A micro unmanned aerial vehicle body structure
Patent Information
- Application Number
- CN202522469051.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-21
- Publication Date
- 2026-10-20
- Estimated Expiration
- 2035-11-21
AI Technical Summary
[0003]在现有技术中，一些飞行器的部件连接方式不够稳固，抗冲击能力差，在跌落或碰撞时容易损坏，这种不紧密的结合在设备使用过程中，容易因震动等因素导致上壳松动，进一步降低整机的可靠性，缩短设备的使用寿命，给用户造成不必要的损失，因此，本技术领域人员提供一种微型无人机机身结构以解决上述背景技术中所提出的问题
本实用新型通过多个防护框架与第一、第二连接梁形成一体化防护框架，既减轻重量又提升结构强度，并且上盖主体采用凸起结构并通过固定柱与第一限位螺栓配合，保证了上盖主体与防护框架连接的稳定性，同时主板通过螺纹连接套与第二限位螺栓紧固在防护框架上，有效避免松动，提高了飞行稳定性与抗冲击性能。
Smart Images
Figure CN224868626U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a micro unmanned aerial vehicle (UAV) fuselage structure. Background Technology
[0002] Drone technology has become a key force driving change in many fields. Among them, micro drones have shown great application potential in many scenarios due to their unique advantages. Micro drones are characterized by small size, light weight, and strong concealment. Their small bodies can easily move through narrow spaces, so this method is highly playable for some drone operators.
[0003] In the prior art, the connection of some aircraft components is not stable enough and has poor impact resistance. They are easily damaged when dropped or collided. Such loose connection can easily cause the upper shell to loosen due to vibration and other factors during the use of the equipment, further reducing the reliability of the whole machine, shortening the service life of the equipment, and causing unnecessary losses to users. Therefore, those skilled in the art provide a micro unmanned aerial vehicle fuselage structure to solve the problems mentioned in the background art. Utility Model Content
[0004] The purpose of this invention is to provide a micro unmanned aerial vehicle (UAV) fuselage structure to solve the problems mentioned in the background art.
[0005] This utility model provides the following technical solution: a micro unmanned aerial vehicle (UAV) fuselage structure, including four protective frames located in four quadrants. The four protective frames are placed at equal intervals, and each protective frame has a connecting mechanism on its side that is close to each other, connecting to form a whole with a central accommodating space. A top cover mechanism is provided above the accommodating space, and a motherboard mechanism for placing electronic components is provided below the accommodating space.
[0006] Preferably, each of the protective frames has three support beams fixedly connected in a ring array on its inner sidewall. The three support beams are fixedly connected to a support plate at their ends away from the protective frame. The upper top of the support plate is fixedly connected to a drive motor connected to the propeller.
[0007] Preferably, the upper cover mechanism includes an upper cover body located directly above the four protective frames. Side plates are fixedly connected to both sides of the outer wall of the upper cover body, and two fixing columns are symmetrically fixedly connected to the bottom ends of the two side plates.
[0008] Preferably, the connecting mechanism includes a first connecting beam and a second connecting beam fixedly connected between every two protective frames, wherein the lower bottom end of the second connecting beam is fixedly connected to a lower threaded post, and the upper top end of each protective frame is fixedly connected to an upper threaded post.
[0009] Preferably, the four fixing posts correspond to the upper threaded posts at the top of the four protective frames, and the fixing posts are threadedly connected to the upper threaded posts with first limiting bolts.
[0010] Preferably, the motherboard mechanism includes a motherboard body located in the accommodating space, and threaded connecting sleeves are fixedly connected to the four corners of the upper top of the motherboard body. The four threaded connecting sleeves correspond to the lower threaded posts, and the lower threaded posts are inserted into the inside of the threaded connecting sleeves.
