overlapping design of the first extension part and the second extension part, the vibration and impact generated during flight can be more effectively dispersed and absorbed, thereby improving the durability and reliability of the UAV shell;

[0023] 3. Improved durability: By optimizing the connection method, the structural design of the plug-in part helps to enhance the durability of the connection point, reduce fatigue cracks or material degradation caused by long-term use or harsh environment, and extend the service life of the drone;

[0024] 4. Simplify the maintenance and repair process: The arm is connected to the plug-in part through the plug-in hole and quickly connected through fasteners. This design significantly simplifies the disassembly and assembly process of the arm. Maintenance personnel can replace or repair parts more quickly, reducing maintenance time and costs;

[0025] 5. Improve rapid deployment capabilities: Simplified connection methods reduce the preparation time before drone deployment. Because the connection is more secure and easier to check, drones can be put into missions faster, improving rapid response capabilities. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a schematic structural diagram of the outer shell structure of the UAV according to the first embodiment of the present utility model;

[0027] Figure 2 This is an exploded view of the outer shell structure of the drone of the first embodiment of the utility model (after hiding the arms);

[0028] Figure 3 This is a simplified structural diagram of the outer shell structure of the UAV according to the first embodiment of the present utility model;

[0029] Figure 4 This is a simplified structural diagram of the outer shell structure of the UAV of the second embodiment of the present utility model;

[0030] Figure 5 This is a simplified structural diagram of the outer shell structure of the UAV of the third embodiment of the present utility model.

[0031] Description of labels:

[0032] 1. Upper shell; 11. First extension part; 2. Bottom shell; 21. Second extension part; 3. Arm; 31. Plug-in hole; 4. Guide protrusion; 5. Fixing hole; 6. Through hole; 7. Threaded hole; 8. Fastening bolt. DETAILED DESCRIPTION

[0033] In order to explain the technical content, achieved objectives and effects of the present invention in detail, the following is an explanation in conjunction with the implementation modes and the accompanying drawings.

[0034] Please refer to Figures 1 to 5 A shell structure of a drone includes an upper shell 1, a bottom shell 2, an arm 3 and a fastener, wherein the upper shell 1 is provided with a first extension portion 11, and the bottom shell 2 is provided with a second extension portion 21. After the upper shell 1 is connected to the bottom shell 2, the first extension portion 11 and the second extension portion 21 overlap to form a plug-in portion, the arm 3 is provided with a plug-in hole 31 and is sleeved on the plug-in portion through the plug-in hole 31, and the arm 3, the first extension portion 11 and the second extension portion 21 are connected by the fastener.

[0035] From the above description, it can be seen that the beneficial effect of the utility model is that: through the plug-in portion formed by overlapping the first extension portion 11 of the upper shell 1 and the second extension portion 21 of the bottom shell 2, a novel mechanical interlocking structure is realized, which enhances the stability and integrity of the drone shell. This design simplifies the assembly process, reduces the dependence on traditional fasteners, and thus reduces assembly costs and maintenance difficulties.

[0036] Furthermore, the first extension portion 11 and / or the second extension portion 21 is provided with a guide protrusion 4 , and the side wall of the plug hole 31 is provided with a guide groove that slidably cooperates with the guide protrusion 4 .

[0037] Furthermore, the first extension portion 11 and / or the second extension portion 21 is provided with a guide groove, and the side wall of the plug hole 31 is provided with a guide protrusion 4 that slidably cooperates with the guide groove.

[0038] As can be seen from the above description, the sliding cooperation between the guide protrusion 4 and the guide groove provides a guide mechanism to ensure that the machine arm 3 is correctly aligned and firmly sleeved on the plug-in portion. This design improves the accuracy and reliability of assembly.

[0039] Furthermore, the first extension portion 11 and / or the second extension portion 21 is made of metal.

