Vertical take-off and landing fixed-wing unmanned aerial vehicle convenient to disassemble and assemble

Abstract

The utility model discloses a vertical take-off and landing fixed-wing unmanned aerial vehicle convenient to disassemble and assemble, and relates to the technical field of unmanned aerial vehicles, the vertical take-off and landing fixed-wing unmanned aerial vehicle comprises an unmanned aerial vehicle body and a wire, four corners of the unmanned aerial vehicle body are fixedly provided with fixing seats, and the outer sides of the fixing seats are fixedly provided with clamping mechanisms; a wing shell is installed on the outer side of the fixing base through a clamping mechanism. By the adoption of the structure, the rotor wing and the wing shell of the unmanned aerial vehicle can be rapidly disassembled and assembled through the clamping mechanism with the unique design, during use, the sliding block and the limiting shaft are matched with the outer rail and the limiting hole, stable installation of the wing shell is guaranteed, and when maintenance is needed, only the push plate needs to be pushed to release the limiting shaft, and the rotor wing and the wing shell can be rapidly disassembled and assembled. By means of the design, the disassembly and assembly convenience of the rotor wing and the wing shell of the unmanned aerial vehicle is greatly improved, the overhaul and maintenance efficiency of the unmanned aerial vehicle is effectively improved, and the overall maintenance of the unmanned aerial vehicle body is more convenient and efficient.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a vertical take-off and landing fixed-wing unmanned aerial vehicle which is easy to disassemble and assemble. Background Art

[0002] A vertical take-off and landing UAV is a new type of UAV that combines the features of a rotary-wing UAV and a fixed-wing UAV. This type of UAV can take off and land vertically in an environment without a runway or with a short runway, while also having the advantages of high-speed cruising and long range of fixed-wing UAVs. The design principle of a vertical take-off and landing UAV mainly relies on its unique flight control system and power structure. Usually, this type of UAV is equipped with an electric rotor or a tilt-rotor mechanism, which generates an upward airflow by adjusting the pitch rate or tilt angle of the rotor, thereby supporting the vertical take-off and landing of the UAV. During the vertical take-off and landing stage, the UAV's rotor or tilt-rotor will generate sufficient lift to overcome the gravity of the UAV, allowing it to fly vertically. Ascending or descending, once the drone reaches a certain height and speed, the flight control system will adjust the angle of the rotor or tilt-rotor to put it into horizontal flight mode. In the horizontal flight stage, the fixed wing of the drone will provide the main lift and stability, while the rotor or tilt-rotor will be transformed into a propulsion device. By adjusting the thrust and direction, the speed and direction of the drone can be controlled. The advantage of vertical take-off and landing drones lies in their flexibility and adaptability. They can operate in various complex terrains and environments without relying on special runways and take-off and landing facilities. In addition, because it combines the advantages of rotary-wing drones and fixed-wing drones, vertical take-off and landing drones also perform well in terms of range, speed, and load capacity.

[0003] A Chinese patent with announcement number "CN206954505U" discloses a tethered cruise multi-mode vertical take-off and landing UAV, which includes a fixed-wing fuselage, wings, tail wings, horizontal propeller power system, vertical propeller motor system, bracket, rotor fuselage, cables and payload components. The design features of the utility model are: according to different mission requirements, the structure of the aircraft can be changed in a short time by disassembling and assembling parts, and the mode suitable for performing the mission requirements can be selected. When used as a tethered UAV mode, it has the characteristics of strong maneuverability and long hovering time; when used as a cruise vertical take-off and landing UAV mode, it has the characteristics of efficient cruise flight, can hover above the target area and can take off and land vertically in a small space. When not in use, the main components can be disassembled and placed to save storage space;

[0004] Although the above-mentioned device has the characteristics of being able to hover above the target area and take off and land vertically in a small space during use, in its specific application process, the drone wing and the drone are designed as an integrated whole. In its specific use process, when the drone wing is damaged, it is not convenient to disassemble and assemble the whole during carrying, which will cause inconvenience in carrying. At the same time, it is obvious that the overall disassembly, assembly, inspection and maintenance are also cumbersome and inconvenient. It can be seen that its overall use has certain defects and shortcomings, and it needs to be improved. Utility Model Content

[0005] In view of the problems mentioned in the background technology, the purpose of the present invention is to provide a vertical take-off and landing fixed-wing UAV that is easy to disassemble and assemble, so as to solve the problems raised by the background technology.