[0011] Compared with the prior art, the beneficial effects of this utility model are: This utility model forms an integrated protective frame by combining multiple protective frames with the first and second connecting beams, which reduces weight and increases structural strength. The main body of the upper cover adopts a raised structure and is connected to the first limiting bolt through a fixing column, which ensures the stability of the connection between the main body of the upper cover and the protective frame. At the same time, the main board is fastened to the protective frame through a threaded connecting sleeve and the second limiting bolt, which effectively prevents loosening and improves flight stability and impact resistance. Attached Figure Description
[0012] Figure 1 This is a schematic diagram of the overall structure of a micro unmanned aerial vehicle (UAV). Figure 2 This is a schematic diagram of the protective frame and the main board body in the fuselage structure of a micro unmanned aerial vehicle. Figure 3 This is a schematic diagram of the bottom of the upper cover body in the fuselage structure of a micro unmanned aerial vehicle.
[0013] In the diagram: 1. Protective frame; 11. Support beam; 12. Drive motor; 13. Support plate; 2. Upper cover mechanism; 21. First limit bolt; 22. Second limit bolt; 23. Upper cover body; 24. Side plate; 25. Fixing column; 3. Main board mechanism; 31. Main board body; 32. Threaded connecting sleeve; 4. Connecting mechanism; 41. First connecting beam; 42. Second connecting beam; 43. Lower threaded column; 44. Upper threaded column. Detailed Implementation
[0014] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention.
[0015] Please see Figures 1-3As shown, this utility model provides a technical solution: a micro unmanned aerial vehicle (UAV) fuselage structure, including four protective frames 1 located in four quadrants. The four protective frames 1 are placed at equal intervals. Each protective frame 1 has a connecting mechanism 4 on its side that is close to each other, forming an integral whole with a central accommodating space. A top cover mechanism 2 is provided above the accommodating space, and a motherboard mechanism 3 for placing electronic components is provided below the protective frames 1.
[0016] It should be noted that the four protective frames 1 are located in the four quadrants and are placed at equal intervals, forming a stable basic structure for the fuselage. This effectively disperses the impact force received during flight, greatly enhances the fuselage's collision resistance, reduces the risk of fuselage damage due to collisions, and improves the drone's survivability in complex environments. The connecting mechanism 4 tightly connects the four protective frames 1 into a single unit, enhancing the integrity and stability of the fuselage structure, reducing vibration and swaying during flight, improving flight stability, and ensuring that the drone can accurately execute various flight missions. The top cover mechanism 2 is installed above the protective frames 1, effectively protecting the internal structure from external factors such as dust and rain, and extending the drone's service life. The motherboard mechanism 3 is located below the protective frames 1, providing a stable and safe placement space for electronic components, reducing the impact of external interference on electronic components, and ensuring the normal operation of the drone's electronic system.
[0017] As one implementation method in this embodiment, please refer to Figure 1 and Figure 2 As shown, three support beams 11 are fixedly connected to the inner sidewall of each protective frame 1 in a ring array. The three support beams 11 are fixedly connected to a support plate 13 at the ends away from the protective frame 1. A drive motor 12 connected to the propeller is fixedly connected to the top of the support plate 13. The drive motor 12 and the support plate 13 are located at the center of the protective frame 1. The propeller used for flight is fixedly connected to the output end of the drive motor 12 through a transmission shaft.
[0018] It should be noted that three support beams 11 are fixed in a ring array on the inner sidewall of each protective frame 1. This layout ensures a uniform distribution of the support structure, effectively dispersing the vibration and stress generated by the propeller during flight, greatly enhancing the stability of the fuselage structure, reducing component loosening or damage caused by vibration, and extending the service life of the UAV. The three support beams 11 together fix the support plate 13, providing a stable mounting platform for the drive motor 12. The drive motor 12 is fixedly connected to the top of the support plate 13, and both are located at the center of the protective frame 1, ensuring uniform force distribution on the drive motor 12 during operation. The upper cover mechanism 2 includes an upper cover body 23 located directly above the four protective frames 1. Side plates 24 are fixedly connected to both sides of the outer wall of the upper cover body 23, and two fixing posts 25 are symmetrically fixed to the bottom ends of the two side plates 24. The main body 23 of the top cover is precisely positioned above the four protective frames 1, effectively preventing external dust, rain, debris, and other contaminants from entering the drone's interior. This provides reliable protection for the internal electronic components and critical structures, significantly reducing the risk of malfunctions caused by external factors. The four fixed posts 25, symmetrically fixed at the bottom of the two side plates 24, play a crucial role in ensuring a stable connection. They can work closely with the protective frames 1 to firmly fix the top cover mechanism 2 to the fuselage, preventing the top cover from loosening or falling off during flight and ensuring the integrity of the drone's structure and the safety of its flight.