[0040] It can be seen from the above description that the first extension portion 11 and / or the second extension portion 21 are made of metal, which improves the strength and durability of the connection parts, so that the drone can withstand greater flight loads and more severe environmental conditions.

[0041] Furthermore, the fastener is a fastening bolt 8.

[0042] It can be seen from the above description that the use of the fastening bolts 8 as fasteners provides a reliable fixing method, ensures a firm connection between the arm 3 and the upper shell 1 and the bottom shell 2, and enhances the stability of the overall structure.

[0043] Furthermore, the plug-in portion is provided with a fixing hole 5, a through hole 6 is provided on one side of the arm 3 at a position corresponding to the fixing hole 5, and a threaded hole 7 is provided on the other side of the arm 3 at a position corresponding to the fixing hole 5, and the fastening bolt 8 passes through the through hole 6 and the fixing hole 5 in sequence and is threadedly connected to the threaded hole 7.

[0044] It can be seen from the above description that, through the design of the fixing hole 5 and the threaded hole 7, the fastening bolt 8 can pass through the arm 3 and be threadedly connected to the threaded hole 7, providing a stable connection method while allowing quick disassembly and assembly for easy maintenance and repair.

[0045] Furthermore, there are multiple fixing holes 5, and the multiple fixing holes 5 are evenly spaced and distributed along the plug-in direction of the plug-in part.

[0046] From the above description, it can be seen that a plurality of fixing holes 5 are arranged evenly spaced along the plug-in direction of the plug-in part, and the plug-in depth between the plug-in part and the plug-in hole 31 can be adjusted by inserting the fastening bolts 8 into the fixing holes 5 at different positions, thereby realizing the adjustment of the assembly position of the arm 3.

[0047] Furthermore, the first extension portion 11 is provided with a fixing hole 5, the second extension portion 21 is provided with a threaded hole 7 at a position corresponding to the fixing hole 5, the arm 3 is provided with a through hole 6 at a position corresponding to the fixing hole 5, and the fastening bolt 8 sequentially passes through the through hole 6 and the fixing hole 5 and is threadedly connected to the threaded hole 7.

[0048] As can be seen from the above description, this design allows the fastening bolt 8 to provide a stable connection between the first extension portion 11 and the second extension portion 21. At the same time, the through hole 6 of the arm 3 is designed so that the fastening bolt 8 can penetrate and fix the arm 3, thereby enhancing the stability of the overall structure.

[0049] Furthermore, the first extension portion 11 is provided with a threaded hole 7, the second extension portion 21 is provided with a fixing hole 5 at a position corresponding to the threaded hole 7, the arm 3 is provided with a through hole 6 at a position corresponding to the fixing hole 5, and the fastening bolt 8 passes through the through hole 6 and the fixing hole 5 in sequence and is threadedly connected to the threaded hole 7.

[0050] As can be seen from the above description, this design provides a stable connection by using the fastening bolts 8 between the first extension portion 11 and the second extension portion 21 , and allows for quick disassembly and assembly of the machine arm 3 .

[0051] Furthermore, a threaded joint is provided in the threaded hole 7 , and the threaded joint is threadedly connected to the fastening bolt 8 .

[0052] As can be seen from the above description, the threaded joint is arranged in the threaded hole 7 and is threadedly connected with the fastening bolt 8, providing a mechanism to prevent the fastening bolt 8 from loosening, further improving the reliability of the connection and the stability of the UAV during flight.

[0053] Please refer to Figures 1 to 3 The first embodiment of the utility model is: a shell structure of a drone, including an upper shell 1, a bottom shell 2, an arm 3 and a fastener, wherein the upper shell 1 is provided with a first extension portion 11, and the bottom shell 2 is provided with a second extension portion 21. After the upper shell 1 is connected to the bottom shell 2, the first extension portion 11 and the second extension portion 21 overlap to form a plug-in portion, the arm 3 is provided with a plug-in hole 31 and is sleeved on the plug-in portion through the plug-in hole 31, and the arm 3, the first extension portion 11 and the second extension portion 21 are connected through the fastener; the plug-in portion formed by the overlap of the first extension portion 11 of the upper shell 1 and the second extension portion 21 of the bottom shell 2 realizes a novel mechanical interlocking structure, which enhances the stability and integrity of the drone shell. This design simplifies the assembly process, reduces the dependence on traditional fasteners, and thus reduces the assembly cost and maintenance difficulty.