[0006] The above technical objectives of the utility model are achieved through the following technical solutions:

[0007] A vertical take-off and landing fixed-wing drone that is easy to disassemble and assemble, comprising a drone body and a wire, characterized in that: a fixing seat is fixedly installed at each of the four corners of the drone body, a clamping mechanism is fixedly installed on the outer side of the fixing seat, a wing shell is installed on the outer side of the fixing seat through the clamping mechanism, a drone rotor is movably installed in the middle of the wing shell, a buffer mechanism is fixedly installed at the bottom of the wing shell, plugs are fixedly connected at both ends of the wire, a socket is fixedly connected at the top of the fixing seat and the inner side of the top of the wing shell, the plug is plugged into the inner side of the socket, the wing shell is connected to the drone body through the wire, and drone cameras are fixedly installed at equal intervals at the bottom of the drone body;

[0008] The clamping mechanism includes a mounting frame and an outer rail, the outer rail is fixedly mounted on the inner side of the wing shell, the mounting frame is fixedly mounted on the outer side of the fixing seat, a limit spring is fixedly mounted inside the mounting frame, a limit plate is fixedly mounted on the end of the limit spring, a limit shaft is fixedly mounted on the outer end of the limit plate, a slider is fixedly mounted on the outer end of the mounting frame, the slider is slidably connected to the inner side of the outer rail, the outer end of the limit shaft passes through the mounting frame and the slider, a limit hole is opened in the middle part of the outer rail, and the outer end of the limit shaft is inserted into the inside of the limit hole.

[0009] As a preferred technical solution, the buffer mechanism includes a threaded sleeve, which is fixedly installed at the bottom inner end of the wing shell, the bottom of the threaded sleeve is threadedly connected with a threaded joint, and the bottom of the threaded joint is fixedly installed with a buffer assembly.

[0010] As a preferred technical solution, the overall cross-sectional shape of the outer rail is arranged in a convex shape, and the overall cross-sectional shape of the slider is also arranged in a convex shape.

[0011] As a preferred technical solution, an adjustment frame is fixedly installed at the bottom of the limit plate, the side surface of the adjustment frame is in a concave shape, and a push plate is fixedly installed in the middle of the bottom of the adjustment frame.

[0012] As an optimal technical solution, the buffer assembly includes a support rod, which is fixedly installed at the bottom of the threaded joint. A base frame is fixedly installed at the bottom of the support rod, and buffer springs are fixedly connected at both ends of the base frame. The ends of the buffer springs pass through the base frame and are fixedly connected to a buffer bottom plate.

[0013] As a preferred technical solution, support shafts are fixedly installed on both sides of the top of the buffer bottom plate, and the ends of the support shafts pass through the base frame.

[0014] As a preferred technical solution, an adjusting button handle is fixedly connected to the outer surface of the threaded joint, and anti-slip protrusions are fixedly connected to the outer surface of the adjusting button handle at equal intervals.

[0015] In summary, the utility model mainly has the following beneficial effects:

[0016] First, the device realizes the rapid disassembly and assembly of the UAV rotor and wing shell by designing a unique clamping mechanism. When in use, the slider and the limit shaft cooperate with the outer rail and the limit hole to ensure the stable installation of the wing shell. When maintenance is required, the wing shell and the rotor can be easily removed by simply pushing the push plate to release the limit shaft. This design greatly improves the convenience of disassembly and assembly of the UAV rotor and wing shell, effectively improves the efficiency of UAV maintenance, and makes the overall maintenance of the UAV body more convenient and efficient;