[0019] As one implementation method in this embodiment, please refer to Figure 1 and Figure 2 As shown, the connecting mechanism 4 includes a first connecting beam 41 and a second connecting beam 42 fixedly connected between every two protective frames 1. The second connecting beam 42 is close to the intersection of the four protective frames 1. The bottom end of each second connecting beam 42 is fixedly connected to a lower threaded post 43, and the top end of each protective frame 1 is fixedly connected to an upper threaded post 44. The four fixed posts 25 correspond to the upper threaded posts 44 at the top ends of the four protective frames 1. After the fixed posts 25 correspond to the upper threaded posts 44, a first limiting bolt 21 is threadedly connected to them. The first limiting bolt 21 is located at the top end of the side plate 24.
[0020] It should be noted that the first connecting beam 41 and the second connecting beam 42 fixed between every two protective frames 1 form a stable connection structure. The second connecting beam 42 is close to the intersection of the four protective frames 1, which can effectively disperse the stress generated during flight, allowing the four protective frames 1 to be tightly connected into a whole, which greatly enhances the integrity and stability of the fuselage structure, effectively resists the impact of external forces during flight, reduces the risk of fuselage deformation, and ensures flight safety. The threaded post 44 at the top of the protective frame 1 corresponds to the fixing post 25 of the upper cover mechanism 2. The upper cover mechanism 2 can be accurately and firmly installed on the protective frame 1 through the threaded connection of the first limiting bolt 21. The first limiting bolt 21 is located at the top of the side plate 24, which is convenient for operators to install and disassemble, improving assembly efficiency and maintenance convenience.
[0021] As one implementation method in this embodiment, please refer to Figure 1 and Figure 2 As shown, the main board mechanism 3 includes a main board body 31 located in the accommodating space. Threaded connecting sleeves 32 are fixedly connected to the four corners of the top of the main board body 31. The four threaded connecting sleeves 32 correspond to the lower threaded posts 43. The lower threaded posts 43 are inserted into the inside of the threaded connecting sleeves 32. A protective frame 1 with four second limiting bolts 22 is provided at the bottom of the main board body 31. The threaded connecting sleeves 32 and the lower threaded posts 43 are corresponding and then limited by the second limiting bolts 22.
[0022] It should be noted that the threaded connecting sleeves 32 at the top four corners of the main board body 31 correspond to the lower threaded posts 43 in the connecting mechanism 4. The lower threaded posts 43 are inserted into the threaded connecting sleeves 32, which makes the installation and positioning of the main board body 31 accurate and stable. This can effectively prevent the main board from shifting due to shaking or vibration during flight, ensure the stability of the electronic component connection, reduce failures caused by poor contact, and improve the reliability of the UAV operation. The second limiting bolt 22 limits the threaded connecting sleeves 32 and the lower threaded posts 43, further enhancing the fixing effect of the main board body 31 and making the connection between the main board and the fuselage structure more firm and reliable.