[0054] Optionally, the first extension part 11 and / or the second extension part 21 is provided with a guide protrusion 4, and the side wall of the plug hole 31 is provided with a guide groove that slides with the guide protrusion 4, or the first extension part 11 and / or the second extension part 21 is provided with a guide groove, and the side wall of the plug hole 31 is provided with a guide protrusion 4 that slides with the guide groove. It is easy to understand that the sliding cooperation between the guide protrusion 4 and the guide groove provides a guiding mechanism to ensure that the machine arm 3 is correctly aligned and firmly sleeved on the plug part. This design improves the accuracy and reliability of assembly.

[0055] Optionally, the first extension portion 11 and / or the second extension portion 21 is made of metal. The first extension portion 11 and / or the second extension portion 21 uses metal material, which improves the strength and durability of the connection parts, so that the drone can withstand greater flight loads and more severe environmental conditions; specifically in this embodiment, the bottom shell 2 and the second extension portion 21 are an integrally formed one-piece structure, and the bottom shell 2 is made of metal, and the metal material is magnesium alloy, aluminum alloy or other lightweight metal material.

[0056] Preferably, the fastener is a fastening bolt 8. Using the fastening bolt 8 as a fastener provides a reliable fixing method, ensures a firm connection between the machine arm 3 and the upper shell 1 and the bottom shell 2, and enhances the stability of the overall structure. Specifically, the plug-in portion is provided with a fixing hole 5, a through hole 6 is provided on one side of the machine arm 3 at a position corresponding to the fixing hole 5, and a threaded hole 7 is provided on the other side of the machine arm 3 at a position corresponding to the fixing hole 5. The fastening bolt 8 sequentially penetrates the through hole 6 and the fixing hole 5 and is threadedly connected to the threaded hole 7. By designing the fixing hole 5 and the threaded hole 7 , so that the fastening bolt 8 can pass through the arm 3 and be threadedly connected with the threaded hole 7, providing a stable connection method, while allowing quick disassembly and assembly, and facilitating maintenance and repair; as an option, the number of the fixing holes 5 can be multiple, and the multiple fixing holes 5 are evenly spaced along the plug-in direction of the plug-in part. It is easy to understand that multiple fixing holes 5 are evenly spaced along the plug-in direction of the plug-in part. The fastening bolts 8 can be inserted into the fixing holes 5 at different positions, so as to adjust the plug-in depth of the plug-in part and the plug-in hole 31, thereby realizing the adjustment of the assembly position of the arm 3.

[0057] Optionally, a threaded joint is provided in the threaded hole 7, and the threaded joint is threadedly connected to the fastening bolt 8. The threaded joint is arranged in the threaded hole 7 and threadedly connected to the fastening bolt 8, providing a mechanism to prevent the fastening bolt 8 from loosening, further improving the reliability of the connection and the stability of the UAV during flight.

[0058] Please refer to Figure 4 The difference between the second embodiment of the utility model and the first embodiment is that: the first extension portion 11 is provided with a fixing hole 5, the second extension portion 21 is provided with a threaded hole 7 at a position corresponding to the fixing hole 5, the arm 3 is provided with a through hole 6 at a position corresponding to the fixing hole 5, and the fastening bolt 8 passes through the through hole 6 and the fixing hole 5 in sequence and is threadedly connected to the threaded hole 7. This design allows the fastening bolt 8 to provide a stable connection between the first extension portion 11 and the second extension portion 21. At the same time, the through hole 6 design of the arm 3 enables the fastening bolt 8 to fix the arm 3, thereby enhancing the stability of the overall structure.