[0017] Second, this device effectively improves the protection performance of the UAV during take-off and landing by setting up a buffer mechanism. When the UAV lands, the buffer bottom plate contacts the ground and reduces shock through the action of the buffer spring to protect the UAV body. In addition, the buffer mechanism is connected to the threaded sleeve through a threaded joint, which is convenient for disassembly and maintenance when necessary. This design not only enhances the buffer protection capability of the UAV, but also allows the UAV to reduce its volume by removing the wing shell when it is carried, making it easier to carry and use. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0019] Figure 2 It is a schematic diagram of the structure of the utility model when viewed from above;

[0020] Figure 3 It is a schematic diagram of the overall structure of the clamping mechanism and the buffer mechanism of the utility model;

[0021] Figure 4 It is a schematic diagram of the structure of the clamping mechanism and the buffer mechanism of the utility model when viewed from above.

[0022] Figure numerals: 1. UAV body; 2. wire; 3. fixing seat; 4. wing shell; 5. clamping mechanism; 51. mounting frame; 52. outer rail; 53. limit spring; 54. limit plate; 55. limit shaft; 56. slider; 57. adjustment frame; 58. push plate; 59. limit hole; 6. UAV rotor; 7. buffer mechanism; 71. threaded sleeve; 72. threaded joint; 73. buffer assembly; 731. support rod; 732. base frame; 733. buffer spring; 734. buffer bottom plate; 735. support shaft; 736. adjustment knob handle; 8. plug; 9. socket; 10. UAV camera. DETAILED DESCRIPTION

[0023] Example

[0024] refer to Figures 1 to 4 , a vertical take-off and landing fixed-wing UAV that is easy to disassemble and assemble in this embodiment includes a UAV body 1 and a wire 2, a fixing seat 3 is fixedly installed at the four corners of the UAV body 1, a clamping mechanism 5 is fixedly installed on the outer side of the fixing seat 3, a wing shell 4 is installed on the outer side of the fixing seat 3 through the clamping mechanism 5, a UAV rotor 6 is movably installed in the middle of the wing shell 4, a buffer mechanism 7 is fixedly installed at the bottom of the wing shell 4, plugs 8 are fixedly connected at both ends of the wire 2, a socket 9 is fixedly connected at the top of the fixing seat 3 and the inner side of the top of the wing shell 4, the plug 8 is plugged into the inner side of the socket 9, the wing shell 4 is connected to the UAV body 1 through the wire 2, and UAV cameras 10 are fixedly installed at equal intervals at the bottom of the UAV body 1;

[0025] The clamping mechanism 5 includes a mounting frame 51 and an outer rail 52. The outer rail 52 is fixedly mounted on the inner side of the wing shell 4. The mounting frame 51 is fixedly mounted on the outer side of the fixing seat 3. A limit spring 53 is fixedly mounted inside the mounting frame 51. A limit plate 54 is fixedly mounted on the end of the limit spring 53. A limit shaft 55 is fixedly mounted on the outer end of the limit plate 54. A slider 56 is fixedly mounted on the outer end of the mounting frame 51. The slider 56 is slidably connected to the inner side of the outer rail 52. The outer end of the limit shaft 55 passes through the mounting frame 51 and the slider 56. A limiting hole 59 is provided in the middle of the outer rail 52, and the outer end of the limiting shaft 55 is inserted into the limiting hole 59. The four corners of the drone body 1 are equipped with fixing seats 3, which are tightly connected to the wing shell 4 through an innovative clamping mechanism 5. The core of the clamping mechanism 5 is composed of a mounting frame 51 and an outer rail 52. The mounting frame 51 is fixed to the outside of the fixing seat 3, and the outer rail 52 is installed on the inside of the wing shell 4. A limiting spring 53 and a limiting plate 54 are installed inside the mounting frame 51. The limiting plate 54 is connected to the limiting shaft 5 5 is connected to the slider 56, and the slider 56 can slide freely along the inner side of the outer rail 52. When the slider 56 completely slides into the outer rail 52, the elastic force of the limit spring 53 will push the limit shaft 55 to insert into the limit hole 59 in the middle of the outer rail 52, thereby firmly locking the wing shell 4. This design not only simplifies the installation and disassembly process of the wing shell 4, but also improves the stability of the UAV during flight. The UAV rotor 6 is movably installed inside the wing shell 4 to provide the UAV with the power required for vertical take-off and landing and flight. At the same time, a buffer mechanism 7 is installed at the bottom of the wing shell 4, which can effectively reduce the impact on the UAV during landing and protect the UAV from damage. In order to achieve electrical signal conduction between the wing shell 4 and the UAV body 1, plugs 8 are provided at both ends of the wire 2, which can be easily inserted into the sockets 9 on the top of the fixing seat 3 and the inner side of the top of the wing shell 4. In addition, a fixing seat 3 is also fixedly installed at the bottom of the UAV body 1, and UAV cameras 10 are evenly distributed on it to provide the UAV with all-round visual perception capabilities.