[0023] Working principle: Four protective frames 1 located in the four quadrants and placed at equal intervals, together with the first connecting beam 41 fixedly connected between every two protective frames 1 and the second connecting beam 42 near the intersection of the four protective frames 1, form an integrated protective frame. While reducing the weight of the fuselage, the overall structural strength is improved through a reasonable structural layout, which can effectively resist the impact of external forces during flight and provide reliable protection for internal components. In the upper cover mechanism 2, the upper cover body 23, located directly above the four protective frames 1 and with side plates 24 on both sides of the outer wall, has four fixed posts 25 symmetrically fixed to the lower bottom side plates 24. After corresponding to the upper threaded posts 44 at the top of the protective frames 1, they are connected by the first limiting bolt 21 located at the top of the side plates 24. The protruding structure that the upper cover body 23 can adopt further enhances the structural stability. In addition, the arc design of the outer wall of the upper cover body 23 can effectively reduce wind resistance and avoid the wind affecting the flight during flight. In the main board mechanism 3, the main board body 31 located at the intersection of the four protective frames 1 has threaded connecting sleeves 32 at the four corners of its top end that are inserted into the lower threaded post 43 at the bottom of the second connecting beam 42. The main board body 31 is then limited by four second limiting bolts 22 set at the bottom of the protective frame 1, so that the main board is fastened to the protective frame 1, effectively preventing loosening, thereby improving the stability and impact resistance of the UAV flight. In addition, three support beams 11 fixed in a ring array on the inner sidewall of each protective frame 1 are connected to a support plate 13. The drive motor 12, which is connected to the propeller and fixed at the top of the support plate 13, is located at the center of the protective frame 1. The propeller is fixedly connected to the output end of the drive motor 12 through a transmission shaft to provide power for the drone flight.
[0024] The above embodiments are only used to illustrate the technical solution of this utility model, and are not intended to limit it.
Claims
1. A micro unmanned aerial vehicle (UAV) fuselage structure, comprising four protective frames located in four quadrants (1), characterized in that: The four protective frames (1) are placed at equal intervals. Each of the protective frames (1) is provided with a connecting mechanism (4) on the side that is close to each other, and they are connected to form a whole with a central accommodating space. A cover mechanism (2) is provided above the accommodating space, and a motherboard mechanism (3) for placing electronic components is provided below the accommodating space.
2. The fuselage structure of a micro unmanned aerial vehicle according to claim 1, characterized in that: Each of the protective frames (1) has three support beams (11) fixedly connected to the inner sidewall of the ring array. The three support beams (11) are fixedly connected to a support plate (13) at the end away from the protective frame (1). The upper top of the support plate (13) is fixedly connected to a drive motor (12) connected to the propeller.
3. The fuselage structure of a micro unmanned aerial vehicle according to claim 1, characterized in that: The upper cover mechanism (2) includes an upper cover body (23) located directly above the four protective frames (1). Side plates (24) are fixedly connected to both sides of the outer wall of the upper cover body (23), and two fixed columns (25) are symmetrically fixedly connected to the bottom ends of the two side plates (24).
4. The fuselage structure of a micro unmanned aerial vehicle according to claim 3, characterized in that: The connecting mechanism (4) includes a first connecting beam (41) and a second connecting beam (42) fixedly connected between each pair of protective frames (1). The bottom end of the second connecting beam (42) is fixedly connected with a lower threaded post (43), and the top end of each protective frame (1) is fixedly connected with an upper threaded post (44).
5. The fuselage structure of a micro unmanned aerial vehicle according to claim 4, characterized in that: The four fixed posts (25) correspond to the upper threaded posts (44) at the top of the four protective frames (1), and the fixed posts (25) are threadedly connected to the upper threaded posts (44) with the first limiting bolt (21).
6. The fuselage structure of a micro unmanned aerial vehicle according to claim 5, characterized in that: The main board mechanism (3) includes a main board body (31) located in the accommodating space. Threaded connecting sleeves (32) are fixedly connected to the four corners of the top end of the main board body (31). The four threaded connecting sleeves (32) correspond to the lower threaded posts (43), and the lower threaded posts (43) are inserted into the inside of the threaded connecting sleeves (32).