[0059] Please refer to Figure 5 The difference between the third embodiment of the utility model and the first embodiment is that: the first extension portion 11 is provided with a threaded hole 7, the second extension portion 21 is provided with a fixing hole 5 at a position corresponding to the threaded hole 7, the arm 3 is provided with a through hole 6 at a position corresponding to the fixing hole 5, and the fastening bolt 8 passes through the through hole 6 and the fixing hole 5 in sequence and is threadedly connected to the threaded hole 7. This design provides a stable connection by using the fastening bolt 8 between the first extension portion 11 and the second extension portion 21, and allows quick disassembly and assembly of the arm 3.

[0060] In summary, the shell structure of the drone provided by the utility model realizes a novel mechanical interlocking structure through the plug-in portion formed by the overlap of the first extension portion of the upper shell and the second extension portion of the bottom shell, thereby enhancing the stability and integrity of the drone shell. This design simplifies the assembly process, reduces the reliance on traditional fasteners, and thus reduces assembly costs and maintenance difficulties.

[0061] The above description is only an embodiment of the present invention, and does not limit the patent scope of the present invention. Any equivalent transformations made using the contents of the specification and drawings of the present invention, or directly or indirectly applied in the relevant technical field, are also included in the patent protection scope of the present invention.

Claims

1. A shell structure of a drone, characterized in that: It includes an upper shell, a bottom shell, an arm and a fastener, the upper shell is provided with a first extension part, the bottom shell is provided with a second extension part, after the upper shell is connected to the bottom shell, the first extension part and the second extension part overlap to form a plug-in part, the arm is provided with a plug-in hole and is sleeved on the plug-in part through the plug-in hole, and the arm, the first extension part and the second extension part are connected by the fastener.

2. The shell structure of the drone according to claim 1, characterized in that: The first extension portion and / or the second extension portion is provided with a guide protrusion, and the side wall of the plug hole is provided with a guide groove that is slidably matched with the guide protrusion.

3. The shell structure of the drone according to claim 1, characterized in that: The first extension portion and / or the second extension portion is provided with a guide groove, and the side wall of the plug hole is provided with a guide protrusion that slidably cooperates with the guide groove.

4. The shell structure of the drone according to claim 1, characterized in that: The first extension portion and / or the second extension portion is made of metal.

5. The shell structure of the drone according to claim 1, characterized in that: The fastener is a fastening bolt.

6. The shell structure of the drone according to claim 5, characterized in that: The plug-in portion is provided with a fixing hole, a through hole is provided at a position corresponding to the fixing hole on one side of the arm, and a threaded hole is provided at a position corresponding to the fixing hole on the other side of the arm, and the fastening bolt passes through the through hole and the fixing hole in sequence and is threadedly connected with the threaded hole.

7. The shell structure of the drone according to claim 6, characterized in that: There are multiple fixing holes, and the multiple fixing holes are evenly spaced and distributed along the plugging direction of the plug-in portion.

8. The shell structure of the drone according to claim 5, characterized in that: The first extension portion is provided with a fixing hole, the second extension portion is provided with a threaded hole at a position corresponding to the fixing hole, the arm is provided with a through hole at a position corresponding to the fixing hole, and the fastening bolt passes through the through hole and the fixing hole in sequence and is threadedly connected with the threaded hole.

9. The shell structure of the drone according to claim 5, characterized in that: The first extension portion is provided with a threaded hole, the second extension portion is provided with a fixing hole at a position corresponding to the threaded hole, the arm is provided with a through hole at a position corresponding to the fixing hole, and the fastening bolt passes through the through hole and the fixing hole in sequence and is threadedly connected with the threaded hole.

10. The shell structure of the drone according to any one of claims 6, 8 and 9, characterized in that: A threaded joint is provided in the threaded hole, and the threaded joint is threadedly connected to the fastening bolt.

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