[0026] refer to Figure 4The buffer mechanism 7 includes a threaded sleeve 71, which is fixedly installed at the bottom inner end of the wing shell 4. The bottom of the threaded sleeve 71 is threadedly connected with a threaded joint 72, and the bottom of the threaded joint 72 is fixedly installed with a buffer component 73. The buffer mechanism 7 is an important component thereof, which is intended to reduce the impact on the drone during take-off and landing to protect the fuselage. This mechanism mainly includes a threaded sleeve 71, a threaded joint 72 and a buffer component 73. The threaded sleeve 71 is firmly installed at the bottom inner end of the wing shell 4 to provide stable support for the entire buffer mechanism 7. The bottom of the threaded sleeve 71 is tightly combined with the threaded joint 72 through a threaded connection. This design allows the user to adjust the position of the threaded joint 72 as needed, thereby optimizing the buffer effect. The bottom of the threaded joint 72 is fixedly installed with a buffer component 73, which can effectively absorb and disperse the impact force when the drone takes off and lands, and protect the drone from damage. This buffer mechanism 7 is not only compact in structure, but also powerful in function. It is a key component to ensure the safe take-off and landing of the drone.

[0027] refer to Figure 3-Figure 4 The overall cross-sectional shape of the outer rail 52 is convex, and the overall cross-sectional shape of the slider 56 is also convex. The overall cross-sectional shape of the outer rail 52 is convex, and the overall cross-sectional shape of the slider 56 is also convex accordingly. This design allows the slider 56 to slide smoothly inside the outer rail 52 while maintaining a stable connection state. When the slider 56 completely slides into the outer rail 52, the limit spring 53 causes the limit shaft 55 to be inserted into the limit hole 59 in the middle of the outer rail 52, thereby achieving a firm locking of the wing shell 4. This convex cross-sectional design not only increases the stability of the connection, but also makes the disassembly and assembly process simpler and faster, thereby improving the maintainability and ease of use of the UAV.

[0028] refer to Figure 4 , an adjusting frame 57 is fixedly installed at the bottom of the limit plate 54, and the side shape of the adjusting frame 57 is concave, and a push plate 58 is fixedly installed in the middle of the bottom of the adjusting frame 57. The side shape of the adjusting frame 57 is concave, so that the user can easily operate it with his hands or tools. In the middle of the bottom of the adjusting frame 57, a push plate 58 is fixedly installed. The user can operate the adjusting frame 57 by pushing the push plate 58, and then adjust the position of the limit plate 54. When the wing shell 4 needs to be removed, the user only needs to simply push the push plate 58, and the adjusting frame 57 will drive the limit plate 54 to slide downward, so that the limit shaft 55 withdraws from the limit hole 59. Once the limit shaft 55 is out of the limit hole 59, the wing shell 4 can be easily removed from the drone body 1, which greatly improves the convenience and efficiency of disassembly. This design not only facilitates users to maintain and replace parts, but also ensures the safety and stability of the drone during flight.

[0029] refer to Figure 4 The buffer assembly 73 includes a support rod 731, which is fixedly installed at the bottom of the threaded joint 72. A base frame 732 is fixedly installed at the bottom of the support rod 731. Both ends of the base frame 732 are fixedly connected with buffer springs 733. The ends of the buffer springs 733 pass through the base frame 732 and are fixedly connected with a buffer bottom plate 734. The support rod 731 is the basic part of the buffer assembly 73. It is fixedly installed at the bottom of the threaded joint 72 and serves as a bridge connecting the threaded joint 72 and the base frame 732. The stability and strength of the support rod 731 are crucial to the overall performance of the buffer assembly 73. Next, the base frame 732 is fixedly installed at the bottom of the support rod 731. Its function is to provide a buffer The spring 733 provides installation space and connects the support rod 731 and the buffer base plate 734. The buffer springs 733 are fixedly connected at both ends of the base frame 732. These springs are the core part of the buffer assembly 73. They can absorb and disperse the impact force when the UAV takes off and lands. Finally, the end of the buffer spring 733 passes through the base frame 732 and is fixedly connected to the buffer base plate 734. The buffer base plate 734 directly contacts the ground or the landing platform and bears the impact force from the ground. When the UAV takes off and lands, the buffer base plate 734 will be impacted by the ground, but due to the presence of the buffer spring 733, these impact forces will be absorbed and dispersed, thereby reducing the direct effect on the UAV body.

[0030] refer to Figure 4 A support shaft 735 is fixedly installed on both sides of the top of the buffer bottom plate 734, and the end of the support shaft 735 passes through the base frame 732. By setting the support shaft 735, the buffer spring 733 can be supported and reinforced, thereby improving the overall stability of the device.

[0031] refer to Figure 4 The outer surface of the threaded joint 72 is fixedly connected with an adjusting knob handle 736, and the outer surface of the adjusting knob handle 736 is fixedly connected with anti-skid protrusions at equal intervals. The adjusting knob handle 736 is provided, and the threaded structure can be adjusted by twisting the adjusting knob handle 736 during use, which is convenient for quick and flexible adjustment. The anti-skid protrusions can increase the friction force of the outer surface of the adjusting knob handle 736, which can improve the overall adjustment convenience of the device.

[0032] Principle and advantages of use: By setting the card-mounting mechanism 5, the device can be used to slide the slider 56 into the inner side of the socket 9. At this time, the limit spring 53 can be reset to resist the pressure, which can prompt the limit spring 53 to drive the limit shaft 55 to insert into the inner side of the limit hole 59. The limit hole 59 and the limit shaft 55 limit each other, which can assist in the card-mounting installation of the slider 56 on the inner side of the outer rail 52. The slider 56 and the outer rail 52 are installed in a mutually embedded manner, which can assist in the stable installation of the wing shell 4 of the drone body 1. If the wing shell 4 and the drone rotor need to be adjusted, When inspecting and maintaining 6, the push plate 58 can be pushed to drive the adjustment frame 57 to pull the limit plate 54 to drive the limit shaft 55 to be pulled out of the limit hole 59, and the limit shaft 55 and the slider 56 can be separated from each other, so that the slider 56 can be pulled out from the inner side of the outer rail 52. At this time, the plug 8 and the socket 9 on the wire 2 can be separated from each other, and the UAV rotor 6 can be removed, so that the device as a whole can quickly replace and disassemble the UAV rotor 6, which can improve the convenience of disassembling and assembling the wing shell 4 and the UAV rotor 6 of the device as a whole, and can improve the efficiency of disassembling and overhauling the UAV body 1 of the device as a whole;

[0033] By setting up the buffer mechanism 7, when the drone body 1 falls from the air to the ground during use, the buffer bottom plate 734 contacts the bottom plate, and the vibration force of the buffer bottom plate 734 can be assisted by the buffer spring 733 to perform buffering and shock absorption, so that the drone body 1 can perform buffering and shock absorption when falling to the ground, so that the drone body 1 can have better protection performance during the take-off and landing process, and when it needs to be repaired and maintained, the adjustment button handle 736 on the outside of the threaded joint 72 can be twisted to remove the buffer mechanism 7 from the inside of the threaded sleeve 71 by twisting the threaded joint 72. It can be seen that the present device not only has better buffering and protective performance, but also its overall disassembly, assembly, inspection and maintenance are more convenient, so that the wing shell 4 can be removed while the drone body 1 is being carried, and the whole is easy to carry and use.

Claims

1. A vertical take-off and landing fixed-wing UAV that is easy to assemble and disassemble, comprising a UAV body (1) and a wire (2), characterized in that: A fixing seat (3) is fixedly installed at each of the four corners of the drone body (1); a clamping mechanism (5) is fixedly installed on the outer side of the fixing seat (3); a wing shell (4) is installed on the outer side of the fixing seat (3) through the clamping mechanism (5); a drone rotor (6) is movably installed in the middle of the wing shell (4); a buffer mechanism (7) is fixedly installed at the bottom of the wing shell (4); plugs (8) are fixedly connected to both ends of the wire (2); a socket (9) is fixedly connected to the top of the fixing seat (3) and the inner side of the top of the wing shell (4); the plug (8) is plugged into the inner side of the socket (9); the wing shell (4) is connected to the drone body (1) through the wire (2); and drone cameras (10) are fixedly installed at equal intervals at the bottom of the drone body (1); The clamping mechanism (5) comprises a mounting frame (51) and an outer rail (52), wherein the outer rail (52) is fixedly mounted on the inner side of the wing shell (4), and the mounting frame (51) is fixedly mounted on the outer side of the fixing seat (3). A limit spring (53) is fixedly mounted inside the mounting frame (51), a limit plate (54) is fixedly mounted on the end of the limit spring (53), a limit shaft (55) is fixedly mounted on the outer end of the limit plate (54), a slider (56) is fixedly mounted on the outer end of the mounting frame (51), the slider (56) is slidably connected to the inner side of the outer rail (52), the outer end of the limit shaft (55) passes through the mounting frame (51) and the slider (56), a limit hole (59) is provided in the middle of the inner side of the outer rail (52), and the outer end of the limit shaft (55) is inserted into the inner side of the limit hole (59).

2. The vertical take-off and landing fixed-wing UAV that is easy to assemble and disassemble according to claim 1, characterized in that: The buffer mechanism (7) comprises a threaded sleeve (71), the threaded sleeve (71) is fixedly mounted on the bottom inner end of the wing shell (4), the bottom of the threaded sleeve (71) is threadedly connected to a threaded joint (72), and the bottom of the threaded joint (72) is fixedly mounted with a buffer assembly (73).

3. The detachable fixed-wing UAV according to claim 2, characterized in that: The overall cross-sectional shape of the outer rail (52) is arranged in a convex shape, and the overall cross-sectional shape of the slider (56) is also arranged in a convex shape.

4. The detachable fixed-wing UAV according to claim 2, characterized in that: An adjustment frame (57) is fixedly mounted on the bottom of the limiting plate (54), the side surface of the adjustment frame (57) is in a concave shape, and a push plate (58) is fixedly mounted in the middle of the bottom of the adjustment frame (57).

5. The detachable fixed-wing UAV according to claim 4, characterized in that: The buffer assembly (73) comprises a support rod (731), wherein the support rod (731) is fixedly mounted on the bottom of the threaded joint (72), a base frame (732) is fixedly mounted on the bottom of the support rod (731), both ends of the base frame (732) are fixedly connected with a buffer spring (733), and the end of the buffer spring (733) passes through the base frame (732) and is fixedly connected with a buffer bottom plate (734).

6. The detachable fixed-wing UAV according to claim 5, characterized in that: Support shafts (735) are fixedly mounted on both sides of the top of the buffer bottom plate (734), and the ends of the support shafts (735) pass through the base frame (732).

7. The detachable fixed-wing UAV according to claim 5, characterized in that: An adjusting button handle (736) is fixedly connected to the outer surface of the threaded joint (72), and anti-slip protrusions are fixedly connected to the outer surface of the adjusting button handle (736) at equal intervals.

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